Accession Number:

AD0705057

Title:

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

Descriptive Note:

Corporate Author:

NAVAL AIR PROPULSION TEST CENTER TRENTON N J AERONAUTICAL TURBINE DEPT

Personal Author(s):

Report Date:

1970-04-01

Pagination or Media Count:

20.0

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

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE