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