TURBOJET ENGINE Russian patent published in 2009 - IPC F01D25/24 

FIELD: engines and pumps.

SUBSTANCE: turbojet engine comprises a high-pressure compressor, a diffuser and a combustion chamber. The high-pressure compressor incorporates an outer ring to radially constrict the primary flow channel that is jointed to ring-like structure extending radially outward. The diffuser comprises an outer casing jointed to the tapered support directed backward and constricting the combustion chamber from above. Note that the support is jointed to outer ring of the casing locked on the ring-like structure extending by clamping elements. The aforesaid support, casing outer ring and ring-like structure form the space between the diffuser. Note that air intake holes are made in the support, while the casing outer ring is furnished with outlet air intake holes. There is a pipe arranged between the said two groups of holes. The pipe first end is fitted in the outlet air intake hole pivoted thereto to rotate with no axial travel. The pipe second end is installed pivoted to the air intake hole to rotate and move therein.

EFFECT: compressor bleed with seal over diffuser space.

9 cl, 6 dwg