CN1779223A - 具有流体捕获管的流体混合器 - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
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- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
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- B64D33/06—Silencing exhaust or propulsion jets
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Abstract
用于混合两个流体流(40、42)的流体混合器包括一组限定交替的初级主通道和次级主通道(30、32)的主凸叶(26)、在主凸叶的两个中间的一个或者多个辅助凸叶(28)，以及辅助流体捕获管(62)。辅助凸叶至少部分由管的排出端限定。在运行中，尽管存在否则阻碍两个流体流的完全混合的障碍物(18)，管将次级流体输送到由凸叶限定的次级通道(36)，从而改进混合器的性能。
Description
技术领域
本发明涉及在混合流涡轮风扇燃气轮机中有用的流体混合器类型，特别是涉及一种具有辅助管来捕获否则被障碍物阻碍的流体的混合器。
背景技术
典型的涡轮风扇发动机包括核心发动机、风扇和混合流排放***。该排放***包括排放管，其向前的或者上游端围绕内部混合器。典型的混合器特征在于一组圆周分布的凸叶，其限定圆周交替的初级通道和次级通道。在运转期间，核心发动机将热的高速燃烧产物的初级流排放到初级通道中。同时，风扇将相对凉相对低速的旁路空气的次级流排放到次级通道中。圆周交替的初级通道和次级通道促进燃烧产物与旁路空气的完全的圆周均匀混合，这导致增强的推进效率和减小的排放噪声。
在一些飞机中，发动机安装支杆和相关的整流装置径向跨过次级空气流。整流装置轴向***由凸叶占据的混合器的部分中，且也具有相当大的圆周宽度，通常大约与两个或者三个混合器凸叶的圆周宽度相同。由于该***，发动机制造商不能邻近整流装置提供有效的次级通道。替代地，混合器邻近整流装置只具有单个圆周宽的凸叶以及相应宽的初级通道。宽的初级通道和缺少次级通道损害了混合器均匀地且完全地混合初级流体流和次级流体流的能力。这导致减小的推进效率和升高的声音发射。
所需要的是，尽管邻近混合器凸叶存在障碍物，也能够实现完全的圆周均匀的混合的流体混合器。
发明内容
根据本发明的一个实施例，流体混合器包括一组限定交替的初级通道和次级通道的主凸叶，圆周上在主凸叶的两个之间的一个或者多个辅助凸叶，以及一个或者多个辅助流体捕获管。辅助凸叶至少部分由管的排出端限定。在运转中，管输送次级流体到由凸叶限定的次级通道，从而改进混合器的性能。
在另一个实施例中，辅助流体捕获管的向前端突出到次级流体流中，以促进有效的空气捕获和总的压力恢复。
从下面的实现本发明的最佳模式和附图的描述，可以更加明白本发明的这些和其它实施例的特征。
附图说明
图1是从飞机机翼悬挂且由发动机舱围绕的涡轮风扇燃气轮机的侧面正视图。
图2是图1的后部部分的放大的透视图，去掉了发动机舱，以暴露包括辅助流体捕获管的流体混合器。
图3是图2的混合器的透视图。
图4是图3的混合器的平面图。
图5是图4的5-5方向的视图，即，轴向向上游看。
图6是图4的6-6方向的视图，即，轴向向下游看。
图7是图2的混合器的透视图。
具体实施方式
参考图1-3，飞机推进***包括具有轴线12的涡轮风扇燃气轮机10。空气动力学的流线型的发动机舱14围绕发动机。没有显示的安装支杆将发动机从飞机机翼16悬挂。流线型的整流装置18包围安装支杆和在发动机和机翼之间延伸的其它部件(例如，燃料管线)。
排放***包括排放管22，其向前的或者上游端围绕内部流体混合器24。混合器包括一组圆周分布的凸叶，其包括几个主凸叶26和三个辅助凸叶28。如图2可以最好地看出，整流装置18轴向且圆周***凸叶附近。暂时参考图5，凸叶限定圆周交替的初级通道和次级通道，诸如主的初级通道30、主的次级通道32、辅助初级通道34，特别为34A、34B、34C，以及辅助次级通道36，特别为36A、36B。
在发动机运转期间，发动机将热的高速燃烧气体的初级核心流40排放到初级通道中，以及将相对凉相对低速的旁路空气的次级环形流42排放到次级通道中。混合器部分地将每个流40、42分为许多初级和次级支流44、46，其流过圆周交替的初级通道和次级通道。该通道促进燃烧气体与旁路空气的完全混合，以产生单一很好混合的排放流48。
每个主凸叶26包括一对大致径向延伸的侧壁50和圆周桥接在侧壁之间的槽52。主凸叶限定由侧壁和槽在三侧上界定且在第四侧上开口的交替的初级主通道30和次级主通道32。初级通道和次级通道共用共同的侧壁。例如，侧壁50Q是初级通道30F和次级通道32F两者的侧壁。主凸叶的侧壁包括扇贝形结构54(图2和3)，其增强初级流体流和次级流体流的混合。如图4可见，主凸叶的最后的末端限定旋绕的主凸叶后缘58，以及相关的主排出平面60。
参考图4-7，主要参考图4，混合器还包括一对辅助流体捕获管62，整流装置18的每侧一个。该管整合到混合器。每个管具有进口端64和排出端66。每个管的进口端包括径向内壁68A或者68B、径向外壁70A或者70B、内侧侧壁72A或者72B，以及外侧侧壁74A或者74B。管前缘78限定每个管的近似矩形的进口开口80(图6和7)和相关的管进口平面82(图4)。每个管的进口端径向突出到次级流体流42中。每个进口平面以相对于垂直于发动机轴线12的平面84成大约0度到25度之间的偏斜角α定向。在所示的混合器中，进口平面82以大约20度的角α定向。该定向角将管进口与次级流体流的局部方向对准，如图4最好地看出。
管壁68、72、74在管的排出端处过渡到辅助凸叶的侧壁和槽且至少部分限定辅助凸叶的侧壁和槽。辅助凸叶分别限定初级辅助通道和次级辅助通道34A-34C和36A-36B，类似于初级主通道30和次级主通道32。例如，管内侧侧壁72A、72B限定辅助初级通道34B的侧壁50C、50D。这些侧壁50C、50D也是辅助次级通道36A、36B的内侧侧壁。管外侧侧壁74A和径向内部管壁68A沿着管的长度逐渐合在一起，以限定辅助次级通道36A的外侧侧壁50B和槽52。类似的，管外侧侧壁74B和径向内部管壁68B沿着管的长度逐渐合在一起，以限定辅助次级通道36B的外侧侧壁50E和槽52。侧壁50B、50E每个还形成辅助初级通道34A、34C的一个侧壁。每个通道34A、34C的另一个壁分别由侧壁50A、50F形成。
辅助凸叶的最后的末端限定辅助凸叶后缘86和相关的辅助排出平面88。辅助凸叶后缘86不比主凸叶后缘58向前。当辅助凸叶后缘与主凸叶后缘轴向重合时，出现最优混合。然而，在所示的混合器中，辅助凸叶后缘在主凸叶后缘的后部，使得流过每个管62的流体能够从在管进口平面82处的角度β相对渐进地转变到在辅助排出平面88处的大致轴向。较渐进的转变有助于减小空气动力学损耗，且防止流体从管壁分离。
每个管从进口平面到辅助排出平面会聚大约20％的面积。该会聚加速次级流体，且有助于防止流体从管壁分离。
如果需要额外的噪声降低，在辅助凸叶的侧壁上包括类似于扇贝形结构54的扇贝形结构是有益的。
所示的混合器包括两个管、两个辅助次级通道和三个辅助初级通道。每个管将流体输送到一个辅助辅助次级通道。然而，其它布置也是可能的，包括那些其中每个管将次级流体输送到多个辅助次级通道的情况。
在发动机运转期间，整流装置18妨碍次级流体流流入紧接着整流装置后部的区域。因此，本发明之前的混合器在混合器与整流装置圆周对准的区域中没有次级通道。替代地，本发明之前的混合器在整流装置附近只有单个圆周宽的凸叶和相应宽的初级通道。宽的初级通道和缺少次级通道损害了混合器的效率。
通过对比，本发明的混合器的管62捕获流过整流装置的侧面的次级流体，且将流体输送到辅助次级通道36。因为每个管62的进口端64径向突出到次级流体流中，进口充当塞入收集器。塞入收集器捕获足够的空气，以完全填充管和辅助次级通道，且与依赖在进口和排放处的静压力之间的差来推动流体通过管的被动管的情况相比，将恢复更大的总压力。同时，一定量的初级流体进入辅助初级通道34。辅助初级通道和辅助次级通道的存在在与整流装置圆周对准的混合器的部分中改进了流体混合。
虽然参考本发明的特殊实施例显示和描述了本发明，但是本领域中的普通技术人员应该理解，在不偏离如后附权利要求书中阐述的本发明的情况下，可以进行在形式和细节上的各种变化。
Claims (13)
1.一种流体混合器，其包括：
一组限定交替的初级通道和次级通道的主凸叶；
在主凸叶的两个中间的一个或者多个辅助凸叶；以及
具有进口端和排出端的管，其中，辅助凸叶至少部分由管的排出端限定。
2.如权利要求1所述的混合器，其中，管的进口端突出到次级流体流中。
3.如权利要求1所述的混合器，其中，主凸叶具有主凸叶后缘，辅助凸叶具有辅助凸叶后缘，且辅助后缘不比主后缘向前。
4.如权利要求1所述的混合器，其中，管在下游方向上的区域中会聚。
5.如权利要求4所述的混合器，其中，管从进口端到排出端会聚大约20％的面积。
6.如权利要求1所述的混合器，其中，至少主凸叶具有扇贝形结构的侧壁。
7.如权利要求1所述的混合器，其中，管具有以偏斜角定向的进口平面。
8.如权利要求1所述的混合器，其中，该偏斜角在大约0度和25度之间。
9.如权利要求1所述的混合器，包括正好两个管。
10.如权利要求1所述的混合器，其中，每个管将次级流体输送到正好一个次级通道。
11.如权利要求1所述的混合器，其中，混合器是涡轮发动机的部件，初级流体流是相对热的燃烧产品的流，次级流体流是相对凉的旁路空气的流。
12.如权利要求1所述的混合器，其中，混合器是具有跨过次级流体流的障碍物的涡轮发动机的部件，辅助凸叶与障碍物圆周对准。
13.如权利要求1所述的混合器，其中，管是混合器的整体部分。
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/973103 | 2004-10-25 | ||
| US10/973,103 US7434384B2 (en) | 2004-10-25 | 2004-10-25 | Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts |
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| Publication Number | Publication Date |
|---|---|
| CN1779223A true CN1779223A (zh) | 2006-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN200510118071.2A Pending CN1779223A (zh) | 2004-10-25 | 2005-10-25 | 具有流体捕获管的流体混合器 |
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| Country | Link |
|---|---|
| US (1) | US7434384B2 (zh) |
| EP (1) | EP1650126B1 (zh) |
| JP (1) | JP2006116539A (zh) |
| CN (1) | CN1779223A (zh) |
| DE (1) | DE602005007829D1 (zh) |
| RU (1) | RU2005133419A (zh) |
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| US9353682B2 (en) | 2012-04-12 | 2016-05-31 | General Electric Company | Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation |
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| US9784185B2 (en) | 2012-04-26 | 2017-10-10 | General Electric Company | System and method for cooling a gas turbine with an exhaust gas provided by the gas turbine |
| WO2014007907A2 (en) * | 2012-04-27 | 2014-01-09 | General Electric Company | Variable immersion lobe mixer for turbofan jet engine exhauts and method of fabricating the same |
| US10190536B2 (en) | 2012-09-17 | 2019-01-29 | Pratt & Whitney Canada Corp. | Turbine exhaust case mixer of gas turbine with variable thickness |
| US9708977B2 (en) | 2012-12-28 | 2017-07-18 | General Electric Company | System and method for reheat in gas turbine with exhaust gas recirculation |
| US10107495B2 (en) | 2012-11-02 | 2018-10-23 | General Electric Company | Gas turbine combustor control system for stoichiometric combustion in the presence of a diluent |
| US9803865B2 (en) | 2012-12-28 | 2017-10-31 | General Electric Company | System and method for a turbine combustor |
| US9611756B2 (en) | 2012-11-02 | 2017-04-04 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
| US9599070B2 (en) | 2012-11-02 | 2017-03-21 | General Electric Company | System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system |
| US10100741B2 (en) | 2012-11-02 | 2018-10-16 | General Electric Company | System and method for diffusion combustion with oxidant-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system |
| US9631815B2 (en) | 2012-12-28 | 2017-04-25 | General Electric Company | System and method for a turbine combustor |
| US10215412B2 (en) | 2012-11-02 | 2019-02-26 | General Electric Company | System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system |
| US9574496B2 (en) | 2012-12-28 | 2017-02-21 | General Electric Company | System and method for a turbine combustor |
| US9869279B2 (en) | 2012-11-02 | 2018-01-16 | General Electric Company | System and method for a multi-wall turbine combustor |
| US10208677B2 (en) | 2012-12-31 | 2019-02-19 | General Electric Company | Gas turbine load control system |
| US9581081B2 (en) | 2013-01-13 | 2017-02-28 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
| US9512759B2 (en) | 2013-02-06 | 2016-12-06 | General Electric Company | System and method for catalyst heat utilization for gas turbine with exhaust gas recirculation |
| US9938861B2 (en) | 2013-02-21 | 2018-04-10 | Exxonmobil Upstream Research Company | Fuel combusting method |
| TW201502356A (zh) | 2013-02-21 | 2015-01-16 | Exxonmobil Upstream Res Co | 氣渦輪機排氣中氧之減少 |
| US10221762B2 (en) | 2013-02-28 | 2019-03-05 | General Electric Company | System and method for a turbine combustor |
| TW201500635A (zh) | 2013-03-08 | 2015-01-01 | Exxonmobil Upstream Res Co | 處理廢氣以供用於提高油回收 |
| US9618261B2 (en) | 2013-03-08 | 2017-04-11 | Exxonmobil Upstream Research Company | Power generation and LNG production |
| CA2902479C (en) | 2013-03-08 | 2017-11-07 | Exxonmobil Upstream Research Company | Power generation and methane recovery from methane hydrates |
| US20140250945A1 (en) | 2013-03-08 | 2014-09-11 | Richard A. Huntington | Carbon Dioxide Recovery |
| US9631542B2 (en) | 2013-06-28 | 2017-04-25 | General Electric Company | System and method for exhausting combustion gases from gas turbine engines |
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| US10197010B2 (en) * | 2013-08-12 | 2019-02-05 | The Boeing Company | Long-duct, mixed-flow nozzle system for a turbofan engine |
| US10030588B2 (en) | 2013-12-04 | 2018-07-24 | General Electric Company | Gas turbine combustor diagnostic system and method |
| US9752458B2 (en) | 2013-12-04 | 2017-09-05 | General Electric Company | System and method for a gas turbine engine |
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| US10079564B2 (en) | 2014-01-27 | 2018-09-18 | General Electric Company | System and method for a stoichiometric exhaust gas recirculation gas turbine system |
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| US9574518B2 (en) | 2014-06-02 | 2017-02-21 | The Boeing Company | Turbofan engine with variable exhaust cooling |
| US10060359B2 (en) | 2014-06-30 | 2018-08-28 | General Electric Company | Method and system for combustion control for gas turbine system with exhaust gas recirculation |
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| US9819292B2 (en) | 2014-12-31 | 2017-11-14 | General Electric Company | Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine |
| US9869247B2 (en) | 2014-12-31 | 2018-01-16 | General Electric Company | Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation |
| US10788212B2 (en) | 2015-01-12 | 2020-09-29 | General Electric Company | System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation |
| US10094566B2 (en) | 2015-02-04 | 2018-10-09 | General Electric Company | Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation |
| US10253690B2 (en) | 2015-02-04 | 2019-04-09 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
| US10316746B2 (en) | 2015-02-04 | 2019-06-11 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
| US10267270B2 (en) | 2015-02-06 | 2019-04-23 | General Electric Company | Systems and methods for carbon black production with a gas turbine engine having exhaust gas recirculation |
| US10145269B2 (en) | 2015-03-04 | 2018-12-04 | General Electric Company | System and method for cooling discharge flow |
| US10480792B2 (en) | 2015-03-06 | 2019-11-19 | General Electric Company | Fuel staging in a gas turbine engine |
| US10272398B2 (en) * | 2015-11-06 | 2019-04-30 | Ford Global Technologies, Llc | Static flow mixer with multiple open curved channels |
