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：US11261734B2

公开(公告)日：2022-03-01

申请号：US16545011

申请日：2019-08-20

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M Baralon ,  George Crammond ,  Stuart Andrews

IPC: F01D5/14 ,  F04D29/66 ,  F04D29/32

Abstract: The present disclosure relates to a fan blade for a gas turbine engine, the fan blade comprising an aerofoil portion having a leading edge extending from a root to a tip, the radial distance between the leading edge at the root and the leading edge at the tip defining a blade span. A maximum thickness of the cross-sections through the aerofoil portion from a suction surface of the aerofoil portion to a pressure surface of the aerofoil portion perpendicular to the camber line decreases along the blade span from the root to the tip. There is a discontinuity in the rate of decrease of maximum thickness between a radius at 30% of the blade span from the aerofoil root and 70% of the blade span from the aerofoil root. The rate of decrease of the maximum thickness before the discontinuity is less than the rate of decrease of the maximum thickness after the discontinuity.

公开(公告)号：US20210156317A1

公开(公告)日：2021-05-27

申请号：US17100429

申请日：2020-11-20

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. Phelps ,  Stephane M M Baralon

IPC: F02C9/22 ,  F02C7/36

Abstract: Gas turbine aircraft engine comprising an engine core comprising a turbine, a compressor, a core shaft connecting the turbine to the compressor; and a fan upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each fan blade comprises a main blade and an auxiliary blade. Over substantially all of the auxiliary blade's radial span, the leading edge of the auxiliary blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem.

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：US10451005B2

公开(公告)日：2019-10-22

申请号：US15333624

申请日：2016-10-25

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M Baralon

IPC: F02K3/06 ,  F01D9/04 ,  F02C7/20 ,  B64D27/26

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.