WO2023246804A1 - Structure d'aube directrice de turbine - Google Patents

Structure d'aube directrice de turbine Download PDF

Info

Publication number
WO2023246804A1
WO2023246804A1 PCT/CN2023/101482 CN2023101482W WO2023246804A1 WO 2023246804 A1 WO2023246804 A1 WO 2023246804A1 CN 2023101482 W CN2023101482 W CN 2023101482W WO 2023246804 A1 WO2023246804 A1 WO 2023246804A1
Authority
WO
WIPO (PCT)
Prior art keywords
wall surface
guide vane
turbine guide
vane structure
metal cover
Prior art date
Application number
PCT/CN2023/101482
Other languages
English (en)
Chinese (zh)
Inventor
洪辉
鲍骐力
张诗尧
曹源
谭智勇
张屹尚
Original Assignee
中国航发商用航空发动机有限责任公司
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 中国航发商用航空发动机有限责任公司 filed Critical 中国航发商用航空发动机有限责任公司
Publication of WO2023246804A1 publication Critical patent/WO2023246804A1/fr

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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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 present disclosure relates to the field of turbine guide vanes, and specifically to the field of CMC turbine guide vanes.
  • Ceramic Matrix Composites have the following advantages: (1) High temperature resistance: By improving the properties of fibers and matrix and combining the use of environmental coatings, CMC materials can withstand operating temperatures of 1650°C; (2) Corrosion resistance; (3) Low density: the density is about 1/4 to 1/3 of high-temperature alloys. Based on these advantages, applying CMC materials to turbine stator parts such as turbine guide blades can improve the performance of aeroengines in many aspects such as reducing the amount of cold air, increasing turbine temperature, and reducing NOx emissions, thereby meeting the needs of the next generation of advanced aeroengines.
  • CMC components need to be used with metal materials.
  • CMC materials are difficult to form and process. Therefore, it is difficult to prepare components with complex shapes. Otherwise, it will bring great difficulties to the assembly and installation of CMC and metal structures.
  • the thermal expansion coefficient of CMC materials is about 1/3 that of metal materials.
  • metal materials are assembled and used, it is easy to produce expansion differences in the radial and axial directions, which can lead to problems such as cold air leakage, vibration, and loss of restraint.
  • CMC material has good high temperature resistance but low strength.
  • it is necessary to reduce the stress carried by the CMC structural part as much as possible.
  • sufficient protection for metal parts needs to be provided in the same high temperature environment to ensure the reliability of the guide vane structure. sex.
  • An object of the present disclosure is to provide a turbine guide vane structure that can effectively maintain close contact between metal components and CMC components in the axial direction and overcome the problem of axial expansion.
  • the turbine guide vane structure includes CMC components and metal cover plates.
  • the CMC components It includes an edge plate, and the edge plate is used to cooperate with the metal cover plate.
  • An axial force applying member is provided between the edge plate and the metal cover plate, and the axial force applying member is used to provide an axial preload force; at least part of the axial side of the edge plate includes a notch, and the The notch includes a first wall surface, at least part of the first wall surface is an inclined surface, and the axial side surface of the metal cover plate that cooperates with this part of the edge plate includes a folding portion for matching with the notch, and the folding portion It includes a side wall surface, which is parallel to the first wall surface and in surface contact with the first wall surface.
  • the contact length between the inclined surface and the side wall surface is greater than the difference between the expansion amount of the CMC component and the metal cover plate in the axial direction and the cosine of the inclination angle of the inclined surface. ratio.
  • the notch further includes a second wall, at least part of the second wall is arranged parallel to the axial direction, the folded portion further includes a radial end, and the second wall is to separate the radial end from the CMC component.
  • At least part of the circumferential side of the edge plate includes a notch, and the circumferential side of the metal cover plate that cooperates with the part of the edge plate includes a folded portion.
  • At least part of said first wall is arranged parallel to the radial direction.
  • the notch is provided on the suction side of the turbine guide vane structure.
  • the notch is provided on the trailing edge side of the turbine guide vane structure.
  • the turbine guide vane structure further includes a connecting rod that penetrates the CMC component and the metal cover plate, and the length variation of the axial force applying member at a temperature It is set to be greater than the difference in radial expansion of the connecting rod and the CMC component at the same temperature.
  • At least part of the first wall surface and the side wall surface are arranged parallel to the radial direction, and the contact length of the first wall surface and the side wall surface is set to be larger than the connecting rod and the side wall surface. The difference in radial expansion of the CMC components.
  • a circumferential seal is further included between the metal cover plate and the edge plate.
  • the above-mentioned turbine guide vane structure provides an axial rebound force by setting an axial force applying member, and also provides a side wall surface and a first wall surface that are in contact with each other at an inclined angle.
