CN101240719B - 带有反转高压和低压涡轮的燃气涡轮 - Google Patents

带有反转高压和低压涡轮的燃气涡轮 Download PDF

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CN101240719B
CN101240719B CN2008100061071A CN200810006107A CN101240719B CN 101240719 B CN101240719 B CN 101240719B CN 2008100061071 A CN2008100061071 A CN 2008100061071A CN 200810006107 A CN200810006107 A CN 200810006107A CN 101240719 B CN101240719 B CN 101240719B
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turbine
pressure
pressure turbine
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low
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CN101240719A (zh
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让-迈克尔·甘巴尔
雷诺·马尔泰
埃里克·施瓦茨
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Safran Aircraft Engines SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

一种带有反转HP和LP涡轮的燃气涡轮，包括：LP涡轮(50)，其具有多个与喷嘴(52)相替出现的移动轮(56)，所述LP涡轮的所述移动轮沿着与所述HP涡轮的所述移动轮旋转方向相反的方向旋转；中间涡轮壳体(60)具有内、外壳体壁，与跨越在内、外壳体壁之间通道上的臂(68)共同限定HP和LP涡轮之间的气流通道。该燃气涡轮在HP涡轮(40)的出口与LP涡轮(50)的第一移动轮(561)之间没有具有气流偏转功能的喷嘴或装置。HP涡轮(40)有利地被设计成输送在中间涡轮壳体(60)中回旋的气体。

