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  • 1
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    OFF-DESIGN PERFORMANCE OF RADIAL INFLOW TURBINES (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: This program calculates off design performance of radial inflow turbines. The program uses a one dimensional solution of flow conditions through the turbine along the main streamline. The loss model accounts for stator, rotor, incidence, and exit losses. Program features include consideration of stator and rotor trailing edge blockage and computation of performance to limiting load. Stator loss (loss in kinetic energy across the stator) is proportional to the average kinetic energy in the blade row and is represented in the program by an equation which includes a stator loss coefficient determined from design point performance and then assumed to be constant for the off design calculations. Minimum incidence loss does not occur at zero incidence angle with respect to the rotor blade, but at some optimum flow angle. At high pressure ratios the level of rotor inlet velocity seemed to have an excessive influence on the loss. Using the component of velocity in the direction of the optimum flow angle gave better correlations with experimental results. Overall turbine geometry and design point values of efficiency, pressure ratio, and mass flow are needed as input information. The output includes performance and velocity diagram parameters for any number of given speeds over a range of turbine pressure ratio. The program has been implemented on the IBM 7094 and operates in batch mode.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: LEW-12500
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The NASA Lewis Research Center Internal Fluid Mechanics Facility (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental facility specifically designed to investigate internal fluid duct flows is described. It is built in a modular fashion so that a variety of internal flow test hardware can be installed in the facility with minimal facility reconfiguration. The facility and test hardware interfaces are discussed along with design constraints of future test hardware. The plenum flow conditioning approach is also detailed. Available instrumentation and data acquisition capabilities are discussed. The incoming flow quality was documented over the current facility operating range. The incoming flow produces well behaved turbulent boundary layers with a uniform core. For the calibration duct used, the boundary layers approached 10 percent of the duct radius. Freestream turbulence levels at the various operating conditions varied from 0.64 to 0.69 percent of the average freestream velocity.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-105187 , E-6487 , NAS 1.15:105187
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    NASA low-speed centrifugal compressor for 3-D viscous code assessment and fundamental flow physics research (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A low speed centrifugal compressor facility recently built by the NASA Lewis Research Center is described. The purpose of this facility is to obtain detailed flow field measurements for computational fluid dynamic code assessment and flow physics modeling in support of Army and NASA efforts to advance small gas turbine engine technology. The facility is heavily instrumented with pressure and temperature probes, both in the stationary and rotating frames of reference, and has provisions for flow visualization and laser velocimetry. The facility will accommodate rotational speeds to 2400 rpm and is rated at pressures to 1.25 atm. The initial compressor stage being tested is geometrically and dynamically representative of modern high-performance centrifugal compressor stages with the exception of Mach number levels. Preliminary experimental investigations of inlet and exit flow uniformly and measurement repeatability are presented. These results demonstrate the high quality of the data which may be expected from this facility. The significance of synergism between computational fluid dynamic analysis and experimentation throughout the development of the low speed centrifugal compressor facility is demonstrated.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 91-GT-140
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental investigation of a high subsonic mach number turbine having a 40-blade rotor with zero suction-surface diffusion (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Experimental investigation of high subsonic turbine with forty blade rotor with zero suction-surface diffusion
    Keywords: AERODYNAMICS
    Type: NACA-RM-E57J22
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Cold performance evaluation of a 4.59-inch radial-inflow turbine designed for a Brayton- cycle space power system (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Cold performance characteristics of small radial inflow turbine designed for Brayton cycle power system
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TN-D-3260
    Format: application/pdf
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  • 6
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    Cross spectra between temperature and pressure in a constant area duct downstream of a combustor (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The feasibility of measuring pressure temperature cross spectra and coherence and temperature-temperature cross spectra and coherence at spatially separated points along with pressure and temperature auto-spectra in a combustion rig was investigated. The measurements were made near the inlet and exit of a 6.44 m long duct attached to a J-47 combustor. The fuel used was Jet A. The cross spectra and coherence measurements show the pressure and temperature fluctuations correlate best at low frequencies. At the inlet the phenomena controlling the phase relationship between pressure and temperature could not be identified. However, at the duct exit the phase angle of the pressure is related to the phase angle of the temperature by the convected flow time delay. Previously announced in STAR as N83-23116
    Keywords: ACOUSTICS
    Type: AIAA PAPER 83-0762
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Comparison of turbine annulus mass flow computed by one- and two-dimensional analysis (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Variations in specific heat ratio, flow angle, critical velocity ratio, swirl distribution exponent, and radius ratio were considered in computing the mass flow. Variations in specific heat ratio had no significant effect and variations in critical velocity ratio had only small effect on computed mass flow between a one- and two-dimensional analysis. All non-free-vortex cases considered showed larger differences in computed mass flow between one- and two-dimensional analysis than for free vortex flow. For the non-free-vortex cases, decreasing radius ratio and increasing flow angle resulted in larger differences in mass flow as computed by the two methods.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-2661 , E-6909
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Experimental performance evaluation of a 4.59- inch radial-inflow turbine over a range of Reynolds number (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effect of Reynolds number on performance of 4.59-inch tip diameter radial inflow turbine
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-3835
    Format: application/pdf
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  • 9
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    Experimental performance evaluation of a radial-inflow turbine over a range of specific speeds (1966)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Radial-inflow turbine performance over range of specific speeds
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TN-D-3742
    Format: application/pdf
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  • 10
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    Experimental investigation of a high subsonic Mach number turbine having a 32-blade rotor with low suction-surface diffusion (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: High subsonic Mach number 32-blade rotor turbine with low suction-surface diffusion experiment to determine effect of low rotor blade solidity on losses
    Keywords: PROPULSION SYSTEMS
    Type: NASA-MEMO-10-2-58E
    Format: text
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