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公开(公告)号：US20210222616A1
公开(公告)日：2021-07-22
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：US20210301764A1
公开(公告)日：2021-09-30
申请号：US17196460
申请日：2021-03-09
Applicant: ROLLS-ROYCE PLC
Inventor： Rory D STIEGER
Abstract: A gas turbine engine includes an engine core having high and low pressure compressors and high and low pressure turbines. The engine further includes a fan coupled to a low pressure shaft and the low pressure turbine by a reduction gearbox. The low pressure compressor includes no more than two compressor stages, and the low and high pressure compressor together define a cruise overall core pressure ratio of between 30 and 50.
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公开(公告)号：US20210301719A1
公开(公告)日：2021-09-30
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：US20200025109A1
公开(公告)日：2020-01-23
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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