The Role of the TNO-PML Free Jet Test Facility in Solid Fuel Ramjet Projectile Development

Veraar, R.G.; Mayer, Alfons

doi:10.2514/6.2005-3828

Cited by 10 publications

(9 citation statements)

References 1 publication

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“…Computational Fluid Dynamics (CFD) was extensively used to design a shock-induced combustion experiment in which hydrogen was injected from the nose of a dual-cone test object into a supersonic airstream. Given the operational envelope and the dimensional constraints of the TNO Free Jet Test Facility [3] (see Section 2.5.1) it was decided to design an axi-symmetric test object having a second cone base diameter of roughly 60 mm. A half cone angle of 5° was selected for the upstream slender cone part while the half cone angle of the second cone was to be determined from gas dynamic analysis.…”

Section: Gas Dynamic and Thermo-mechanic Design Of The Test Objectmentioning

confidence: 99%

“…To maximize the chance of successfully demonstrating shock-induced combustion, the flow conditions in the combustion region were subsequently studied. Given the limitations of the TNO Free Jet Test Facility [3], it appeared that the local flow conditions were most favorable using the Mach 3.25 free jet nozzle with a total temperature of 1500 K. To achieve maximum mixing efficiency, the momentum flux ratio between the hydrogen jet and the supersonic air cross flow was set to 1.0. Figure 6 shows the predicted flow conditions in the combustion region resulting from a non-reactive simulation for a cylindrical ramp injector assuming second cone angles equal to 35° and 39°.…”

Section: Gas Dynamic Analysismentioning

confidence: 99%

“…The TNO free jet facility was developed to enable on-ground verification of the functioning of gunlaunched ramjet propelled projectiles [3]. It consists of a gas supply system, an air heater and a convergent-divergent nozzle to generate a supersonic air flow.…”

Section: Tno Free Jet Facilitymentioning

confidence: 99%

See 2 more Smart Citations

Proof-of-Principle Experiment of a Shock-Induced Combustion Ramjet

Veraar

Mayer

Verreault

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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By injecting and mixing the fuel upstream of the combustor and initiating the combustion of the fuel-air mixture by a shock wave in the combustor, shock-induced combustion ramjets offer the potential to drastically reduce the length and mass of scramjet propulsion systems. Based on extensive numerical gas dynamic and thermo-mechanical analysis, an axi-symmetric dual cone test object was designed and manufactured to demonstrate that it is possible to inject hydrogen into a high enthalpy supersonic air flow without causing premature ignition and subsequently induce combustion of this mixture by a strong oblique shock wave. The test object was instrumented with 16 thermocouples and a shadowgraph technique was used to visualize density changes in the flow field. A test series was executed in the TNO Free Jet Test Facility using the Mach 3.25 free jet nozzle in which the air flow stagnation temperature and the injected hydrogen mass flow rate was varied. Due to thermal expansion of the strut holding the test object, a small angle-of-attack was induced and resulted in different types of combustion occurring at the top and bottom sides of the test object. At the bottom, hydrogen was captured and subsequently burned in the boundary layer separation zone resulting in very high local heat loads. At the top side of the test object, shock-induced combustion occurred in the inviscid flow field only at a higher level of stagnation temperature with a peak heat load clearly downstream of the boundary layer separation zone. This experimental result is an important step in demonstrating the feasibility of a shock-induced combustion ramjet as a future hypersonic propulsion system.

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Section: Gas Dynamic and Thermo-mechanic Design Of The Test Objectmentioning

confidence: 99%

Section: Gas Dynamic Analysismentioning

confidence: 99%

See 1 more Smart Citation

Proof-of-Principle Experiment of a Shock-Induced Combustion Ramjet

Veraar

Mayer

Verreault

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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“…Cross-sectional view of the TNO freejet test facility including the gas supply system, the vitiator (air heater) and the freejet nozzle [36] ... A.l Variation of the shock wave angle with the cône semivertex angle for various upstream Mach numbers [37] B.l Effect of calorie imperfections on the ratio of static température to stag nation température [37] Nomenclature…”

Section: 1mentioning

confidence: 99%

Design of a Shock-Induced Combustion Experiment in an Axisymmetric Configuration with Hydrogen Injection

Verreault¹,

deChamplain²,

Mayer³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Under some circumstances, the combustor may be required to operate at high spinning speed. For example, it could be a combustor installed in a spin-stabilized gunlaunched projectile [86], in which all of the mechanical parts are rotating together at a spinning speed rate around 10,000 rpm to 30,000 rpm. In this situation, the strong spinning motion brings centrifugal and Coriolis forces, which may have a profound effect on the cavity flow field, fuel-air mixing, and combustion performance.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of trapped vortex combustors characteristics in small ramjets

Chen¹

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my current supervisor, who continuously provides me valuable suggestions and discussions during these years in many ways. I am also grateful to Dr. Simon Ching-Man Yu of Singapore Institute of Technology, my co-supervisor, for continuously providing me encouragement, guidance, discussions and caring in both research and personal life. Without their guidance, the research would not have been so enriching and fulfilling.

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The Role of the TNO-PML Free Jet Test Facility in Solid Fuel Ramjet Projectile Development

Cited by 10 publications

References 1 publication

Proof-of-Principle Experiment of a Shock-Induced Combustion Ramjet

Proof-of-Principle Experiment of a Shock-Induced Combustion Ramjet

Design of a Shock-Induced Combustion Experiment in an Axisymmetric Configuration with Hydrogen Injection

Numerical study of trapped vortex combustors characteristics in small ramjets

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