公开(公告)号：US11339727B2

公开(公告)日：2022-05-24

申请号：US17100429

申请日：2020-11-20

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. Phelps ,  Stephane M M Baralon

IPC: F02C7/36 ,  F02C9/22 ,  F01D5/14

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：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：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：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.