EP3489466B1 - Ensemble de turbine à gaz - Google Patents

Ensemble de turbine à gaz Download PDF

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Publication number
EP3489466B1
EP3489466B1 EP17203661.8A EP17203661A EP3489466B1 EP 3489466 B1 EP3489466 B1 EP 3489466B1 EP 17203661 A EP17203661 A EP 17203661A EP 3489466 B1 EP3489466 B1 EP 3489466B1
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EP
European Patent Office
Prior art keywords
gas turbine
turbine assembly
clearance control
vane carrier
control cavity
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.)
Active
Application number
EP17203661.8A
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German (de)
English (en)
Other versions
EP3489466A1 (fr
Inventor
Meisam Sistaninia
Uwe Wolfgang RUEDEL
Phillipe LOTT
Sven Olmes
Hyazinth Immanuel HENNEL
Oliver Joseph Taheny
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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.)
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Publication date
Application filed by Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP17203661.8A priority Critical patent/EP3489466B1/fr
Priority to CN201811406760.7A priority patent/CN109869197B/zh
Publication of EP3489466A1 publication Critical patent/EP3489466A1/fr
Application granted granted Critical
Publication of EP3489466B1 publication Critical patent/EP3489466B1/fr
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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
    • 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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor

Definitions

  • the present invention relates to a gas turbine assembly.
  • the gas turbine assembly is part of an electric power production plant.
  • Gas turbine assemblies normally comprise a compressor, a combustion chamber and a gas turbine.
  • the compressor comprises an inlet supplied with air and a plurality of rotating blades configured for compressing the incoming air.
  • the compressed air leaving the compressor flows into a plenum delimited by an outer casing and from there enters into the combustor.
  • the compressed air is mixed with at least one fuel and such resulting mixture of fuel and compressed air flows into a combustion chamber where this mixture is combusted.
  • the resulting hot gas leaves the combustion chamber and expands in the turbine. In the turbine the hot gas expansion moves rotating blades connected to a rotor.
  • Both the compressor and the turbine comprises a plurality of vanes axially interposed between the rotating blades.
  • Rotating blades are supported by a rotor rotating about a main axis, while the vanes of the gas turbine are supported by a gas turbine vane carrier and the vanes of the compressor are supported by a compressor vane carrier.
  • rotor parts and stator parts have different responses to temperature changes due to the fact that they are made of different materials and also due to the fact that they are exposed to different temperature gradients, especially in the gas turbine.
  • the object of the present invention is therefore to provide a gas turbine assembly wherein the described drawbacks are avoided or at least mitigated.
  • the governing ring can obtain a controlled thermal behaviour of the vane carrier so as to control the clearance in the turbine or in the compressor.
  • the clearance control cavity can be oriented so as to optimize the occupation of the available space in the specific portion of the governing ring which can influence better the thermo-mechanical behaviour of the vane carrier. Said solution therefore brings more flexibility and considerable benefits in terms of design space.
  • a significantly less amount of fluid is required than for obtaining the same thermal expansion directly in the vane carrier.
  • the governing ring design is more effective and more controllable with respect to solutions which try to obtain a thermal expansion directly on the vane carrier.
  • the clearance control is active along the entire circumferential portion of the vane carrier and the influence of the thermo-mechanical behaviour of the vane carrier is more effective.
  • the clearance control cavity extends radially with respect to the longitudinal axis.
  • the plurality of clearance control cavities are evenly distributed along a circumferential direction. In this way a circumferentially homogeneous temperature field is obtained in the vane carrier.
  • the clearance control cavity is a through hole made into the governing ring.
  • the clearance control cavities are obtainable in a rapid, simple and economic way, for example by drilling the governing ring.
  • the governing ring is made by at least two parts coupled together. In this way the governing ring can be advantageously housed in the annular seat without requiring any dismantling of the vane carrier.
  • the clearance control cavity has at least one outlet connected to a respective discharge conduit.
  • the vane carrier comprises at least a portion of the discharge conduit; the discharge conduit flowing into a working channel of the gas turbine assembly provided with vanes. In this way the control fluid discharged in the working channel can provide further useful work for the assembly.
  • the gas turbine assembly comprises at least one insert which is arranged inside at least one clearance control cavity.
  • the thermal exchange between the control fluid and the governing ring can be controlled in order to optimize the heat transfer and reduce the amount of control fluid required.
  • the insert is hollow and preferably provided with an inlet hole and with a plurality of outlet holes on its surface.
  • the passage of control fluid through the insert is allowed and an impingement effect on the inner wall of the control cavity is obtained. Consequently a further optimization of the heat transfer and a reduction of the amount of control fluid required is obtained.
  • the governing ring and the vane carrier may be made of different materials.
  • the governing ring can be made by a particular material that is too expensive for realizing the entire vane carrier.
  • the radial dimensions of the governing ring are greater than the radial dimensions of the vane carrier at the annular seat. In this way, the governing ring can control the radial expansion of the vane carrier more effectively.
  • the governing ring can be coupled to the vane carrier by releasable coupling elements. In this way the replacement of the governing ring is easier.
  • the gas turbine assembly comprises a compressor, a combustor and a gas turbine; wherein the gas turbine comprises the vane carrier and the compressor clearance control cavity is connected to an extraction line, which is configured to extract air from the compressor and feed it to the clearance control cavity.
  • the governing ring can be used for controlling the turbine clearance.
  • the gas turbine assembly comprises a compressor, a combustor and a gas turbine; wherein the compressor comprises the vane carrier and the compressor clearance control cavity is connected to a further extraction line, which is configured to extract air from the compressor, cool it preferably by means of an external cooler and feed it to the clearance control cavity.
  • the governing ring can be used for controlling the compressor clearance.
  • reference numeral 1 indicates a gas turbine assembly for an electrical energy production plant extending along a longitudinal axis A (for the sake of simplicity only an half of the assembly is illustrated in figure 1 as the assembly being symmetrical with respect to axis A).
  • the assembly 1 comprises a combustor 2, a compressor 3 and a gas turbine 5.
  • the gas turbine 5 extends along the longitudinal axis A and is provided with a shaft 6 (also extending along axis A) to which compressor 3 is also connected.
  • Gas turbine 5 comprises a working expansion channel 7 wherein the hot gas working fluid coming from the combustor 2 flows in a direction D.
  • the working expansion channel 7 has a section which radially increases along the axis A in the direction D.
  • Compressor 3 comprises a working compression channel 8 wherein external air is compressed and flows in direction D.
  • the end of the working compression channel 8 is connected to combustor 2.
  • the working compression channel 8 has a section which radially decreases along the axis A in the direction D.
  • the turbine 5 comprises an outer casing (not visible in the attached figures), a vane carrier 10, which extends about axis A and is static, a plurality of gas turbine stator vanes 11 fastened at least to the vane carrier 10 and divided into arrays, and a plurality of gas turbine rotor blades 13 divided into arrays coupled to the shaft 6 and arranged radially with respect to axis A.
  • Each gas turbine rotor blade 13 is provided with an end 14 coupled to the shaft 6 and a free end 15 facing the vane carrier 10.
  • the gap between the free end 15 and the vane carrier 10 defines a turbine clearance 16 (indicated schematically in figure 1 ).
  • radial arrays of rotor gas turbine blades 13 are alternated along axis A by radial arrays of stator gas turbine vanes 11.
  • the compressor 3 comprises at least one vane carrier 20, which extends about axis A and is static, a plurality of stator compressor vanes 21 fastened at least to the vane carrier 20 and divided into arrays, and a plurality of rotor compressor blades 23 divided into arrays coupled to the shaft 6 and arranged radially with respect to axis A.
  • Each rotor compressor blade 23 is provided with an end 24 coupled to the shaft 6 and a free end 25 facing the vane carrier 20.
  • the gap between the free end 25 and the vane carrier 20 defines a compressor clearance 26 (indicated schematically in figure 1 ).
  • radial arrays of rotor blades 23 are alternated along axis A by radial arrays of stator vanes 21.
  • the vane carrier 10 of the gas turbine 5 comprises at least one annular seat 27.
  • the gas turbine assembly 1 comprises at least one governing ring 28 housed in the annular seat 27 of the turbine vane carrier 10.
  • the governing ring 28 comprises at least one clearance control cavity 29 which extends transversally with respect to the longitudinal axis A for controlling the turbine clearance 16.
  • the axis B of extension of the clearance control cavity 29 is transversal with respect to the longitudinal axis A.
  • the angular position of the axis B of the clearance control cavity 29 can vary from radially to axially (axially excluded) depending on the available space in the governing ring 28.
  • the clearance control cavity 29 extends radially with respect to the longitudinal axis A (configuration illustrated in figures 2 and 3 ).
  • the vane carrier 20 of the compressor 3 can comprise at least one annular seat wherein at least one governing ring provided with at least one clearance control cavity is housed.
  • the clearance control cavity of the governing ring housed in the seat of the compressor vane carrier extends transversally with respect to the longitudinal axis A for controlling the compressor clearance 26.
  • gas turbine 5 can be applied, mutatis mutandis, to the compressor 3 and in particular to at least one annular seat into the vane carrier 20 and to at least one ring housed in the annular seat of the vane carrier 20 of the compressor 3 for controlling the compressor clearance 26.
  • annular seat 27 is realized in correspondence of at least one axial position A1 of the vane carrier 10.
  • the vane carrier 10 can comprise more than one annular seat arranged at respective different axial positions. Each seat being configured to house at least one respective governing ring. In this way the thermo-mechanical behaviour of the vane carrier in different zones of the vane carrier is influenced.
  • the governing ring 28 comprises a plurality of clearance control cavities 29 which are evenly or unevenly distributed along the circumferential direction.
  • thermo-mechanical behaviour of the vane carrier 10 at the axial position A1 is influenced by the presence of the clearance control cavities 29 in the governing ring 28 and the turbine clearance 16 can be opportunely controlled.
  • the plurality of clearance control cavities 29 are evenly distributed along the circumferential direction.
  • the evenly distribution of the clearance control cavities 29 create a more homogeneous circumferential temperature field.
  • the clearance control cavity 29 is a through hole made into the governing ring 28.
  • the clearance control cavity 29 is a channel extending from an outer surface 18 of the governing ring 28, which faces in use the outer casing 9 (see figure 3 )and an inner surface 19 of the governing ring 28, which faces in use the annular seat 27 of the vane carrier 10.
  • the clearance control cavity can be a cylindrical blind hole.
  • the governing ring 28 is split into two half-rings 12a 12b which are connected one to the other at a split plane S (indicated in figure 3 ).
  • each clearance control cavity 29 has an inlet 30 connected to an annular feeding common channel 31 which is made in the governing ring and is connected to a control fluid source preferably by means of a plurality of conduits.
  • At least one of the plurality of the clearance control cavities 29 has also an outlet 33 connected to a discharge conduit 34.
  • control fluid is air extracted from the compressor 3 by a dedicated extraction line 36 (illustrated in figure 1 ).
  • a regulator 37 configured to regulate the temperature and/or the pressure and/or the flow rate of the control fluid before feeding it to the common manifold.
  • the regulator 37 can regulate the temperature and the pressure of the control fluid in order to have a temperature and a pressure as required.
  • turbine clearance 16 can be controlled by adjusting the temperature, the pressure and the flow rate of the control fluid fed to the clearance control cavity 29.
  • the regulator 37 is configured to regulate the temperature and/or the pressure and/or the flow rate of the control fluid on the basis of the assembly parameters in order to keep the turbine clearance 16 at the desired values.
  • the regulator 37 is configured to regulate the temperature and/or the pressure and/or the flow rate of the control fluid on the basis of at least one parameter such as local temperature and/or clearance measurements and/or load condition of the turbine 5 and/or the speed of load variations of the turbine 5 and/or temperature at the turbine inlet, etc.
  • the discharge conduit 34 connected to the outlet 33 of at least one of the clearance control cavities 29 extends substantially axially and flows into the working expansion channel 7.
  • the discharge conduit 34 does not extend axially and is inclined at an angle with respect to the axis A.
  • the vane carrier 10 comprises at least a portion of the discharge conduit 34.
  • discharge conduit 34 is completely realized in the vane carrier 10 and extends from the annular seat 27 to the expansion channel 7.
  • discharge conduit 34 discharges the control fluid into the expansion channel 7 through a discharge port 38.
  • part of the discharge conduit 34 can be realized also in the governing ring 28.
  • the control fluid discharged in the expansion channel 7 can provide a further useful work in the turbine 5, improving the overall efficiency of the assembly 1.
  • discharge port 38 is arranged on the vane carrier 10 between a radial array of rotor gas turbine blades 13 and a radial array of stator gas turbine vanes 11.
  • At least one of the discharge conduits can discharge the control fluid directly or indirectly into components requiring cooling, such as vanes, stator platforms (not illustrated in the attached figures), heat shields (not illustrated in the attached figures).
  • the control fluid can be used for save dedicated cooling air (generally extracted from the compressor) thus improving the overall efficiency of the assembly 1.
  • At least one of the discharge conduits can discharge the control fluid directly or indirectly into selected stator cavities (not illustrated in the attached figures) needing purging air for preventing entrance of hot fluid coming from the expansion channel 7.
  • the governing ring 28 and the vane carrier 10 are separated pieces made of different materials.
  • the governing ring can be made by a particular material that is too expensive for realizing the entire vane carrier 10. For instance a material with better lifetime as the governing ring 28 needs to withstand more severe load cycles since it is exposed to alternating temperatures.
  • the governing ring 28 has radial dimensions greater than the radial dimensions of the vane carrier 10 at the annular seat 27 (i.e. substantially at the axial position A1). In this way the governing ring 28 has a radial stiffness higher than the radial stiffness of the vane carrier 10.
  • the governing ring 28 has a thermal delay lower than the thermal delay of the vane carrier 10 in order to be able to response to the clearance controller faster.
  • the governing ring 28 and the vane carrier 10 are separated pieces coupled together with a permanent joint (i.e. welding) or with a releasable joint (i.e. releasable coupling elements such as bolts 40 shown in figure 2 ).
  • the coupling with a releasable joint allows an easy replacement of the governing ring 28.
  • At least one insert 41 is arranged inside at least a portion of the clearance control cavity 29.
  • Said insert 41 can be shaped in order to guide the flow of the control fluid inside the clearance control cavity 29 allowing freedom in designing the position of the inlet 30 and of the outlet 33 along the axis B of the clearance control cavity 29.
  • Said insert 41 can furthermore enhance the heat transfer between the control fluid flowing in the clearance control cavity 29 and the material of the governing ring 28 in order to influence the temperature of the governing ring 28 and consequently of the vane carrier 10.
  • the insert 41 in fact, allow to operate with moderate flow quantities of the control fluid.
  • Insert 41 can be one of the inserts disclosed in EP 3023600 .
  • the insert 41 has mainly the shape of a cylindrical hollow tube so as the flow of control fluid can pass through the insert 41, in order to limit the heat transfer with the governing ring 28, and in a gap 42 defined between the insert 41 and the respective inner surface of the clearance control cavity 29, in order to keep the maximum heat transfer area and increase the flow velocity.
  • the gap 42 defined between the insert 41 and the respective inner surface of the clearance control cavity 29 has a thickness (intended as the measure along a direction perpendicular to the axis B) which is a function of the diameter of the clearance control cavity 29.
  • the ratio between the diameter of the clearance control cavity 29 and the thickness is comprised between 1:200 to 1:2.
  • FIGS 4 and 5 another embodiment of a governing ring 128 is shown.
  • the governing ring 128 differs from the governing ring 28 of figures 1-3 for having a different clearance control cavity 140 and a different insert 141.
  • the clearance control cavity 140 is a blind hole made into the governing ring 128 having an outlet 133 connected to a discharge channel 134 and an inlet 133 connected to an annular feeding common channel 131.
  • the insert 141 has mainly the shape of a cylindrical hollow body which is provided with a plurality of holes 142 on its surface.
  • the insert 141 is provided with first outlet holes 142a on the bottom surface 143 of the cylindrical hollow body and a plurality of second outlet holes 142b on the lateral surface 144 of the cylindrical hollow body which faces, in use, the inner surface of the clearance control cavity 29.
  • the insert 141 is further provided with a main inlet hole 145 (see figure 4 ) on the top surface 146 which faces, in use, the annular feeding common channel 31.
  • the flow of control fluid enters inside the insert 141 through the main hole 145 on the top surface 146 and exits through the plurality of first outlet holes 142a and through the second outlets 142b in order to impinges on the inner surface of the clearance control cavity 140.
  • the flow of control fluid can pass also in the substantially annular gap 147 defined between the insert 141 and the respective inner surface of the clearance control cavity 140.
  • the insert can be provided with turbulators on the outer surface in order to create turbulence inside the gap. In this way the flow velocity and the heat transfer is improved.
  • said turbulators may be helicoidally bended ribs protruding from the outer surface of the insert.
  • the insert is not cylindrical and has a shape defined by a combination of conical and cylindrical part so that the thickness T of the gap 42 can vary along the length of the insert.
  • the insert is provided with damping means configured to resist vibrations.
  • the clearance control cavity comprises also a dirt trap configured to accumulate dirt.
  • Insert 41 and 141 can be fixed in the respective clearance control cavity 29 either by screwing it in the clearance control cavity 29 (in this case the insert and the clearance control cavity have respective threaded portions) or by shrinking it to the clearance control cavity 29 or by caulking it with the clearance control cavity 29 or by fixing it to the clearance control cavity 29 with a locking screw, or by welding it to the clearance control cavity 29 or by press fitting it into the clearance control cavity 29.

