Accession Number : AD0865411

Title :   Evaluation of Acoustic Liners in 35,000 LBF Thrust Storable Propellant Rocket Engines.

Descriptive Note : Final rept. Nov 65-Sep 67, 9

Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF

Personal Author(s) : Berls,George O. ; Ensminger,James F.

Report Date : OCT 1969

Pagination or Media Count : 74

Abstract : An evaluation was made of the effectiveness of acoustic liners in a 35,000-lb-thrust, storable propellant rocket engine. Fifty-two tests were accomplished using three different open area ratio liners. Testing was conducted at chamber pressures of 300 and 600 psia over a mixture ratio range of 1.8 to 2.2 with the N2O4/Aerozine-50 propellant combination. The three acoustic liners were evaluated in conjunction with four injection patterns, a like doublet and three variations of an oxidizer-fuel-oxidizer triplet. The pulse gun stability-rating technique was used to artificially perturb the combustion process. The resultant disturbance was recorded by high-frequency-response pressure transducers. The effectiveness of the acoustic liner was then evaluated by comparing the stability results of the liner tests with those of baseline tests. (Author)

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, ACOUSTIC INSULATION), (*COMBUSTION CHAMBERS, ACOUSTIC INSULATION), (*ACOUSTIC INSULATION, PERFORMANCE(ENGINEERING)), STORABLE ROCKET PROPELLANTS, COMBUSTION, STABILITY, INJECTORS, HYPERGOLIC ROCKET PROPELLANTS, SUPPRESSORS, NOZZLE AREA RATIO, DAMPING, HEAT FLUX

Subject Categories : Combustion and Ignition
      Liquid Propellant Rocket Engines
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE