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：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：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：US10851655B2

公开(公告)日：2020-12-01

申请号：US15898973

申请日：2018-02-19

Applicant: ROLLS-ROYCE plc

Inventor： Gabriel Gonzalez-Gutierrez

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/28 ,  F04D29/66 ,  F04D29/32 ,  F01D5/10 ,  F02C3/04

Abstract: A fan for a gas turbine engine, the fan comprising a first set of fan blades and a second set of fan blades arranged circumferentially around a hub. Each of the fan blades of the first and second set comprises an organic matrix composite body and a leading edge member connected to the body. The leading edge member of the first set of fan blades has a mass less than the leading edge member of the second set of fan blades.

公开(公告)号：US10724536B2

公开(公告)日：2020-07-28

申请号：US15898305

申请日：2018-02-16

Applicant: ROLLS-ROYCE plc

Inventor： Antonios Kalochairetis ,  Gabriel Gonzalez-Gutierrez

IPC: F04D29/34 ,  F04D29/32 ,  F02K3/06 ,  F01D5/10 ,  F01D5/30 ,  F01D5/16 ,  F01D5/32 ,  F04D29/66

Abstract: A fan for a gas turbine engine, the fan comprising a first set of fan blades, each fan blade comprising a root and an axial retention feature provided on the root at a first position, and a second set of fan blades, each fan blade comprising a root and an axial retention feature provided on the root at a second position. Relative to the respective blade on which the respective retention feature is provided, the first position is different to the second position.

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.

公开(公告)号：US20190107050A1

公开(公告)日：2019-04-11

申请号：US16123466

申请日：2018-09-06

Applicant: ROLLS-ROYCE plc

Inventor： Jeffrey S. Green ,  Gabriel Gonzalez-Gutierrez ,  Domenico Sgro

IPC: F02C7/04

Abstract: A gas turbine engine and air intake assembly comprises an intake passage extending between an inlet highlight at a first end and an upstream face of a fan at a second end and comprising in flow series an intake lip, a most upstream portion of which defines the intake highlight and a most downstream portion of which defines a throat, a diffuser with sectional area broadening towards the fan; and a straight conditioning duct, arranged immediately upstream of the fan. The camber line of the intake passage intersects the engine main axis at an intersecting point upstream of the fan at an intersecting point and the camber line is parallel to the engine main axis in the straight conditioning duct.