An Overview on the Structure and Work of the DFG Research Training Group GRK 1095: "Aero-Thermodynamic Design of a Scramjet Propulsion System"

Numerical analysis of the hypersonic combustion and flow structure through a scramjet engine at a flight Mach 7 with parallel fuel injection at different angles of attack, α= (-5°), 0° and 5° have been studied in the present research paper. The scramjet configuration incorporates an inlet angle of 8 o compression ramp followed by an insulator and a divergent combustor for parallel injection. The shape of the strut is chosen such that it produces strong stream wise vorticity and thus enhances the air/fuel mixing. These numerical simulations were aimed to study the flow structure, supersonic mixing and combustion efficiency. For parallel injection investigation; the influence of strut injector, the variation of angle of attack on the flow behavior in reacting cases have been studied. The shock structure and combustion phenomenon are affected by the combustor geometry, flight Mach number and by the trajectory.

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“…Where, k is 0.42 The term Y k represents the dissipation of turbulent kinetic energy Y k =ρβ * kω (14) Dissipation of ω…”

Section: Modeling the Turbulence Production (Lumley Jl 1978)mentioning

confidence: 99%

Computational Analysis of Hypersonic Combustor Using Strut Injector at Flight Mach 7

Pandey

Roga

Choubey

2015

Combustion Science and Technology

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“…The Scramjet demonstrator, designed within the program GRK 1095/2, 4,5 consists of an intake with a compression ramp and converging sidewalls, followed by a combustor and a nozzle (Fig. 1).…”

Section: The Scramjet Modelmentioning

confidence: 99%

Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

Riehmer

Rabadan

Gülhan

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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In the present paper the comparison between experiments and numerical simulations for a generic Scramjet configuration are been presented. The experiments have been conducted for a Mach 7 condition at the hypersonic blow down wind tunnel H2K at the German Aerospace Center (DLR) in Cologne. The corresponding numerical simulations have been performed using two different numerical solvers. During the experiments, air was injected through central strut and wall-ramp injectors to simulate a combustion backpressure. In order to generate a database for a comparison between numerical and experimental data, wall pressures were measured along the bottom and top side walls, Pitot pressure at the exit of the combustor, and heat flux on the sidewalls. The reasonable good agreement between the experiments and the numerical solutions show the feasibility of the numerical tools to predict complex flow structures in high-speed flows. Furthermore, an extrapolation of the numerical and experimental data to real flight conditions at an altitude of 30 km was undertaken and the feasibility of the proposed Scramjet configuration is been shown.

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“…2 There are research projects, dealing with aero thermal flow phenomena in the intake, the supersonic combustion process and overall system aspects. The present work is embedded into subproject A3, which deals with the design and characterization of a three-dimensional SCRamjet intake.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Starting Behavior of a three-dimensional SCRamjet Intake with a Movable Cowl and Exchangeable Cowl Geometry at Different Mach Numbers

Flock

Guelhan

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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In the current work we focused our research on the intake starting process which is crucial for proper performance of Supersonic Combustion Ramjet engines. To this date there is no generally valid method to accurately predict intake starting for a certain threedimensional SCRamjet intake configuration. Therefore we conducted starting experiments at Mach 6 and 7 in a blow down wind tunnel on a three dimensional intake model, equipped with a movable cowl and therefore variable internal contraction. Our focus was on the influence of the cowl geometry, the free stream Mach number, the angle of attack and the ratio of total temperature in the free stream to model wall temperature on intake starting. While the influence of total temperature was minor in the temperature ranges considered, the effect of angle of attack was twofold: when the intake was pitched, that the leading edge shock decreased in strength, the intake showed improved starting characteristics.

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An Overview on the Structure and Work of the DFG Research Training Group GRK 1095: "Aero-Thermodynamic Design of a Scramjet Propulsion System"

Cited by 15 publications

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Computational Analysis of Hypersonic Combustor Using Strut Injector at Flight Mach 7

Computational Analysis of Hypersonic Combustor Using Strut Injector at Flight Mach 7

Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

Experimental Investigation of the Starting Behavior of a three-dimensional SCRamjet Intake with a Movable Cowl and Exchangeable Cowl Geometry at Different Mach Numbers

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