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TECHNICAL PAPERS: Gas Turbines: Heat Transfer

Gas Turbine Engine Durability Impacts of High Fuel-Air Ratio Combustors—Part I: Potential for Secondary Combustion of Partially Reacted Fuel

[+] Author and Article Information
S. P. Lukachko, D. R. Kirk, I. A. Waitz

Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Eng. Gas Turbines Power 125(3), 742-750 (Aug 15, 2003) (9 pages) doi:10.1115/1.1584479 History: Received December 01, 2001; Revised March 01, 2002; Online August 15, 2003
Copyright © 2003 by ASME
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References

Figures

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Phenomenology of secondary combustion in the turbine. (Original engine and film cooling graphics from 19 and 20.)
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XCO,HH2,XOH,XO, and efficiency (ηb) at constant enthalpy and pressure equilibrium for lean and stoichiometric aviation fuel-air mixtures
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Representative current and future turbine flow compositions. (Portion of fuel energy represented by CO, HC, and/or H2 specified at 99%, 85%, and 73% for compositions 1 through 3. ηlocal reduced with changes in local T and P.)
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Potential local temperature rise. (Grayed area indicates thermodynamically incompatible T,P,X combinations.)
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Characteristic chemical time scales for turbine heat release for representative flow compositions. (Boxes represent median values and bracketed lines indicate ranges for a typical NGV flow space for a current era advanced engine.)
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ΔTT and Da comparing ignition and blade row traverse times for representative flow compositions. (Blank area indicates thermodynamically incompatible T,P,X combinations.)
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Turbulent diffusive mixing

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