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：US11181042B2

公开(公告)日：2021-11-23

申请号：US16411347

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael O Hales ,  Craig W Bemment ,  Stephane M M Baralon ,  Benjamin J Sellers ,  Christopher Benson ,  Benedict R Phelps ,  Mark J Wilson

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine has a cycle operability parameter β 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 range of cycle operability parameter β 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：US10436035B1

公开(公告)日：2019-10-08

申请号：US16399102

申请日：2019-04-30

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M Baralon ,  Christopher Benson ,  Benedict R Phelps

IPC: F01D5/14 ,  F04D29/38 ,  F01D5/28 ,  F04D29/32

Abstract: A gas turbine engine has a fan tip air angle and/or a fan blade tip air angle in a defined range to achieve improved over all performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of fan tip air angle and/or a fan blade tip air angle 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：US10364773B2

公开(公告)日：2019-07-30

申请号：US15298927

申请日：2016-10-20

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M Baralon

IPC: F04D29/54 ,  F02K3/06 ,  B64D27/18 ,  F04D29/32

Abstract: A gas turbine engine comprising a fan, a bypass duct positioned downstream of the fan and defined by an inner casing and an outer casing, a series of outlet guide vanes arranged downstream of the fan, the outlet guide vanes extending between the inner casing and the outer casing of the bypass duct; and a bifurcation positioned downstream of the outlet guide vanes and extending between the inner casing and the outer casing. The bifurcation comprises a leading edge, and the leading edge of the bifurcation is shaped so as to protrude axially forward by a varying distance from the inner casing to the outer casing so as to improve uniformity of a static pressure field formed, in use, immediately upstream of the bifurcation.

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：US10760427B2

公开(公告)日：2020-09-01

申请号：US16012891

申请日：2018-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M Baralon

IPC: F01D5/14 ,  F01D17/10 ,  F01D9/04

Abstract: A slot is provided in an endwall of a flow passage, for example between two stator vanes or rotor blades of a gas turbine engine. The length direction of the flow passage is aligned substantially with the main flow through the flow passage. The alignment of the slot means that the “over-turned” boundary layer flow can be extracted through the slot but with minimal impact on the mainstream flow.

公开(公告)号：US12065942B2

公开(公告)日：2024-08-20

申请号：US18303430

申请日：2023-04-19

Applicant: Rolls-Royce plc

Inventor： Stephane M M Baralon

IPC: F01D5/02

CPC classification number: F01D5/021 ,  F05D2220/32 ,  F05D2220/36

Abstract: A fan stage of a ducted fan gas turbine engine has a rotor hub having a principal axis of rotation and a plurality of fan blades having a hub end attached to the hub and extending radially towards a tip end so as to define a blade span dimension. Each blade has a leading and a trailing edge, a chord for a section of the blade being a straight line joining the leading and trailing edges within the section. A difference between a stagger angle in a mid-span region and in the vicinity of the tip end of each blade is greater than or equal to 20°. The fan blades are twisted to a greater extent than conventional between the mid-span and tip end. A camber angle difference between the mid-span region and the tip end may be greater than 30 degrees.

公开(公告)号：US11268386B2

公开(公告)日：2022-03-08

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：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.