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1.发明申请公开(公告)号：US20200173368A1
公开(公告)日：2020-06-04
申请号：US16679576
申请日：2019-11-11
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Ahmed M Y RAZAK , Paul R. MILLER
Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling ignition within a combustion chamber of the gas turbine engine; controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a self-sustaining threshold pressure; and in response to determining that the exit pressure of the high pressure compressor is equal to or greater than the self-sustaining threshold pressure, ceasing controlling rotation of the low pressure compressor using the first electrical machine, and/or the high pressure compressor using a second electrical machine.
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公开(公告)号：US20180149115A1
公开(公告)日：2018-05-31
申请号：US15810263
申请日：2017-11-13
Applicant: ROLLS-ROYCE plc
Inventor： Ahmed M Y RAZAK , Paul FLETCHER
Abstract: A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine may be provided downstream of the re-heat combustor and coupled to the low pressure compressor (14) by a low pressure shaft, the low pressure and high pressure shafts being independently rotatable. A shaft power transfer arrangement may be provided, which is configured to selectively transfer power between the low pressure and high pressure shafts.
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公开(公告)号：US20200173301A1
公开(公告)日：2020-06-04
申请号：US16694047
申请日：2019-11-25
Applicant: ROLLS-ROYCE plc
Inventor： Ahmed M Y RAZAK
Abstract: A combined cycle heat engine (10). The engine (10) comprises a first gas turbine engine (11) comprising a first air compressor (14), a first combustion system (16, 20) and a first turbine system (18, 22), and a second gas turbine engine (32) comprising a second air compressor (36) and a second turbine system (40). The engine further comprises a heat exchanger (38) configured to transfer heat from an exhaust of the first turbine system (18, 22) to compressed air from the second air compressor (36). The first combustion system comprises a first combustor (16) provided downstream of the first air compressor (14) and upstream of the first turbine system (18, 22), and a second combustor (20) downstream of a first turbine section (18) of the first turbine system and upstream of a second turbine section (22) of the first turbine system.
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公开(公告)号：US20200223554A1
公开(公告)日：2020-07-16
申请号：US16716894
申请日：2019-12-17
Applicant: ROLLS-ROYCE plc
Inventor： Ahmed M Y RAZAK
Abstract: An aircraft including an aft-mounted boundary layer energisation system is shown. The system comprises a nacelle arranged around a tailcone of the aircraft which thereby defines a duct, the duct having, in axial flow series, an intake, a heat exchanger, and a nozzle, and no turbomachinery therein, whereby the system energises a boundary layer of the aircraft by means of Meredith effect.
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