-
公开(公告)号：US20230167768A1
公开(公告)日：2023-06-01
申请号：US17940055
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Jonathan A. CHERRY , Paul R. DAVIES , David A. JONES , Andrew J. NEWMAN , Benjamin J. SELLERS , Stephen J. BRADBROOK
CPC classification number: F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
-
公开(公告)号：US20190128215A1
公开(公告)日：2019-05-02
申请号：US16162860
申请日：2018-10-17
Applicant: ROLLS-ROYCE plc
Inventor： Edward C. GOWER , Paul R. DAVIES
Abstract: A gas turbine engine includes a main gas flow exhaust nozzle having an annular inner surface which, in use, bounds a flow of exhaust gas. The gas turbine engine further includes cooling passages having respective outlets therefrom to provide a flow of cooling air over a surface of the engine or an adjacent airframe component, thereby protecting the cooled surface from the exhaust gas flow. Adjacent cooling passages of the or each pair of the nested cooling passages are separated from each other by a respective dividing wall. The outlets from the nested cooling passages are staggered in the axial direction of the exhaust nozzle such that cooling air flowing out of an inner one of the adjacent cooling passages of the or each pair of the nested cooling passages flows over the dividing wall separating the adjacent passages.
-
公开(公告)号：US20240077022A1
公开(公告)日：2024-03-07
申请号：US18233533
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , David A. JONES , Richard G. MOCHRIE
CPC classification number: F02C7/16 , B64D27/10 , F05D2260/232
Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, a first heat exchanger, and one or more first ancillary systems. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the or each first electric machine, the first gas turbine engine, the first heat exchanger, and the or each first ancillary system. Waste heat energy generated by at least one of the first gas turbine engine, the or each first electric machine, and the or each first ancillary system, is transferred to the first heat transfer fluid. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.
-
公开(公告)号：US20230184171A1
公开(公告)日：2023-06-15
申请号：US17988504
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Gareth E. MOORE , Paul R. DAVIES , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE , Douglas M M. HERBERT
IPC: F02C7/262
CPC classification number: F02C7/262 , F05D2220/323 , F05D2220/76 , F05D2260/85 , F05D2270/092 , F05D2270/093
Abstract: Multi-engine aircraft power and propulsion systems and methods of restarting an engine of a multi-engine aircraft during fight are provided. One such method comprises: determining a condition to the effect that a flame in the combustion equipment of the second gas turbine engine has been extinguished; responsive to the determination, supplying electrical power from the electrical energy storage system to one or more of the electric machines of the second gas turbine engine and operating said one or more electric machines as motors to limit a reduction in a speed of the one or more spools of the second gas turbine engine following extinguishment of the flame in its combustion equipment; and restarting the second gas turbine engine by relighting the combustion equipment of the second gas turbine engine.
-
公开(公告)号：US20230184128A1
公开(公告)日：2023-06-15
申请号：US17940614
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , Gareth E. MOORE , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE
CPC classification number: F01D15/10 , F02K3/06 , F05D2220/323 , F05D2260/213 , F05D2260/232 , F05D2260/42 , F05D2200/13 , F05D2200/14
Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module. The gas turbine engine further comprises a first electric machine that is rotationally connected to the turbine module, and an electrical energy storage unit. The gas turbine engine is configured to generate a maximum dry thrust T (N). The first electric machine is configured to generate a maximum electrical power PEM1 (W). The electrical energy storage unit has an energy storage capacity E (Wh), a maximum charge rate C (h−1), and a maximum discharge rate D (h−1). The electrical energy storage unit is configured to store electrical energy that may be generated by the first electric machine.
-
Patent Agency Ranking
公开(公告)号：US20240076053A1
公开(公告)日：2024-03-07
申请号：US18233502
申请日：2023-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Paul R. DAVIES , Alexander T. JOYCE , David A. JONES
CPC classification number: B64D33/08 , F02C6/18 , F05D2260/20
Abstract: A thermal management system for an aircraft includes a first thermal bus including one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources. The vapour compression system includes a compressor, a condenser, a receiver, a first side of a recuperator, an expansion valve, an evaporator, a second side of the recuperator, and the compressor. A first heat flow (Q1) of waste heat energy generated by the first heat sources is transferred via the first heat transfer fluid to the heat sink. A second heat flow (Q2) of waste heat energy generated by the second heat source(s) being transferred via the evaporator to a refrigerant. A third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid. The controller is configured to ensure that:
1.1*Q2-
公开(公告)号：US20210010382A1
公开(公告)日：2021-01-14
申请号：US16914867
申请日：2020-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES
Abstract: An aircraft gas turbine engine (10) comprises a main engine shaft (22, 23), a main engine shaft bearing arrangement (36, 44, 49, 50) configured to rotatably support the main engine shaft (22, 23) and an electric machine (30) comprising a rotor (34) and a stator (32). The rotor (34) is mounted to the main engine shaft (22, 23) and is rotatably supported by the main engine shaft bearing arrangement (36, 44, 49, 50), and the stator (32) is mounted to static structure (46) of the gas turbine engine (10).
-
公开(公告)号：US20240077019A1
公开(公告)日：2024-03-07
申请号：US18233518
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , Alexander T. JOYCE , David A. JONES
CPC classification number: F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.
-
公开(公告)号：US20230184130A1
公开(公告)日：2023-06-15
申请号：US17988393
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Gareth E. MOORE , Paul R. DAVIES , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE , Douglas M M HERBERT
Abstract: Aircraft power and propulsion systems, aircraft comprising such power and propulsion systems, and methods of restarting a gas turbine engine of such power and propulsion systems during flight are provided. One such aircraft power and propulsion system comprises: a propulsive gas turbine engine comprising a plurality of spools, combustion equipment, one or more electric machines mechanically coupled with one or more of the spools and an electrically-powered fuel pump for delivering fuel to the combustion equipment; an electrical system connected with the one or more electric machines and the electrically-powered fuel pump, the electrical system comprising an energy storage system; and a control system configured to: responsive to a determination to the effect that a flame in the combustion equipment has been extinguished, control the electrical system to supply electrical power from the energy storage system to the fuel pump during an engine restart attempt.
-
公开(公告)号：US20230182917A1
公开(公告)日：2023-06-15
申请号：US17988371
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Gareth E. MOORE , Paul R. DAVIES , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE , Douglas M. M. HERBERT
CPC classification number: B64D31/06 , B64D27/24 , B64D27/10 , F01D15/10 , F05D2220/76 , F05D2220/323 , B64D2221/00 , B64D2027/026
Abstract: Multi-engine aircraft power and propulsion systems and methods of starting the engines of multi-engine aircraft disclosed, including supplying electrical power from an electrical power source to electric machines of the a first gas turbine engine and operating electric machines as motors to drive rotation of spools of the first gas turbine engine; starting the first gas turbine engine by lighting combustion equipment of the first gas turbine engine; operating the electric machines of the first gas turbine engine as generators to extract mechanical power and generate electrical power from spools of the first gas turbine engine; transferring the electrical power to electric machines of a second gas turbine engine and operating the electric machines as motors to drive rotation of spools of the second gas turbine engine; and starting the second gas turbine engine by lighting combustion equipment of the second gas turbine engine.
-
-
-
-
-
-
-
-
-
Search Results
13
records
(took 0.016 seconds)
