公开(公告)号：US20190063368A1

公开(公告)日：2019-02-28

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 HS SMITH ,  Marco BARALE ,  Kashmir S. JOHAL ,  Stephane MM BARALON ,  Craig W. BEMMENT

IPC: F02K3/06 ,  F02C3/06 ,  F01D5/14

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：US20190063369A1

公开(公告)日：2019-02-28

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 HS SMITH ,  Marco BARALE ,  Kashmir S. JOHAL ,  Stephane MM BARALON ,  Craig W. BEMMENT

IPC: F02K3/06 ,  F02C3/06 ,  F01D5/14

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：US20210156260A1

公开(公告)日：2021-05-27

申请号：US16952534

申请日：2020-11-19

Applicant: ROLLS-ROYCE plc

Inventor： Stephane MM BARALON

IPC: F01D5/14 ,  F02K3/06 ,  F02C7/36 ,  F01D5/30

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：US20190063370A1

公开(公告)日：2019-02-28

申请号：US16106765

申请日：2018-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. PHELPS ,  Mark J. WILSON ,  Gabriel GONZALEZ-GUTIERREZ ,  Nigel HS SMITH ,  Marco BARALE ,  Kashmir S. JOHAL ,  Stephane MM BARALON ,  Craig W. BEMMENT

IPC: F02K3/075 ,  F02K3/06 ,  F01D5/16 ,  F01D5/14

Abstract: A gas turbine engine 10 is provided in which a fan root pressure ratio is no greater than a given value at cruise conditions. The gas turbine engine may provide improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.