公开(公告)号：US20200049063A1

公开(公告)日：2020-02-13

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 ,  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.

公开(公告)号：US20200049067A1

公开(公告)日：2020-02-13

申请号：US16423227

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M TOWNES ,  Pascal DUNNING ,  Michael J WHITTLE

IPC: F02C6/02

Abstract: A highly efficient gas turbine engine has a fan that 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：US20220268216A1

公开(公告)日：2022-08-25

申请号：US17731673

申请日：2022-04-28

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M TOWNES ,  Michael J WHITTLE ,  Pascal DUNNING

IPC: F02C7/36 ,  F01D5/28

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：US20200291782A1

公开(公告)日：2020-09-17

申请号：US16444341

申请日：2019-06-18

Applicant: ROLLS-ROYCE PLC ,  ITP NEXT GENERATION TURBINES SLU

Inventor： Roderick M TOWNES ,  Diego TORRE RUIZ

IPC: F01D5/08 ,  F01D5/04

Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.

公开(公告)号：US20200049065A1

公开(公告)日：2020-02-13

申请号：US16411253

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael J WHITTLE ,  Roderick M TOWNES ,  Pascal DUNNING

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine is highly efficient. 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.