公开(公告)号：US11067035B2

公开(公告)日：2021-07-20

申请号：US16162860

申请日：2018-10-17

Applicant: ROLLS-ROYCE plc

Inventor： Edward C Gower ,  Paul R Davies

IPC: F02K1/82 ,  F02C7/18 ,  B64D33/04 ,  B64D33/08 ,  F02K1/38

Abstract: A gas turbine engine includes a main gas flow exhaust nozzle having an annular inner surface which, in use, bounds a flow of exhaust gas. The gas turbine engine further includes cooling passages having respective outlets therefrom to provide a flow of cooling air over a surface of the engine or an adjacent airframe component, thereby protecting the cooled surface from the exhaust gas flow. Adjacent cooling passages of the or each pair of the nested cooling passages are separated from each other by a respective dividing wall. The outlets from the nested cooling passages are staggered in the axial direction of the exhaust nozzle such that cooling air flowing out of an inner one of the adjacent cooling passages of the or each pair of the nested cooling passages flows over the dividing wall separating the adjacent passages.