EP1890010A2 - Ensemble de virole de turbine en céramique - Google Patents

Ensemble de virole de turbine en céramique Download PDF

Info

Publication number
EP1890010A2
EP1890010A2 EP07253097A EP07253097A EP1890010A2 EP 1890010 A2 EP1890010 A2 EP 1890010A2 EP 07253097 A EP07253097 A EP 07253097A EP 07253097 A EP07253097 A EP 07253097A EP 1890010 A2 EP1890010 A2 EP 1890010A2
Authority
EP
European Patent Office
Prior art keywords
ring
ceramic shroud
shroud
ceramic
clamp ring
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.)
Granted
Application number
EP07253097A
Other languages
German (de)
English (en)
Other versions
EP1890010A3 (fr
EP1890010B1 (fr
Inventor
Jun Shi
Kevin E. Green
Shaoluo L. Butler
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 US11/502,079 external-priority patent/US7665960B2/en
Priority claimed from US11/502,212 external-priority patent/US7771160B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP1890010A2 publication Critical patent/EP1890010A2/fr
Publication of EP1890010A3 publication Critical patent/EP1890010A3/fr
Application granted granted Critical
Publication of EP1890010B1 publication Critical patent/EP1890010B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics

Definitions

  • the present invention relates to an outer shroud assembly for use in a gas turbine engine. More particularly, the present invention relates to a ceramic shroud assembly including a metal clamp ring shrink fitted around a ceramic shroud ring, where the metal clamp ring is configured to attach to a turbine engine casing.
  • metal alloy metal alloy
  • ceramic ceramic materials are able to withstand higher operating temperatures and require less cooling than metals. Ceramic components are also generally less sensitive to thermal expansion than metal components because ceramic materials generally exhibit a lower coefficient of thermal expansion (CTE) than a metal.
  • a static shroud ring is disposed radially outwardly from a turbine rotor, which includes a plurality of blades radially extending from a disc.
  • the shroud ring at least partially defines a flow path for combustion gases as the gases pass from a combustor through turbine stages.
  • some gas turbine engines are able to reduce the clearance by utilizing a ceramic shroud ring rather than a metal shroud ring.
  • a ceramic shroud ring undergoes less thermal distortion during engine operation than many metal shroud rings due to the higher stiffness, lower CTE, and higher thermal conductivity of ceramic materials as compared to metals.
  • a ceramic shroud requires less cooling than a metal shroud because ceramic material is capable of withstanding higher operating temperatures.
  • the present invention in one aspect provides a ceramic shroud assembly that allows a ceramic shroud to be attached to a metal gas turbine engine casing in a manner that compensates for a difference in CTEs between the ceramic and metal materials.
  • the ceramic shroud assembly includes a metal clamp ring shrink fitted around a ceramic shroud and a compliant and insulating layer positioned between the ceramic shroud and the clamp ring.
  • the metal clamp ring is configured to attach to the gas turbine engine casing, thereby attaching the ceramic shroud to the casing.
  • the ceramic shroud assembly also includes a ring configured to axially restrain the ceramic shroud.
  • FIG. 1 is a partial cross-sectional view of gas turbine engine 10, which includes combustion chamber 12, turbine engine casing 13, and first compressor turbine stage 14.
  • First compressor turbine stage 14 includes a plurality of nozzle vanes 16 circumferentially arranged about casing 13, rotor blades 18 radially extending from a rotor disc (not shown), and ceramic shroud assembly 20 in accordance with the present invention.
  • Shroud assembly 20 is attached to turbine engine casing 13.
  • hot gases from combustion chamber 12 enter first high pressure turbine stage 14 through turbine inlet region 22. More specifically, the hot gases move downstream (indicated by arrow 24) in an aft direction past a plurality of nozzle vanes 16.
  • Nozzle vanes 16 direct the flow of hot gases past rotor blades 18, which radially extend from a rotor disc (not shown), as known in the art.
  • Rotor blades 18 may be attached to the rotor disk using a mechanical attachment, such as a dovetail attachment, or may be integral with the rotor (i.e., an integrally bladed rotor).
  • shroud assembly 20 defines an outer surface for guiding the flow of hot gases through first compressor turbine stage 14, while platform 21 positioned on an opposite end of rotor blade 18 from shroud assembly 20 defines an inner flow path surface.
