Accession Number : ADD011891

Title :   Resonant Cavities for Stall Recovery in Gas Turbine Engines.

Descriptive Note : Patent Application,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : French,

Report Date : 23 Jul 1985

Pagination or Media Count : 20

Abstract : The present patent application related generally to aircraft which use gas turbine engines as a means of propulsion, and specifically to a means for improvement in the stall recoverability characteristics of such gas turbine engines through the use of resonant cavities. The ability of gas turbine engines to recover when their compressors enter a rotating is enhanced with the accessing resonant cavity to the compressor exhaust port. The added volume of the resonant cavities induces a dynamically unstable operating point in the rotating stall as the cavity acts as a Helmholtz resonator matched with the dynamics of the primary flow. The resonant cavity is effective in enhancing the stall recovery characteristics of the engine.

Descriptors :   *PATENT APPLICATIONS, *GAS TURBINES, *STALLING, AIRCRAFT ENGINES, ACOUSTIC RESONATORS, MATCHING, ROTATION, COMPRESSORS, FLOW, RECOVERY, EXHAUST SYSTEMS, PORTS(OPENINGS), DYNAMICS, CAVITIES, RESONANCE

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE