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1. 发明申请

US20180209335A1 INTERDIGITATED COUNTER ROTATING TURBINE SYSTEM AND METHOD OF OPERATION 审中-公开
公开(公告)号：US20180209335A1
公开(公告)日：2018-07-26
申请号：US15412197
申请日：2017-01-23
申请人： General Electric Company
发明人： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
IPC分类号： F02C3/04 , F02C7/36 , F02K3/06
CPC分类号： F02C3/04 , F02C3/067 , F02C7/36 , F02K3/06 , F02K3/072 , F05D2220/32 , F05D2260/40311
摘要： The present disclosure is directed to a method of operating a gas turbine engine with an interdigitated turbine section. The engine includes a fan rotor, an intermediate pressure compressor, a high pressure compressor, a combustion section, and a turbine section in serial flow arrangement. The turbine section includes, in serial flow arrangement, a first stage of a low speed turbine rotor, a high speed turbine rotor, a second stage of the low speed turbine rotor, an intermediate speed turbine rotor, and one or more additional stages of the low speed turbine rotor. The low speed turbine rotor is coupled to the fan rotor via a low pressure shaft. The intermediate speed turbine rotor is coupled to the intermediate pressure compressor via an intermediate pressure shaft. The high speed turbine rotor is coupled to the high pressure compressor via a high pressure shaft. The method includes rotating the low speed turbine rotor in a first direction along the circumferential direction; rotating the high speed turbine rotor in a second direction opposite of the first direction along the circumferential direction; and rotating the intermediate speed turbine rotor in the second direction.

2. 发明申请

US20180142619A1 MULTIPLE AXLE-SLEEVE DRIVING BIDIRECTIONAL ROTATING WHEEL-SHAPED FAN TURBINE AND A BUSHING WHEEL-SHAPED FAN COMPRESSOR 审中-公开
公开(公告)号：US20180142619A1
公开(公告)日：2018-05-24
申请号：US15849640
申请日：2017-12-20
申请人： Li SU
发明人： Li SU
IPC分类号： F02C3/067 , F01D5/02 , F04D19/00 , F04D29/32 , F01D5/18 , F01D5/14 , F04D29/54 , F04D29/056 , F02C7/268 , F02C7/36
CPC分类号： F02C3/067 , F01D1/20 , F01D1/26 , F01D5/02 , F01D5/141 , F01D5/18 , F02C7/268 , F02C7/36 , F04D19/005 , F04D25/024 , F04D29/056 , F04D29/321 , F04D29/325 , F04D29/541 , F05D2260/31 , Y02T50/671
摘要： A multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor, including: a working component, a driving component, a structural and installed component and a starting component. A wheel-shaped fan of the turbine drives a corresponding wheel-shaped fan of compressor to rotate through a driving axle sleeve. A rotating direction of the wheel-shaped fan of the turbine is opposite to a rotating direction of a wheel-shaped fan adjacent to the wheel-fan and rotating speed of the plurality of wheel-shaped fan is different. Each of the auxiliary wheel-shape fans is respectively bushed on each of the wheel-shaped fans of the compressor. A turbojet assembled with this disclosure has a high functionality, a light weight, a quick heat dissipation, an excellent anti-surging and a low energy consumption.

3. 发明授权

US09926070B2 Turbine engine having a pair of propellers for an aircraft 有权
公开(公告)号：US09926070B2
公开(公告)日：2018-03-27
申请号：US14612661
申请日：2015-02-03
申请人： SNECMA
发明人： Jean-Christophe Duffet , Tewfik Boudebiza , Augustin Curlier
IPC分类号： F01D13/00 , B64C11/30 , F02C3/067 , F02C6/20 , B64D27/00
CPC分类号： B64C11/306 , B64C11/308 , B64D2027/005 , F02C3/067 , F02C6/206 , Y02T50/66 , Y02T50/672
摘要： An engine includes systems for changing the pitch of propeller blades, a system for an upstream propeller including a linear actuator and a transmission mechanism connecting the actuator to the blades to transform the sliding of the actuator into a rotation of the blades, the upstream propeller including a rotatable housing rigidly connected to a rotatable shaft supported in a static housing of the turbine engine by an upstream bearing and by a downstream bearing. The rotatable housing of the upstream propeller includes a support rigidly connected to the rotatable housing and surrounding the static housing. The actuator is annular and fixed outside to the support, the transfer mechanism includes connecting rods and rotatable radial arms traversing the gaseous flow path, and the downstream bearing is radially located between the static housing and the support.

