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WO2025184546A1 - Système de mesure et de marquage pour une turbomachine et procédé associé - Google Patents

Système de mesure et de marquage pour une turbomachine et procédé associé

Info

Publication number
WO2025184546A1
WO2025184546A1 PCT/US2025/017905 US2025017905W WO2025184546A1 WO 2025184546 A1 WO2025184546 A1 WO 2025184546A1 US 2025017905 W US2025017905 W US 2025017905W WO 2025184546 A1 WO2025184546 A1 WO 2025184546A1
Authority
WO
WIPO (PCT)
Prior art keywords
measuring
abradable liner
arm portion
marking
measuring device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
PCT/US2025/017905
Other languages
English (en)
Inventor
Subramanya SHANKAR
Edeth Stephens CAMP
Joshua B. JAMISON
Nicholas J. Kray
Prakash PARAMASIVAM
German PULIDO PEÑA
Marc CHRISTOPFEL
Raul BALDERAS
Juan Hernan MARTÍNEZ COLCHADO
Ryan CALHOUN
Ndeye Fatou Diop
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of WO2025184546A1 publication Critical patent/WO2025184546A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/14—Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures

Definitions

  • the present disclosure relates generally to a measuring and marking system for a turbine engine, and a related method.
  • Turbine engines for example, for aircraft, generally include a fan and a turboengine arranged in flow communication with one another.
  • the fan is generally encased in a nacelle.
  • the inner surface of the nacelle includes an abradable liner and close clearance to tips of the fan.
  • the abradable liner may be reworked as a course of regular maintenance.
  • FIG. 1 is a schematic, cross-sectional diagram of a turbine engine, taken along a longitudinal centerline axis of the turbine engine, according to the present disclosure.
  • FIG. 2 is a partial, schematic diagram of a portion of the turbine engine of FIG. 1, taken at detail 2 in FIG. 1, showing an abradable liner and a fan tip-liner clearance, according to the present disclosure.
  • FIG. 3B is an enlarged, schematic, side view of a portion of the measuring apparatus, taken at detail 3B of FIG. 3 A, according to the present disclosure.
  • FIG. 4A is a schematic side view of the measuring apparatus mounted to a fan disk of the turbine engine, taken along the longitudinal centerline axis of the turbine engine, and with fan blades of the fan removed, according to the present disclosure.
  • FIG. 4B is a perspective side view of the measuring apparatus mounted to the fan disk of the turbine engine, taken along the longitudinal centerline axis of the turbine engine, according to the present disclosure.
  • FIG. 4C is a schematic, front elevational view of the measuring apparatus mounted to a fan disk of a turbine engine, viewed along the longitudinal centerline axis of the turbine engine, according to the present disclosure.
  • FIG. 5B is an enlarged, schematic view of the portion of the measuring apparatus, taken at detail 5B of FIG. 5 A, according to the present disclosure.
  • FIG. 5C is a schematic, cross-sectional view of the portion of the measuring apparatus, showing a measuring device in a first measuring position, according to the present disclosure.
  • FIG. 5D is a schematic, cross-sectional view of the portion of the measuring apparatus, showing a measuring device in a second measuring position, according to the present disclosure.
  • FIG. 6B is a partial, top schematic view of the marking apparatus, mounted to the nacelle, according to the present disclosure.
  • FIG. 8 is a flowchart illustrating a method of measuring and marking an abradable liner, according to the present disclosure.
  • FIG. 9B is an enlarged, schematic view of a portion of the measuring apparatus, including the measuring device, taken at detail 9B in FIG. 9A, according to another embodiment.
  • first and second may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.
  • upstream and downstream refer to the relative direction with respect to fluid flow in a fluid pathway.
  • upstream refers to the direction from which the fluid flows
  • downstream refers to the direction to which the fluid flows.
  • forward and aft refer to relative positions within a turbine engine or vehicle, and refer to the normal operational attitude of the turbine engine or vehicle. More particularly, forward and aft are used herein with reference to a direction of travel of the vehicle and a direction of propulsive thrust of the gas turbine engine.
  • the terms “axial” and “axially” refer to directions and orientations that extend substantially parallel to a centerline of the turbine engine.
  • the terms “radial” and “radially” refer to directions and orientations that extend substantially perpendicular to the centerline of the turbine engine.
  • the terms “circumferential” and “circumferentially” refer to directions and orientations that extend arcuately about the centerline of the turbine engine.
  • top refers to a highest or uppermost point, portion, or surface of a component in the orientations shown in the figures.
  • bottom refers to a lowest or lowermost point, portion, or surface of a component in the orientations shown in the figures.
  • a “low-power” setting defines the engine or the combustor configured to operate at a power output lower than a “high-power” setting of the engine or the combustor
  • a “mid-level power” setting defines the engine or the combustor configured to operate at a power output higher than a “low-power” setting and lower than a “high-power” setting.
  • the terms “low,” “mid” (or “mid-level”) or “high” in such aforementioned terms may additionally, or alternatively, be understood as relative to minimum allowable speeds, pressures, or temperatures, or minimum or maximum allowable speeds, pressures, or temperatures relative to normal, desired, steady state, etc., operation of the engine.
  • a mission cycle for a turbine engine includes, for example, a low-power operation, a mid-level power operation, and a high-power operation.
  • Low-power operation includes, for example, engine start, idle, taxiing, and approach.
  • Mid-level power operation includes, for example, cruise.
  • High-power operation includes, for example, takeoff and climb.
  • Coupled refers to both direct coupling, fixing, attaching, or connecting, as well as indirect coupling, fixing, attaching, or connecting through one or more intermediate components or features, unless otherwise specified herein.
  • the singular forms “a,” “an,” and “the” include plural references unless the context clearly dictates otherwise.
  • Approximating language is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about,” “approximately,” “generally,” and “substantially” is not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or the machines for constructing the components and/or the systems or manufacturing the components and/or the systems. For example, the approximating language may refer to being within a one, two, four, ten, fifteen, or twenty percent margin in either individual values, range(s) of values and/or endpoints defining range(s) of values.
  • Gas turbine engines may contain an abradable inner liner, axially aligned with blades of a fan assembly. Over time, this abradable liner may wear or erode, increasing a tip clearance between a tip of the fan and the abradable liner. Periodically, the abradable liner may be repaired or reworked to replace worn or eroded material in the liner. Tools for measuring and mapping an abradable liner profile, and for marking a reworked liner for additional rework, improve the rework process by increasing precision and decreasing a total time required for rework.
  • Tools are used for axial-cut-line marking during the fan abradable liner repair process and for verification of the machined abradable liner surface.
  • the abradable liner repair process makes multiple cuts at various axial locations and these cut line locations become very important in deciding the accuracy of the abradable profile.
  • the abradable profile is machined by removing abradable liner material along a circumferential direction and at various axial positions.
  • a marking tool uses a flange as a reference and makes consistent cut line marks along an axial direction.
  • the surface of the machined abradable liner is measured and mapped using a line laser.
  • the line laser is attached to a rotor, mounted to a fan disk. This unique arrangement helps to verify the quality of abradable repair and take appropriate corrective actions.
  • the abradable liner may be cylindrical in shape, but preferably, the abradable liner has a complex, non-cylindrical profile, consisting of multiple profile segments. As viewed in the circumferential direction, the profile segments may be straight, increasing, decreasing, or arcuate in shape.