  • Ceramic shroud assembly 20 in accordance with the present invention includes clamp ring 26, ceramic shroud 28, interlayer 30, which is positioned between clamp ring 26 and ceramic shroud 28, and axial restraint ring 32.
  • Shroud assembly 20 allows for relative movement between ceramic and metal parts (i.e., between metal casing 13 and ceramic shroud 28), which helps compensate for a difference in thermal growth between metal casing 13 and ceramic shroud 28.
  • metal casing 13 and ceramic shroud 28 are directly interfaced, stresses may generate at the interface because of the difference in CTE values between the ceramic and metal materials. The stresses may cause shroud 28 to fail.
  • Shroud assembly 20 of the present invention allows ceramic shroud 28 to be attached to metal casing 13 using metal clamp ring 26, which is configured to attach to metal turbine casing 13, such as by a mechanical attachment means (e.g., bolts).
  • metal clamp ring 26 is shrink fit around ceramic shroud 28 and interlayer 30, which allows metal clamp ring 26 and shroud 28 to be attached, yet allows for relative thermal growth therebetween without generating undue stress on shroud 28.
  • Shrink fitting is a process in which heat is used to produce a very strong joint between two components, one of which is at least partially inserted into the other. In the present invention, clamp ring 26 is heated to a "preheat temperature,” which causes clamp ring 26 to expand.
  • clamp ring 26 Upon expansion, ceramic shroud 28 and interlayer 30 are inserted into clamp ring 26. After clamp ring 26 cools, clamp ring 26 contracts, thereby compressing (or “clamping") ceramic shroud 28 and interlayer 30. In this way, clamp ring 26 holds shroud assembly 20 together by interference fit.
  • Clamp ring 26 is formed of a metal, such as a nickel-base alloy. Front face 26A of clamp ring 26 abuts axial restraint ring 32, while aft face 26B abuts an aft surface of ceramic shroud assembly 20. Flange 26C of clamp ring 26 is configured to mate with casing 13. In alternate embodiments, flange 26C may extend from clamp ring 26 in a different direction or may be removed from clamp ring 26, depending on a structure of casing 13. In one embodiment, clamp ring 26 and turbine casing 13 exhibit similar CTE values.
  • clamp ring 26 and turbine casing 13 exhibit different CTE values and clamp ring 26 is attached to turbine casing 13 using an attachment means allowing for relative growth therebetween (e.g., a U-slot).
  • metal clamp ring 26 and metal casing 13 interface, rather than metal casing 13 interfacing directly with ceramic shroud 28, which helps prevent the formation of stresses at an interface between ceramic shroud 28 and metal casing 13.
  • Clamp ring 26 includes a plurality of cooling holes 27, which are circumferentially positioned near front face 26A.
  • casing 13 includes a plurality of cooling holes 36.
  • Air seal 38 may optionally be placed near aft face 26B of clamp ring 26 in order to help direct cooling air from cooling holes 36 through cooling holes 27, and minimize cooling air leakage.
  • Ceramic shroud 28 is a continuous uninterrupted annular ring having a substantially constant thickness (measured in a radial direction). Of course, in alternate embodiments, shroud 28 may also be formed of a plurality of split shroud segments in an annular arrangement. However, a continuous ring improves sealing about the outer flow path through first compressor stage 14, which helps increase the efficiency of turbine engine 10 by minimizing leakages of hot gases. Ceramic shroud 28 may be formed of any suitable material known in the art, such as silicon nitride.
  • Interlayer 30 is formed of a thermally insulating and compliant material exhibiting a relatively high compressive yield stress (e.g., greater than about 6 x 10 6 kilopascals (kPa)).
  • interlayer 30 is formed of mica, which exhibits a through thickness CTE of about 15 x 10 -6 /°C to about 20 x 10 -6 /°C.
  • clamp ring 26 and shroud 28 During operation of gas turbine engine 10, high operating temperatures cause clamp ring 26 and shroud 28 to expand (i.e., thermal growth).
  • Clamp ring 26 is formed of a metal
  • shroud 28 is formed of a ceramic material
  • clamp ring 26 is likely to encounter more thermal growth than shroud 28 during operation of gas turbine engine 10.
  • interlayer 30 is positioned between clamp ring 26 and shroud 28.
  • Interlayer 30 is formed of a compliant and thermally insulative material. The compliancy of interlayer 30 helps absorb the thermal growth mismatch between clamp ring 26 and 28.
