TY - CONF
T1 - Investigation of three dimensional flow field in a turbine including rotor/stator interaction part I
T2 - AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992
AU - Lakshminarayana, B.
AU - Camci, C.
AU - Halliwell, I.
AU - Zaccaria, M.
N1 - Funding Information:
Funding for thu facility was provided by the Department of Defence through the Instrumentation Pmpam (DAAL 03-86-G-0013), National Aeronautical Space Administration through the grant (NSG 5-666) and The Pennsylvania State University. The Teledyne Corporation was involved with the initial design of the facility and General Electric Company (Aircraft Engine Group) provided the design of blading and the flow path. A major facility such as this involves numerous organisations and individual who contributed fund. and assistance. Without their assistance the facility would not hove been completed. These individuals are: T. Doligalski and R. E. Singleton of the Army Research Office; K. Civinskas, R. Gauglsr, L. Povinelli, and J. Schwab of the NASA Lewis Research Center; J. Manshall and B. Niehaus. of Belcan Corporation; G. Sherman and G. Slough of West Milton, Inc.; T. Staub of Starwin Industries; L. H. Smith, M.Suo, and D. Wisler of General Electric Co., Aircraft Engine Group; G. Sayers, J. Fetterolf, H. Houts, of the Pennsylvania State University; J. Giles and D. Lawrence of Quality Aero Technology; R. Gray, T. Hajek and E. Rasinsky of Teledyne CAE Inc. These individuals, organisations, and authors of this report can be proud of a state-of-the-art facility which will be used to carry out aerodynamic and heat transfer research for the next generation of aircraft and spacecraft turbines.
PY - 1992
Y1 - 1992
N2 - A description of the Axial Flow Turbine Research Facility (AFTRF) installed at the Turbomachinery Laboratory of the Pennsylvania State University is presented in this paper. The facility diameter is 91.66 cm (3 feet) and the hub-to-tip ratio of the blading it 0.73. The flow path consist of turbulence generating grid, 23 nozzle vane and 29 rotor blade followed by outlet guide vanes. The blading design, carried out by General Electric Company personnel, embody modem HP turbine design philosophy, loading and flow coefficient, reaction, aspect ratio, and blade turning angles; all within the current aircraft engine design turbine practice. State-of-the-art quasi-3D blade design techniques were used to design the vane and the blade shapes. The vanes and blades are heavily instrumented with faat response pressure, shear stress, and velocity probes and have provision for flow visualisation and laser doppler anemometer measurement. Furthermore, provision has been made for detailed nozzle wake, rotor wake and boundary layer surveys. A 150 channel slip ring unit is used for transmitting the rotor data to a stationary instrumentation system. All the design objectives have been met.
AB - A description of the Axial Flow Turbine Research Facility (AFTRF) installed at the Turbomachinery Laboratory of the Pennsylvania State University is presented in this paper. The facility diameter is 91.66 cm (3 feet) and the hub-to-tip ratio of the blading it 0.73. The flow path consist of turbulence generating grid, 23 nozzle vane and 29 rotor blade followed by outlet guide vanes. The blading design, carried out by General Electric Company personnel, embody modem HP turbine design philosophy, loading and flow coefficient, reaction, aspect ratio, and blade turning angles; all within the current aircraft engine design turbine practice. State-of-the-art quasi-3D blade design techniques were used to design the vane and the blade shapes. The vanes and blades are heavily instrumented with faat response pressure, shear stress, and velocity probes and have provision for flow visualisation and laser doppler anemometer measurement. Furthermore, provision has been made for detailed nozzle wake, rotor wake and boundary layer surveys. A 150 channel slip ring unit is used for transmitting the rotor data to a stationary instrumentation system. All the design objectives have been met.
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M3 - Paper
AN - SCOPUS:85006070000
Y2 - 6 July 1992 through 8 July 1992
ER -