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1. 发明申请

US20190219057A1 CENTRIFUGAL COMPRESSOR WITH DIFFUSER WITH THROAT 审中-公开
公开(公告)号：US20190219057A1
公开(公告)日：2019-07-18
申请号：US16314170
申请日：2017-06-29
申请人： Cummins Ltd.
发明人： Subenuka Sivagnanasundaram
IPC分类号： F04D17/10 , F04D29/44
CPC分类号： F04D17/10 , F04D29/441 , F05D2250/16 , F05D2250/323 , F05D2250/324 , F05D2250/52 , F05D2250/71 , F05D2250/711
摘要： A diffuser is proposed which is formed as the gap between rotationally-symmetric surfaces which face each other. Moving in the radial direction, the axial extent of the gap generally decreases to a minimum value in a throat portion of the diffuser, and then generally increases again. The distance from the rotational axis of the compressor to the throat may be approximately at least 125% of the radius of the compressor wheel. The inventors have found that a throat at this distance from the rotational axis may lead to higher efficiency at high flow rates, especially for relatively low turbo speeds. This is because the spacing between the compressor wheel and the throat permits diffusion of the gas streams leaving the compressor wheel.

2. 发明授权

US09995151B2 Article and manifold for thermal adjustment of a turbine component 有权
公开(公告)号：US09995151B2
公开(公告)日：2018-06-12
申请号：US14828094
申请日：2015-08-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Ibrahim Sezer , Gary Michael Itzel , Jaime Javier Maldonado , Sandip Dutta
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12 , F02C7/12 , F23R3/00
CPC分类号： F01D5/189 , F01D5/186 , F01D9/02 , F01D25/12 , F02C7/12 , F05D2250/32 , F05D2250/324 , F05D2260/201 , F05D2260/2212 , F23R3/002 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

3. 发明授权

US09732700B2 Methods and apparatus for passive thrust vectoring and plume deflection 有权
公开(公告)号：US09732700B2
公开(公告)日：2017-08-15
申请号：US14496526
申请日：2014-09-25
申请人： The Boeing Company
发明人： David F. Cerra , Robert H. Willie , Alvaro Prieto
IPC分类号： F02K1/00 , F02K1/06 , F02K1/30 , F02K1/46 , B64C7/02 , B64D33/04
CPC分类号： F02K1/006 , B64C7/02 , B64D33/04 , F02K1/002 , F02K1/06 , F02K1/30 , F02K1/46 , F05D2250/323 , F05D2250/324 , F05D2250/71 , F05D2250/73 , F05D2260/96 , Y02T50/671
摘要： A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.

4. 发明授权

US09482098B2 Convective shielding cooling hole pattern 有权
标题翻译：对流屏蔽冷却孔图案
公开(公告)号：US09482098B2
公开(公告)日：2016-11-01
申请号：US13469647
申请日：2012-05-11
申请人： San Quach , Steven Bruce Gautschi , Christina E. Botnick
发明人： San Quach , Steven Bruce Gautschi , Christina E. Botnick
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/145 , F01D5/187 , F05D2240/81 , F05D2250/23 , F05D2250/231 , F05D2250/232 , F05D2250/324 , F05D2260/201
摘要： The cooling system for a turbine may include a plurality of platform cooling openings positioned in a platform of the turbine airfoil. In particular, the first set of cooling openings may create a first cooling path and a second set of cooling openings may be placed in the path of the first cooling path where the first cooling flow will cool the second set of cooling openings.
摘要翻译：涡轮机的冷却系统可以包括定位在涡轮机翼型平台中的多个平台冷却开口。特别地，第一组冷却开口可以产生第一冷却路径，并且第二组冷却开口可以放置在第一冷却路径的路径中，其中第一冷却流将冷却第二组冷却开口。

