Investigation of three dimensional flow field in a turbine including rotor/stator interaction part I: Design development and performance of the research facility

B. Lakshminarayana; C. Camci; I. Halliwell; M. Zaccaria

Investigation of three dimensional flow field in a turbine including rotor/stator interaction part I: Design development and performance of the research facility

B. Lakshminarayana, C. Camci, I. Halliwell, M. Zaccaria

Aerospace Engineering

Research output: Contribution to conference › Paper

6 Scopus citations

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

All Science Journal Classification (ASJC) codes

Mechanical Engineering
Aerospace Engineering
Energy Engineering and Power Technology
Control and Systems Engineering
Electrical and Electronic Engineering

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Lakshminarayana, B., Camci, C., Halliwell, I., & Zaccaria, M. (1992). Investigation of three dimensional flow field in a turbine including rotor/stator interaction part I: Design development and performance of the research facility. Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States.

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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.",

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year = "1992",

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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

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AU - Zaccaria, M.

PY - 1992/1/1

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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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