Performance of supersonic model combustors with staged injections of supercritical aviation kerosene

Zhong, Fengquan; Fan, Xuejun; Gong, Yu; Li, Jianguo; Sung, Chih-Jen

doi:10.1007/s10409-010-0367-y

Cited by 9 publications

(5 citation statements)

References 7 publications

(12 reference statements)

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“…Recently, the staged fuel injection scheme has become a hot spot for the airbreathing hypersonic propulsion system [21][22][23] for it can improve the overall combustion performance of the scramjet combustor. Lai et al 24 have formulated a general sink-doublet model to predict the interaction of multiple tandem jets in a cross flow, and the predicted jet trajectory shows very good agreement with the experimental data.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Huang

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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The staged injection scheme has drawn an increasing attention for the airbreathing hypersonic propulsion system, and the fuel injection angle has a large impact on the mixing improvement between the fuel and the supersonic cross flow. The Reynolds-averaged Navier-Stokes equations associated with the SST k-! turbulence model have been employed to investigate the interaction mechanism in the staged sonic injection flow field, and the influences of the injection angle, the injection angle arrangement, and the distance between the injectors on the flow field characteristics have been analyzed comprehensively. At the same time, three grid scales have been used to perform the grid independency analysis, and the predicted results have been compared with the experimental data in the open literature for the single transverse injection scheme. The obtained results show that the penetration height for the cases with the distance between the injectors being 1 mm is the highest in the range considered in the current study, and this may be due to the strongest shock wave/shock wave interaction between the injectors. At the same time, due to the blockage of the fuel injection, the penetration height increases as the supersonic air stream flows downstream, and the influence of the wave system generated by the first and third injectors cannot propagate downstream and upstream, respectively. The multi-port injection scheme can provide better fuel penetration performance than the single one when the flow flux keeps constant, and the multi-port injection scheme with a certain angle can provide a higher total pressure recovery efficiency than the staged transverse injection scheme. Further, the staged transverse injection flow field can provide a better recirculation zone for the mixing between the fuel jet and the boundary layer, and the separation length increases with the increase of the distance between the injectors.

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Section: Introductionmentioning

confidence: 99%

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Huang

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Norris [6] and Huang et al [7] proved the feasibility of using heated kerosene to improve the thrust. Recent experimental investigations [8][9][10] demonstrated that the use of supercritical kerosene injection holds the potential of enhancing fuel-air mixing and promoting overall burning in comparison with liquid fuel injections at similar fuel flow rates. However, a further increase in the fuel flow rate and the pressure rise with the singlestage injection was limited by the upstream propagation of boundary-layer separation due to excessive heat release [10].…”

mentioning

confidence: 99%

“…Recent experimental investigations [8][9][10] demonstrated that the use of supercritical kerosene injection holds the potential of enhancing fuel-air mixing and promoting overall burning in comparison with liquid fuel injections at similar fuel flow rates. However, a further increase in the fuel flow rate and the pressure rise with the singlestage injection was limited by the upstream propagation of boundary-layer separation due to excessive heat release [10]. The idea of staged fuel injection [11][12][13] uses the combustion of an upstream-injected fuel to improve the mixing and burning processes of the downstream-injected fuel while still keeping the fuel flow rate through the upstream injectors below the allowable value.…”

mentioning

confidence: 99%

Experimental Investigation of Supersonic Model Combustor with Distributed Injection of Supercritical Kerosene

Sun

Zhong

Liang

et al. 2014

Journal of Propulsion and Power

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Supersonic combustion with distributed injection of supercritical kerosene in a model scramjet engine was experimentally investigated in a Mach 2.92 facility with stagnation temperatures of approximately 1430 K. Multicavities were used to stabilize and enhance the combustion in the supersonic combustor. Supercritical kerosene at temperatures of approximately 780 K was prepared using a heat exchanger driven by the hot gas from a preburner and injected into the combustor at equivalence ratios of 1.0. Static pressure distribution in the axial direction was measured along the centerline of the model combustor top walls. A high-speed imaging camera was used to capture flame luminosity and combustion region distribution. In the experiments, combustor performances with different injection locations, injection stages, cavity locations, and numbers of cavities were investigated systematically. The experimental results showed that the injection penetration and local combustion had a strong coupling with the upstream flow. The combustion region and heat release distribution changes obviously due to the various cavityinjection schemes, and the combustion performance could be improved when the injection location and distribution of supercritical kerosene mass flow rate were optimized. Nomenclature A= cavity rear wall angle Bn = nth cavity on bottom wall of the scramjet combustor Bnf = injection set upstream of the cavity Bn front wall D = cavity depth L = cavity length LD = cavity length-to-depth ratio Ma = Mach number P 0i = stagnation pressure of the supercritical kerosene Tn = nth cavity on top wall of the scramjet combustor Tnf = injection set upstream of the cavity Tn front wall Tnr = injection set downstream of the cavity Tn rear wall T 0i = stagnation temperature of the supercritical kerosene ψ = equivalence ratio

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“…Refs. [33,34]). If considering only high-temperature chemistry (> 900 K), such skeletal mechanisms can be further reduced.…”

Section: Skeletal Mechanism Of N-alkanes With Low-temperature Chemistrymentioning

confidence: 99%

“…Refs. [33,34]). Figure 8 indicates that the 72-species skeletal mechanism works quite well and the maximum discrepancy with the detailed mechanism is 31 %.…”

Section: Skeletal Mechanism Of a Kerosene Surrogatementioning

confidence: 99%

Development of efficient and accurate skeletal mechanisms for hydrocarbon fuels and kerosene surrogate

Zhong

Zhang

et al. 2015

Acta Mech. Sin.

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In this paper, the methodology of the directed relation graph with error propagation and sensitivity analysis (DRGEPSA), proposed by Niemeyer et al. (Combust Flame 157:1760-1770, and its differences to the original directed relation graph method are described. Using DRGEPSA, the detailed mechanism of ethylene containing 71 species and 395 reaction steps is reduced to several skeletal mechanisms with different error thresholds. The 25-species and 131-step mechanism and the 24-species and 115-step mechanism are found to be accurate for the predictions of ignition delay time and laminar flame speed. Although further reduction leads to a smaller skeletal mechanism with 19 species and 68 steps, it is no longer able to represent the correct reaction processes. With the DRGEPSA method, a detailed mechanism for n-dodecane considering low-temperature chemistry and containing 2115 species and 8157 steps is reduced to a much smaller mechanism with 249 species and 910 steps while retaining good accuracy. If considering only high-temperature (higher than 1000 K) applications, the detailed mechanism can be simplified to even smaller mechanisms with 65 species and 340 steps or 48 species and 220 steps. Furthermore, a detailed mechanism for a kerosene surrogate having 207 species and 1592 steps is reduced with various error thresholds and the results show that the 72-species and 429-step mechanism and the 66-species and 392-step mechanism are capable of predicting correct combustion properties compared to those of the detailed mechanism. It is well recognized that kinetic mechanisms can be effectively used in computations only after they are reduced to an acceptable size level for computation capacity and at the same time retaining accuracy. Thus, the skeletal mechanisms generated from the present work are expected to be useful for the application of kinetic mechanisms of hydrocarbons to numerical simulations of turbulent or supersonic combustion.

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Performance of supersonic model combustors with staged injections of supercritical aviation kerosene

Cited by 9 publications

References 7 publications

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Experimental Investigation of Supersonic Model Combustor with Distributed Injection of Supercritical Kerosene

Development of efficient and accurate skeletal mechanisms for hydrocarbon fuels and kerosene surrogate

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