公开(公告)号：US20180231019A1

公开(公告)日：2018-08-16

申请号：US15894206

申请日：2018-02-12

Applicant: ROLLS-ROYCE plc

Inventor： Marco BARALE ,  Gabriel GONZALEZ-GUTIERREZ ,  Mark J. WILSON ,  Benedict PHELPS ,  Kashmir S. JOHAL ,  Nigel HS SMITH

IPC: F04D29/38 ,  F04D29/32

CPC classification number: F04D29/386 ,  F01D5/141 ,  F04D29/325 ,  F05D2220/36 ,  F05D2230/239 ,  F05D2240/303 ,  Y02T50/672 ,  Y02T50/673

Abstract: A fan blade for a gas turbine engine is provided with forward axial lean. The fan blade may have a substantially straight leading edge. The geometry of the fan blade results in a lower susceptibility to flutter, thereby allowing a gas turbine engine comprising such a fan blade to operate over a wider range of operating conditions.

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：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.

公开(公告)号：US20180231021A1

公开(公告)日：2018-08-16

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 HS SMITH

IPC: F04D29/38 ,  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：US20180231018A1

公开(公告)日：2018-08-16

申请号：US15894240

申请日：2018-02-12

Applicant: ROLLS-ROYCE plc

Inventor： Nigel HS SMITH ,  Mark J. WILSON ,  Gabriel GONZALEZ-GUTIERREZ ,  Marco BARALE ,  Benedict PHELPS ,  Kashmir S. JOHAL

IPC: F04D29/38 ,  F02K3/06

CPC classification number: F04D29/384 ,  F01D5/141 ,  F01D5/26 ,  F02K3/06 ,  F04D29/388 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/301 ,  F05D2240/303 ,  Y02T50/672 ,  Y02T50/673

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：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：US20180231020A1

公开(公告)日：2018-08-16

申请号：US15894249

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 HS SMITH

IPC: F04D29/38 ,  F02K3/06

CPC classification number: F04D29/386 ,  F01D5/141 ,  F01D5/147 ,  F02K3/06 ,  F04D29/324 ,  F04D29/388 ,  F05D2220/32 ,  F05D2230/239 ,  F05D2240/303 ,  Y02T50/672 ,  Y02T50/673

Abstract: A fan blade for a gas turbine engine is arranged such that for any two points on its leading edge that are in the radially outer 40% of the blade span and are radially separated by at least 5% of the blade span, the radially outer of the two points is axially forward of the radially inner point. The radius of the leading edge of a given fan blade at the hub divided by the radius of the leading edge of the fan blade at the tip is less than or equal to 0.3. Such an arrangement may result in an improved operability range.