CN101149019A - 直升机燃气涡轮发动机消音装置和装有这种装置的发动机 - Google Patents
直升机燃气涡轮发动机消音装置和装有这种装置的发动机 Download PDFInfo
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Abstract
在直升机燃气涡轮发动机中,形成径向进气道(34)的进气道前缘(30,32)沿发动机压气机供气通道(12)的开口(12a)连接。进气道前缘至少部分由消音器(40,42)构成,设计用来衰减因压气机转动而产生的声频。
Description
技术领域
本发明涉及降低安装燃气涡轮发动机的直升机的噪声级。
背景技术
人们一直在努力降低直升机主旋翼桨叶所产生的噪声,结果发现,驱动桨叶的发动机所产生的噪声在燃气涡轮发动机直升机的噪声中占相当大的比例。
美国4 421 455号专利文件披露了一种燃气涡轮发动机,特别是一种APU(辅助动力装置),其中,起抑制噪声作用的涂层在金属机体壁板的一些部位形成,这些壁板构成了发动机压气机的供气通道。涂层的厚度意味着决定发动机尺寸的实际所需要的容积。此外,发动机-特别是金属机体-就必须在最初设计时考虑到能安装消音器。
发明专利内容
本发明的一个目的是提供一种直升机用消音装置,所述设备将会解决上述问题。
这个目的可以通过使用一种直升机燃气涡轮发动机的消音装置来实现,包括一个压气机和一个压气机供气通道,该通道在上游端开口,它是通过一个由发动机金属机体形成边界的外部开口来形成的,消音装置包括进气道前缘,这些进气道前缘形成了压气机供气通道的进气道,它们带有内端部,沿通道外开口接到金属机体上,并至少部分通过消音器形成,后者设计用来衰减压气机转动产生的声频。
本发明所提出的消音处理具有几个优点。其位置离压气机不远,即发动机的主要噪声源,从而提供了良好的降噪效果。另外,因为进气道前缘位于发动机外侧金属壳体上,所以消音器的使用不会产生重量问题,也不必对发动机设计进行改动;消音处理,或者称减音装置处理,可以很方便地在现有发动机上应用。此外,带有消音器的进气道前缘可以采用轻材料制成,诸如纤维树脂脂类复合材料,这样,消音器的加装就不会产生重量上的大的变化。而且,采用这种布置,还可以用防冰护盖来覆盖径向进气道。
另外,还需要注意的是,因为对桨叶转动造成的噪声具有明显的衰减效果,桨叶在设计上就可以考虑优化空气动力特性,而不需要考虑解决涉及噪声的问题。
根据一个具体实施例,消音装置也可以包括一个消音器,构成了自供气通道外开口的供气通道部分长度上的压气机供气通道壁。
例如,消音处理可以是一种亥姆霍兹共鸣式或任何其它已知形式的壁板覆盖物。
附图说明
下面参照附图并结合阅读发明说明,可以更好地理解本发明,但本发明的特性决不仅限于所述示例。附图如下:
图1为直升机燃气轮机示意图;图2为一张放大的半剖面局部示意图,介绍了消音器在图1所示发动机压气机径向进气道前缘的安装情况;
图3为一张放大的半剖面局部示意图,介绍了消音器在图1所示压气机径向进气道前缘和供气通道壳体上的安装情况。
具体实施方式
图1为直升机燃气涡轮发动机的示意图,所述燃气涡轮发动机包括一个压气机级10(例如,一个离心式压气机),通过一个环形供气通道12接收外部空气。在其上游端,供气通道12通过一个环形外部开口12a打开,而发动机的金属机体14确定了该开口的界线。金属机体14还构成了供气通道12的壁。环形燃烧室16以及例如一个逆流系统安装有喷射器(图中未示),后者提供有燃油和来自压气机10的主空气流。来自燃烧室的燃烧气体带动涡轮18进而带动压气机10-通过轴20与压气机连接,和一个通过轴23连接到齿轮系的动力涡轮22(例如,只有一个级的动力涡轮),齿轮系向输出轴24以及同轴连接的轴20和轴23提供机械动力。
如图2所示,两个进气道前缘30和32(图1中未示)构成了供气通道12的进气道34。这些进气道前缘分别由环形部件构成,环形部件的内端在开口12a的上面及两侧与供气通道12的上游端连接,而在另一个端,即外端,环形部件带有凸缘30a,32a向外弯曲成U形状。进气道前缘30,32的内端都有一个环形体或地脚30b,32b,进气道前缘通过这个环形体或地脚固定到机体14上。
进气道34的端部34a由进气道前缘30a,32a形成,上面覆盖有一个带有折缘的防冰护盖36,其端部与进气道前缘30a,32a的凹槽相啮合,并固定到进气道前缘上。护盖36用来防止进气道34和供气通道12处结霜,护盖36的外表面可能会出现任何结冰情况。为此,提供有一个环状旁通管道38,目的是向供气通道12提供足够的空气,尽管护盖36可能会结冰。通道38的一侧为弯曲环形导向壁39或中空构件来形成,提供有加强筋39a,并固定到机体14上。壁39的位置面向进气道前缘,例如进气道前缘32,从而形成了通道38的另一边,并带有开口或端口32c,供通道38来的空气流通。如上所述的进气结构是为人们所熟知的。
进气道前缘30,32的壁至少在进气道前缘径向尺寸的部分构成了消音器40.42,而径向尺寸部分形成了进气道34,与供气通道12连接,优选用于进气道34的整个径向尺寸上,目的是衰减发动机最近声源所产生的噪声,例如压气机。如果需要,每个消音器都可以采用几个邻近的部分构成,从而为生产制造提供了更大的方便。
正如图2所详细说明的那样,每个消音器,例如参考号40,可以是由若干个相邻的腔室或空间40a组成,采用隔板40b相隔开,例如形成了一个蜂窝夹心状结构,隔板40b的布置垂直于背部40c和前端面40d之间的进气道前缘表面,背部40c是由刚性板或薄板构成,经过密封的(声波不能穿过),而前端面40d也是由板材或薄板构成,但声波可以穿过。例如,前部的板材或薄板40d可以是穿孔的。另外,也可以使用孔板或薄板,能够使被衰减的声波渗透。
腔体40a的深度(背部和前端面之间的距离)取决于拟要衰减的声波的波长。声波主要是由压气机10产生的,对于目前的直升机燃气涡轮发动机来讲,声部的频率是大约5到14kHz的倍数,涉及到的腔室深度(波长的四分之一)大约0.6厘米到1.6厘米。安装消音器并不会引起进气道前缘处的重量增加。连接进气道34的进气道前缘30,32的壁可以很方便地采用消音器来形成。
由于进气道34位于发动机的“冷”区域,并不是发动机结构部分,装有或构成消音器40,42的进气道前缘30,32的材料可以从大量材料中选取。特别是,进气道前缘30,32和消音器40,42的材料可以选用复合材料,采用纤维增强,例如,玻璃纤维或碳纤维以及树脂基复合材料。由于这种材料很轻,使用消音器并不会影响重量。
构成腔室构件39的壁板可以使用与进气道前缘30,32相同的材料,另外,也可以装有或构成一个类似于消音器30,32的消音器。
这样,压气机所产生的噪声的有效衰减就可以很容易实现,不会造成重量问题,也不需要对发动机进行改装,包括供气通道,因此,本发明很容易应用于现有发动机。
然而,正如图3所示,也可以在供气通道12的壁板上使用消音器26,28,可在与进气通道34相连接的整个长度的某个部分上使用。消音器26,28可以采用同消音器40,42相同的结构,也可以使用同机体14相同的金属材料或不同的材料,例如在金属机体上加装一个陶瓷消音器。
如上所述,已经考虑使用亥姆霍兹衰减器形式的消音器。不过,其它类型的消音器结构件也可使用,例如泡沫塑料或陶瓷或金属孔状材料。
如上详细描述的那样,进气道前缘30,32沿供气通道12的环形外部开口12a在发动机的整个外围上延伸。另外,本发明还适合供气通道的外部开口是在发动机外围的仅仅一个部分延伸,带有消音器的进气道前缘沿外部开口布置,并在其进气道前缘端部处连接到一起。
Claims (5)
1.一种直升机燃气涡轮发动机的消音装置,包括一个压气机(10)和一个压气机供气通道(12),所述通道的开口设在上游端,通过一个由发动机金属机体(14)形成界线的外开口(12a)来实现,消音装置包括进气道前缘(30,32),形成了压气机供气通道的进气道(34),进气道前缘设有内端部(30b,32b),用来沿通道外开口(12a)连接到金属机体,这些进气道前缘至少部分是通过消音器来构成(40,42),设计用来衰减压气机转动时产生的声频。
2.根据权利要求1所述的消音装置,其特征在于:进气道前缘(30,32)是采用带有树脂致密的纤维增强的复合材料制成。
3.根据权利要求1和2任一权利要求所述的消音装置,其特征在于:径向进气道(34)提供有一个安装在进气道前缘(30,32)外端上的防冰护盖(36)。
4.根据权利要求1到3任一权利要求所述的消音装置,所述装置还包括一个消音器(26,28),构成压气机供气通道(12)的一个壁,该壁位于从供气道(12)外开口(12a)开始的所述通道部分长度上。
5.安装有根据上述权利1到4任一权利要求所述消音装置的直升机燃气涡轮发动机。
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Application Number | Priority Date | Filing Date | Title |
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FR0653835 | 2006-09-20 | ||
FR0653835A FR2905983B1 (fr) | 2006-09-20 | 2006-09-20 | Dispositif d'insonorisation d'un moteur d'helicoptere a turbine a gaz, et moteur ainsi obtenu |
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CN101149019A true CN101149019A (zh) | 2008-03-26 |
CN101149019B CN101149019B (zh) | 2012-09-05 |
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US (1) | US7938618B2 (zh) |
EP (1) | EP1902953B1 (zh) |
JP (1) | JP4942594B2 (zh) |
CN (1) | CN101149019B (zh) |
BR (1) | BRPI0703627A (zh) |
CA (1) | CA2602179C (zh) |
ES (1) | ES2684537T3 (zh) |
FR (1) | FR2905983B1 (zh) |
PL (1) | PL1902953T3 (zh) |
RU (1) | RU2457344C2 (zh) |
ZA (1) | ZA200707841B (zh) |
Cited By (3)
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CN103786890A (zh) * | 2012-10-26 | 2014-05-14 | 奥格斯塔韦斯兰股份公司 | 能悬停的飞行器 |
CN104507810A (zh) * | 2012-07-30 | 2015-04-08 | 涡轮梅坎公司 | 具有改进的旁通流的直升机发动机进气口 |
CN114030636A (zh) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | 一种前出轴发动机直升机进气道构型设计方法 |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2379409B1 (en) * | 2008-12-30 | 2017-12-20 | Sikorsky Aircraft Corporation | Engine air particle separator |
