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  • 1975-1979  (7)
  • 1
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    Measurements of reactive gaseous rocket injector admittances (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper describes the results of an experimental study of the quantitative determination of the capabilities of the combustion processes associated with coaxial gaseous propellant rocket injectors to drive combustor pressure oscillations. The data, obtained by employing the modified impedance tube technique with compressed air as the oxidizer and acetylene gas as the fuel, describe the frequency dependence of the admittance of the combined injector-combustion process. The measured data are compared with the predictions of the Feiler and Heidmann analytical model utilizing different values for the characteristic combustion time tau sub b. The values of tau sub b which result in a best fit between the measured and predicted data are indicated for different equivalence ratios. It is shown that for the coaxial injector investigated in this study the tau sub b varies between 0.7 and 1.2 msec for equivalence ratios in the range of 0.57 to 1.31. In addition, the experimental data indicate that the tested injector system could drive combustion instabilities over a frequency range that is in qualitative agreement with the predictions of the Feiler and Heidmann model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Combustion Science and Technology; 20; 5-6,; 1979
    Format: text
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  • 2
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    Measurements of admittances and characteristic combustion times of reactive gaseous propellant coaxial injectors (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental investigation that was concerned with the quantitative determination of the capabilities of combustion processes associated with coaxial injectors to amplify and sustain combustor oscillations was described. The driving provided by the combustion process was determined by employing the modified standing-wave method utilizing coaxial injectors and air-acetylene mixtures. Analyses of the measured data indicate that the investigated injectors are capable of initiating and amplifying combustion instabilities under favorable conditions of injector-combustion coupling and over certain frequency ranges. These frequency ranges and the frequency at which an injector's driving capacity is maximum are observed to depend upon the equivalence ratio, the pressure drop across the injector orifices and the number of injector elements. The characteristic combustion times of coaxial injectors were determined from steady state temperature measurements.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NASA-CR-159542
    Format: application/pdf
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  • 3
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    Characteristics of response factors of coaxial gaseous rocket injectors (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental investigation undertaken to determine the frequency dependence of the response factors of various gaseous propellant rocket injectors subject to axial instabilities are presented. The injector response factors were determined, using the modified impedance-tube technique, under cold-flow conditions simulating those observed in unstable rocket motors. The tested injectors included a gaseous-fuel injector element, a gaseous-oxidizer injector element and a coaxial injector with both fuel and oxidizer elements. Emphasis was given to the determination of the dependence of the injector response factor upon the open-area ratio of the injector, the length of the injector orifice, and the pressure drop across the injector orifices. The measured data are shown to be in reasonable agreement with the corresponding injector response factor data predicted by the Feiler and Heidmann model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-134788
    Format: application/pdf
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  • 4
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    Measurements of acoustic responses of gaseous propellant injectors (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Results are presented for an investigation intended to provide experimental data that can quantitatively describe the way in which various coaxial injector designs affect the stability of gaseous propellant rocket motors. The response factors of configurations that simulate the flow conditions in a gaseous-fuel injector element and a gaseous-oxidizer injector element are measured by using a modified impedance-tube technique and under cold-flow conditions simulating those observed in rocket motors with axial instability. The measured injector response factor data are presented and discussed. It is shown that there is reasonable agreement between the measured injector response factors and those predicted by the Feiler and Heidmann model (1967), and that the orifice length can be varied to shift the resonant frequency of the injector without any change in the magnitude of the response factor at resonance. A change in the injector open-area ratio is found to have a significant effect on the characteristics of the injector response factor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Sound and Vibration; 47; Aug. 22
    Format: text
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  • 5
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    Measurements of reactive gaseous rocket injector response factors (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results presented represent the first successful attempt at the measurement of the driving capabilities of coaxial gaseous propellant rocket injectors. The required data have been obtained by employing the modified impedance tube technique with compressed air as the oxidizer and acetylene gas as the fuel. The data describe the frequency dependence of the injector admittances, from which the frequency dependence of the injection response factors can be calculated. The measured injector admittances have been compared with the predictions of the Feiler and Heidmann (1967) analytical model assuming different values for the characteristic combustion time. The values of combustion time which result in a best fit between the measured and predicted data are indicated for different equivalence ratios. It is shown that for the coaxial injector system investigated in this study the characteristic combustion times vary between .7 and 1.2 msec for equivalence ratios in the range of .57 to 1.31. The experimental data clearly show that the tested injector system could indeed drive combustion instabilities over a frequency range that is in qualitative agreement with the predictions of the Feiler and Heidmann model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Spring Technical Meeting; Mar 28, 1977 - Mar 30, 1977; Cleveland, OH
    Format: text
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  • 6
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    Coaxial injector response to axial instability under simulated cold-flow (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The frequency dependence of the admittances and response factors of various gaseous rocket injector configurations subject to axial instabilities under cold-flow conditions, have been measured using the modified impedance-tube technique. The tested configurations simulate the flows in a gaseous-fuel injector, gaseous-oxidizer injector and a coaxial injector with both fuel and oxidizer elements. Comparison of the measured response data with corresponding data predicted by the Feiler and Heidmann model indicates good agreement between the two sets of data.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-230 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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  • 7
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    Driving of combustor oscillations by gaseous propellant injectors (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Measurements of reactive admittances that describe the capabilities of the combustion processes associated with coaxial gaseous fuel injectors to amplify combustor oscillations are presented. These admittances are needed in (1) stability analyses of rocket motors and gas turbine combustors; (2) for the evaluation of 'driving' capabilities of injectors; and (3) for checking the applicability of a theoretical model. The modified standing-wave technique was used to determine the admittances of the combustion processes in coaxial injectors utilizing air-acetylene mixtures. The measurements indicated that (1) coaxial injectors can sustain combustion instabilities over wide frequency ranges; (2) the maximum driving capability of an injector decreases with an increased equivalence ratio; (3) the frequency at which maximum driving is observed decreases with the increased equivalence ratio; and (4) the characteristic combustion time of an injector design decreases with increased frequency.
    Keywords: PROPELLANTS AND FUELS
    Type: Symposium /International/ on Combustion; Aug 20, 1978 - Aug 25, 1978; Leeds
    Format: text
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