CN111655973A - 燃气轮机定子 - Google Patents

燃气轮机定子 Download PDF

Info

Publication number
CN111655973A
CN111655973A CN201880065364.4A CN201880065364A CN111655973A CN 111655973 A CN111655973 A CN 111655973A CN 201880065364 A CN201880065364 A CN 201880065364A CN 111655973 A CN111655973 A CN 111655973A
Authority
CN
China
Prior art keywords
gas turbine
support element
stator
ring
turbine stator
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
CN201880065364.4A
Other languages
English (en)
Other versions
CN111655973B (zh
Inventor
V·A·库兹涅科夫
V·K·西切夫
V·M·亚泽夫
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.)
United Engine Manufacturing Group Co ltd
Original Assignee
United Engine Manufacturing Group Co ltd
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 United Engine Manufacturing Group Co ltd filed Critical United Engine Manufacturing Group Co ltd
Publication of CN111655973A publication Critical patent/CN111655973A/zh
Application granted granted Critical
Publication of CN111655973B publication Critical patent/CN111655973B/zh
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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

本发明涉及应用于航空领域的燃气涡轮发动机的燃气轮机定子。在燃气轮机定子的外壳体中安装有剖分式蜂窝环(被制成为双层环)的区段，在区段的前后轴向端上具有支承元件。在本发明中，区段的面向外壳体的层被制成为在平面中呈U形，支承元件被制成为沿着周边均匀地分布的单独的旋转体，并且在气流方向上的前支承元件的几何尺寸是后支承元件的1.1至1.5倍。因此，具有上述特征的所提出的发明的实施与要求保护的发明的已知特征相结合能够在不损害涡轮机效率的情况下减轻燃气轮机的定子的重量并提高其可靠性。

Description

燃气轮机定子
技术领域
本发明涉及应用于航空领域的燃气涡轮发动机的燃气轮机定子。
背景技术
现有技术公开了一种燃气轮机定子，其包括涡轮机的外壳体以及由片状材料层制成的区段型(扇形)剖分式(分割式)蜂窝环，区段/扇区的(在气流方向上的)前部部分是单层，区段的中央部分为双层，区段/扇区的后部部分为三层(2014年12月10日公开的专利RU2534669，IPC F01D25/24)。这种设计的缺点是重量大。
最接近要求保护的发明的是一种燃气轮机的定子，在该定子的外壳体中，剖分式蜂窝环的区段被制成双层，在区段的前后轴向端具有支承元件(2014年11月27日公开的专利RU 2534333，IPC F01D 25/24)。
用作原型的已知设计的缺点是其重量大，这损害了飞机燃气涡轮发动机的性能。
发明内容
通过本发明解决的技术问题在于在不损害涡轮机效率的情况下提高可靠性并减少燃气轮机定子重量。
该技术解决方案的实质在于，在燃气轮机定子中，在其外壳体中，剖分式蜂窝环(被制成为双层环)的区段在区段的前后轴向端上具有支承元件，根据本发明，区段的面向外壳体的层被制成为在平面中呈U形，支承元件被制成为沿着周边均匀地分布的单独的旋转体，并且(在气流方向上的)前支承元件的几何尺寸是后支承元件的1.1至1.5倍。
此外，根据本发明，支承元件被制成为截锥体。
使蜂窝体区段的面向涡轮机壳体的层在平面中呈U形一般而言能够大幅减轻区段和燃气轮机定子的重量，而不会增加区段外侧的气体杂散泄漏。
将支承元件制成为沿着周边均匀地安置的分离的旋转体能够使支承元件的重量最小化，并将重量最小化与设计的高可靠性结合。
将支承元件制成为截头锥体能够增加用于将支承元件与蜂窝区段根部实体联接(例如，焊接或钎焊)的表面积，这提高了区段和燃气轮机定子的可靠性。
使(在气流方向上的)前支承元件的几何尺寸是后支承元件的1.1至1.5倍提高了蜂窝体区段的可靠性，因为前支承元件使前喷嘴叶片的锁定环在径向方向上固定并且位于温度比后支承元件高的区域中，后支承元件上的径向负载仅等于蜂窝环区段的重量。
在几何尺寸比＜1.1时，支承元件和蜂窝体区段的重量增加；在几何尺寸比＞1.5时，由于后支承元件的几何尺寸过度减小，蜂窝体区段的可靠性降低。
附图说明
图1示出了燃气轮机定子的纵向截面图；图2示出图1的视图A；图3：图1的视图B，图4：图2的视图В。
具体实施方式
燃气轮机的定子1包括外壳体2，在外壳体2中，在沿着气流5的前喷嘴叶片3和后喷嘴叶片4之间安装有剖分式蜂窝环7的区段6。区段6由两层金属板制成，内层8是实心的，而面向外壳体2的外层9被制成在平面中呈U形。在区段6的前端10和后端11上，安装有被制成为沿着周边均匀地分布的旋转体(例如，截头圆锥体)的前支承元件12和后支承元件13。前支承元件12锁住锁定环14以防止径向位移，因此，前支承元件12被制成为是仅承受区段6自身载荷的后支承元件13的1.1至1.5倍(就几何尺寸而言)。支承元件12和13的几何相似性使得它们的制造成本降低。
该设备的操作如下。
在运行过程中，高温气流5在燃气轮机的定子1内部流动；在与流接触的情况下，定子1的外壳体2可能被损坏。然而，由于剖分式蜂窝环7的区段6在区段6具有最小重量的情况下可靠地防止了外壳体2与气流5接触，因此这种情况不会发生。因此，区段6的前端10和后端11是双层的，并且具有前支承元件12和后支承元件13，这提高了区段6锁定在前喷嘴叶片3和后喷嘴叶片4中的可靠性。
因此，具有上述特征的所提出的发明的实施与要求保护的发明的已知特征相结合能够在不损害涡轮机效率的情况下减轻燃气轮机的定子的重量并提高其可靠性。

