EP2163734A2 - Dispositif de fixation d'aubes statoriques de turbine à gaz - Google Patents

Dispositif de fixation d'aubes statoriques de turbine à gaz Download PDF

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Publication number
EP2163734A2
EP2163734A2 EP09169441A EP09169441A EP2163734A2 EP 2163734 A2 EP2163734 A2 EP 2163734A2 EP 09169441 A EP09169441 A EP 09169441A EP 09169441 A EP09169441 A EP 09169441A EP 2163734 A2 EP2163734 A2 EP 2163734A2
Authority
EP
European Patent Office
Prior art keywords
vane
base
casing
hook
liner
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Withdrawn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
EP09169441A
Other languages
German (de)
English (en)
Other versions
EP2163734A3 (fr
Inventor
Christian Michael Hansen
Roger Claude Beharrysingh
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 EP2163734A2 publication Critical patent/EP2163734A2/fr
Publication of EP2163734A3 publication Critical patent/EP2163734A3/fr
Withdrawn legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the subject matter disclosed herein relates to gas turbine engines and, more particularly, to the attachment of vanes within a casing of a compressor of a gas turbine engine.
  • Stator vanes located in the back-end stages of a compressor are typically configured as singlets (one airfoil per attachment), and have a square base that includes an attachment hook on the forward and aft sides of the base.
  • the hooks are commonly constructed with a straight geometry such that when they are slid into the radial compressor casing grooves, the resulting reaction load distribution is concentrated at discrete (determinable) point locations or contact zones. This is due in part to the fact that the base of a vane is planar while the casing grooves are curved to some extent.
  • the stators are subject to an unsteady aerodynamic vibratory environment that causes vibration motion to be transmitted to the constraint points in the base hooks.
  • the responsive mode of vibration can result in a concentration of vibratory stress near these same attachment points.
  • These hook attachment points experience fretting related damage, including fretting wear and fretting fatigue, which significantly shortens the design life of the vane.
  • Vanes and case hooks experience fretting wear damage as indicated by stator rock-check measurements and pictures of case hook material degradation upon top-halving a unit. If the stator hook damage becomes excessive before repair, the stator airfoils can clash into the rotating stages in front of the stators, resulting in catastrophic damage to the flowpath components.
  • displacement measurements may be performed on the stator attachment bases while pushing the airfoil in a specified direction. These measurements, referred to as a "rock check", indicate the level of hook deterioration associated with the fretting wear and fretting fatigue experienced during operation. If the measured values exceed a specified threshold, then the stators are removed from the compressor. After the required inspection of the compressor discharge casing (CDC) grooves and of the stator attachment hooks, and depending upon the extent of the damage, the casing section can be machined out. After machining, a custom patch ring may then be retrofitted with a custom fit to provide a restored assembly groove for the stators. New stators may then be installed in the patch ring. However, while this solution may provide extended operation capability, it does not address the root cause of the problem. Another stopgap measure is to attach adjacent vanes together in packs through welding or bolting, which again does not address the root cause of the problem.
  • Another stopgap measure is to attach adjacent vanes together in packs through welding or bolting, which again does not address the root
  • the base hooks of a vane includes an approximate two times thicker radial geometry of the hooks, with a dimensioning and tolerancing scheme that results in a line-line to loose fit on the forward outer diameter (OD) hook surface and the same on the aft inner diameter (ID) hook surface. Tolerances are thus allowed to stack up on the opposite, non-critical, surfaces of the hooks (i.e., the forward ID hook surface and the aft OD hook surface).
  • the base of the vane is curved to match the curvature of the casing that the base resides in.
  • a material interface is provided between the vane base and the casing groove.
  • the material interface includes a metal alloy liner that interfaces between the base of the vane and the associated casing in which the vane is disposed.
  • a wear coating is provided on the vane attachment hooks. The liner protects the casing groove from wear damage, while the combination of the hook coating and the liner provide a wear coupling between the base of the vane and the casing. The wear coupling provides a barrier between the vane bases and the casing to decrease the wear rate.
  • FIG. 1 is a cross-section view of a compressor within a gas turbine engine
  • FIG. 2 illustrates the base of a vane according to an embodiment of the invention overlaid with a vane of the prior art
  • FIG. 3 illustrates the casing for the base of the vane according to an embodiment of the invention overlaid with the casing for the vane within the prior art
  • FIG. 4 illustrates a spring-loaded liner in accordance with an aspect of the invention.
  • FIG. 5 illustrates the base of a vane within a casing groove with the liner of FIG. 4 .
  • FIG. 1 there illustrated is a cross-section view of a compressor 100 within a gas turbine engine.
  • the compressor includes a discharge case 102 having a number of circular rows or stages 104, wherein each stage 104 has a plurality of vanes 106 that are located around the circumference of the casing 102 within a groove on the inner periphery of the casing 102.
  • the vanes 106 commonly are slide-in singlets with respect to the groove of the casing 102.
  • the stages 104 located towards the back end of the compressor 100 (i.e., on the right hand side of the compressor 100 when viewing FIG. 1 ) that experience the most fretting-related damage, as discussed hereinabove.