  • interlayer 30 is also thermally insulative, interlayer 30 also helps isolate clamp ring 26 from combustion gases and heat flow from shroud 28 (which is at a high temperature due to the flow of hot gases between platform 21 and shroud 28) to clamp ring 26. Finally, interlayer 30 also helps prevent any chemical reaction between clamp ring 26 and shroud 28, which are formed of different materials.
  • Interlayer 30 includes first portion 30A and second portion 30B.
  • a thickness of first portion 30A is greater than a thickness of second portion 30B.
  • first portion 30A of interlayer 30 is about 2.54 millimeters (100 mils) thick, while second portion 30B is about 1.27 millimeters (50 mils) thick.
  • first portion 30A of interlayer 30 contacts both clamp ring 26 and shroud 28.
  • First portion 30A is preferably substantially centered in the middle (i.e., midway between front axial face 28A and aft axial face 28B) of shroud 28 so that shroud 28 does not cone under the compressive stress of clamp ring 26.
  • Second portion 30B covers approximately one-third of an aft portion (i.e., the portion closest to aft axial face 28B) of shroud 28, as well as aft axial face 28B.
  • Second portion 30B of interlayer 30 thermally insulates the aft portion of shroud 28, as well as aft axial face 28, which helps to even out a temperature distribution across shroud 28.
  • the percentage of shroud 28 covered by interlayer 30 may be adjusted, depending upon the desired temperature distribution across shroud 28.
  • Axial restraint ring 32 abuts front face 26A of clamp ring 26A and front face 28A of shroud 28, and helps restrain shroud 28 in an axial direction. Details of one embodiment of axial restraint ring 32 are described in reference to FIG. 4.
  • FIG. 2 is a perspective assembly view of shroud assembly 20, which illustrates a process of shrink fitting metal clamp ring 26 around shroud 28 and interlayer 30.
  • Metal clamp ring 26 has radius R 1 and includes a plurality of cooling holes 27 near front face 26A.
  • clamp ring 26 is heated to a preheat temperature in order to expand clamp ring 26 to a size sufficient enough to receive shroud 28 and interlayer 30.
  • metal clamp ring 26 expands to metal clamp ring 26 (shown in phantom) having radius R 2 .
  • the difference between R 1 and R 2 depends upon the material which metal clamp ring 26 is constructed of, as well as the preheat temperature. As those skilled in the art recognize, in general, the higher the preheat temperature, the greater the difference between R 1 and R 2 .
  • shroud 28 and interlayer 30, which are typically at room temperature (approximately 21-23 °C) (i.e., unexpanded), are introduced into expanded clamp ring 26.
  • interlayer 30 is attached to shroud 28 before being introduced into clamp ring 26. Because clamp ring 26 is expanded to radius R 2 , shroud 28 and interlayer 30, which are approximately at room temperature, are able to fit within clamp ring 26.
  • First portion 30A of interlayer 30 has outer radius R 3
  • second portion 30B of interlayer 30 has outer radius R 4 , which is less than radius R 3 .
  • outer radius R 3 of first portion 30A is approximately equal to radius R 2 of heated and expanded clamp ring 26.
  • the preheat temperature of clamp ring 26 affects a clamp load which is applied to ceramic shroud 28 and interlayer 30.
  • the higher the preheat temperature the higher the clamp load and the higher the stress in clamp ring 26 for a given radius at the preheat temperature (after metal clamp ring 26 is brought back down to room temperature).
  • This relationship is attributable to the fact that in a typical shrink fit process, the amount clamp ring 26 expands (i.e., the difference between R 1 and R 2 ) is generally proportional to the amount clamp ring 26 shrinks upon being returned to room temperature. The more clamp ring 26 shrinks, the greater the stresses generated in clamp ring 26 and the greater the load clamp ring 26 exerts on shroud 28.
  • the preheat temperature is chosen based on the desirable stresses and clamp loads.
  • the preheat temperature is preferably low enough to prevent metal clamp ring 26 from exceeding its yield limit or creep strength.
  • the preheat temperature is preferably high enough to achieve a clamp load that is sufficient enough to hold shroud assembly 20 together during all engine 10 (FIG. 1) operation levels (e.g., from start-up to shutdown).
  • clamp ring 26 is formed of Inconel 783, which is an oxidation-resistant nickel-based superalloy.