Description

带有反转高压和低压涡轮的燃气涡轮
技术领域
本发明涉及一种具有反转高压(High Pressure，HP)和低压(Low Pressure，LP)涡轮的燃气涡轮，即每个高压涡轮的轮子沿着与低压涡轮的移动轮旋转的方向相反的方向旋转。本发明的应用领域更特别涉及航空发动机的应用。
背景技术
本发明并不局限于具有高压和其低压两个线圈的涡轮。也可以应用到具有超过两个线圈的涡轮中，其中术语高压(HP)涡轮和低压(LP)涡轮然后应用到沿着流过燃气涡轮的流动方向的两个串联线圈的两个涡轮上。
使用反转高压和低压涡轮的优点在于需要出口流从高压涡轮的偏移更小，所以由于低压涡轮的吸入喷嘴而使空气动力损失减小。因而提高涡轮功能的性能。
出于结构的原因，可以将中间壳体或“中间涡轮”壳体置于高压涡轮和低压涡轮之间，以使其容纳在各壳体之间。中间壳体具有内壁和外壁，它们同内、外壁之间延伸的壁一同限定高压涡轮和低压涡轮之间气流的流动截面。
图1中非常概略地示出了一种这样的结构。高压涡轮10包括喷嘴12，接收来自燃烧室的原始气流并使其偏转以将其提供给沿一方向(箭头F1)转向的移动轮16。低压涡轮20包括多个阶段，每一阶段带有喷嘴221，222，…，22n和移动轮261，262，…，26n，这些移动轮沿着与轮16方向相反的方向(箭头F2)转向。中间涡轮壳体30位于涡轮10和带有跨越气流通道的臂22的涡轮20之间，臂32是流线型的以减少空气动力损失。然而，中间涡轮壳体的存在会产生压力损失，因而使涡轮的综合性能下降。
如图2中非常概略地示出，人们已经提出一种发明以减少低压涡轮入口阶段的喷嘴并为中间涡轮壳体36设置偏转功能(其它部件与图1所示的相似，并使用相同的附图标记表示)。中间涡轮壳体的臂38被赋予适于偏转翼片的形状。然而，与没有设置中间涡轮壳体的结构相比，其性能损失仍然存在。每个臂遭受到较高水平的几何应力(在绳索长度和最大横截面方面)，因此产生比低压涡轮第一阶段的常规喷嘴所产生的更大的压力损失。
发明内容
本发明的目的在于提供一种用于反转HP和LP涡轮和中间涡轮壳体的结构，使空气动力性能达到最佳，同时使重量和成本也达到最佳。
利用燃气涡轮来实现本目的，该燃气涡轮包括：
高压(HP)涡轮；带有多个与喷嘴交替存在的移动轮的低压(LP)涡轮，所述LP涡轮的所述移动轮沿着与所述HP涡轮的所述移动轮旋转方向相反的方向旋转；和中间涡轮壳体，其具有内、外壳体壁，与跨越在内、外壳体壁之间的臂共同限定HHP和LP涡轮之间的气流通道。
该涡轮在所述HP涡轮的出口与所述LP涡轮的所述第一移动轮之间没有具有偏转气流功能的喷嘴或装置。
因而，尽管省略了所述LP涡轮第一阶段的所述喷嘴，但是中间涡轮壳体的功能从只是结构上的扩展成任何气流-偏转功能。在所述LP涡轮第一阶段不对气流进行偏转与现有技术中的结构相比，实际上会造成整个所述LP涡轮载荷分布上存在一些退化，然而可以通过减小叶片数量上的节约来补偿这种退化。在所述中间涡轮壳体中，所述臂不会执行任何气流偏转功能，因此可以存在有限的个数，只要充分执行壳体的结构功能即可。而且，这种类型的非偏转臂比具有偏转形的臂产生的压力损失更小，因此由于轮廓形状造成的损失的次级损失大大减少了。此外，接收非偏转气流的LP涡轮第一阶段的移动轮具有较小的偏移以传递气流，因此可以具有更少数量的叶片。此外可完全省略所述LP涡轮的所述入口喷嘴。
减少叶片的数量还可以使重量和成本明显降低。
优选地，为了获得良好的绩效预算，将所述HP涡轮设计成为所述中间涡轮壳体输送回旋气流，所述HP涡轮中存在的气流的大体方向与所述涡轮的轴向形成例如不少于20°的角度，至少用于寻找最佳性能的操作点。
本发明还提供一种装备有如上所述涡轮的燃气涡轮发动机。
附图说明
通过阅读参考非限制性说明的下列描述并结合附图，本发明会更加易于理解，其中：
图1和图2，如上所述，非常概略地示出了现有技术中的反转高压和低压涡轮结构的示意图；
图3非常概略地示出可实现本发明的燃气涡轮的示意图；
图4非常概略地示出本发明用于反转高压和低压涡轮的结构的示意图；和
图5是沿装置轴向半截面的简化局部视图，其中该装置包括本发明一个实施方式的高压涡轮、中间涡轮壳体，和低压涡轮。
具体实施方式
本发明特别适用于航空喷气发动机。这种发动机，如图3非常概略地示出，沿着从上游到下游的气体流动方向包括：置于发动机入口处的风扇1；压缩机2；燃烧室3；高压(HP)涡轮4；和低压(LP)涡轮5。HP和LP涡轮分别通过同轴连接到压缩机上和风扇上。
根据本发明的结构，如图4以非常示意性地和图5中局部轴向半截面示出，该装置包括HP涡轮、中间涡轮壳体，和LP涡轮。
在这些实施例中，HP涡轮40包括单个涡轮阶段，带有涡轮入口喷嘴42，用来接收来自燃烧室(未示出)的原始气流；和移动轮46，具有由存在于其正下游的由HP涡轮输送的气流。喷嘴42包括静翼片43，延伸由内、外平台44和45限定的空间，该空间构成气流进入涡轮的入口流动截面。移动轮46包括叶片47，在由外涡轮环48包围的空间中旋转运动。移动轮46可围绕涡轮的轴49旋转运动，并连接到涡轮轴(未示出)上。
LP涡轮包括多个涡轮阶段。第一阶段，或者最上游阶段，包括移动轮561，其前面没有LP涡轮的入口喷嘴，而每个下列阶段包括喷嘴522，…，52n和移动轮562，…，56n，其中n是大于2的整数，并且优选地为3以上。在图5所示的实施例中，LP涡轮阶段的数量等于3，移动轮561，562，563和喷嘴522，523。LP涡轮的移动轮可以沿着与移动轮46旋转方向相反的方向围绕轴49旋转移动，并且它们与涡轮轴(未示出)连接。每个LP涡轮喷嘴，例如522，包括在由内、外喷嘴环542、552限定的空间中延伸的翼片532。LP涡轮的每个移动轮，例如562，包括在由外涡轮环582包围的空间中旋转移动的叶片572。
只执行结构功能的中间涡轮壳体60，介于HP和LP涡轮之间。壳体60包括内、外壳体结构61和63，其支撑中间限定HP和HP涡轮之间气流的通道66的内、外壁62和64。结构臂68跨越壁62和64之间的通道66的整个宽度并与其连接。臂68是流线型的以减少通道66中的空气动力损失，但是它们没有被定形为如图2中实施例所示以执行气流偏转功能。因此可以将臂的数量限制在能够充分执行预期结构功能的个数。应该注意到外壳体结构63连接HP和LP涡轮的外壳体结构41和51。
利用根据本发明的结构，LP涡轮的上游移动轮561轻载。因此可以只设置有限数量的叶片。为了补偿轮561上的轻载，可以在轮562和563上提供与在LP涡轮第一移动轮上游带有喷嘴的常规结构相比更大的负载。
有利地，为了从轮561获得良好的绩效预算，希望给来自HP涡轮的气流施加相当大量围绕轴49的回转。优选地，来自HP涡轮的气流的总体方向与轴49之间的角度，在由移动轮46传递时，应该不小于30°，例如位于20°到45°范围内。
尽管LP涡轮没有入口喷嘴，然而在LP涡轮的移动轮之间存在不平衡负载时，因叶片数量而在重量和成本上的节约使其可以获得与现有技术相比绝对综合的绩效预算。

