Multimission Aircraft Propulsion Simulator Initial Aero/Mechanical Test Results and Evaluation.
Abstract
Initial aero/mechanical tests of the Multi-Mission Aircraft Propulsion Simulator were conducted in the AEDC R2C4 Test Cell of the engine test facility. A total of 38.1 hours of successful operation was completed. The simulator is designed with a compressor, turbine and mixer which result in the capability of simultaneously simulating scaled inlet airflow, nozzle pressure ratio and nozzle flow function which significantly improves scale model simulation. The simulator utilizes mass addition through a mixer from the spent turbine drive air to simulate heat addition. The physical size of the simulator represents a scale of from 6-10% of various aircraft engines thus, establishing the scale for installed performance aircraft models to be tested in wind tunnels. Aerodynamic and mechanical data obtained in this test included compressor and turbine mapping for compressor inlet pressures of 14.2, 12, and 6 psia. Also, one 180 deg. extent 1/rev distortion screen was tested where IDC ranged from 0.02 to .09. An analytical model has been developed to represent the simulator and a modification guide is included which gives procedures for modifying the mixer/nozzle to simulate other aircraft propulsion systems. Examples of typical aircraft engines which were simulated are included. Comprehensive mechanical data analysis and recommended follow-on development is included. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1973
- Accession Number
- AD0915898
Entities
People
- Bobby R. Delaney
- Har West
Organizations
- General Electric