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)


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    Title :

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


    Contributors:

    Publication date :

    1969


    Size :

    74 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English