Effect of Trapped Vortex Combustion with Radial Vane Cavity Arrangements on Predicted Inter-Turbine Burner Performance

Sekar, Balu; Thornburg, Hugh; Briones, Alejandro M.; Zelina, Joseph

doi:10.2514/6.2009-4603

Cited by 21 publications

(15 citation statements)

References 15 publications

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“…Due to the lack of experimental results available for these four configurations, similar trapped vortex combustor experiments [12,15,16,18] results is adopted in this work for model validation.…”

Section: Validation Of Numerical Resultsmentioning

confidence: 99%

“…These operating conditions were selected as provided in Ref. [12]. The fuel mass flow rate is 6.36 × 10 -4 kg/s and at 310 K. Mean diameter of the droplet size is 1.5 × 10 -2 mm.…”

Section: Boundary Condition and Meshingmentioning

confidence: 99%

“…However, the G loading in the circumferential cavity is inversely proportional to the radius of the circumferential cavity. The effectiveness of the high G operation and the corresponding benefits on flame speed will reduce if one needs to scale this concept for a larger spool of turbine components, and hence the performance will degrade [12]. In order to make a general TIB to replace the jet-swirl flow combustion, an alternate concept was proposed using a trapped vortex cavity [12][13][14] to enhance mixing rates via a jet-vortex flow in the cavity, followed by further mixing of the free stream air through the guide vane with a notch.…”

Section: Introductionmentioning

confidence: 98%

“…Reference [12] focused on three basic structures by using numerical simulation method and came to conclusions that the application of trapped vortex cavity for TIB can improve mixing and temperature distribution at the exit of the guide vane. References [13][14] dealt with ramps and convex dimples, placed on the guide vane and in the trapped vortex cavity to create additional vorticity to transport cavity air flow into the air main stream; however ramps and convex dimples are difficult to apply in practice.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Zheng

Tang

et al. 2014

International Journal of Turbo &Amp; Jet-Engines

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Four different secondary airflow angles for the turbine inter-guide-vane burners with trapped vortex cavity were designed. Comparative analysis between combustion performances influenced by the variation of secondary airflow angle was carried out by using numerical simulation method. The turbulence was modeled using the Scale-Adaptive Simulation (SAS) turbulence model. Four cases with different secondary jet-flow angles (-45°, 0°, 30°, 60°) were studied. It was observed that the case with secondary jet-flows at 60° angle directed upwards (1) has good mixing effect; (2) mixing effect is the best although the flow field distributions inside both of the cavity and the main flow passage for the four models are very similar; (3) has complete combustion and symmetric temperature distribution on the exit section of guide vane (X = 70 mm), with uniform temperature distribution, less temperature gradient, and shrank local high temperature regions in the notch located on the guide vane.

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Section: Validation Of Numerical Resultsmentioning

confidence: 99%

“…These operating conditions were selected as provided in Ref. [12]. The fuel mass flow rate is 6.36 × 10 -4 kg/s and at 310 K. Mean diameter of the droplet size is 1.5 × 10 -2 mm.…”

Section: Boundary Condition and Meshingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Zheng

Tang

et al. 2014

International Journal of Turbo &Amp; Jet-Engines

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“…Mawid M A promoted the mixing of gas and mainstream in the circumferential cavity by setting a radial vane cavity (RVC) on the UCC guide vanes [7,8]. Because of the conventional UCC performance decreasing with the increase of the main channel size, a rectangular structure based on the principle of cavity vortex combustion is proposed [9].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Increasing Number of Cavities in the Cavity

Guang-qi¹,

Guan²,

Chang³

et al. 2017

dtcse

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Abstract. The Interstage Turbine Burner (ITB) engine provide significantly higher specific thrust with no or only small increases in thrust specific fuel consumption substitute for conventional gas engine with after-burners. Continue combustion between a high pressure turbine stage and low pressure turbine stage is organized. Ultra-Compact Combustor (UCC), which is one of mainstream design concepts of ITB, has a broad application prospect in the field of aviation with the advantages of compact structure and high combustion efficiency. In order to improve the application of Ultra-Compact Turbine interstage combustor in aero-engine, the numerical simulation was carried out by using CFD technique to research on the influence of the number of cavities in the cavity on the ITB. The results show that the increasing number of structures of cavities in the cavity will enhance the circumferential cavity of the fuel and air mixing and burning, promote the combustion mixture to the mainstream radial transport capacity and improve combustion efficiency and uniformity of exit temperature field.

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Premixed Gas Mixing Performance of Lobe-Forced Mixer at Different Configurations

Wang

et al. 2022

J. Therm. Sci.

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Effect of Trapped Vortex Combustion with Radial Vane Cavity Arrangements on Predicted Inter-Turbine Burner Performance

Cited by 21 publications

References 15 publications

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Increasing Number of Cavities in the Cavity

Premixed Gas Mixing Performance of Lobe-Forced Mixer at Different Configurations

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