  • Inconel 783 exhibits a yield stress of about 7.58 x 10 6 kPa (about 110 ksi). At each of the preheat temperatures in Table 1, the maximum Von Mises stress for clamp ring 26 is below the yield stress of Inconel 783. Therefore, for clamp ring 26 formed of Inconel 783, preheat temperatures ranging from about 204 °C to about 316 °C are suitable.
  • Table 2 illustrates the results of the finite element analysis for stresses and clamp loads during engine 10 start-up conditions: Table 2: Stresses and Clamp Loads during Engine Start-up Conditions Preheat Temperature (°C) Maximum Von Mises Stress in Metal Clamp (kPa) First Principal Stress in Ceramic Shroud at Engine Steady State Conditions (kPa) Minimum Clamp Load (kN) 260 (500 °F) 6.21 x 10 5 (90 ksi) 4.83 x 10 4 (7 ksi) 22.24 (5000 lbf) 316 (600 °F) 6.89 x 10 5 (100 ksi) 6.21 x 10 4 (9 ksi) 40.03 (9000 lbf)
  • Table 3 illustrates the results of the finite element analysis for stresses and clamp loads during engine 10 shutdown conditions: Table 3: Stresses and Clamp Loads During Engine Shutdown Conditions Preheat Temperature (°C) Maximum Von Mises Stress in Metal Clamp (kPa) First Principal Stress in Ceramic Shroud at Engine Steady State Conditions (kPa) Minimum Clamp Load (kN) 260 (500 °F) 4.14 x 10 5 (60 ksi) 3.45 x 10 4 (5 ksi) 7.18 (1600 lbf) 316 (600 °F) 6.21 x 10 5 (90 ksi) 1.45 x 10 5 (21 ksi) 9.34 (2100 lbf)
  • clamp ring 26 is formed of Inconel 783
  • the stresses in clamp ring 26 remain below the yield stress of Inconel 783 (about 7.58 x 10 5 kPa) during engine 10 start-up and shutdown conditions when the preheat temperature of clamp ring 26 is up to about 316 °C.
  • a preheat temperature of about 316 °C is suitable for an Inconel 783 clamp ring 26 (or a material exhibiting similar properties).
  • shroud 28 contracts faster than clamp ring 26 and it is critical to maintain a minimum clamp load.
  • minimum clamp loads drop compared to clamp loads at steady-state engine 10 operating conditions (detailed in Table 1).
  • a concern at engine 10 shutdown is whether clamp ring 26 will apply sufficient clamp load on shroud 28.
  • the preheat temperature is dependent upon the desirable clamp loads. For example, if a clamp load of approximately 7.18 kN needs to be maintained at all times to maintain the integrity of shroud assembly 20, the lower limit of a preheat temperature is about 260 °C.
  • ceramic shroud 28 It is also desirable for ceramic shroud 28 to remain under compression for substantially all engine conditions because ceramic material is stronger in a compressive stress state than in a tensile stress state.
  • the preheat temperature is selected in the range of about 260 °C to about 316 °C, ceramic shroud 28 remains under compression for all engine conditions, while at the same time, clamp ring 26 operates below its yield limit.
  • FIG. 3' is a perspective view of an alternate embodiment of clamp ring 40, which includes a plurality of axially-extending slots 42 extending from front face 40A to aft face 40B, and a plurality of cooling holes 44. Slots 42 increase the radial compliance of clamp ring 40 and allow a shroud (e.g., shroud 28 of FIG. 1) disposed inside clamp ring 40 to expand without generating undue stress on the shroud or clamp ring 40.
  • a shroud e.g., shroud 28 of FIG.
  • FIG. 4 is a plan view of axial restraint ring 32, which includes slot 45 and a plurality of radially extending cuts 46 along inner radius 32A.
  • axial restraint ring 32 is a snap ring, which, as known in the art, is a discontinuous annular ring that can be distorted to decrease its diameter.
  • a force is applied to axial restraint ring 32 in order to decrease its diameter, as shown in phantom.
  • Axial restraint ring 32 is then fit into turbine casing 13 (shown in FIG.
  • Axial restraint ring 32 is formed of any suitable material, such as a nickel-based alloy (e.g., Inconel 625).
  • Radial cuts 46 in axial restraint ring 32 define a plurality of radial tabs 48 that are configured to push against front face 28A of shroud 28 (shown in FIG. 1) in order to axially restraint shroud 28 and prevent movement of shroud 28 in an upstream direction 25 (shown in FIG. 1).
  • tabs 48 are coated with a coating that reduces heat transfer from shroud 28 to tabs 48 and prevents reaction between axial restraint ring 32 and shroud 28.
  • the coating may be, for example, a ceramic thermal barrier coating known in the art, such as yttria stabilized zirconia.
  • Radial cuts 46 also allow for cooling air from chamber 34 (which has flowed through cooling holes 36 in casing 13 and cooling holes 27 in metal clamp ring 26) to cool axial restraint ring 32.