  • the material of the vanes 106 (particularly those in the back end of the compressor 100) typically comprises a 403cb stainless steel, while the compressor discharge case 102 may typically comprise a 2.25 CrlMo steel alloy material.
  • a geometry change to the base hooks 110, 112 of a vane 106 from that of the prior art includes an approximate two times thicker radial geometry of the hooks 110, 112, with a dimensioning and tolerancing scheme that results in a line-line to loose fit on the outer diameter (OD) of the forward hook surface 114 and the same on the inner diameter (ID) of the aft hook surface 116. Tolerances are thus allowed to stack up on the opposite, non-critical, surfaces of the hooks 110, 112 (i.e., the forward ID hook surface 118 and the aft OD hook surface 120).
  • FIG. 2 illustrates the outline of a base of a vane 106 having the geometry features of this aspect of the present invention.
  • FIG. 2 also illustrates the outline of a base of a vane 122 in the prior art, where the vane 106 overlays the vane 122 to illustrate the contrast between the size of the physical features of the hooks of both vanes 106, 122.
  • the base of the vane 106 including the hooks 110, 112
  • the base of the vane 122 of the prior art has no curvature and is straight or planar.
  • An attachment geometry based on curved or radial hooks 110, 112 (instead of planar hooks as in the prior art) with the critical load surfaces (i.e., the forward OD hook surface 118 and the aft ID hook surface 120) thereby achieves a line on line assembly fit, such that the load surfaces of the vanes 106 are established at assembly, minimizing any rigid body relative motion of the hooks 110, 112 to the casing 102, and optimizing the load pressure distribution on the surface of the hooks 110, 112.
  • the optimized load distribution results in the lowest possible pressure placed on the hooks 110, 112, which is the primary parameter in reducing fretting wear.
  • the hooks 110, 112 of the vanes 106 of this aspect of the invention are thicker and longer than the prior art designs.
  • the dimensioning and tolerancing scheme for the vane hooks or rails 110, 112 are tighter, allowing for better fit-ups and reduced manufacturing variation. Assembly clearances are increased over that of the prior art for ease of assembly. Because durability of the vanes 106 and the case 102 has been increased, customer down time is reduced.
  • FIG. 2 also illustrates a groove 124 formed in the vane 106 of an embodiment of the invention.
  • the groove 124 acts as an error-proofing feature that ensures proper assembly of the vane 106 to the casing 102.
  • FIG. 3 illustrates the groove portion 128 of the casing 102 for the base of the vane 106 according to an embodiment of the invention overlaid with the corresponding groove portion 130 of the casing 132 for a vane within the prior art.
  • FIG. 3 illustrates the contrast in size between these features. From FIG. 3 it can be seen that the groove portion 128 of the casing 102 that accommodates the base of the vane 106 has been made larger to accommodate the now larger hooks 110, 112 of the vane 106 according to an aspect of the invention.
  • a material interface is provided between the base of the vane 106 and the groove 128 of the casing 102.
  • the material interface includes a pair of spring-loaded liners 140 that interface between the hooks 110, 112 of the base of the vane 106 and the associated groove portion 128 of the casing 102.
  • Fig. 4 illustrates the liner 140 in an unloaded position.
  • the liner 140 may comprise a cobalt-based metal alloy that has a thickness of, e.g., 10 mils.
  • the liners 140 may be configured within the casing 102 such that more than one vane 106 (for example, 16 vanes per liner) contacts a single pair of liners 140 within the compressor casing 102.
  • the liner material may comprise a stainless steel with a thermal spray coating on the inner surface of the liner 140.
  • the primary purpose of the liner 140 is to protect the casing groove 128 from wear damage, which is accomplished by the material comprising the liner 140.
  • two liners 140 are provided (one for each hook 110, 112) and the liners 140, which are easily assembled in between the hooks 110, 1120 and the casing 102, completely surround the hooks or rails 110, 112 of the base of the vane 106.
  • a hard-face wear coating may be provided on the surface of the vane attachment hooks 110, 112.
  • the hook coating may comprise a metal alloy, for example, a cobalt-based alloy that may comprise that sold under the trademark Stellite®.
  • the coating may be approximately 5 mils thick and may comprise a thermal spray coating applied by the high velocity oxygen fuel (HVOF) process.
  • HVOF high velocity oxygen fuel
  • the hook coating and the liner 140 together provide an improved wear couple for the base of the vane 106 and the casing groove 128.
  • the cobalt-based wear couple provides a barrier between the base of each vane 106 and the casing 102 to decrease the wear rate when compared to the bare 403cb stainless steel vane and 2.25Cr1Mo steel alloy case materials used in the prior art.
  • the improved wear couple provides a wear liner interface to protect the casing material, and provide a load surface for the critical hook surfaces of the vanes.
  • the wear couple liner and the hard-face coating on the hooks 110, 112 provides a long term durable interface in a dynamic environment. Suitable alternative wear coatings include tungsten carbide, chromium carbide, T800, T400, T400C (all cobalt-based materials) or other cobalt-based materials.
  • Embodiments of the present invention have been described and illustrated herein for use with stator vanes that are located within a compressor of a gas turbine engine. However, various aspects of the present invention contemplate other types of vanes for use therewith. Also, embodiments of the invention can be retrofitted in the field onto older vanes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09169441A 2008-09-12 2009-09-04 Dispositif de fixation d'aubes statoriques de turbine à gaz Withdrawn EP2163734A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/209,314 US20100068050A1 (en) 2008-09-12 2008-09-12 Gas turbine vane attachment

