公开(公告)号：US20150122952A1

公开(公告)日：2015-05-07

申请号：US14185045

申请日：2014-02-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Razvan Virgil Florea ,  Claude G. Matalanis ,  Mark B. Stucky

IPC: F02C7/04 ,  B64D27/10 ,  B64D33/02

CPC classification number: F02C7/04 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F05D2220/36 ,  F05D2250/14 ,  Y10T137/0536

Abstract: A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.

Abstract translation: 燃气涡轮发动机具有形成为具有在一半中具有第一椭圆的形状的入口管道和在后半部分中的第二椭圆形状的入口管道。 下半部具有比第一椭圆小的上游端。 入口管道具有限定第二椭圆的表面，其从第一椭圆开始弯曲，使得第二椭圆在中间位置较大。 在进入风扇的入口管道的下游端，第二个椭圆较大。

公开(公告)号：US20190241258A1

公开(公告)日：2019-08-08

申请号：US16316872

申请日：2017-05-12

Applicant: SIKORSKY AIRCRAFT CORPORATION ,  United Technologies Corporation

Inventor： Derek Geiger ,  Seung Bum Kim ,  Claude G. Matalanis ,  Brian E. Wake ,  Patrick Bowles

IPC: B64C27/00 ,  G01B11/16

CPC classification number: B64C27/008 ,  B64C27/473 ,  B64D45/00 ,  F03D17/00 ,  F05B2270/804 ,  G01B11/16

Abstract: A rotor blade deflection sensing system including a rotor blade having a first surface, a second surface, a third surface and a fourth surface. At least two fiber optic sensor arrays are mounted to the rotor blade. At least one of the at least two fiber optic sensor arrays is mounted to one of the first surface, the second surface, the third surface and the fourth surface and another of the at least two fiber optic sensor arrays being mounted to another of the first surface, a second surface, a third surface and a fourth surface. A controller is operatively connected to the at least two fiber optic sensor arrays. The controller determines one or more of a flapwise and an edgewise displacement based on inputs from the at least two fiber optic sensor arrays.

公开(公告)号：US09291101B2

公开(公告)日：2016-03-22

申请号：US14185045

申请日：2014-02-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Razvan Virgil Florea ,  Claude G. Matalanis ,  Mark B. Stucky

IPC: B64D33/02 ,  F02C7/04 ,  B64D27/20

CPC classification number: F02C7/04 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F05D2220/36 ,  F05D2250/14 ,  Y10T137/0536

Abstract: A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.

Abstract translation: 燃气涡轮发动机具有形成为具有在一半中具有第一椭圆的形状的入口管道和在后半部分中的第二椭圆形状的入口管道。 下半部具有比第一椭圆小的上游端。 入口管道具有限定第二椭圆的表面，其从第一椭圆开始弯曲，使得第二椭圆在中间位置较大。 在进入风扇的入口管道的下游端，第二个椭圆较大。