CN104246176A - 包括温差发电机的涡轮发动机 - Google Patents
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Abstract
本发明涉及涡轮风扇发动机,其包括至少一个流体回路和一个空气/流体交换器(40)和热水器,通过该空气/流体交换器(40),由涡轮风扇外部的空气冷却所述流体,该热水器(3)将风扇下游的空气流分成主流和次级流,其特征在于:热交换器(40)与温差发电机(46)相关联,该温差发电机(46)包括第一热交换表面(47)和第二热交换表面(48),其中第一表面与所述空气流热接触,并且第二表面与交换器(40)中待要被冷却的流体热接触。
Description
本发明涉及特别地在用于推进航空器的航空学领域中使用的涡轮发动机。更特别地,所述发明涉及温差发电机在所述涡轮发动机中的应用。
背景技术
用于推进航空器的涡轮发动机,诸如涡轮喷气发动机通常是多轴和多流路的涡轮发动机。例如,图1中所示的涡轮喷气发动机作为双流路发动机从上游到下游包括具有进气管道的舱室,该进气管道引导所吸入的空气朝向其下游的风扇转子2,以及在流的分流器3处,压缩的空气流被分成两个同心的环形流:主中心流Fp和主流径向地外部的次级流Fs。在旁路管道4中引导次级流,在发动机的轴线XX中的5处被整流,这样尽管还没有被加热,以被喷射出和以产生显著程度的发动机的推力。在图1的例子中,分别地喷射出主流和次级流。引导主流Fp通过中心体6,这产生了驱动风扇转子2所需的能量。中心体6是燃气涡轮机单元,包括向燃烧室8供应压缩空气的高和低压压气区域7,燃料注入燃烧室8中和在燃烧室8中产生发动机燃烧气体。由涡轮机区域9转换其中一些能量。涡轮机转子机械地连接压气机的转子,包括风扇和驱动它们旋转。
因为重量和燃料消耗是航空学领域中两个不利的因素,所以总是试图一方面减少构件的重量,并且另一方面利用没有被转换成机械能的耗散的能量。
温差电池是已知的,通过布置在具有一个是热的和另一是冷的温度梯度的两个热源之间,该温差电池能够将通过它们的热能转换为电能。
图2表示温差电池10的例子,其包括两个半导体元件11和12,分别地具有n类型和p类型掺杂。这两个元件在一端连接电连接13,并且每个在另一端终止于形成终端14和15的另一个电连接。电池被安装在两个电绝缘但是热传导的支撑16和17之间。在支撑16和17之间联合多个电池,经由终端14和15串联地电连接它们。因此,平行地热布置电池和形成温差发电机模块,此后称为“TEG”。
这种TEG模块,当安装在两个热源之间时,一个在与支撑16热接触的较高温度时是热的,另一个在与另一个支撑17接触的较低温度时是冷的,TEG模块能够在具有串联放置的终端的终端14和15之间产生电流。TEG模块的效率取决于几个因素,包括形成半导体的材料的性质,p-n结的数量,它们的横截面,它们的几何学,它们的厚度和对于特定模块,热源和冷源之间的温度差异。
已经提出利用燃气涡轮发动机中,并且更特别地涡轮喷气发动机中耗散的能量。
例如,公司Turbomeca已经开发出在推进航空器的燃气涡轮机中温差发电机的布置,这在专利申请WO 2010/089505中进行了描述。所述布置由同心的环形元件构成,每个同心的环形元件包括多个温差电池。环形元件在它们之间产生冷气体循环管道和热气体循环管道。管道也是同心和连通的。冷流体扫过元件中每个的面,并且热流体扫过这些元件的相对面。能够用作热源或冷源的流体分别地可以是发动机的燃料,它的冷却和润滑油,外侧空气,在压气机处吸入的空气或在涡轮机的下游所喷射出气流处所吸入的气体。
由该装置所产生的电能用于给发动机配件,诸如FADEC或电动机所驱动的泵供提供动力。
发明内容
本发明涉及TEGs在航空器发动机中的另一种应用。
因此,本发明涉及前风扇涡轮喷气发动机,其包括至少一个流体回路和空气/流体交换器和分流器,通过该空气/流体交换器,由涡轮喷气发动机外部的空气冷却所述流体,该分流器在主流和次级流之间分离风扇下游的流。
涡轮发动机的特征在于:热交换器包括至少一个温差发电机,该温差发电机包括第一和第二热交换表面,其第一表面与所述空气流热接触,并且第二表面与待要被冷却的流体热接触。
待要被冷却的流体,其主要是油,来自于发动机设备的部件和零件,后者耗散由内摩擦所产生的热和需要润滑和冷却。它们可以是,例如,用于各种旋转轴的轴承油封和用于驱动附件的齿轮机构。
通过这种方式待要被冷却的流体之间相当大的温度梯度和在风扇下游路径中循环的空气也帮助所有这些等于确保温差发电机的最佳效率。