  • the cooperation of the two enables the high-temperature alloy and CMC to remain in contact with each other after the expansion difference occurs. It can maintain contact in the axial direction, while ensuring that the axial force on the CMC blade is transmitted to the high-temperature alloy structure, effectively overcoming the radial and axial expansion differences between the metal and the CMC material after thermal expansion, and avoiding cold air leakage. , vibration, loss of restraint and other problems, ensuring the structural reliability of the guide vane.
  • Figure 1 is a schematic structural diagram of a typical aeroengine.
  • Figure 2 is a schematic structural diagram of a typical turbine guide blade.
  • Figure 3 is an exploded view of an embodiment of a turbine guide vane.
  • Figure 4 is a front view of one embodiment of the turbine guide vane structure.
  • Figure 5 is a cross-sectional view of an embodiment of a turbine guide vane structure.
  • FIG. 6A is an enlarged view of position A in FIG. 4 .
  • FIG. 6B is an enlarged view of position B in FIG. 5 .
  • Figure 7 is a front view of another embodiment of a turbine guide vane structure.
  • FIG. 8 is an enlarged view of position C in FIG. 7 .
  • the typical structure of the engine can be understood with reference to Figure 1. It mainly includes nacelle 1, fan 2, compressor 3, combustion chamber 4, turbine 5 and other parts. Turbine 5 contains a certain number of turbine guide vanes 10 for Organize upstream airflow.
  • the turbine guide vane 10 is provided in the high-temperature turbine component of the gas turbine engine, and is used to rectify the upstream high-temperature and high-pressure gas and output it to the downstream.
  • the turbine guide vanes 10 are generally installed on the casing, and together with the casing form a stator. As the total engine inlet temperature continues to rise, the gas temperature in front of the turbine is higher under high-temperature take-off conditions.
  • the turbine guide vane 10 can be made of ceramic matrix composites (Ceramic Matrix Composites, CMC) and metal parts are made together, including CMC part 12 and metal cover 9.
  • the metal cover 9 includes an upper cover 13 and a lower supporting plate 14; the CMC component 12 includes an edge plate 6, which includes an upper edge plate 121 and a lower edge plate 123.
  • the edge plate 6 is used to cooperate with the metal cover plate 9 to complete the assembly between the CMC components and the metal components.
  • the thermal expansion coefficients of the CMC component 12 and the metal cover plate 9 are quite different. Therefore, under high temperature operating conditions, the turbine guide vanes will produce a certain expansion difference in the axial and radial directions, which will cause cold air leakage, vibration, and loss of restraint. And other issues.
  • the strength of CMC materials is lower than that of metal materials, but it can withstand higher temperatures. Therefore, the turbine guide vane structure must take into account the strength and temperature resistance properties of both CMC materials and metal materials to ensure the reliability of the guide vane structure. sex.
  • the disclosed turbine guide vane structure can alleviate the thermal mismatch problem in the axial direction, and can also take into account the strength and temperature resistance characteristics of CMC materials and metal materials to ensure the reliability of the guide vane structure.
  • the turbine guide vane 10 includes a CMC component 12 and a metal cover plate 9 .
  • the metal cover plate 9 includes an upper cover plate 13 and a lower supporting plate 14 .
  • the X direction represents the axial direction, such as the extension direction shown by the engine axis 11;
  • the Y direction represents the radial direction of the turbine.
  • the Z direction that is perpendicular to both the X direction and the Y direction represents the circumferential direction.
  • the axial side refers to the surface along the two ends of the X-axis, that is, the left and right direction in Figure 3; the circumferential side refers to the surface along the two ends of the Z-axis, which is the front-to-back direction in Figure 3.
  • the upper cover 13 , the lower supporting plate 14 and the CMC component 12 are connected by connecting rods 15 .
  • the CMC component 12 includes an upper edge plate 121 , a lower edge plate 123 and an airfoil 122 connecting the upper edge plate 121 and the lower edge plate 123 .
  • the upper edge plate 121, the lower edge plate 123 and the blade body 122 can be made in one piece, that is, the fibers are continuous; or they can be prepared separately and then assembled into an integral structure, that is, the fibers are discontinuous.
  • the upper and lower edge plates of the CMC and the CMC blade body 122 form a flow channel, which is in contact with high-temperature gas and isolates other metal parts from direct contact with the gas, thus playing a protective role.
  • the upper edge plate 121 cooperates with the upper cover plate 13, the lower edge plate 123 cooperates with the lower supporting plate 14, the connecting rod 15 passes through the upper cover plate 13, the CMC component 12 and the lower supporting plate 14, and is tightened through the nut 160 at one end. force to realize the connection constraints between the CMC component 12, the upper cover plate 13 and the lower supporting plate 14.
  • the upper cover 13 is connected to the external casing through the hook mounting edge 131 and the mounting hole 132 to secure the turbine guide vane 10 .
  • an axial force applying member 150 is provided between the edge plate 6 and the metal cover plate 9 , and the axial force applying member 150 is used to provide axial predetermination.
