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CN1654804A - 具有高旁路比的三轴旁路涡轮喷气发动机 - Google Patents

具有高旁路比的三轴旁路涡轮喷气发动机 Download PDF

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CN1654804A
CN1654804A CNA2005100091798A CN200510009179A CN1654804A CN 1654804 A CN1654804 A CN 1654804A CN A2005100091798 A CNA2005100091798 A CN A2005100091798A CN 200510009179 A CN200510009179 A CN 200510009179A CN 1654804 A CN1654804 A CN 1654804A
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fan
grid
bypass
turbojet engine
turbojet
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CN1654804B (zh
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雅克·巴尔特
法比耶纳·拉科尔
扬·勒布雷
瓦妮莎·勒鲁索
帕特里克·莫雷尔
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

本发明涉及一种空气动力学地匹配涡轮喷气发动机的后风扇(3)，所述涡轮喷气发动机具有位于中间壳体(2)前部的两个风扇(3，5)和低压压缩机，所述风扇由两个独立的轴(4，6)驱动。所述压缩机(7)置于两个风扇的叶片(10，14)之间，并包括位于前风扇(3)的驱动轴(4)驱动的轮(41)周边的至少一个转子叶片环(40)，以及置于所述转子叶片环(40)的任一侧、并在格栅承载环(47)内侧的定子叶片的至少两个格栅(45，46)。静止外格栅(48)和可变节距定子(50)将环(47)连接到风扇壳体(12)。

Description

具有高旁路比的三轴旁路涡轮喷气发动机
技术领域
本发明涉及一种具有高旁路比(by-pass ratio)的三轴(spool)旁路涡轮喷气发动机，该涡轮喷气发动机在中间壳体前部具有前风扇和后风扇，在旁路气流中存在外结构格栅，在主气流中存在内结构格栅，风扇具有沿径向向外延伸到风扇壳体的叶片，该风扇壳体形成旁路气流的外侧，所述涡轮喷气发动机还具有低压压缩机，用于压缩进入主气流通道中的空气，所述前风扇和所述后风扇通过两根同轴的轴直接和单独旋转。
背景技术
在具有高旁路比的现代高功率涡轮喷气发动机中，风扇具有大的直径，叶片末端的圆周速度正比于该直径以及风扇转速。为了得到高的效率，圆周速度必须低于声速。在具有单一风扇的传统涡轮喷气发动机中，这是通过在驱动轴和风扇之间插入减速齿轮装置实现的。然而，齿轮装置明显增大了发动机重量，并且还降低效率。另一种技术包括装备具有两个风扇的涡轮喷气发动机，即前风扇和后风扇，所述风扇装配在中间壳体的前部，每个风扇由各自的低速驱动轴驱动，没有插入任何减速齿轮装置。每个风扇提供旁路通道的气流，基本是旁路空气推进功率的一半。
特别是在美国专利3861139和4860537中解释了目前工艺水平，其中描述了引言中提及的喷气发动机类型，每个专利具有两个相互反向旋转的风扇，该风扇连接到也有相互反向旋转转子的低压压缩机，一个转子由前风扇的驱动轴驱动，另一个转子由后风扇的驱动轴驱动。两个风扇叶片固定节距的确定，达到特定发动机速度下优化两个风扇的匹配。但在其它速度下效率必然降低。
发明内容
本发明的目的是使不同发动机速度下优化后风扇匹配成为可能。
本发明通过以下事实达到上述目的：低压压缩机轴向布置在前风扇叶片与后风扇叶片之间，并包括从前风扇的驱动轴驱动的轮圆周延伸的至少一个转子叶片环，以及轴向布置在所述转子叶片环任一侧、并且径向布置在格栅承载环内侧的定子叶片的至少两个格栅，所述环由置于旁路气流中的外格栅支撑，所述外格栅由风扇壳体支撑，以及可变节距定子置于所述外格栅下游，用于保证后风扇可接受地匹配。
并且，优先采用下面有优势的方案。
外格栅具有多个静止径向臂，并且可变节距定子具有能绕径向轴线枢转的多个可移动径向臂，每个可移动径向臂紧靠静止径向臂的进入点。
每个可移动径向臂具有插在格栅承载环中的径向内铰链。
每个可移动径向臂具有插在风扇壳体中的径向外铰链。
径向外铰链装有驱动臂，所述驱动臂具有铰接在控制环上的自由端。
非常优选地是，前风扇和后风扇是反向旋转的风扇。
附图说明
通过参考附图，并阅读下面以例子形式给出的描述，将清楚本发明的其它优点和特征。附图是：
图1是根据本发明涡轮喷气发动机前部的半个部分的示意图。
具体实施方式
附图表示沿轴线X的涡轮喷气发动机的前部1，其在中间壳体2前部具有前风扇3和后风扇5，所述前风扇3由内驱动轴4驱动，所述后风扇5由与内轴4同轴并环绕所述内轴的中间驱动轴6驱动，并且低压压缩机沿轴向布置在前风扇3和后风扇5之间，以便压缩进入主气流F1的通道8的空气。
前风扇3具有叶片10，从轮11的周边延伸到风扇壳体12，风扇壳体12形成旁路空气F2的通道13外侧。
同样地，后风扇具有叶片14，从轮15的周边延伸到风扇壳体12，穿过主气流F1的通道8以及穿过旁路空气F2的通道13。
前风扇3的轮11通过锥体16连接到内轴4，后风扇5的轮15通过锥体17连接到中间轴6。
内轴支座18和内轴滚柱轴承19置于内轴4和中间轴6之间。中间轴6通过止推轴承20和滚柱轴承21由中间壳体2支撑。标号22代表使中间壳体2支撑高压压缩机24的驱动轴23的止推轴承，其中高压压缩机24位于中间壳体2之后。
中间壳体2具有位于旁路气流F2内的外结构格栅30以及位于主气流F1内的内结构格栅31。外结构格栅30外侧连接到风扇壳体12。环形盒32置于外结构格栅30和内结构格栅31之间，在用于分离主气流F1和旁路气流F2的分离尖端33的下游。分离尖端33位于后风扇5的叶片14的上游。
低压压缩机7位于前风扇3和后风扇5之间。所述压缩机具有处于主气流F1内的转子叶片环40，转子叶片环40从轮41的周边延伸，轮41在结构上通过相反取向锥体42连接到锥体16，并通过壳43连接到前风扇3的叶片10的平台，壳43形成主气流F1通道8的内侧，并且还具有轴向置于转子叶片40的环的任一侧的定子叶片45和46的两个格栅。
定子叶片的两个格栅45和46径向延伸到格栅承载环47的孔中，所述格栅承载环通过外结构格栅48由风扇壳体12支撑，外结构格栅48具有臂49，臂49沿径向穿过旁路气流F2的通道13。臂49的径向内端连接到格栅承载环47的前部。
节距可变的定子50设置成紧靠外结构格栅48的下游。所述定子50具有多个按空气动力学成形的可移动径向臂51，径向臂能协调一致地绕径向轴转动，并穿过旁路气流F2的通道13。可移动臂51的数量等于外结构格栅48中静止臂49的数量，每个可移动臂紧靠静止臂49的下游。每个可移动臂51具有插在格栅承载环47中的径向内铰链52，以及插在风扇壳体12中的径向外铰链53。在这种特定实施例中，铰链53、53可以枢转。径向外铰链53装有驱动臂54，驱动臂54具有自由端55，自由端铰接在轴线X的控制环56上。当通过致动器(未图示)移动使控制环56轴向运动，导致所有驱动臂54绕其铰链52和53限定的径向轴线转动，并随着飞行参数的变化改变定子50的节距，特别是随着不同发动机速度下两个风扇3和5的旋转速度的变化改变定子的节距。
低压压缩机7包括定子和限制成随风扇3旋转的转子的事实，使两个风扇3和5沿相同方向旋转成为可能。但是，两个风扇3和5也可以相互反向旋转并由两个相互反向旋转的涡轮转子驱动，所述涡轮转子具有轴向交错的各自转子叶片环，从而由于没有涡轮定子而可减小工作涡轮的长度和重量。

