TECHNICAL PAPERS: Gas Turbines: Combustion and Fuel

Quantifying Fuel/Air Unmixedness in Premixing Nozzles Using an Acetone Fluorescence Technique

[+] Author and Article Information
J. H. Stufflebeam, D. W. Kendrick, W. A. Sowa

United Technologies Research Center, Aeromechanical, Chemical and Fluid Systems, 411 Silver Lane, East Hartford, CT 06108

T. S. Snyder

Pratt & Whitney, 400 Main Street, East Hartford, CT 06108

J. Eng. Gas Turbines Power 124(1), 39-45 (Mar 01, 1999) (7 pages) doi:10.1115/1.1396840 History: Received October 01, 1998; Revised March 01, 1999
Copyright © 2002 by ASME
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Snyder,  T. S., Rosfjord,  T. J., McVey,  J. B., Hu,  A. S., and Schlein,  B. C., 1996, “Emission and Performance of a Lean-Premixed Gas Fuel Injection System for Aeroderivative Gas Turbine Engines,” ASME J. Eng. Gas Turbines Power, 118, pp. 38–45.
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Grahic Jump Location
Normalized F/A distribution 6 mm from exit plane for different fuel distributions along the inlet slot length, rCB/rexit=0.47
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Mixing efficiency over range of fuel momentum ratios
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Normalized F/A distribution 6 mm from exit plane for different levels of fuel penetration, rCB/rexit=0.60
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Acetone PLIF experimental apparatus
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Air flow facility for acetone PLIF measurements. Laser sheet is 6 mm from nozzle exit plane. R, regulator; V, venturi; Rm, rotameter; P, pressure transducer; T, thermocouple.
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Main fuel distribution orifice arrays evaluated in mixing studies. When inserted in the nozzle, the downstream end of the fuel tube is to the right.
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Mixing efficiency over range of fuel momentum ratio for two different rCB/rexit
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F/A distribution 6 mm from exit plane of premixing nozzle with 15(8/7) main fuel orifice array for several levels of centerline pilot
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Emission results from SNR for rCB/rexit=0.47 and 15(8/7) fuel tubes
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Acoustic data from combustion tests of baseline and 15(8/7) orifice arrays with rCB/rexit=0.47 in the SNR
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Global Rayleigh indexes for both injection schemes at 15.6 atm, and five percent CL piloting



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