因此,本发明所提供的方案可以帮助冷却这些流体,同时回收否则将已经流失的一些热能。所产生的电能取决于冷源的表面面积和有利地用于给部件提供动力,诸如本领域称为“VSV”压气机级与压气机的泄气或“VBV”,阀门之间的可变几何的压气机静子叶片的致动器。
根据一个实施方式,温差发电机的所述第一表面形成分流器的壁元件,该元件位于次级流路径的侧面上所述分流器的前缘的下游。如果必要,TEG的第一表面可以被结合到舱室的壁的结构中,这是热传导的。
由于该特征,本发明的布置可以减少由与空气流接触的交换器的元件所引起的空气动力学载荷损失。
特别地,将第一表面安装到固定的引导鳍的上游是有利的,该引导鳍布置为整流次级空气流。实际上,在分流器的前缘和引导鳍之间所限定的该区域中有足够的可用空间,称为OGV,其代表出口导向叶片。
根据另一个实施方式,分离空气流的边缘下游的分流器的所述壁元件包括与次级空气流交换热的径向鳍。
尽管该方案具有更少的空气动力学,但是当证明这是必要时,它允许热力发电机和次级空气流之间增加的热交换。
附图说明
在通过下面参考附图的纯示例性和非限制性实施例所给出的本发明实施方式的详细示例性描述的过程中将更好地理解本发明,并且它的其它目的、细节、特征和优点将变得更清楚。
在这些图中:
图1是在通过旁路涡轮喷气发动机的机械的轴线的平面中所取的截面,本发明可以在旁路涡轮喷气发动机上实施。
图2示意性地表示可以在本发明中使用的温差电池的实施例。
图3是图1中涡轮喷气发动机的分流器的部分横截面视图,根据本发明,温差装置应用于该涡轮喷气发动机。
图4是图3中装置的变化形式。
具体实施方式
参考图1,由风扇2所压缩的空气流通过流的分流器3时,它被分成两个同心的环形流,即,主流和次级流。由此,在中心体中由引导鳍(称为“IGV”,并且未示出)引导主空气流,并且在内部地中心体的壳体和外部地风扇舱室之间所界定的冷却流管道中引导次级流。
来自于风扇的环形空气流被中心体6舱室的环形上游边缘分成两个同心流,该边缘形成流的分流器3,如图3中更大比例所示。
在包括发动机的轴线XX的径向平面中,分流器具有基本上三角形横截面。它包括从形成前缘31的上游环形边缘线下游延伸的壁部分32。该壁部分径向地内部地界定次级流路径的上游部分。所述部分沿着OGV引导鳍5后的次级流路径延伸,设置该OGV引导鳍5以整流轴线XX中次级流。
从前缘31,流的分流器包括壁部分33,其径向外部地界定主流路径的上游部分。
该分流器由此在两个壁元件32和33之间产生空间,该空间具有足够体积以安装空气/油热交换器。
图3表示结合温差发电机的交换器布置的实施例。
交换器40包括封罩41,待要被冷却的流体流过它,并且它布置在沿着次级流路径的壁元件32的内面的两个相互平行的壁44和45之间。流体通过进口42穿过该封罩,该进口42经由管状管路与回路连通。封罩41内所形成的是回路,该回路确保与径向地外壁44最佳的热交换。封罩包括流体出口43,该出口43经由管状管路与流体回路连通。封罩内的管道形成,例如,盘管,该盘管的主方向是轴向或周向的。
径向外壁44与温差发电机模块46热接触,并且形成其热源。温差发电机模块包括多个温差电池,诸如参考图2所描述的温差电池,该温差电池安装在两个热传导的壁47和48之间。壁48与待要被冷却的流体通过的封罩40的径向外壁44热接触。
TEG模块的相对壁47结合到次级流路径的内壁32中,或者与形成中心体6的舱室的壁元件热接触。因此,所述壁是在次级流Fs的空气温度。
根据用于TEGs安装可用的表面面积选择模块。所考虑的参数是制造所述TEGs的材料,p-n结点的数量,它们的横截面,它们的几何学和它们的厚度。优选的模块是热阻尽可能低以不降低热交换器效率的模块。
因为当航空器飞行时,发动机工作,两个壁47和48之间的温度差异在半导体元件的终端之间产生了电势差异,供应了电流。在49处的电流可以分配给涡轮喷气发动机的电动力部件。
图4表示变化形式。和图3中相同的元件具有相同的附图标记加上100。
热交换器140包括封罩141的壁144和145之间的流体进口142和流体出口143,布置该封罩141热接触温差发电机146。TEG146的热壁148热接触交换器的壁144。TEG的冷却壁147热接触鳍150,该鳍150从分流器3的壁32径向地延伸。
如前所述,由TEG所产生的电流被收集在引线端149,用于分配给适合的部件。
Claims (4)