Claims (6)

1.一种具有高旁路比的三轴旁路涡轮喷气发动机，所述涡轮喷气发动机在中间壳体(2)前部具有前风扇(3)和后风扇(5)，所述中间壳体(2)在旁路气流(F2)中存在外结构格栅(30)，在主气流(F1)中存在内结构格栅(31)，所述风扇具有沿径向向外朝风扇壳体(12)延伸的叶片(10，14)，所述风扇壳体形成旁路气流的(F2)外侧，所述涡轮喷气发动机还具有低压压缩机(7)，用于压缩进入主气流(F1)通道(8)中的空气，所述前风扇(3)和所述后风扇(5)通过同轴的两根轴(4，6)直接和单独地旋转；
所述涡轮喷气发动机的特征在于，低压压缩机(7)轴向布置在前风扇(3)叶片(10)与后风扇(5)叶片(14)之间，并包括从前风扇(3)的驱动轴(4)驱动的轮(41)周边延伸的至少一个转子叶片环(40)，以及轴向布置在所述转子叶片环(40)任一侧、并且径向布置在格栅承载环(47)内侧的定子叶片的至少两个格栅(45，46)，所述格栅承载环(47)由置于旁路气流(F2)中的外格栅(48)支撑，所述外格栅由风扇壳体(12)支撑，以及可变节距定子(50)置于所述外格栅(48)下游，以保证后风扇可接受地被匹配。
2.如权利要求1所述的涡轮喷气发动机，其特征在于，外格栅(48)具有多个静止径向臂(49)，并且可变节距定子(50)具有能绕径向轴线枢转的多个可移动径向臂(51)，每个可移动径向臂(51)设置成紧靠静止径向臂(49)后边。
3.如权利要求2所述的涡轮喷气发动机，其特征在于，每个可移动径向臂(51)具有插在格栅承载环(47)中的径向内铰链(52)。
4.如权利要求3所述的涡轮喷气发动机，其特征在于，每个可移动径向臂(51)具有插在风扇壳体(12)中的径向外铰链(53)。
5.如权利要求4所述的涡轮喷气发动机，其特征在于，径向外铰链(53)装有驱动臂(54)，所述驱动臂具有铰接在控制环(56)上的自由端(55)。
6.如权利要求1所述的涡轮喷气发动机，其特征在于，前风扇(3)和后风扇(5)是反向旋转的风扇。
CN2005100091798A 2004-02-12 2005-02-16 具有高旁路比的三轴旁路涡轮喷气发动机 Expired - Lifetime CN1654804B (zh)

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FR0401384A FR2866387B1 (fr) 2004-02-12 2004-02-12 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante

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DE (1) DE602005010923D1 (zh)
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CN104520542A (zh) * 2012-08-09 2015-04-15 斯奈克玛 包括多个被安装在风扇上游的固定径向叶片的涡轮机组
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EP1566522B1 (fr) 2008-11-12
DE602005010923D1 (de) 2008-12-24
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US7299621B2 (en) 2007-11-27
RU2005103706A (ru) 2006-07-20
UA83995C2 (ru) 2008-09-10
JP2005226644A (ja) 2005-08-25
ES2317168T3 (es) 2009-04-16
CN1654804B (zh) 2011-06-01
CA2495992A1 (fr) 2005-08-12
US20050241291A1 (en) 2005-11-03
FR2866387A1 (fr) 2005-08-19

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