Experimental Evaluation of a 3.50-inch Radial Turbine Designed for a 10-kilowatt Space Power System PDF Download
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Author: Milton G. Kofskey
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 28
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Book Description
3.50 inch radial turbine designed for 10 kilowatt space power system.
Author: Milton G. Kofskey
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 28
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Book Description
3.50 inch radial turbine designed for 10 kilowatt space power system.
Author: Donald E. Holeski
Publisher:
ISBN:
Category : Brayton cycle
Languages : en
Pages : 26
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Book Description
Author: William J. Nusbaum
Publisher:
ISBN:
Category : Brayton cycle
Languages : en
Pages : 28
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Book Description
Author: Milton G. Kofskey
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 28
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Book Description
Author: Charles A. Wasserbauer
Publisher:
ISBN:
Category : Brayton cycle
Languages : en
Pages : 26
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Book Description
Author: Milton G. Kofskey
Publisher:
ISBN:
Category : Axial flow
Languages : en
Pages : 34
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Author: William J. Nusbaum
Publisher:
ISBN:
Category : Brayton cycle
Languages : en
Pages : 26
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Book Description
Author: Samuel M. Futral
Publisher:
ISBN:
Category : Turbomachines
Languages : en
Pages : 19
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722163693
Category :
Languages : en
Pages : 76
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Book Description
The aerodynamic evaluation of two highly loaded compact radial turbine rotors was conducted at the NASA Lewis Research Center Small Engine Component Test Facility (SECTF). The experimental results were used for proof-of-concept, for modeling radial inflow turbine rotors, and for providing data for code verification. Two rotors were designed to have a shorter axial length, up to a 10-percent reduced diameter, a lighter weight, and equal or higher efficiencies with those of conventional radial inflow turbine rotors. Three configurations were tested: rotor 1, having a 40-percent shorter axial length, with the design stator (stator 1); rotor 1 with the design stator vanes closed down (stator 2); and rotor 2, slightly shorter axially and having higher loading, with stator 2. The stator had 36 vanes and the rotors each had 14 solid blades. Although presently uncooled, the rotor blades were designed for thicknesses which would allow cooling passages to be added. The overall stage performance measurements and the rotor and stator exit flow field surveys were obtained. Measurements of steady state temperatures, pressures, mass flow rates, flow angles, and output power were made at various operating conditions. Data were obtained at corrected speeds of 80, 90, 100, 110, and 120 percent of design over a range of equivalent inlet-to-exit pressure ratios of 3.5, 4.0, 4.5, and 5.0, the maximum pressure ratio achieved. The test showed that the configuration of rotor 1 with stator 1 running at the design pressure ratio produced a flow rate which was 5.6 percent higher than expected. This result indicated the need to close down the stator flow area to reduce the flow. The flow area reduction was accomplished by restaggering the vanes. Rotor 1 was retested with the closed-down stator vanes and achieved the correct mass flow. Rotor 2 was tested only with the restaggered vanes. The test results of the three turbine configurations were nearly identical. Although the measured efficiencie...
Author: Harold E. Rohlik
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 38
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Book Description
