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WO2008110543A1 - Liaison de renforts d'une aube de turbine - Google Patents

Liaison de renforts d'une aube de turbine Download PDF

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Publication number
WO2008110543A1
WO2008110543A1 PCT/EP2008/052840 EP2008052840W WO2008110543A1 WO 2008110543 A1 WO2008110543 A1 WO 2008110543A1 EP 2008052840 W EP2008052840 W EP 2008052840W WO 2008110543 A1 WO2008110543 A1 WO 2008110543A1
Authority
WO
WIPO (PCT)
Prior art keywords
radius
contact surface
curvature
cross
turbine wheel
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.)
Ceased
Application number
PCT/EP2008/052840
Other languages
German (de)
English (en)
Inventor
Jaroslaw Szwedowicz
Bent Phillipsen
Thomas Secall Wimmel
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of WO2008110543A1 publication Critical patent/WO2008110543A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/181—Two-dimensional patterned ridged
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the invention relates to the field of turbomachines, in particular exhaust gas turbocharger for supercharged internal combustion engines, steam and gas turbines.
  • It relates to a turbine wheel with a plurality of blades, which each have at their free ends cover plates and a blade of such a turbine wheel.
  • Prior art impellers of thermal turbomachines such as steam turbines, gas turbines or turbines of exhaust gas turbochargers, have a plurality of blades, which are arranged on a hub which is rotatably mounted about a shaft.
  • the impellers often have shrouds - referred to in technical language as "Shroud" - at their radially outer, free ends.
  • a shroud is composed of individual segments (hereinafter referred to as cover plates), which are integrally connected to one blade each.
  • the cover plates are braced against each other by a torsional bias of the blades during assembly or in operation by the natural unwinding of the blades under the influence of centrifugal force.
  • the function of the cover plates is to improve the thermodynamic efficiency by minimizing the gap losses, as well as in the optimization of the vibration behavior by their damping and stiffening effect.
  • the design of the transition between the cover plates of two adjacent blades arranged according to various criteria in terms of thermodynamics, durability, surface pressure, assembly and manufacturing.
  • the object of the present invention is to improve the transition between the cover plates of adjacently disposed blades of a turbine wheel.
  • the transition between the cover plates of adjacently arranged rotor blades of a turbine wheel with a flat and an uneven contact surface is designed for this purpose.
  • planar contact is provided at one of the ends of the cover plate, the contact surface with at least two semi-cylindrical elevations (wrinkles) with radius r. These semi-cylindrical protrusions optionally have along their axis a curvature of radius R.
  • the mating contact surface of the cover plate is flat. By changing the cylinder radius r, the surface pressure can be varied and adapted to the cover plate size. In the case of purely level contact, uncontrolled local stress concentrations and misplacement of contact zones occur. This results in a different design of the wear on the cover plates of the same blade wreath. Small manufacturing differences between blade to blade within the tolerance have great effects on the formation of the contact on flat cover plate surfaces and lead to a detuning of the blade ring with it.
  • Pleated cover panels reduce the likelihood of misplacement. Because of the controllability of the contact, the blade kranzver michuri and thus the scattering of the blade natural frequencies is reduced. If the folded contact surface is provided with several, ie at least two rows of folds, forces and moments can be transmitted well at any time and a strong coupling between blades is ensured.
  • FIG. 1 is a view - perpendicular to the axis and directed radially inward - on a blade assembly according to the invention designed cover plate
  • FIG. 2 shows a section along M-II through a cover plate transition of the blade group according to FIG. 1, FIG.
  • Fig. 3 shows a guided along Ml-Ml section through the cover plate transition of Fig. 2, and 4 shows a section along IV-IV through the cover plate transition according to FIG. 2.
  • Fig. 1 shows an application example of the invention, a part of the blades of an axial turbine of a turbocharger.