Claims (2)

1.一种燃气轮机定子，在其外壳体中安装有剖分式蜂窝环的区段；所述环被制成为双层环，在所述区段的前、后轴向端上有支承元件，其特征在于，面向所述壳体的区段层被制成为在平面中呈U形，所述支承元件被制成为沿着周边均匀地分布的单独的旋转体，并且在气流方向上的前支承元件的几何尺寸是后支承元件的1.1至1.5倍。
2.根据权利要求1所述的燃气轮机定子，其特征在于，所述支承元件被制成为截锥体。
CN201880065364.4A 2017-10-05 2018-10-03 燃气轮机定子 Active CN111655973B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
RU2017135493A RU2674813C1 (ru) 2017-10-05 2017-10-05 Статор газовой турбины
RU2017135493 2017-10-05
PCT/RU2018/000643 WO2019070157A1 (ru) 2017-10-05 2018-10-03 Статор газовой турбины

Publications (2)

Publication Number Publication Date
CN111655973A true CN111655973A (zh) 2020-09-11
CN111655973B CN111655973B (zh) 2023-03-10

Family

ID=64753154

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201880065364.4A Active CN111655973B (zh) 2017-10-05 2018-10-03 燃气轮机定子

Country Status (5)

Country Link
US (1) US11473440B2 (zh)
EP (1) EP3693565A4 (zh)
CN (1) CN111655973B (zh)
RU (1) RU2674813C1 (zh)
WO (1) WO2019070157A1 (zh)

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5267828A (en) * 1992-11-13 1993-12-07 General Electric Company Removable fan shroud panel
RU2214514C2 (ru) * 1997-12-17 2003-10-20 Прэтт энд Уитни Кэнэдэ Корп. Цилиндрическое опорное устройство для узла статора газотурбинного двигателя и узел статора газотурбинного двигателя
US7334984B1 (en) * 2003-12-24 2008-02-26 Heico Corporation Turbine shroud assembly with enhanced blade containment capabilities
US7407368B2 (en) * 2003-07-04 2008-08-05 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
RU2374471C2 (ru) * 2004-05-04 2009-11-27 Снекма Кольцевой корпус статора газовой турбины и устройство охлаждения кольцевого корпуса
US20110318170A1 (en) * 2010-06-29 2011-12-29 Snecma Turbine stage
RU2465466C1 (ru) * 2011-05-05 2012-10-27 Открытое акционерное общество "Авиадвигатель" Высокотемпературная турбина газотурбинного двигателя
WO2013156734A1 (fr) * 2012-04-20 2013-10-24 Snecma Etage de turbine pour une turbomachine
RU2534333C1 (ru) * 2013-11-25 2014-11-27 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Статор газовой турбины
US20150308290A1 (en) * 2014-04-28 2015-10-29 Rolls-Royce Corporation Fan containment case

