公开(公告)号：US20230279810A1

公开(公告)日：2023-09-07

申请号：US18166308

申请日：2023-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Richard G. MOCHRIE

IPC: F02C7/14 ,  F02C7/224 ,  F02C7/22

CPC classification number: F02C7/14 ,  F02C7/224 ,  F02C7/222 ,  F05D2260/213

Abstract: A fuel management system for a gas turbine engine. The fuel management system comprises a fuel supply line configured to supply fuel from an inlet to a combustor of the gas turbine engine. The fuel management system also includes a recirculation line extending from a recirculation point on the fuel supply line and configured to recirculate excess fuel from the fuel supply line for resupply to the fuel supply line. In addition, the fuel management system comprises a heat exchanger configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel management system. The heat exchanger is disposed on the fuel supply line upstream of the recirculation point or on the recirculation line. The fuel management system further comprises a fuel cooling device disposed along the recirculation line and configured to reject heat from the excess fuel therein.

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

IPC: F02C7/16 ,  B64D27/10

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：US20230279812A1

公开(公告)日：2023-09-07

申请号：US18166253

申请日：2023-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Richard G. MOCHRIE ,  Graeme E F SUTCLIFFE ,  Jade WHITTLE

IPC: F02C9/28 ,  F02C7/224 ,  F02C7/16

CPC classification number: F02C9/28 ,  F02C7/224 ,  F02C7/16 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2260/232

Abstract: A fuel management system for a gas turbine engine, the fuel management system comprising a fuel supply line configured to supply fuel from a system inlet to a combustor of the gas turbine engine via a combustor pump and combustor valve. A heat exchanger is configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel supply line between the system inlet and the combustor valve. There is a downstream recirculation line configured to recirculate a downstream excess portion of fuel from the fuel supply line, the downstream recirculation line extending from a downstream recirculation point on the fuel supply line between the heat exchanger and the combustor valve.