CN1007171B - 飞机用气流排放装置 - Google Patents
飞机用气流排放装置Info
- Publication number
- CN1007171B CN1007171B CN86102097A CN86102097A CN1007171B CN 1007171 B CN1007171 B CN 1007171B CN 86102097 A CN86102097 A CN 86102097A CN 86102097 A CN86102097 A CN 86102097A CN 1007171 B CN1007171 B CN 1007171B
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- air
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 238000005070 sampling Methods 0.000 claims description 28
- 239000012634 fragment Substances 0.000 claims description 5
- 239000000523 sample Substances 0.000 abstract 2
- 230000000694 effects Effects 0.000 description 2
- 241000238631 Hexapoda Species 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Images
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
- G01K13/028—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow for use in total air temperature [TAT] probes
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- 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
- Y02T50/10—Drag reduction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measuring Fluid Pressure (AREA)
- Structure Of Belt Conveyors (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Measuring Volume Flow (AREA)
Abstract
在本发明的一种形式中,边界层空气被移开飞机的探测器,导致自由气流碰撞到探测器上。
Description
本发明涉及到对一种飞机用气流采样装置,该气流是在贴近飞机的边界层流动。采样的目的是为了测量诸如温度和压力等气流的特性。
图1示出了一个发动机舱3,该发动机舱用来容纳一个燃气涡轮发动机(没示出)而悬挂在飞机的机翼6上。测量进入气流9的诸如气流温度,压力和速度等特性是很重要的。为此,人们已经发明了各种类型的探测器,它们一般从发动机舱3的内筒体12伸出,正如图示的探测器15。
图2是探测器15的一个放大图。通常,为将敏感元件18固定在边界层24的外面,探测器15的敏感元件18由支架21支撑,以便减小边界层24对测量值造成的影响。通常,边界层24具有的特性与图1中进入的气流9(有时称作自由气流)大大地不同,因此,要避免测量边界层。例如,不同的特征产生于这样的事实-某些发动机舱包含将内筒体12加热到几百度下的设备,以防止结冰。这种人为加热改变了边界层24的温度,这就使其温度与通常进入气流9的温度相比有显著的不同。
除了对边界层的上述考虑,探测器15还面临着其它一些问题。一,探测器往往要与进入的物体诸如鸟类,昆虫,冰类和其它类型的碎片碰撞。二,雨水将必然射落到敏感元件18上,雨水会改变温度探测器的测量值。
即使撇开上述的考虑,进入的气流9也并不总是与如图1所示的发动机舱3的中心线27平行。例如,在起飞期间,进入的气流更接近象
箭头30所指的那样。在图2中,探测器15所包含的一个压力传感器将根据进入空气冲击的方向给出不同的读数。即,在图2中由箭头33A-B所表示(其它方面均相同)的气流,仅仅由于从不同的方向冲击到探测器15上,而给出不同的压力读数,总之,人们希望加到压力传感器上气流的攻角要保持恒定。
本发明的目的是提供一种改进的飞机用气流采样装置,该装置通过对气流探测器安装位置的改进以及增加一条空气通道来减少边界层空气作用于气流探测器的效应,并避免进入的碎片及雨水对探测器的影响。
本发明提供一种有安装在飞机发动机舱内的气流探测器的飞机用气流采样装置,其特征在于该装置还包括一条安装在飞机发动机舱内的空气通道,该空气通道由扩散形接收通道,及安装在接收通道下游的采样通道构成,气流探测器安置在采样通道中。
图1图示了一个飞机发动机舱中的探测器15。
图2是图1中探测器15的放大图。
图3图示了本发明的一种形式。
图3A图示了图3中的涡流76A和B。
图4示出了图3中区域38的锥形部分。
图5是图3的一个侧视图。
图6示出了本发明的另一种形式。
图3表示了本发明的一种形式。图3的装置隐藏于图1发动机舱的内筒体12内部,而且最好装在上半部的线35上,以便减少由于吸入跑道上的碎片造成的碰撞损坏。
图3的发明包括一个扩散形接收通道38,当然,图3中的接收通道除了当然没有图4中的面38B外,实际上就是图4中38A所示的锥状通道,即接收通道38是3面的。
把接收通道38称为“扩散形”,是因为其顺流方向(由箭头40
指出)的横截面是增加的,即,图4中矩形44的面积大于矩形46。另外,接收通道38穿过发动机舱3的表面12,以使图5中的角度65B大约为10度。
在图3和5中接收通道38的下游安置有采样通道52,该采样通道正如下游方向40所得的某个横截面一样,大体上是保持恒定的,采样探测器55被置于采样通道52中,该探测器通常包含一个压力传感器和一个温度传感器(没具体指出)。采样通道52的下游置有排出通道58,该排出通道在顺流方向上其横截面是减小的,正如矩形60A与矩形60B相比所示。图5是安装于发动机舱内筒体12内的图3装置的侧视图。角度65A-C分别具有下列值:10、10和20度。
本发明被认为是按如下方式工作的,图3中,进入的移动气流70遇到在图3和5中锥形接收通道38边缘72上的理论上的固定边界层空气,由于进入的气流70具有有限的、非零的粘滞度,如弯曲箭头74所示进入气流70又转入接收通道38。当气流74顺流前进时,它们发展成涡流面76A和B(同样示于图3A中),该涡流是借助于接收通道38的锥形特性形成的。该锥形降低了空气的速度:点82的速度要小于点80的速度。
涡流面76A和B的一个重要方面,在于它们的旋转方向。涡流空气按图3A中箭头78A和78所示向通道底板84的中心线83(如图3所示)处流动并如图3A箭头78C和78D所示在通道壁87附近离开该底板84。另一方面的特征,涡流面76A和B在锥形接收通道38的中心线83上叉开而相互反向旋转。而且,这些方向是使气流向着接近中心线的通道底板84流动。
图3A中的这些涡流76A和B在采样通道52中引起了一个如图3A所示的低压区90。低压区90使图3和5中的采样气流流入该低压区,如图5中区域74B中的箭头所示的曲线,采样气流74A大约
开始于图3中边界层24上面的点94。从另一方面看,采样气流74A由相邻的涡流76A和B所牵引,由于箭头76A和B的方向是向着接近中心的通道底板84,气流74A也被它们带向通道底板。
因此,传感器55接收图2中从边界层24外侧引出的气流74A(即从图3中的点94引出),这通常更能代表进入的气流。此外,申请人已发现,向着探测器55的气流74A的加速度(即,在图5中,箭头89的方向,该方向是朝着通道底板84)是如此之大以致微粒90A(诸如雨水,冰块,或碎片等)均被抛出采样气流74A。这些微粒继续沿着由箭头101所示路径前进而不是跟随采样气流74A,因而采样气流101被离心和滤去。
为收集一股气流由探测器敏感元件加以测量的发明已经作了叙述。本发明最好安装于飞机发动机舱的内表面(或筒体)。本发明从实际上在图3中的边界层24影响之外的区域收集一股气流。被采样的是自由空气流而不是边界层。无论探测器被置于图3中的边界层以下还是在边界层本身之中均能产生这种作用。即,本发明实际上分裂3边界层(如图3中分裂成弯曲箭头74的箭头70所示),并从点94引出采样气流74A,通过边界层的裂口,并加到探测器55上而被采样。
本发明的一个重要方面在于省去了图2中把传感器支撑在边界层外面所需的支架21。正如上面已指出,图3中的传感器55实际上置于边界层之中或之下。
本发明的另一重要方面在于:它引导图3中采样气流74A沿着通常与中心线83平行的通道前进。这种引导使得不管图1中进入气流9的方向如何,采样气流74A从大致相同的方向撞击到探测器55上,这一概念避免了所论述的关于由图1中箭头9和30及图2中的33A和33B所代表的气流的误差。因此,本发明补偿了当飞机改变姿态时而使压力传感器出现的读数误差。
本发明装置可无需如图5所示那样穿过发动机舱的内表面12,而可以固定在该表面的顶部。因此,作为一个如此表面连接的实施例示于图6,该图本身已能说明一切。第二个实施例,除了在图6中没有图3中的排出通道58外,采用了与图3同样的工作方式。
申请人指出:有些探测器15本身就具有防水能力,本发明也能使用这类探测器,通过对气流74A预先过滤减少其水份器,使这种能力进一步增强。
在不脱离本发明由如下的权利要求所限定的实质精神和范围的情况下,可能进行许多改型和替代。
Claims (3)
1、一种飞机用气流采样装置,包括一个安装在飞机发动机舱内的气流探测器,其特征在于该装置还包括一条空气通道,该通道安装在飞机发动机舱内,且由扩散形接收通道及安装在接收通道下游的采样通道构成,气流探测器安置在采样通道中。
2、根据权利要求1所述的飞机用气流采样装置,其特征在于扩散形接收通道有一增加的横截面,而采样通道有一基本上不变的横截面,其中在从入口的第一空气流的扩散形接收通道中产生了相反移动的涡流,进入的第一空气流包括引起在靠近气流探测器区域和自由空气流之间产生一压差的附面层空气,该压差使自由空气流向着采样装置方向加速,而且使自由空气流中所携带的碎片从自由空气流中分离出。
3、根据权利要求2所述的飞机用气流采样装置,其特征在于采样通道的下流置有排出通道,该排出通道在顺流方向上其横截面是减小的。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/725,963 US4644806A (en) | 1985-04-22 | 1985-04-22 | Airstream eductor |
US725.963 | 1985-04-22 | ||
US725,963 | 1991-07-05 |
Publications (2)
Publication Number | Publication Date |
---|---|
CN86102097A CN86102097A (zh) | 1986-10-22 |
CN1007171B true CN1007171B (zh) | 1990-03-14 |
Family
ID=24916648
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN86102097A Expired CN1007171B (zh) | 1985-04-22 | 1986-03-26 | 飞机用气流排放装置 |
Country Status (7)
Country | Link |
---|---|
US (1) | US4644806A (zh) |
JP (1) | JPS61244698A (zh) |
CN (1) | CN1007171B (zh) |
DE (1) | DE3608035A1 (zh) |
