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)
Evaluation of Acoustic Liners in 35,000 LBF Thrust Storable Propellant Rocket Engines
1969
74 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Rocket Propellants , Combustion & Ignition , Liquid propellant rocket engines , Acoustic insulation , Combustion chambers , Performance(Engineering) , Storable rocket propellants , Combustion , Stability , Injectors , Hypergolic rocket propellants , Suppressors , Nozzle area ratio , Damping , Heat flux , Acoustic liners , Storable propellant rocket engines