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  • AIRCRAFT PROPULSION AND POWER  (5)
  • 1975-1979  (5)
  • 1945-1949
  • 1
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    Performance of a short annular dump diffuser using suction-stabilized vortices at inlet Mach numbers to 0.41 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short, annular dump diffuser was designed to use suction to establish stabilized vortices on both walls for improved flow expansion in the region of an abrupt area change. The diffuser was tested at near ambient inlet pressure and temperature. The overall diffuser area ratio was 4.0. The inlet height was 2.54 cm and the exit pitot-static rakes were located at a distance from the vortex fence equal to two or six times the inlet height. Performance data were taken at near ambient temperature and pressure for nominal inlet Mach numbers of 0.18 to 0.41 with suction rates of 0 to 18 percent of the total inlet airflow. The exit velocity profile could be shifted toward either wall by adjusting the inner- or outer-wall suction rate. Symmetrical exit velocity profiles were unstable, with a tendency to shift back to hub- or tip-weighted profile. Diffuser effectiveness was increased from about 47 percent without suction to over 85 percent at a total suction rate of about 14 percent. The diffuser total pressure losses at inlet Mach numbers of 0.18 and 0.41 decreased from 1.1 and 5.6 percent without suction to 0.48 and 5.2 percent at total suction rates of 14.4 and 5.6 percent, respectively.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1194 , E-9332
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Performance of a vortex-controlled diffuser in an annular swirl-can combustor at inlet Mach numbers up to 0.53 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short, annular dump diffuser with suction stabilized vortices in the region of abrupt area change was tested with a full scale, annular swirl can combustor. The prediffuser area ratio was 1.4. Performance data were obtained for both isothermal and burning conditions at inlet temperatures of 589 to 895 K and pressures of 0.5 to 1.0 MPa for a range of diffuser inlet Mach numbers from 0.25 to 0.53. Suction rates were 0 to 20 percent of the total diffuser mass flow rate. Diffuser effectiveness increased from 47 percent without suction to approximately 80 percent for a total suction rate of 14 percent. Combustor total pressure loss for the same total suction rate was reduced from 6.8 percent without suction to 4.0 percent at an inlet Mach number of 0.40.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1452 , E-9832
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Design and preliminary results of a semitranspiration cooled /Lamilloy/ liner for a high-pressure high-temperature combustor (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A Lamilloy combustor liner has been designed, fabricated and tested in a combustor at pressures up to 8 atmospheres. The liner was fabricated of a three layer Lamilloy structure and designed to replace a conventional step-louver liner. The liner will be used in a combustor that provides hot gases to a turbine cooling test facility at pressures up to 40 atmospheres. The Lamilloy liner was tested extensively at lower pressures and demonstrated lower metal temperatures than the conventional liner, while at the same time requiring about 40 percent less cooling air flow. Tests conducted at combustor exit temperatures in excess of 2200 K have not indicated any cooling or durability problems with the Lamilloy liner.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-997 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Design and preliminary results of a semitranspiration cooled (Lamilloy) liner for a high-pressure high-temperature combustor (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A Lamilloy combustor liner was designed, fabricated and tested in a combustor at pressures up to 8 atmospheres. The liner was fabricated of a three layer Lamilloy structure and designed to replace a conventional step louver liner. The liner is to be used in a combustor that provides hot gases to a turbine cooling test facility at pressures up to 40 atmospheres. The Lamilloy liner was tested extensively at lower pressures and demonstrated lower metal temperatures than the conventional liner, while at the same time requiring about 40 percent less cooling air flow. Tests conducted at combustor exit temperatures in excess of 2200 K have not indicated any cooling or durability problems with the Lamilloy linear.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78874 , E-9607 , Propulsion Conf.; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of high-area-ratio annular dump diffuser using suction-stabilized-vortex flow control (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short annular dump diffuser having a geometry conductive to formation of suction stabilized toroidal vortices in the region of abrupt area change was tested. The overall diffuser area ratio was 4.0 and the length to inlet height ratio was 2.0. Performance data were obtained at near ambient temperature and pressure for inlet Mach numbers of 0.18 and 0.30 with suction rates ranging from 0 to 18 percent of total inlet mass flowrate. Results show that the exit velocity profile could be readily biased toward either wall by adjustment of inner and outer wall suction rates. Symmetric exit velocity profiles were inherently unstable with a tendency to revert to a hub or tip bias. Diffuser effectiveness was increased from about 38 percent without suction to over 85 percent at a total suction rate of 10 to 12 percent. At the same time diffuser total pressure loss was reduced from 3.1 percent to 1.1 percent at an inlet Mach number of 0.3.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3535 , E-9011
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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