CN102272477A - 飞行器涡轮发动机及该涡轮发动机的用途 - Google Patents

飞行器涡轮发动机及该涡轮发动机的用途 Download PDF

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CN102272477A
CN102272477A CN201080004111XA CN201080004111A CN102272477A CN 102272477 A CN102272477 A CN 102272477A CN 201080004111X A CN201080004111X A CN 201080004111XA CN 201080004111 A CN201080004111 A CN 201080004111A CN 102272477 A CN102272477 A CN 102272477A
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CN102272477B (zh
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J.H.马尔什
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Airbus Operations SAS
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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
    • F02K3/06—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
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • 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
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F02C3/113—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
    • 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
    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • 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
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other

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  • Combustion & Propulsion (AREA)
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Abstract

本发明涉及一种飞行器涡轮发动机及该涡轮发动机的用途。根据本发明，涡轮发动机(1a)包括能够使鼓风机(9a)的轴线(la-la)在横向于热气流发生器(4a)的轴线(La-La)的方向上发生偏移的装置。

Description

飞行器涡轮发动机及该涡轮发动机的用途
技术领域
本发明涉及一种飞行器涡轮发动机及该涡轮发动机的用途。
背景技术
众所周知，现代飞行器涡轮发动机尽管性能好但体积庞大，因此显著增加了将它们安装在飞行器上的难度。由于这种涡轮发动机整体结构的原因，使安装的难度变得更大。因此，这种安装操作常常伴随着所述飞行器的结构、尤其是发动机的承载结构的显著更改和调整。
然而，这种更改和调整可能并不是所期望的，例如出于技术问题和明显的成本原因。
发明内容
本发明的目的在于解决这种弊端，尤其在于使这种涡轮发动机在飞行器上的安装变得更加容易。
为了这个目的，根据本发明，所述飞行器涡轮发动机包括：
- 具有至少大致为水平的轴线的热气流发生器，用至少一个紧固件将该热气流发生器钩挂在所述飞行器的机翼上；
- 具有至少大致为水平的轴线的冷气流鼓风机，所述热气流发生器驱动该冷气流鼓风机发生旋转；以及
- 吊舱，其位于所述热气流发生器和所述冷气流鼓风机的周围，并且围绕所述热气流发生器形成环形截面的冷气流通道，
其特征在于，所述涡轮发动机包括能够在横向于所述热气流发生器的轴线的方向上使所述鼓风机的轴线发生偏移的偏移装置。
因此，由于本发明，可以调整涡轮发动机的结构和形状，从而使该发动机在飞行器上的安装变得更加容易。
在热气流发生器借助于减速机构驱动鼓风机发生旋转的情况下，所述偏移装置有利地至少部分地由所述减速机构构成，从而允许在横向于所述热气流发生器轴线的方向上使所述鼓风机的轴线发生偏移。
所述减速机构可以包括外摆线减速器和直线减速器（réducteur droit）。
当然，本发明进一步涉及如前所述的飞行器涡轮发动机的用途。
有利地，当借助于悬挂架把所述涡轮发动机挂在所述飞行器的机翼上时，可以在横向于所述热气流发生器的轴线的方向上使所述鼓风机的轴线向上偏移，从而增加所述涡轮发动机的离地距离。
