Accession Number:

AD0517006

Title:

Acoustic Liner Design and Demonstration.

Descriptive Note:

Final rept. 15 Nov 68-30 Apr 71,

Corporate Author:

PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FLA FLORIDA RESEARCH AND DEVELOPMENT CENTER

Report Date:

1971-08-28

Pagination or Media Count:

152.0

Abstract:

The objectives of this two-phase exploratory development program were 1 to demonstrate the effectiveness for suppressing combustion instability of a regeneratively cooled acoustic liner installed in flight-type hardware, and 2 to extend the acoustic liner design theory to include rocket chamber applications with high combustion gas velocities and high dynamic pressure amplitudes. Phase I consisted of the design, fabrication and firing of a fuel cooled, 15,000 lb thrust chamber incorporating an integral acoustic liner, using an injector known to be dynamically unstable with N2O450 N2H4-50 UDMH propellants. Before fabrication of the chamber was initiated, adequate suppression characteristics of the liner design were demonstrated in short duration tests of uncooled hardware. The uncooled test series included firings during which both the baseline heat transfer rates and the effects of liner apertures on the heat transfer rates were measured. Other uncooled firings were conducted to measure the dynamic stability characteristics of the potential flightweight liner design, to determine the minimum required liner length, and to supply data for the final liner design. Thirty uncooled firings and thirteen firings of the regeneratively cooled chamber were made combustion in the regeneratively cooled chamber was demonstrated to be dynamically stable.

Subject Categories:

  • Acoustics
  • Combustion and Ignition
  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE