Turbine Nozzle Endwall Film Cooling Study Using Pressure-Sensitive Paint
- 1 February 2001
- journal article
- Published by ASME International in Journal of Turbomachinery
- Vol. 123 (4), 730-738
- https://doi.org/10.1115/1.1400113
Abstract
Endwall surface film cooling effectiveness was measured on a turbine vane endwall surface using the pressure-sensitive paint (PSP) technique. A double staggered row of holes and a single row of discrete slots were used to supply film cooling in front of the nozzle cascade leading edges. Nitrogen gas was used to simulate film cooling flow as well as a tracer gas to indicate oxygen concentration such that film effectiveness by the mass transfer analogy could be obtained. Cooling mass flow was controlled to be 0.5 to 3.0 percent of the mainstream mass flow. The free-stream Reynolds number was about 283,000 and Mach number was about 0.11. The free-stream turbulence intensity was kept at 6.0 percent for all the tests, measured by a thermal anemometer. The PSP was calibrated at various temperatures and pressures to obtain better accuracy before being applied to the endwall surface. Film effectiveness distributions were measured on a flat endwall surface for five different mass flow rates. The film effectiveness increased nonlinearly with mass flow rate, indicating a strong interference between the cooling jets and the endwall secondary flows. At lower mass flow ratios, the secondary flow dominated the near wall flow field, resulting in a low film effectiveness. At higher mass flow ratios, the cooling jet momentum dominated the near wall flow field, resulting in a higher film effectiveness. The comparison between hole injection and slot injection was also made.Keywords
This publication has 14 references indexed in Scilit:
- Effects of Slot Bleed Injection Over a Contoured End Wall on Nozzle Guide Vane Cooling Performance: Part II — Thermal MeasurementsPublished by ASME International ,2000
- Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I — Flow Field MeasurementsPublished by ASME International ,2000
- The Design of an Improved Endwall Film-Cooling ConfigurationJournal of Turbomachinery, 1999
- Aerodynamic Aspects of Endwall Film-CoolingJournal of Turbomachinery, 1997
- Heat Transfer Committee Best Paper of 1995 Award: Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo TechniqueJournal of Turbomachinery, 1996
- Experimental Contribution on the Significance and the Control by Transverse Injection of the Horseshoe VortexPublished by ASME International ,1996
- Film Cooling of the Gas Turbine Endwall by Discrete-Hole InjectionJournal of Turbomachinery, 1996
- Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1 — Experimental Technique and ResultsPublished by ASME International ,1991
- An Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbine NozzlesJournal of Turbomachinery, 1990
- Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane ShroudPublished by ASME International ,1990