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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    Titel :

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


    Beteiligte:
    G. O. Berls (Autor:in) / J. F. Ensminger (Autor:in)

    Erscheinungsdatum :

    1969


    Format / Umfang :

    74 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch