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公开(公告)号：US20200056496A1
公开(公告)日：2020-02-20
申请号：US16526508
申请日：2019-07-30
Applicant: ROLLS-ROYCE plc
Inventor： Clare L. BEWICK , Robert GOULDS
IPC: F01D11/24
Abstract: A turbine-tip clearance control system offtake for a gas turbine engine, comprising: an air input duct in fluid communication with a compressor bleed air outlet, the air input duct comprising an exit aperture, the exit aperture defining an exit flow path for at least a portion of the air flowing in the air input duct during use of the gas turbine engine. The direction of airflow through the exit aperture, during use of the gas turbine engine, has at least a component that is anti-parallel to the direction of airflow in the air input duct in a region of the air input duct adjacent to the exit aperture. A turbine-tip clearance control system, a gas turbine engine for an aircraft and a method of supplying airflow to a turbine-tip clearance control system in a gas turbine engine are also disclosed.
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公开(公告)号：US20210087971A1
公开(公告)日：2021-03-25
申请号：US16943184
申请日：2020-07-30
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Konstantinos EMMANOUIL , Robert GOULDS
Abstract: A supersonic gas turbine engine for an aircraft that comprises a nacelle, a fan, an engine core including a primary duct configured to guide a core airflow through the engine core, a bypass duct extending between the engine core and an engine casing and configured to guide a bypass airflow through the bypass duct, an intake located upstream of the fan, and a tertiary airflow duct extending between the engine casing and the nacelle and configured to guide a tertiary airflow. The intake is configured to extract air from the intake and guide it to the tertiary airflow duct in which the extracted air flows as tertiary airflow. It is provided that at least one heat exchanger is mounted in the tertiary airflow duct.
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公开(公告)号：US20170065986A1
公开(公告)日：2017-03-09
申请号：US15235637
申请日：2016-08-12
Applicant: ROLLS-ROYCE plc
Inventor： Robert GOULDS , Roger A. SUTHERLAND
CPC classification number: B04C3/06 , B01D21/267 , B04C9/00 , B04C2009/002 , F02C7/222 , F05D2220/32 , F23K5/007 , F23K5/18
Abstract: A centrifugal debris separator for removing debris from a gas turbine engine fuel system comprises a debris separator inlet, a debris separator outlet and a separating chamber with a centreline extending in an axial direction and defined by an outer wall formed around the centreline. The separating chamber comprises a separating chamber inlet for receiving fluid, a first separator outlet to the separating chamber, a second separator outlet to the separating chamber provided to the outer wall of the separating chamber and a third separator outlet to the separating chamber defined by a third separator outlet wall formed around the centreline of the separating chamber. The debris separator inlet is fluidly connected to the separating chamber inlet. The debris separator outlet is fluidly connected to the first separator outlet.
Abstract translation: 用于从燃气涡轮发动机燃料系统去除碎屑的离心碎片分离器包括碎片分离器入口，碎片分离器出口和具有沿轴向方向延伸并由围绕中心线形成的外壁限定的中心线的分离室。 分离室包括用于接收流体的分离室入口，到分离室的第一分离器出口，设置到分离室的外壁的分离室的第二分离器出口和分离室的第三分离器出口， 第三分离器出口壁围绕分离室的中心线形成。 碎片分离器入口流体地连接到分离室入口。 碎片分离器出口流体地连接到第一分离器出口。
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公开(公告)号：US20200290741A1
公开(公告)日：2020-09-17
申请号：US16401220
申请日：2019-05-02
Applicant: ROLLS-ROYCE plc
Inventor： Richard PEACE , Robert GOULDS
Abstract: A single-piece gas turbine engine bleed duct for a gas turbine engine including: a main airflow conduit configured to transmit a bleed flow to a location outside the gas turbine engine; a pressure regulating valve for regulating airflow through the main airflow conduit; a first inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the first inlet duct including a non-return valve; and a second inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the second inlet duct including a control valve; wherein each of the first and second inlet ducts are directly connectable to an engine casing of a gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US20190072035A1
公开(公告)日：2019-03-07
申请号：US16104240
申请日：2018-08-17
Applicant: ROLLS-ROYCE plc
Inventor： Richard PEACE , Robert GOULDS
Abstract: The disclosure concerns a heat exchange system or cooling system for a flow machine (10) having a cooling duct (30) with a coolant inlet opening (32) and a closure (34) for selectively opening the inlet opening (32). A component (38) is arranged to be fluid washed by flow along the cooling duct (30). A flow injector (40) is spaced from the closure (34) along the cooling duct (30) and oriented to inject flow into the cooling duct (30) in a direction that creates a negative fluid pressure downstream of the closure (34), wherein the closure (34) is openable in response to said negative pressure. The component may be a heat exchanger (38). The flow injector (40) may be fed by a compressor (14, 15) of the flow machine (10).
