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：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：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：US20180238174A1

公开(公告)日：2018-08-23

申请号：US15898973

申请日：2018-02-19

Applicant: ROLLS-ROYCE plc

Inventor： Gabriel GONZALEZ-GUTIERREZ

IPC: F01D5/16 ,  F02C3/04 ,  F01D5/28 ,  F01D5/10

CPC classification number: F01D5/16 ,  F01D5/10 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F02C3/04 ,  F04D29/324 ,  F04D29/666 ,  F04D29/668 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/96 ,  F05D2260/961 ,  F05D2300/133 ,  Y02T50/672 ,  Y02T50/673

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：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.

公开(公告)号：US20190101002A1

公开(公告)日：2019-04-04

申请号：US16128671

申请日：2018-09-12

Applicant: ROLLS-ROYCE PLC

Inventor： Roger S. DUFFIN ,  Gabriel GONZALEZ-GUTIERREZ

IPC: F01D5/14 ,  F01D5/16 ,  F04D29/38 ,  F04D29/66 ,  F01D9/04

Abstract: A blade or vane for a gas turbine engine comprising a pressure surface and a suction surface. The pressure surface or the suction surface comprises a roughness zone which is configured to provide greater flow resistance in a direction along the blade or vane than in a direction across the blade or vane.

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：US20180238342A1

公开(公告)日：2018-08-23

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

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.