PERFORMANCE ANALYSIS OF A ROTARY NOZZLE UTILIZING A 30 DEG SPIN ANGLE ROTOR,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1970
- Accession Number
- AD0705057
Entities
People
- J. Lawrence Palcza