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

Personal Author(s) : Garrison,Gary D. ; Russell,P. L. ; Baldwin,C. D. ; Genchi,A. P. ; Presley,J. F.

Report Date : 28 AUG 1971

Pagination or Media Count : 152

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 N2O4/50% 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.

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, REGENERATIVE COOLING), (*COMBUSTION CHAMBERS, DAMPING), (*COMBUSTION CHAMBER LINERS, ACOUSTICS), (*COMBUSTION, STABILITY), COMBUSTION CHAMBER GASES, CAPTIVE TESTS, STABILIZATION, FUEL INJECTORS, HEAT TRANSFER, TETROXIDES, NITROGEN OXIDES, HYDRAZINE, DIMETHYL HYDRAZINE (1-1), VELOCITY, LIQUID ROCKET PROPELLANTS, COLD FLOW, CORRELATION TECHNIQUES, COMPUTER PROGRAMS (U) ORIFICES, SUBSONIC FLOW, RESONANCE ABSORPTION, REFRACTORY COATINGS, ACOUSTIC IMPEDANCE

Subject Categories : Acoustics
      Combustion and Ignition

Distribution Statement : APPROVED FOR PUBLIC RELEASE