5. 发明申请

US20160160797A1 NOZZLE OF A TURBOMACHINE PROVIDED WITH CHEVRONS WITH A NON-AXISYMMETRIC INNER FACE 审中-公开
标题翻译：具有非轴对称内镜的涡轮增压器的喷嘴
公开(公告)号：US20160160797A1
公开(公告)日：2016-06-09
申请号：US14904330
申请日：2014-07-15
申请人： SNECMA
发明人： Jonathan LANGRIDGE , Julien SZYDLOWSKI
IPC分类号： F02K1/44
CPC分类号： F02K1/44 , F02K1/34 , F02K1/386 , F02K1/46 , F05D2250/11 , F05D2250/183 , F05D2250/184 , F05D2250/323 , F05D2250/324 , F05D2250/711 , F05D2250/712 , F05D2260/96
摘要： A nozzle of a turbomachine is provided with chevrons with a non-axisymmetric inner face. A cover for the nozzle of longitudinal axis L-L includes an internal wall having a section with a predetermined abscissa on the L-L axis defining, on the wall, a neck line. The cover has, downstream from the abscissa, indentations in the trailing edge of the cover delimiting chevrons distributed in the circumferential direction, in which, on the cover, from the abscissa the internal wall moves away radially towards the outside of the upstream tangent, to the top of an indentation, the outer wall of the cover moves towards the upstream tangent to the top of an indentation, and the internal wall moves away radially towards the inside of the upstream tangent, to the tip of a chevron.
摘要翻译：涡轮机的喷嘴设置有具有非轴对称内表面的人字纹。用于纵向轴线L-L的喷嘴的盖包括内壁，其具有在L-L轴上具有预定横轴的部分，在壁上限定颈部线。盖子在横向方向的下游具有沿着圆周方向分隔的人字形的后缘上的凹口，其中，在盖子上，从横坐标的角度看，内壁朝向上游切线的外侧径向移动到凹陷的顶部，盖的外壁朝向凹陷顶部的上游切线移动，并且内壁朝向上游切线的内侧径向移动到人字形的尖端。

6. 发明授权

US09260974B2 System and method for active clearance control 有权
标题翻译：主动间隙控制的系统和方法
公开(公告)号：US09260974B2
公开(公告)日：2016-02-16
申请号：US13625924
申请日：2012-09-25
申请人： General Electric Company
发明人： William Howard Hasting , David William Crall , Craig William Higgins , Erich Alois Krammer
IPC分类号： F02C6/08 , F01D11/24 , F01D11/20 , F01D25/24
CPC分类号： F01D11/24 , F01D11/20 , F01D25/24 , F02C6/08 , F05D2250/323 , F05D2250/324
摘要： Active clearance control ejector systems and methods are disclosed. An example system may include an air ejector; an entrance pipe arranged to supply compressor bleed air to the air ejector; an inlet duct arranged to supply fan bypass air to the air ejector; and a supply pipe arranged to receive ejector outlet air from the air ejector and supply the ejector outlet air to an active clearance control system. The ejector outlet air may include a mixture of the compressor bleed air and the fan bypass air. The air ejector may include a venturi arranged to conduct the compressor bleed air therethrough, thereby drawing the fan bypass air into the air ejector.
摘要翻译：公开了主动间隙控制喷射器系统和方法。示例性系统可以包括空气喷射器; 入口管，布置成将压缩机排放空气供应到空气喷射器; 入口管道，其布置成将风扇旁路空气供应到空气喷射器; 以及供应管，布置成从喷射器接收喷射器出口空气，并将喷射器出口空气供应到主动间隙控制系统。喷射器出口空气可以包括压缩机排出空气和风扇旁路空气的混合物。空气喷射器可以包括文丘里管，其布置成将压缩机排气通过其中，从而将风扇旁路空气抽入空气喷射器。

7. 发明申请

US20140321970A1 PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL 审中-公开
标题翻译：用于空气入口空气流量控制的被动边界层系统
公开(公告)号：US20140321970A1
公开(公告)日：2014-10-30
申请号：US14325583
申请日：2014-07-08
申请人： United Technologies Corporation
发明人： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
IPC分类号： F02C9/18
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
摘要： A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
摘要翻译：用于燃气涡轮发动机系统的机舱包括具有压力侧和吸力侧的壳体。通道在压力侧和吸力侧之间延伸，以允许从压力侧到吸力侧的气流。通道包括在压力侧具有入口的第一弯曲部分。线性部分与第一弯曲部分连接。第二弯曲部分与线性部分连接并且在吸力侧具有出口。出口的横截面积小于线性部分的横截面面积。

8. 发明申请

US20140216055A1 GAS TURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：US20140216055A1
公开(公告)日：2014-08-07
申请号：US14343369
申请日：2012-09-12
申请人： Yasuro Sakamoto , Keisuke Matsuyama , Keizo Tsukagoshi , Masanori Yuri , Hiroaki Kishida , Shunsuke Torii
发明人： Yasuro Sakamoto , Keisuke Matsuyama , Keizo Tsukagoshi , Masanori Yuri , Hiroaki Kishida , Shunsuke Torii
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F01D9/023 , F05D2250/324 , F05D2250/52 , F05D2250/71 , F23C2201/20 , F23C2900/06043 , F23D11/106 , F23D11/38 , F23D2214/00 , F23R3/16 , F23R3/283 , F23R3/36 , F23R3/42 , F23R3/46 , F23R2900/00014 , F23R2900/03341
摘要： In this gas turbine, at a downstream portion of a transition piece of a combustor, inner surfaces of a pair of lateral walls facing each other in a circumferential direction of a turbine rotor form inclination surfaces that incline down to a downstream end of the transition piece in a direction approaching the transition piece of another adjacent combustor that gradually draws closer as it goes to the downstream side of the transition piece in an axis direction.
摘要翻译：在该燃气轮机中，在燃烧器的过渡件的下游部分，在涡轮转子的圆周方向上彼此相对的一对侧壁的内表面形成向下倾斜到过渡件的下游端的倾斜表面在接近另一相邻燃烧器的过渡件的方向上，当其沿着轴向移动到过渡件的下游侧时，其逐渐变得更靠近。

9. 发明申请

US20140130503A1 TURBOFAN ENGINE WITH CONVERGENT - DIVERGENT EXHAUST NOZZLE 审中-公开
标题翻译： TURBOFAN发动机具有融合 - 多样的排气喷嘴
公开(公告)号：US20140130503A1
公开(公告)日：2014-05-15
申请号：US14131802
申请日：2012-07-13
申请人： Cor Leep
发明人： Cor Leep
IPC分类号： F02K1/28
CPC分类号： F02K1/28 , F02K1/36 , F02K3/065 , F05D2250/323 , F05D2250/324 , F05D2260/601
摘要： With the speedy and hot airplane turbojet exhaust gases a lot of energy is blown away and wasted nowadays. By this invention a venturi (35) and a diverging duct (14) transform this exhaust energy into a useful and strong low pressure gas stream that sucks outside air through a fan (3) and a bypass (9,10,11) outside the original turbojet engine. (here called core engine). Thus the fan (3) is propelled and drives the central shaft (2) of the core engine (4). Now the turbine (7) in the rear of the core engine (4) can deliver less energy to the central shaft (21) for maintaining the right rotation. Likewise turbine (7) can absorb less energy out of the hot and speedy gases inside the core engine. A bigger part of this energy is available for creating thrust now. That is the major profit of this new invention.
摘要翻译：随着快速和热的飞机涡轮喷气式废气，现在大量的能量被吹走和浪费。通过本发明，文丘里管（35）和发散管道（14）将该排气能量转化成有用且强力的低压气流，其通过外部的风扇（3）和旁路（9,10,11）吸入外部空气。原始涡轮喷气发动机。（这里称为核心引擎）。因此，风扇（3）被推进并驱动核心发动机（4）的中心轴（2）。现在，核心发动机（4）后部的涡轮机（7）可以向中心轴（21）输送更少的能量以维持正确的旋转。同样，涡轮机（7）可以从核心发动机内的热和快速气体中吸收更少的能量。这种能量的较大部分现在可用于创建推力。这是这项新发明的主要利润。

10. 发明授权

US08707713B2 Cooling hole with crenellation features 有权
标题翻译：冷却孔具有排气功能
公开(公告)号：US08707713B2
公开(公告)日：2014-04-29
申请号：US13544107
申请日：2012-07-09
申请人： Glenn Levasseur , Edward F. Pietraszkiewicz
发明人： Glenn Levasseur , Edward F. Pietraszkiewicz
IPC分类号： F02C7/12
CPC分类号： F01D25/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2250/182 , F05D2250/183 , F05D2250/324 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676 , Y10T29/49229 , Y10T29/49323
摘要： A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section in communication with the inlet and extending to the outlet. The diffusing section includes a plurality of crenellation features that encourage lateral spreading of cooling air flowing through the cooling hole.
摘要翻译：燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。冷却孔包括位于第一壁表面处的入口，位于第二壁表面处的出口和与入口连通并延伸到出口的扩散部分。扩散部分包括多个刺激特征，其促进流过冷却孔的冷却空气的横向扩散。

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