1.前风扇涡轮喷气发动机,其包括至少一个流体回路和空气/流体交换器(40、140)和分流器(3),通过该空气/流体交换器(40、140),由涡轮喷气发动机外部的空气冷却所述流体,该分流器(3)用于在主流和次级流之间分离风扇下游的流,其特征在于:热交换器(40、140)与温差发电机(46、146)相关联,该温差发电机(46、146)包括第一热交换表面(47、147)和第二热交换表面(48、148),其第一表面与所述空气流热接触,并且第二表面与交换器(40、140)中待要被冷却的流体热接触。
2.根据权利要求1的涡轮喷气发动机,其中所述第一表面(47、147)形成分流器的壁元件(32),该元件位于次级流路径(Fs)侧面上空气流的分流器的前缘(31)的下游。
3.根据权利要求2的涡轮喷气发动机,其中所述第一表面(47、147)是用于整流次级流(Fs)的固定引导鳍(5)的上游。
4.根据权利要求2或权利要求3的涡轮喷气发动机,其中分流器的所述壁元件(32)包括与空气流交换热的径向鳍(150),该元件是前缘(31)的下游。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1253754 | 2012-04-24 | ||
FR1253754A FR2989734B1 (fr) | 2012-04-24 | 2012-04-24 | Turboreacteur incorporant des generateurs thermoelectriques |
PCT/FR2013/050892 WO2013160602A1 (fr) | 2012-04-24 | 2013-04-22 | Turboreacteur incorporant des generateurs thermoelectriques |
Publications (2)
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US (1) | US9638105B2 (zh) |
EP (1) | EP2859208B1 (zh) |
CN (1) | CN104246176B (zh) |
BR (1) | BR112014026081B1 (zh) |
CA (1) | CA2870766C (zh) |
FR (1) | FR2989734B1 (zh) |
RU (1) | RU2631847C2 (zh) |
WO (1) | WO2013160602A1 (zh) |
Cited By (4)
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CN106121746A (zh) * | 2015-05-04 | 2016-11-16 | 航空技术空间股份有限公司 | 用于轴流涡轮机械压缩机的复合分流器唇边 |
CN108248369A (zh) * | 2018-01-23 | 2018-07-06 | 天津商业大学 | 一种带冷能回收装置的气动汽车动力系统 |
CN108843460A (zh) * | 2018-06-28 | 2018-11-20 | 厦门大学 | 涡轮冲压组合发动机预冷热电转换及增推方法 |
CN113906267A (zh) * | 2019-05-20 | 2022-01-07 | 赛峰集团 | 用于涡轮机的优化的热交换系统 |
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WO2015073101A2 (en) | 2013-09-16 | 2015-05-21 | United Technologies Corporation | Systems for generating auxillary electrical power for jet aircraft propulsion systems |
EP2942508B1 (en) * | 2014-05-08 | 2022-08-24 | Rolls-Royce North American Technologies, Inc. | Enhanced heat sink availability on gas turbine engines through the use of solid state heat pumps |
DE102016107303A1 (de) * | 2016-04-20 | 2017-10-26 | Rolls-Royce Deutschland Ltd & Co Kg | Energiewandlungssystem einer Turbomaschine, Getriebe oder Lagergehäuse einer Turbomaschine und Turbomaschine |
