CN1654804B - 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 PDFInfo
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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
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- 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
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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
- 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
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- 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
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。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR0401384 | 2004-02-12 | ||
FR0401384A FR2866387B1 (fr) | 2004-02-12 | 2004-02-12 | Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante |
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CN1654804A CN1654804A (zh) | 2005-08-17 |
CN1654804B true CN1654804B (zh) | 2011-06-01 |
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CN2005100091798A Active CN1654804B (zh) | 2004-02-12 | 2005-02-16 | 具有高旁路比的三轴旁路涡轮喷气发动机 |
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US (1) | US7299621B2 (zh) |
EP (1) | EP1566522B1 (zh) |
JP (1) | JP4237712B2 (zh) |
CN (1) | CN1654804B (zh) |
CA (1) | CA2495992C (zh) |
DE (1) | DE602005010923D1 (zh) |
ES (1) | ES2317168T3 (zh) |
FR (1) | FR2866387B1 (zh) |
RU (1) | RU2364740C2 (zh) |
UA (1) | UA83995C2 (zh) |
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- 2005-01-27 EP EP05290180A patent/EP1566522B1/fr active Active
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- 2005-01-31 US US11/045,365 patent/US7299621B2/en active Active
- 2005-02-02 JP JP2005026018A patent/JP4237712B2/ja active Active
- 2005-02-02 CA CA2495992A patent/CA2495992C/fr active Active
- 2005-02-10 UA UAA200501217A patent/UA83995C2/ru unknown
- 2005-02-11 RU RU2005103706/06A patent/RU2364740C2/ru active
- 2005-02-16 CN CN2005100091798A patent/CN1654804B/zh active Active
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Also Published As
Publication number | Publication date |
---|---|
CA2495992C (fr) | 2011-11-22 |
ES2317168T3 (es) | 2009-04-16 |
CN1654804A (zh) | 2005-08-17 |
US20050241291A1 (en) | 2005-11-03 |
FR2866387B1 (fr) | 2008-03-14 |
RU2364740C2 (ru) | 2009-08-20 |
DE602005010923D1 (de) | 2008-12-24 |
JP4237712B2 (ja) | 2009-03-11 |
FR2866387A1 (fr) | 2005-08-19 |
CA2495992A1 (fr) | 2005-08-12 |
EP1566522A1 (fr) | 2005-08-24 |
US7299621B2 (en) | 2007-11-27 |
UA83995C2 (ru) | 2008-09-10 |
JP2005226644A (ja) | 2005-08-25 |
EP1566522B1 (fr) | 2008-11-12 |
RU2005103706A (ru) | 2006-07-20 |
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