Patent ID: 8959926
Filing Date: 2015-02-24
Classification: F02C,F04D,F05D

Abstract:
1. A turbomachine or a bypass turbojet comprising: an intermediate casing arranged axially between a low pressure compressor and a high pressure compressor, the low pressure compressor and the high pressure compressor being housed within a primary annular air path that is surrounded by a secondary annular path, the intermediate casing including an inner wall forming a body of revolution defining an outside of the primary annular air path and an outer wall forming a body of revolution that defines the inside of the secondary annular path, the inner wall of the intermediate casing being fastened at its downstream end to an outer casing of the high pressure compressor, air bleed means for bleeding air downstream from the primary annular air path through the high pressure compressor, an outlet of the air bleed means being connected to air reinjection means for reinjecting air into an upstream portion of the high pressure compressor, wherein the air bleed means is connected to the air reinjection means by an annular manifold surrounding the inner wall of the intermediate casing upstream from the high pressure compressor and situated radially between said inner wall of the intermediate casing and the outer wall of the intermediate casing.