Abstract
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.
| Original language | English (US) |
|---|---|
| State | Published - Jan 1 1992 |
| Event | AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 - Nashville, United States Duration: Jul 6 1992 → Jul 8 1992 |
Other
| Other | AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 |
|---|---|
| Country | United States |
| City | Nashville |
| Period | 7/6/92 → 7/8/92 |
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All Science Journal Classification (ASJC) codes
- Mechanical Engineering
- Aerospace Engineering
- Energy Engineering and Power Technology
- Control and Systems Engineering
- Electrical and Electronic Engineering
Cite this
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Investigation of three dimensional flow field in a turbine including rotor/stator interaction part I : Design development and performance of the research facility. / Lakshminarayana, B.; Camci, C.; Halliwell, I.; Zaccaria, M.
1992. Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States.Research output: Contribution to conference › Paper
TY - CONF
T1 - Investigation of three dimensional flow field in a turbine including rotor/stator interaction part I
T2 - Design development and performance of the research facility
AU - Lakshminarayana, B.
AU - Camci, C.
AU - Halliwell, I.
AU - Zaccaria, M.
PY - 1992/1/1
Y1 - 1992/1/1
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
ER -