Publications (2)

Publication Number Publication Date
EP2163734A2 true EP2163734A2 (fr) 2010-03-17
EP2163734A3 EP2163734A3 (fr) 2012-11-07

Family

ID=41258938

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09169441A Withdrawn EP2163734A3 (fr) 2008-09-12 2009-09-04 Dispositif de fixation d'aubes statoriques de turbine à gaz

Country Status (3)

Country Link
US (1) US20100068050A1 (fr)
EP (1) EP2163734A3 (fr)
CN (1) CN101672300A (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2434107A3 (fr) * 2010-09-23 2017-01-11 Rolls-Royce plc Module d'un moteur de turbine avec revêtement anti-usure
EP2612998A3 (fr) * 2012-01-05 2017-07-12 United Technologies Corporation Garniture de fixation intégrée d'aube de stator et ressort amortisseur
EP2508715A3 (fr) * 2011-04-06 2018-01-10 Rolls-Royce plc Ensemble d'aubes de guidage
FR3120911A1 (fr) * 2021-03-16 2022-09-23 Safran Aircraft Engines Aube comprenant un membre d’attache résistant au frottement et roue mobile comprenant une telle aube d’une turbine axiale de turbomachine

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FR2986836B1 (fr) * 2012-02-09 2016-01-01 Snecma Tole annulaire anti-usure pour une turbomachine
US20140030084A1 (en) * 2012-07-24 2014-01-30 General Electric Company Article of manufacture for turbomachine
US9650905B2 (en) * 2012-08-28 2017-05-16 United Technologies Corporation Singlet vane cluster assembly
US9353649B2 (en) * 2013-01-08 2016-05-31 United Technologies Corporation Wear liner spring seal
US9796055B2 (en) * 2013-02-17 2017-10-24 United Technologies Corporation Turbine case retention hook with insert
US10801342B2 (en) * 2014-04-10 2020-10-13 Raytheon Technologies Corporation Stator assembly for a gas turbine engine
CA2951425C (fr) * 2014-06-12 2019-12-24 General Electric Company Ensemble de suspension de carenage
PL415487A1 (pl) * 2015-12-31 2017-07-03 General Electric Company Formowana kompozytowa osłona chroniąca przed zużyciem krawędzi dla złącza w postaci wpustu V-kształtnego i łopatki V-kształtnej
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FR3085412B1 (fr) * 2018-08-31 2020-12-04 Safran Aircraft Engines Secteur de distributeur d'une turbomachine comprenant une encoche anti-rotation a insert d'usure
US11047250B2 (en) * 2019-04-05 2021-06-29 Raytheon Technologies Corporation CMC BOAS transverse hook arrangement
US12359575B2 (en) * 2022-12-13 2025-07-15 Rtx Corporation Machinable coating with thermal protection
US12492640B2 (en) * 2024-05-30 2025-12-09 General Electric Company Turbine engine including a vane support and a vane
US20260028913A1 (en) * 2024-07-25 2026-01-29 Kenneth Knecht Gas turbine compressor stator blade

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2434107A3 (fr) * 2010-09-23 2017-01-11 Rolls-Royce plc Module d'un moteur de turbine avec revêtement anti-usure
EP2508715A3 (fr) * 2011-04-06 2018-01-10 Rolls-Royce plc Ensemble d'aubes de guidage
EP2612998A3 (fr) * 2012-01-05 2017-07-12 United Technologies Corporation Garniture de fixation intégrée d'aube de stator et ressort amortisseur
FR3120911A1 (fr) * 2021-03-16 2022-09-23 Safran Aircraft Engines Aube comprenant un membre d’attache résistant au frottement et roue mobile comprenant une telle aube d’une turbine axiale de turbomachine

Also Published As

Publication number Publication date
EP2163734A3 (fr) 2012-11-07
US20100068050A1 (en) 2010-03-18
CN101672300A (zh) 2010-03-17

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