Experimental Evaluation of a Cooled Radial-inflow Turbine PDF Download
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Author: Lizet Tirres
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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Book Description
Author: Lizet Tirres
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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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: Glenn S. Calvert
Publisher:
ISBN:
Category : High temperatures
Languages : en
Pages : 224
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Book Description
The report describes the design, fabrication and test of a radial turbine designed to produce 219.6 Btu/lb stage work at 87.5% efficiency, with a 5:1 stage pressure ratio. Turbine inlet gas conditions at design point were 257.5 psia and 2300F. The resulting turbine configuration consisted of an air-cooled, 12-bladed rotor designed for 67,000 rpm, and a 20-vaned air-cooled nozzle section of a reflex-type (supersonic) design. Both parts were designed as IN100 (PWA 658) investment castings. As part of the preliminary design effort, a fabrication study was conducted to evaluate feasible methods of casting the turbine nozzle and rotor. Results showed that the nozzle section could be cast as an integral assembly, but fabrication of the rotor as an integral casting was much more difficult. Bicasting was evaluated as an alternate method of fabricating the rotor, and results showed substantial advantages for the bicasting technique. However, neither method could produce designed rotor properties, and testing was conducted with structurally limited rotors. A test rig was designed and fabricated by the contractor. The test rig consisted of a supercharged gas generator, which had the capability of controlling the turbine load by varying the compressor flow rate. Burner testing preceded turbine testing. (Author).
Author: Richard J. Roelke
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
An experimental performance evaluation was made of two moveable sidewall variable area radial turbines. The turbine designs were representative of the gas generator turbine of a variable flow capacity rotorcraft engine. The first turbine was an uncooled design while the second turbine had a cooled nozzle but an uncooled rotor. The design, fabrication and testing were carried out by Teledyne CAE under a series of government contracts. Performance measurements were taken over a turbine flow range of 2:1 in the Contractor's warm (121 C) air facility. The cooled nozzle turbine was evaluated both with and without coolant flow. The test results showed that the moveable nozzle wall is a viable and efficient means to effectively control the flow capacity of a radial turbine. Peak efficiencies of the second turbine with and without nozzle coolant were 86.5 and 88 percent respectively. These values are comparable to pivoting vane variable geometry turbines; however, the decrease in efficiency as the flow was varied from the design value was much less for the moveable wall turbine. The measured turbine performance over the entire flow range was within one point of the estimated turbine performance used in a previously conducted variable flow capacity engine analysis which showed significant fuel savings. Several design improvements were identified which should increase the turbine efficiency one or more points. These design improvements include reduced leakage losses and relocating the vane coolant ejection holes to reduce mainstream disturbance.
Author: Donald E. Holeski
Publisher:
ISBN:
Category : Brayton cycle
Languages : en
Pages : 26
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Book Description
Author: Milton G. Kofskey
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 16
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Book Description
Author: Samuel M. Futral
Publisher:
ISBN:
Category : Turbomachines
Languages : en
Pages : 28
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 492
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781730936142
Category : Science
Languages : en
Pages : 98
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Book Description
The objective of this program was the design and fabrication of a air-cooled high-temperature radial turbine (HTRT) intended for experimental evaluation in a warm turbine test facility at the LeRC. The rotor and vane were designed to be tested as a scaled version (rotor diameter of 14.4 inches diameter) of a 8.021 inch diameter rotor designed to be capable of operating with a rotor inlet temperature (RIT) of 2300 F, a nominal mass flow of 4.56 lbm/sec, a work level of equal or greater than 187 Btu/lbm, and efficiency of 86 percent or greater. The rotor was also evaluated to determine it's feasibility to operate at 2500 F RIT. The rotor design conformed to the rotor blade flow path specified by NASA for compatibility with their test equipment. Fabrication was accomplished on three rotors, a bladeless rotor, a solid rotor, and an air-cooled rotor. Snyder, Philip H. Unspecified Center...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 95
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Book Description
The objective of this program was the design and fabrication of a air-cooled high-temperature radial turbine (HTRT) intended for experimental evaluation in a warm turbine test facility at the Lewis Research Center. The rotor and vane were designed to be tested as a scaled version (rotor diameter of 14.4 inches diameter) of a 8.021 inch diameter rotor designed to be capable of operating with a rotor inlet temperature (RIT) of 2300 deg. F, a nominal mass flow of 4.56 lbm/sec, a work level of equal or greater than 187 Btu/lbm, and an efficiency of 86% or greater. The rotor was also evaluated to determine it's feasibility to operate at 2500 deg F RIT. The rotor design conformed to the rotor blade flow path specified by NASA for compatibility with their test equipment. Fabrication was accomplished on three rotors, a bladeless rotor, a solid rotor, and an air-cooled rotor.
