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  • 1
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    Development and operating characteristics of an advanced two-stage combustor (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 813, Accession no. A82-17833
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: (ISSN 0146-0412)
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Turbine engine Hot Section Technology (HOST) project (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Hot Section Technology (HOST) Project is a NASA-sponsored endeavor to improve the durability of advanced gas turbine engines for commercial and military aircraft. Through improvements in the analytical models and life prediction systems, designs for future hot section components , the combustor and turbine, will be more accurately analyzed and will incorporate features required for longer life in the more hostile operating environment of high performance engines.
    Keywords: STRUCTURAL MECHANICS
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 1-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Toward improved durability in advanced combustors and turbines - Progress in prediction of thermomechanical loads (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: NASA is sponsoring the Turbine Engine Hot Section Technology (HOST) Project to address the need for improved durability in advanced combustors and turbines. Analytical and experimental activities aimed at more accurate prediction of the aerothermal environment, the thermomechanical loads, the material behavior and structural responses to such loading, and life predictions for high temperature cyclic operation have been underway for several years and are showing promising results. Progress is reported in the development of advanced instrumentation and in the improvement of combustor aerothermal and turbine heat transfer models that will lead to more accurate prediction of themomechanical loads.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 86-GT-172
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Improved multiple-shot gun for use as a combustion stability rating device (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to develop and experimentally evaluate an improved version of a modified machine gun for use as a device for rating the relative combustion stability of various rocket combustors. Following the results of a previous study involving a caliber .30 machine gun, a caliber .50 machine gun was modified in order to extend the charge-size range of the device. Nitrocellulose charge sizes ranging from 1.004 to 9.720 grams were fired at rates up to four shots per second. Shock pressures up to 25,512 kN/sq m were measured near the end of a shortened gun barrel. A minimal resistance type of check valve permitted the gun to fire into pressurized regions; back pressures up to 3448 kN/sq m abs were tested. The final modified assembly was evaluated during combustion stability tests on rocket combustors burning a FLOX-methane propellant combination.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2792 , E-7287
    Format: application/pdf
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  • 5
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    Study of chugging instability with liquid- oxygen and gaseous-hydrogen combustors (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test firings and analytical model used to evaluate chugging instability in subscale experiments with LOX-gaseous hydrogen combustors
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-4005
    Format: application/pdf
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  • 6
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    Heat exchanger (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat exchanger, as exemplified by a rocket combustion chamber, is constructed by stacking thin metal rings having microsized openings therein at selective locations to form cooling passages defined by an inner wall, an outer wall and fins. Suitable manifolds are provided at each end of the rocket chamber. In addition to the cooling channel openings, coolant feed openings may be formed in each of rings. The coolant feed openings may be nested or positioned within generally U-shaped cooling channel openings. Compression on the stacked rings may be maintained by welds or the like or by bolts extending through the stacked rings.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: application/pdf
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  • 7
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    Some aspects of flox-methane rocket engine throttling (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Four injector designs and two chamber profiles were experimentally evaluated for structural integrity, combustion efficiency, and resistance to combustion instabilities. Vacuum thrust measurements were used as a primary measure of combustion efficiency. Stability rating to test the sensitivity of the injectors to high frequency combustion was conducted, but not extensively. To map the boundary between stable operation and chugging instability, chamber pressure was throttled downward from 689.5 to 206.9 kN/sq m abs (100 to 30 psia). Best operational results were obtained with an injector configuration having no hydraulic swirlers, a 0.00102-m (0.040-in.) recessed FLOX tube, and a nonflared exit in the methane annulus. This injector design exhibited stable combustion and good integrity of hardware, and it exceeded the design goal efficiency (88 percent) at the 10 to 1 throttled condition.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3094 , E-7911
    Format: application/pdf
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  • 8
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    Screech suppression techniques for rocket combustors using earth-storable propellants (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Injector baffles for flame stability in combustion chambers using nitrogen tetroxide and hydrazine mixture
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-1595
    Format: application/pdf
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  • 9
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    Rocket combustion instability. (1967)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Rocket combustion instability studied experimentally using theoretical model characterizing combustion by time lag and interaction index
    Keywords: PROPULSION SYSTEMS
    Type: SAINT LOUIS STUDENT CONFERENCE; May 08, 1966 - May 10, 1966; ST. LOUIS, MO
    Format: text
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  • 10
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    Characterization of pressure perturbations induced in a rocket combustor by a machine gun (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Characterization of pressure perturbations induced in rocket combustor by machine gun
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-5214
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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