  • the tip clearance exists between fan blade tips and the abradable liner. The tip clearance is the distance between the profile of the abradable liner and the tip of fan blades.
  • a tip clearance profile may be generated, representing the tip clearance at points between an axial width of the fan blade tip and the abradable liner.
  • the material of the abradable liner is removed through a machining process.
  • the machining process may be performed by planing, sanding, or any method as may be appropriate for removal of the material.
  • the ideal profile of the abradable liner may be a complex splined profile made up of cylindrical, convergent conical, divergent conical, or arcuate axisymmetric shapes.
  • the fan blades are removed from the fan disk.
  • the measurement apparatus is then mounted to the fan disk of the turbine engine.
  • the measurement apparatus has a generally radial arm portion and a generally axial arm portion.
  • the generally axial arm portion enables one or more line lasers to be mounted axially aft of the front face of the fan disk, aligned with the location of the tip interface.
  • Rotating handles are additionally mounted to the fan disk, for manual rotation of the fan disk with the measurement apparatus attached.
  • An optical scanning apparatus having an optical scanner is mounted to the axial arm portion.
  • the optical scanner uses the one or more line lasers to measure the surface profde of the liner, along the axial length of the tip of the fan blades.
  • the optical scanning apparatus may require more than one line laser in order to measure along the entire axial length of the abradable liner profile at once. In the embodiment of FIG. 3, two line lasers are used.
  • a data acquisition system including a controller, with a processor and a memory apparatus is included in the measurement apparatus, for controlling the line lasers and collecting the mapped surface profile of the abradable liner.
  • the data collected includes arrays of points, each point corresponding to an axial position along the longitudinal centerline axis, a rotational position from zero degrees to three hundred-sixty degrees, and a distance. The distance may be expressed as a distance from the longitudinal centerline axis about which the measurement apparatus rotates.
  • the measurement apparatus is first mounted to the fan disk. Next, the measurement apparatus is rotated to a first reference position. Next, the fan disk is manually rotated, using multiple handles mounted to the fan disk, thereby rotating the measurement apparatus about the longitudinal centerline axis, and scanning with the optical scanner, the abradable liner along the circumference, and along the length of the fan tip interface.
  • the data acquisition system determines the rotational alignment of the apparatus, in order to correlate the diameter data for each of the axial locations to a precise point in space. After manually rotating the fan disk and the measurement apparatus about an entire three hundred sixty degrees, the data points may be used to interpolate a mapped surface of the abradable liner.
  • the diameter of the inside surface of the abradable liner may be locally too large, decreasing the efficiency of the fan in operation, and, therefore, in need of new material to be added.
  • the diameter of the inside surface of the abradable liner may be too small, and, therefore, in need of machining away of a portion of the abradable liner, locally, to prevent physical interference between the fan blade tip and the abradable liner.
  • the liner may be marked to visually aid a human worker or a robot in identifying the locations in need of rework.
  • the marking apparatus specifically, a first component, mounts to the front edge of the nacelle, at a known angular position on the circumference of the edge of the nacelle.
  • the first component has a plate portion and an arm portion.
  • the first component additionally contains a handle, attached to the arm portion, for manually positioning the first component, when mounting the first component to the nacelle.
  • the marking apparatus additionally has a second component.
  • the second component is a plate, generally arcuate in shape, with bolt holes and end clamps.
  • the second component being lighter than the first component, is manually placed into position and clamped to a forward flange on the nacelle, holding the second component in position.
  • the bolt holes of the second component are manually aligned with corresponding bolt holes in the forward flange of the nacelle.
  • the first component is manually placed into position, using the handle to align the bolt holes of the first component with the bolt holes of the forward flange and the bolt holes of the second component. While being held in position manually, bolts are assembled through the bolt holes, sandwiching the forward flange between the first component and the second component, thereby establishing the axial position of the marking apparatus.
  • the bolt holes of the forward flange are at known angular positions along the circumference of the forward flange, the corresponding angular position of the marking apparatus may likewise be fixed and known.
  • the arm portion is fixed in a cantilever fashion to the bolted assembly of the plate portion, the forward flange, and the second component. When assembled, the arm position does not contact the abradable liner.
  • the first component is located axially and oriented only by the forward flange, and, as the first component is located rotationally only by the bolt holes in the forward flange, the location and the orientation of the first component are precisely established independent of the abradable liner.
  • the first component additionally contains multiple slots at prescribed axial locations on the first component. Each slot extends in the circumferential direction, with respect to the longitudinal centerline axis, when the marking apparatus is mounted to the nacelle.
  • the arm portion has a generally C-shaped cross section, when viewed down the length of the arm portion.
  • a prismatic portion is disposed within a channel of the C-shape in a location of each of the slots.
  • the slots extend through the prismatic portions, such that, when inserted, the scribe tool is aligned with an axial location along the longitudinal centerline axis. Absent the prismatic portions, the scribe tool may be angled during use, thereby permitting the user to errantly mark forward of, or aft of, the intended axial position.
  • Each slot corresponds to a position along the surface profile of the abradable liner that is an endpoint of a profile shape, or a transition point between profile shapes.
  • a slot may correspond to a location forward of which is a cylindrical profile, and aft of which is a divergent conical profile.
  • the slot locations may correspond to axial locations related to an order of operations for reworking the abradable liner.
  • the first component additionally has a plurality of visual markings in the form of lines, on one or both sides of the arm portion. Each of the lines corresponds to one of the plurality of slots, to aid in identifying the location of each slot, as the first component is viewed along the circumferential direction.
  • the first component additionally has shape identifiers, on the sides, between adjacent lines, indicating the shape of the abradable liner between the adjacent slots, to aid the user in scribing the proper location, as desired on the abradable liner.
  • the shape identifiers may show an angle, indicating a divergent conical shape, or indicating a convergent conical shape, between adjacent lines.
  • the first component has operational identifiers, between adjacent lines, indicating the intended order of operations for reworking the abradable liner.
  • the operational identifiers may include integer numerals, indicating the discrete steps to be taken in the rework process. Additionally, or alternatively, the operational identifiers may include directional arrows, pointing forward or aft, indicating the axial direction of a rework machining operation. For example, the axial distance between adjacent lines, corresponding to a single profile segment, may be longer than the tool used to machine the abradable liner. In such circumstances, the rework operation is to commence at either the forward end or the aft end of the segment.
  • the marking apparatus further includes a scribe tool.
  • the scribe tool has a handle portion and a scribe portion. The diameter of the scribe portion is a close fit in the width of the slots. Once the marking tool is assembled to a known angular position on the nacelle, the scribe tool may be inserted into one of the slots.
  • a scribe mark may be then made in the abradable liner, corresponding to a known angular position and a known axial position, and visually identifying the known angular position and known axial position to a human operator conducting the rework process.
  • any positions identified on the map of points may be identified on the abradable liner, and reworked accordingly, by either deposition of new material to the abradable liner, or by removal of existing material from the abradable liner.
  • the rework tools as described herein allow for precise measurement and marking of an abradable liner of a turbine engine.
  • the measurement apparatus fixes directly to the fan disk and is manually rotated about the entire circumference of the abradable liner.
  • the data acquisition system of the measurement apparatus enables the measurement apparatus to gather a set of point locations, each defined by a rotational (or angular) position, an axial location, and a distance.
  • the set of point locations defines a map, which, when compared to the nominal, or design-intent, surface profile, indicates locations requiring rework.
  • Rework may take the form of new material deposition or material removal.
  • the marking apparatus enables a user to mark the abradable liner with a scribing tool, at a precise rotational (and angular) position and a precise axial location without any effect on the current liner condition. Additionally, the marking tool aids the operator by providing numerous visual aids on the sides of the tool.
  • the measuring apparatus can be used in conjunction with the marking apparatus, where both the measuring apparatus and the marking apparatus are mounted to the turbine engine and in use at the same time. Using the measuring apparatus and the marking apparatus concurrently allows the measuring apparatus to verify dimensional alignment, for example in the axial direction, of the marking apparatus and of the visual markings on the marking apparatus relative to the fan casing to which the marking apparatus is mounted.
  • FIG. l is a schematic, cross-sectional diagram of a turbine engine 10, taken along a longitudinal centerline axis 12 of the turbine engine 10, according to an embodiment of the present disclosure.
  • the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 provided for reference) and a radial direction R that is normal to the axial direction A.
  • the turbine engine 10 includes a fan section 14 and a turbo-engine 16 disposed downstream from the fan section 14.
  • the turbo-engine 16 includes, in serial flow relationship, a compressor section 21, a combustion section 26, and a turbine section 27.
  • the turbo-engine 16 is substantially enclosed within an outer casing 18 that is substantially tubular and defines a core inlet 20 that is annular about the longitudinal centerline axis 12.
  • the compressor section 21 includes a booster or a low pressure (LP) compressor 22 followed downstream by a high pressure (HP) compressor 24.
  • the combustion section 26 is downstream of the compressor section 21 .
  • the turbine section 27 is downstream of the combustion section 26 and includes a high pressure (HP) turbine 28 followed downstream by a low pressure (LP) turbine 30.
  • the turbo-engine 16 further includes a jet exhaust nozzle section 32 that is downstream of the turbine section 27, a high-pressure (HP) shaft 34 or a spool, and a low-pressure (LP) shaft 36.
  • the HP shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24.
  • the HP turbine 28 and the HP compressor 24 rotate in unison through the HP shaft 34.
  • the LP shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22.
  • the LP turbine 30 and the LP compressor 22 rotate in unison through the LP shaft 36.
  • the compressor section 21, the combustion section 26, the turbine section 27, and the jet exhaust nozzle section 32 together define a core air flow path.
  • the fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 coupled to a fan disk 42 in a spaced apart manner. As depicted in FIG. 1, the fan blades 40 extend outwardly from the fan disk
  • the plurality of fan blades 40 are rotatable relative to the fan disk 42 about a pitch axis P by virtue of the fan blades 40 being operatively coupled to an actuation member 44 configured to collectively vary the pitch of the fan blades 40 in unison.
  • the fan blades 40, the fan disk 42, and the actuation member 44 are together rotatable about the longitudinal centerline axis 12 via a fan shaft 45 that is powered by the LP shaft 36 across a power gearbox, also referred to as a gearbox assembly 46.
  • the fan 38 is drivingly coupled to, and powered by, the turbo-engine 16, and the turbine engine 10 is an indirect drive engine.
  • the gearbox assembly 46 is shown schematically in FIG. 1.
  • the gearbox assembly 46 is a reduction gearbox assembly for adjusting the rotational speed of the fan shaft 45 and, thus, the fan 38 relative to the LP shaft 36 when power is transferred from the LP shaft 36 to the fan shaft 45.
  • the fan disk 42 is covered by a fan hub 48 that is aerodynamically contoured to promote an airflow through the plurality of fan blades 40.
  • the fan section 14 includes an annular fan casing or a nacelle 50 that circumferentially surrounds the fan 38 and at least a portion of the turbo-engine 16.
  • the nacelle 50 is supported relative to the turbo-engine 16 by a plurality of outlet guide vanes 52 that are circumferentially spaced about the nacelle 50 and the turbo-engine 16.
  • a downstream section 54 of the nacelle 50 extends over an outer portion of the turbo-engine 16, and, with the outer casing 18, defines a bypass airflow passage 56 therebetween.
  • a volume of air 58 enters the turbine engine 10 through an inlet 60 of the nacelle 50 or the fan section 14.
  • a first portion of air also referred to as bypass air 62
  • a second portion of air also referred to as core air 64
  • the ratio between the bypass air 62 and the core air 64 is commonly known as a bypass ratio.
  • the pressure of the core air 64 is then increased, generating compressed air 65.
  • the compressed air 65 is routed through the HP compressor 24 and into the combustion section 26, where the compressed air 65 is mixed with fuel and ignited to generate combustion gases 66.
  • the combustion gases 66 are routed into the HP turbine 28 and expanded through the HP turbine 28, where a portion of thermal energy or kinetic energy from the combustion gases 66 is extracted via one or more stages of HP turbine stator vanes 68 and HP turbine rotor blades 70 that are coupled to the HP shaft 34. This causes the HP shaft 34 to rotate, supporting operation of the HP compressor 24 (self-sustaining cycle). In this way, the combustion gases 66 do work on the HP turbine 28.
  • the combustion gases 66 are then routed into the LP turbine 30 and expanded through the LP turbine 30.
  • a second portion of the thermal energy or the kinetic energy is extracted from the combustion gases 66 via one or more stages of LP turbine stator vanes 72 and LP turbine rotor blades 74 that are coupled to the LP shaft 36.
  • This causes the LP shaft 36 to rotate, supporting operation of the LP compressor 22 (self- sustaining cycle) and rotation of the fan 38 via the gearbox assembly 46. In this way, the combustion gases 66 do work on the LP turbine 30.
  • the combustion gases 66 are subsequently routed through the jet exhaust nozzle section 32 of the turbo-engine 16 to provide propulsive thrust.
  • the bypass air 62 is routed through the bypass airflow passage 56 before being exhausted from a fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust.
  • the HP turbine 28, the LP turbine 30, and the jet exhaust nozzle section 32 at least partially define a hot gas path 78 for routing the combustion gases 66 through the turbo-engine 16.
  • the turbine engine 10 depicted in FIG. 1 is by way of example only.
  • the turbine engine 10 may have any other suitable configuration.
  • the fan 38 may be configured in any other suitable manner (e g., as a fixed pitch fan) and further may be supported using any other suitable fan frame configuration.
  • the turbine engine 10 may also be a direct drive engine, which does not have a power gearbox. In a direct drive configuration, the fan speed is the same as the LP shaft speed for a direct drive engine.
  • any other suitable number or configuration of compressors, turbines, shafts, or a combination thereof may be provided.
  • aspects of the present disclosure may be incorporated into any suitable turbofan engine.
  • the fan section 14 includes a tip interface area 100 between the abradable liner 104 and a fan blade tip 108 on an inner surface 102 of the nacelle 50.
  • the abradable liner 104 has a profde, also referred to as a surface profile, that can be cylindrical in shape, but, preferably, the surface profile of the abradable liner 104 is a complex, non-cylindrical profile, consisting of multiple profile segments. As viewed in the circumferential direction, the profile segments may be straight, increasing, decreasing, or arcuate in shape.
  • the fan tip-liner clearance 106 also referred to as a tip clearance, exists between the fan blade tip 108 and the abradable liner 104.
  • the fan tip-liner clearance 106 is the distance between the surface profile of the abradable liner 104 and fan blade tip 108.
  • a tip clearance profile may be generated, representing the fan tip-liner clearance 106 at points between the axial width of the fan blade tip 108 and the abradable liner 104.
