公开(公告)号：US11181042B2

公开(公告)日：2021-11-23

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：US11208895B2

公开(公告)日：2021-12-28

申请号：US17064667

申请日：2020-10-07

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin Mohankumar ,  Mark J Wilson ,  Cesare A Hall

IPC: F01D5/14

Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, compressor, and core shaft connecting turbine to the compressor; a fan located upstream of engine core, the fan containing a plurality of fan blades mounted for rotation about an engine axis, each blade of the plurality of fan blades having a leading edge and trailing edge extending across a span of an airflow duct from blade root to tip; and a gearbox that receives an input from core shaft and outputs drive to fan so as to drive the fan at a lower rotational speed than the core shaft, wherein the trailing edge of each blade is characterized by a metric M defined as a rate of change of an angle of trailing edge between 0.4 and 0.8 of the span divided by an area averaged trailing edge angle, M being not less than around 4.

公开(公告)号：US10145387B2

公开(公告)日：2018-12-04

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 ,  F04D19/00 ,  F04D27/00 ,  F04D29/32 ,  F04D29/68 ,  B64C21/04 ,  B64D13/02 ,  B64D13/04 ,  F16H15/38 ,  F16H37/08 ,  F04D25/02 ,  F04D27/02 ,  B64D33/02

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.