Vitiation Effects on Scramjet Engine Performance in Mach 6 Flight Conditions

Tomioka, Sadatake; Hiraiwa, Tetsuo; Kobayashi, Kan; Izumikawa, Muneo; Kishida, Tomoyuki; Yamasaki, Hiroyuki

doi:10.2514/1.28149

Cited by 32 publications

(22 citation statements)

References 10 publications

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“…At the standpoint of inflow vitiation effects on combustion, the pressure magnitudes with vitiated inflow were smaller than that with clean inflow under at the same equivalence ratio condition. This pressure trend qualitatively matches to the experimental results (1,4) .…”

Section: Combustor Inflow Conditions For the Calculationsupporting

confidence: 89%

“…Especially in supersonic combustible flow, the Mach number is easily changed by the fuel heat release. Tomioka et al carried out a quasi-one dimensional one-stream-tube flow calculation for supersonic combustible flow (4) . As mentioned above, their flame holding modeling contained an experimental coefficient.…”

Section: Modeling For Flame Holdingmentioning

confidence: 99%

“…This point is important to perform a parametric study for a conceptual design in earlier stage of projects. Tomioka et al carried out a quasi-one dimensional calculation for a supersonic combustor, previously (4) . The wall pressure distributions of their chemical kinetic calculation results well matched to that of the experimental results.…”

Section: Introductionmentioning

confidence: 99%

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Estimation of Mode Transition in a Supersonic Combustor

Noda

Murakami

Kudo

et al. 2013

JTST

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A quasi-one dimensional calculation was carried out to figure out supersonic combustor performances. Three flow tubes were considered in the combustor region. Those were an air-flow-tube, a combustion-flow-tube and a fuel-flow-tube. A Mach=1 condition was assumed in the combustion-flow-tube. The estimation of a mode-transition was considered as a result of thermal choking. Both clean and vitiated inflows were tested with the calculation model. Experimental combustion tests were also carried out to compare and confirm the validity of calculated results. Mode-transition equivalence ratios and combustor wall pressure distributions were focused to compare between calculated and experimental results. The calculation model estimated the mode-transition equivalence ratio and the thrust performance with the relative errors at about 11% and 6% compared to the experimental results, respectively.

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Section: Combustor Inflow Conditions For the Calculationsupporting

confidence: 89%

Section: Modeling For Flame Holdingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Estimation of Mode Transition in a Supersonic Combustor

Noda

Murakami

Kudo

et al. 2013

JTST

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“…Thus, VAH is widely used although the heated air flow contains vitiating matter such as water vapor and radicals. Combustion test results for scramjet engines which used clean air (by EAH or SAH) or vitiated air (by VAH) have been conducted (1), (2) . For example, combustor wall pressure with VAH was observed to be lower than that with SAH at the same equivalence ratio(φ), and engine un-start (i.e., flow separation interfering with the inlet), more easily occurred with SAH than VAH.…”

Section: Introductionmentioning

confidence: 99%

Estimation of Enthalpy Effects in Direct-Connect Dual-Mode Combustor

Noda

Tomioka

Izumikawa

et al. 2011

JTST

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To estimate the enthalpy effects of test gas in a direct-connect dual-mode combustor, an experimental study was conducted. Wall pressures were compared under two cases with different types of air heater (combustion heater and electric heater) at various H2 fuel equivalence ratios. Considering flame holding, dual-mode transition and wall pressure value, matching total enthalpy was found to be more effective than matching total temperature in terms of mitigating vitiation effects in the case of a combustion heater. On the other hand, for vitiation flow, matching total temperature is more effective than matching total enthalpy for ignition to duplicate that of clean air flow. Therefore, flow total condition (total temperature or total enthalpy) should be selected according to experimental candidates.

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“…Pellet et al [15] reviewed vitiation effects on scramjet ignition and flame holding, and revealed that the existence of H 2 O may change the reaction kinetics. Generally, all of the above studies matched total pressure and total temperature between clean air and vitiated air, so matching other parameters, such as static pressure, total enthalpy, become another research focus [11,13,17]. It was revealed that matching total enthalpy rather than total temperature get closer mode transition critical equivalence ratio related to clean air [11].…”

Section: Introductionmentioning

confidence: 95%

Effects of Air Vitiation on Scramjet Performance Based on Thermodynamic Cycle Analysis

Chang¹

2014

J Aeronaut Aerospace Eng

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The influences of air vitiation on scramjet performance were studied in this paper based on thermodynamic cycle analysis. By the aid of NASA Glenn's computer program Chemical Equilibrium with Applications (CEA), parameters of vitiated air at combustion heater exit could be calculated. Based on thermodynamic cycle analysis, scramjet performance, including internal thrust, specific thrust, and specific impulse, were analyzed with 9 simulation criterions under Mach 4.5 and 6.5 conditions, respectively. The results show that, (1) specific heat and specific heat ratio of vitiated air are mainly affected by combustion heating medium, and also have minor connection with temperature criterions. Moreover, choosing different simulation criterions influences the temperature or pressure between clean air and vitiated air significantly; (2) the internal thrust and specific thrust of scramjet with hydrogen heated airstream are greater than that of scramjet with alcohol and kerosene heated airstream; (3) matching static pressure and dynamic pressure will obtain higher internal thrust compared to total pressure, and the effect of pressure criterions on internal thrust is more remarkable than temperature criterions. On the other hand, these findings proved that the method based on thermodynamic cycle analysis is a simple, dependable, and effective approach to evaluate the scramjet performance affected by air vitiation.

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Vitiation Effects on Scramjet Engine Performance in Mach 6 Flight Conditions

Cited by 32 publications

References 10 publications

Estimation of Mode Transition in a Supersonic Combustor

Estimation of Mode Transition in a Supersonic Combustor

Estimation of Enthalpy Effects in Direct-Connect Dual-Mode Combustor

Effects of Air Vitiation on Scramjet Performance Based on Thermodynamic Cycle Analysis

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