Entrainment of mainstream flow in a trapped-vortex combustor

Sturgess, G. J.; Hsu, Kuang–Yu

doi:10.2514/6.1997-261

Cited by 45 publications

(14 citation statements)

References 5 publications

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“…Burrus et al studied the double trapped vortex combustor at a slow air inlet using both JP-8 type fuel and DL-1 type fuel [2]. Hsu et al studied the combustion characteristics [7,6,5], entrainment of the mainstream [15], and fuel distribution of TVC [8]. Burrus and Roquemore presented the application of TVC for the main combustion chamber of gas turbine engines.…”

Section: Introductionmentioning

confidence: 97%

Experimental investigation of a single trapped-vortex combustor with a slight temperature raise

Xing¹,

Zhang²,

Wang³

et al. 2010

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 97%

Experimental investigation of a single trapped-vortex combustor with a slight temperature raise

Xing¹,

Zhang²,

Wang³

et al. 2010

Aerospace Science and Technology

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“…The first is the high-g combustor, 5,12,13 where the fuel and air are swirled in the cavity in the azimuthal direction (around the engine centerline). The second, a trapped-vortex UCC, [14][15][16] utilizes vortices that are trapped in the cavity and have an axis of rotation tangent to the circumference of the combustor. The combustion products from both of these cavity types exhaust into the combustor core flow, where the combustion process is completed.…”

Section: Introductionmentioning

confidence: 99%

Experimental Characterization of the Reaction Zone in an Ultra-Compact Combustor

Erdmann¹,

Burrus²,

Gross³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Significant benefits can be obtained with respect to engine thrust-to-weight ratio and specific fuel consumption if the length, weight, and pressure drop of the combustor can be reduced. The ultra-compact combustor (UCC) has the potential to aid the realization of these benefits by integrating neighboring components such as the compressor exit diffuser and the turbine inlet guide vanes (IGV) within the combustor using a systems-level engineering approach. The UCC presented here utilizes a trapped-vortex cavity. This combustor design has been shown to exhibit larger turn-down ratios, higher flame stability, shorter flame lengths, and acceptable NOx emissions when compared to conventional richburn, quick-quench, lean-burn combustors. The axial distance required to complete combustion within the mainstream dictates a minimum combustor length for obtaining acceptable levels of combustion efficiency. Hence, characterization of the reaction zone within a UCC is required to optimize the length. In this study OH* chemiluminescence imaging is used to assess the characteristics of the reaction zone via windows in the side and top of the combustor. CO, NOx, and total hydrocarbon (THC) emissions indices obtained with gas-sample probes at the exit of the combustor as well as computed combustion efficiencies are provided as a reference for the OH* chemiluminescence. Configurations with no turning vanes (CDF and CDF-2), with standard vanes (CDF-2SV), and with radialvane-cavity (RVC) vanes (CDF-2RV) were used. The first study shows that the CDF-2 configuration has similar combustion efficiencies compared to that of the previously studied CDF configuration between 0.6 1.1 but has a higher peak OH* intensity and higher window exit intensity than that of the CDF configuration. The second study shows that the addition of standard vanes to the UCC decreases the peak and exit OH* intensities and lowers the exit temperature peak to 30% height, while the addition of the RVC vane tends to increase the peak and exit OH* intensities and raise the exit temperature peak to 50% height. Nomenclature CDF = Combined diffuser-flameholder CH* = Electronically excited CH radicals CO = Carbon monoxide D = Cavity depth EICO = Emissions index of carbon monoxide EINO x = Emissions index of the oxides of nitrogen EITHC = Emissions index of total unburned hydrocarbons = Stoichiometric fuel-air ratio of JP-8 H = Height of combustor exit = Summation of normalized OH* intensity from the top window IGV = Inlet guide vane ITB = Inter-turbine burner L t = Axial length of turbine inlet vane ̇ = Mass flow of fuel ̇ = Total mass flow of air into the trapped-vortex cavity NO x = Oxides of nitrogen OH* = Electronically excited OH radicals OGV = Outlet guide vane RVC = Radial-vane-cavity T = Temperature T avg = Average temperature THC = Total unburned hydrocarbons TVC = Trapped-vortex combustor UCC = Ultra-compact combustor W = Width of cavity x = Downstream distance from CDF y = Vertical distance from top of cavity z = Spanwise distance from top window edge Greek Φ...

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“…Roquemore (1996,1998) performed numerical simulations and demonstrated (consistent with Little and Whipkey's results) that a stable vortex would be trapped in the cavity when the stagnation point was located at the downstream comer of the cavity. By analyzing the lean-blow-out data, Sturgess and Hsu (1997) found that the entrainment of the main annular flow into the cavity is minimal when a vortex is trapped inside the cavity.…”

Section: Introductionmentioning

confidence: 99%

Mixing and Combustion in Vortex Dominated Combustors with Distributed Air- and Fuel-Injection

Acharya¹,

Murphy²

1998

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Entrainment of mainstream flow in a trapped-vortex combustor

Cited by 45 publications

References 5 publications

Experimental investigation of a single trapped-vortex combustor with a slight temperature raise

Experimental investigation of a single trapped-vortex combustor with a slight temperature raise

Experimental Characterization of the Reaction Zone in an Ultra-Compact Combustor

Mixing and Combustion in Vortex Dominated Combustors with Distributed Air- and Fuel-Injection

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