Turbulent velocity and temperature measurements from a gas-fueled technology combustor with a practical fuel injector

Combustion characteristics of a propane-fueled, practical injector operating in a burner that closely reproduces the flow patterns of a gas turbine combustor have been investigated. The practical injector converges co-swirling airsheets on either side of a coannular fuel sheet into the central air p...

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Bibliographic Details
Main Authors: Hedman, P.O, Warren, D.L.
Format: Conference Proceeding
Language:English
Subjects:
03 NATURAL GAS
330103 > Internal Combustion Engines-- Turbine
ADVANCED PROPULSION SYSTEMS
AIRCRAFT
ALKANES
BURNERS
CHEMICAL REACTIONS
COMBUSTION
FLAMES
FLUID FLOW
FLUID MECHANICS
FUEL INJECTION SYSTEMS
FUEL SYSTEMS
FUEL-AIR RATIO
GAS BURNERS
GAS FLOW
GAS TURBINES
HYDROCARBONS
HYDROXYL RADICALS
MACHINERY
MECHANICS
MORPHOLOGY
ORGANIC COMPOUNDS
OXIDATION
PROPANE
RADICALS
TEMPERATURE MEASUREMENT
THERMOCHEMICAL PROCESSES
TURBINES
TURBOMACHINERY 034000 > Natural Gas-- Combustion
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Summary:Combustion characteristics of a propane-fueled, practical injector operating in a burner that closely reproduces the flow patterns of a gas turbine combustor have been investigated. The practical injector converges co-swirling airsheets on either side of a coannular fuel sheet into the central air passage. Instantaneous planar-laser-induced fluorescence (PLIF) images of OH radical, laser doppler anemometer (LDA) measurements of mean and rms velocity, and coherent anti-Stokes Raman spectroscopic (CARS) measurements of mean and rms temperatures in the same burner at the same operating conditions have provided improved understanding of the complicated processes in a gas turbine combustor. The PLIF images of the OH radical have confirmed the vortex characteristics of the swirling flames and the highly variable nature of the flame shape as [phi] must lie between the lean and rich flammability limits for a flame to be locally present. Three recirculation zones were identified from LDA measurements. The highest axial velocity region is about 75 mm downstream for the fuel lean case, but is near the injector for the fuel rich case. The highest tangential velocities are located near the injector for both lean and rich cases. The effects of the injector on velocity were dissipated by one combustor diameter downstream. Large rms velocities occurred in areas where significant velocity gradients exist. The high temperatures changed location as the fuel equivalence ratio was varied from fuel lean (over the injector) to fuel rich (near the outer recirculation zone).
ISSN:0010-2180
1556-2921