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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)

Claims (13)

  1. Ensemble de turbine à gaz comprenant :
    un carter externe (9) ;
    au moins un support d'aubes (10 ; 20) s'étendant le long d'un axe longitudinal (A) et pourvu d'au moins un siège annulaire (27) ; et
    au moins un anneau de régulation (28 ; 128) logé dans le siège annulaire (27) ;
    l'ensemble de turbine à gaz étant caractérisé en ce qu'au moins un anneau de régulation (28 ; 128) est pourvu d'une pluralité de cavités de contrôle de dégagement (29 ; 140) distribuées le long d'une direction circonférentielle ; dans lequel chaque cavité de contrôle de dégagement (29 ; 140) s'étend le long d'un axe (B) qui est transversal par rapport à l'axe longitudinal (A) ; dans lequel chaque cavité de contrôle de dégagement (29 ; 140) est définie par un trou traversant pratiqué dans l'anneau de régulation (28 ; 128) s'étendant à partir d'une surface externe (18) de l'anneau de régulation (28 ; 128), qui est orientée lors de l'utilisation vers le carter externe (9) et d'une surface interne (19) de l'anneau de régulation (28 ; 128), qui est orientée lors de l'utilisation vers le siège annulaire (27) du support d'aubes (10) ou par un trou aveugle cylindrique s'étendant depuis la surface externe (18) de l'anneau de régulation (28 ; 128) ; dans lequel chaque cavité de contrôle de dégagement (29 ; 140) a au moins une entrée (30) reliée à une source de fluide de commande.
  2. Ensemble de turbine à gaz selon la revendication 1, dans lequel la cavité de contrôle de dégagement (29 ; 140) s'étend radialement par rapport à l'axe longitudinal (A).
  3. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel la pluralité des cavités de contrôle de dégagement (29 ; 140) sont distribuées de manière régulière le long d'une direction circonférentielle.
  4. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel la cavité de contrôle de dégagement (29) est un trou traversant pratiqué dans l'anneau de régulation (28).
  5. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel l'anneau de régulation (28 ; 128) est constitué d'au moins deux parties (12a, 12b) couplées ensemble.
  6. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel la cavité de contrôle de dégagement (29 ; 140) a au moins une sortie (33) reliée à un conduit d'évacuation (34) respectif.
  7. Ensemble de turbine à gaz selon la revendication 6, dans lequel le support d'aubes (10 ; 20) comprend au moins une partie du conduit d'évacuation (34) ; le conduit d'évacuation (34) s'écoulant dans un canal de travail (7 ; 8) de l'ensemble de turbine à gaz pourvu d'aubes (11 ; 21).
  8. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, comprenant au moins un insert (41 ; 141) qui est agencé à l'intérieur d'au moins une cavité de contrôle de dégagement (29 ; 140).
  9. Ensemble de turbine à gaz selon la revendication 8, dans lequel l'insert (41 ; 141) est creux et de préférence pourvu d'un trou d'entrée (145) et d'une pluralité de trous de sortie (142a, 142b) sur sa surface (143, 144).
  10. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel l'anneau de régulation (28 ; 128) et le support d'aubes (10 ; 20) sont constitués de matériaux différents.
  11. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel les dimensions radiales de l'anneau de régulation (28 ; 128) sont supérieures aux dimensions radiales du support d'aubes (10 ; 20) au niveau du siège annulaire (27).
  12. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, dans lequel l'anneau de régulation (28 ; 128) est couplé au support d'aubes (10 ; 20) par des éléments de couplage amovibles (40).
  13. Ensemble de turbine à gaz selon l'une quelconque des revendications précédentes, comprenant un compresseur (3), une chambre de combustion (4) et une turbine à gaz (5) ; dans lequel la turbine à gaz comprend le support d'aubes (10) et la cavité de contrôle de dégagement (29 ; 140) de compresseur est reliée à une conduite d'extraction (36), qui est conçue pour extraire l'air du compresseur (3) et l'envoyer dans la cavité de contrôle de dégagement (29 ; 140).
EP17203661.8A 2017-11-24 2017-11-24 Ensemble de turbine à gaz Active EP3489466B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17203661.8A EP3489466B1 (fr) 2017-11-24 2017-11-24 Ensemble de turbine à gaz
CN201811406760.7A CN109869197B (zh) 2017-11-24 2018-11-23 燃气涡轮组件

