公开(公告)号：US20210071586A1

公开(公告)日：2021-03-11

申请号：US17060797

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Craig W. BEMMENT

IPC: F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine includes: an engine core, compressor system, and core shaft. A compressor exit pressure is defined as an average airflow pressure at the exit of the highest pressure compressor at cruise conditions. The core has an annular splitter and bypass flow. Stagnation streamlines around the engine circumference form a streamsurface. A fan is upstream the core with blades having leading and trailing edges, and a radially inner portion within the streamtube. A fan root entry pressure is an average airflow pressure across the radially inner portion leading edge of each fan blade at cruise conditions. An overall pressure ratio is defined as the compressor exit pressure divided by the fan root entry pressure. A bypass jet velocity is defined as the jet velocity of air flow exiting the bypass exhaust nozzle at cruise conditions. A jet velocity is in a range between 4.7 m/s and 7.7 m/s.

公开(公告)号：US20210071572A1

公开(公告)日：2021-03-11

申请号：US16680668

申请日：2019-11-12

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Craig W. BEMMENT

IPC: F02C3/06 ,  F01D17/10

Abstract: A gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine system comprising one or more turbines (17, 19), a compressor system comprising one or more compressors (14,15), and a core shaft (26) connecting the turbine system to the compressor system, wherein a compressor exit pressure (P30) is defined as an average pressure of airflow at the exit of the highest pressure compressor of the compressor system at cruise conditions, the engine core (11) further comprises an annular splitter (70) at which flow is divided between a core flow (A) that flows through the engine core and a bypass flow (B) that flows along a bypass duct (22), wherein stagnation streamlines (110) around the circumference of the engine (10), stagnating on a leading edge of the annular splitter (70), form a streamsurface (110) forming a radially outer boundary of a streamtube that contains all of the core flow (A); a fan (23) located upstream of the engine core (11), the fan comprising a plurality of fan blades (64) extending from a hub, each fan blade (64) having a leading edge (64a) and a trailing edge (64b), each fan blade (64) having a radially inner portion (65a) lying within the streamtube that contains the core flow (A), and wherein a fan root entry pressure (P20) is defined as an average pressure of airflow across the leading edge (64a) of the radially inner portion of each fan blade (64) at cruise conditions; and a nacelle (21) surrounding the engine core (11), the nacelle (21) defining the bypass duct (22) and a bypass exhaust nozzle (18). An overall pressure ratio is defined as the compressor exit pressure (P30) divided by the fan root entry pressure (P20). A bypass nozzle pressure ratio is defined as the nozzle pressure ratio of the bypass exhaust nozzle (18) at cruise conditions. A combined pressure ratio defined as: overall   pressure   ratio bypass   nozzle   pressure   ratio is in a range between 20 and 29. A method of operating a gas turbine engine on an aircraft is also disclosed.

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：US20200049066A1

公开(公告)日：2020-02-13

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

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：US20200049021A1

公开(公告)日：2020-02-13

申请号：US16423343

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

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

IPC: F01D9/04 ,  F02C3/073 ,  F02C7/36 ,  F01D11/12 ,  F01D5/14

Abstract: A highly efficient gas turbine engine includes a fan 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：US20240426251A1

公开(公告)日：2024-12-26

申请号：US18825435

申请日：2024-09-05

Applicant: ROLLS-ROYCE plc

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

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

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：US20240191657A1

公开(公告)日：2024-06-13

申请号：US18583395

申请日：2024-02-21

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：US20230228232A1

公开(公告)日：2023-07-20

申请号：US18123091

申请日：2023-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Pascal DUNNING

IPC: F02K3/06

CPC classification number: F02K3/06 ,  F05D2220/36 ,  F05D2200/14 ,  F05D2260/4031 ,  F05D2240/307 ,  F05D2220/323

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：US20220307448A1

公开(公告)日：2022-09-29

申请号：US17586401

申请日：2022-01-27

Applicant: ROLLS-ROYCE plc

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

IPC: F02K3/065 ,  F01D5/14 ,  F02C3/107 ,  F01D5/02 ,  F02C7/36 ,  F02K3/02

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：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.