公开(公告)号：US09976484B2

公开(公告)日：2018-05-22

申请号：US14981229

申请日：2015-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott

IPC: F02C7/12 ,  F02K3/06 ,  F02C3/04 ,  F02C7/25 ,  F02C7/28 ,  B64D29/00 ,  F01D25/14

CPC classification number: F02C7/12 ,  B64D29/00 ,  F01D25/145 ,  F02C3/04 ,  F02C7/25 ,  F02C7/28 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/15 ,  F05D2240/91 ,  F05D2260/605 ,  F05D2260/608 ,  Y02T50/671 ,  Y02T50/675

Abstract: A core compartment ventilation device is provided. The core compartment ventilation device comprises a fireproof sealing member for substantially sealing a core compartment in a nacelle for a gas turbine engine and a chimney configured to be in fluid communication with the fireproof sealing member for conducting hot air from the core compartment to the external atmosphere via the fireproof sealing member. A gas turbine engine and nacelle including the core compartment ventilation device are also provided.

公开(公告)号：US09925732B2

公开(公告)日：2018-03-27

申请号：US14459930

申请日：2014-08-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott

IPC: B29D99/00 ,  F02K1/72 ,  B29L31/08

CPC classification number: B29D99/0025 ,  B29L2031/082 ,  F02K1/72 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2240/129 ,  F05D2300/143 ,  F05D2300/43 ,  F05D2300/433 ,  F05D2300/611 ,  Y02T50/672 ,  Y10T29/49323

Abstract: A thrust reverser cascade for a gas turbine engine is disclosed. The thrust reverser cascade may comprise a plurality of turning vanes. One or more of the turning vanes may comprise a core formed from a polymer and a metallic coating applied to at least a portion of an outer surface of the core. The metallic coating may comprise nickel or a nickel alloy.

公开(公告)号：US20170298871A1

公开(公告)日：2017-10-19

申请号：US15131955

申请日：2016-04-18

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Priscilla Chin

IPC: F02K1/76 ,  F01D25/24 ,  F02K1/62

CPC classification number: F02K1/763 ,  F01D25/24 ,  F02K1/625 ,  F02K1/72 ,  F02K1/766 ,  F02K1/80 ,  F05D2220/32 ,  F05D2260/30 ,  Y02T50/672

Abstract: Systems for thrust reverser link arm connections are described herein. A fitting for a thrust reverser link arm may comprise a base plate configured to be fastened to a proximal surface of an inner fixed structure (IFS), a first wall extending orthogonally from the base plate, a pin extending orthogonally from the first wall, a second wall extending orthogonally from the base plate, a removable member, a first column located between the first wall and the second wall, and a second column located between the first wall and the second wall. The removable member may surround at least a portion of the pin. The removable member may be removed from a radially outward side of the IFS.

公开(公告)号：US20170297730A1

公开(公告)日：2017-10-19

申请号：US15131933

申请日：2016-04-18

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott

IPC: B64D29/06 ,  B64D27/10 ,  F02K1/70 ,  F02K1/76

CPC classification number: B64D29/06 ,  B64D27/10 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F05D2260/31 ,  F05D2260/50 ,  F16C11/045 ,  F16C2360/23 ,  Y02T50/672

Abstract: Systems for thrust reverser link arm connections are described herein. A linkage system for a nacelle may comprise a thrust reverser link arm and a fitting. The fitting may comprise a base plate configured to be fastened to a proximal surface of an inner fixed structure (IFS), a first wall extending orthogonally from the base plate, a second wall extending orthogonally from the base plate, and a pin extending orthogonally from the first wall and extending orthogonally from the second wall. A first end of the thrust reverser link arm may comprise a removable member, the removable member having an inner surface comprising a semi-circle, the inner surface configured to seat against the pin. The removable member may be removed from the linkage system from a radially outward side of the IFS.

公开(公告)号：US20160032832A1

公开(公告)日：2016-02-04

申请号：US14766825

申请日：2014-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Gilson ,  Nigel David Sawyers-Abbott

IPC: F02C7/045 ,  F01D25/24 ,  F01D5/02

CPC classification number: F02C7/045 ,  F01D5/02 ,  F01D25/24 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/963

Abstract: A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature.

Abstract translation: 用于燃气涡轮发动机的风扇部分包括可操作地安装到风扇轮毂的风扇轮毂和鼻锥部分。 鼻锥部分包括噪声衰减特征。