因此，在特定的飞行器再机动化的情况下，本发明能够用新的现代涡轮发动机(通常体积更庞大)取代其现有的涡轮发动机，同时保持涡轮发动机原来的承载结构不变。实际上，涡轮发动机的鼓风机的向上偏移，允许在不改变发动机承载结构的情况下提升吊舱。于是，涡轮发动机的离地距离增加了等于鼓风机轴线偏移的值。
作为变型，当把所述涡轮发动机安装在所述飞行器的机翼上时，可以在横向于所述热气流发生器的轴线的方向上使所述鼓风机的轴线向上偏移，从而使所述涡轮发动机的空气入口向外偏移。由此，增大了能够经过所述涡轮发动机空气入口的空气量，因而改进了其性能。
在本发明的另一个变型中，将所述涡轮发动机挂在所述飞行器的机翼下面，由此可以在横向于所述热气流发生器的轴线的方向上使所述鼓风机的轴线向下偏移，从而使所述涡轮发动机的空气入口向外偏移，由此增加进入涡轮发动机的空气量。
此外，本发明还涉及一种包括至少一个如前所述的涡轮发动机的飞行器。
附图说明
附图中的图将更好地解释如何实施本发明。在这些图中，相同的附图标记表示相似的部件。
图1是借助于悬挂架挂在飞行器机翼下面的涡轮发动机的纵向断面示意性侧视图。
图2与图1相似，机翼涡轮发动机符合本发明的一个实施例。
图3示出了图1的机翼涡轮发动机(以点划线表示)以及根据本发明的图2的机翼涡轮发动机(以实线表示)的示意性侧视图。
图4是根据本发明另一个实施例的、安装在飞行器机翼上的涡轮发动机的纵向断面示意性侧视图。
图5示出了仍根据本发明的另一个实施例的、挂在飞行器机翼下面的涡轮发动机的纵向断面示意性侧视图。
具体实施方式
在参照图1至图3所描述的根据本发明的飞行器涡轮发动机的一个实施例中，在不改变原来(性能较低的)涡轮发动机承载结构的情况下，尤其是在不改变机翼、悬挂架以及该悬挂架上保持不变的紧固件的情况下，考虑用现代高性能发动机对飞行器进行再机动化。可能需要通过施行这种再机动化来降低飞行器的燃料消耗、增加其可用功率、减小其噪声释放等。
图1示出了借助于悬挂架3被钩挂在飞行器机翼2上的双流式涡轮发动机1。
如图1中所示，双流式涡轮发动机1通常包括：
- 具有至少大致为水平的轴线L-L的热气流发生器4。用前紧固件5和后紧固件6将热气流发生器4钩挂在悬挂架3上。分别在所述热气流发生器4的高压压缩机7和低压涡轮8处将前紧固件5和后紧固件6固定在热气流发生器4上；
- 具有至少大致为水平的轴线I-I的冷气流鼓风机9。鼓风机9的轴线I-I与热气流发生器4的轴线L-L重合。热气流发生器4借助于减速机构10(例如外摆线齿轮减速器)驱动所述鼓风机9发生旋转，减速机构10将热气流发生器4的驱动轴11机械连接到鼓风机9的驱动轴12，鼓风机9的转速低于热气流发生器4的转速；以及
- 吊舱13，其位于热气流发生器4和冷气流鼓风机9的周围并且形成冷气流通道14，该冷气流通道关于轴线I-I或L-L是轴对称的，并且具有围绕所述热气流发生器4的环形截面。吊舱13在其两端分别由空气入口15和冷气流出口16限定，冷气流出口16位于机翼2的前缘17的前面。
作为说明性的数值实例(而不是限制性的实例)，该双流式涡轮发动机1的离地距离(亦即，地面G与吊舱13最低点之间的间距，在图2中用GC标示)可以等于523mm。
根据本发明，如图2中所示(其中，与图1中的涡轮发动机相对应的各元件分别具有相同的附图标记，但带有后缀“a”)，已使鼓风机9a的轴线Ia-Ia在横向于热气流发生器4的轴线La-La的方向上向上偏移，并保持飞行器(图1)的悬挂架3以及紧固点5和6的特征不变。
为了这个目的，用改造的减速机构来代替图1中的通常的减速机构10，所述改造的减速机构包括例如相互关联的外摆线减速器10a和直线减速器18。此外，外摆线减速器10a和直线减速器18分别直接连接到鼓风机9a的驱动轴12a和热气流发生器4a的驱动轴11a。当然，也可以考虑其它减速机构。
如图2和图3中所示，鼓风机9a的向上偏移允许在不改变悬挂架3或者紧固件5和6的情况下将涡轮发动机1a的吊舱13a提高等于轴线Ia-Ia的偏移的值。由于鼓风机9a的偏移，导致了冷气流环形通道14a的改变，使冷气流环形通道14a不再是轴对称的。
因此，由于本发明，使涡轮发动机1a的离地距离增加了与鼓风机9a的轴线Ia-Ia的向上偏移值相对应的ΔGC。
根据上述数值例，该偏移可以等于15mm，使得涡轮发动机1a的离地距离GC+ΔGC变为等于673mm。
在图4中所示的根据本发明的另一个实施例中，涡轮发动机1a.I安装在飞行器机翼2.I上。用前紧固件5.I和后紧固件6.I将涡轮发动机的热气流发生器钩挂在机翼2.I上。鼓风机9a的轴线Ia-Ia在横向于热气流发生器4a的轴线La-La的方向上向上偏移了ΔGC，从而显著增加穿过空气入口15a的空气量。由此，改进了空气对涡轮发动机1a.I的填充。
此外，如图5中所示，本发明的又一个实施例使用位于飞行器机翼2.II下面的涡轮发动机1a.II。利用前紧固件5.II和后紧固件6.II(均安装在热气流发生器4a上)将这种涡轮发动机1a.II钩挂在机翼2.II的下面。使鼓风机9a的轴线Ia-Ia在横向于热气流发生器4a的轴线La-La的方向上向下偏移△GC，从而显著增加经过空气入口15a的空气量。由此，改进了空气对涡轮发动机1a.I的填充。 