Claims (4)

1.一种燃气涡轮，包括：具有移动轮(46)的高压涡轮(40)；带有多个与喷嘴(52)相替出现的移动轮(56)的低压涡轮(50)，所述低压涡轮的所述移动轮沿着与所述高压涡轮的移动轮旋转方向相反的方向旋转；中间涡轮壳体(60)，具有内、外壳体壁(62、64)，与跨越在内、外壳体壁之间的臂(68)共同限定所述高压涡轮的出口与所述低压涡轮之间的气流通道；
所述燃气涡轮的特征在于，在所述高压涡轮(40)的出口与所述低压涡轮(50)的最上游的移动轮(561)之间没有具有气流偏转功能的装置。
2.如权利要求1所述的燃气涡轮，其特征在于，所述高压涡轮(40)被设计成输送在所述中间涡轮壳体(60)中回旋的气流。
3.如权利要求2所述的燃气涡轮，其特征在于，存在于所述高压涡轮(40)中的气流方向相对于所述涡轮的轴向形成不小于20°的角度。
4.一种燃气轮发动机，装备有如权利要求1至3之一所述的涡轮。
CN2008100061071A 2007-02-07 2008-02-03 带有反转高压和低压涡轮的燃气涡轮 Expired - Fee Related CN101240719B (zh)

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Families Citing this family (41)

* Cited by examiner, † Cited by third party
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US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
US20150308351A1 (en) 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
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US10605168B2 (en) 2017-05-25 2020-03-31 General Electric Company Interdigitated turbine engine air bearing cooling structure and method of thermal management
US10738617B2 (en) 2017-09-20 2020-08-11 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10823000B2 (en) 2017-09-20 2020-11-03 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10781717B2 (en) 2017-09-20 2020-09-22 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10914194B2 (en) 2017-09-20 2021-02-09 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US11098592B2 (en) 2017-09-20 2021-08-24 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10823001B2 (en) 2017-09-20 2020-11-03 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10508546B2 (en) 2017-09-20 2019-12-17 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US11118535B2 (en) 2019-03-05 2021-09-14 General Electric Company Reversing gear assembly for a turbo machine
US11549373B2 (en) 2020-12-16 2023-01-10 Raytheon Technologies Corporation Reduced deflection turbine rotor
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
DE102022124926A1 (de) * 2022-09-28 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zum Erzeugen von elektrischer Energie für ein Luftfahrzeug und Luftfahrzeug

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1021588C (zh) * 1988-10-10 1993-07-14 通用电气公司 燃气涡轮发动机
US5443590A (en) * 1993-06-18 1995-08-22 General Electric Company Rotatable turbine frame
EP1577491A1 (en) * 2004-03-19 2005-09-21 ROLLS-ROYCE plc Turbine engine arrangements
CN1877084A (zh) * 2005-06-06 2006-12-13 通用电气公司 向前倾斜的涡轮机喷嘴

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2207191B (en) * 1987-07-06 1992-03-04 Gen Electric Gas turbine engine
US4976102A (en) * 1988-05-09 1990-12-11 General Electric Company Unducted, counterrotating gearless front fan engine
GB2267736B (en) * 1992-06-09 1995-08-09 Gen Electric Segmented turbine flowpath assembly
US6619030B1 (en) * 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US7594388B2 (en) * 2005-06-06 2009-09-29 General Electric Company Counterrotating turbofan engine
US7513102B2 (en) * 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1021588C (zh) * 1988-10-10 1993-07-14 通用电气公司 燃气涡轮发动机
US5443590A (en) * 1993-06-18 1995-08-22 General Electric Company Rotatable turbine frame
EP1577491A1 (en) * 2004-03-19 2005-09-21 ROLLS-ROYCE plc Turbine engine arrangements
CN1877084A (zh) * 2005-06-06 2006-12-13 通用电气公司 向前倾斜的涡轮机喷嘴

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CN101240719A (zh) 2008-08-13
FR2912181B1 (fr) 2009-04-24
UA95608C2 (ru) 2011-08-25
EP1956191B1 (fr) 2012-04-11
FR2912181A1 (fr) 2008-08-08
CA2619894A1 (fr) 2008-08-07

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