VENTILATION CHANNEL IN AFTERBURNER CHAMBER CONFLUENCE SHEET

摘要

PROBLEM TO BE SOLVED: To provide an aircraft turbo machine reducing danger of reverse flow and temperature gradient without changing a shape or length of a diffuser. SOLUTION: The turbo machine includes the diffuser 2. A casing and a confluence sheet form an annular channel 5. And the turbo machine includes an upstream fuel injector 6 and a flame catcher 7. The confluence sheet includes two bent parts spreading to the downstream side to decrease speed of primary flow F1 in the downstream side of the upstream injector 6. An annular scoop 11 is provided around an upstream part 10a of the confluence sheet 3 to extract an air flow F3 from a low temperature flow. The extracted air flow F3 is injected in a tangent direction of the primary flow F1 via a plurality of channels 12 formed on a wall part of the confluence sheet 3 between the scoop 11 and the diffuser 2. COPYRIGHT: (C)2005,JPO&NCIPI