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公开(公告)号：US11339714B2
公开(公告)日：2022-05-24
申请号：US17061057
申请日：2020-10-01
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE CORPORATION
Inventor： Rory D Stieger , Daniel Swain
Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.
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公开(公告)号：US11378017B2
公开(公告)日：2022-07-05
申请号：US16448214
申请日：2019-06-21
Applicant: ROLLS-ROYCE plc
Inventor： Rory D Stieger , Conor Hickey
Abstract: A turbofan engine has an engine core including in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core, has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake, has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct, and has a mixer for mixing an exhaust gas flow exiting the engine core and bypass airflow exiting bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller controlling the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb.
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Patent Agency Ranking
公开(公告)号：US10246197B2
公开(公告)日：2019-04-02
申请号：US15280170
申请日：2016-09-29
Applicant: ROLLS-ROYCE plc
Inventor： Rory D Stieger , Matthew Moxon , Mikko Mattila
Abstract: An aircraft (10) comprising a fuselage (12), the fuselage (10) comprising at least first and second inwardly tapering portions (20, 22) extending in a generally rearward direction from an aft end of the fuselage (12), each inwardly tapering portion (20, 22) comprising a boundary layer ingesting propulsor (36) mounted thereon.
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公开(公告)号：US11480134B2
公开(公告)日：2022-10-25
申请号：US17196546
申请日：2021-03-09
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J Bousfield , Michael O Hales , Rory D Stieger
Abstract: A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.
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公开(公告)号：US10167084B2
公开(公告)日：2019-01-01
申请号：US14830143
申请日：2015-08-19
Applicant: ROLLS-ROYCE PLC
Inventor： Rory D Stieger , Lorenzo Raffaelli
Abstract: An air duct arrangement (58) for an aircraft (40). The arrangement (58) comprises an environmental control system (ECS) (50). The ECS (50) comprises an air inlet (60) arranged to ingest a low velocity portion of a boundary layer flow adjacent the aircraft fuselage (44), and to deliver a flow of air to an environmental control system air intake (66). The arrangement (58) further comprises an ejector (70) arranged to receive an ECS exhaust (76), and boundary layer air from an aft region of the aircraft (40), and to exhaust air to the ambient airstream at an aft portion of the aircraft (40).
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公开(公告)号：US11629668B2
公开(公告)日：2023-04-18
申请号：US17196546
申请日：2021-03-09
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J Bousfield , Michael O Hales , Rory D Stieger
Abstract: A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.
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公开(公告)号：US11486302B2
公开(公告)日：2022-11-01
申请号：US17060986
申请日：2020-10-01
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Rory D Stieger , Mark D Taylor , Erik Janke
Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The expansion ratios of the turbines are dependent upon an outlet temperature of the combustor, and an expansion relationship between the turbines is defined as the ratio of expansion ratios of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A second derivative of the expansion relationship is from 0.6 to 1.0.
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