Heat Transfer and Cooling in Gas Turbines
Abstract
Partial Contents: Rotating Heat Transfer on a Multipass Cooling Geometry; Pressure Drop and Heat Transfer Characteristics of Circular and Oblong Low Aspect Ratio Pin Fins; External Heat Transfer Study on a HP Turbine Rotor Blade; Effects of Wakes on the Heat Transfer in Gas Turbine Cascades; Effect of Hole Geometry, Wall Curvature and Pressure Gradient on Film Cooling Downstream of a Single Row; The Effect of Density Ratio on the Film-Cooling of a Flat Plate; Shroud Segments for Unshrouded Blade Turbines; Heat Transfer Test Evaluation of the Shell-Spar Blade Cooling Concept Applied to Industrial Gas Turbines; Heat-Flux Measurements and Analysis for a Rotating Turbine Stage; Calculation of Laminar-Turbulent Boundary Layer Transition on Turbine Blades; A Model for Correlating Flat Plate Film Cooling Effectiveness for Rows of Round Holes; Heat Transfer in Gas Turbine Combustors; Effectiveness Measurements for a Cooling Film Disrupted by a Single Jet with Wall Plunging; Full Coverage Impingement Heat Transfer: The Variation in Pitch to Diameter Ratio at a Constant Gap; The Measurement of Local Heat Transfer Coefficients in Blade Cooling Geometries; High Frequency Response Heat Flux Gauge for Metal Blading; Transient Thermal Behavior of a Compressor Rotor with Ventilation - Test Results under Simulated Engine Conditions; Heat Exchangers in Regenerative Gas Turbine Cycles.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1985
- Accession Number
- ADA162080
Entities
Organizations
- AGARD