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5232340A (en) * 1992-09-28 1993-08-03 General Electric Company Gas turbine engine stator assembly
DE10122464C1 (de) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantelring
RU2534669C1 (ru) 2013-11-25 2014-12-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Статор турбины низкого давления

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5267828A (en) * 1992-11-13 1993-12-07 General Electric Company Removable fan shroud panel
RU2214514C2 (ru) * 1997-12-17 2003-10-20 Прэтт энд Уитни Кэнэдэ Корп. Цилиндрическое опорное устройство для узла статора газотурбинного двигателя и узел статора газотурбинного двигателя
US7407368B2 (en) * 2003-07-04 2008-08-05 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US7334984B1 (en) * 2003-12-24 2008-02-26 Heico Corporation Turbine shroud assembly with enhanced blade containment capabilities
RU2374471C2 (ru) * 2004-05-04 2009-11-27 Снекма Кольцевой корпус статора газовой турбины и устройство охлаждения кольцевого корпуса
US20110318170A1 (en) * 2010-06-29 2011-12-29 Snecma Turbine stage
RU2465466C1 (ru) * 2011-05-05 2012-10-27 Открытое акционерное общество "Авиадвигатель" Высокотемпературная турбина газотурбинного двигателя
WO2013156734A1 (fr) * 2012-04-20 2013-10-24 Snecma Etage de turbine pour une turbomachine
RU2534333C1 (ru) * 2013-11-25 2014-11-27 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Статор газовой турбины
US20150308290A1 (en) * 2014-04-28 2015-10-29 Rolls-Royce Corporation Fan containment case

Also Published As

Publication number Publication date
US11473440B2 (en) 2022-10-18
US20210363895A1 (en) 2021-11-25
EP3693565A4 (en) 2021-06-16
RU2674813C1 (ru) 2018-12-13
WO2019070157A1 (ru) 2019-04-11
CN111655973B (zh) 2023-03-10
EP3693565A1 (en) 2020-08-12

Similar Documents

Publication Publication Date Title
US9863260B2 (en) Hybrid nozzle segment assemblies for a gas turbine engine
CN104246138B (zh) 具有局部壁厚控制的涡轮翼型件及涡轮叶片
US9394915B2 (en) Seal land for static structure of a gas turbine engine
US7946811B2 (en) Assembly of sectorized fixed stators for a turbomachine compressor
JP5748960B2 (ja) 圧縮機ディフューザ
US20080279679A1 (en) Multivane segment mounting arrangement for a gas turbine
JP6409072B2 (ja) 主要ストラットと小型ストラットを備えた排気ガスディフューザ
US10227880B2 (en) Turbine blade attachment mechanism
EP2855892B1 (en) Mid-turbine frame for a gas turbine engine comprising a seal land
JP2015075107A (ja) タービン部品の冷却を行う方法及びシステム
EP3048372B1 (en) Flexible swirlers
US10018066B2 (en) Mini blind stator leakage reduction
JP2008309157A (ja) タービンエンジンの排気カウリング
US8128349B2 (en) Gas turbine engines and related systems involving blade outer air seals
EP3051072B1 (en) Airfoil module
US11585230B2 (en) Assembly for a turbomachine
US11274563B2 (en) Turbine rear frame for a turbine engine
CN104975886A (zh) 用于压缩机或轴向涡轮机的涡轮区段的静叶承载器
US10273821B2 (en) Advanced stationary sealing cooled cross-section for axial retention of ceramic matrix composite shrouds
CN111655973B (zh) 燃气轮机定子
JP2018115656A (ja) タービンシステムの排気フレーム用ストラット
US9845686B2 (en) Overlapping herringbone filmhole patterned airfoil
US20160298464A1 (en) Cooling hole patterned airfoil
EP3043031B1 (en) Vane assembly, vane set, and method of manufacturing a vane assembly
US20190003316A1 (en) Helical skin cooling passages for turbine airfoils

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant