公开(公告)号：US20200277868A1

公开(公告)日：2020-09-03

申请号：US16786037

申请日：2020-02-10

Applicant: ROLLS-ROYCE plc

Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Quentin BORLON

IPC: F01D9/02 ,  F01D15/02 ,  F23R3/42

Abstract: A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction. The combustion liner also comprises a fluid-guiding surface at an upstream side of the chute which defines an arc terminating at the exhaust hole, the fluid guiding surface configured to guide fluid from a direction generally parallel to the outer surface into the chute to be ejected from the chute exhaust hole at a direction generally perpendicular to the inner surface.