公开(公告)号：US12037942B2

公开(公告)日：2024-07-16

申请号：US17731673

申请日：2022-04-28

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M Townes ,  Michael J Whittle ,  Pascal Dunning

IPC: F02C7/08 ,  F01D5/28 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06

CPC classification number: F02C7/08 ,  F01D5/282 ,  F01D5/284 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2300/6033

Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US11326512B2

公开(公告)日：2022-05-10

申请号：US17345588

申请日：2021-06-11

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Pascal Dunning

IPC: F02C7/36 ,  F02C3/04

Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.

公开(公告)号：US11047301B2

公开(公告)日：2021-06-29

申请号：US16411224

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Pascal Dunning ,  Michael J Whittle ,  Roderick M Townes

IPC: F02C3/107 ,  F02C3/073 ,  F02C7/36 ,  F01D5/28

Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US10989112B2

公开(公告)日：2021-04-27

申请号：US16411341

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Pascal Dunning ,  Roderick M Townes ,  Michael J Whittle

IPC: F02C3/073 ,  F02C7/36 ,  F01D5/28 ,  F01D5/30

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US10738693B2

公开(公告)日：2020-08-11

申请号：US16398760

申请日：2019-04-30

Applicant: ROLLS-ROYCE PLC

Inventor： Michael J Whittle ,  Pascal Dunning ,  Roderick M Townes

IPC: F02C3/06 ,  F02C7/36 ,  F02K3/06 ,  F01D5/28

Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.