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公开(公告)号：US11732603B2
公开(公告)日：2023-08-22
申请号：US17969826
申请日：2022-10-20
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J Bousfield , Duncan A MacDougall
CPC classification number: F01D25/02 , F01D5/141 , F01D5/147 , F04D29/324 , F05D2220/32 , F05D2240/303 , F05D2240/307
Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft, and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.
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公开(公告)号：US11634994B2
公开(公告)日：2023-04-25
申请号：US17663600
申请日：2022-05-16
Applicant: ROLLS-ROYCE plc
Inventor： Duncan A MacDougall , Jaime Terron Fraile
Abstract: A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.
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公开(公告)号：US11512607B2
公开(公告)日：2022-11-29
申请号：US17235234
申请日：2021-04-20
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J Bousfield , Duncan A MacDougall
Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.
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公开(公告)号：US11686248B2
公开(公告)日：2023-06-27
申请号：US17333631
申请日：2021-05-28
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J Bousfield , Duncan A MacDougall
CPC classification number: F02C7/05 , F01D5/143 , F01D21/10 , F01D25/02 , F02C7/04 , F02C7/30 , F02K1/82
Abstract: A core duct assembly for a gas turbine engine includes a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.
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Patent Agency Ranking
公开(公告)号：US11634993B2
公开(公告)日：2023-04-25
申请号：US17514977
申请日：2021-10-29
Applicant: ROLLS-ROYCE plc
Inventor： Geoffrey B Jones , Edward J Spalton , Duncan A MacDougall
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：US11619135B2
公开(公告)日：2023-04-04
申请号：US17218617
申请日：2021-03-31
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：US11047311B2
公开(公告)日：2021-06-29
申请号：US16437283
申请日：2019-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Ian J Bousfield , Duncan A MacDougall
Abstract: A core duct assembly for a gas turbine engine, the core duct assembly including: a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.
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公开(公告)号：US11002149B2
公开(公告)日：2021-05-11
申请号：US16437501
申请日：2019-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Ian J Bousfield , Duncan A MacDougall
Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein the ratio of a maximum leading edge radius of the first rotor blades to a minimum leading edge radius of the first rotor blades is included between 2.2 and 3.5.
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公开(公告)号：US10578027B1
公开(公告)日：2020-03-03
申请号：US16411312
申请日：2019-05-14
Applicant: ROLLS-ROYCE PLC
Inventor： Duncan A MacDougall , Ian J Bousfield
Abstract: A gas turbine engine includes a fan, compressor, combustor, and turbine coupled to the compressor through a shaft. The compressor includes first, second, and third stages with respective rotor blades and stator vanes. The rotor blades and stator vanes are arranged such that a sum of mid-span axial gaps between the trailing edge of the first rotor blades and the leading edge of the first stator vanes, the trailing edge of the first stator vanes and the leading edge of the second rotor blades, the trailing edge of the second rotor blades and the leading edge of the second stator vanes, and the trailing edge of the second stator vanes and the leading edge of the third rotor blades is equal to a × inlet flow function 10 . a ≥ 75 mm and the inlet flow function = m T P .
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