  • Tightening force such as elastic parts such as springs, or force-applying parts made of shape memory alloys, rely on the pseudo-elasticity of shape memory alloys (pseudoelasticity), applying an axial preload force to the edge plate 6 and the metal cover plate 9 through thermal expansion at high temperatures.
  • At least part of the axial side of the edge plate 6 includes a notch 8.
  • the notch 8 includes a first wall 81. At least part of the first wall 81 is a slope.
  • the axial side of the metal cover 9 that cooperates with this part of the edge plate 6 includes a folded portion. 7.
  • the folded portion 7 is used to cooperate with the notch 8.
  • the folded portion 7 includes a side wall surface 71 which is parallel to the first wall surface 81 and in surface contact with the first wall surface 81 .
  • At least part of the first wall surface 81 on the axial side is set as an inclined surface, that is, a certain angle a is formed with respect to the X direction.
  • the first wall surface 81 and the side wall surface 71 can generate component forces in both the radial and axial directions. , that is, the component force along the Y direction and the component force along the X direction.
  • the inclined first wall surface 81 and the side wall surface 71 can always ensure close contact in the axial direction. Since the axial force applying member 150 is in a compressed state during initial installation, it is compressed to provide a radial preload force.
  • the axial force applying member 150 such as the elastic member generates a certain compression restoring force, which first offsets the gap in the radial direction caused by the expansion difference, and also generates movement in the axial direction with the help of the design of the inclined surface, so that the first wall 81
  • the two inclined surfaces of the side wall surface 71 are in close contact with each other.
  • the mutual displacement of the two inclined surfaces of the side wall surface 71 and the first wall surface 81 can simultaneously offset the gap caused in the axial direction, overcome the axial expansion difference to a certain extent, and ensure the installation
  • the stability and sealing performance alleviate the thermal mismatch problem in the axial direction.
  • the axial force applying member 150 can be disposed on the same side in the radial direction as the notch 8, as shown in Figure 3; it can also be disposed on different sides, as shown in Figure 7.
  • the notch 8 can be provided on both sides of the axial direction at the same time, or can be provided on only one side of the axial direction, so as to achieve the effect of alleviating the axial expansion difference.
  • the axial force applying member 150 continuously applies an upward rebound force to the CMC component. When thermal expansion occurs, the rebound force can compensate for the expansion difference between the CMC component and the metal component. With the first wall surface 81 and the side wall surface 71 located on the axial side that are tilted, compensation in the axial direction can be achieved, thereby simultaneously reducing the effects of expansion differences in the axial and radial directions.
  • the notch 8 is provided on the trailing edge side of the turbine guide vane structure. As shown in FIG. 7 , the right F area represents the blade leading edge, and the left T area represents the blade trailing edge. The pressure at the blade leading edge is greater than the blade trailing edge, and the airflow will flow from the F area to the T area. In one embodiment, the notch 8 and the folded portion 7 are only provided on the trailing edge side of the turbine guide vane, that is, the side of the blade close to the T area, so that with the help of air pressure, the parts located on the CMC component 12 will be moved under the action of aerodynamic force.
  • the force is transmitted to the metal parts through face-to-face contact, and the force on the CMC parts is transferred to the metal parts, thereby reducing the self-stress on the CMC parts and alleviating the expansion difference at the same time. It also ensures that the strength of CMC components always meets the requirements.
  • the contact length between the inclined surface and the side wall surface 71 needs to meet a certain length.
  • the contact length between the inclined surface and the side wall surface 71 needs to be continuously greater than the ratio of the difference between the expansion amount of the CMC component 12 and the metal cover plate in the axial direction to the cosine of the inclination angle a of the inclined surface, that is, L1 ⁇ cos(a)> ⁇ Lx, where L1 is the contact length of the contact surface, and ⁇ Lx is the difference in expansion amount between the upper cover plate 13 and the upper edge plate 121 in the axial direction, that is, the X direction, at a certain high temperature, thereby ensuring that When the engine is running, the upper edge plate 121 and the upper cover plate 13 always rely on the cooperation of the inclined surfaces to ensure the connection between the metal parts and the CMC parts.
  • the notch 8 further includes a second wall 82
  • the folded portion 7 further includes a radial end 72
  • the second wall 82 is used to separate the radial end. End 72 and CMC component 12 . Since the CMC material is more resistant to high temperatures than metal materials, the second wall 82 can prevent the radial end 72 of the metal folding portion 7 from directly contacting the high-temperature gas near the CMC blade 122 , thereby effectively protecting the metal components. , to prevent it from being damaged by high temperatures.
  • the second wall surface 82 is arranged parallel to the axial direction, that is, the second wall surface 82 is parallel to the X-axis direction, so as to play a buffering and protective role. It can be understood that the second wall surface 82 can also be configured as other angled inclined surfaces that can play a buffering and protective role.
  • the circumferential side of the edge plate 6 may also include a notch 8', and the circumferential side of the metal component mated with this part of the edge plate may include a folded portion 7'.
  • the notch 8' also includes a first wall surface 81'
  • the folded portion 7' includes a side wall surface 71'
  • the first wall surface 81' and the side wall surface 71' are in face-to-face contact.
  • the first wall 81 is arranged parallel to the radial direction, that is, parallel to the Y direction.
  • the first wall surface 81' is parallel to the Y direction
  • the side wall surface 71' parallel to the first wall surface 81 is also parallel to the Y direction.
  • the side wall surface 71 ′ of the folded portion 7 ′ located on the circumferential side of the upper cover plate 13 or the lower supporting plate 14 is also parallel to the Y-axis direction, and is located on the upper edge plate 121 or the lower edge plate.
  • the first wall surface 81' of the notch 8' on the circumferential side of 123 fits, and is arranged in a radial direction to help achieve better transmission of force.
  • the contact surface length L2 of the first wall surface 81' and the side wall surface 71' is continuously larger than the diameter of the connecting rod 15 and the CMC component 12.
  • the difference in expansion amount As shown in Figure 6B, L2> ⁇ Ly, ⁇ Ly is the relationship between the connecting rod 15 and the CMC component 12 at high temperature. The difference in expansion in the radial direction. If the above formula is satisfied, it can be ensured that the CMC component 12 and the metal cover plate 9 always maintain contact in the radial direction without separation at high temperatures.
  • the area P located on the left side of the turbine guide vane structure is the pressure surface side
  • the area S located on the right side of the turbine guide vane structure is the suction surface side. Since the working air pressure on the pressure surface is higher than the suction surface, therefore, in one embodiment, the notch 8' and the folded portion 7' are provided on the suction side of the turbine guide vane structure, so that under the action of aerodynamic force, the CMC component 12 can also be close to the high temperature in the circumferential direction, that is, in the circumferential direction. Alloy ensures that the hoop force can be transmitted to the high-temperature alloy structure, thereby ensuring the reliability of the guide vane structure.
  • the radial length change of the axial force applying member 150 at a temperature is greater than the difference in radial extension of the connecting rod 15 and the CMC component 12 at the same temperature.
  • the axial force applying member 150 can be an elastic member made of high-temperature alloy or ceramic material, such as a spring, a disc spring, etc.; it can also be a specific material with a thermal expansion coefficient greater than the thermal expansion coefficient of the connecting rod 15, such as an elastic member made of a shape memory alloy. force parts.
  • the axial force applying member 150 can maintain close contact between the CMC component 12 and the metal cover 9 through elastic recovery or thermal expansion properties at high temperatures.
  • the axial force applying member 150 can resume elongation or thermal expansion at high temperature.
  • ⁇ Ls at high temperature is greater than that of the connecting rod 15 and CMC components at the same temperature.
  • the difference in radial extension of 12, that is, ⁇ Ls> ⁇ Ly ensures that the CMC upper edge plate 121 and the axial force applying member 150, and the CMC lower edge plate 123 and the metal lower supporting plate 14 can always maintain close contact assembly.
  • ⁇ Ly is the difference between the radial expansion amounts of the connecting rod 15 and the CMC component 12 at a certain high temperature. Therefore, through the cooperation of elastic parts and oblique contact surfaces, the CMC material and the high-temperature alloy always maintain close contact under high temperature conditions, while overcoming the radial and axial expansion differences, ensuring installation stability.
  • a circumferential seal 127 is further included between the metal cover plate and the edge plate.
  • the circumferential seal 127 is disposed in the groove opened by the boss 141 and the lower edge plate 123 for Block the airflow path to avoid gas leakage.
  • the above-mentioned turbine guide vane structure can ensure close axial contact between CMC components and metal components by configuring inclined side walls and first wall surfaces. It can also use pressure differences to transfer forces through surface contact to minimize CMC. Partially bear the stress; in addition, by setting up the second wall, the metal components are effectively protected from direct impact of high temperatures and the stability of the structure is improved.
  • this application uses specific words to describe the embodiments of the application.
  • “one embodiment”, “an embodiment”, and/or “some embodiments” means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that “one embodiment” or “an embodiment” or “an alternative embodiment” mentioned twice or more at different places in this specification does not necessarily refer to the same embodiment. .
  • certain features, structures or characteristics in one or more embodiments of the present application may be appropriately combined.

