公开(公告)号：US10473112B2

公开(公告)日：2019-11-12

申请号：US15894240

申请日：2018-02-12

Applicant: ROLLS ROYCE plc

Inventor： Nigel H S Smith ,  Mark J. Wilson ,  Gabriel Gonzalez-Gutierrez ,  Marco Barale ,  Benedict Phelps ,  Kashmir S. Johal

IPC: F04D29/38 ,  F02K3/06

Abstract: A fan blade is provided with an aerofoil portion for which, at radii between 20% and 40% of the blade span, the location of the position of maximum thickness along the camber line is at less than a defined percentage of the total length of the camber line. For all cross-sections through the aerofoil portion at radii greater than 70% of the blade span, the location of the position of maximum thickness along the camber line is at more than a defined percentage of the total length of the camber line. The geometry of the fan blade may result in a lower susceptibility to flutter.

公开(公告)号：US11692454B2

公开(公告)日：2023-07-04

申请号：US17453501

申请日：2021-11-04

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin Mohankumar ,  Mark J. Wilson ,  Cesare A. Hall

IPC: F01D15/12 ,  F02C7/04 ,  F01D25/24 ,  F02K3/068

CPC classification number: F01D15/12 ,  F01D25/24 ,  F02C7/04 ,  F02K3/068 ,  F05D2220/32 ,  F05D2260/4031

Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric Stip, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, L/D is between 0.2 and 0.45 and Stip is from −1 to 0.1.

公开(公告)号：US11598214B2

公开(公告)日：2023-03-07

申请号：US17412759

申请日：2021-08-26

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin Mohankumar ,  Mark J. Wilson ,  Cesare A. Hall

IPC: F01D5/14 ,  B64D27/10 ,  B64D27/24 ,  B64D33/02 ,  F02K3/075 ,  F02K3/06

Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric S, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, and L/D is between 0.2 and 0.45.

公开(公告)号：US11359493B2

公开(公告)日：2022-06-14

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：US11149690B2

公开(公告)日：2021-10-19

申请号：US16106813

申请日：2018-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. Phelps ,  Mark J. Wilson ,  Gabriel Gonzalez-Gutierrez ,  Nigel H S Smith ,  Marco Barale ,  Kashmir S. Johal ,  Stephane M M Baralon ,  Craig W. Bemment

IPC: F02K3/06 ,  F02C7/04 ,  F02C7/36 ,  F02C3/06 ,  F01D5/14 ,  F01D5/16

Abstract: A gas turbine engine 10 is provided in a fan root to tip pressure ratio, defined as the ratio of the mean total pressure of the flow at the fan exit that subsequently flows through the engine core (P102) to the mean total pressure of the flow at the fan exit that subsequently flows through the bypass duct (P104), is no greater than a certain value. The gas turbine engine 10 may provide improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US20210172323A1

公开(公告)日：2021-06-10

申请号：US17181594

申请日：2021-02-22

Applicant: Rolls-Royce plc

Inventor： Benedict Phelps ,  Stephane M. M. Baralon ,  Mark J. Wilson

IPC: F01D5/16 ,  F02K3/06 ,  F01D25/06 ,  F01D5/14

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US11085399B2

公开(公告)日：2021-08-10

申请号：US16106853

申请日：2018-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. Phelps ,  Mark J. Wilson ,  Gabriel Gonzalez-Gutierrez ,  Nigel H S Smith ,  Marco Barale ,  Kashmir S. Johal ,  Stephane M M Baralon ,  Craig W. Bemment

IPC: F02K3/06 ,  F02C7/04 ,  F01D5/14 ,  F02C3/06

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades in which the camber distribution along the span allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US11346229B2

公开(公告)日：2022-05-31

申请号：US17181594

申请日：2021-02-22

Applicant: Rolls-Royce plc

Inventor： Benedict Phelps ,  Stephane M M Baralon ,  Mark J. Wilson

IPC: F01D5/16 ,  F02K3/06 ,  F01D25/06 ,  F01D5/14 ,  F02C7/36

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US10954798B2

公开(公告)日：2021-03-23

申请号：US16170688

申请日：2018-10-25

Applicant: ROLLS-ROYCE plc

Inventor： Benedict Phelps ,  Stephane M M Baralon ,  Mark J. Wilson

IPC: F01D5/16 ,  F02K3/06 ,  F01D25/06 ,  F01D5/14 ,  F02C7/36

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US10577937B2

公开(公告)日：2020-03-03

申请号：US15894276

申请日：2018-02-12

Applicant: ROLLS-ROYCE plc

Inventor： Mark J. Wilson ,  Gabriel Gonzalez-Gutierrez ,  Marco Barale ,  Benedict Phelps ,  Kashmir S. Johal ,  Nigel H S Smith

IPC: F01D5/14 ,  F01D5/16 ,  F02K3/06

Abstract: A fan blade is provided with an aerofoil portion for which, for cross-sections through the aerofoil portion at radii between 15% and 25% of the blade span from the root radius, the average leading edge thickness is greater than the leading edge thickness at the tip. The geometry of the fan blade may result in a lower susceptibility to flutter.