  • Normal engine operation, periodic tip interference, ingestion of material such as precipitation, dust, or debris, or other deleterious events may cause wear or erosion of the abradable liner 104, thus, increasing the fan tip-liner clearance 106 and affecting the tip clearance profile.
  • Such wear or erosion may require repair or rework of the abradable liner 104.
  • the rework process involves a deposition of new material onto the inner surface 102 of the nacelle 50.
  • the deposition of the new material may occur over preexisting, albeit worn, abradable liner material.
  • the new material can be a resin, an epoxy, or any other polymer capable of being abraded by the fan blades 40.
  • material of the abradable liner 104 may be removed with a machining tool to achieve a desired surface profile of the abradable liner 104, and, thus, achieve a desired tip clearance profile between the fan blade tip 108 and the abradable liner 104.
  • a machining tool to achieve a desired diameter and surface profile of the abradable liner 104, multiple material removal cuts are made to the deposited material at various axial positions. A desired profile dimension at a plurality of axial positions of the abradable liner 104 is established, and material of the abradable liner 104 is removed through a machining process to reach the desired diameter and surface profile.
  • the machining process may be performed by grinding, planing, sanding, or any other method as may be appropriate for removal of the material.
  • the desired surface profile of the abradable liner 104 may be a complex splined profile made up of cylindrical, convergent conical, divergent conical, or arcuate axisymmetric shapes. Accordingly, the surface profile of the abradable liner 104 varies in radial extent as the abradable liner 104 extends axially.
  • FIG. 3A is a schematic, front elevational view of a measuring apparatus 200 for the abradable liner 104 (FIG. 2), according to the present disclosure.
  • the measuring apparatus 200 measures the surface profile of the abradable liner 104.
  • the measuring apparatus 200 includes a frame assembly 202 having a generally radial arm portion 204, that, when the measuring apparatus 200 is mounted to the fan 38 of the turbine engine 10, extends substantially in the radial direction R.
  • the generally radial arm portion 204 includes a first end 208 and a second end 210 opposite the first end 208.
  • the frame assembly 202 also includes a generally axial arm portion 206 connected to the second end 210.
  • the generally axial arm portion 206 includes an axial plate 212, that, when the measuring apparatus 200 is mounted to fan 38 of the turbine engine 10, extends in a substantially axial direction.
  • the measuring apparatus 200 includes a track 214 mounted to a radially outer surface 220 of the axial plate 212.
  • the track 214 extends in the axial direction A and engages with a slide plate 216 to allow the slide plate 216 to move along a length of the track 214 in the axial direction.
  • a measuring device 218 is mounted to the slide plate 216, such that the measuring device 218 can slide in the axial direction to adjust a position of the measuring device 218, in order to measure the surface profde of the abradable liner 104 over the axial length of the abradable liner 104.
  • the measuring device 218 is an optical scanner.
  • the measuring device 218 can be a laser.
  • the laser is a line laser that projects a line, particularly, in the axial direction, when mounted to the measuring apparatus 200, to capture the surface profile over the axial length of the abradable liner 104.
  • the line laser can be capable of measuring the surface profile over only a portion of the axial length of the abradable liner 104 and requires a first measurement to be made at a first measuring position 244 (described in further detail in the discussion of FIGS. 5C and 5D) and a second measurement to be made at a second measuring position 246 (described in further detail in the discussion of FIGS. 5C and 5D).
  • the measuring apparatus 200 includes a plurality of measuring devices 218.
  • the measuring device 218 can be a mechanical measuring device as detailed further below with respect to FIGS. 9A and 9B.
  • the measuring device 218 can include a plurality of pins, such as spring-loaded pins. Various positions of the measuring device 218 along the track 214 are described in more detail with respect to FIGS. 5A to 5D.
  • the measuring apparatus 200 further includes a mounting plate 222 connected to the generally radial arm portion 204 for mounting the measuring apparatus 200 to the fan section 14 of the turbine engine 10.
  • the mounting plate 222 is mounted to the fan disk 42.
  • the mounting plate 222 can be ring-shaped to correspond with a perimeter shape of the fan disk 42.
  • the mounting plate 222 is attached to the fan disk 42 such that rotation of the measuring apparatus 200 also rotates the fan disk 42.
  • a plurality of handles 224 are disposed on the mounting plate 222 at various circumferential locations around the mounting plate 222. The handles 224 allow an operator to rotate the measuring apparatus 200 about the longitudinal centerline axis 12 to measure the abradable liner 104 at various circumferential locations. As depicted in FIG.
  • four sets of the handles 224 are disposed on the mounting plate 222 at regular angular intervals. Any number of the handles 224, however, can be disposed at any angular intervals for the convenience of the operator. In some embodiments, as an example, four of the handles 224 may be disposed at two o’clock, four o’clock, eight o’clock, and ten o’clock positions.
  • the measuring apparatus 200 also includes an extension bracket 236 extending radially outwardly from the axial plate 212.
  • the extension bracket 236 provides an alternative mounting point for the measuring device 218.
  • mounting the measuring device 218 to the extension bracket 236 reduces the measuring distance of the optical scanner and improves accuracy.
  • the measuring device 218 may need to be mounted in closer proximity to the abradable liner 104, and, in such cases, the measuring device 218 would be attached to the extension bracket 236 instead of the slide plate 216. Additional features and usage of the extension bracket 236 are described in more detail in the discussions of FIG. 5 A and FIG. 9A.
  • the measuring apparatus 200 also includes a data acquisition system including a controller 80 (FIG. 1) for controlling the measuring device 218 and collecting measurements of the abradable liner 104 to generate a mapped surface profile of the abradable liner 104.
  • a set of data collected by the controller 80 can include an array of points, each point corresponding to an axial position on the abradable liner 104, a rotational position of the measuring apparatus 200 from zero degrees to three hundred-sixty degrees, and a distance.
  • the rotational position of the measuring apparatus 200 can be measured using devices known in the art such as an inclinometer or an accelerometer.
  • the distance can be expressed as a distance from the longitudinal centerline axis 12 (FIG. 1) about which the measuring apparatus 200 rotates. The distance can be used to determine a radial height of the abradable liner 104 to determine the surface profile of the abradable liner 104.
  • FIG. 3B is an enlarged, schematic, side view of a portion of the measuring apparatus 200, taken at detail 3B of FIG. 3 A, according to the present disclosure.
  • the generally axial arm portion 206 of the measuring apparatus 200 includes the axial plate 212.
  • the track 214 is mounted to the radially outer surface 220 of the axial plate 212. As depicted in FIG. 3B, the track 214 is shown to be extending axially beyond the axial plate 212 in the axial direction.
  • the track 214 can be disposed at any position relative to the axial plate 212 to adequately span the axial length of the abradable liner 104 (FIG. 2).
  • the track 214 can have at least one rail 226 with which the slide plate 216 can slidably engage.
  • the slide plate 216 can have at least one groove 228 to receive the rail 226 of the track 214.
  • the slide plate 216 can further have a locking mechanism 230 to prevent movement of the slide plate 216 relative to the track 214.
  • the locking mechanism 230 can be a manually operated screw, or the like.
  • the locking mechanism 230 can frictionally engage with the track 214.
  • the track 214 can have indexed holes for receiving the manually operated screw.
  • the locking mechanism 230 can be a clamp.
  • the locking mechanism 230 can be a detent on either the track 214 or the slide plate 216.
