Measurement of Heat Flux and Pressure in a Turbine Stage.
Abstract
Selected portions of the first-stage stationary inlet nozzle, shroud, and rotor of the AiResearch TFE 731-2 turbine were instrumented with thin-film heat-transfer gages and heat-flux measurements were performed using a shock tunnel as a source of high-temperature, high-pressure gas. Experiments were performed over a range of Reynolds numbers, based on mid-annular stator chord, from 160,000 to 310,000 and corrected speeds from approximately 70% to 106%. The full-stage heat-flux results are cast in the form of a Stanton number and are then compared to previous measurements obtained with a stator only, in the absence of a rotor. The previous results are shown to be in good agreement with the full-stage data for the tip end-wall region, but the stator-only Stanton numbers for the stator airfoil are shown to be approximately 20% less than the corresponding full-stage results. Pressure measurements were obtained throughout the model and these results are shown to be in excellent agreement with the steady-state rig data for this turbine. Stanton-number results are also presented for the stationary shroud as a function of rotor mid-annular chord. The shroud Stanton-number data are shown to be in excess of the rotor blade results. Rotor-tip Stanton-number data are likewise shown to be slightly greater than the shroud results. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1981
- Accession Number
- ADA103539
Entities
People
- Michael G. Dunn
Organizations
- Calspan