Design and Development of a Turbine Research Facility to Study Rotor-Stator Interaction Effects

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

Research output: Contribution to journalArticle

29 Citations (Scopus)

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 is 0.73. The flow path consists of turbulence generating grid, 23 nozzle vanes and 29 rotor blades followed, by outlet guide vanes. The blading design, carried out by General Electric Company personnel, embodies modern HP turbine design philosophy, loading and flow coefficient, reaction, aspect ratio, and blade turning angles, all within 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 fast response pressure, shear stress, and velocity probes and have provision for flow visualization 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.

Original languageEnglish (US)
Pages (from-to)155-172
Number of pages18
JournalInternational Journal of Turbo and Jet Engines
Volume13
Issue number3
StatePublished - Dec 1 1996

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Stators
Turbines
Rotors
Nozzles
Aircraft engines
Turbomachinery
Axial flow
Anemometers
Flow visualization
Turbomachine blades
Shear stress
Aspect ratio
Boundary layers
Turbulence
Personnel
Lasers
Industry

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

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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 is 0.73. The flow path consists of turbulence generating grid, 23 nozzle vanes and 29 rotor blades followed, by outlet guide vanes. The blading design, carried out by General Electric Company personnel, embodies modern HP turbine design philosophy, loading and flow coefficient, reaction, aspect ratio, and blade turning angles, all within 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 fast response pressure, shear stress, and velocity probes and have provision for flow visualization 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.",
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Design and Development of a Turbine Research Facility to Study Rotor-Stator Interaction Effects. / Lakshminarayana, B.; Camci, Cengiz; Halliwell, I.; Zaccaria, M.

In: International Journal of Turbo and Jet Engines, Vol. 13, No. 3, 01.12.1996, p. 155-172.

Research output: Contribution to journalArticle

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