公开(公告)号：US20200018169A1

公开(公告)日：2020-01-16

申请号：US16566383

申请日：2019-09-10

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane M M BARALON ,  Christopher BENSON ,  Benedict R. PHELPS

IPC: F01D5/14 ,  F01D5/28 ,  F04D29/38

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 overall 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：US20170145959A1

公开(公告)日：2017-05-25

申请号：US15333624

申请日：2016-10-25

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M BARALON

IPC: F02K3/06

CPC classification number: F02K3/06 ,  B64D27/26 ,  F01D9/04 ,  F02C7/20 ,  F04D29/544 ,  F05D2210/12 ,  F05D2220/36 ,  F05D2250/30

Abstract: A gas turbine engine comprising in flow series: a fan; a series of outlet guide vanes; and a bifurcation. The outlet guide vanes are more densely distributed in a region circumferentially aligned with the bifurcation than in a region circumferentially offset from the bifurcation.

公开(公告)号：US20210071672A1

公开(公告)日：2021-03-11

申请号：US17096581

申请日：2020-11-12

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane M M BARALON ,  Mark J WILSON ,  Benedict R PHELPS

IPC: F04D15/00 ,  F02K1/38 ,  F02K3/075 ,  F04D27/02

Abstract: A gas turbine engine has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The bypass flow rate at the optimum bypass efficiency is appreciably lower than the maximum bypass flow rate at the given conditions. This results in increased design flexibility and improved overall engine performance.

公开(公告)号：US20200072058A1

公开(公告)日：2020-03-05

申请号：US16554713

申请日：2019-08-29

Applicant: ROLLS-ROYCE plc

Inventor： Christopher BENSON ,  Stephane M M BARALON

IPC: F01D5/14 ,  F01D5/28

Abstract: A gas turbine engine comprises carbon fibre fan blades. At cruise conditions, the fan tip air angle θ in the range: 64 degrees≤θ≤67 degrees. Additionally or alternatively, the fan blade tip angle β is in the range of from 62 to 69 degrees. Arrangements in accordance with the present disclosure provide advantages which may include improved bird-strike performance. This may allow advantages associated with carbon fibre fan blades to be better exploited.

公开(公告)号：US20210404342A1

公开(公告)日：2021-12-30

申请号：US17352468

申请日：2021-06-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. PHELPS ,  Stephane M M BARALON ,  Mark J. WILSON

IPC: F01D5/14 ,  F02K3/06

Abstract: A fan blade for a gas turbine engine has a covered passage. A cross section through the fan blade at a point along the blade span is defined as having particular change in angle (α3−α1) of the camber line between the leading edge and the trailing edge and/or between the leading edge and the point on the camber line that corresponds to the start of the covered passage.

公开(公告)号：US20200011333A1

公开(公告)日：2020-01-09

申请号：US16398878

申请日：2019-04-30

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M BARALON ,  Mark J WILSON ,  Benedict R PHELPS

IPC: F04D15/00 ,  F02K3/075 ,  F02K1/38 ,  F04D27/02

Abstract: A gas turbine engine has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The bypass flow rate at the optimum bypass efficiency is appreciably lower than the maximum bypass flow rate at the given conditions. This results in increased design flexibility and improved overall engine performance.