Claims (7)

1.一种飞行器涡轮发动机，包括：
- 具有至少大致为水平的轴线的热气流发生器，其借助于至少一个紧固件钩挂到所述飞行器的机翼上；
- 具有至少大致为水平的轴线的冷气流鼓风机，其被所述热气流发生器驱动旋转；以及
- 吊舱，其位于所述热气流发生器和所述冷气流鼓风机的周围，并且围绕所述热气流发生器形成环形截面的冷气流通道；
其特征在于，所述涡轮发动机包括能够在横向于所述热气流发生器(4a)的轴线(La-La)的方向上使所述鼓风机(9a)的轴线(Ia-Ia)发生偏移的偏移装置(10a,18)。
2.如权利要求1所述的飞行器机翼涡轮发动机，其中，所述热气流发生器利用减速机构驱动所述鼓风机发生旋转；
其特征在于，所述偏移装置至少部分地由所述减速机构(10a,18)构成，从而允许所述鼓风机(9a)的轴线(Ia-Ia)在横向于所述热气流发生器(4a)的轴线(La-La)的方向上发生偏移。
3.如权利要求2所述的飞行器机翼涡轮发动机，其特征在于，所述减速机构(10a,18)包括外摆线减速器(10a)和直线减速器(18)。
4.如权利要求1至3中任一项所述的飞行器涡轮发动机的用途，其中，借助于悬挂架(3)将所述涡轮发动机挂在所述飞行器的机翼(2)上；
其特征在于，在横向于所述热气流发生器(4a)的轴线的方向上使所述鼓风机(9a)的轴线向上偏移，从而增加所述涡轮发动机(1a)的离地距离。
5.如权利要求1至3中任一项所述的飞行器涡轮发动机的用途，其特征在于，所述涡轮发动机(1a.I)安装在所述飞行器的机翼(2.I)上，在横向于所述热气流发生器(4a)的轴线(La-La)的方向上使所述鼓风机(9a)的轴线(Ia-Ia)向上偏移，从而使所述涡轮发动机(1a.I)的空气入口(15a)向外偏移。
6.如权利要求1至3中任一项所述的飞行器涡轮发动机的用途，其特征在于，所述涡轮发动机(1a.II)挂在所述飞行器的机翼(2.II)的下面，在横向于所述热气流发生器(4a)的轴线(La-La)的方向上使所述鼓风机(9a)的轴线(Ia-Ia)向下偏移，从而使所述涡轮发动机(1a.I)的空气入口(15a)向外偏移。
7.一种飞行器，其特征在于，包括至少一个如权利要求1至3中任一项所述的涡轮发动机(1a)。
CN201080004111.XA 2009-01-07 2010-01-05 飞行器涡轮发动机及该涡轮发动机的用途 Expired - Fee Related CN102272477B (zh)

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FR2940818A1 (fr) 2010-07-09
US20110314788A1 (en) 2011-12-29
US8844263B2 (en) 2014-09-30
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