| US11028778B2 (en) | 2018-09-27 | 2021-06-08 | Pratt & Whitney Canada Corp. | Engine with start assist |
| GB2592267A (en) * | 2020-02-24 | 2021-08-25 | Altair Uk Ltd | Pulse nozzle for filter cleaning systems |
Family Cites Families (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3053340A (en) * | 1958-07-21 | 1962-09-11 | Gen Electric | Noise suppression nozzle |
| US3084505A (en) * | 1960-05-03 | 1963-04-09 | Robert A Cherchi | Exhaust duct for turbo-jet engine |
| US3027710A (en) * | 1960-10-10 | 1962-04-03 | Stephen P Maytner | Methods and apparatus for suppressing jet noise |
| US4335573A (en) * | 1970-09-02 | 1982-06-22 | General Electric Company | Gas turbine engine mixer |
| US4077206A (en) * | 1976-04-16 | 1978-03-07 | The Boeing Company | Gas turbine mixer apparatus for suppressing engine core noise and engine fan noise |
| US4072008A (en) * | 1976-05-04 | 1978-02-07 | General Electric Company | Variable area bypass injector system |
| US4149375A (en) * | 1976-11-29 | 1979-04-17 | United Technologies Corporation | Lobe mixer for gas turbine engine |
| US4302934A (en) * | 1979-11-01 | 1981-12-01 | United Technologies Corporation | Lobed mixer/inverter |
| GB2082259B (en) * | 1980-08-15 | 1984-03-07 | Rolls Royce | Exhaust flow mixers and nozzles |
| GB2104967B (en) * | 1981-09-03 | 1985-07-17 | Rolls Royce | Exhaust mixer for turbofan aeroengine |
| US4819425A (en) * | 1982-03-18 | 1989-04-11 | The Boeing Company | Primary-secondary ventilated flow mixer nozzle for high bypass turbo fan jet propulsion system |
| US4422524A (en) * | 1982-03-22 | 1983-12-27 | Lockheed Corporation | Variable shape, fluid flow nozzle for sound suppression |
| GB2149456B (en) * | 1983-11-08 | 1987-07-29 | Rolls Royce | Exhaust mixing in turbofan aeroengines |
| GB2209054B (en) * | 1987-08-26 | 1992-04-15 | Rolls Royce Plc | Gas turbine nozzles |
| US5117628A (en) * | 1990-01-25 | 1992-06-02 | General Electric Company | Mixed flow augmentor pre-mixer |
| US5216879A (en) * | 1991-08-30 | 1993-06-08 | United Technologies Corporation | Propulsion system assembly |
| US5265807A (en) * | 1992-06-01 | 1993-11-30 | Rohr, Inc. | Aerodynamic stiffening ring for an aircraft turbine engine mixer |
| US5372006A (en) * | 1993-02-08 | 1994-12-13 | Aeronautical Concept Of Exhaust, Ltd. | Turbine engine equipped with thrust reverser |
| ATE159567T1 (de) * | 1993-06-25 | 1997-11-15 | Nordam Group Inc | System zur schalldämpfung |
| US5638675A (en) * | 1995-09-08 | 1997-06-17 | United Technologies Corporation | Double lobed mixer with major and minor lobes |
