公开(公告)号：US20210355873A1

公开(公告)日：2021-11-18

申请号：US17231130

申请日：2021-04-15

Applicant: ROLLS-ROYCE plc

Inventor： Robert E CHRISTIE ,  David G MACMANUS ,  Christopher T J SHEAF

IPC: F02C7/045 ,  F02K3/06 ,  B64D33/02

Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The nacelle further includes a protrusion extending radially inward from the air intake downstream of the intake lip. The protrusion extends circumferentially by a protrusion angle (θp) with respect to the longitudinal centre line of the gas turbine engine.

公开(公告)号：US20210355871A1

公开(公告)日：2021-11-18

申请号：US17231275

申请日：2021-04-15

Applicant: ROLLS-ROYCE plc

Inventor： Robert E CHRISTIE ,  David G MACMANUS

IPC: F02C7/04

Abstract: An intake centre fairing for a gas turbine engine includes a body. The body includes an outer surface, an apex point and a base. The apex point is at a first end of the body and the base is at a second end of the body. The base includes a base centre. The body defines a longitudinal axis along its length, a radial direction relative to the longitudinal axis and a circumferential direction relative to the longitudinal axis. The outer surface of the body is tapered from the base to the apex point along the longitudinal axis. The apex point is radially offset relative to the base centre along the radial direction. The apex point is further circumferentially offset relative to the base centre along the circumferential direction.