CN101228069B - 用于飞行器的发动机组件和包括至少一个这种发动机组件的飞行器 - Google Patents

用于飞行器的发动机组件和包括至少一个这种发动机组件的飞行器 Download PDF

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CN101228069B
CN101228069B CN2006800270610A CN200680027061A CN101228069B CN 101228069 B CN101228069 B CN 101228069B CN 2006800270610 A CN2006800270610 A CN 2006800270610A CN 200680027061 A CN200680027061 A CN 200680027061A CN 101228069 B CN101228069 B CN 101228069B
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turbojet
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让-马克·马尔蒂努
海尔韦·马尔什
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • F05D2250/22—Three-dimensional parallelepipedal
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/208—Heat transfer, e.g. cooling using heat pipes
    • 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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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
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  • Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
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Abstract

本发明涉及飞行器发动机组件，该组件包括涡轮喷气发动机(1)和热交换器(13)，热交换器位于涡轮喷气发动机上方并在涡轮喷气发动机中取冷却空气流和热空气流，其特征在于，冷却空气流和热空气流进入外壳的表面朝向涡轮喷气发动机的前方，并且它们的法线(n1、n2)相对于涡轮喷气发动机的轴线(A)倾斜。本发明还涉及带有至少一个本发明的发动机组件的飞行器。

Description

用于飞行器的发动机组件和包括至少一个这种发动机组件的飞行器
本发明涉及一种包括涡轮喷气发动机和热交换器的飞行器发动机组件。更确切地说，本发明涉及冷却空气和热空气到热交换器的路径，所述气流用于在交换器中流动。本发明还涉及热交换器相对于涡轮喷气发动机的位置。 
为了给飞行器机组人员和旅客所在的加压舱的空调管线提供空气，已经知道在所述飞行器的涡轮喷气发动机的压缩机处提取压缩空气。通过管道将这些压缩空气从涡轮喷气发动机送往加压舱的空调管线。但是，在涡轮喷气发动机的压缩机处得到的空气温度太高(该温度一般高于400℃)的情况下，必须预先冷却该压缩空气。 
为此，已经知道使用一种热交换器，该热交换器可以在从涡轮喷气发动机的压缩机处取出的压缩空气被注入到空调管线之前至少部分冷却所述压缩空气。该热交换器包括外壳，来自涡轮喷气发动机的压缩机的热空气流与在涡轮喷气发动机的进气管道取出的冷却空气流在外壳中交叉。在涡轮喷气发动机的进气管道取出的冷却空气流的温度约为70℃到100℃。气流交叉时有热量交换，该热交换使得可以在热交换器外壳的出口得到足够冷却的压缩空气，即温度约为200℃。然后冷却后的热空气流被引向空调管线，而冷却空气流通过设在发动机支柱或者说将涡轮喷气发动机固定在飞行器机翼上的支柱的罩上的孔眼排到涡轮喷气发动机外。 
热交换器的缺点之一是它的体积笨重。实际上，热交换器常常位于可以使涡轮喷气发动机与飞行器机翼中的一个机翼连接的支柱处。热交换器一般与支柱的上表面连在一起。更确切地说，热交换器安装在形成支柱的刚性结构的箱体的前部的上方，并且在覆盖所述箱体的流线型外罩内。因此需要把应冷却的热空气流和可以冷却热空气流的冷却空气流从位于支柱下方的涡轮喷气发动机引向位于支柱上方的热交换器。 
实际上，由于热交换器在支柱上的位置以及在涡轮喷气发动机中取出冷空气和热空气，热空气和冷却空气的到达管道二者都从支柱的箱体通过。支柱箱体是支柱的工作结构，该结构在管道穿过它的结构处变弱。另外，箱体内部空间中的管道的尺度很大，迫使所述管道在箱体中交叉。这 些交叉可能使冷却空气和热空气到达管道在涡轮喷气发动机和热交换器上的安装很困难。 
另外，冷空气实际上在涡轮喷气发动机的侧面，即在进气管道处取出，使得可以把冷却空气从涡轮喷气发动机带到热交换器的冷却空气到达管道应穿过涡轮喷气发动机的推力反向器的罩子。然而，推力反向器的罩子在它可以具有关闭位置和打开位置的情况下是运动的。因此，在推力反向器打开时，冷却空气到达管与反向器罩子之间的连接不能进行。因此需要设置带有密封垫的连接系统，以便能够在冷却空气到达管与反向器外罩之间建立无泄漏的连接。 
因此本发明的目的是通过改变冷空气流和热空气流向热交换器方向的路径来提供现有发动机组件的替代方案，从而避免使支柱箱体结构脆弱化，并简化热交换器在支柱和涡轮喷气发动机上的安装。 
为此，在本发明中，提出使热空气流和冷空气流从正面进入到热交换器外壳中。“从正面”的意思是指从前面，面对位于交换器外的空气流动。不仅热空气流，还有一般从下面进入到外壳中的冷空气流都从前面进入到外壳中。交换器外壳相对涡轮喷气发动机轴线的方向使其具有两个在涡轮喷气发动机前部的正面，使冷空气的到达管和热空气的到达管能够从正面伸入到热交换器中。所谓“前部”，是相对于外壳外空气流动方向而言。冷空气流和热空气流互相垂直地在外壳中流动。在一个具体的例子中，用于在热交换器中流动的冷空气流不再在进气管道处取出，而是在一岔口处取出，该岔口在进气管道的上游将进入到涡轮喷气发动机中的空气流分为两个分别沿发动机支柱的左翼和右翼的气流。该岔口或分离整流罩(carenage)由固定的即没有任何运动的前缘形成。因此冷空气到达管也可固定在位于所述岔口中的空气入口处。因此不再从涡轮喷气发动机罩的一侧或另一侧侧向取空气，而是从前面，与涡轮喷气发动机轴线平行地取空气。冷空气到达管从正面到达外壳。 
因此本发明的目的是一种飞行器发动机组件，该组件包括涡轮喷气发动机和热交换器，热交换器位于涡轮喷气发动机上方并从涡轮喷气发动机中取冷却空气流和热空气流，该组件的特征在于，冷却空气流和热空气流进入外壳的面朝向涡轮喷气发动机的前方，并且它们的法线相对于涡轮喷气发动机的轴线倾斜。 
根据本发明的发动机组件的实施例，所述组件可以包括以下附加特征的全部或部分： 
-交换器外壳连接到将涡轮喷气发动机固定在飞行器机翼上的支柱的上表面； 
-在所述涡轮喷气发动机的反向器罩的上游，在涡轮喷气发动机罩内的空气流动岔口区取所述冷却空气流； 
-外壳是沿涡轮喷气发动机轴线延伸并相对于所述轴线倾斜设置的平行六面体，冷却空气流从第一前进入面进入到外壳中，并从所述外壳的第一后输出面流出，热空气从外壳的第二前进入面进入，并从外壳的第二后输出面流出。 
-冷却空气流和热空气流在外壳中从前向后流动，并互相垂直； 
-外壳是相对于涡轮喷气发动机的轴线横向延伸的平行六面体，冷却空气流从下进入面进入到外壳中，并且从外壳的上输出面流出，热空气流从外壳的前进入面进入，并从所述外壳的后输出面流出； 
-冷却空气流在外壳中从下向上流动，热空气流在所述外壳中从前向后流动，冷却空气流和热空气流在外壳中互相垂直地流动。 
本发明还涉及包括至少一个根据本发明的发动机组件的飞行器。 
根据优选实施例，飞行器带有两个或四个根据本发明的发动机组件。 
通过下面的描述并参照附图将更好地了解本发明。附图作为本发明的非限定性示例给出。附图如下： 
-图1A：根据本发明第一实施例的发动机组件的俯视图； 
-图1B：根据图1A的热交换器的示意透视图； 
-图2A：根据本发明第二实施例的发动机组件的俯视图； 
-图2B：根据图2A的热交换器的示意透视图； 
图1A表示没有发动机舱的涡轮喷气发动机1。支柱10可以把涡轮喷气发动机1固定在飞行器的机翼(未示出)上。支柱10的金字塔形端部11固定在涡轮喷气发动机1的进气装置的后面。支柱10的主体或箱体12本身在两个点上固定在涡轮喷气发动机1的推进器部分2上。 
热交换器13与支柱10的箱体12的上表面15连接。上表面15是指支柱10朝向天空的表面。热交换器13包括外壳16，冷却空气流和热空气流在外壳16中流动，以便冷却应送往飞行器空调管线的热空气。热交换器13还包括把空气流带到外壳16中的空气到达管17、18和可以使空 气流从所述外壳16流出的空气排出部件。 
冷却空气流从进气装置通过冷却空气到达管17到外壳16，并且例如通过设在所述涡轮喷气发动机1的舱上的孔眼从涡轮喷气发动机排出。热空气流从发动机通过在支柱10的箱体12的高度上穿过箱体12的热空气到达管18到外壳16。热空气到达管18和冷却空气到达管17不交叉，因为冷却空气到达管17穿过机翼支柱10的金字塔部11，而热空气到达管18穿过箱体12(图1B)。 
外壳16的整体形状为长方形，并且相对于涡轮喷气发动机1的轴线A倾斜，以便具有两个分别形成冷却空气进入面19和热空气进入面20的前表面。冷却空气进入面19和热空气进入面20的法线n1和n2相对于涡轮喷气发动机1的轴线A倾斜。每个到达管17、18通过外壳16的不同前表面19、20进入到外壳16中，因此空气到达管17、18不再在外壳16处交叉。 
在外壳16内，来自冷却空气到达管17的冷却空气流和来自热空气到达管18的热空气流相对于飞行器前进方向从前向后流动。在外壳16内，冷却空气流和热空气流在互相平行的水平面内流动，但在互相垂直的方向流动。因此，热交换器13水平工作。 
部分冷却的热空气流通过热空气排出管21在外壳16的后输出面24处从外壳16流出，以便被送往空调管线(未出示)。另外，从外壳16流出的冷却空气流通过所述外壳16的第二后输出面向外排出，以便能够很容易地喷射到发动机支柱外。 
在本发明另一实施例中，热交换器13的外壳16的整体形状可以为斜方形，所述斜方形沿涡轮喷气发动机1的轴线A延伸。因此，外壳16仍有两个可以接纳冷却空气到达管17和热空气到达管18的前空气进入面。 
图2A表示热交换器13在支柱10上的定位的另一例子。外壳16的整体形状为长方形。 
如图2B中看到的，外壳16倾斜在支柱12上，并相对于涡轮喷气发动机1的轴线A横向延伸。外壳16的下表面22不与机翼支柱10的上表面15连在一起，而是倾斜延伸在所述上表面15上方。下表面22是指外壳16的朝向机翼支柱10的上表面15的表面。外壳16例如通过外壳16的后表面和下表面22的公共棱与支柱10的上表面15连接。 
外壳16的倾斜使其在所述外壳16的下表面释放出一进入口。因此下 表面22和在机翼支柱10上方比下表面22抬高的前表面19一样，在涡轮喷气发动机1的前面。下表面22和前表面19面对在交换器外流动的空气。下表面22和前表面19的法线相对于涡轮喷气发动机1的轴线A倾斜。 
冷却空气流从下表面22进入到外壳16中，而热空气流从前表面19进入到所述外壳16中。冷却空气流从下进入面22到上输出面23穿过外壳16，而热空气流从前进入面19到所述外壳16的后输出面24穿过外壳16。因此冷却空气流与热空气流垂直地穿过外壳。因此热交换器13垂直工作。 