  • the slide plate 216 can have a transverse extending portion 232 to which the measuring device 218 can be mounted. Although the transverse extending portion 232 for receiving the measuring device 218 is shown as a flat surface, other shapes that can receive the measuring device 218, can be used. In one embodiment, the slide plate 216 can include a pocket or a cavity for receiving the measuring device 218 therein. [0078] FIGS. 4A to 4C show various views of the measuring apparatus 200 in use. FIG.
  • FIG. 4A is a schematic side view of the measuring apparatus 200 mounted to the fan disk 42 of the turbine engine 10, taken along the longitudinal centerline axis 12, and with the fan blades 40 (FIG. 1) of the fan 38 (FIG. 1) removed, according to the present disclosure.
  • the mounting plate 222 mounts the measuring apparatus 200 to the fan disk 42.
  • the fan blades 40 are removed so that the generally axial arm portion 206 can extend into an axial space where the fan blades 40 would normally occupy, allowing the measuring device 218 to be positioned along the axial length of the abradable liner 104.
  • a measurement process includes rotating the measuring apparatus 200 to a reference position 240 (FIG. 4C) in the circumferential direction where the measuring device 218 begins measuring the surface profile of the abradable liner 104. The operator then manually rotates the measuring apparatus 200, using the handles 224, three hundred sixty degrees about the longitudinal centerline axis 12, until the measuring apparatus 200 returns to the reference position 240.
  • the measuring device 218 measures the entire surface profile of the abradable liner 104.
  • the measuring apparatus 200 can be rotated less than three hundred sixty degrees about the longitudinal centerline axis 12 to measure only a portion of the surface profile of the abradable liner 104.
  • the measuring device 218 can include a line laser which measures the surface profile over the entire axial length of the abradable liner 104 at each circumferential location, such that the measuring device 218 captures the entire surface profile of the abradable liner 104 during one rotation of the measuring apparatus 200.
  • the controller 80 determines the rotational position of the measuring apparatus 200 in order to correlate the measurements of the abradable liner 104 with a circumferential location. After rotation of the measuring apparatus 200 is complete, the controller 80 can combine the measurements of the abradable liner 104 with the rotational position to generate the mapped surface profde of the abradable liner 104.
  • FIG. 4B is a perspective side view of the measuring apparatus 200 mounted to the fan disk 42 of the turbine engine 10, taken along the longitudinal centerline axis 12, according to the present disclosure.
  • the measuring apparatus 200 includes the mounting plate 222 mounted to the fan disk 42.
  • the mounting plate 222 is generally concentric with the fan disk 42. Rotating the mounting plate 222 via the handles 224 also rotates the fan disk 42. In this way, although the fan disk 42 in FIG.
  • the measuring apparatus 200 can simplify the rework process on a turbine engine with the fan blades 40 still attached by requiring removal of only a small number of fan blades 40 to accommodate the measuring apparatus 200 and still be able to measure the surface profile around the entire circumference of the abradable liner 104.
  • FIG. 4C is a schematic, front elevational view of the measuring apparatus 200 mounted to the fan disk 42 of the turbine engine 10 (FIG. 1), viewed along the longitudinal centerline axis 12 (FIG. 1), according to another embodiment.
  • the measuring apparatus 200 includes the reference position 240.
  • the reference position 240 can be a position wherein the measuring apparatus 200 is in a generally vertical orientation relative to the human operator or a gravity vector, such as an orientation as depicted in FIG. 4C.
  • the reference position 240 can be any orientation of the measuring apparatus 200 that is convenient for the human operator.
  • the measuring device 218, has a calibration position 242.
  • the calibration position 242 is a reference position for the controller 80 to take calibrating measurements with the measuring device 218 (FIG. 3B).
  • the calibrating measurements can include measuring a feature of a marking apparatus 300 (shown and described in further detail in the discussion of FIGS. 6A, 6C, and 7) using the measuring device 218 at the calibration position 242, where a dimension of the feature of the marking apparatus 300 relative to the calibration position 242 (shown and described in further detail in the discussion of FIG. 7) is known.
  • One or more visual markings 248 can indicate the calibration position 242.
  • the one or more visual markings 248 can be placed on the track 214, the slide plate 216, or both.
  • the measuring apparatus 200 includes the extension bracket 236.
  • the extension bracket 236 includes a first leg 250 having a first leg radially inner end 252 that can be attached to the track 214 and a first leg radially outer end 254 radially opposite the first leg radially inner end 252.
  • the extension bracket 236 also includes a second leg 256 axially spaced from the first leg 250 and having a second leg radially inner end 258 that can be attached to the track 214 and a second leg radially outer end 260 radially opposite the second leg radially inner end 258.
  • a bracket crossbar 262 connects the first leg radially outer end 254 and the second leg radially outer end 260.
  • the bracket crossbar 262 can serve as an alternate mounting point for the measuring device 218.
  • the measuring device 218 is mounted to the bracket crossbar 262, instead of to the track 214. Doing so allows shorter pins to be used, and, thereby, reduces errors from manufacturing and measurement, as well as reduces the overall weight of the device.
  • the first leg radially inner end 252 and the second leg radially inner end 258 can be attached to the radially outer surface 220 of the axial plate 212, instead of the track 214.
  • FIG. 5B is an enlarged, schematic view of the portion of the measuring apparatus 200, taken at detail 5B of FIG. 5 A, according to the present disclosure.
  • the axial plate 212 includes one or more visual markings 248 to indicate the calibration position 242 of the slide plate 216, and, correspondingly, the measuring device 218 (FIG. 3B).
  • the one or more visual markings 248 can be a line.
  • the one or more visual markings 248 can be a dot or a marking of any other shape to aid the human operator in aligning the measuring device 218 relative to the axial plate 212.
  • the measuring device 218 is placed in the calibration position 242 by sliding the slide plate 216 between two visual markings 248.
  • the slide plate 216 also includes one or more visual markings 248.
  • the measuring device 218 is placed in the calibration position 242 by aligning the visual marking 248 on the slide plate 216 with one of the visual markings 248 on the axial plate 212.
  • FIG. 5C is a schematic, cross-sectional view of the portion of the measuring apparatus 200, showing the measuring device 218 in the first measuring position 244, according to the present disclosure.
  • the slide plate 216 carrying the measuring device 218 (not shown) is at the first measuring position 244 at a track first end 264 of the track 214.
  • the track first end 264 is a first axial end of the track 214.
  • the first measuring position 244 can be anywhere along a length of the track 214 to maximize coverage of the measuring device
  • FIG. 5D is a schematic, cross-sectional view of the portion of the measuring apparatus 200, showing the measuring device 218 in the second measuring position 246 according to the present disclosure.
  • the slide plate 216 carrying the measuring device 218 (not shown) is at the second measuring position 246 at a track second end 266 of the track 214 opposite the track first end 264.
  • the track second end 266 is a second axial end of the track 214.
  • the measuring device 218 is unable to measure the surface profile over the entire axial length of the abradable liner 104, for example, due to a limited axial extent of the line laser.
  • measurements may need to be performed at the first measuring position 244 and at the second measuring position 246, to ensure that the surface profile over the entire axial length of the abradable liner 104 is captured.
  • the measuring device 218 is placed at the first measuring position 244, and the measurement process is performed at the first measuring position 244 to generate a first set of measurement data.
  • the measuring device 218 is then moved to the second measuring position 246, and the measurement process is repeated at the second measuring position 246 to generate a second set of measurement data.
  • the controller 80 (FIG. 1) can then combine the first set of measurement data and the second set of measurement data together to generate the mapped surface profile of the abradable liner 104.
  • the first measuring position 244 and the second measuring position 246 can be indicated by visual markings.
  • a first abutment can be provided at a first axial location of the track 214 that corresponds to the first measuring position 244 and a second abutment can be provided at a second axial location of the track 214 that corresponds to the second measuring position 246.
  • the first abutment and the second abutment can stop the slide plate 216 at the first measuring position 244 and the second measuring position 246, respectively.
  • the measuring apparatus 200 can include a plurality of measuring devices 218.
  • the measuring device 218 can be placed at the first measuring position 244 and at the second measuring position 246. In some embodiments, more than two measuring devices 218 can be provided on the measuring apparatus 200. Having multiple measuring devices 218 allows multiple instances of the measurement process to be performed concurrently.
  • FIGS. 6A to 6D show various views of a marking apparatus 300, also referred to as a liner marking apparatus or an axial marking tool, used to precisely mark the abradable liner 104.
  • a diameter of the inner surface 102 (FIG. 2) of the abradable liner 104 may be locally too large, or, put another way, the fan tip-liner clearance 106 (FIG. 2) may be too large, decreasing efficiency of the fan 38 (FIG. 1) in operation, and, therefore, in need of new material to be added.
  • the diameter of the inner surface 102 of the abradable liner 104 may be too small, or put another way, the tip clearance may be too small, and, therefore, a portion of the abradable liner 104 may need to be removed locally to prevent physical interference between the fan blade tip 108 and the abradable liner 104.
  • the abradable liner 104 may be marked to visually aid the operator in identifying locations in need of rework.
  • the marking apparatus 300 provides a tool to allow the operator to quickly and accurately mark the abradable liner 104.
  • FIG. 6A is a partial, top perspective view of a marking apparatus 300, mounted to the nacelle 50, according to the present disclosure.
  • the marking apparatus 300 includes a first component 302 having a mounting plate 304, also referred to as a plate portion.
  • the mounting plate 304 includes a radially outer end 308 to be positioned on a forward edge 338 of the nacelle 50.
  • the radially outer end 308 includes a plurality of openings 312 for receiving a plurality of fasteners 314 therethrough.
  • the plurality of fasteners 314 secure the mounting plate 304 to the forward edge 338 of the nacelle 50.
  • the mounting plate 304 further includes a radially inner end 310 radially opposite the radially outer end 308.
  • the marking apparatus 300 also includes an arm portion 306 connected to the radially inner end 310 of the mounting plate 304.
  • the arm portion 306 extends axially into the nacelle 50.
  • the arm portion 306 is connected to the mounting plate 304 in a cantilever fashion, such that a first end 316 of the arm portion 306 is connected to the mounting plate 304 and a second end 318 of the arm portion 306 is free of an attachment.
  • the arm portion 306 does not contact the abradable liner 104.
  • the arm portion 306 can be welded to the mounting plate 304.
  • the arm portion 306 can be removably attached to the mounting plate 304, such as with threaded fasteners.
  • the marking apparatus 300 also includes a plurality of slots 320 at prescribed axial locations on the arm portion 306.
  • the prescribed axial locations of the plurality of slots 320 can each correspond to a position along the surface profile of the abradable liner 104 that is an endpoint of a profile shape or a transition point between profile shapes.
  • one of the slots 320 may correspond to a location forward of which is a cylindrical profile, and aft of which is a divergent conical profile.
  • the locations of the plurality of slots 320 can correspond to axial locations related to an order of operations for reworking the abradable liner 104.
  • Each of the plurality of slots 320 extends in the circumferential direction with respect to the longitudinal centerline axis 12 when the marking apparatus 300 is mounted to the nacelle 50.
  • the plurality of slots 320 can be circular instead of extending in the circumferential direction.
  • the plurality of slots 320 can also be shaped to allow a marker 322 to be inserted therethrough to mark the abradable liner 104. As will be described in detail below, measurement can be performed through the plurality of slots 320 to provide measurement data at each of the prescribed axial locations.
  • the marking apparatus 300 further includes a plurality of visual markings 326 on one or both sides of the arm portion 306.
  • the visual markings 326 can indicate a geometry, an angle, a profile, a sequence of rework, or any combination thereof, of the abradable liner 104.
  • Each of the visual markings 326 can be in the form of lines that correspond to one of the plurality of slots 320 to aid in identifying the location of each slot when the first component 302 is viewed along the circumferential direction.
  • the visual markings 326 can further include shape identifiers between adjacent lines indicating the profile shape of the abradable liner 104 between adjacent lines to aid the human operator in scribing the proper location on the abradable liner 104.
  • the shape identifiers may, as an example, show an angle indicating a divergent conical shape or indicating a convergent conical shape between adjacent lines.
  • the visual markings 326 can, additionally or alternatively, include operational identifiers between adjacent lines indicating an intended order of operations for reworking the abradable liner 104.
  • the operational identifiers may include integer numerals indicating discrete steps to be taken in the rework process.
  • the operational identifiers can further include directional arrows, pointing forward or aft, indicating an axial direction of a rework machining operation. For example, the axial distance between adjacent lines, corresponding to a single profile segment, may be longer than the tool used to machine the abradable liner 104.
  • the rework process is to commence at either a forward end or an aft end of the profile segment.
  • the process increments in the axial direction indicated by the directional arrow for a next circumferential operation about the abradable liner 104.
  • Such operation continues incrementally in either the forward direction or the aft direction, as indicated by the directional arrow, until the operation of machining of the segment is complete.
  • FIG. 6B is a partial, top schematic view of the marking apparatus 300, mounted to the nacelle 50, according to the present disclosure.
  • the marking apparatus 300 includes a back plate 328 having a first end section 330, a second end section 332, and a generally arcuate bridge section 336 connected the first end section 330 and the second end section 332.
  • the first end section 330 includes a first end clamp 334a and the second end section 332 includes a second end clamp 334b.
  • the first end clamp 334a and the second end clamp 334b provide for grasping a flange 340 at the forward edge 338 of the nacelle 50 (FIG. 6A).
  • the bridge section 336 includes a plurality of openings 346 matching the plurality of openings 312 on the mounting plate 304 (FIG. 6A) for receiving the plurality of fasteners 314 to assemble the back plate 328 to the mounting plate 304.
  • the back plate 328 is manually positioned on an aft surface 344 (FIG. 6B) of the flange 340 at the forward edge 338 and held in place using the end clamps 334.
  • the plurality of openings 346 are manually aligned with corresponding openings in the flange 340.
  • the first component 302 is manually placed into position at a forward surface 342 of the flange 340, using a handle 324 to align the plurality of openings 312 in the mounting plate 304 with the plurality of openings 346 in the back plate 328.
  • the plurality of fasteners 314 are inserted through the plurality of openings 312 in the mounting plate 304 and the plurality of openings 346 (FIG. 6B) in the back plate 328.
  • the back plate 328 together with the mounting plate 304, sandwiches the flange 340 therebetween.
  • the openings in the flange 340 can be indexed to known angular positions along the circumference of the forward edge 338 of the nacelle 50.
  • a corresponding angular position of the marking apparatus 300 may likewise be known.
  • the marking apparatus 300 uses the flange 340 as a reference point to measure axial distance from the forward edge 338, thereby establishing the axial position of the plurality of slots 320 along the arm portion 306.
  • the location and the orientation of the marking apparatus 300 can be precisely established.
  • the marking apparatus 300 further includes the marker 322, also referred to as a scribe tool, to create a visual indicator on, or to mark, the abradable liner 104 (FIG. 2).
  • the marker 322 includes a handle portion 348 and a scribe portion 350 (FIG. 6C). A diameter of the scribe portion 350 is sized to provide a close fit with the width of the plurality of slots 320.
  • a scribe mark may then be made in the abradable liner 104, corresponding to a known angular position and a known axial position, and visually identifying the known angular position and the known axial position to the human operator conducting the rework process.
  • FIG. 6C is a partial, bottom perspective schematic view of the marking apparatus
  • the arm portion 306 has a generally C-shaped cross section, when viewed down the length of the arm portion 306.
  • a plurality of prismatic portions 352 are disposed within a channel 354 of the C-shape cross section in the location of each of the plurality of slots 320.
  • the plurality of slots 320 extend through the plurality of prismatic portions 352, such that, when inserted, the marker 322 is aligned with one of the prescribed axial locations along the axial length of the abradable liner 104. Absent the plurality of prismatic portions 352, the marker 322 tool may be angled during use, thereby permitting the user to errantly mark forward of, or aft of, the intended axial position.
  • FIG. 7 is a schematic view of a measuring and marking system 400 including the measuring apparatus 200 and the marking apparatus 300, taken along the longitudinal centerline axis 12 (FIG. 1), according to the present disclosure.
  • the measuring apparatus 200 and the marking apparatus 300 can be used concurrently such that both the measuring apparatus 200 and the marking apparatus 300 are mounted to the turbine engine 10 at the same time.
  • the measuring device 218, such as a line laser is configured to project a laser 219 that penetrates, or otherwise extend through, the arm portion 306 at the slots 320 during a beginning of the measurement process.
  • the controller 80 (FIG. 1) can detect portions of the laser 219 that extend through the slots 320 and identify axial locations corresponding to the portions of the laser 219.
  • the method 500 includes mounting the marking apparatus 300 to the nacelle 50.
  • the human operator mounts the marking apparatus 300 to the nacelle 50.
  • the human operator manually positions and clamps the back plate 328 to the aft surface 344 of the flange 340 at the forward edge 338 of the nacelle 50.
  • the operator positions the first component 302 at the forward surface 342 of the flange 340 and fastens the back plate 328 and the first component 302 together, thereby sandwiching the flange 340. This establishes an axial reference position and an angular reference position.
  • the method 500 includes measuring the surface profile of the abradable liner 104 with the measuring device 218 to generate measurement data.
  • the measurement process starts by using the measuring device 218 to measure the surface profile of the abradable liner 104.
  • the human operator rotates the measuring apparatus 200 in the circumferential direction about the longitudinal centerline axis 12 until the measuring apparatus 200 is back at the angular reference position.
  • the measuring device 218 may need to be moved from the first measuring position 244 to the second measuring position 246 with step 506 being repeated to make a second measurement.
  • the controller 80 generates a mapped surface profile of the abradable liner 104 from the measurement data generated in step 506.
  • the measurement data includes the distance to the abradable liner 104 as well as the axial position on the abradable liner 104 for each measured location, and the rotational position of the measuring apparatus 200 when each measurement was taken.
  • the mapped surface profile is compared with a nominal, or intended, surface profile of the abradable liner 104 to determine one or more repair locations on the abradable liner 104 where rework is required. This includes determining whether the rework requires removing material or depositing additional material, as well as the shape and the direction of the rework.
  • the method 500 includes marking the one or more repair locations on the abradable liner 104.
  • the operator marks the one or more repair locations on the abradable liner 104 by inserting the marker 322 through the plurality of slots 320 to scribe the abradable liner 104.
  • the one or more repair locations identified from the mapped surface profile and scribed on the abradable liner 104 are reworked accordingly, by either deposition of new material to the abradable liner 104, or by removal of existing material from the abradable liner 104.
  • the pins 612 may travel radially inwards or radially outwards to reflect changes in the surface profile of the abradable liner 104.
  • the controller 80 receives an indication of a radial position of the pins 612 as the measurement data on the surface profile.
  • the pins 612 can also be used concurrently with the marking apparatus 300 (FIG. 6A), wherein any of the pins 612 located at the slots 320 will extend through the slots 320 to trigger measurement data at corresponding axial locations of the slots 320.
  • the installation brackets 610 can be configured to removably attach the measuring device 602 to the extension bracket 236.
  • the installation brackets 610 can be mounted to the bracket crossbar 262 of the extension bracket 236.
  • the installation brackets 610 can use any conventional attachment means, such as by being hook shaped or using fasteners.
  • the measuring device 602 includes springs 616 surrounding the pins 612 to provide a resilient biasing force to the pins 612. During operation, as the pins 612 travel due to changes in the surface profile of the abradable liner 104, the springs 616 can compress or decompress. In some embodiments, spring compression can be used as measurement data acquired by the controller 80.
  • Each of the pins 612 includes a tip end 614 configured to be in contact with the surface of the abradable liner 104 when in use. The tip end 614 preferably does not abrade or otherwise leave a marking on the surface of the abradable liner 104.
  • the measuring device 602 further includes one or more pin mounting portions 618 disposed on the first surface 606 of the mounting plate 604.
  • Each of the pin mounting portions 618 is shaped to receive each of the pins 612 therethrough to provide consistent spacing between adjacent pins 612 and to keep the pins 612 aligned and in parallel during use, to increase accuracy of measurements by reducing errors from lateral movement and wobble.
  • Three pin mounting portions 618 can be disposed along a length of each of the pins 612. In some embodiments, any other number of pin mounting portions 618 can be used. As an example, each of the pins 612 can be inserted through two pin mounting portions 618 instead.
  • the measuring and marking system as described herein improves the rework process of the abradable liner 104 of the turbine engine 10 by increasing precision and decreasing the total time required for the rework.
  • the measuring apparatus 200 includes the measuring device 218 to measure the profile over the axial length of the surface of the abradable liner 104, instead of measuring point by point, to increase an efficiency of the rework process.
  • the measuring apparatus 200 is also made to be relatively lightweight and can be manually installed by the operator.
  • the marking apparatus 300 enables the operator to make markings on the abradable liner 104 at precise axial and rotational positions.
  • the marking apparatus 300 further simplifies the rework process for the operator by providing numerous visual aids on the marking apparatus 300 to verify measurements and subsequent addition or removal of material on the abradable liner 104.
  • a measuring and marking system for a turbine engine including a fan section having a nacelle and an abradable liner on the nacelle
  • the measuring and marking system including a measuring apparatus including a frame assembly having a generally radial arm portion configured to be mounted to the fan section of the turbine engine and having a first end and a second end opposite the first end, and a generally axial arm portion connected to the second end of the generally radial arm portion, and a measuring device mounted to the generally axial arm portion of the frame assembly to measure a profile of the abradable liner
  • a marking apparatus including a mounting plate for mounting to the nacelle and including a radially outer end, and an arm portion extending generally orthogonally from the mounting plate and having a first end and a second end opposite the first end, the arm portion arranged as a cantilever such that the first end is attached to the mounting plate and the second end is free from an attachment, the arm portion having
  • the measuring and marking system of the preceding clause further including a track mounted to the generally axial arm portion of the frame assembly, the track extending in an axial direction and a slide plate slidably mounted to the track, wherein the measuring device is mounted to the slide plate.