  • FIG. 5 is a partial perspective cross-sectional view of turbine engine casing 50, turbine vane 52, turbine rotor 53, and a second embodiment of ceramic shroud assembly 54, which is similar to ceramic shroud assembly 20 of FIG. 1, except that shroud 58 is tapered at angle S with respect to line 66, which is parallel to an axial centerline of turbine engine 10, from front face 58A to aft face 58B. In the embodiment illustrated in FIG. 5, angle S is about 10 degrees.
  • Shroud assembly 54 further includes clamp ring 56, which is attached to turbine casing 50, interlayer 60, first axial restraint ring 62, and second axial restraint ring 64.
  • Clamp ring 56 is also tapered to match shroud 58, such that clamp ring 56 and shroud 58 have similar contours.
  • Interlayer 60 is similar to interlayer 30 of FIG. 1.
  • First axial restraint ring 62 helps locate clamp ring 56 such that clamp ring 56 does not move in an upstream direction (indicated by arrow 25).
  • Taper angle S of shroud 58 is governed by a frictional coefficient that is necessary to keep shroud 58 located axially (i.e., prevent shroud 58 from moving in aft (or downstream) direction 24 or upstream direction 25).
  • a frictional coefficient that is necessary to keep shroud 58 located axially (i.e., prevent shroud 58 from moving in aft (or downstream) direction 24 or upstream direction 25).
  • taper angle S may be up to 31° with respect to line 66 without compromising the axial location of shroud 58.
  • FIG. 5 also provides an axial force that pushes shroud 58 in the aft direction (indicated by arrow 24), against aft surface 56B of clamp ring 56, thereby helping to prevent shroud 58 from moving in the aft direction 24.
  • front face 58A of shroud 58 is axially restrained by second axial restraint ring 64.
  • FIG. 6 is a perspective view of a third embodiment of shroud assembly 70 including clamp ring 72 and shroud 74.
  • Shroud assembly 70 also includes an interlayer (not shown) positioned between clamp ring 72 and shroud 74.
  • Shroud assembly 70 is similar to shroud assembly 20 of FIG. 1, except that shroud 74 includes a plurality of anti-rotation tabs 76, which are configured to engage with corresponding openings 78 in clamp ring 72.
  • Anti-rotation tabs 76 circumferentially locate shroud 74 with respect to clamp ring 72, and help limit rotational movement of shroud 74 about center axis 80.
  • shroud 74 includes three equally spaced anti-rotation tabs 76.
  • shroud 74 may include any suitable number of anti-rotation tabs 76, such as two, four, five, etc., as well as any suitable arrangement (e.g., equally or unequally spaced).
  • clamp ring 72 includes a corresponding number of openings 78.
  • FIG. 7 is a partial perspective cross-sectional view of gas turbine engine 82, which includes turbine casing 84 (similar to turbine casing 13 of FIG. 1), stationary vane 86 (similar to stationary vane 16 of FIG. 1), turbine rotor 88 (similar to rotor blade 18 of FIG. 1), and a fourth embodiment of shroud assembly 90.
  • Shroud assembly 90 includes clamp ring 92, shroud 94, and an interlayer (not shown in FIG. 7) positioned between clamp ring 92 and shroud 94.
  • shroud 94 includes anti-rotation tab 96, which is configured to engage with a corresponding opening 98 in clamp ring 92.
  • openings 98 in clamp ring 92 each include leaf spring 100.
  • Leaf spring 100 allows opening 98 to be adaptable to different anti-rotation tab 96 locations by providing a range of locations for which anti-rotation tab 96 may be introduced into opening 98, while still allowing opening 98 to engage with anti-rotation tab 96.
  • Leaf spring 100 preferably has a controlled stiffness that keeps shroud 94 in position without introducing high stress in shroud 94.
  • a second leaf spring is located on opening 98 opposite leaf spring 100.
  • Shroud assembly 90 may be modified to include any suitable number of leaf springs.
  • shroud assembly in accordance with the present invention has been described in reference to a first high pressure turbine stage, the inventive shroud assembly is suitable for incorporation into any turbine stage of a gas turbine engine, as well as any other application of a shroud ring.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07253097.5A 2006-08-10 2007-08-07 Ensemble de virole de turbine en céramique Active EP1890010B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/502,079 US7665960B2 (en) 2006-08-10 2006-08-10 Turbine shroud thermal distortion control
US11/502,212 US7771160B2 (en) 2006-08-10 2006-08-10 Ceramic shroud assembly

