专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明公开

EP3165826A1 IGNITER FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气轮机发动机
公开(公告)号：EP3165826A1
公开(公告)日：2017-05-10
申请号：EP16197343.3
申请日：2016-11-04
申请人： General Electric Company
发明人： BENNETT, William Thomas , KLASING, Kevin Samuel , GONYOU, Craig Alan
IPC分类号： F23R3/34 , F23Q3/00
CPC分类号： F02C7/264 , F05D2260/99 , F23Q3/008 , F23R3/343
摘要： A gas turbine engine includes a combustion section 26 spaced between a compressor section in a turbine section. The combustion section 26 defines a combustion chamber 88 and includes a combustor member defining an opening 118 to the combustion chamber 88. A mounting assembly 120 extends around or is positioned adjacent to the opening 118 defined by the combustor member. An igniter 114 extends through a ferrule 122 of the mounting assembly 120 and includes a distal end 116 positioned proximate the opening 118 in the combustor member. The igniter 114 defines a plurality of channels 138, each channel 138 extending between a first end 140 and a second end 142. The first end 140 is positioned away from the distal end 116 of the igniter 114 relative to the second end 142, and the second end 142 is a terminal end spaced from the distal end 116 of the igniter 114.
摘要翻译：燃气涡轮发动机包括在涡轮部分中的压缩机部分之间间隔开的燃烧部分26。燃烧部分26限定燃烧室88并且包括限定通向燃烧室88的开口118的燃烧器构件。安装组件120围绕由燃烧器构件限定的开口118延伸或邻近于开口118延伸。点火器114延伸穿过安装组件120的套箍122并且包括位于燃烧器构件中的开口118附近的远端116。点火器114限定了多个通道138，每个通道138在第一端140和第二端142之间延伸。第一端140相对于第二端142远离点火器114的远端116定位，并且第二端142是与点火器114的远端116隔开的终端。

2. 发明公开

EP3098429A4 JET ENGINE, FLYING BODY, AND METHOD FOR OPERATING JET ENGINE 有权
标题翻译： TRIEBWERK，FLUGZEUG UND VERFAHRENFÜRDEN BETRIEB EINES TRIEBWERKS
公开(公告)号：EP3098429A4
公开(公告)日：2017-03-22
申请号：EP15769123
申请日：2015-02-17
申请人： MITSUBISHI HEAVY IND LTD
发明人： UENO YOSHIHIKO , FURUYA SHOJIRO
IPC分类号： F02K7/10 , F02C7/00 , F02C7/042 , F02K7/18 , F23R3/22
CPC分类号： F23R3/22 , F02C7/042 , F02K7/10 , F02K7/18 , F05D2220/10 , F05D2220/80 , F05D2260/99 , F23R3/60 , F23R2900/00015 , F23R2900/00017 , Y02T50/671
摘要： A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.
摘要翻译：喷气式发动机包括吸入空气的入口（11）和使燃料与空气燃烧的燃烧器（12）。燃烧器（12）具有喷射器（20），多个火焰稳定器（21,22）和消失部分（31）。喷射器（20）喷射燃料。多个火焰稳定器（21,22）可以保持用于在燃烧器（12）中燃烧的火焰（F）。该消失部31设置成覆盖位于多个火焰稳定器21,22中靠近入口一侧的第一火焰稳定器21的凹陷，并且随着时间的推移而消失飞行。

3. 发明公开

EP1849974A2 Turbine engine tailcone resonator 有权转让
标题翻译： Tailcone-Resonatorfürein Turbinentriebwerk
公开(公告)号：EP1849974A2
公开(公告)日：2007-10-31
申请号：EP07250806.2
申请日：2007-02-27
申请人： United Technologies Corporation
发明人： Baarck, Jenny N. , Proscia, William , Krayenvenger, Daren , Jones, Christopher D.
IPC分类号： F02C5/10 , F02C5/11 , F23R3/00 , G10K11/172
CPC分类号： F01D25/30 , F02C5/10 , F02K1/827 , F02K3/10 , F05D2260/96 , F05D2260/99 , F23R3/00 , F23R2900/00014
摘要： A turbine engine resonator (80) comprising a panel (52) and a vessel (82). The panel (52) is along a flow path within the engine and has an aperture (72). The vessel (82) has a mounting flange (92) secured to the panel (52). The flange (92) has an aperture mated to the aperture (72) of the panel (52). The vessel (82) has a body secured to the mounting flange (92) with an interior of the body in communication with the flange aperture. A first portion (182) of the panel (52) extends into the mounting flange aperture and may redirect a leakage flow, if any, to limit an effect of leakage upon resonator performance.
摘要翻译：一种包括面板（52）和容器（82）的涡轮发动机谐振器（80）。面板（52）沿着发动机内的流动路径并且具有孔（72）。容器（82）具有固定到面板（52）的安装凸缘（92）。凸缘（92）具有与面板（52）的孔（72）配合的孔。容器（82）具有固定到安装凸缘（92）的主体，主体的内部与凸缘孔连通。面板（52）的第一部分（182）延伸到安装凸缘孔中，并且可以重定向泄漏流（如果有的话），以限制泄漏对谐振器性能的影响。

4. 发明公开

EP3098427A4 COMBUSTOR, JET ENGINE, FLYING BODY, AND METHOD FOR OPERATING JET ENGINE 有权
标题翻译： BRENNKAMMER，STRAHLTRIEBWERK，FLUGKÖRPERUND VERFAHREN ZUM BETRIEB DES STRAHLTRIEBWERKS
公开(公告)号：EP3098427A4
公开(公告)日：2017-03-15
申请号：EP15767934
申请日：2015-02-13
申请人： MITSUBISHI HEAVY IND LTD
发明人： UENO YOSHIHIKO , SUZUKI TASUKU , FURUYA SHOJIRO
IPC分类号： F02K7/10 , F02C7/00 , F02C7/26
CPC分类号： F02K7/105 , F02C7/264 , F02K7/10 , F05D2220/10 , F05D2260/99 , Y02T50/671
摘要： A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.
摘要翻译：喷气发动机包括吸入空气的入口和使用空气燃烧燃料的燃烧器。燃烧器包括燃料喷射器和用于点燃空气和燃料的气体混合物的点火器。点火器通过通过入口吸入的空气的压缩产生的热和压力自动点燃并激活。

5. 发明公开

EP3098427A1 COMBUSTOR, JET ENGINE, FLYING BODY, AND METHOD FOR OPERATING JET ENGINE 有权
标题翻译： COMBUSTOR，JET ENGINE，FLYING BODY以及用于操作JET ENGINE的方法
公开(公告)号：EP3098427A1
公开(公告)日：2016-11-30
申请号：EP15767934.1
申请日：2015-02-13
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： UENO, Yoshihiko , SUZUKI, Tasuku , FURUYA, Shojiro
IPC分类号： F02K7/10 , F02C7/00 , F02C7/26
CPC分类号： F02K7/105 , F02C7/264 , F02K7/10 , F05D2220/10 , F05D2260/99 , Y02T50/671
摘要： A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.
摘要翻译：喷气发动机包括吸入空气的进气口和使用空气燃烧燃料的燃烧室。燃烧器包括燃料喷射器和用于点燃空气和燃料的混合气体的点火器。点火器通过压缩通过进气口吸入的空气而产生的热量和压力自动点燃和激活。

6. 发明授权

EP1313937B1 HIGH FREQUENCY EXCITATION APPARATUS AND METHOD FOR REDUCING JET AND CAVITY NOISE 有权
标题翻译：用于降低喷气噪声的装置和方法高频振动的方式
公开(公告)号：EP1313937B1
公开(公告)日：2007-04-18
申请号：EP01955947.5
申请日：2001-07-24
申请人： The Boeing Company
发明人： KIBENS, Valdis , RAMAN, Ganesh
IPC分类号： F02K1/82
CPC分类号： F02K1/34 , F02K1/827 , F05D2260/96 , F05D2260/962 , F05D2260/99 , Y02T50/671
摘要： An active noise suppression apparatus and method for reducing jet engine noise and buffeting. A plurality of resonant cavities (12) are formed in a structural member disposed on or adjacent to a jet engine exhaust nozzle (22). Each resonant cavity opens toward an output slot. A compressed air chamber is used to supply a pressurized, supersonic jetstream airflow through the inlet port (16) into the interior area of the resonant cavity (12). This causes a high frequency, pulsed, excitation airstream to be generated outwardly form the cavity, out of the output slot and into the developing shear layer of the exhaust airflow. This high frequency, pulsed, excitation airstream induces modifications in the shear layer, which leads to a major reduction in the noise and buffeting generated by the developing shear layer.

7. 发明公开

EP1313937A1 HIGH FREQUENCY EXCITATION APPARATUS AND METHOD FOR REDUCING JET AND CAVITY NOISE 有权
标题翻译：用于降低喷气噪声的装置和方法高频振动的方式
公开(公告)号：EP1313937A1
公开(公告)日：2003-05-28
申请号：EP01955947.5
申请日：2001-07-24
申请人： THE BOEING COMPANY
发明人： KIBENS, Valdis , RAMAN, Ganesh
IPC分类号： F02K1/82
CPC分类号： F02K1/34 , F02K1/827 , F05D2260/96 , F05D2260/962 , F05D2260/99 , Y02T50/671
摘要： An active noise suppression apparatus and method for reducing jet engine noise and buffeting. A plurality of resonant cavities (12) are formed in a structural member disposed on or adjacent to a jet engine exhaust nozzle (22). Each resonant cavity opens toward an output slot. A compressed air chamber is used to supply a pressurized, supersonic jetstream airflow through the inlet port (16) into the interior area of the resonant cavity (12). This causes a high frequency, pulsed, excitation airstream to be generated outwardly form the cavity, out of the output slot and into the developing shear layer of the exhaust airflow. This high frequency, pulsed, excitation airstream induces modifications in the shear layer, which leads to a major reduction in the noise and buffeting generated by the developing shear layer.

8. 发明授权

EP3098427B1 COMBUSTOR, JET ENGINE, FLYING BODY, AND OPERATION METHOD OF JET ENGINE 有权
公开(公告)号：EP3098427B1
公开(公告)日：2018-12-26
申请号：EP15767934.1
申请日：2015-02-13
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： UENO, Yoshihiko , SUZUKI, Tasuku , FURUYA, Shojiro
IPC分类号： F02K7/10 , F02C7/00 , F02C7/26
CPC分类号： F02K7/105 , F02C7/264 , F02K7/10 , F05D2220/10 , F05D2260/99 , Y02T50/671
摘要： A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

9. 发明公开

EP3098515A1 JET ENGINE, FLYING BODY, AND METHOD OF OPERATING A JET ENGINE 有权
标题翻译：喷气发动机，飞行体，以及喷射引擎的操作方法
公开(公告)号：EP3098515A1
公开(公告)日：2016-11-30
申请号：EP15768566.0
申请日：2015-02-17
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： UENO, Yoshihiko , FURUYA, Shojiro
IPC分类号： F23R3/28 , F02C7/228 , F02C9/28 , F02K7/10
CPC分类号： F23R3/28 , F02K7/10 , F02K7/18 , F05D2220/80 , F05D2250/184 , F05D2250/313 , F05D2260/99 , F23R2900/00014 , Y02T50/671
摘要： A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.
摘要翻译：喷气发动机包括进气口和燃烧室。入口吸入空气。燃烧器与空气燃烧燃料。燃烧器（12）包括具有多个开口（31a，31b）的喷射器（20），燃料从该开口注入。多个开口（31a，31b）在与燃烧器（12）内的空气的流路方向垂直的方向上排列。多个开口（31a，31b）包括面积不同的两种开口。

10. 发明公开

EP3098429A1 JET ENGINE, FLYING BODY, AND METHOD FOR OPERATING JET ENGINE 有权
标题翻译： TRIEBWERK，FLUGZEUG UND VERFAHRENFÜRDEN BETRIEB EINES TRIEBWERKS
公开(公告)号：EP3098429A1
公开(公告)日：2016-11-30
申请号：EP15769123.9
申请日：2015-02-17
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： UENO, Yoshihiko , FURUYA, Shojiro
IPC分类号： F02K7/10 , F02C7/00 , F02C7/042 , F02K7/18 , F23R3/22
CPC分类号： F23R3/22 , F02C7/042 , F02K7/10 , F02K7/18 , F05D2220/10 , F05D2220/80 , F05D2260/99 , F23R3/60 , F23R2900/00015 , F23R2900/00017 , Y02T50/671
摘要： A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.
摘要翻译：喷气发动机包括吸入空气的入口（11）和燃烧燃料的燃烧器（12）。燃烧器（12）具有喷射器（20），多个火焰稳定器（21,22）和消除部分（31）。喷射器（20）喷射燃料。多个火焰稳定器（21,22）可以保持用于在燃烧器（12）中燃烧的火焰（F）。减轻部分31被设置为覆盖位于多个火焰稳定器（21,22）中的入口附近的第一火焰稳定器（21）的凹陷，随着时间的推移而消失飞行。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式