Accession Number : AD0705057

Title :   PERFORMANCE ANALYSIS OF A ROTARY NOZZLE UTILIZING A 30 DEG SPIN ANGLE ROTOR,

Corporate Author : NAVAL AIR PROPULSION TEST CENTER TRENTON N J AERONAUTICAL TURBINE DEPT

Personal Author(s) : Palcza,J. Lawrence

Report Date : APR 1970

Pagination or Media Count : 20

Abstract : Static thrust augmentation experiments have been performed with a rotary nozzle induction device to determine the effect of a large spin angle on performance. A 30 deg spin angle rotor with a shroud area to primary nozzle exit area ratio of 19.6 was tested over a primary to secondary pressure range of 1.2 to 1.8 at a primary-secondary temperature ratio of 1.0. (Author)

Descriptors :   (*TURBOJET ENGINES, *THRUST AUGMENTOR NOZZLES), ROTATION, DRAG, PRESSURE, FLOW SEPARATION

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE