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公开(公告)号：US12172757B2
公开(公告)日：2024-12-24
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
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：US11873731B2
公开(公告)日：2024-01-16
申请号：US18114583
申请日：2023-02-27
Applicant: ROLLS-ROYCE plc
Inventor： Ian J. Bousfield , Duncan A. Macdougall
CPC classification number: F01D5/141 , F01D5/142 , F02C7/05 , F02C7/36 , F05D2220/32 , F05D2240/24 , F05D2240/303 , F05D2260/94
Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.
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公开(公告)号：US20240426216A1
公开(公告)日：2024-12-26
申请号：US18825241
申请日：2024-09-05
Applicant: ROLLS-ROYCE plc
Inventor： Ian J. Bousfield , Duncan A. Macdougall
Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.
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公开(公告)号：US12110804B2
公开(公告)日：2024-10-08
申请号：US18524490
申请日：2023-11-30
Applicant: ROLLS-ROYCE plc
Inventor： Ian J. Bousfield , Duncan A. Macdougall
CPC classification number: F01D5/141 , F01D5/142 , F02C7/05 , F02C7/36 , F05D2220/32 , F05D2240/24 , F05D2240/303 , F05D2260/94
Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.
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