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  • 1
    Electronic Resource
    Electronic Resource
    Noise from Aircraft Turbomachinery (1973)
    Palo Alto, Calif. : Annual Reviews
    Annual Review of Fluid Mechanics 5 (1973), S. 281-300 
    Details
    ISSN: 0066-4189
    Source: Annual Reviews Electronic Back Volume Collection 1932-2001ff
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1146/annurev.fl.05.010173.001433
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Noise from Aircraft Turbomachinery (1973)
    Annual Reviews
    Details
    Publication Date: 1973-01-01
    Print ISSN: 0066-4189
    Electronic ISSN: 1545-4479
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Annual Reviews
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    PAPER CURRENT
  • 3
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    Effects of rotation on impingement cooling of turbine blades (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effects of rotation on impingement cooling of turbine blades were studied experimentally as a specialized facility at M.I.T. A foil heated resistively was cooled by a jet flow on one side and temperature monitored on the other. Rotating the blade limits the heat transfer path to conduction through the support structure and radiation. IR radiometry furnishes the temperature distributions on the chamber wall, permitting the internal heat transfer coefficient to be measured. The heat transfer efficiency has been found to fall as much as 30 percent as rotational speed increases. The conditions observed confirm the significance of rotational effects, particularly with regard to potential early blade failure.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 85-1217
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Rotational effects on impingement cooling (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The present consideration of rotation effects on heat transfer in a radially exhausted, impingement-cooled turbine blade model gives attention to experimental results for Reynolds and Rossby numbers and blade/coolant temperature ratio values that are representative of small gas turbine engines. On the basis of a model that encompasses the effects of Coriolis force and buoyancy on heat transfer, bouyancy is identified as the cause of an average Nusselt number that is 20-30 percent lower than expected from previous nonrotating data. A heuristic model is proposed which predicts that the impingement jets nearest the blade roots should deflect inward, due to a centripetal force generated by their tangential velocity counter to the blade motion. Potentially serious thermal stresses must be anticipated from rotation effects in the course of blade design.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Exit flow from a transonic compressor rotor (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The three dimensional unsteady flow field behind a transonic compressor rotor with a design pressure ratio of 1.6 at a tip Mach number of 1.2 has been resolved on the blade passing time scale. Quantities determined were total and static pressures, tangential flow angle, and radial flow angle. The spatial and temporal resolution achieved was sufficient to determine velocity components inside individual blade wakes and in the surrounding flow. From these measurements the flow structure is described at stations immediately behind the rotor and one chord downstream. Some dominant features of the flow just behind the rotor are large radial velocity components, large static pressure fluctuations near the blade wakes, and definite unsteadiness (in rotor coordinates) of the wakes. The wake behavior one chord downstream is described in terms of the effect of the strong mean swirl on the behavior of shear disturbances. In the outer portion of the annulus, where the mean flow approximates a solid body rotation, a strong, persistent oscillatory flow is found with 16 periods in the circumference as roughly predicted by theory. In the inner portion of the annulus the disturbances attenuate axially.
    Keywords: AERODYNAMICS
    Type: AGARD Unsteady Phenomena in Turbomachinery; 23 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Time resolved measurements in a low aspect ratio transonic compressor stage (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The time resolved flowfield in a low aspect ratio transonic compressor stage has been studied using a high frequency response sphere probe with a bandpass of D.C. to 20 kHz in a blowdown compressor facility. Averaged over the compressor annulus, the data agree well with those measured with standard pitot type probes on the same stage in a conventional test rig. Not all the spanwise distributions agree, however. These differences are explained as errors in the pitot probe readings due to fluctuations in the flow. The experimental data are compared to the results of a three-dimensional inviscid Euler calculation.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 82-GT-201 , International Gas Turbine Conference and Exhibit; Apr 18, 1982 - Apr 22, 1982; London
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    A miniature high frequency sphere probe (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A spherical probe having five surface mounted silicon pressure sensors is described. The probe is 0.2 inches in diameter yielding a frequency response above 30 kHz. A scheme is described for retrieving from the five pressure signals the stagnation and static pressures, Mach number and flow angles in two planes. The calibrations forming the base for this procedure, obtained from steady state tests, are given in the form of polynomials in the two flow angles. A method for compensating the silicon pressure sensors for thermal effects is given. Typical data obtained in the MIT Blowdown Compressor are presented in raw form and after reduction to flow angles, Mach number and stagnation pressure.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Measurement methods in rotating components of turbomachinery; Mar 10, 1980 - Mar 13, 1980; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Shock structure in transonic compressor rotors (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The inadequacy of axisymmetric theory in modeling the structure of the shock system in a transonic compressor rotor is shown with a simple model. A more accurate model for the flow near the sonic radius is proposed, which is supported by some flow visualization data and three-dimensional computations.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 17; Apr. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    An acoustic instability driven by absorption of radiation in gases (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustic instability driven by thermal radiation absorption in extremely high temperature gases
    Keywords: PHYSICS, PLASMA
    Type: CSR-T-69-4 , FLORIDA UNIV. RES. ON URANIUM PLASMAS AND THEIR TECHNOL. APPL. 1971; P 135-137
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Energy conversion research (1966)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design, operation, and evaluation of large, segmented electrode nonequilibrium magnetohydrodynamic generator
    Keywords: PHYSICS, PLASMA
    Format: text
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    NASA TECHNICAL REPORTS
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