4. 发明授权

US09909452B2 Device for sealing between the coaxial shafts of a turbomachine 有权
公开(公告)号：US09909452B2
公开(公告)日：2018-03-06
申请号：US14390726
申请日：2013-03-08
申请人： SNECMA
发明人： Arnaud Jean-Marie Pierrot , Serge Rene Morreale
IPC分类号： F01D25/18 , F16J15/40 , F16J15/42 , F16J15/54 , F16J15/34 , F02C3/067 , F02C7/28 , F01D11/02
CPC分类号： F01D25/183 , F01D11/02 , F02C3/067 , F02C7/28 , F05D2240/55 , F16J15/34 , F16J15/40 , F16J15/42 , F16J15/54 , Y10T29/4932
摘要： A device for sealing the coaxial shafts of a turbomachine includes an annular seal able to perform sealing by contact with the outer shaft, and a lubricating device to lubricate the region of contact between the annular seal and the outer shaft.

5. 发明授权

US09897001B2 Compressor areas for high overall pressure ratio gas turbine engine 有权
公开(公告)号：US09897001B2
公开(公告)日：2018-02-20
申请号：US14620395
申请日：2015-02-12
申请人： United Technologies Corporation
发明人： Frederick M. Schwarz , Stephen G. Pixton
IPC分类号： F02C3/107 , F02C3/067 , F02C7/36
CPC分类号： F02C3/107 , F02C3/067 , F02C7/36 , F05D2250/44 , F05D2260/4031
摘要： A gas turbine engine comprises a high pressure turbine rotor, an intermediate pressure turbine rotor and a fan drive turbine rotor. The fan drive turbine rotor drives a fan rotor through a gear reduction. The intermediate pressure rotor drives a low pressure compressor rotor and the high pressure turbine rotor drives a high pressure compressor rotor. A first flow cross-sectional area is between an outer periphery of a hub in the low pressure compressor rotor, and an outer tip of an upstream most blade row of the low pressure compressor rotor. A second flow cross-sectional area is between an outer periphery of a hub in the high pressure compressor rotor, and an outer tip of an upstream most blade row of the high pressure compressor rotor. A ratio of the first and second flow cross-sectional areas is greater than or equal to about 0.12 and less than or equal to about 0.33.

6. 发明授权

US09650954B2 Gas turbine engine with distributed fans 有权
公开(公告)号：US09650954B2
公开(公告)日：2017-05-16
申请号：US14597510
申请日：2015-01-15
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Michael E. McCune , Jesse M. Chandler , Alan H. Epstein , Steven M. O'Flarity , Christopher J. Hanlon , William F. Schneider , Joseph B. Staubach , James A. Kenyon
IPC分类号： F02C3/107 , B64D35/04 , F01D13/00 , F02K3/077 , F02C7/36 , F02C3/06 , F02C3/067 , F02C9/18 , B64D27/18
CPC分类号： F02C3/107 , B64D27/18 , B64D35/04 , F01D13/003 , F02C3/06 , F02C3/067 , F02C7/36 , F02C9/18 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312
摘要： A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.

7. 发明授权

US09494077B2 Gas turbine engine comprising three rotary bodies 有权
标题翻译：包括三个旋转体的燃气涡轮发动机
公开(公告)号：US09494077B2
公开(公告)日：2016-11-15
申请号：US14122777
申请日：2012-05-31
申请人： Philippe Gérard Chanez , Lamine M'Bengue
发明人： Philippe Gérard Chanez , Lamine M'Bengue
IPC分类号： F02C7/04 , F02C3/067 , F02K3/06 , F02K3/072
CPC分类号： F02C7/04 , F02C3/067 , F02K3/06 , F02K3/072 , F05D2220/3213 , F05D2220/323 , Y02T50/671
摘要： A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade.
摘要翻译：一种用于推进飞机的燃气涡轮发动机，包括包括低压涡轮转子叶片的低压旋转体，包括中间涡轮转子叶片的中间旋转体，包括高压涡轮转子叶片的高压旋转体，流过发动机从上游到下游。所述至少一个中间涡轮机转子叶片直接通过低压涡轮转子叶片在下游，以便使由中间涡轮转子叶片偏转的空气流伸直。

8. 发明授权

US09429031B2 Hub for radial housing of a helical ring of a turbomachine with variable-pitch blades and assembly comprising such a hub 有权
标题翻译：具有可变桨距叶片的涡轮机的螺旋环的径向壳体的毂和包括这种轮毂的组件
公开(公告)号：US09429031B2
公开(公告)日：2016-08-30
申请号：US13933538
申请日：2013-07-02
申请人： SNECMA
发明人： Christophe Perdrigeon , Laurent Jablonski , Philippe Gerard Edmond Joly
IPC分类号： F01D7/00 , F01D5/30 , F02C3/067 , F02C6/20
CPC分类号： F01D7/00 , F01D5/3023 , F02C3/067 , F02C6/206 , F05D2220/324 , F05D2220/325 , F05D2260/33 , F05D2260/79
摘要： A helical ring including a polygonal body and a plurality of cylindrical radial housings arranged in the body is provided. Each housing includes a surface adapted to receive a support of a blade of a helix. The surface of each housing is arranged on a radially internal surface of a corresponding hub. Each hub is a separate piece attached to the body of the ring, intended to be received in a radial housing of the body of the ring. The hub includes two projecting pins relative to its external surface to be fastened to the edges of a housing of the annular body, the two projecting pins forming a centering axis.
摘要翻译：提供了包括多边体的螺旋环和布置在主体中的多个圆柱形径向壳体。每个壳体包括适于接收螺旋叶片的支撑件的表面。每个壳体的表面布置在相应毂的径向内表面上。每个轮毂是附接到环的主体的分开的部件，旨在被容纳在环的主体的径向壳体中。轮毂包括相对于其外表面的两个突出销，以将其紧固到环形体的壳体的边缘，两个突出的销形成定心轴。

9. 发明授权

US09387923B2 Gas turbine engine 有权
标题翻译：燃气轮机
公开(公告)号：US09387923B2
公开(公告)日：2016-07-12
申请号：US13914882
申请日：2013-06-11
申请人： ROLLS-ROYCE PLC
发明人： Richard Geoffrey Stretton , Nicholas Howarth
IPC分类号： B64C11/00 , F02C3/067
CPC分类号： B64C11/001 , B64D27/00 , B64D2027/005 , F02C3/067 , F02C7/04 , F02C7/05 , F02K3/025 , F02K3/04 , F05D2220/323 , F05D2220/325 , F05D2240/302 , F05D2250/324 , F05D2250/51 , Y02T50/66 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (122) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (122) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).
摘要翻译：一种在使用中具有轴流动方向（X）的燃气轮机（10）。燃气涡轮发动机（10）包括一个或多个转子级，每个转子级包括至少一个具有根部（122）的转子叶片（120）。燃气涡轮发动机（10）包括相对于轴向流动方向（X）定位在一个或多个转子级的上游的护罩（122）。护罩（122）限定在入口（130）和包括扩散器区域（138）的出口（132）之间延伸的通道（128）。扩散器区域（138）构造成在使用时相对于进入扩散器部分（138）的空气减少离开出口（132）的空气的轴向速度，其中出口（132）定位成使得离开出口（132）的空气）仅基本上指向转子叶片（120）的根部（122）。

10. 发明申请

US20150226117A1 GAS TURBINE ENGINE WITH DISTRIBUTED FANS 有权
标题翻译：具有分布式风机的气体涡轮发动机
公开(公告)号：US20150226117A1
公开(公告)日：2015-08-13
申请号：US14597510
申请日：2015-01-15
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Michael E. McCune , Jesse M. Chandler , Alan H. Epstein , Steven M. O'Flarity , Christopher J. Hanlon , William F. Schneider , Joseph B. Staubach , James A. Kenyon
IPC分类号： F02C3/107 , F02C9/18 , F02C3/067 , F02C3/06
CPC分类号： F02C3/107 , B64D27/18 , B64D35/04 , F01D13/003 , F02C3/06 , F02C3/067 , F02C7/36 , F02C9/18 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312
摘要： A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
摘要翻译：气体发生器具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分。风扇驱动涡轮机位于已经通过至少一个气体发生器涡轮机转子的燃烧产物的路径的下游。风扇驱动涡轮机驱动轴并且轴接合齿轮以驱动至少三个风扇转子。

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