Accession Number:

AD0915898

Title:

Multimission Aircraft Propulsion Simulator Initial Aero/Mechanical Test Results and Evaluation.

Descriptive Note:

Final rept. 1 Jul 71-30 Jun 73,

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP

Personal Author(s):

Report Date:

1973-12-01

Pagination or Media Count:

432.0

Abstract:

Initial aeromechanical 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 1rev 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 mixernozzle 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

Subject Categories:

  • Computer Programming and Software
  • Test Facilities, Equipment and Methods
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE