公开(公告)号：US20240077025A1

公开(公告)日：2024-03-07

申请号：US18233619

申请日：2023-08-14

Applicant: ROLLS-ROYCE PLC

Inventor： Paul R DAVIES ,  David A JONES ,  Alexander T JOYCE ,  Richard G MOCHRIE

IPC: F02C7/16 ,  F02C6/18

CPC classification number: F02C7/16 ,  F02C6/18 ,  F05D2220/323 ,  F05D2260/213

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. 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 first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat is exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

公开(公告)号：US20240084735A1

公开(公告)日：2024-03-14

申请号：US18233510

申请日：2023-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Paul R DAVIES ,  David A JONES

IPC: F02C7/14 ,  B64D27/10 ,  F02C7/18

CPC classification number: F02C7/14 ,  B64D27/10 ,  F02C7/18 ,  F05D2220/323 ,  F05D2260/213

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, first thermal bus and heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, or each first electric machine, and the first heat exchanger. Waste heat energy transfers to the first heat transfer fluid. The first heat exchanger configures to transfer waste heat energy from the first heat transfer fluid to a dissipation medium. During steady-state operation of the first gas turbine engine, the first heat transfer fluid entering the first heat exchanger has a temperature of TFLUID(° C.), and a temperature of an inlet air flow entering the first gas turbine engine has a temperature TAIR(° C.) and a ratio B is in a range of between 5.0-18.0.




B
=


(


First
⁢

Heat
⁢

Transfer
⁢

Fluid
⁢

Temperature

=

T
FLUID


)


(


Inlet
⁢

Air
⁢

Temperature

=

T
AIR


)

公开(公告)号：US20240077021A1

公开(公告)日：2024-03-07

申请号：US18233531

申请日：2023-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Paul R DAVIES ,  Richard G MOCHRIE ,  David A JONES

IPC: F02C7/16 ,  B64D27/10

CPC classification number: F02C7/16 ,  B64D27/10 ,  F05D2260/20

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, and a first heat exchanger. Waste heat energy generated by at least one first gas turbine engine, and first electric machine, transfers to the first heat transfer fluid. The first heat exchanger directs a first proportion of the first heat transfer fluid through a first heat dissipation portion wherein a first proportion of the waste heat energy transfers to a first dissipation medium dependent on the first dissipation medium temperature and mass flow rate. The first heat exchanger directs a second proportion of the first heat transfer fluid through a second heat dissipation portion wherein the second proportion of waste heat energy transfers to a second dissipation medium dependent on the second dissipation medium temperature and mass flow rate.

公开(公告)号：US20220205388A1

公开(公告)日：2022-06-30

申请号：US17494537

申请日：2021-10-05

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

IPC: F02C7/08 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, a combustor module, and an exhaust module.
The machine body comprises either one or two fluid inlet apertures. The or each fluid inlet aperture is configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan module, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module.

公开(公告)号：US20220112838A1

公开(公告)日：2022-04-14

申请号：US17484771

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

IPC: F02C7/08 ,  F02K3/00

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes fan blades defining a corresponding fan area (AFAN). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and includes radially-extending vanes arranged in a circumferential array with at least one vane including a heat transfer element for heat transfer from a first fluid contained within each element to an airflow passing over a surface of each heat transfer element before entering the fan assembly inlet. Each heat transfer element extends axially along the corresponding vane, with a swept heat transfer element area (AHTE) being the wetted surface area of all heat transfer elements in contact with the airflow. A Fan to Element Area parameter FEA of AHTE/AFAN lies in the range of 47 to 132.

公开(公告)号：US20240077020A1

公开(公告)日：2024-03-07

申请号：US18233521

申请日：2023-08-14

Applicant: ROLLS-ROYCE PLC

Inventor： Richard G MOCHRIE ,  David A JONES

IPC: F02C7/16 ,  F02C6/18

CPC classification number: F02C7/16 ,  F02C6/18 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/303

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, and a first heat exchanger module. 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 first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to the first heat transfer fluid. The first heat exchanger module comprises a first flow path and a second flow path. The first flow path is configured to direct a flow of the first heat transfer fluid either to a first heat dissipation portion in which a first proportion QA of the waste heat energy from the first heat transfer fluid is transferred to a first dissipation medium, or additionally to a second heat dissipation portion in which a second proportion QB of the waste heat energy from the first heat transfer fluid is transferred to a second dissipation medium, in dependence on a temperature of the first heat transfer fluid entering the first heat exchanger module, a temperature of the first heat dissipation medium, and a temperature of the second heat dissipation medium. The second flow path is configured to direct the flow of the first heat transfer fluid to a second heat dissipation portion in which a second proportion QB of the waste heat energy from the first heat transfer fluid is transferred to a second dissipation medium, or additionally to the first heat dissipation portion in which a first proportion QA of the waste heat energy from the first heat transfer fluid is transferred to a first dissipation medium, in dependence on a temperature of the first heat transfer fluid entering the first heat exchanger module, a temperature of the first heat dissipation medium, and a temperature of the second heat dissipation medium.

公开(公告)号：US20240076052A1

公开(公告)日：2024-03-07

申请号：US18233495

申请日：2023-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Paul R DAVIES ,  David A JONES ,  Richard G MOCHRIE

IPC: B64D33/08 ,  F02C7/12

CPC classification number: B64D33/08 ,  F02C7/12 ,  F05D2220/323 ,  F05D2260/213

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, a first thermal bus, and a first heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to first heat transfer fluid. When airspeed of aircraft is less than Mn0.6, the first heat exchanger transfers the waste heat energy from the first heat transfer fluid to a first dissipation medium. When the airspeed of the aircraft is greater than Mn0.6, the first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a second dissipation medium.

公开(公告)号：US20230193822A1

公开(公告)日：2023-06-22

申请号：US18110664

申请日：2023-02-16

Applicant: ROLLS-ROYCE PLC

Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

IPC: F02C7/04 ,  F02C7/18 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D27/20 ,  B64D33/10 ,  F02K3/06 ,  F02K3/075 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F01D9/06

CPC classification number: F02C7/04 ,  F02C7/18 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D27/20 ,  B64D33/10 ,  F02K3/06 ,  F02K3/075 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F01D9/065 ,  F05D2260/213 ,  B64D2033/0286 ,  F05D2220/323 ,  B64D2033/024 ,  F05D2220/36 ,  F02K3/115

Abstract: An aircraft includes a machine body that encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine includes, in axial flow sequence, a first heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The aircraft includes a second heat exchanger module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the first heat exchanger module. When a temperature of the fluid cooling flow is less than a temperature of a fluid to be cooled, the fluid to be cooled is directed to the first heat exchanger module, and when a temperature of the fluid cooling flow is greater than a temperature of the fluid to be cooled, the fluid to be cooled is directed to the second heat exchanger module and cooled using a fuel supply for the gas turbine engine.

公开(公告)号：US20230184197A1

公开(公告)日：2023-06-15

申请号：US17940531

申请日：2022-09-08

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J. SELLERS ,  Andrew J NEWMAN ,  David A JONES ,  Stephen J BRADBROOK

IPC: F02K3/06 ,  B64D27/20 ,  F02K3/068

CPC classification number: F02K3/06 ,  B64D27/20 ,  F02K3/068 ,  F05D2200/14 ,  F05D2220/323

Abstract: An gas turbine engine for an aircraft includes, in axial flow sequence, a compressor module, a combustor module, and a turbine module, together with a first electrical machine rotationally connected to the turbine module. The combustor module has a combustor volume V (cm3). In use, at a full power condition, the gas turbine engine has a maximum corrected core flow Q (m3/sec), and a ratio T of:




T
=


(


Maximum
⁢

Corrected
⁢

Core
⁢

Flow

=
Q

)


(


Combustor
⁢

volume

=
V

)






is in a range of between 450 and 2,500.

公开(公告)号：US20230167769A1

公开(公告)日：2023-06-01

申请号：US17940473

申请日：2022-09-08

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew J NEWMAN ,  Martin N GOODHAND ,  Paul R DAVIES ,  David A JONES ,  Stephen J BRADBROOK

IPC: F02C7/14 ,  F02C7/18

CPC classification number: F02C7/14 ,  F02C7/18 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/232

Abstract: A cooling system for an aircraft comprises an apparatus, a heat exchanger, and a vapour cycle machine. The apparatus comprises a first fluid being circulated to provide cooling to the apparatus, with the heat exchanger being configured to transfer waste heat energy from the first fluid to a second fluid. The second fluid has a temperature T2 (°C), and the vapour cycle machine is configured to increase a temperature T1 (°C) of the first fluid, to a temperature greater than T2 (°C).