Landscapes

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

Abstract

L'invention concerne une structure d'aube directrice de turbine, comprenant un élément composite à matrice céramique (CMC) et une plaque de recouvrement métallique, l'élément CMC comprenant une plaque de bord, et la plaque de bord étant utilisée pour agir de concert avec la plaque de recouvrement métallique ; un élément d'application de force axiale est disposé entre la plaque de bord et la plaque de recouvrement métallique, l'élément d'application de force axiale étant utilisé pour fournir une force de préserrage axiale à la plaque de bord et à la plaque de recouvrement métallique ; au moins une partie d'une surface latérale axiale de la plaque de bord comprend une encoche, l'encoche comportant une première surface de paroi ; au moins une partie de la première surface de paroi est une surface inclinée ; une surface latérale axiale de la plaque de recouvrement métallique agissant de concert avec ladite partie de la plaque de bord comprend une partie pliante utilisée pour agir de concert avec l'encoche ; la partie pliante comprend une surface de paroi latérale ; la surface de paroi latérale est parallèle à la première surface de paroi et est en contact de surface à surface avec la première surface de paroi. La structure de l'aube directrice de turbine permet de maintenir l'élément métallique et l'élément CMC en contact étroit dans une direction axiale, ce qui permet de surmonter les différences de dilatation radiale et axiale et de garantir la stabilité de l'installation.
PCT/CN2023/101482 2022-06-21 2023-06-20 Structure d'aube directrice de turbine WO2023246804A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202210706830.0A CN117307258A (zh) 2022-06-21 2022-06-21 一种涡轮导叶结构
CN202210706830.0 2022-06-21

