Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 95
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.
Cooled High-Temperature Radial Turbine Program. Phase 2
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 95
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.
Publisher:
ISBN:
Category :
Languages : en
Pages : 95
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.
Cooled High-Temperature Radial Turbine
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781730936142
Category : Science
Languages : en
Pages : 98
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...
Publisher: Independently Published
ISBN: 9781730936142
Category : Science
Languages : en
Pages : 98
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...
Cooled Radial In-flow Turbines for Advanced Gas Turbine Engines
Author: J. M. Lane
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Paper presents the results of several Army-sponsored programs, the first of which addresses the performance potential for high-temperature radial turbine.
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Paper presents the results of several Army-sponsored programs, the first of which addresses the performance potential for high-temperature radial turbine.
High-Temperature Radial Turbine Demonstration
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 204
Book Description
The objective of this program was to provide and demonstrate the technology required to economically manufacture a cooled, high-temperature, radial turbine with sufficient integrity and aerodynamic performance to meet future Army requirements for a reliable, low-cost, high performance, small gas turbine engine. The work to accomplish this objective was subdivided into three phases. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 204
Book Description
The objective of this program was to provide and demonstrate the technology required to economically manufacture a cooled, high-temperature, radial turbine with sufficient integrity and aerodynamic performance to meet future Army requirements for a reliable, low-cost, high performance, small gas turbine engine. The work to accomplish this objective was subdivided into three phases. (Author).
Design and Evaluation of a High Temperature Radial Turbine
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Radial turbines offer greater stage work capacity than axial turbines. If this advantage can be coupled with a capability of accommodating high turbine inlet temperatures, radial turbines will permit appreciable simplification of small gas turbine engines for use in future Army vehicles. A two-phase program is being conducted involving the design and testing of a cooled, single-stage, radial inflow turbine. A bicast rotor with solid blades was spun to failure, which occurred at a speed lower than predicted. Two spindle failures prevented a successful destructive spin-test of the rotor damaged in Turbine Build One. The third and final nozzle section was chosen from the two castings submitted by the casting vendor for evaluation. An integral-cored rotor casting was not acceptable for rig test and is being evaluated for possible use as a spin-test part. Turbine Build One was hot tested for seven hours. Considerable foreign object damage was experienced by the turbine, and performance data is not believed to be representative of the turbine design. A replacement turbine rotor and nozzle were prepared and used in Turbine Build Two. Testing was aborted because of high vibrations caused by a turbine rotor-to-shroud rub during the initial stand checkout. Turbine Build Three is now in progress, using hardware salvaged from Build Two. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Radial turbines offer greater stage work capacity than axial turbines. If this advantage can be coupled with a capability of accommodating high turbine inlet temperatures, radial turbines will permit appreciable simplification of small gas turbine engines for use in future Army vehicles. A two-phase program is being conducted involving the design and testing of a cooled, single-stage, radial inflow turbine. A bicast rotor with solid blades was spun to failure, which occurred at a speed lower than predicted. Two spindle failures prevented a successful destructive spin-test of the rotor damaged in Turbine Build One. The third and final nozzle section was chosen from the two castings submitted by the casting vendor for evaluation. An integral-cored rotor casting was not acceptable for rig test and is being evaluated for possible use as a spin-test part. Turbine Build One was hot tested for seven hours. Considerable foreign object damage was experienced by the turbine, and performance data is not believed to be representative of the turbine design. A replacement turbine rotor and nozzle were prepared and used in Turbine Build Two. Testing was aborted because of high vibrations caused by a turbine rotor-to-shroud rub during the initial stand checkout. Turbine Build Three is now in progress, using hardware salvaged from Build Two. (Author).
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Development of high temperature turbine subsystem technology to a "technology readiness status".
Author: General Electric Company. Gas Turbine Division
Publisher:
ISBN:
Category :
Languages : en
Pages : 580
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 580
Book Description
Development of high temperature turbine subsystem technology to a "technology readiness status".
Author: General Electric Company. Gas Turbine Division
Publisher:
ISBN:
Category :
Languages : en
Pages : 332
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 332
Book Description
Development of High Temperature Turbine Subsystem Technology to a "technology Readiness Status" Phase II
Author: General Electric Company. Gas Turbine Division
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 208
Book Description
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 208
Book Description
The Design of an Air-cooled Metallic High Temperature Radial Turbine
Author: P.H. Snyder
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description