Phase-resolved surface pressure, and unsteady pressure measurements are reported for the first-stage blade row of the Space Shuttle Main Engine two-stage fuel-side turbine. Measurements were made at 10, 50, and 90 percent span on both the pressure and suction surfaces of the blade. The relative magnitude of the heat-flux envelope was found to be significantly larger than the pressure envelope which is consistent with previous measurements. Measurements obtained at several different blade locations were presented to demonstrate that the ensemble average of the phase-resolved surface pressure data was well defined and the run-to-run variation at a given location on the blade was relatively small. Representative comparisons between the phase-resolved surface pressure and heat-flux were presented for two locations on the blade suction surface; one in the region of a favorable pressure gradient and the other in a region of an unfavorable pressure gradient. For this subsonic turbine, these two quantities are qualitatively in phase with each other.
Phase-resolved surface pressure and heat-transfer measurements on the blade of a two-stage turbine
Phasenaufgelöste Oberflächendruck- und Wärmeflußmessungen auf den Radschaufeln einer Zweistufenturbine
Transactions of the ASME, Series I. Journal of Fluids Engineering ; 117 , 4 ; 653-658
1995
6 Seiten, 12 Bilder, 2 Tabellen, 8 Quellen
Article (Journal)
English
Strahltriebwerk , Radschaufel , zweistufiger Verdichter , Druckmessung , Temperaturmessung , instationäre Strömung , Turbinenstufe , Raumfahrzeug , Wärmefluss , Versuchsdurchführung , Instrumentierung , Zeitverhalten , Phase (Schwingung) , Messergebnis , Frequenzbereich , Druckverhältnis , Fourier-Analyse , Raumfähre , Druckgradient
Phase-Resolved Surface Pressure and Heat-Transfer Measurements on the Blade of a Two-Stage Turbine
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