公开(公告)号：US20210062758A1

公开(公告)日：2021-03-04

申请号：US16985809

申请日：2020-08-05

Applicant: ROLLS-ROYCE plc

Inventor： Christopher T. J. SHEAF ,  Chia Hui LIM

IPC: F02K3/02 ,  F02C3/113 ,  F01D25/34 ,  F01D15/12

Abstract: A gas turbine engine for an aircraft includes an engine core, fan, air intake and gearbox. The engine core includes a turbine, compressor, and core shaft connecting the turbine and compressor. The fan is located upstream of the core and includes a plurality of fan blades, the fan having a diameter greater than 2.0 m. The air intake is located upstream of the fan and has ratio of intake length to fan diameter of 0.20 to 0.60 and defines highlight, throat and diffuser areas. The gearbox receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gas turbine engine has a bypass ratio greater than 10; and the air intake has an intake length and the ratio of the intake length to the fan diameter is from 0.20 to 0.60.

公开(公告)号：US20170191413A1

公开(公告)日：2017-07-06

申请号：US15372289

申请日：2016-12-07

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A. KNIGHT ,  Alan R. MAGUIRE ,  Daniel ROBINSON ,  George BOSTOCK ,  Christopher T. J. SHEAF

IPC: F02C6/08 ,  B64D27/10 ,  B64D13/02 ,  F02C7/36 ,  F02C7/04

CPC classification number: F02C6/08 ,  B64D13/02 ,  B64D27/10 ,  F02C7/04 ,  F02C7/057 ,  F02C7/277 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2270/102 ,  F05D2270/1022 ,  Y02T50/671

Abstract: A gas turbine engine including an intake, a fan and an injector system. The intake has an inner wall which defines an intake passage for the fan. The injector system includes a cabin blower system including a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and by the injector system. The intake includes an injector of the injector system through which in use fluid from the cabin blower compressor is injected into a main airflow for flow control of air on the way to the fan.