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公开(公告)号：US20230323810A1
公开(公告)日：2023-10-12
申请号：US18184008
申请日：2023-03-15
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY , Nicholas HOWARTH , Richard G. STRETTON
CPC classification number: F02C6/08 , B64D13/06 , B64D2013/0618 , F05D2260/205 , F05D2220/323
Abstract: There is provided a gas turbine engine comprising a blower system for supplying pressurised air to an airframe via an airframe port. The blower system comprises a compressor configured to receive air from a bypass duct or a core of the gas turbine engine and to discharge compressed air into a delivery line extending from the compressor to the airframe port. The blower system also comprises a heat exchanger configured to transfer heat from the compressed air to a coolant and a valve arrangement configured to switch between operation of the blower system in a baseline mode and a cooling mode, the valve arrangement being configured to: selectively divert the compressed air within the delivery line to the heat exchanger for operation in the cooling mode; and/or selectively provide the coolant to the heat exchanger for operation in the cooling mode.
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公开(公告)号：US20230373635A1
公开(公告)日：2023-11-23
申请号：US18163143
申请日：2023-02-01
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY
CPC classification number: B64D13/02 , F02C6/08 , F05D2220/323
Abstract: There is provided an air pressurisation system comprising: a blower compressor coupled to a spool of a gas turbine engine and configured to receive inlet air from a bypass duct of the gas turbine engine; an air treatment apparatus to mix air from the air cycle line with air from the bypass line to control a temperature of air for discharge to an airframe system; and a core bleed line configured to provide a second inlet flow of air from a compressor of the gas turbine engine to the air treatment apparatus in an augmented air supply mode of the air pressurisation system; wherein the core bleed line is configured to provide the second inlet flow of air directly to the bypass line or mix the second inlet flow of air with air from the blower compressor upstream of the bypass line.
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公开(公告)号：US20230242260A1
公开(公告)日：2023-08-03
申请号：US18155351
申请日：2023-01-17
Applicant: ROLLS-ROYCE plc , Rolls-Royce Corporation
Inventor： Christopher A. MURRAY , Nicholas HOWARTH , Daniel SWAIN , Ian J. BOUSFIELD
CPC classification number: B64D13/06 , F04D25/04 , F02C7/32 , B64D2013/0603
Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.
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公开(公告)号：US20240317406A1
公开(公告)日：2024-09-26
申请号：US18609241
申请日：2024-03-19
Applicant: Rolls-Royce plc
Inventor： Christopher A. MURRAY , Nicholas HOWARTH
CPC classification number: B64D13/04 , F01D11/04 , F02C7/06 , F02C7/28 , F05D2240/55 , F05D2260/98
Abstract: A compressor of an aircraft air pressurization system comprises: a rotor configured to be mechanically coupled to a spool of a gas turbine engine; an oil-lubricated bearing for supporting rotation of the rotor, wherein the oil-lubricated bearing is disposed within a bearing chamber; and a seal assembly for restricting oil from the bearing chamber from reaching an inlet of the blower compressor, wherein the seal assembly comprises: a seal disposed between the bearing chamber and an air buffer chamber; an air buffer inlet configured to receive a flow of pressurized air into the air buffer chamber; and an air buffer outlet configured to allow the flow of pressurized air to be exhausted from the air buffer chamber together with oil from the bearing chamber that has passed through the seal and become entrained within the flow of pressurized air.
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公开(公告)号：US20240317405A1
公开(公告)日：2024-09-26
申请号：US18609248
申请日：2024-03-19
Applicant: Rolls-Royce plc
Inventor： Christopher A. MURRAY
Abstract: A compressor of an aircraft air pressurization system comprises: a rotor configured to be mechanically coupled to a spool of a gas turbine engine; and a housing, wherein the rotor is supported for rotation within the housing about a rotor axis, wherein the rotor and housing define a primary air channel extending between an inlet of the blower compressor for receiving the inlet flow of air and an outlet from which the blower compressor is configured to output pressurized air to a delivery line. The housing further comprises a bleed opening in a wall of the housing between the inlet and the outlet, the bleed opening extending circumferentially about the rotor axis, wherein the bleed opening is for contaminants within the inlet flow of air, which have been driven outward due to the rotation of the rotor, to be bled out of the blower compressor.
