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公开(公告)号：US12135313B2
公开(公告)日：2024-11-05
申请号：US17958996
申请日：2022-10-03
Applicant: ROLLS-ROYCE plc
Inventor： Duncan A Macdougall , Julian M Reed , Sophoclis Patsias , Antonio Pellegrino , Clive R Siviour , Daniel Eakins , Yuan Xu , Junyi Zhou
Abstract: A system for measuring loading on a test specimen. The system includes the test specimen arranged between a first loading bar and a second loading bar. The system further includes a first loading unit and a second loading unit configured to apply a first load and a second load to the first and second loading bars, respectively. The system further includes a first clamp and a second clamp configured to hold the first and second loading bars against the first and second loads, respectively. The system further includes a clamp actuating unit configured to selectively release at least the first clamp. The clamp actuating unit further includes a controller configured to electrically actuate at least one first electromechanical transducer from a retained state to a released state to release the first clamp, such that the first loading bar applies a first loading wave to the test specimen.
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公开(公告)号：US12286895B2
公开(公告)日：2025-04-29
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：US11920499B2
公开(公告)日：2024-03-05
申请号：US18122807
申请日：2023-03-17
Applicant: ROLLS-ROYCE plc
Inventor： Geoffrey B Jones , Edward J Spalton , Duncan A Macdougall
CPC classification number: F01D9/041 , F01D9/04 , F01D17/162 , F02C7/042 , F05D2220/32 , F05D2220/323 , F05D2240/12
Abstract: A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.
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公开(公告)号：US10995677B2
公开(公告)日：2021-05-04
申请号：US16813830
申请日：2020-03-10
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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