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  • 1
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    Combustion stabilization with acoustic cavities. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An experimental and analytical study has been performed to develop the technology necessary for effective use of acoustic cavities to suppress acoustic modes of combustion instability. An unbaffled variation of the LM ascent engine has been made dynamically stable with acoustic cavities only; five different cavity configurations were found sufficient to produce dynamic stability. An analytical model was developed to calculate the damping contributed by the cavity. Further, subscale tests were made to determine the nonlinear acoustic impedance of these cavities.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 8; Dec. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Analysis of combustion instability in liquid propellant engines with or without acoustic cavities (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical studies have been made of the relative combustion stability of various propellant combinations when used with hardware configurations representative of current design practices and with or without acoustic cavities. Two combustion instability models, a Priem-type model and a modification of the Northern Research and Engineering (NREC) instability model, were used to predict the variation in engine stability with changes in operating conditions, hardware characteristics or propellant combination, exclusive of acoustic cavity effects. The NREC model was developed for turbojet engines but is applicable to liquid propellant engines. A steady-state combustion model was used to predict the needed input for the instability models. In addition, preliminary development was completed on a new model to predict the influence of an acoustic cavity with specific allowance for the effects the nozzle, steady flow and combustion.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134387 , R-9353
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced acoustic cavity technology (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A series of rocket motor firings was performed in a modified linear aerospike thrust chamber with the H2/O2 propellant combination to allow determination of the physical properties of the combustion gases in acoustic cavities located in the chamber side walls. A preliminary analytical study was first conducted to define theoretically both the appropriate cavity dimensions and the combustion gas flow field adjacent to the cavity openings. During the subsequent motor firings, cavity gas temperature profiles were measured and gas samples were withdrawn from the bottom of the cavities for compositional analysis by measurement of pressure/temperature variation and gas chromatography. Data were obtained with both radially and axially oriented cavities and with and without hydrogen bleed flow through the cavities. A simplified procedure was developed for predicting gas cavity and acoustic velocity for use in acoustic cavity design analyses.
    Keywords: PHYSICS, GENERAL
    Type: NASA-CR-134388 , R-9136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Further analysis of the effects of baffles on combustion instability (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computerized analytical model, developed to predict the effects of baffles on combustion instability, was modified in an effort to improve the ability to properly predict stability effects. The model was modified: (1) to replace a single spatially-averaged response factor by separate values for each baffle compartment; (2) to calculate the axial component of the acoustic energy flux, and (3) to permit analysis of traveling waves in a thin annular chamber. Allowance for separate average response factors in each baffle compartment was found to significantly affect the predicted results. With this modification, an optimum baffle length was predicted which gave maximum stability.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NASA-CR-134832
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Analysis and computer programs to calculate acoustic wave properties of baffled chambers (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical methods and four computer programs have been developed for calculating wave motion in closed, baffled chambers with rigid and non-rigid boundaries. Application of these methods to design of injector-face baffles in liquid propellant engines will provide significant insight into effects of baffles on combustion stability.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LEW-11529
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Combustion stabilization with acoustic cavities (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Acoustic cavities use in suppressing acoustic modes of combustion instability demonstrated on LM ascent engine
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 70-618 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, PROPULSION JOINT SPECIALIST CONFERENCE, 6TH; Jun 15, 1970 - Jun 19, 1970; SAN DIEGO, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Analysis of the Wave Motion in Baffled Combustion Chambers (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: Variational-iterational technique for predicting wave motion and instability frequencies in baffled combustion chambers
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-72879 , R-8758 , GRC-E-DAA-TN19553
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    High-temperature earth-storable propellant acoustic cavity technology (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design criteria, methods and data, were developed to permit effective design of acoustic cavities for use in regeneratively cooled OME-type engines. This information was developed experimentally from two series of motor firings with high-temperature fuel during which the engine stability was evaluated under various conditions and with various cavity configurations. Supplementary analyses and acoustic model testing were used to aid cavity design and interpretation of results. Results from this program clearly indicate that dynamic stability in regeneratively cooled OME-type engines can be ensured through the use of acoustic cavities. Moreover, multiple modes of instability were successfully suppressed with the cavity.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA-CR-141688 , R-9401
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Space shuttle maneuvering engine reusable thrust chamber program. Task 11: Stability analyses and acoustic model testing data dump (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The combustion stability characteristics of engines applicable to the Space Shuttle Orbit Maneuvering System and the adequacy of acoustic cavities as a means of assuring stability in these engines were investigated. The study comprised full-scale stability rating tests, bench-scale acoustic model tests and analysis. Two series of stability rating tests were made. Acoustic model tests were made to determine the resonance characteristics and effects of acoustic cavities. Analytical studies were done to aid design of the cavity configurations to be tested and, also, to aid evaluation of the effectiveness of acoustic cavities from available test results.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-141676 , CT-74-13
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Evaluation of acoustic cavities for combustion stabilization Final report, 30 Jun. 1969 - 30 Jan. 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Stabilizing influence of acoustic cavities on acoustic modes of combustion instability in rocket engines
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-115087 , R-8757
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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