FR (1) | FR2580809B1 (zh) |
GB (1) | GB2173861B (zh) |
IT (1) | IT1188567B (zh) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN1072704C (zh) * | 1998-10-13 | 2001-10-10 | 中国石油化工集团公司 | 一种馏分油的加氢精制方法 |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5517865A (en) * | 1991-06-13 | 1996-05-21 | General Electric Company | Vortex suppression for an eductor |
FR2808874B1 (fr) * | 2000-05-15 | 2002-07-26 | Auxitrol Sa | Capteur pour la mesure de parametres physiques sur un flux de fluide et notamment capteur de temperature d'air degivre |
US7192462B2 (en) * | 2004-04-14 | 2007-03-20 | Aerospace Filtration Systems, Inc. | Engine air filter and sealing system |
US7156552B2 (en) * | 2004-09-07 | 2007-01-02 | University Corporation For Atmospheric Research | Temperature sensor system for mobile platforms |
US8935073B2 (en) * | 2006-10-12 | 2015-01-13 | United Technologies Corporation | Reduced take-off field length using variable nozzle |
FR2920141B1 (fr) * | 2007-08-20 | 2009-10-30 | Aircelle Sa | Nacelle de turboreacteur, destinee a equiper un aeronef |
EP2031243A1 (en) * | 2007-08-31 | 2009-03-04 | Lm Glasfiber A/S | Means to maintain a flow attached to the exterior of a flow control member |
EP2031244A1 (en) | 2007-08-31 | 2009-03-04 | Lm Glasfiber A/S | Means to maintain flow of a flowing medium attached to the exterior of a flow control member by use of crossing sub-channels |
US9157368B2 (en) * | 2007-09-05 | 2015-10-13 | United Technologies Corporation | Active flow control for nacelle inlet |
US8100582B1 (en) * | 2007-12-13 | 2012-01-24 | Powell Bradley J | Temperature probe |
US9010198B2 (en) * | 2011-07-29 | 2015-04-21 | United Technologies Corporation | Aircraft debris monitoring sensor assembly |
US9340281B2 (en) | 2014-07-31 | 2016-05-17 | The Boeing Company | Submerged vortex generator |
US20160376010A1 (en) * | 2015-06-26 | 2016-12-29 | Rosemount Aerospace Inc. | Systems and methods for preventing ice accumulation |
CN105865852A (zh) * | 2016-03-30 | 2016-08-17 | 中国科学院城市环境研究所 | 一种矢量化流通式采样器 |
GB2584464B (en) * | 2019-06-05 | 2023-03-22 | Bae Systems Plc | Aircraft |
US11774466B2 (en) | 2019-06-05 | 2023-10-03 | Bae Systems Plc | Aircraft with skin layer air data sensor |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB568170A (zh) * | 1900-01-01 | |||
GB397992A (en) * | 1931-06-25 | 1933-09-07 | Jean Alexandre Rey | Devices for propelling by reaction |
GB715817A (en) * | 1951-07-06 | 1954-09-22 | Sebac Nouvelle Sa | Improvements in or relating to spraying or spreading apparatus |
US3079105A (en) * | 1957-10-21 | 1963-02-26 | Raspet Mabel Wilson | Reserve lift indicator for aircraft and the like |