| FR2740175B1 (fr) * | 1995-10-18 | 1997-11-21 | Snecma | Dispositif de pylone associe au melangeur d'une tuyere d'ejection de turboreacteur a flux melangeur |
| US6016651A (en) * | 1997-06-24 | 2000-01-25 | Sikorsky Aircraft Corporation | Multi-stage mixer/ejector for suppressing infrared radiation |
| US6487848B2 (en) * | 1998-11-06 | 2002-12-03 | United Technologies Corporation | Gas turbine engine jet noise suppressor |
| US6578355B1 (en) * | 1999-03-05 | 2003-06-17 | Rolls-Royce Deutschland Ltd & Co Kg | Bloom mixer for a turbofan engine |
| US6276127B1 (en) * | 1999-06-22 | 2001-08-21 | John R. Alberti | Noise suppressing mixer for jet engines |
| US6612106B2 (en) * | 2000-05-05 | 2003-09-02 | The Boeing Company | Segmented mixing device having chevrons for exhaust noise reduction in jet engines |
| US6640537B2 (en) * | 2000-12-18 | 2003-11-04 | Pratt & Whitney Canada Corp. | Aero-engine exhaust jet noise reduction assembly |
| US7017331B2 (en) * | 2002-12-07 | 2006-03-28 | Anderson Jack H | Jet nozzle mixer |
| US7114323B2 (en) * | 2004-03-05 | 2006-10-03 | United Technologies Corporation | Jet exhaust noise reduction system and method |
-
2004
- 2004-10-25 US US10/973,103 patent/US7434384B2/en active Active
-
2005
- 2005-10-24 JP JP2005308242A patent/JP2006116539A/ja active Pending
- 2005-10-25 DE DE602005007829T patent/DE602005007829D1/de active Active
- 2005-10-25 CN CN200510118071.2A patent/CN1779223A/zh active Pending
- 2005-10-25 EP EP05256605A patent/EP1650126B1/en active Active
- 2005-10-25 RU RU2005133419/06A patent/RU2005133419A/ru not_active Application Discontinuation
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101517219B (zh) * | 2006-06-21 | 2011-06-01 | 法国空中巴士公司 | 包含具有凹形机翼后缘的喷射管道的飞行器推进*** |
| CN101809272B (zh) * | 2007-08-14 | 2013-09-04 | 空中客车运营简化股份公司 | 用于尾喷管的抗噪v形尾缘、具有这种v形尾缘的尾喷管和涡轮发动机 |
| CN103988020A (zh) * | 2011-12-12 | 2014-08-13 | 西门子公司 | 用于两种燃料的燃料喷嘴 |
| US9435262B2 (en) | 2011-12-12 | 2016-09-06 | Siemens Aktiengesellschaft | Fuel nozzle having an inner tube and an outer tube engaged with the inner tube |
| CN105508133A (zh) * | 2016-01-25 | 2016-04-20 | 云南电网有限责任公司电力科学研究院 | 一种流体元素的捕获装置和方法 |
| CN105508133B (zh) * | 2016-01-25 | 2018-09-14 | 云南电网有限责任公司电力科学研究院 | 一种流体元素的捕获装置和方法 |
| CN113464277A (zh) * | 2021-07-15 | 2021-10-01 | 哈尔滨工程大学 | 一种带异形波瓣引射混合器的船舶燃气轮机 |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1650126B1 (en) | 2008-07-02 |
| EP1650126A3 (en) | 2006-08-16 |
| JP2006116539A (ja) | 2006-05-11 |
| US20080190096A1 (en) | 2008-08-14 |
| US7434384B2 (en) | 2008-10-14 |
| DE602005007829D1 (de) | 2008-08-14 |
| EP1650126A2 (en) | 2006-04-26 |
| RU2005133419A (ru) | 2007-04-27 |
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