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  • 1
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    Combustion overview (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objective of this effort is to develop improved analytical models of the internal combustor flow field and liner heat transfer as a means to shorten combustor development time and increase turbine engine hot section life. A four-element approach was selected to meet this objective. First, existing models were utilized to determine their deficiencies. Supporting research was then commenced to improve the exisiting models. While the research effort is in progress, the models are being refined to improve numerics and numerical diffusion. And lastly, the research results and improved numerics will be integrated into existing models.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Turbine Engine Hot Section Technology, 1984; 6 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Component testing of a ground based gas turbine steam cooled rich-burn primary zone combustor for emissions control of nitrogeneous fuels (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This effort summarizes the work performed on a steam cooled, rich-burn primary zone, variable geometry combustor designed for combustion of nitrogeneous fuels such as heavy oils or synthetic crude oils. The steam cooling was employed to determine its feasibility and assess its usefulness as part of a ground based gas turbine bottoming cycle. Variable combustor geometry was employed to demonstrate its ability to control primary and secondary zone equivalence ratios and overall pressure drop. Both concepts proved to be highly successful in achieving their desired objectives. The steam cooling reduced peak liner temperatures to less than 800 K. This low temperature offers the potential of both long life and reduced use of strategic materials for liner fabrication. These degrees of variable geometry were successfully employed to control air flow distribution within the combustor. A variable blade angle axial flow air swirler was used to control primary zone air flow, while the secondary and tertiary zone air flows were controlled by rotating bands which regulated air flow to the secondary zone quench holes and the dilutions holes respectively.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-88873 , DOE/NASA/-13111/16 , E-3280 , NAS 1.15:88873
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Heat pipes to reduce engine exhaust emissions (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A fuel combustor is presented that consists of an elongated casing with an air inlet conduit portion at one end, and having an opposite exit end. An elongated heat pipe is mounted longitudinally in the casing and is offset from and extends alongside the combustion space. The heat pipe is in heat transmitting relationship with the air intake conduit for heating incoming air. A guide conduit structure is provided for conveying the heated air from the intake conduit into the combustion space. A fuel discharge nozzle is provided to inject fuel into the combustion space. A fuel conduit from a fuel supply source has a portion engaged in heat transfer relationship of the heat pipe for preheating the fuel. The downstream end of the heat pipe is in heat transfer relationship with the casing and is located adjacent to the downstream end of the combustion space. The offset position of the heat pipe relative to the combustion space minimizes the quenching effect of the heat pipe on the gaseous products of combustion, as well as reducing coking of the fuel on the heat pipe, thereby improving the efficiency of the combustor.
    Keywords: MECHANICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Techniques for enhancing durability and equivalence ratio control in a rich-lean, three-stage ground power gas turbine combustor (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Rig tests of a can-type combustor were performed to demonstrate two advanced ground power engine combustor concepts: steam cooled rich-burn combustor primary zones for enhanced durability; and variable combustor geometry for three stage combustion equivalence ratio control. Both concepts proved to be highly successful in achieving their desired objectives. The steam cooling reduced peak liner temperatures to less than 800 K. This offers the potential of both long life and reduced use of strategic materials for liner fabrication. Three degrees of variable geometry were successfully implemented to control airflow distribution within the combustor. One was a variable blade angle axial flow air swirler to control primary airflow while the other two consisted of rotating bands to control secondary and tertiary or dilution air flow.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-82922 , DOE/NASA/10350-33-E-1313 , NAS 1.15:82922
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Spontaneous ignition in afterburner segment tests at an inlet temperature of 1240 K and a pressure of 1 atmosphere with ASTM jet-A fuel (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A brief testing program was undertaken to determine if spontaneous ignition and stable combustion could be obtained in a jet engine afterburning operating with an inlet temperature of 1240 K and a pressure of 1 atmosphere with ASTM Jet-A fuel. Spontaneous ignition with 100-percent combustion efficiency and stable burning was obtained using water-cooled fuel spraybars as flameholders.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2952 , E-7560
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Factors affecting altitude relight performance of a double-annular ram-induction combustor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test program was conducted to evaluate the altitude relight capabilities of a short-length, double-annular, ram-induction combustor which was designed for Mach 3 cruise operation. The use of distorted inlet-air flow profiles was tried to evaluate their effect on the relight performance. No significant improvement in altitude relight performance was obtained with this approach. A study was also made to determine the effects of the reference Mach number, the fuel temperature, and the fuel volatility (ASTM-A1 against JP-4) on the altitude relight performance. Decreasing the reference Mach number, increasing the fuel temperature, and using more volatile fuel all decrease the combustor pressure necessary for relight.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2630 , E-6788
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effects of radial and circumferential inlet velocity profile distortions on performance of a short-length double-annular ram induction combustor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Inlet air velocity profile tests were conducted on a full-scale short-length 102-centimeter-diameter annual combustor designed for advanced gas turbine engine applications. The inlet profiles studied include radial distortions that were center peaked, and tip peaked, as well as a circumferential distortion which was center peaked for one-third of the circumference and flat for the other two-thirds. An increase in combustor pressure loss was the most significant effect of the radial air velocity distortions. With the circumferential distortion, exit temperature pattern factor doubled when compared to a flat velocity profile.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6706 , E-6464
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Space shuttle main engine definition (phase B). Volume 5: Valves and interconnects (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The steady state thermodynamic cycle balance of the single preburner staged combustion engine, coupled with dynamic transient analyses, dictated in detail the location and requirements for each valve defined in this volume. Valve configuration selections were influenced by overall engine and vehicle system weight and failure mode determinations. Modulating valve actuators are external to the valve and are line replaceable. Development and satisfactory demonstration of a high pressure dynamic shaft seal has made this configuration practical. Pneumatic motor driven actuators that use engine pumped hydrogen gas as the working fluid are used. The helium control system is proposed as a module containing a cluster of solenoid actuated valves. The separable couplings and flanges are designed to assure minimum leakage with minimum coupling weight. The deflection of the seal surface in the flange is defined by finite element analysis that has been confirmed with test data. The seal design proposed has passed preliminary pressure cycling and thermal cycling tests.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-120633 , PWA FR-4249-VOL-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of design features on performance of a double-annular ram-induction combustor (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An extensive test program was undertaken to determine the effect of many design features such as the size and number of air scoops, and the type of diffuser airflow distribution to use to optimize performance of a double-annular ram-induction combustor of 94 cm outer diameter. Six combustor configurations were tested. It was found that a snouted double annular combustor built with 256 ram-induction air scoops with a combustor open area giving a total pressure loss of 5.0 percent at a diffuser inlet Mach number of 0.25 gave the best overall performance of the configurations tested.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TN-D-7878 , E-8210
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Modifications that improve performance of a double annular combustor at simulated engine idle conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques were evaluated to determine if simple combustor modifications could be used to reduce the engine ground idle emissions of a double annular combustor designed for Mach 3.0 cruise operation. These techniques were radial fuel staging, the use of radial-inflow rather than axial-flow air swirlers, and the optimization of fuel-nozzle spray angle and differential pressure. Radial fuel staging and the use of radial-inflow air swirlers significantly improved performance at two ground idle test conditions simulating both low- and high-compression ratio engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3127 , E-7960
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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