公开(公告)号：US20200011238A1

公开(公告)日：2020-01-09

申请号：US16411347

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael O. HALES ,  Craig W. BEMMENT ,  Stephane M. M. BARALON ,  Benjamin J. SELLERS ,  Christopher BENSON ,  Benedict R. PHELPS ,  Mark J. WILSON

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US20230167775A1

公开(公告)日：2023-06-01

申请号：US17940419

申请日：2022-09-08

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J. SELLERS ,  Andrew J. NEWMAN ,  Gordon MARGARY ,  Paul R. DAVIES ,  Stephen J. BRADBROOK

IPC: F02C7/32 ,  F02C6/00 ,  F02C6/20 ,  F02C7/12

CPC classification number: F02C7/32 ,  F02C6/00 ,  F02C6/20 ,  F02C7/12 ,  F05D2220/76 ,  F05D2220/323 ,  F05D2260/213

Abstract: A gas turbine engine for an aircraft includes, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a total electrical power PEM1 (W), and the gas turbine engine is configured to generate a total shaft power PSHAFT (W); and a ratio R of:




R
=




Total Shaft Power =

P

S
H
A
F
T










Total Electrical Power Generated = P


E
M
1










is in a range of between 0.005 and 0.020.

公开(公告)号：US20180079510A1

公开(公告)日：2018-03-22

申请号：US15704831

申请日：2017-09-14

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  Benjamin J. SELLERS ,  Rory D. STIEGER

IPC: B64D13/04 ,  B64D27/16 ,  F04D25/02 ,  F04D27/00 ,  F02C7/32

CPC classification number: B64D13/04 ,  B64D27/16 ,  B64D2013/0603 ,  F02C7/32 ,  F04D25/02 ,  F04D27/002 ,  F04D27/0261 ,  F05D2220/323 ,  F05D2260/40 ,  F05D2270/101 ,  F05D2270/30 ,  Y02T50/671

Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.

公开(公告)号：US20230184197A1

公开(公告)日：2023-06-15

申请号：US17940531

申请日：2022-09-08

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J. SELLERS ,  Andrew J NEWMAN ,  David A JONES ,  Stephen J BRADBROOK

IPC: F02K3/06 ,  B64D27/20 ,  F02K3/068

CPC classification number: F02K3/06 ,  B64D27/20 ,  F02K3/068 ,  F05D2200/14 ,  F05D2220/323

Abstract: An gas turbine engine for an aircraft includes, in axial flow sequence, a compressor module, a combustor module, and a turbine module, together with a first electrical machine rotationally connected to the turbine module. The combustor module has a combustor volume V (cm3). In use, at a full power condition, the gas turbine engine has a maximum corrected core flow Q (m3/sec), and a ratio T of:




T
=


(


Maximum
⁢

Corrected
⁢

Core
⁢

Flow

=
Q

)


(


Combustor
⁢

volume

=
V

)






is in a range of between 450 and 2,500.

公开(公告)号：US20200011274A1

公开(公告)日：2020-01-09

申请号：US16423523

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J. SELLERS ,  Craig W. BEMMENT ,  Michael O. HALES ,  Stephane M. M. BARALON ,  Benedict R. PHELPS ,  Christopher BENSON ,  Mark J. WILSON

IPC: F02K3/06 ,  F02C7/36

Abstract: A gas turbine engine has a quasi-non-dimensional mass flow rate in a defined range and a specific thrust in a defined range to achieve improved over all performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of quasi-non-dimensional mass flow rate and specific thrust may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US20230167768A1

公开(公告)日：2023-06-01

申请号：US17940055

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG ,  Jonathan A. CHERRY ,  Paul R. DAVIES ,  David A. JONES ,  Andrew J. NEWMAN ,  Benjamin J. SELLERS ,  Stephen J. BRADBROOK

IPC: F02C7/12 ,  F02C6/20 ,  F02C7/32

CPC classification number: F02C7/12 ,  F02C6/20 ,  F02C7/32 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/213

Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.

公开(公告)号：US20210301718A1

公开(公告)日：2021-09-30

申请号：US17196382

申请日：2021-03-09

Applicant: ROLLS-ROYCE plc

Inventor： Michael O. HALES ,  Craig W. BEMMENT ,  Benjamin J. SELLERS ,  Ian J. BOUSFIELD ,  Amarveer S. MANN

IPC: F02C3/06 ,  F02C7/36

Abstract: A gas turbine engine (10) comprising:
a high pressure turbine (17);
a low pressure turbine (19);
a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27);
a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low pressure shaft (26) and a reduction gearbox (30); wherein
the low pressure compressor (14) consists of four compressor stages (14) and defines a cruise pressure ratio of between 2.4:1 and 3.3:1;
the high pressure compressor (15) defines a cruise pressure ratio of less than 17:1; and
the high pressure compressor (15) and low pressure compressor (14) together define a cruise core overall pressure ratio of greater than 36:1.

公开(公告)号：US20190186360A1

公开(公告)日：2019-06-20

申请号：US16211360

申请日：2018-12-06

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J. SELLERS

IPC: F02C7/057 ,  B64D31/00 ,  B64D27/10 ,  B64F5/60 ,  F01D25/02 ,  F02C7/047

CPC classification number: F02C7/057 ,  B64D15/12 ,  B64D27/10 ,  B64D31/00 ,  B64D2221/00 ,  B64F5/60 ,  F01D15/10 ,  F01D25/02 ,  F02C7/047 ,  F02C7/32 ,  F02C9/00 ,  F05D2220/76 ,  F05D2270/101 ,  F05D2270/309 ,  F05D2270/335

Abstract: A method of controlling electrical power supplied to a component of a vehicle, the method comprising: receiving a signal comprising information associated with an operating condition of a gas turbine engine; determining whether a parameter exceeds a predetermined threshold value using the information in the received signal; and controlling a reduction in electrical power supplied to a component of a vehicle from a generator of the gas turbine engine if the parameter exceeds the predetermined threshold value.