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EP3259453A1 - Revêtement de barrière thermique pour composant de turbine avec éléments de surface verticalement alignés et éléments de rainure à bifurcations multiples - Google Patents

Revêtement de barrière thermique pour composant de turbine avec éléments de surface verticalement alignés et éléments de rainure à bifurcations multiples

Info

Publication number
EP3259453A1
EP3259453A1 EP15820362.0A EP15820362A EP3259453A1 EP 3259453 A1 EP3259453 A1 EP 3259453A1 EP 15820362 A EP15820362 A EP 15820362A EP 3259453 A1 EP3259453 A1 EP 3259453A1
Authority
EP
European Patent Office
Prior art keywords
tbc
layer
groove
component
pattern
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.)
Withdrawn
Application number
EP15820362.0A
Other languages
German (de)
English (en)
Inventor
Kai Kadau
Jose Antonio PASCUAL-GUTIERREZ
Atin SHARMA
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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
Priority claimed from PCT/US2015/016331 external-priority patent/WO2015130528A1/fr
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP3259453A1 publication Critical patent/EP3259453A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • 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
    • 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
    • F01D5/14—Form or construction
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion

Definitions

  • the TBC has a TBC inner surface that is applied over and coupled to the anchoring layer and a TBC outer surface for exposure to combustion gas.
  • a planform pattern of engineered groove features (EGFs), having groove depths, is cut and formed into the TBC outer surface, penetrating the previously applied TBC layer.
  • the EGF pattern defines a planform pattern of overlying vertices, which are respectively in vertical alignment with an underlying corresponding ESF. At least three respective groove segments within the EGF pattern converge at each respective overlying vertex in a multifurcated pattern, so that each converging groove segment has at least two other adjoining converging groove segments at each overlying vertex.
  • FIG. 9 is a fragmentary view of a turbine component having an exemplary embodiment of a roughened bond coat ("RBC") layer applied over previously formed ESFs in a lower BC that was previously applied to the component substrate;
  • RBC roughened bond coat
  • turbine component surfaces that are exposed to combustion gasses are often constructed with a TBC layer for insulation of their underlying substrates.
  • Typical TBC coated surfaces include the turbine blades 92, the vanes 104 and 106, ring segments 120, and related turbine vane carrier surfaces and combustion section transitions 85.
  • the TBC layer for blade 92, vanes 104 and 106, ring segments 120, and transition 85 exposed surfaces are often applied by thermal sprayed or vapor deposition or solution/ suspension plasma spray methods, with a total TBC layer thickness of 300-2000 microns ( ⁇ ).
  • ESF cross sectional profiles, their planform array patterns, and their respective dimensions may be varied during design and manufacture of the turbine component to optimize thermal protection by inhibiting crack formation, crack propagation, and TBC layer spallation.
  • Different exemplary permutations of ESF cross sectional profiles their three-dimensional planform array patterns and their respective dimensions are shown in FIGs.5 -9.
  • ESF height, ESF ridge width, ridge spacing, and groove width between ridges are illustrated.
  • the ESFs are selectively arrayed in three-dimensional planform linear or polygonal patterns. For example, the ESF planform pattern of parallel vertical projections shown in FIGs.
  • the metallic substrate 391 also has a BC over layer 382 to which is affixed a TBC layer 396.
  • the TBC layer 396 further comprises a lower thermal barrier coating ("LTBC") layer 397 that has ESFs 394 formed therein for interlocking with the outer thermal barrier coat (“OTBC”) layer 398.
  • LTBC thermal barrier coating
  • the LTBC layer 397 with its ESFs 394 effectively functions as the anchoring layer for the OTBC layer 398.
  • the LTBC layer 397 has greater strength and ductility material properties than the OTBC layer 398, while the latter has greater thermal resistivity and brittleness material properties.
  • TBC layer 402 material bounded by the cracks and the cratered floor 406 protects the underlying metallic substrate 401 from further damage.
  • the engineered groove feature (“EGF") embodiments herein form cut or ablated grooves or other voids through the previously formed TBC layer outer surface to a desired depth.
  • the engineered groove feature ("EGF") planform pattern embodiments of FIGs. 21-28 incorporate converging groove segments, at least three of which, in repetitive patterns, share a common vertex.
  • each groove terminus at its common vertex furcates, or branches out to at least two other diverging grooves, which is analogous to an upstream water stream splitting into two downstream tributary streams.
  • the flow volume is divided between the two downstream tributaries.
  • the downstream flow volume in either tributary is less than the upstream flow volume.
  • Localized downstream material in the TBC or OTBC absorbs the induced, now bifurcated, or reduced applied stress that crossed the common vertex boundary. If the downstream-localized material has sufficient strength to avoid cracking, any upstream cracking is thereby arrested. If the downstream-localized material cracks, the applied stress (and possibly the crack) propagates in cascading fashion to the next one or more common vertices. Cascading propagation continues until stress is reduced sufficiently to arrest further crack formation.
  • FIG. 21 is illustrative of an exemplary embodiment of furcated, engineered groove features ("EGFs") in the TBC outer surface of a turbine blade, vane, or transition component 500.
  • the EGFs form a hexagonal- or honeycomb-shaped planform pattern of adjoining hexagons 502, respectively having six grooves 504, which terminate in six vertices 505.
  • Each pair of adjoining hexagons 502 shares a common groove segment 504A and a pair of two vertices 505 A, 505B.
  • Each shared common vertex 505 has three converging groove segments 504.
  • the trio of grooves 504 at each shared vertex 505 is oriented at 120 degrees.
  • the bifurcated, or in some embodiments multifurcated, groove geometry concept of FIG. 21 is useful for arresting crack propagation in the OTBC or TBC outer surface, whether the crack inducing stress in the TBC is caused by thermo- mechanical stress, induced by heating transients, or foreign object damage ("FOD") impact mechanical stress.
  • crack-inducing stress OA initiated within the boundaries of the hexagons 506 and 507 will either be dissipated by the TBC material volume within those hexagons (i.e., arrested therein), or the stress- induced crack in the TBC material will eventually intersect one or more of the groove segments 511, 512 in the circumscribing hexagonal boundary of hexagon 508.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Composants pour moteur à turbine (80), tels que des pales (92), des aubes (104, 106), des surfaces abradables (120) de segments de bague (110), ou des transitions (85), comportant des éléments de surface mis au point (ESF) alignés verticalement (632, 634) et des éléments de rainure mis au point (EGF) bifurqués (642, 652). Un motif de forme plane d'EGF (642, 652) est découpé dans la surface extérieure du revêtement de barrière thermique (TBC) du composant. Le motif EGF comprend un motif de forme plane de sommets superposés (644) respectivement en alignement vertical sur un ESF (632, 634) correspondant sous-jacent. Au moins trois segments de rainure respectifs (642, 652, 642) dans le motif EGF (640) convergent au niveau de chaque sommet respectif (644) selon un motif à multiples bifurcations, de sorte que les contraintes induites par des fissures sont atténuées en cascade, quand la contrainte (σA) est bifurquée (σB, σC) à chaque jointure de sommet.
EP15820362.0A 2015-02-18 2015-12-08 Revêtement de barrière thermique pour composant de turbine avec éléments de surface verticalement alignés et éléments de rainure à bifurcations multiples Withdrawn EP3259453A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
PCT/US2015/016331 WO2015130528A1 (fr) 2014-02-25 2015-02-18 Revêtement de barrière thermique de composant de turbine avec éléments de surface usinés d'isolation contre les fissures
PCT/US2015/016318 WO2015130526A2 (fr) 2014-02-25 2015-02-18 Revêtement formant une barrière thermique pour pièce de turbine présentant des éléments de rainure usinés pour isoler les fissures
PCT/US2015/064420 WO2016133580A1 (fr) 2015-02-18 2015-12-08 Revêtement de barrière thermique pour composant de turbine avec éléments de surface verticalement alignés et éléments de rainure à bifurcations multiples

Publications (1)

Publication Number Publication Date
EP3259453A1 true EP3259453A1 (fr) 2017-12-27

Family

ID=61334785

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15820362.0A Withdrawn EP3259453A1 (fr) 2015-02-18 2015-12-08 Revêtement de barrière thermique pour composant de turbine avec éléments de surface verticalement alignés et éléments de rainure à bifurcations multiples

Country Status (2)

Country Link
EP (1) EP3259453A1 (fr)
WO (1) WO2016133580A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10731482B2 (en) 2015-12-04 2020-08-04 Raytheon Technologies Corporation Enhanced adhesion thermal barrier coating
CN111805715B (zh) * 2020-07-23 2021-09-03 内蒙古元史文化传媒有限公司 一种陶瓷喷釉机

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8357454B2 (en) * 2001-08-02 2013-01-22 Siemens Energy, Inc. Segmented thermal barrier coating
US9194243B2 (en) * 2009-07-17 2015-11-24 Rolls-Royce Corporation Substrate features for mitigating stress
US9713912B2 (en) * 2010-01-11 2017-07-25 Rolls-Royce Corporation Features for mitigating thermal or mechanical stress on an environmental barrier coating

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2016133580A1 *

Also Published As

Publication number Publication date
WO2016133580A1 (fr) 2016-08-25

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