HOT CYCLE ROTOR SYSTEM WHIRL TESTS
Abstract
The results of a 60 hr whirl test program conducted on the Hot Cycle Pressure Jet Rotor System is presented. The system is based on a principle wherein the exhaust gases from high pressure ratio turbojet engine(s) located in the fuselage are ducted through the rotor hub and blades and are exhausted through a nozzle at the blade tips. Forces thus produced drive the rotor. The structural feasibility of the system has been more than demonstrated by 60 hr of whirl testing accomplished with no significant problems. The final 25 hr of the whirl test program have been conducted with no substitution or alteration of any components. The spectrum of test conditions agrees very closely with the conditions called for in the military specifications for rotor and engine preflight tests. No dynamic problems have evidenced themselves, in confirmation of the prediction of no resonances in the operating rotor speed range. The measured temperatures for all components have been within design limits. The measured loads have generally been within design limits. The two primary parameters required to predict Hot Cycle performance, duct friction coefficient and nozzle velocity coefficient, have been verified.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1962
- Accession Number
- AD0290285
Entities
People
- K. B. Amer