公开(公告)号：US11988157B2

公开(公告)日：2024-05-21

申请号：US18166268

申请日：2023-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Mochrie ,  Graeme E F Sutcliffe ,  Jade Whittle

IPC: F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F02C9/26

CPC classification number: F02C9/26 ,  F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213

Abstract: A gas turbine engine comprising a combustor and a fuel management system. The fuel management system comprises a fuel supply line, recirculation line and heat exchanger. The fuel supply line is configured to supply fuel to the combustor. The recirculation line is configured to recirculate excess fuel from the fuel supply line to an engine-located fuel tank via a fuel cooling device. The fuel cooling device is configured to reject heat from the excess fuel in the recirculation line. The heat exchanger is 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 or on the recirculation line. The fuel supply line is configured to receive fuel from an external source and from the engine-located fuel tank.

公开(公告)号：US20230279815A1

公开(公告)日：2023-09-07

申请号：US18166268

申请日：2023-02-08

Applicant: Rolls-Royce plc

Inventor： Richard G MOCHRIE ,  Graeme E F Sutcliffe ,  Jade Whittle

IPC: F02C9/26 ,  F02C7/224 ,  F02C7/22 ,  F02C7/14

CPC classification number: F02C9/26 ,  F02C7/224 ,  F02C7/22 ,  F02C7/14 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213

Abstract: A gas turbine engine comprising a combustor and a fuel management system. The fuel management system comprises a fuel supply line, recirculation line and heat exchanger. The fuel supply line is configured to supply fuel to the combustor. The recirculation line is configured to recirculate excess fuel from the fuel supply line to an engine-located fuel tank via a fuel cooling device. The fuel cooling device is configured to reject heat from the excess fuel in the recirculation line. The heat exchanger is 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 or on the recirculation line. The fuel supply line is configured to receive fuel from an external source and from the engine-located fuel tank.

公开(公告)号：US12078109B2

公开(公告)日：2024-09-03

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: F02C7/224 ,  F02C7/16 ,  F02C9/28

CPC classification number: F02C7/224 ,  F02C7/16 ,  F02C9/28 ,  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.