CN1755080B - 用于涡轮机的鼻锥 - Google Patents

用于涡轮机的鼻锥 Download PDF

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CN1755080B
CN1755080B CN200510087595XA CN200510087595A CN1755080B CN 1755080 B CN1755080 B CN 1755080B CN 200510087595X A CN200510087595X A CN 200510087595XA CN 200510087595 A CN200510087595 A CN 200510087595A CN 1755080 B CN1755080 B CN 1755080B
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nose cone
fan blade
axle
air
turbo machine
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CN1755080A (zh
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扬·勒布雷
爱德华·拉姆斯腾
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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
    • F02C7/057—Control or regulation
    • 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
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • 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
    • 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
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/406—Transmission of power through hydraulic systems
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/64—Hydraulic actuators
    • 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]

Abstract

本发明公开了一种用于涡轮机，特别是像涡轮喷气机这样的鼻锥。所述鼻锥被安装在一支承风扇叶的轴的端部并且与控制轴向位移装置相连，从而可以调整所述鼻锥相对于所述风扇叶片的轴向位置。

Description

用于涡轮机的鼻锥
技术领域
本发明涉及一种用于涡轮机，特别是涡轮喷气机的鼻锥。
背景技术
一涡轮喷气机在其上游侧具有一同时向一风扇和一压缩机供应空气的进气口，该压缩机具有一些由固定到一轴上的圆盘所支承的叶片，该轴延伸过所述涡轮喷气机的大部分空间并且由所述涡轮喷气机的一涡轮机驱动而旋转。
一鼻锥安装在所述轴的上游侧，从而使得部分进入到涡轮喷气机内部的空气流被朝着风扇叶片反射，所述气流然后被分成一穿过所述压缩机入口的主气流，和环绕压缩机流动的次气流，并且该次气流然后与所述主气流相混合，并且/或供给冷却循环以冷却所述涡轮喷气机的冷却元件。
在现有技术中，所述鼻锥被固定安装在轴的一端，并且其形状和尺寸被确定为可以针对特定飞行状态对进入到风扇叶片根部的气流角度进行优化。
所述鼻锥的形状和尺寸也可以被确定为可以防止冰和固体物质或颗粒进入。
因此，所述鼻锥所选定的形状和尺寸是这两个相互矛盾因素折中的结果，并且因而实际上他们并不真正满足这两个矛盾因素中的任何一个。
发明内容
本发明的一个特定目是针对上述问题提供一种简单、廉价和有效的解决方案。
本发明提供了一涡轮喷气机的鼻锥，其允许针对特定飞行状态对进入到所述风扇叶片根部的气流角度进行优化，同时保证有效防止冰和固体物质或颗粒进入。
为此，本发明提供一种用于涡轮机，特别是涡轮喷气机的鼻锥，所述鼻锥被安装在一支承风扇叶片的轴的端部上，并用于控制一进入到所述风扇叶片根部气流的攻角，所述鼻锥通过一控制轴向位移装置安装在上述轴上，从而可以调整所述鼻锥相对于所述风扇叶片的轴向位置。
在上述轴的端部轴向移动所述鼻锥使得能够为适应不同的飞行状态对进入到所述风扇叶片根部气流的攻角进行调整和优化，并且提供更好的防止冰和固体进入的防护。
作为例子，在起飞过程中，所述鼻锥轴向移动到一相对于风扇叶片的前面位置，从而尽可能地将冰和固体向外反射。
在飞行过程中，所述鼻锥可从所述前面位置轴向向后移动到一或多个的后面位置上，以便调整进入到所述风扇叶片根部气流的攻角，并且作为飞行状态的函数对所述角进行优化。
在本发明的一优选实施例中，所述鼻锥通过一液压致动器与上述轴连接，该致动器具有一固定在所述轴端部的缸体和一支承所述鼻锥的活塞杆。
用于控制所述鼻锥轴向位移的控制装置由所述轴支撑，并且被驱动与所述鼻锥和风扇叶片一起旋转.所述控制装置与一旋转液压流体供应装置相连，该旋转液压流体供应装置具有一受压状态的液压流体供应源和用于调节压力的调节装置.
所述鼻锥的轴向位置是通过调节所述液压致动器中的压力来确定的。该轴向位移控制装置具有易于制作和实现的优点。
本发明还公开了一种诸如涡轮喷气机的涡轮机，所述涡轮机包括一具有如上所述类型的鼻锥。
附图说明
通过阅读下述由非限定性实例给出的描述以及参考附图，可见本发明的其他优点和特征。
图1为一个高度简化的有关一装有如本发明所述鼻锥的涡轮喷气机的轴向截面的半视图。
具体实施方式
如附图所示的涡轮喷气机具有一轴10，其由一安装在燃烧室出口处的涡轮机驱动而绕着其轴线12旋转，在旋转中该轴10通过被安装在涡轮喷气机定子的部分16上的轴承14而对中和引导。
在其上游侧，该轴10支承多个带有径向内缘20的风扇叶片18，它们通过常规方式被安装在轴10的截头圆锥体部分的周边。
风扇叶片18的外围由一大致圆筒状管22所环绕，从而将进气流导入所述涡轮喷气机。
一鼻锥24被安装在轴10的上游侧并且与支承着风扇叶片18的轴的截头圆锥体部分相连，从而使进气流的中心部分26朝向叶片18转向。
在紧临着风扇叶片18的下游侧有一用于向一带有叶片的压缩机进气的环状孔28，这些叶片被支承在轴10的部分30上并被容置在一圆筒状外壳32中，该外壳与管22的内表面一起形成了一环状空间34。
进入到压缩机环状孔28中的空气形成了被涡轮喷气机的压缩机压缩的主气流，然后与燃油混合并在一燃烧室中燃烧，在释放气流的过程中提供能量给涡轮机的活动叶片从而驱动轴10旋转。进入到环状空间34内的空气形成了和主气流相混合的次气流从而对涡轮喷气机的各个元件进行冷却，并且可增大涡轮喷气机的推力。
在现有技术中，鼻锥被固定安装在轴的一端，并且其形状和尺寸被确定为针对特定飞行状态对进入到风扇叶片18根部的气流角度进行优化，鼻锥还能够将固体和颗粒向外反射。
在本发明中，一控制装置通过轴10支承并且设计成用于改变鼻锥24相对于风扇叶片18的轴向位置，通过该控制装置，鼻锥24被安装成可沿着轴10的轴线12进行轴向移动。
因此，鼻锥24在一后面位置38和一前面位置40之间可移动，所述后面位置38可以是现有技术中的固定位置或另一更靠后的位置(如图中实线所示)，所述前面位置40增加空气和固体以及颗粒相对于轴10轴线的对外反射。鼻锥24还可被定位在前面位置40与后面位置38之间的预定的中间位置上。
在所示实施例中，控制鼻锥24轴向位移的控制装置包括一液压致动器42，该液压致动器42具有一通过特定装置44安装在轴10上并沿轴向延伸的缸体，并且具有一活塞杆46，该活塞杆46沿轴向向上游延伸并与鼻锥24相连从而使其发生轴向运动。
液压致动器42包括用于接收液压流体的一上游室48和一下游室50，所述室被致动器的活塞52以密封方式分割开，并且通过与安装在轴10上的旋转连接器56相连的管54来输入液压流体，并且它们自身通过一具有可调节压力的压力调节器60的受压液压流体回路58进行供给流体，该压力调节装置60和回路58都安装在涡轮喷气机的定子中。
本发明所述装置按如下方式进行操作：起飞时，致动器42的室50中输入来自源58的液压流体，从而使活塞52向上游移动，与此同时经由活塞杆46鼻锥24被带动，直到该鼻锥到达前面位置40，在该位置上，存在于空气中的固体和颗粒被尽量地相对于旋转轴线12向外反射。在飞行过程中，致动器42的室48，50中的压力被调节使得活塞52将鼻锥运动至后面位置38，或运动到一位于上述前面位置40和后面位置38之间的预定位置，从而针对特定飞行状态对进入到风扇叶片18根部的气流角度进行优化。

