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Patent Agency Ranking
公开(公告)号：US11181042B2
公开(公告)日：2021-11-23
申请号：US16411347
申请日：2019-05-14
Applicant: ROLLS-ROYCE plc
Inventor： Michael O Hales , Craig W Bemment , Stephane M M Baralon , Benjamin J Sellers , Christopher Benson , Benedict R Phelps , Mark J Wilson
Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
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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：US11519363B2
公开(公告)日：2022-12-06
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.
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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：US11441517B2
公开(公告)日：2022-09-13
申请号：US16658832
申请日：2019-10-21
Applicant: ROLLS-ROYCE plc
Inventor： Michael O Hales , Stephen J Bradbrook
Abstract: A supersonic jet aircraft and a method of operating the same. The supersonic jet aircraft having at least three turbofan engines and an engine management computer. A first engine of the at least three turbofan engines is configured to be de-activatable during flight to move from an operational state in which it provides thrust to an operational state in which it stops providing thrust. Other engines of the at least three turbofan engines are configured to provide sufficient thrust to the supersonic jet aircraft when the first engine is de-activated such that the aircraft can perform a supersonic climb operation and/or a supersonic cruise operation.
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