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：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：US20210348555A1

公开(公告)日：2021-11-11

申请号：US17196345

申请日：2021-03-09

Applicant: ROLLS-ROYCE plc

Inventor： Ian J. BOUSFIELD ,  Michael O. HALES

IPC: F02C3/06

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 or five compressor stages (14); the high pressure compressor (15) consists of eight or nine compressor stages; the low pressure turbine (19) comprises four or more stages; and the high pressure compressor (15) and low pressure compressor (14) together define a core overall pressure ratio of greater than 36:1.

公开(公告)号：US20210301763A1

公开(公告)日：2021-09-30

申请号：US17196393

申请日：2021-03-09

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Michael O. HALES

IPC: F02K3/06 ,  F02C3/107 ,  F02C3/06 ,  F02C7/36

Abstract: A gas turbine engine including an engine core with high and low pressure compressors and high and low pressure turbines, the high pressure compressor and high pressure turbine being coupled by a high pressure shaft, and the low pressure compressor and low pressure turbine being coupled by a low pressure shaft, the engine further including a fan coupled to the low pressure shaft by a reduction gearbox. The high pressure compressor consists of 8 or 9 stages and has an average stage loading at cruise conditions of between 1.39 and 1.42, and the low and high pressure compressor together define an overall core pressure ratio at cruise conditions of between 40 and 60.

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.