Performance and Operating Characteristics of a Turbine Engine Propulsion Simulator at Simulated Flight Conditions
Abstract
An investigation was conducted on an engine propulsion simulator (S/N 002/2) to determine the compressor operating maps at compressor inlet pressures of 7, 12, and 16 psia at an inlet total temperature of 120 deg F with both dry and reheat mixer/nozzle configurations, to determine the dry and reheat nozzle entrance pressure and temperature distortion with the anti-distortion screens installed upstream of the nozzle, and to determine nozzle thrust and nozzle flow coefficients at simulated altitude/Mach number flight conditions of 12,700/0.6, 21,400/0.8, 24,800/0.9, 34,200/1.2, and 43,700/1.5 with both mixer/nozzle configurations. Compressor maps and nozzle performance are presented and compared with the predicted values. Nozzle entrance pressure and temperature distortions are presented. In addition, simulator operational experiences are discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1976
- Accession Number
- ADB011346
Entities
People
- J. O. Brooks
- R. A. Wasson Jr.
Organizations
- Arnold Engineering Development Complex