US3083568A (en) * | 1958-05-14 | 1963-04-02 | Svenska Ackumulator Ab | Device used in connection with ship log based on measurement of the dynamic pressure |
US3252323A (en) * | 1961-12-29 | 1966-05-24 | Litton Systems Inc | Particulate sampling device |
US3451268A (en) * | 1967-05-18 | 1969-06-24 | Gen Motors Corp | Cooled thermocouple |
US3512414A (en) * | 1968-05-23 | 1970-05-19 | Rosemount Eng Co Ltd | Slotted airfoil sensor housing |
DE1785158C3 (de) * | 1968-08-17 | 1979-05-17 | Metallgesellschaft Ag, 6000 Frankfurt | Runddiise zum Abziehen und Ablegen von Fäden zu einem Fadenvlies |
GB1298069A (en) * | 1969-05-03 | 1972-11-29 | Secr Defence | Air intake for a gas turbine engine |
US3557537A (en) * | 1969-11-06 | 1971-01-26 | Rolls Royce | Dust or sand separators |
US3978656A (en) * | 1975-02-20 | 1976-09-07 | Avco Corporation | Gas turbine engine air inlets having particle separators |
US4047379A (en) * | 1976-04-28 | 1977-09-13 | General Electric Company | Transient air temperature sensing system |
US4268284A (en) * | 1977-11-07 | 1981-05-19 | Avco Corporation | Multichannel particle separator of the anti-icing type |
GB2155106A (en) * | 1984-02-29 | 1985-09-18 | Chlorine Eng Corp Ltd | Steam ejector |
US4605315A (en) * | 1984-12-13 | 1986-08-12 | United Technologies Corporation | Temperature probe for rotating machinery |
US4644746A (en) * | 1985-12-30 | 1987-02-24 | L. W. Fleckenstein, Inc. | Gas compressor for jet engine |
-
1985
- 1985-04-22 US US06/725,963 patent/US4644806A/en not_active Expired - Lifetime
-
1986
- 1986-03-06 IT IT19648/86A patent/IT1188567B/it active
- 1986-03-10 GB GB8605884A patent/GB2173861B/en not_active Expired
- 1986-03-11 JP JP61051591A patent/JPS61244698A/ja active Pending
- 1986-03-11 DE DE19863608035 patent/DE3608035A1/de not_active Withdrawn
- 1986-03-14 FR FR868603645A patent/FR2580809B1/fr not_active Expired
- 1986-03-26 CN CN86102097A patent/CN1007171B/zh not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN1072704C (zh) * | 1998-10-13 | 2001-10-10 | 中国石油化工集团公司 | 一种馏分油的加氢精制方法 |
Also Published As
Publication number | Publication date |
---|---|
GB8605884D0 (en) | 1986-04-16 |
IT8619648A0 (it) | 1986-03-06 |
JPS61244698A (ja) | 1986-10-30 |
CN86102097A (zh) | 1986-10-22 |
FR2580809A1 (fr) | 1986-10-24 |
GB2173861B (en) | 1989-12-28 |
DE3608035A1 (de) | 1986-10-23 |
IT8619648A1 (it) | 1987-09-06 |
FR2580809B1 (fr) | 1989-10-27 |
US4644806A (en) | 1987-02-24 |
GB2173861A (en) | 1986-10-22 |
IT1188567B (it) | 1988-01-20 |
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