CN102378855A - 用于涡轮发动机的具有偏心前端的旋转进气整流罩 - Google Patents

用于涡轮发动机的具有偏心前端的旋转进气整流罩 Download PDF

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CN102378855A
CN102378855A CN201080015030XA CN201080015030A CN102378855A CN 102378855 A CN102378855 A CN 102378855A CN 201080015030X A CN201080015030X A CN 201080015030XA CN 201080015030 A CN201080015030 A CN 201080015030A CN 102378855 A CN102378855 A CN 102378855A
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cowling
air inlet
cone
axis
spin axis
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CN102378855B (zh
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麦克·德拉皮埃尔
哈维·吉格诺克斯
盖尔·罗若
西尔维·温腾伯格
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • 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
    • F02K3/06—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 front fan
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
    • Y10T137/0645—With condition responsive control means

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

本发明涉及用于涡轮发动机的旋转进气整流罩(30)，该整流罩具有旋转轴线(34)，并且其前端设置为相对于该旋转轴线(34)偏心。此外，整流罩的前部圆锥体(32)被限定进气整流罩的前端(44)的截断表面(70)截断。

Description

用于涡轮发动机的具有偏心前端的旋转进气整流罩
技术领域
本发明涉及涡轮发动机，特别是飞机涡轮发动机，所述发动机的类型优选地为喷气涡轮发动机。更具体地，本发明涉及安装在这些涡轮发动机上的旋转进气整流罩。
背景技术
上述的旋转进气整流罩通常由两个彼此固定的部分组成，其中前部的形式为圆锥体，后部的形式为护罩。后部护罩的后端以公知的方式与风扇叶片平台齐平，其与这些平台具有空气动力连续性，并位于这些平台的前面。
前部圆锥体具有形状为圆锥体尖端的前端，该圆锥体尖端的中心位于进气整流罩的旋转轴线上，该旋转轴线还对应于风扇和整个涡轮发动机的纵轴线。
已经公知，上述尖端为涡轮发动机上的一点，在该点处冰很容易聚集，因为尖端的中心位于旋转轴线上，无法施加大的离心力。因此，形成在圆锥体尖端上的冰在脱落之前会变大，在最终从尖端脱落时击中风扇叶片，导致损坏风扇叶片的风险。
已知可以安装除冰系统来降低上述风险，安装除冰系统的目的是确保聚集在圆锥体尖端上的冰在达到临界尺寸之前被脱除。但是，这种类型的系统由于其质量和尺寸而非常昂贵，尤其是归咎于安装该系统的进气整流罩的旋转，很难对其进行安装。
发明内容
因此，相较现有技术中的实施方式而言，本发明的目的为至少部分地提供解决上述缺点的方案。
为此，发明的第一个目的为用于涡轮发动机的旋转进气整流罩，该整流罩具有旋转轴线，并包括限定整流罩的前端的前部圆锥体。根据本发明，该前端设置为相对于整流罩的旋转轴线而偏心，并且该前端被限定进气整流罩的前端的截断表面所截断。
因此，在运行过程中，当冰在进气整流罩的前端上聚集时，得益于前端的偏心性质，冰将会承受大的离心力。这将会促进冰的脱除，使得冰在达到能够对下游风扇叶片造成损坏的临界尺寸之前从杆上分离。
因此，本发明具有以下优点：设计简单，极其可靠，成本和尺寸不会很大。前部圆锥体被截断对设计的简化做出了巨大贡献。
根据本发明的优选实施方式，所述前部圆锥体是倾斜的，其具有与进气整流罩的旋转轴线倾斜的轴线。然而，前部圆锥体也可以是直的，其轴线可以与进气整流罩的旋转轴线重合。因此，优势是可以从现有技术中的传统前部圆锥体开始，对其进行截断，以实现所要求的实施方式。
优选地，上述截断表面近似于平的，相对于同进气整流罩的旋转轴线正交的平面倾斜。
如上所述，不管何种实施方式，旋转进气整流罩优选地包括前部圆锥体和后护罩。
最后，本发明的另一个目的为优选地用于飞机的涡轮发动机，该涡轮发动机包括如上所述的旋转进气整流罩。
本发明的其他优点和特征在以下非限制性的详细内容中进行描述。
附图说明
参照附图，进行如下说明：
图1示出了根据本发明优选实施方式的飞机涡轮发动机的前部的纵向半截面图；
图2示出了安装于图1所示的涡轮发动机上的旋转进气整流罩的放大图；以及
图3为安装于图2所示的旋转进气整流罩上的前部圆锥体的透视图。
优选实施方式的详细描述
图1示出了根据本发明优选实施方式的涡轮喷气式飞机的涡轮发动机的前部1。
在图1中仅示出了气体发生器的低压压缩机3，举例来说，所述气体发生器为双压缩机气体发生器。
从前端开始，沿着箭头9所示的在涡轮发动机中流体朝着后端流动的大致方向，涡轮发动机包括空气入口4，风扇6，用于将气体分为环形核心发动机气流16和位于核心发动机气流16径向外侧的环形风扇气流18的分流器14，以及支撑风扇出口引导叶片组件12的内部环10。显然，本领域技术人员公知的这些常规元件中的每一个都是环形的，并且中心位于涡轮发动机的纵轴线22上。
因此，穿过风扇6的气流F与分流器14的上游端接触后被划分为两个单独的气流，即，进入通道16的主气流F1，以及进入通道18并穿过风扇出口引导叶片组件12的辅气流F2。
此外，涡轮发动机在前端包括旋转连接至风扇6的旋转进气整流罩30。以公知的方式，整流罩30包括具有轴线33的前部圆锥体32，以及优选地通过螺栓38固定安装于圆锥体32上的后护罩36。整流罩的后端与风扇叶片42的平台40齐平，在这些平台的前面与这些平台具有空气动力连续性。
本发明的特殊特征之一是旋转进气整流罩30的前端44与整流罩30的旋转轴线34不同中心，轴线34还对应于风扇6的轴线，更普遍地，还对应于涡轮发动机的纵轴线22。
在图1至图3所示的优选实施方式中，通过使用直的前部圆锥体32来获得前端4的离心性质，前部圆锥体32的轴线33与圆锥体的旋转轴线34以及涡轮发动机的纵轴线22重合。此外，圆锥体的前部被近似于平的截断表面70截断，相对于同轴线22、34正交的平面P，该截断表面以例如1度至15度之间的角度B倾斜。因此，所述截断可以限定前部离心端44，因为其对应于椭圆形72的最前部，如图3所示，所述椭圆形72由圆锥体32和近似于平的截断表面70之间的交集形成。
应该注意到，可以想到另外一个相似的实施方式，其具有倾斜的前部圆锥体32，也就是说，其具有相对于旋转轴线34倾斜的轴线33。
以公知的方式，平衡珠50可以设置于前部圆锥体32，内侧接近于与后护罩36螺栓连接处。设置珠50的目的是对不均衡质量进行补偿，由此，如图2所示，其沿圆周方向具有变化的厚度。可以通过形成扩孔52来形成所述珠，扩孔52的轴线54与轴线22、34不同中心。另一个平衡珠62被提供，以完善平衡珠50以及对不均衡质量进行补偿，该不均衡质量本质上是由于前端44相对于旋转轴线34的偏移所造成的，该平衡珠62设置于内侧，接近于前端44。如图2所示，珠62沿圆周方向具有变化的厚度，并同样可以通过形成扩孔64来形成，扩孔64的轴线66与轴线22、34不同中心。可替代地，或者同时地，可以通过在圆周方向改变形成圆锥体32的外壳的厚度来对不平衡质量进行补偿。
当风扇和进气整流罩30与聚集有冰60的偏心前端44一起旋转时，巨大的离心力被施加到冰上，促进冰从整流罩脱除。
当然，本领域技术人员可以对以上仅作为非限制性例子进行描述的本发明进行各种修改。

Claims (6)

1.用于涡轮发动机的旋转进气整流罩(30)，所述整流罩具有旋转轴线(34)，并包括限定所述进气整流罩的前端(44)的前部圆锥体(32)，特征在于所述前端(44)设置为相对于所述进气整流罩的所述旋转轴线(34)偏心，还在于所述前部圆锥体(32)被限定所述进气整流罩的所述前端(44)的截断表面(70)截断。
2.根据权利要求1所述的整流罩，特征在于所述前部圆锥体(32)是倾斜的，并具有与所述进气整流罩的所述旋转轴线(34)倾斜的轴线(33)。
3.根据权利要求1所述的整流罩，特征在于所述前部圆锥体(32)具有与所述进气整流罩旋转轴线(34)平行且重合的轴线(33)。
4.根据上述权利要求任意一项所述的整流罩，特征在于截断表面(70)为近似于平的，并相对于同所述进气整流罩的所述旋转轴线(34)正交的平面(P)倾斜。
5.根据上述权利要求任意一项所述的整流罩，特征在于该整流罩包括从后护罩(36)向前的所述前部圆锥体(32)。
6.涡轮发动机(1)，其优选用于飞机，其包括根据上述权利要求任意一项所述的旋转进气整流罩(44)。
CN201080015030.XA 2009-03-31 2010-03-29 用于涡轮发动机的具有偏心前端的旋转进气整流罩 Active CN102378855B (zh)

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FR0952056 2009-03-31
FR0952056A FR2943726B1 (fr) 2009-03-31 2009-03-31 Capot d'entree tournant pour turbomachine, comprenant une extremite avant excentree
PCT/EP2010/054080 WO2010112453A1 (fr) 2009-03-31 2010-03-29 Capot d'entree tournant pour turbomachine, comprenant une extremite avant excentree

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US8984855B2 (en) 2015-03-24
JP2012522170A (ja) 2012-09-20
US20120036827A1 (en) 2012-02-16
FR2943726B1 (fr) 2014-04-25
US20160003146A1 (en) 2016-01-07
RU2011143863A (ru) 2013-05-10
EP2414655B1 (fr) 2013-06-05
EP2414655A1 (fr) 2012-02-08
CA2756845C (fr) 2017-01-24
BRPI1013370B1 (pt) 2020-06-23
BRPI1013370A2 (pt) 2016-03-29
CA2756845A1 (fr) 2010-10-07
JP5466291B2 (ja) 2014-04-09
US9243562B1 (en) 2016-01-26
CN102378855B (zh) 2014-03-12
WO2010112453A1 (fr) 2010-10-07
RU2529766C2 (ru) 2014-09-27

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