  • the blades are arranged with blade roots in a blade carrier, the hub of the turbine wheel.
  • the hub of the turbine wheel is rotatably mounted on a shaft about an axis.
  • the terms “radial,” “axial,” and “circumferential direction” refer to this axis, and typically the blade roots are fir-tree shaped and axially inserted into oppositely-shaped grooves and axially secured body 10, which is exposed to the flow, that is to say the hot exhaust gases or the steam in the case of a steam turbine
  • the rotor blades At their radially outer, free ends, the rotor blades have a shroud which projects at least in sections in the axial direction over the blade body divided into many short segments, the cover plates 20, which are each integrally connected to a blade.
  • the cover plate of the ith blade has an uneven contact surface 21 in the contact region according to the invention.
  • the cover plate of the (i-1) -th blade has a flat contact surface 25.
  • Fig. 2 shows a view in the arrow direction on the section, which is guided along the designated M-Il, dashed line.
  • the uneven contact surface 21 has a plurality of elevations 22.
  • Fig. 3 - a view in the radial direction of the section, which is guided along the designated IM-III, dashed line - is shown - the elevations have a round, semicircular or semi-elliptical cross-section.
  • the flat contact surface 25 and one or more of the elevations 22 touch. It can be seen from the section in FIG. 4 taken along the broken line indicated by IV-IV that the elevations 22, or the underlying surface, has a curvature.
  • the curvature - exaggerated in FIG. 4 - extends radially from the view of the rotor blades, so that contact between the two contact surfaces of the two cover plates, regardless of any slight relative skew, certainly takes place.
  • a protrusion curved with radius R is pressed more and more against its planar counterpart, so that the "cylinder plane" contact with Hertz sets in.
  • the curvature of the elevation is denoted by R in the figures, where R is smaller than the radius r the individual surveys is significantly larger.
  • the surface of the protuberances has the surface shape of a tome, where a toms is a geometric body in which the points on the surface of a circle of radius R are the distance r, where r is less than R.
  • Such toroidal elevations with a radius of curvature R and a cylinder radius r on one of the contact surfaces of the cover plate avoid stress concentrations under load of the blade.
  • the surface pressure can be varied - a larger cylinder radius leads to a lower surface pressure - and an adaptation to the cover plate size can be made.
  • the cross-sectional radii r of the bumps in the radial direction, i. towards the root of the blade decrease, so that instead of the semi-cylindrical elevations, semi-conical elevations now result.
  • the corresponding Toms thus has along the radius of curvature R a variable cross-sectional radius r.
  • the elevations are made without the curvature defined by the radius R.
  • several surveys with different radius r are provided, which is maximum at the middle elevation and decreases towards the edge elevations.
  • a plurality of elevations of the same radius r are placed on a curved surface 21. The axis of this curvature points in the radial direction.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne une roue de turbine comprenant plusieurs aubes mobiles (10) qui sont placées sur un moyeu pouvant tourner autour d'un axe et qui présentent respectivement (10) des plaques de renfort (20) à leurs extrémités radialement externes. La transition entre deux aubes mobiles voisines dans la région des plaques de renfort est définie par une première surface de contact non plane (21) et par une seconde surface de contact plane (25). La surface de contact non plane est formée par une saillie toroïdale présentant un rayon de courbure R et un rayon de section transversale r, R étant supérieur à r. Le contact entre une surface non plane et une surface plane permet de mieux commander la position de contact, et des concentrations de contraintes indésirables peuvent être évitées.
PCT/EP2008/052840 2007-03-15 2008-03-11 Liaison de renforts d'une aube de turbine Ceased WO2008110543A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07104182.6 2007-03-15
EP07104182A EP1970535A1 (fr) 2007-03-15 2007-03-15 Contour de raccordement d'une aube de turbine

Publications (1)

Publication Number Publication Date
WO2008110543A1 true WO2008110543A1 (fr) 2008-09-18

Family

ID=38332479

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/052840 Ceased WO2008110543A1 (fr) 2007-03-15 2008-03-11 Liaison de renforts d'une aube de turbine

Country Status (2)

Country Link
EP (1) EP1970535A1 (fr)
WO (1) WO2008110543A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2015075045A (ja) * 2013-10-09 2015-04-20 三菱重工業株式会社 動翼及び回転機械
WO2016120013A1 (fr) * 2015-01-30 2016-08-04 Pharmathen S.A. Composition pharmaceutique comprenant de l'aprépitant et son procédé de préparation

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8075272B2 (en) * 2008-10-14 2011-12-13 General Electric Company Steam turbine rotating blade for a low pressure section of a steam turbine engine
CH699984A1 (de) * 2008-11-27 2010-05-31 Alstom Technology Ltd Verfahren zur Optimierung der Kontaktflächen von aneinander anstossenden Deckbandsegmenten benachbarter Schaufeln einer Gasturbine.
EP2696032A1 (fr) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Agencement d´aubes directrices pour une turbomachine
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
FR3161707A1 (fr) * 2024-04-30 2025-10-31 Safran Aircraft Engines Aube munie d'un temoin d'usure visuel

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE339565C (de) * 1916-12-08 1921-07-29 Ljungstroms Angturbin Ab Bildung dichter Stossfugen zwischen Turbinenschaufelkoepfen
US1423466A (en) * 1920-10-02 1922-07-18 Westinghouse Electric & Mfg Co Interlocking blade shroud
US3014695A (en) * 1960-02-03 1961-12-26 Gen Electric Turbine bucket retaining means
JPS54132011A (en) * 1978-04-04 1979-10-13 Toshiba Corp Turbine moving vane joint
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
JPH0216303A (ja) * 1988-07-04 1990-01-19 Toshiba Corp タービン動翼の結合装置
JPH08144705A (ja) * 1994-11-18 1996-06-04 Hitachi Ltd 蒸気タービン動翼
JPH0972202A (ja) * 1995-09-06 1997-03-18 Hitachi Ltd タービン動翼の連結構造及びその方法
JPH11159302A (ja) * 1997-11-25 1999-06-15 Hitachi Ltd 蒸気タービン動翼
EP1408199A1 (fr) * 2002-10-08 2004-04-14 United Technologies Corporation Configuration des fentes dans un segment d'un anneau de guidage
JP2004156557A (ja) * 2002-11-07 2004-06-03 Toshiba Corp タービン動翼の結合装置
JP2005256786A (ja) * 2004-03-12 2005-09-22 Mitsubishi Heavy Ind Ltd 回転機械、及び、回転機械の連成方法

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE339565C (de) * 1916-12-08 1921-07-29 Ljungstroms Angturbin Ab Bildung dichter Stossfugen zwischen Turbinenschaufelkoepfen
US1423466A (en) * 1920-10-02 1922-07-18 Westinghouse Electric & Mfg Co Interlocking blade shroud
US3014695A (en) * 1960-02-03 1961-12-26 Gen Electric Turbine bucket retaining means
JPS54132011A (en) * 1978-04-04 1979-10-13 Toshiba Corp Turbine moving vane joint
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
JPH0216303A (ja) * 1988-07-04 1990-01-19 Toshiba Corp タービン動翼の結合装置
JPH08144705A (ja) * 1994-11-18 1996-06-04 Hitachi Ltd 蒸気タービン動翼
JPH0972202A (ja) * 1995-09-06 1997-03-18 Hitachi Ltd タービン動翼の連結構造及びその方法
JPH11159302A (ja) * 1997-11-25 1999-06-15 Hitachi Ltd 蒸気タービン動翼
EP1408199A1 (fr) * 2002-10-08 2004-04-14 United Technologies Corporation Configuration des fentes dans un segment d'un anneau de guidage
JP2004156557A (ja) * 2002-11-07 2004-06-03 Toshiba Corp タービン動翼の結合装置
JP2005256786A (ja) * 2004-03-12 2005-09-22 Mitsubishi Heavy Ind Ltd 回転機械、及び、回転機械の連成方法

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2015075045A (ja) * 2013-10-09 2015-04-20 三菱重工業株式会社 動翼及び回転機械
WO2016120013A1 (fr) * 2015-01-30 2016-08-04 Pharmathen S.A. Composition pharmaceutique comprenant de l'aprépitant et son procédé de préparation

Also Published As

Publication number Publication date
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