Claims (5)

1.一种用于涡轮机的鼻锥，所述鼻锥被安装在一支承风扇叶片的轴的一端，所述风扇叶片被管环绕，并且，所述鼻锥用于控制一进入到所述风扇叶片根部气流的攻角，所述鼻锥通过一个控制轴向位移装置安装在上述轴上，从而可以调整所述鼻锥相对于所述风扇叶片的轴向位置，所述鼻锥可在所述管内在一个前面位置和一个后面位置之间发生轴向位移，在所述前面位置防止固体和颗粒通过用于使空气进入涡轮机的压缩机的孔进入，在所述后面位置对进入到所述风扇叶片根部的空气的攻角进行优化。
2.一种如权利要求1所述的鼻锥，其特征在于，所述鼻锥通过一液压致动器与上述轴连接，该致动器具有一固定在所述轴端部的缸体和一支承所述鼻锥的活塞杆。
3.一种如权利要求2所述的鼻锥，其特征在于，所述液压致动器与旋转液压流体供应装置相连。
4.一种如权利要求3所述的鼻锥，其特征在于，所述液压供应装置包括一压力状态下的液压流体源和用于调节所述压力的调节装置。
5.一种涡轮机，所述涡轮机具有一种如权利要求1所述的鼻锥。
CN200510087595XA 2004-07-28 2005-07-28 用于涡轮机的鼻锥 Active CN1755080B (zh)

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FR0408338 2004-07-28
FR04/08338 2004-07-28
FR0408338A FR2873751B1 (fr) 2004-07-28 2004-07-28 Cone d'entree d'une turbomachine

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DE (1) DE602005005903T2 (zh)
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CA2513783C (fr) 2013-07-09
EP1621744A1 (fr) 2006-02-01
US20060056977A1 (en) 2006-03-16
JP2006037955A (ja) 2006-02-09
FR2873751A1 (fr) 2006-02-03
CN1755080A (zh) 2006-04-05
FR2873751B1 (fr) 2006-09-29
RU2005123972A (ru) 2007-02-10
DE602005005903T2 (de) 2009-06-04
US7419364B2 (en) 2008-09-02
DE602005005903D1 (de) 2008-05-21
EP1621744B1 (fr) 2008-04-09
CA2513783A1 (fr) 2006-01-28
RU2358130C2 (ru) 2009-06-10

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