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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：US20200271012A1
公开(公告)日：2020-08-27
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 edges, 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 curvature of the first rotor blades to a minimum leading edge radius of curvature of the first rotor blades is included between 2.2 and 3.5.
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公开(公告)号：US20210285379A1
公开(公告)日：2021-09-16
申请号：US17333631
申请日：2021-05-28
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J. BOUSFIELD , Duncan A. MACDOUGALL
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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公开(公告)号：US20200291862A1
公开(公告)日：2020-09-17
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：US20230045400A1
公开(公告)日：2023-02-09
申请号：US17969826
申请日：2022-10-20
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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Patent Agency Ranking
公开(公告)号：US20210348555A1
公开(公告)日：2021-11-11
申请号：US17196345
申请日：2021-03-09
Applicant: ROLLS-ROYCE plc
Inventor： Ian J. BOUSFIELD , Michael O. HALES
IPC: F02C3/06
Abstract: A gas turbine engine (10) comprising: a high pressure turbine (17); a low pressure turbine (19); a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27); a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low pressure shaft (26) and a reduction gearbox (30); wherein the low pressure compressor (14) consists of four or five compressor stages (14); the high pressure compressor (15) consists of eight or nine compressor stages; the low pressure turbine (19) comprises four or more stages; and the high pressure compressor (15) and low pressure compressor (14) together define a core overall pressure ratio of greater than 36:1.
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公开(公告)号：US20210301718A1
公开(公告)日：2021-09-30
申请号：US17196382
申请日：2021-03-09
Applicant: ROLLS-ROYCE plc
Inventor： Michael O. HALES , Craig W. BEMMENT , Benjamin J. SELLERS , Ian J. BOUSFIELD , Amarveer S. MANN
Abstract: A gas turbine engine (10) comprising:
a high pressure turbine (17);
a low pressure turbine (19);
a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27);
a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low pressure shaft (26) and a reduction gearbox (30); wherein
the low pressure compressor (14) consists of four compressor stages (14) and defines a cruise pressure ratio of between 2.4:1 and 3.3:1;
the high pressure compressor (15) defines a cruise pressure ratio of less than 17:1; and
the high pressure compressor (15) and low pressure compressor (14) together define a cruise core overall pressure ratio of greater than 36:1.-
公开(公告)号：US20240093610A1
公开(公告)日：2024-03-21
申请号：US18524490
申请日：2023-11-30
Applicant: ROLLS-ROYCE plc
Inventor： Ian J. BOUSFIELD , Ducan 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：US20230228196A1
公开(公告)日：2023-07-20
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 , F02C7/05 , F02C7/36 , F05D2220/32 , 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：US20200232392A1
公开(公告)日：2020-07-23
申请号：US16718405
申请日：2019-12-18
Applicant: ROLLS-ROYCE plc
Inventor： Ian J. BOUSFIELD
Abstract: A gas turbine engine includes an inlet duct to guide a core engine flow to a compressor and an engine section stator arranged in the inlet duct upstream of the compressor including vanes with leading edges defining a first annulus area in the inlet duct, a mid-span leading edge point of the engine section stator vanes being arranged at a first radius. The compressor includes a first rotor with a row of first blades with leading edges defining a second annulus area; a mid-span leading edge point of the compressor first blades being arranged at a second radius and an axial distance from the engine section stator vane mid-span leading edge point. The ratio of the second to the first annulus area is equal or greater than 0.75, and the ratio of a difference between the first and second radius to the axial distance is equal or greater than 0.23.
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