Turbine vane coolant flow variations and calculated effects on metal temperatures
Abstract
Seventytwo aircooled turbine vanes were tested to determine coolant flow variations among the vanes. Calculations were made to estimate the effect of measured coolant flow variations on local vane metal temperatures. The calculations were based on the following assumed operating conditions: turbine inlet temperature, 1700 K (2600 F); turbine inlet pressure, 31 N/sq cm (45 psia); coolant inlet temperature, 811 K (1000 F); and total coolant to gas flow ratio, 0.065. Variations of total coolant flow were not large (about 10 percent from the arithmetic mean) for all 72 vanes, but variations in local coolant flows were large. The local coolant flow variations ranged from 8 to 75 percent, and calculated metal temperature variations ranged from 8 to 60 K (15 to 180 F).
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 June 1975
 Bibcode:
 1975STIN...7525098Y
 Keywords:

 Flow Distribution;
 Jet Vanes;
 Temperature Gradients;
 Turbojet Engines;
 Coolants;
 Gas Flow;
 Heat Transfer;
 Tables (Data);
 Fluid Mechanics and Heat Transfer