Claims (9)

1.一种飞行器发动机组件，包括涡轮喷气发动机(1)和热交换器(13)，该涡轮喷气发动机安装在支柱下面，该热交换器位于所述支柱上方并在涡轮喷气发动机中取冷却空气流和热空气流，其特征在于，冷却空气流和热空气流进入外壳的表面朝向涡轮喷气发动机的前方，并且它们的法线(n1、n2)相对于涡轮喷气发动机的轴线(A)倾斜，所述热空气流和所述冷却空气流在所述外壳中彼此垂直地流动，以及
所述热空气流从所述涡轮喷气发动机的推进器(2)通过在所述支柱的箱体(12)的高度上穿过所述箱体(12)的管(18)到所述热交换器的外壳(16)，所述冷却空气流通过穿过所述支柱的金字塔部(11)的管(17)到达。
2.如权利要求1所述的发动机组件，其特征在于，在所述涡轮喷气发动机的反向器外罩上游，在涡轮喷气发动机外罩内的空气流分岔区内取冷却空气流。
3.如权利要求1所述的发动机组件，其特征在于，热交换器的外壳(16)连接到将涡轮喷气发动机固定在飞行器机翼上的支柱(10)的上表面(15)。
4.如权利要求2所述的发动机组件，其特征在于，热交换器的外壳(16)连接到将涡轮喷气发动机固定在飞行器机翼上的支柱(10)的上表面(15)。
5.如权利要求1-4之一所述的发动机组件，其特征在于，外壳是沿涡轮喷气发动机的轴线延伸并相对于所述轴线倾斜设置的平行六面体，冷却空气流从第一前进入面(19)进入到外壳中，并从所述外壳的第一后输出面(24)流出，热空气流从外壳的第二前进入面(20)进入，并从外壳的第二后输出面流出。
6.如权利要求5所述的发动机组件，其特征在于，冷却空气流和热空气流在外壳中互相垂直地从前向后流动。
7.如权利要求1-4之一所述的发动机组件，其特征在于，外壳是相对于涡轮喷气发动机的轴线横向延伸的平行六面体，冷却空气流从下进入面(22)进入到外壳中，并从所述外壳的上输出面(23)流出，热空气流从外壳的前进入面(19)进入，并从所述外壳的后输出面(24)流出。
8.如权利要求7所述的发动机组件，其特征在于，冷却空气流在外壳中从下向上流动，热空气流在所述外壳中从前向后流动，冷却空气流和热空气流互相垂直地在外壳中流动。
9.一种飞行器，其特征在于，该飞行器包括至少一个如权利要求1-8之一所述的发动机组件。
CN2006800270610A 2005-07-28 2006-07-07 用于飞行器的发动机组件和包括至少一个这种发动机组件的飞行器 Expired - Fee Related CN101228069B (zh)

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FR0552352A FR2889250B1 (fr) 2005-07-28 2005-07-28 Ensemble propulseur pour aeronef et aeronef comportant au moins un tel ensemble propulseur
PCT/FR2006/001695 WO2007012722A1 (fr) 2005-07-28 2006-07-07 Ensemble propulseur pour aeronef et aeronef comportant au moins un tel ensemble propulseur

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