FR2941495B1 (fr) * | 2009-01-27 | 2017-09-29 | Turbomeca | Conduit d'echappement insonorise pour turbomoteur |
CN101761512B (zh) * | 2010-02-09 | 2011-06-15 | 清华大学 | 开槽位置为圆弧分布的离心压气机非对称自循环处理机匣 |
CN101749279A (zh) * | 2010-02-09 | 2010-06-23 | 清华大学 | 基于变开槽位置的离心压气机非对称自循环处理机匣 |
CN102892995B (zh) * | 2010-06-04 | 2015-11-25 | 博格华纳公司 | 排气涡轮增压器的压缩机 |
FR2961260B1 (fr) * | 2010-06-15 | 2014-05-02 | Turbomeca | Architecture de turbomoteur non lubrifie |
US9752494B2 (en) | 2013-03-15 | 2017-09-05 | Kohler Co. | Noise suppression systems |
US9388731B2 (en) * | 2013-03-15 | 2016-07-12 | Kohler Co. | Noise suppression system |
FR3008679B1 (fr) * | 2013-07-16 | 2015-08-14 | Eurocopter France | Installation motrice modulaire et aeronef muni d'un rotor de sustentation |
US9957889B2 (en) * | 2014-08-19 | 2018-05-01 | Pratt & Whitney Canada Corp. | Low noise aeroengine inlet system |
US10013900B2 (en) * | 2014-09-23 | 2018-07-03 | Amazon Technologies, Inc. | Vehicle noise control and communication |
FR3029568B1 (fr) * | 2014-12-05 | 2016-11-18 | Turbomeca | Plenum d'alimentation en air |
US10648458B2 (en) | 2016-06-27 | 2020-05-12 | Martin E Nix | Downdraft and updraft tornado wind chimney |
US10388327B2 (en) * | 2017-02-28 | 2019-08-20 | Western Digital Technologies, Inc. | Fan noise attenuation at hard disk drive in rack-mount |
RU2682804C1 (ru) * | 2018-02-07 | 2019-03-21 | Марк Евгеньевич Дискин | Выходное устройство авиационного реактивного двигателя |
KR20220159158A (ko) * | 2021-05-25 | 2022-12-02 | 현대자동차주식회사 | 차량 흡기계의 기류음 저감장치 |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2943683A (en) * | 1957-05-31 | 1960-07-05 | Nick R Dirksen | Top seal for bottom lock pumps |
US3077731A (en) * | 1958-11-24 | 1963-02-19 | Gen Motors Corp | Compressor mechanism for internal combustion engines and the like |
US3118278A (en) * | 1959-06-26 | 1964-01-21 | Gas turbine power plant | |
US3371471A (en) * | 1965-10-15 | 1968-03-05 | Avco Corp | Sand and dust collector for engine air inlets |
US3449891A (en) * | 1966-11-15 | 1969-06-17 | United Aircraft Corp | Engine inlet air particle separator |
CA1015290A (en) * | 1972-12-18 | 1977-08-09 | Pall Corporation | Vortex air cleaner assembly with acoustic attenuator |
FR2250671B1 (zh) * | 1973-11-09 | 1980-01-04 | Aerospatiale | |
CH586351A5 (zh) * | 1975-06-18 | 1977-03-31 | Bbc Brown Boveri & Cie | |
US4204586A (en) * | 1975-12-11 | 1980-05-27 | Bbc Brown Boveri & Company Limited | Silencer on the intake side of a compressor with assembly of axially spaced annular sound-damping elements |
GB2044359B (en) * | 1979-03-16 | 1982-10-27 | Rolls Royce | Gas turbine engine air intakes |
