Empirical cooling correlation for an experimental afterburner with an annular cooling passage
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Koffel, William K↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine XII : Cooling Effectiveness of a Blade with an Insert and with Fins Made of a Continuous Corrugated Sheet
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Bartoo, Edward R↗
Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude I : liquid-cooling systems
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Schramm, Wilson B↗
Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude II : air-cooling systems
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Schramm, Wilson B↗
Mechanical Design Analysis of Several Noncritical Air-cooled Turbine Disks and a Corrugated-insert Air-cooled Turbine Rotor Blade
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Moseson, Merland L↗
Performance of Two Air-cooled Turbojet Engines Determined Analytically from Engine Component Performance for a Range of Cooling-air Weight Flows
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Ziemer, Robert R↗
Analysis of Factors Affecting Selection and Design of Air-cooled Single-stage Turbines for Turbojet Engines IV : Coolant-flow Requirements and Performance of Engines Using Air-cooled Corrugated-insert Blades
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Slone, Henry O↗
Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles
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Hubbartt, James E↗
Experimental Investigation of Effect of Cooling Air on Turbine Performance of Two Turbojet Engines Modified for Air-cooling
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Smith, Gordon T↗
Temperature drops through liquid-cooled turbine blades with various cooling-passage geometries
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Bartoo, Edward R↗
Cooling Characteristics of a Transpiration-cooled Afterburner with a Porous Wall of Brazed and Rolled Wire Cloth
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Koffel, William K↗
Method of Designing Corrugated Surfaces Having Maximum Cooling Effectiveness Within Pressure-drop Limitations for Application to Cooled Turbine Blades
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Slone, Henry O↗
Cooling Performance and Structural Reliability of a Modified Corrugated-insert Air-cooled Turbine Blade with an Integrally Cast Shell and Base
A modified corrugated-insert blade with integrally cast shell and base was developed. This blade was as light as a conventional fabricated corrugated-insert blade. Of four test blades operated in a full-scale turbojet engine, one failed after about 15 hours operation at an inlet gas temperature of 1670 degrees F, a coolant-flow ratio of 0.0064, and a 1/3-span centrifugal stress of approximately 28,000 psi. Three other test blades ran for approximately 16, 31, and 36 hours without failure at similar conditions.
Freche, John C↗
Cascade Investigation of Cooling Characteristics of a Cast-finned Air-cooled Turbine Blade for Use in a Turboprop Engine
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Stepka, Francis S↗
Flight and Test-stand Investigation of High-performance Fuels in Double-row Radial Air-cooled Engines I : Determination of Cooling Characteristics of Flight Engine
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Pragliola, Philip C↗
Flight and Test-stand Investigation of High-performance Fuels in Double-row Radial Air-cooled Engines II : Flight Knock Data and Comparison of Fuel Knock Limits with Engine Cooling Limits in Flight
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Werner, Milton↗
Flight and Test-stand Investigation of High-performance Fuels in Double-row Radial Air-cooled Engines III : Comparison of Cooling Characteristics of Flight and Test-stand Engines
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Dandois, Marcel↗
Flight and Test-stand Investigation of High-performance Fuels in Modified Double-row Radial Air-cooled Engines I : Determination of the Cooling Characteristics of the Flight Engine
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White, H Jack↗