Patent ID: 8082738

Claim:
A gas turbine engine, comprising: an axial flow compressor arranged along a longitudinal axis of a turbine that produces a compressed gas flow; an annular combustion chamber inclined radially inward in a downstream direction and having a rear wall segment inclined at a wall angle of at least 30° relative to the turbine longitudinal axis; a turbine that extracts mechanical energy from the compressed gas flow; and a diffuser located along the turbine longitudinal axis adapted to channel the gas flow from the compressor to the combustion chamber, comprising: a flow-dividing element formed by an inner deflecting flank and an outer deflecting flank that divides the compressed gas flow into two partial flows at a branching point, wherein a direction of each partial flow is changed by a respective deflecting flank, the two deflecting flanks defining: a tip angle of less than 90° along portions of the deflecting flanks that meet at a flow-dividing element tip, wherein the flow-dividing element tip defines the branching point, and a dividing angle between 15° and 90° between a tip angle bisecting line and the turbine longitudinal axis; a main deflecting region arranged upstream of the branching point and directed at an acute angle from the turbine longitudinal axis toward an inner combustion chamber shell.