Void fraction inference in cavitating fuel injector flows

Experimental data on the characteristics of the spray produced by a gas turbine engine airblast fuel injector are reported. The data acquired include the mass-flux distribution, measured by use of a high-resolution spray patternator; the gas-phase velocity field, measured by use of a two-component laser-Doppler velocimeter; and the liquid droplet size and velocity distributions, measured by use of a single-component phase-Doppler anemometer. The data are intended for use in assessments of two-phase flow computational methods as applied to combustor design procedures.

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Validation of LES Predictions of Scalar Mixing in High-swirl Fuel Injector Flows

Flow Turbulence and Combustion ◽

10.1007/s10494-011-9382-8 ◽

2011 ◽

Vol 88 (1-2) ◽

pp. 143-168 ◽

Cited By ~ 7

Author(s):

Liangta Cheng ◽

Mehriar Dianat ◽

Adrian Spencer ◽

James J. McGuirk

Keyword(s):

Scalar Mixing ◽

Fuel Injector ◽

Injector Flows

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Compressor Exit Conditions and Their Impact on Flame Tube Injector Flows

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.1383773 ◽

1999 ◽

Vol 124 (1) ◽

pp. 10-19 ◽

Cited By ~ 3

Author(s):

A. G. Barker ◽

J. F. Carrotte

Keyword(s):

Flow Field ◽

Axial Flow ◽

Test Facility ◽

Fuel Injector ◽

Turbine Engine ◽

Flame Tube ◽

Subsequent Effect ◽

Injector Flows ◽

Flow Compressor ◽

Combustion Processes

Within a gas turbine engine the flow field issuing from the compression system is nonuniform containing, for example, circumferential and radial variations in the flow field due to wakes from the upstream compressor outlet guide vanes (OGVs). In addition, variations can arise due to the presence of radial load bearing struts within the pre-diffuser. This paper is concerned with the characterization of this nonuniform flow field, prior to the combustion system, and the subsequent effect on the flame tube fuel injector flows and hence combustion processes. A mainly experimental investigation has been undertaken using a fully annular test facility which incorporates a single stage axial flow compressor, diffuser, and flame tube. Measurements have been made of the flow field, and its frequency content, within the dump cavity. Furthermore, the stagnation pressure presented to the core, outer and dome swirler passages of a fuel injector has been obtained for different circumferential positions of the upstream OGV/pre-diffuser assembly. These pressure variations, amounting to as much as 20 percent of the pressure drop across the fuel injector, also affect the flow field immediately downstream of the injector. In addition, general variations in pressure around the fuel injector have also been observed due to, for example, the fuel injector position relative to pre-diffuser exit and the flame tube cowl.

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Compressor Exit Conditions and Their Impact on Flame Tube Fuel Injector Flows

Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations ◽

10.1115/99-gt-238 ◽

1999 ◽

Cited By ~ 1

Author(s):

A. G. Barker ◽

J. F. Carrotte

Keyword(s):

Flow Field ◽

Axial Flow ◽

Test Facility ◽

Fuel Injector ◽

Turbine Engine ◽

Flame Tube ◽

Subsequent Effect ◽

Injector Flows ◽

Flow Compressor ◽

Combustion Processes

Within a gas turbine engine the flow field issuing from the compression system is non-uniform containing, for example, circumferential and radial variations in the flow field due to wakes from the upstream compressor outlet guide vanes (OGVs). In addition, variations can arise due to the presence of radial load bearing struts within the pre-diffuser. This paper is concerned with the characterisation of this non-uniform flow field, prior to the combustion system, and the subsequent effect on the flame tube fuel injector flows and hence combustion processes. A mainly experimental investigation has been undertaken using a fully annular test facility which incorporates a single stage axial flow compressor, diffuser and flame tube. Measurements have been made of the flow field, and its frequency content, within the dump cavity. Furthermore, the stagnation pressure presented to the core, outer and dome swirler passages of a fuel injector has been obtained for different circumferential positions of the upstream OGV/pre-diffuser assembly. These pressure variations, amounting to as much as 20% of the pressure drop across the fuel injector, also affect the flow field immediately downstream of the injector. In addition, general variations in pressure around the fuel injector have also been observed due to, for example, the fuel injector position relative to pre-diffuser exit and the flame tube cowl.

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