FR3091900B1 (fr) * | 2019-01-17 | 2022-05-27 | Safran Aircraft Engines | Turbomachine comprenant un panneau d’echange thermique et de production d’energie electrique |
FR3111394B1 (fr) * | 2020-06-12 | 2022-07-22 | Safran Aircraft Engines | Turbomachine comprenant un organe de séparation d’un flux d’air et un organe de redressement du flux d’air séparé. |
GB202108550D0 (en) * | 2021-06-16 | 2021-07-28 | Rolls Royce Plc | Gas turbine engine |
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- 2013-04-22 US US14/396,290 patent/US9638105B2/en active Active
- 2013-04-22 BR BR112014026081-8A patent/BR112014026081B1/pt active IP Right Grant
- 2013-04-22 CN CN201380021185.8A patent/CN104246176B/zh active Active
- 2013-04-22 RU RU2014144370A patent/RU2631847C2/ru active
- 2013-04-22 EP EP13723850.7A patent/EP2859208B1/fr active Active
- 2013-04-22 CA CA2870766A patent/CA2870766C/fr active Active
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CN106121746A (zh) * | 2015-05-04 | 2016-11-16 | 航空技术空间股份有限公司 | 用于轴流涡轮机械压缩机的复合分流器唇边 |
CN106121746B (zh) * | 2015-05-04 | 2019-03-26 | 赛峰航空助推器股份有限公司 | 用于轴流涡轮机械压缩机的复合分流器唇边 |
CN108248369A (zh) * | 2018-01-23 | 2018-07-06 | 天津商业大学 | 一种带冷能回收装置的气动汽车动力系统 |
CN108843460A (zh) * | 2018-06-28 | 2018-11-20 | 厦门大学 | 涡轮冲压组合发动机预冷热电转换及增推方法 |
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Also Published As
Publication number | Publication date |
---|---|
RU2631847C2 (ru) | 2017-09-26 |
CA2870766A1 (fr) | 2013-10-31 |
EP2859208A1 (fr) | 2015-04-15 |
WO2013160602A1 (fr) | 2013-10-31 |
US20150082804A1 (en) | 2015-03-26 |
RU2014144370A (ru) | 2016-06-10 |
FR2989734B1 (fr) | 2014-04-18 |
CA2870766C (fr) | 2020-07-21 |
BR112014026081B1 (pt) | 2021-12-14 |
US9638105B2 (en) | 2017-05-02 |
BR112014026081A2 (pt) | 2018-05-08 |
EP2859208B1 (fr) | 2019-02-27 |
CN104246176B (zh) | 2016-08-17 |
FR2989734A1 (fr) | 2013-10-25 |
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