Self stabilizing sonic inlet

Fluid handling – Processes – Cleaning – repairing – or assembling

Patent

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Details

244 53B, B64D 3302

Patent

active

041542568

ABSTRACT:
There is disclosed an air inlet for a turbine engine suitable for use on a short takeoff and landing (STOL), a vertical takeoff and landing (VTOL) or a conventional takeoff and landing (CTOL) type of aircraft. A critical region in which critical flow occurs under certain conditions communicates with a less critical region of lower static pressure. Air is drawn away from the critical region and reinjected into the air flow at the less critical region.
In one embodiment a circumferentially extended slot is provided in the inner surface of the air inlet at the windward side and downstream of the throat region. The slot communicates with a circumferential plenum chamber formed in the front of the air inlet just behind the lip. Circumferentially extending rows of apertures are provided on the lip establishing two sets of apertures spaced circumferentially away from the slot in opposite directions. The slot removes the boundary layer from the critical portion of the diffuser to minimize or eliminate flow pressure loss or separations resulting from diffusion or turning. The apertures are in a region of low static pressure on the lip of the inlet and serve as a source of suction to cause air flow into the slot.

REFERENCES:
patent: 2864236 (1958-12-01), Toure
patent: 3123285 (1964-03-01), Lee
patent: 3524458 (1970-08-01), Goldsmith

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