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公开(公告)号：US20200291866A1
公开(公告)日：2020-09-17
申请号：US16401225
申请日：2019-05-02
Applicant: ROLLS-ROYCE plc
Inventor： Richard PEACE , Robert GOULDS
Abstract: A gas turbine engine comprising: a compressor; a first turbine; and a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; wherein the first compressor bleed valve is configured to release bleed air to a downstream location in the engine, the downstream location being downstream of the first turbine; wherein the first compressor bleed valve is configured to open wherein the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor.
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公开(公告)号：US20190242264A1
公开(公告)日：2019-08-08
申请号：US16256303
申请日：2019-01-24
Applicant: ROLLS-ROYCE plc
Inventor： Robert GOULDS
CPC classification number: F01D9/06 , F01D9/041 , F01D9/065 , F01D25/162 , F01D25/30 , F02C9/18 , F02K3/06 , F05D2220/323 , F05D2240/12 , F05D2260/606
Abstract: A tail bearing housing of a turbomachine comprises an inner casing and an outer casing concentrically arranged along a longitudinal axis, and a plurality of vanes having a leading edge, a trailing edge, a first wall extending from the leading edge to the trailing edge and a second wall extending from the leading edge to the trailing edge, the first wall and the second wall defining an aerofoil, the vanes being connected at a first end to the outer casing and at a second end to the inner casing. At least one vane of the plurality of vanes is a vent vane comprising a first aperture arranged in the first end and a second aperture arranged in the aerofoil, the second aperture being configured to be in fluid communication with the first aperture through an inner cavity to vent bleed air.
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公开(公告)号：US20180254580A1
公开(公告)日：2018-09-06
申请号：US15912693
申请日：2018-03-06
Applicant: ROLLS-ROYCE plc
Inventor： Robert GOULDS
IPC: H01R13/533 , H01R9/22 , H01R9/24 , H01R4/28
CPC classification number: H01R13/533 , H01R4/28 , H01R4/304 , H01R9/223 , H01R9/2416 , H01R11/12
Abstract: An electrical connector arrangement comprises a metal mounting bracket for securing the arrangement to a structure; an electrically insulating mounting block abutting the mounting bracket; a clamp to secure an electrical cable to the mounting block, the electrical cable comprising a plurality of electrical conductors; and a plurality of spaced-apart terminals to accommodate the respective electrical conductors.
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公开(公告)号：US20150101331A1
公开(公告)日：2015-04-16
申请号：US14487835
申请日：2014-09-16
Applicant: ROLLS-ROYCE PLC
Inventor： Robert GOULDS , Brian Richard LACE , Richard PEACE
CPC classification number: F02C7/32 , F01D25/08 , F01D25/12 , F01D25/14 , F01D25/145 , F02C3/14 , F02C6/04 , F02C6/06 , F02C6/08 , F02C7/12 , F02C7/125 , F02C7/18 , F02C7/24 , F02C7/25 , F02C7/28 , F05D2260/20 , F05D2260/50 , F16C1/10 , F16C1/103 , F16C1/262 , F16C2360/23
Abstract: A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device.
Abstract translation: 一种具有防火墙的燃气涡轮发动机，其被配置为在所述燃气涡轮发动机中的第一区域和第二区域之间提供耐火屏障，当所述燃气涡轮发动机正在使用时，所述第二区域比所述第一区域热。 燃气轮机还具有致动器，该致动器位于第一区域中并被构造成在被操作时产生机械力，位于第二区域中的致动装置，并被构造成由机械力和机械力传递 装置，其通过防火墙中的孔从致动器延伸到可致动装置。 机械力传递装置构造成当致动器被操作时，通过将由致动器产生的机械力传递到可致动装置来致动可致动装置。
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