中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

45 records (took 0.015 seconds)

    Diversion Of Fan Air To Provide Cooling Air For Gas Turbine Engine
    31.
    发明申请
    Diversion Of Fan Air To Provide Cooling Air For Gas Turbine Engine 审中-公开
    风机空气转向为燃气轮机提供冷却空气

    公开(公告)号：US20160258359A1

    公开(公告)日：2016-09-08

    申请号：US14635366

    申请日：2015-03-02

    Applicant: United Technologies Corporation

    Inventor： Daniel Bernard Kupratis ,  Anthony R. Bifulco

    IPC: F02C7/143 ,  F02C7/18

    CPC classification number: F02C7/143 ,  F01D9/041 ,  F02C3/13 ,  F02C3/32 ,  F02C7/10 ,  F02C7/12 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2260/14 ,  F05D2260/205 ,  F05D2260/232 ,  F05D2260/601 ,  Y02T50/676

    Abstract: A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.

    Abstract translation: 燃气涡轮发动机部分包括多个间隔开的转子级，在间隔开的转子级之间具有静态导向叶片。 静态导向叶片向通向下游一个间隔开的转子级的空气提供涡流，以及围绕间隔开的转子级的外壳。 分流器将空气的一部分径向向外转移穿过外部壳体，并穿过至少一个热交换器。 转向的空气通过外部壳体径向向内返回到管道中，并且朝向下游的一个间隔开的转子级排出。

    Cooling System with a Bearing Compartment Bypass
    32.
    发明申请
    Cooling System with a Bearing Compartment Bypass 有权
    带有轴承舱的冷却系统旁路

    公开(公告)号：US20150285147A1

    公开(公告)日：2015-10-08

    申请号：US14594663

    申请日：2015-01-12

    Applicant: United Technologies Corporation

    Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/187 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/12 ,  F01D25/125 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/221 ,  F05D2260/232 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

    Abstract translation: 公开了一种用于向燃气涡轮发动机的涡轮部分提供缓冲冷却的冷却空气的冷却系统。 冷却系统可以包括构造成将冷却空气朝向涡轮机部分传送的第一管道，被配置为冷却从第一管道转向以提供缓冲空气的排出气流的热交换器，以及配置成引导至少一部分 的缓冲空气通过绕过燃气涡轮发动机的轴承室的至少一个通道。 冷却系统还可以包括歧管，其配置成允许从第一导管排出的冷却空气和离开旁路导管的缓冲空气混合并提供缓冲冷却的冷却空气;以及喷嘴组件，其配置成将缓冲冷却的冷却空气输送到 涡轮段。

    Acoustic liner with obliquely angled slots
    33.
    发明授权
    Acoustic liner with obliquely angled slots 有权

    公开(公告)号：US11480106B2

    公开(公告)日：2022-10-25

    申请号：US16411728

    申请日：2019-05-14

    Applicant: United Technologies Corporation

    Inventor： Bruce L. Morin ,  Anthony R. Bifulco

    IPC: F02C7/24

    Abstract: An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.

    Assembly alignment handling damage tolerant spline
    35.
    发明授权
    Assembly alignment handling damage tolerant spline 有权

    公开(公告)号：US10975915B2

    公开(公告)日：2021-04-13

    申请号：US15864292

    申请日：2018-01-08

    Applicant: United Technologies Corporation

    Inventor： Charles Mayaka ,  Anthony R. Bifulco

    IPC: F16D1/10 ,  F01D5/02 ,  F16C3/02 ,  F16D1/02

    Abstract: Aspects of the disclosure are directed to a gas turbine engine shaft, having an outer circumferential surface that circumscribes a central axis. The gas turbine engine shaft may comprise a plurality of splines extending along a portion of the outer circumferential surface, where each of the plurality of splines comprises an axial face that tapers from the outer circumferential surface to a spline top surface and includes a curved chamfered surface at a radially distal end of the axial face. The plurality of splines may further comprise a first sidewall and a second sidewall separated by a first spline width distance along the outer circumferential surface, where the first and second sidewalls taper inwardly from the outer circumferential surface to a second spline width along the spline top surface where the second spline width distance is less than the first spline width distance.

    Assembly for releasable locking of a spinner or nosecone to an engine structure
    36.
    发明授权
    Assembly for releasable locking of a spinner or nosecone to an engine structure 有权

    公开(公告)号：US10808613B2

    公开(公告)日：2020-10-20

    申请号：US15865998

    申请日：2018-01-09

    Applicant: United Technologies Corporation

    Inventor： Anthony R. Bifulco ,  Joseph M. Wilson ,  Jason B. Hickman

    IPC: F02C7/04 ,  F01D5/02 ,  F01D5/06 ,  F02K3/06 ,  B64C11/14 ,  F04D29/32

    Abstract: Disclosed is an assembly for a gas turbine engine, the assembly includes: a spinner or nosecone comprising a threaded rear portion, an engine structure comprising a threaded front portion, the nosecone being threadingly connected to the engine structure, wherein rotation of the spinner or nosecone about the engine structure in a first direction secures the spinner or nosecone to the engine structure and rotation of the spinner or nosecone about the engine structure in a second direction releases the spinner or nosecone from the engine structure; and a lock ring slidingly connected to the engine structure to slide between: a forward position to engage the spinner or nosecone and block rotation of the spinner or nosecone in the second direction, and a rearward position, where the lock ring is spaced from the spinner or nosecone.

    Stator segment circumferential gap seal
    38.
    发明授权
    Stator segment circumferential gap seal 有权

    公开(公告)号：US10648479B2

    公开(公告)日：2020-05-12

    申请号：US15797577

    申请日：2017-10-30

    Applicant: United Technologies Corporation

    Inventor： Colin G. Amadon ,  Anthony R. Bifulco

    IPC: F04D29/08 ,  F01D9/04 ,  F01D11/00 ,  F04D29/54

    Abstract: A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.

Patent Agency Ranking