公开(公告)号：US11480104B2

公开(公告)日：2022-10-25

申请号：US14767396

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

IPC: F02C7/04 ,  F02K3/06 ,  F01D5/02 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04 ,  B64D33/02

Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

公开(公告)号：US20160003145A1

公开(公告)日：2016-01-07

申请号：US14767396

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

IPC: F02C7/04 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04 ,  F01D5/02

Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

Abstract translation: 一种燃气涡轮发动机，其包括在其之间径向提供旁通流动路径的风扇机舱和核心机舱。 风扇机舱具有包括喉部的入口。 入口具有入口最前面的点。 风扇布置在旁路流动路径中并可围绕轴线旋转。 风扇具有从入口最前端凹入的前缘，其轴向方向上的入口长度。 旋转器的旋转器长度从最远点到最前沿。 旋转器长度与入口长度的比例等于或大于约0.5。

公开(公告)号：US20210131303A1

公开(公告)日：2021-05-06

申请号：US16672938

申请日：2019-11-04

Applicant: United Technologies Corporation

Inventor： Dilip Prasad ,  Gavin Hendricks

IPC: F01D11/24 ,  F01D11/18

Abstract: A compressor with negative coefficient of thermal expansion case material comprising a rotor having blades with tips, the case including an inner case comprising a negative coefficient of thermal expansion material, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of air over the negative coefficient of thermal expansion material.

公开(公告)号：US20190309685A1

公开(公告)日：2019-10-10

申请号：US15946251

申请日：2018-04-05

Applicant: United Technologies Corporation

Inventor： William P. Stillman ,  Lane Mikal Thornton ,  Matthew A. Devore ,  Gavin Hendricks

IPC: F02C7/18 ,  F02C3/06 ,  F02C7/30

Abstract: A gas turbine engine includes a compressor section, a combustor section downstream from the compressor section, and a turbine section downstream from the combustor section. The gas turbine engine also includes a water tank with an outlet, and an injector fluidically connected to the outlet of the water tank and to the turbine section. The injector is configured to direct steam from the water tank into the turbine section.

公开(公告)号：US11255214B2

公开(公告)日：2022-02-22

申请号：US16672938

申请日：2019-11-04

Applicant: United Technologies Corporation

Inventor： Dilip Prasad ,  Gavin Hendricks

IPC: F01D11/24 ,  F01D11/18 ,  F01D11/22 ,  F04D29/58

Abstract: A compressor with negative coefficient of thermal expansion case material comprising a rotor having blades with tips, the case including an inner case comprising a negative coefficient of thermal expansion material, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of air over the negative coefficient of thermal expansion material.