US4421455A (en) * | 1981-12-22 | 1983-12-20 | The Garrett Corporation | Duct lining |
US5140819A (en) * | 1989-09-28 | 1992-08-25 | Sundstrand Corporation | Turbine inlet silencer |
JPH03260336A (ja) * | 1990-03-12 | 1991-11-20 | Mitsubishi Heavy Ind Ltd | 遠心圧縮機の抽気装置 |
DE4340951A1 (de) * | 1992-12-04 | 1994-06-09 | Grumman Aerospace Corp | Einstückiges Triebwerkeinlaß-Schallrohr |
JP2876000B1 (ja) * | 1998-01-13 | 1999-03-31 | 三菱アルミニウム株式会社 | 過給機のサイレンサ |
DE10000418A1 (de) | 2000-01-07 | 2001-08-09 | Abb Turbo Systems Ag Baden | Verdichter eines Abgasturboladers |
JP2004150367A (ja) * | 2002-10-31 | 2004-05-27 | Ishikawajima Harima Heavy Ind Co Ltd | 過給機の吸気冷却・消音装置 |
-
2006
- 2006-09-20 FR FR0653835A patent/FR2905983B1/fr active Active
-
2007
- 2007-09-07 PL PL07115944T patent/PL1902953T3/pl unknown
- 2007-09-07 EP EP07115944.6A patent/EP1902953B1/fr active Active
- 2007-09-07 ES ES07115944.6T patent/ES2684537T3/es active Active
- 2007-09-13 ZA ZA200707841A patent/ZA200707841B/xx unknown
- 2007-09-13 US US11/854,915 patent/US7938618B2/en active Active
- 2007-09-14 JP JP2007238861A patent/JP4942594B2/ja not_active Expired - Fee Related
- 2007-09-18 CA CA2602179A patent/CA2602179C/fr active Active
- 2007-09-19 CN CN2007101541550A patent/CN101149019B/zh active Active
- 2007-09-19 BR BRPI0703627-2A patent/BRPI0703627A/pt not_active Application Discontinuation
- 2007-09-19 RU RU2007134893/06A patent/RU2457344C2/ru not_active IP Right Cessation
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104507810A (zh) * | 2012-07-30 | 2015-04-08 | 涡轮梅坎公司 | 具有改进的旁通流的直升机发动机进气口 |
CN103786890A (zh) * | 2012-10-26 | 2014-05-14 | 奥格斯塔韦斯兰股份公司 | 能悬停的飞行器 |
CN114030636A (zh) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | 一种前出轴发动机直升机进气道构型设计方法 |
CN114030636B (zh) * | 2021-11-19 | 2023-04-28 | 中国直升机设计研究所 | 一种前出轴发动机直升机进气道构型设计方法 |
Also Published As
Publication number | Publication date |
---|---|
EP1902953B1 (fr) | 2018-06-27 |
CA2602179C (fr) | 2014-11-25 |
JP4942594B2 (ja) | 2012-05-30 |
JP2008075648A (ja) | 2008-04-03 |
CN101149019B (zh) | 2012-09-05 |
ES2684537T3 (es) | 2018-10-03 |
EP1902953A1 (fr) | 2008-03-26 |
CA2602179A1 (fr) | 2008-03-20 |
FR2905983A1 (fr) | 2008-03-21 |
US7938618B2 (en) | 2011-05-10 |
RU2007134893A (ru) | 2009-03-27 |
FR2905983B1 (fr) | 2013-03-15 |
BRPI0703627A (pt) | 2008-05-13 |
RU2457344C2 (ru) | 2012-07-27 |
US20080185217A1 (en) | 2008-08-07 |
PL1902953T3 (pl) | 2018-12-31 |
ZA200707841B (en) | 2008-06-25 |
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