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：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：US20170145958A1

公开(公告)日：2017-05-25

申请号：US15298927

申请日：2016-10-20

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M. M. BARALON

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

CPC classification number: F02K3/06 ,  B64D27/18 ,  F04D29/325 ,  F04D29/542 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712

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：US20180371919A1

公开(公告)日：2018-12-27

申请号：US16012891

申请日：2018-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M. M. BARALON

IPC: F01D5/14 ,  F01D9/04

CPC classification number: F01D5/145 ,  F01D5/141 ,  F01D9/041 ,  F01D17/105 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/20 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/17

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：US20200063569A1

公开(公告)日：2020-02-27

申请号：US16545011

申请日：2019-08-20

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M. M. BARALON ,  George CRAMMOND ,  Stuart ANDREWS

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/66

Abstract: The present disclosure relates to a fan blade for a gas turbine engine, the fan blade comprising an aerofoil portion having a leading edge extending from a root to a tip, the radial distance between the leading edge at the root and the leading edge at the tip defining a blade span. A maximum thickness of the cross-sections through the aerofoil portion from a suction surface of the aerofoil portion to a pressure surface of the aerofoil portion perpendicular to the camber line decreases along the blade span from the root to the tip. There is a discontinuity in the rate of decrease of maximum thickness between a radius at 30% of the blade span from the aerofoil root and 70% of the blade span from the aerofoil root. The rate of decrease of the maximum thickness before the discontinuity is less than the rate of decrease of the maximum thickness after the discontinuity.

公开(公告)号：US20200011273A1

公开(公告)日：2020-01-09

申请号：US16411294

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

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

IPC: F02K3/06 ,  F02K3/02

Abstract: A gas turbine engine system has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The fan bypass inlet mass flow rate at the reference operating point is appreciably higher than the mass flow rate through the bypass duct at the peak bypass efficiency at a given fan reference rotational speed and cruise conditions. This results in increased design flexibility and improved overall engine performance.

公开(公告)号：US20190162071A1

公开(公告)日：2019-05-30

申请号：US16170707

申请日：2018-10-25

Applicant: ROLLS-ROYCE plc

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

IPC: F01D5/16 ,  F01D5/14

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.