Investigations of the Effect of Combustor Geometry and End Nozzle Flow on the Performance of GDL (Gas Dynamic Laser) Type Diffusers.
Final rept. 17 Jan-17 Jul 73,
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CONN
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An investigation was conducted to determine some of the performance characteristics of a high aspect ratio supersonic diffuser typical of those employed on gas dynamic laser devices. The experimental investigations were conducted in a sub-scale, cold flow test rig having the same Mach number and Reynolds number as the full scale Split Stage Demonstrator SSD. Experiments and analysis were performed to determine the effect on diffuser performance of variations of the flow duct geometry upstream of the nozzle array and the effect of increased flow rate through the end nozzles of the array. Diffuser performance was determined from experimental measurements of the pressures in the simulated combustor and at the diffuser exit. Modified author abstract
- Lasers and Masers
- Fluid Mechanics