公开(公告)号：US20210054758A1

公开(公告)日：2021-02-25

申请号：US16934052

申请日：2020-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Guy D. SNOWSILL ,  Robert J. IRVING

IPC: F01D11/08 ,  F01D25/16 ,  F01D11/00 ,  F01D17/00 ,  F02C7/06 ,  F02C7/36

Abstract: A gas turbine is provided for an aircraft comprising an engine core and a core flow path, a fan, a front drum cavity arranged radially inward of the core flow path, and a front bearing chamber. The front drum cavity comprises a front drum inlet, for providing air to the front drum cavity from the core air flow, located downstream of a stage of the compressor, and a front drum outlet, for ejecting air from the front drum cavity to the fan air flow, located axially between the fan and the compressor. The front drum inlet is through a seal, and the front drum outlet is through a spaced gap.