Publications (3)

Publication Number Publication Date
EP1890010A2 true EP1890010A2 (fr) 2008-02-20
EP1890010A3 EP1890010A3 (fr) 2011-08-10
EP1890010B1 EP1890010B1 (fr) 2016-05-04

Family

ID=38828710

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07253097.5A Active EP1890010B1 (fr) 2006-08-10 2007-08-07 Ensemble de virole de turbine en céramique

Country Status (1)

Country Link
EP (1) EP1890010B1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8167546B2 (en) 2009-09-01 2012-05-01 United Technologies Corporation Ceramic turbine shroud support
WO2013110792A1 (fr) * 2012-01-26 2013-08-01 Alstom Technology Ltd Élément formant stator pourvu d'une bague intérieure segmentée pour une turbomachine
US8801372B2 (en) 2006-08-10 2014-08-12 United Technologies Corporation Turbine shroud thermal distortion control
US8956700B2 (en) 2011-10-19 2015-02-17 General Electric Company Method for adhering a coating to a substrate structure
EP2313615B1 (fr) 2008-08-15 2016-03-23 Alstom Technology Ltd Dispositif d'aubes d'une turbine à gaz
CN108691577A (zh) * 2017-04-10 2018-10-23 清华大学 涡轮发动机的主动间隙控制结构

