公开(公告)号：JP2011132963A

公开(公告)日：2011-07-07

申请号：JP2011083273

申请日：2011-04-05

Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

Inventor： LORD WESLEY K ,  SHARMA OM P ,  DYE CHRISTOPHER ,  SUCIU GABRIEL L

IPC: F04D29/56

CPC classification number: F01D5/146 ,  F01D5/148 ,  F01D17/162 ,  F04D29/563 ,  F05B2240/311 ,  F05D2240/12 ,  Y02T50/673

Abstract: PROBLEM TO BE SOLVED: To provide an inlet guide vane flap with increased partial-speed operability and flutter margin, thus avoiding fan rotor mistuning at particular operational conditions. SOLUTION: A variable-shape inlet guide vane (IGV) system 46 includes the variable-shape inlet guide vane flap 48 provided with a flexible part 64 that enables the desired spanwise distribution of axial velocities Cx, α, and β at an inlet of the fan rotor 30. The flexible part 64 is formed of a flexible material such as silicone rubber combined with internal reinforcing fibers or filaments. The form of the flap 48 is not symmetric, but twisted during actuation from the maximum opening position to the maximum closed position. COPYRIGHT: (C)2011,JPO&INPIT

Abstract translation: 要解决的问题：提供具有增加的部分速度可操作性和颤振余量的入口导向叶片翼片，从而避免在特定操作条件下风扇转子失谐。 解决方案：可变形入口引导叶片（IGV）系统46包括设置有柔性部分64的可变形入口导向叶片翼片48，其能够在轴向速度Cx，α和β处产生期望的翼展方向分布 风扇转子30的入口。柔性部分64由诸如与内部增强纤维或细丝组合的硅橡胶的柔性材料形成。 翼片48的形状不是对称的，而是在从最大打开位置到最大关闭位置的致动期间扭转。 版权所有（C）2011，JPO＆INPIT

公开(公告)号：WO2013176727A3

公开(公告)日：2014-02-20

申请号：PCT/US2013029003

申请日：2013-03-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DASGUPTA ARINDAM ,  SHARMA OM P

IPC: F02C7/143 ,  F02C7/12

CPC classification number: F02C7/143 ,  B64D15/02 ,  B64D33/10 ,  B64D41/00 ,  F01D25/02 ,  F02C7/18 ,  F02C7/224 ,  F02K3/06 ,  F02K3/115 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

Abstract: A turbine engine has a fan comprising a duct and supporting struts, a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. A cooling circuit is located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor, and includes at least intercooler configured to transfer heat from inlet air to a secondary fluid heat sink.

Abstract translation: 涡轮发动机具有包括管道和支撑支柱的风扇，构造成对入口空气加压的第一压缩机和被构造成进一步加压入口空气的第二压缩机。 冷却回路被定位成在入口空气被第一压缩机加压之后并且在入口空气被第二压缩机进一步加压之前冷却入口空气，并且至少包括中间冷却器，其构造成将热量从入口空气传递到次级流体热 水槽。

公开(公告)号：WO9614494A3

公开(公告)日：1997-02-13

申请号：PCT/US9513402

申请日：1995-10-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SHARMA OM P ,  STAUBACH JOSEPH BRENT ,  STETSON GARY

IPC: F01D5/14 ,  F01D5/20

CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D5/145

Abstract: A rotor blade (24) for a gas turbine engine includes a bowed surface (43) on a tip region (40) of the suction side (32) thereof. The curvature of the bowed surface (43) progressively increases toward the tip (36) of the blade (24). The bowed surface (43) results in a reduction of tip leakage through a tip clearance (50) from the pressure side (30) to the suction side (32) of the blade (24) and reduces mixing loss due to tip leakage.

公开(公告)号：AU2007200773A1

公开(公告)日：2008-09-04

申请号：AU2007200773

申请日：2007-02-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHIN KAR D ,  SHARMA OM P ,  PIETRASZKIEWICS EDWARD F

IPC: F01D5/18 ,  F01D5/08

Abstract: A turbine blade (14) is cooled by cooling air that flows through a radial cooling channel (40). The turbine blade (14) includes a root (20) and an airfoil (22). The flow of cooling air into the cooling channel (40) is limited by a pre-meter orifice (52) to provide a reduced pressure within the cooling channel (40). The pressure drop results from the cross-sectional area (A O ) of the pre-meter orifice (52) being less than the cross-sectional area (A C ) of the adjacent cooling channel (40). After flowing through the cooling channel (40), the cooling air exits the cooling channel (40) through a film hole (38) to form a film layer over the airfoil (22) to cool and insulate the turbine blade (14).

公开(公告)号：SG135099A1

公开(公告)日：2007-09-28

申请号：SG2007007198

申请日：2007-01-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PIETRASZKIEWICZ EDWARD F ,  CHIN KAR D ,  SHARMA OM P

Abstract: A turbine blade is cooled by cooling air that flows through a radial cooling channel. The turbine blade includes a root and an airfoil. The flow of cooling air into the cooling channel is limited by a pre-meter orifice to provide a reduced pressure within the cooling channel. The pressure drop results from the cross-sectional area of the pre-meter orifice being less than the cross-sectional area of the adjacent cooling channel. After flowing through the cooling channel, the cooling air exits the cooling channel through a film hole to form a film layer over the airfoil to cool and insulate the turbine blade.

公开(公告)号：EP2798185A4

公开(公告)日：2015-08-26

申请号：EP12863767

申请日：2012-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SHARMA OM P ,  BLAIR MICHAEL F

IPC: F02K3/00 ,  F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F02K3/08 ,  F03D11/00

CPC classification number: F02C3/14 ,  F01D1/04 ,  F01D5/142 ,  F02C7/18 ,  F05D2220/3212 ,  F05D2240/12 ,  F05D2260/202

公开(公告)号：EP2825749A4

公开(公告)日：2015-11-04

申请号：EP13793845

申请日：2013-03-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DASGUPTA ARINDAM ,  SHARMA OM P

IPC: F02C7/143 ,  B64D15/02 ,  F01D25/02 ,  F02C7/12 ,  F02C7/18 ,  F02C7/224 ,  F02K3/06 ,  F02K3/115

CPC classification number: F02C7/143 ,  B64D15/02 ,  B64D33/10 ,  B64D41/00 ,  F01D25/02 ,  F02C7/18 ,  F02C7/224 ,  F02K3/06 ,  F02K3/115 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

公开(公告)号：EP2798174A4

公开(公告)日：2015-08-19

申请号：EP12871456

申请日：2012-12-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SHARMA OM P ,  BLAIR MICHAEL F

IPC: F02C3/14 ,  F01D5/06 ,  F01D5/18

CPC classification number: F01D5/06 ,  F01D5/186 ,  F05D2260/231

Abstract: An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five.

Abstract translation: 示例性的燃气涡轮发动机包括涡轮机部分，其可操作以将旋转能量赋予压缩机部分。 涡轮部分至少包括低压涡轮机和高压涡轮机，而低压涡轮机中的多个级数为三级至五级。