Investigation of Performance of Scramjet Combustion Used Kerosene with Clean Air

The aaviation kerosene is a practical candidate fuel for scramjet engine in the flight regimes of Mach number less than 8, in considerations of safety, economy and portable. In the present paper, the ignition characteristics of a scramjet combustor model fueled by aviation kerosene was experimentally investigated, using the resistance heating direct-connected supersonic combustion facility of Northwestern Polytechnical University. The inflow conditions at the direct-connected combustor entrance were specified as: the nominal Mach of 2.0, the total temperature of 870～930K and the total pressure of about 770kPa. Three combustor performance of difference ER were compared applied CFD simulated. The experimental result suggested that: the cavity design is a key problem for kerosene successful ignition is the combustor; That chooses appropriate gas-oil ratio could increased performance of combustor and kept isolator interfered by gas.

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Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector

International Journal of Turbo and Jet Engines ◽

10.1515/tjj-2015-0048 ◽

2017 ◽

Vol 34 (1) ◽

Cited By ~ 9

Author(s):

Gautam Choubey ◽

K. M. Pandey

Keyword(s):

Numerical Analysis ◽

Flow Structure ◽

Fuel Injection ◽

Angle Of Attack ◽

Supersonic Combustion ◽

Scramjet Combustor ◽

Numerical Studies ◽

Scramjet Engine

AbstractNumerical analysis of the supersonic combustion and flow structure through a scramjet engine at Mach 7 with alternating wedge fuel injection and with three angle of attack (

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Investigation of kerosene supersonic combustion performance with hydrogen addition and fuel additive at low Mach inflow conditions

Fuel ◽

10.1016/j.fuel.2020.119139 ◽

2021 ◽

Vol 285 ◽

pp. 119139

Author(s):

Feiteng Luo ◽

Wenyan Song ◽

Wenjuan Chen ◽

Yaosong Long

Keyword(s):

Supersonic Combustion ◽

Fuel Additive ◽

Hydrogen Addition ◽

Combustion Performance ◽

Inflow Conditions

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From Supersonic Combustion to Thermal Choking: Numerical and Experimental Analysis of A Scramjet Engine

AIAA AVIATION 2020 FORUM ◽

10.2514/6.2020-2966 ◽

2020 ◽

Author(s):

Eran Arad ◽

Neta Yokev ◽

Haim E. Brod ◽

Dan Michaels

Keyword(s):

Experimental Analysis ◽

Supersonic Combustion ◽

Scramjet Engine

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Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.490-491.931 ◽

2014 ◽

Vol 490-491 ◽

pp. 931-935

Author(s):

Xiao Yuan Zhang ◽

Li Zi Qin ◽

Yu Liu

Keyword(s):

Kinetic Models ◽

Chemical Kinetic ◽

Numerical Results ◽

Supersonic Combustion ◽

Equilibrium Flow ◽

Reaction Models ◽

Total Temperature ◽

Supersonic Combustion Ramjet ◽

Quantity Of Heat ◽

Non Equilibrium

The chemical non-equilibrium flow of supersonic combustion ramjet (scramjet) nozzle is numerical simulated with different chemical kinetic models to research the effects on numerical results of the nozzle performance. The numerical results show that total temperature is increased due to the recombination of dissociation compositions and the combustion of the residual fuel. The effect of the combustion of the residual fuel is more obvious in this paper, and the effect to the performance of the nozzle is noticeable. The species of the compositions in the models influence the quantity of heat sending out when it get equilibrium, so the 9-species chemical kinetic models are more suitable in the simulation of the scramjet nozzle chemical non-equilibrium flows.

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Experimental study on the effect of air throttling on supersonic combustion

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410016680234 ◽

2016 ◽

Vol 232 (3) ◽

pp. 472-480 ◽

Cited By ~ 4

Author(s):

Ye Tian ◽

Shunhua Yang ◽

Baoguo Xiao ◽

Jialing Le

Keyword(s):

Experimental Study ◽

Mass Flux ◽

Equivalence Ratio ◽

Flame Stabilization ◽

Wall Pressure ◽

Supersonic Combustion ◽

Reacting Flow ◽

Flux Rate ◽

Shock Train ◽

Scramjet Combustor

The effect of air throttling on supersonic combustion was investigated by experiments in the present paper. Our results indicated that, in the non-reacting flow, a shock train could be generated in the scramjet combustor due to the increased backpressure caused by air throttling, and the wall pressure increased obviously. But when the mass flux rate of air throttling was not large enough, the shock train would oscillate with the flow. In the reacting flow, the flame stabilization was achieved in the combustor without air throttling when the equivalence ratio of kerosene was 0.2 and 0.31, but the flame was blown off when the equivalence ratio of kerosene was 0.45. On the contrary, the kerosene (equivalence ratio: 0.45) was ignited successfully in the combustor with air throttling, and it kept burning all the time in the cases with air throttling −5% (the flux of air throttling was 5% of the inflow flux) and with air throttling −14% (the flux of air throttling was 14% of the inflow flux), but the flame was blown off in the case with air throttling −1.1% after kerosene had burnt 70 ms. The flux of air throttling should be large enough to achieve flame stabilization, and the hydrogen and air throttling should both exist all the time in order to keep the flame burning steadily.

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Turbine Performance Under Pulsating Inflow: A Similarity Analysis

Volume 2D: Turbomachinery ◽

10.1115/gt2016-56612 ◽

2016 ◽

Author(s):

Hua Chen ◽

Apostolos Pesiridis

Keyword(s):

Strouhal Number ◽

Similarity Analysis ◽

Relative Importance ◽

Computational Results ◽

Gasoline Engines ◽

Turbine Performance ◽

Dimensional Parameters ◽

Total Temperature ◽

Inflow Conditions ◽

Unsteady Conditions

Turbocharger turbines for diesel and gasoline engines work under pulsating inflow conditions. This paper discusses the influences of such unsteady conditions on turbine performance through a similarity analysis. First the assumptions for the analysis are described and key non-dimensional parameters are identified. Some of these parameters are further studied with the assistance from experimental and computational results in the open literature. Strouhal number, which expresses the relative importance of unsteady influences, is discussed in details regarding its definition, its application to experimental setup, and how it affects different components of the turbines. The analysis shows that Strouhal number should be scaled with the square root of turbine inlet total temperature.

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