  • the measuring device includes a plurality of pins arranged in an axial direction.
  • the arm portion of the marking apparatus further includes a plurality of visual markings indicating a geometry, an angle, a profile, a sequence of rework, or any combination thereof, of the abradable liner.
  • the measuring and marking system of any preceding clause further including a first measuring position along a length of the generally axial arm portion and a second measuring position along the length of the generally axial arm portion, and wherein the measuring device is movable to the first measuring position and to the second measuring position.
  • the measuring and marking system of any preceding clause further including a calibration position located between the first measuring position and the second measuring position for calibrating the measuring device.
  • the measuring and marking system of any preceding clause further including a mounting plate attached to the generally radial arm portion of the frame assembly to mount the measuring apparatus to a fan disk of the turbine engine.
  • the mounting plate rotatably mounts the measuring apparatus to the fan disk of the turbine engine such that the measuring apparatus is rotatable around a circumference of the fan section.
  • the measuring and marking system of any preceding clause further including a plurality of handles disposed on the mounting plate for manually rotating the measuring apparatus in a circumferential direction about a longitudinal centerline axis of the turbine engine.
  • the measuring device is a line laser.
  • the mounting plate is configured to be mounted to a forward edge of the nacelle and includes a radially outer end having a plurality of openings for receiving a fastener and a radially inner end opposite the radially outer end.
  • the measuring and marking system of any preceding clause further including an extension bracket having a first leg extending in a generally radial direction having a first leg radially inner end and a first leg radially outer end, a second leg axially spaced from the first leg and extending in the generally radial direction having a second leg radially inner end and a second leg radially outer end, and a bracket plate connecting the first leg at the first leg radially outer end to the second leg at the second leg radially outer end, the extension bracket being connected to the generally axial arm portion of the measuring apparatus.
  • each of the plurality of pins including a tip end configured to be in contact with the surface of the abradable liner.
  • the measuring and marking system of any preceding clause further including a mounting plate having a first surface facing a first circumferential direction and a second surface facing a second circumferential direction opposite the first circumferential direction, the pins being arranged on the first surface of the mounting plate.
  • the measuring and marking system of any preceding clause further including at least one pin mounting portion disposed on the first surface of the mounting plate, the at least one pin mounting portion shaped to receive a pin of the plurality of the pins therethrough.
  • the measuring and marking system of any preceding clause further including at least one installation bracket disposed on the second surface of the mounting plate to removably attach the mounting plate to the extension bracket.
  • the measuring and marking system of any preceding clause further including an inclinometer configured to determine a rotational position of the measuring apparatus.
  • the measuring and marking system of any preceding clause further including at least one visual marking disposed on at least one of the slide plate or the generally axial arm portion indicating a calibration position.
  • the measuring and marking system of any preceding clause further including at least one visual marking disposed on at least one of the track or the generally axial arm portion indicating the first measuring position and the second measuring position.
  • the measuring and marking system of any preceding clause further including a first abutment at a first axial location of the track to stop the slide plate at the first measuring position and a second abutment at a second axial location of the track to stop the slide plate at the second measuring position.
  • a method of using a measuring and marking system for a turbine engine including a fan section having a nacelle and an abradable liner on the nacelle including mounting a measuring apparatus to a fan section of the turbine engine, the measuring apparatus including a measuring device to measure the profile of the abradable liner, mounting a marking apparatus to the nacelle, the marking apparatus including a mounting plate for mounting the marking apparatus to the nacelle and an arm portion extending from the mounting plate and having a plurality of slots to indicate a plurality of known locations along an axial length of the abradable liner, measuring the profile of the abradable liner with the measuring device through the plurality of slots in the arm portion of the marking apparatus at the plurality of known locations, generating a mapped surface profile of the abradable liner, and marking
  • any preceding clause further including comparing the mapped surface profile with a nominal profile, identifying repair locations at which differences between the mapped surface profile and the nominal profile occur, and marking the abradable liner at the repair locations.
  • the method of any preceding clause further including inserting a marker through at least one of the plurality of slots on the arm portion to inscribe a mark on the abradable liner.
  • any preceding clause further including positioning the measuring device at a first measuring position along a length of the generally axial arm portion, measuring, with the measuring device, the abradable liner at a first axial location of the abradable liner corresponding to the first measuring position, positioning the measuring device at a second measuring position along the length of the generally axial arm portion, and measuring, with the measuring device, the abradable liner at a second axial location of the abradable liner corresponding to the second measuring position.
  • the method of any preceding clause further including determining the rotational position of the measuring apparatus using an accelerometer. [0157] The method of any preceding clause, further including removing at least one fan blade from the fan section and mounting the measuring apparatus to the fan section such that the measuring apparatus is positioned at a space opened by removing the at least one fan blade. [0158] The method of any preceding clause, further including optically scanning the abradable liner to generate a mapped surface profile of the abradable liner and comparing the mapped surface profile against a reference profile.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Un système de mesure et de marquage pour une turbomachine comprend un appareil de mesure et un appareil de marquage. La turbomachine comprend une nacelle et un revêtement abradable sur la nacelle. L'appareil de mesure comporte un ensemble cadre présentant une partie bras généralement radiale, une partie bras généralement axiale, et un dispositif de mesure monté sur la partie bras généralement axiale pour mesurer un profil du revêtement abradable. L'appareil de marquage comprend une plaque de montage et une partie bras s'étendant à partir de la plaque de montage. La partie bras comporte une pluralité de fentes pour indiquer une pluralité d'emplacements connus sur une longueur axiale du revêtement abradable. L'appareil de mesure est conçu pour mesurer le profil du revêtement abradable à travers la pluralité de fentes dans la partie bras de l'appareil de marquage au niveau de la pluralité d'emplacements connus.
PCT/US2025/017905 2024-02-28 2025-02-28 Système de mesure et de marquage pour une turbomachine et procédé associé Pending WO2025184546A1 (fr)

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US63/558,924 2024-02-28

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240735A (en) * 1990-02-13 1991-08-14 Rolls Royce Plc Portable machine tool
US5240359A (en) * 1990-12-20 1993-08-31 Furmanite Australia Pty, Ltd. Machining apparatus
US20100030365A1 (en) * 2008-07-30 2010-02-04 Pratt & Whitney Combined matching and inspection process in machining of fan case rub strips
US20160121409A1 (en) * 2014-11-05 2016-05-05 Rolls-Royce Plc Machining tool
US20190360338A1 (en) * 2018-05-24 2019-11-28 General Electric Company In Situ Engine Component Repair
CN114683234A (zh) * 2022-05-09 2022-07-01 中国石油大学(华东) 一种管道动火连头快速测量画线自动化装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240735A (en) * 1990-02-13 1991-08-14 Rolls Royce Plc Portable machine tool
US5240359A (en) * 1990-12-20 1993-08-31 Furmanite Australia Pty, Ltd. Machining apparatus
US20100030365A1 (en) * 2008-07-30 2010-02-04 Pratt & Whitney Combined matching and inspection process in machining of fan case rub strips
US20160121409A1 (en) * 2014-11-05 2016-05-05 Rolls-Royce Plc Machining tool
US20190360338A1 (en) * 2018-05-24 2019-11-28 General Electric Company In Situ Engine Component Repair
CN114683234A (zh) * 2022-05-09 2022-07-01 中国石油大学(华东) 一种管道动火连头快速测量画线自动化装置

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