A method of determining the temperature profile of a single-stage axial-flow turbine disk with uncooled blades is presented. The blade temperature is also estimated. Information required for the solution is: the gas properties and velocity entering the rotor, the blade and disk geometry, the blade fastening geometry, and the disk-to-shaft attachment geometry. Impingement disk cooling may be used. The temperature of the shaft at a point near the journal bearing mutt be assumed, but it is shown that this assumption is not critical. A stepwise numerical solution, suitable for either hand calculation or computer programming, is employed. The method may be extended to multi-stage turbines. A typical example is given and the effect of changing the radius of injection of the disk cooling air is shown.
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ASME 1967 Gas Turbine Conference and Products Show
March 5–9, 1967
Houston, Texas, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7988-7
PROCEEDINGS PAPER
A Rapid Approximate Method of Determining Axial-Flow Turbine Disk and Blade Temperatures
F. M. Simpson
F. M. Simpson
Ingersoll-Rand Company, Phillipsburg, NJ
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F. M. Simpson
Ingersoll-Rand Company, Phillipsburg, NJ
Paper No:
67-GT-14, V001T01A014; 8 pages
Published Online:
April 28, 2015
Citation
Simpson, FM. "A Rapid Approximate Method of Determining Axial-Flow Turbine Disk and Blade Temperatures." Proceedings of the ASME 1967 Gas Turbine Conference and Products Show. ASME 1967 Gas Turbine Conference and Products Show. Houston, Texas, USA. March 5–9, 1967. V001T01A014. ASME. https://doi.org/10.1115/67-GT-14
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