Patent ID: 8419352

Claim:
A bypass turbojet engine comprising: an outer fan duct and an inner fan duct between which secondary flow passes; and a high pressure compressor including an outer casing including an upstream axial portion along bladed disks of the high pressure compressor and a downstream radial portion along an impeller and a diffuser of the high pressure compressor, wherein the inner fan duct is fastened on the outer casing, wherein the outer casing carries a plurality of axially symmetrical air-bleed chambers defined by annular ribs, a first upstream chamber being situated apart from the other chambers, the other chambers including a second intermediate chamber and a third downstream chamber, wherein the first chamber runs along a central segment of the axial portion of the outer casing and is defined by a first radial flange at a downstream end of the first chamber and a first substantially axially extending annular rib, wherein the second chamber runs along a downstream segment of the axial portion of the outer casing and is defined by a second radial flange at an upstream end of the second chamber, a second substantially axially extending annular rib, and a third annular rib, wherein the third chamber runs along an upstream segment of the radial portion of the outer casing and is defined by the third annular rib and a fourth annular rib, and wherein the first radial flange is disposed axially upstream of the second radial flange on the axial portion of the outer casing.