公开(公告)号：US20200080477A1

公开(公告)日：2020-03-12

申请号：US16124506

申请日：2018-09-07

Applicant: United Technologies Corporation

Inventor： Michael Joseph Murphy

IPC: F02C7/057 ,  B64D33/02 ,  B64D29/04 ,  B64D27/20 ,  F02C9/22 ,  F02K3/06

Abstract: A gas turbine engine assembly according to an exemplary embodiment of this disclosure includes, among other possible things, a plurality of fan blades rotatable about a fan rotation axis; a fan nacelle at least partially surrounding the plurality of fan blades, the fan nacelle defining an inlet; at least one sensor positioned forward of the fan nacelle, the at least one sensor generating a signal indicative of an airflow condition entering the inlet; an effector that is actuatable to accommodate distortions in inlet airflow; and a controller receiving the signal from the at least one sensor and determining an inlet distortion condition corresponding to the signal indicative of an airflow condition and actuating the effector based on the identified inlet distortion condition.

公开(公告)号：US10393065B2

公开(公告)日：2019-08-27

申请号：US15808254

申请日：2017-11-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael Joseph Murphy

IPC: F02K1/09 ,  F02K3/06

Abstract: A variable nozzle apparatus may include a radially inward structure and a radially outward structure circumscribing the radially inward structure. An annular flow channel is defined between the radially inward structure and the radially outward structure. One of the radially inward structure and the radially outward structure includes a static portion and a moveable portion. The moveable portion may be to the static portion via helical threads and may thus configured to rotate circumferentially and translate axially relative to the static portion. Movement of the moveable portion relative to the static portion may change a radial dimension of the annular flow channel.

公开(公告)号：US20150052907A1

公开(公告)日：2015-02-26

申请号：US14533611

申请日：2014-11-05

Applicant: United Technologies Corporation

Inventor： Michael Joseph Murphy

IPC: F02C7/14 ,  F01D25/12

CPC classification number: F02C7/14 ,  F01D17/085 ,  F01D17/148 ,  F01D25/12 ,  F02C7/185 ,  F02C9/18 ,  F02K3/075 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2270/303 ,  Y02T50/675

Abstract: A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an Environmental Control System (ECS) pre-cooler or an Air Oil Cooler (AOC) “peaker” through a common inlet.

Abstract translation: 一种用于燃气涡轮发动机的热管理方法，包括选择性地定位阀，以通过公共入口将旁路流传递到环境控制系统（ECS）预冷器或空气油冷却器（AOC）“燃烧器”中。

公开(公告)号：US12109793B2

公开(公告)日：2024-10-08

申请号：US16690519

申请日：2019-11-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian Kenneth Holland ,  Bruce L Morin ,  Michael Joseph Murphy ,  Steven H. Zysman

IPC: B32B38/10 ,  B24C1/04 ,  B32B3/12 ,  B32B3/26 ,  B32B5/02 ,  B32B37/14 ,  B32B37/18 ,  G10K11/168

CPC classification number: B32B38/10 ,  B24C1/045 ,  B32B3/12 ,  B32B3/266 ,  B32B5/02 ,  B32B37/146 ,  B32B37/18 ,  G10K11/168 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2305/02 ,  B32B2315/00 ,  B32B2419/04

Abstract: A face skin for an acoustic panel may comprise a sheet defining a first surface and a second surface. A plurality of slots may be formed through the face skin using abrasive blasting. Each slot of the plurality of slots may comprise a first semi-circular wall and a second semi-circular wall opposite the first semi-circular wall.

公开(公告)号：US10550704B2

公开(公告)日：2020-02-04

申请号：US14911889

申请日：2014-08-22

Applicant: United Technologies Corporation

Inventor： Michael Joseph Murphy ,  Oleg Petrenko

IPC: F02K1/82 ,  F01D9/02 ,  F02K1/78 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  F02K3/04

Abstract: A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed.

公开(公告)号：US09863318B2

公开(公告)日：2018-01-09

申请号：US14533611

申请日：2014-11-05

Applicant: United Technologies Corporation

Inventor： Michael Joseph Murphy

IPC: F02C1/00 ,  F02C7/14 ,  F01D17/08 ,  F01D17/14 ,  F02K3/075 ,  F02C9/18 ,  F01D25/12 ,  F02C7/18

CPC classification number: F02C7/14 ,  F01D17/085 ,  F01D17/148 ,  F01D25/12 ,  F02C7/185 ,  F02C9/18 ,  F02K3/075 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2270/303 ,  Y02T50/675

Abstract: A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an Environmental Control System (ECS) pre-cooler or an Air Oil Cooler (AOC) “peaker” through a common inlet.

公开(公告)号：US20170292882A1

公开(公告)日：2017-10-12

申请号：US15095199

申请日：2016-04-11

Applicant: United Technologies Corporation

Inventor： Joshua V. Wood ,  Michael Joseph Murphy ,  Justin R. Urban ,  Robert E. Malecki ,  William W. Rice ,  David W. Lamarre

IPC: G01L5/13 ,  B64D27/10 ,  G01M15/14 ,  B64C7/02

CPC classification number: G01L5/133 ,  B64C7/02 ,  B64D27/10 ,  F01D21/003 ,  F02K1/15 ,  F05D2260/50 ,  F05D2270/80 ,  F05D2270/821 ,  G01M15/14

Abstract: A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.