公开(公告)号：US20200011274A1

公开(公告)日：2020-01-09

申请号：US16423523

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J. SELLERS ,  Craig W. BEMMENT ,  Michael O. HALES ,  Stephane M. M. BARALON ,  Benedict R. PHELPS ,  Christopher BENSON ,  Mark J. WILSON

IPC: F02K3/06 ,  F02C7/36

Abstract: A gas turbine engine has a quasi-non-dimensional mass flow rate in a defined range and a specific thrust 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 quasi-non-dimensional mass flow rate and specific thrust 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：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：US20200011238A1

公开(公告)日：2020-01-09

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：US20190162070A1

公开(公告)日：2019-05-30

申请号：US16170688

申请日：2018-10-25

Applicant: ROLLS-ROYCE plc

Inventor： Benedict PHELPS ,  Stephane M.M. BARALON ,  Mark J. WILSON

IPC: F01D5/16 ,  F01D5/14 ,  F02K3/06

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 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：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：US20180202391A1

公开(公告)日：2018-07-19

申请号：US15868066

申请日：2018-01-11

Applicant: ROLLS-ROYCE plc

Inventor： Mark J. WILSON ,  Giulio ZAMBONI

IPC: F02K3/06 ,  F01D9/04 ,  F04D29/54

CPC classification number: F02K3/06 ,  F01D9/041 ,  F02K1/00 ,  F02K3/04 ,  F04D29/542 ,  F04D29/547 ,  F05D2250/184 ,  F05D2250/61 ,  F05D2250/73

Abstract: A fan outlet assembly comprises a fan discharge nozzle having a radially inner platform, a radially outer platform arranged coaxially and in radial alignment with the radially inner platform and a circumferential array of outlet guide vanes (110) spanning an annulus defined by the radially inner platform and radially outer platform. An annular duct extends downstream from the circumferential array, the duct having a radially outer wall (112) contiguous with the radially outer platform and a radially inner wall (111) contiguous with the radially inner platform. In a region extending downstream from the circumferential array, the radially inner and outer platforms and/or the radially inner and outer walls having a non-axisymmetric surface bounding the duct. A non-axisymmetric surface may be applied to either or both of the radially outer and radially inner contiguous surfaces and may extend upstream as well as downstream of the circumferential array of outlet guide vanes.

公开(公告)号：US20160341215A1

公开(公告)日：2016-11-24

申请号：US15136409

申请日：2016-04-22

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A. KNIGHT ,  Alan R. MAGUIRE ,  Daniel ROBINSON ,  George BOSTOCK ,  Mark J. WILSON

IPC: F04D29/52 ,  B64D13/06 ,  F04D27/00 ,  F04D19/00 ,  F04D29/32

CPC classification number: F04D29/526 ,  B64C21/04 ,  B64D13/02 ,  B64D13/04 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2033/0286 ,  F04D19/00 ,  F04D25/02 ,  F04D25/028 ,  F04D27/009 ,  F04D27/0261 ,  F04D29/324 ,  F04D29/684 ,  F05D2220/36 ,  F05D2270/101 ,  F16H15/38 ,  F16H37/084 ,  F16H37/086 ,  F16H2037/088

Abstract: A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.

Abstract translation: 公开了一种燃气涡轮发动机，其包括压缩机，围绕压缩机的压缩机壳体和压缩机尖端喷射器系统。 压缩机叶尖喷射器系统包括舱室鼓风机系统，其包括在使用中布置的用于压缩在飞机的舱室中使用的空气和由压缩机叶尖喷射器系统布置的舱室鼓风机压缩机。 压缩机壳体包括一个或多个压缩机尖端喷射器系统的喷射器，在使用时，来自机舱鼓风机压缩机的空气在压缩机旋转时被喷射到压缩机的叶片的叶片末端。