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Patent Agency Ranking
公开(公告)号：US20230278711A1
公开(公告)日：2023-09-07
申请号：US18171491
申请日：2023-02-20
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY , Mark J E BELLIS
CPC classification number: B64D13/02 , F02C6/06 , F02C7/32 , F05D2220/323 , F05D2260/40 , F05D2260/60
Abstract: A blower system for a gas turbine engine comprising: a rotor assembly, an airframe port and a routing-control valve. The rotor assembly is configured to be mechanically coupled to a spool of the gas turbine engine. The airframe port is configured to receive and discharge air to an airframe system. The routing-control valve comprises: a primary channel for bidirectional flow between the rotor assembly and the airframe port; a primary valve member configured to open and close the primary channel; and an auxiliary channel branched from the primary channel. The auxiliary channel is configured to bypass the primary valve member for: a first auxiliary flow from the airframe port to the rotor assembly; or a second auxiliary flow for purging air from the rotor assembly to a discharge port. The blower system is configured to operate in an engine drive mode and in a blower mode.
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公开(公告)号：US20250066024A1
公开(公告)日：2025-02-27
申请号：US18795552
申请日：2024-08-06
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY
Abstract: There is provided an air pressurisation system for an aircraft, the air pressurisation system comprising: a transmission for driving a rotor of a blower compressor for the air pressurisation system, wherein the transmission comprises: a first input configured to receive drive from a spool of a gas turbine engine; a second input; and an output configured to drive to the rotor of the blower compressor, wherein a speed of the output is determined by a function of speeds of the first and second inputs; and a brake coupled to the second input, wherein the brake is operable to engage and brake the transmission at the second input, in order to fix a transmission ratio of the transmission between the first input and the output.
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公开(公告)号：US20230193776A1
公开(公告)日：2023-06-22
申请号：US17990488
申请日：2022-11-18
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY
CPC classification number: F01D15/08 , F01D15/10 , F05D2220/323 , F05D2260/4023 , F05D2260/60
Abstract: A variable speed pumping system, for an aircraft, comprising: a first electrical machine, the first electrical machine comprising an electrical machine rotor shaft mechanically connected to an engine of the aircraft and electrical machine stator coils; an electric pump motor-generator, the electric pump motor-generator comprising an electric pump rotor shaft mechanically connected to the electrical machine rotor shaft via a one way drive arrangement and electric pump stator coils; wherein the electric pump rotor shaft is mechanically connected to a fluid pumping system.
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公开(公告)号：US20230184131A1
公开(公告)日：2023-06-15
申请号：US17988472
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY
IPC: F01D17/16
CPC classification number: F01D17/16 , F05D2220/32
Abstract: A blower assembly for providing air to an airframe system, including a rotor configured to be mechanically coupled to a spool of a gas turbine engine and a flow modifier configured to receive and/or direct flow to the rotor; wherein the blower assembly is configured to permit relative movement between the rotor and the flow modifier to move between: a compressor configuration in which the rotor is configured to be driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system; and a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate.
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公开(公告)号：US20250081418A1
公开(公告)日：2025-03-06
申请号：US18807248
申请日：2024-08-16
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A. MURRAY
Abstract: A power electronics cooling assembly with a housing for power electronics. The housing is mountable to a bulkhead for separating a fire zone from a non-fire zone of a gas turbine engine. In the non-fire zone, one or more ducts extend from the bulkhead to the housing. A fluid supply and return pipes extend through the one or more ducts from the bulkhead to the housing. The fluid supply and return pipes are for carrying an ignitable fluid coolant. A heat exchange structure arranged within the housing is configured to receive the ignitable fluid coolant from the fluid supply pipe, facilitate transfer of heat from the power electronics within the housing to the ignitable fluid coolant, and output the ignitable fluid coolant to the fluid return pipe. A system, gas turbine engine assembly and an aircraft comprising the power electronics cooling assembly are also provided.
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