-
公开(公告)号：US10982597B2
公开(公告)日：2021-04-20
申请号：US16431962
申请日：2019-06-05
Applicant: United Technologies Corporation
Inventor： Brandon T. Slaney , Michael Joseph Murphy , Gary D. Roberge
Abstract: Isolation seals for gas turbine engines are described. The isolation seals include an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end and a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body.
-
公开(公告)号：US20210003485A1
公开(公告)日：2021-01-07
申请号：US16502242
申请日：2019-07-03
Applicant: United Technologies Corporation
Inventor： Joel H. Wagner , Kevin W. Schlichting , Michael Joseph Murphy , Steven H. Zysman , Nigel David Sawyers-Abbott , Andrew A. Consiglio , Charles Waldo Haldeman, IV
IPC: G01N1/22 , G01N23/223
Abstract: An environmental sampling system includes a passage in an aircraft component and a removable collector disposed in the passage. The passage has an inlet at a first region and an outlet at a second region. When the aircraft component is in operation the first region is at a greater pressure than the second region such that air flows through the passage from the inlet to the outlet. The removable collector is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration to predict maintenance activity.
-
公开(公告)号：US10823060B2
公开(公告)日：2020-11-03
申请号：US14974169
申请日：2015-12-18
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Michael Joseph Murphy
IPC: F02C7/047 , F02C7/045 , B64D15/02 , B64D15/04 , F01D25/02 , F02C3/04 , F02C7/36 , F02K3/06 , F04D19/00 , F04D29/32 , F04D29/38 , F04D29/52
Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle.
-
公开(公告)号：US10082081B2
公开(公告)日：2018-09-25
申请号：US14918808
申请日：2015-10-21
Applicant: United Technologies Corporation
Inventor： Michael Joseph Murphy , Sean P. Zamora
CPC classification number: F02C7/18 , F01D25/12 , F01D25/145 , F02K1/46 , F02K1/822 , F04D29/5826 , F05D2220/34 , F05D2220/50 , F05D2260/208 , Y02T50/672 , Y02T50/675
Abstract: A turbine engine cooling arrangement according to an example of the present disclosure includes, among other things, a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, a second airflow source including a second passage adjacent the first passage for conveying a second airflow, and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow. The first airflow and the second airflow stream over the heat exchanger in a parallel radial direction and a parallel axial direction. An engine inlet divides inlet air into the core flow, the first airflow, and the second airflow. A method of providing cooling air is also disclosed.
-
公开(公告)号：US20160194968A1
公开(公告)日：2016-07-07
申请号：US14911889
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael Joseph Murphy , Oleg Petrenko
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.
Abstract translation: 涡扇发动机包括风扇部分。 核心引擎部分驱动风扇部分。 外部机舱围绕风扇部分并且限定了风扇导管的径向外表面。 内部机舱围绕核心发动机部分并且限定风扇管道的径向内表面。 喷嘴设置在外部机舱的终端处，其限定用于旁路气流通过风扇管道的出口区域。 喷嘴包括发散部分前方的收敛部分和大于约12度的发散部分的转动角度。 还公开了一种机舱组件和方法。
-
Patent Agency Ranking
公开(公告)号：US20210158792A1
公开(公告)日：2021-05-27
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: G10K11/168 , B32B3/26 , B32B3/12 , B32B5/02
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：US20200240280A1
公开(公告)日：2020-07-30
申请号：US16260650
申请日：2019-01-29
Applicant: United Technologies Corporation
Inventor： Curtis C. Cowan , Paul W. Duesler , Michael R. Thomas , Michael Joseph Murphy
Abstract: A slider seal assembly for a gas turbine engine, comprising a housing comprising an outer surface and an inner surface, and a recessed opening between the inner surface and the outer surface, wherein the inner surface of the housing includes a flat portion configured to match a receiver on an inner wall of a casing of the gas turbine engine; a seal plate received within the recessed opening and moveable relative to the housing; and a retaining ring configured to retain the seal plate adjacent the housing, the retaining ring includes a plurality of tabs configured to retain the seal plate adjacent the housing.
-
公开(公告)号：US10295420B2
公开(公告)日：2019-05-21
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
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.
-
公开(公告)号：US20170175629A1
公开(公告)日：2017-06-22
申请号：US14974169
申请日：2015-12-18
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Michael Joseph Murphy
CPC classification number: F02C7/047 , F02C3/04 , F02C7/045 , F02C7/36 , F02K3/06 , F04D19/002 , F04D29/325 , F04D29/38 , F04D29/522 , F05D2220/32 , F05D2260/20 , F05D2260/4031
Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle.
-
公开(公告)号：US20160069266A1
公开(公告)日：2016-03-10
申请号：US14918808
申请日：2015-10-21
Applicant: United Technologies Corporation
Inventor： Michael Joseph Murphy , Sean P. Zamora
IPC: F02C7/18
CPC classification number: F02C7/18 , F01D25/12 , F01D25/145 , F02K1/46 , F02K1/822 , F04D29/5826 , F05D2220/34 , F05D2220/50 , F05D2260/208 , Y02T50/672 , Y02T50/675
Abstract: A turbine engine cooling arrangement according to an example of the present disclosure includes, among other things, a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, a second airflow source including a second passage adjacent the first passage for conveying a second airflow, and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow. The first airflow and the second airflow stream over the heat exchanger in a parallel radial direction and a parallel axial direction. An engine inlet divides inlet air into the core flow, the first airflow, and the second airflow. A method of providing cooling air is also disclosed.
Abstract translation: 根据本公开的示例的涡轮发动机冷却装置包括用于接收用于燃烧的芯流的芯通道，第一气流源，其包括邻近所述芯通道的第一通道，用于输送第一气流;第二气流源， 气流源包括邻近第一通道的第二通道，用于传送第二气流;以及热交换器，其与第一通道和第二通道热连接，用于在第一气流和第二气流之间传递热量。 热交换器上的第一气流和第二气流在平行的径向方向和平行的轴向上。 引擎入口将入口空气分成核心流，第一气流和第二气流。 还公开了一种提供冷却空气的方法。
-
-
-
-
-
-
-
-
-
Search Results
17
records
(took 0.026 seconds)
