17 research outputs found
Comparison of outside-surface heat-transfer coefficients for cascades of turbine blades
Get PDFA comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibly influence heat transfer, should be investigated
Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles
Get PDFAverage outside surface heat-transfer coefficients and velocity distributions for heated and cooled impulse turbine blades in static cascades
Get PDFAnalysis 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
Get PDFAnalysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines III : engine design-point performance
Get PDFMethod of Designing Corrugated Surfaces Having Maximum Cooling Effectiveness Within Pressure-drop Limitations for Application to Cooled Turbine Blades
Get PDFMethod for Rapid Determination of Pressure Change for One-Dimensional Flow with Heat Transfer, Friction, Rotation, and Area Change
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NACA Research Memorandums
No full textA comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibly influence heat transfer, should be investigated
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NACA Research Memorandums
No full textReport presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated
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NACA Research Memorandums
No full textReport presenting an analysis made to permit a comparative evaluation of the turbine rotor cooling-air requirements with convection-cooled blades for four combustor-outlet radial gas-temperature profiles: a uniform profile, a profile representable by a complete cycle of the cosine wave using cooler gas layers near the turbine casing, a profile representable by one-half cycle of the cosine wave using cooler gas layers near the stator inner ring, and an optimum profile resulting in the absolute minimum cooling-air requirements
