NASA NTRS · 19830000607
Radially-Graduated Turbine-Temperature Profile
Abstract
Proposed scheme to change temperature distribution in gas-turbine flame increases radially instead of remaining spatially uniform offers important advantages. Radially increasing temperature allows higher mean gas temperature, greater power output, higher rotational speed and longer life for blades. Principle suitable for axial-flow gas turbine directly in line with cylindrical combustor. Included in category many rocket, aircraft, stationary, and shipboard turbines.
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Wagner, W. R., Nitz, F. P., Strangeland, M. L.. 1984-11-01. Radially-Graduated Turbine-Temperature Profile. https://ntrs.nasa.gov/citations/19830000607
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