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17203661.8A EP3489466B1 (fr) 2017-11-24 2017-11-24 Ensemble de turbine à gaz

Publications (2)

Publication Number Publication Date
EP3489466A1 EP3489466A1 (fr) 2019-05-29
EP3489466B1 true EP3489466B1 (fr) 2021-08-25

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP17203661.8A Active EP3489466B1 (fr) 2017-11-24 2017-11-24 Ensemble de turbine à gaz

Country Status (2)

Country Link
EP (1) EP3489466B1 (fr)
CN (1) CN109869197B (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112595520A (zh) * 2019-09-16 2021-04-02 中国航发商用航空发动机有限责任公司 压气机试验台架以及试验方法

Family Cites Families (10)

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Publication number Priority date Publication date Assignee Title
FR2467292A1 (fr) * 1979-10-09 1981-04-17 Snecma Dispositif de reglage du jeu entre les aubes mobiles et l'anneau de turbine
US6659716B1 (en) * 2002-07-15 2003-12-09 Mitsubishi Heavy Industries, Ltd. Gas turbine having thermally insulating rings
US7434402B2 (en) 2005-03-29 2008-10-14 Siemens Power Generation, Inc. System for actively controlling compressor clearances
US20090053042A1 (en) * 2007-08-22 2009-02-26 General Electric Company Method and apparatus for clearance control of turbine blade tip
US8152446B2 (en) * 2007-08-23 2012-04-10 General Electric Company Apparatus and method for reducing eccentricity and out-of-roundness in turbines
US9316111B2 (en) * 2011-12-15 2016-04-19 Pratt & Whitney Canada Corp. Active turbine tip clearance control system
CA2899895A1 (fr) * 2013-02-08 2014-08-14 General Electric Company Systeme de regulation d'espacement actif base sur une aspiration
US9598974B2 (en) * 2013-02-25 2017-03-21 Pratt & Whitney Canada Corp. Active turbine or compressor tip clearance control
US9869196B2 (en) * 2014-06-24 2018-01-16 General Electric Company Gas turbine engine spring mounted manifold
EP3023600B1 (fr) 2014-11-24 2018-01-03 Ansaldo Energia IP UK Limited Élément de carter de moteur

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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Publication number Publication date
CN109869197A (zh) 2019-06-11
CN109869197B (zh) 2023-08-04
EP3489466A1 (fr) 2019-05-29

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