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4087199A (en) 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3019920C2 (de) * 1980-05-24 1982-12-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur äußeren Ummantelung der Laufschaufeln von Axialturbinen für Gasturbinentriebwerke
US4639388A (en) * 1985-02-12 1987-01-27 Chromalloy American Corporation Ceramic-metal composites
US6910853B2 (en) * 2002-11-27 2005-06-28 General Electric Company Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4087199A (en) 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8801372B2 (en) 2006-08-10 2014-08-12 United Technologies Corporation Turbine shroud thermal distortion control
EP2313615B1 (fr) 2008-08-15 2016-03-23 Alstom Technology Ltd Dispositif d'aubes d'une turbine à gaz
EP2313615B2 (fr) † 2008-08-15 2023-09-27 Ansaldo Energia IP UK Limited Dispositif d'aubes d'une turbine à gaz
US8167546B2 (en) 2009-09-01 2012-05-01 United Technologies Corporation Ceramic turbine shroud support
US8956700B2 (en) 2011-10-19 2015-02-17 General Electric Company Method for adhering a coating to a substrate structure
WO2013110792A1 (fr) * 2012-01-26 2013-08-01 Alstom Technology Ltd Élément formant stator pourvu d'une bague intérieure segmentée pour une turbomachine
CN104066934A (zh) * 2012-01-26 2014-09-24 阿尔斯通技术有限公司 用于涡轮机的具有分段式内部环的定子构件
RU2615292C2 (ru) * 2012-01-26 2017-04-04 АНСАЛДО ЭНЕРДЖИА АйПи ЮКей ЛИМИТЕД Деталь статора с сегментированным внутренним кольцом для турбомашины
US9702262B2 (en) 2012-01-26 2017-07-11 Ansaldo Energia Ip Uk Limited Stator component with segmented inner ring for a turbomachine
CN108691577A (zh) * 2017-04-10 2018-10-23 清华大学 涡轮发动机的主动间隙控制结构
CN108691577B (zh) * 2017-04-10 2019-09-20 清华大学 涡轮发动机的主动间隙控制结构

Also Published As

Publication number Publication date
EP1890010A3 (fr) 2011-08-10
EP1890010B1 (fr) 2016-05-04

Similar Documents

Publication Publication Date Title
US7771160B2 (en) Ceramic shroud assembly
US7665960B2 (en) Turbine shroud thermal distortion control
EP2299061B1 (fr) Support d'anneau de turbine en céramique
US6821085B2 (en) Turbine engine axially sealing assembly including an axially floating shroud, and assembly method
EP3088665B1 (fr) Piste aube à clé de voûte
US7686575B2 (en) Inner ring with independent thermal expansion for mounting gas turbine flow path components
EP1890010B1 (fr) Ensemble de virole de turbine en céramique
EP3219938B1 (fr) Support de joint externe d'aubes et procédé de protection de joint externe d'aubes
US9988934B2 (en) Gas turbine engines including channel-cooled hooks for retaining a part relative to an engine casing structure
US20040047726A1 (en) Ceramic matrix composite component for a gas turbine engine
US20130051989A1 (en) Turbine shroud segment with integrated seal
EP3543472B1 (fr) Système de rétention et de contrôle pour une virole de turbine
EP1697617B1 (fr) Enveloppe d'aube de turbine à gaz avec contrôle de fuite amelioré
US11326474B2 (en) Turbine shroud assembly with pinned attachment supplements for ceramic matrix composite component mounting
US20200248568A1 (en) Turbine vane assembly with ceramic matrix composite components and temperature management features
EP3047130B1 (fr) Turbine à gaz comprenant joints d'étanchéité à nid d'abeilles cannelé
GB2468848A (en) Turbomachine assembly
US11255204B2 (en) Turbine vane assembly having ceramic matrix composite airfoils and metallic support spar

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 11/08 20060101AFI20110707BHEP

17P Request for examination filed

Effective date: 20120210

AKX Designation fees paid

Designated state(s): DE GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20151130

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602007046108

Country of ref document: DE

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602007046108

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20170207

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602007046108

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602007046108

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 602007046108

Country of ref document: DE

Owner name: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES , US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, HARTFORD, CONN., US

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20200721

Year of fee payment: 14

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602007046108

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220301

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230720

Year of fee payment: 17