Publications (1)

Publication Number Publication Date
WO2023246804A1 true WO2023246804A1 (fr) 2023-12-28

Family

ID=89279872

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2023/101482 WO2023246804A1 (fr) 2022-06-21 2023-06-20 Structure d'aube directrice de turbine

Country Status (2)

Country Link
CN (1) CN117307258A (fr)
WO (1) WO2023246804A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse
US20160097291A1 (en) * 2014-10-01 2016-04-07 United Technologies Corporation Stator assembly for a gas turbine engine
US20170022833A1 (en) * 2015-07-24 2017-01-26 General Electric Company Method and system for interfacing a ceramic matrix composite component to a metallic component
CN107448245A (zh) * 2016-04-08 2017-12-08 安萨尔多能源瑞士股份公司 涡轮发动机及用于涡轮发动机的导叶载体单元
US20200080429A1 (en) * 2018-09-07 2020-03-12 Rolls-Royce Corporation Turbine vane assembly with ceramic matrix composite components

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse
US20160097291A1 (en) * 2014-10-01 2016-04-07 United Technologies Corporation Stator assembly for a gas turbine engine
US20170022833A1 (en) * 2015-07-24 2017-01-26 General Electric Company Method and system for interfacing a ceramic matrix composite component to a metallic component
CN107448245A (zh) * 2016-04-08 2017-12-08 安萨尔多能源瑞士股份公司 涡轮发动机及用于涡轮发动机的导叶载体单元
US20200080429A1 (en) * 2018-09-07 2020-03-12 Rolls-Royce Corporation Turbine vane assembly with ceramic matrix composite components

Also Published As

Publication number Publication date
CN117307258A (zh) 2023-12-29

Similar Documents

Publication Publication Date Title
JP5887130B2 (ja) 構造的に低延性のタービンシュラウド装置
US8210799B1 (en) Bi-metallic strip seal for a turbine shroud
JP6012174B2 (ja) 低延性タービンシュラウドのための監視装置
JP6039892B2 (ja) 低延性タービンシュラウドを弾力的に実装する装置
US8047773B2 (en) Gas turbine shroud support apparatus
US10221699B2 (en) Shrouded turbine rotor blades
US20110265490A1 (en) Flow mixing vent system
JP2011012682A (ja) タービンエンジンに関するシステム及び装置並びにタービンエンジン用シール
JP2017524088A (ja) シュラウドハンガアセンブリ
US20100178161A1 (en) Compressor Clearance Control System Using Bearing Oil Waste Heat
US20110110767A1 (en) Sealed shaft assembly for exhaust turbines
US20200072066A1 (en) Turbine vane assembly with ceramic matrix composite components mounted to case
US10844734B2 (en) Ceramic turbine volute
EP2613013B1 (fr) Étage et turbine de moteur à turbine à gaz
US20120235366A1 (en) Seal for turbine engine bucket
WO2023246804A1 (fr) Structure d'aube directrice de turbine
US8147190B2 (en) Guide vane having hooked fastener for a gas turbine
Asai et al. Titanium 50‑inch and 60‑inch Last‑stage Blades for Steam Turbines
US9188018B2 (en) Flap seal and sealing apparatus
US20200025129A1 (en) Aircraft nozzle
Baines Radial and mixed flow turbine options for high boost turbochargers
WO2023241450A1 (fr) Structure d'aube de guidage de turbine
US10815793B2 (en) Trip strips for augmented boundary layer mixing
Talal et al. Design and analysis of a gas turbine blade
US10989203B2 (en) Centrifugal compressor and shroud therefore

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 23826451

Country of ref document: EP

Kind code of ref document: A1