Experimental Investigations on Transpiration Cooling for Scramjet Applications Using Different Coolants

Langener, Tobias; Wolfersdorf, Jens von; Steelant, Johan

doi:10.2514/1.j050698

Cited by 82 publications

(53 citation statements)

References 20 publications

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“…Additionaly to the cold side temperature, the dotted line uses the predicted hot wall temperature to evaluate the pressure loss at the mean temperature. This assumes a linear temperature distribution in the porous media and is therefore comparable to the analytic model described by Langener et al 12 It can be seen, that this results in a better agreement with the measurement. Finally, the solid line uses the calculated temperature distribution from the preceding section and numerically solves for pressure loss.…”

Section: Ivb3 Pressure Drop Over Porous Wallsupporting

confidence: 66%

“…12 In the current work the temperature distribution calculated in the preceding section is used to numerically solve the Darcy-Forchheimer equation with temperature dependent fluid properties. Figure 10(b) shows measured pressure loss over a flat plate as used in TRR40, compared to calculations with isothermal through-flow and temperature dependent through flow.…”

Section: Ivb3 Pressure Drop Over Porous Wallmentioning

confidence: 99%

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Systems Analysis of a LOX/LH2 Rocket Engine with a Transpiration-Cooled Ceramic Thrust-Chamber

Herbertz¹,

Selzer²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This paper discusses various different applications of transpiration cooled ceramic thrust chambers. The paper concentrates on medium to high thrust cryogenic propellant (i.e. liquid hydrogen / liquid oxygen) rocket engines. A systems study with a parametric variation of engine-and material specifications (such as chamber pressure, mixture ratio, wall heat conductivity etc.) is performed. Achievable benefits, such as the reduction of weight and manufacturing cost, as well as an increased reliability and higher lifetime due to thermal cycle stability are discussed.

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Section: Ivb3 Pressure Drop Over Porous Wallsupporting

confidence: 66%

Section: Ivb3 Pressure Drop Over Porous Wallmentioning

confidence: 99%

Systems Analysis of a LOX/LH2 Rocket Engine with a Transpiration-Cooled Ceramic Thrust-Chamber

Herbertz¹,

Selzer²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…The experimental results, as pointed out earlier, are obtained from an experimental study on transpiration cooling in Cartesian coordinates for C/C liners, which were prepared as rectangular plates, by Langener [15,16]. Therefore, prior to solving the …”

Section: Mathematical Modeling In Cartesian System and Benchmarkingmentioning

confidence: 99%

“…According to the experimental study [15,16], the inner face is exposed to convective heat flux caused by the main hot flow and the hot face temperature is T w . Also, the coolant flow which is maintained at T c , is injected from the outer face called cold face (see Fig.5).…”

Section: Experimental Studymentioning

confidence: 99%

Mathematical modeling of transpiration cooling in cylindrical domain

Aybar

Faridani

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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This research is conducted to develop numerical schemes modeling one-dimensional steady-state non-equilibrium transpiration cooling in Si-C porous materials. The transpiration cooling process is assumed to be used to protect the thrust chamber of a liquid rocket engine by blocking the enormous heat transfer towards its walls. The flow modeling within the porous media is performed through applying numerical Moreover, the internal convective heat transfer between solid structure and the coolant flow is studied. The porous solver code is then coupled with the gas solver code so that the cooling process can be studied in a more realistic area. The results show the variation of gas properties through the nozzle the effect of transpiration cooling on them. Also, a sample method of controlling the nozzle wall temperature is demonstrated.

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“…Thermal surface effects are especially important for air-breathing hypersonic vehicles that, for drag-reducing purposes, are slender vehicles often with sharp leading edges: a configuration leading to both high thermal loads and consequently high thermally induced stresses [1]. A number of methods to mitigate thermal loads and stresses on hypersonic vehicles exist, the most common of which are the use of exotic materials for thermal protection such as those on NASA's X34 [2] and Space Shuttle [3] vehicles and active cooling technologies [4][5][6]. Incorporating these, however, often comes at significant economic and packaging expense, and thus a third mechanism of passive cooling is becoming a more popular method of thermal management on hypersonic flight-test vehicles [7][8][9].…”

mentioning

confidence: 99%

Aerothermal–Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Ascent

Capra

Brown

Boyce

et al. 2015

Journal of Spacecraft and Rockets

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This paper reports on the methodology and results of a weak-coupled aerothermal-structural analysis on the ascent phase of the SCRAMSPACE Mach 8 scramjet flight experiment. This vehicle was essentially unshrouded during the flight trajectory, relying on the thin, 5 mm thick aluminum external shell of the payload to maintain structural integrity and protect the flight experiment. As such, understanding the thermal-structural response of the vehicle was imperative to mission success. Using two-and three-dimensional models, an iterative procedure was employed to compute the flowfield, convective heating, wall temperatures and structural coupling at flight times covering both peak heating and peak surface temperature. Accounting for such coupling resulted in a 150 K reduction in wall temperature compared to the more conservative cold wall assumption. Despite this, peak temperatures remained of the order of 550 K. Further, thermally induced stresses within these regions were in excess of four times the material failure limits. Irreversible material failure during ascent was therefore concluded likely to occur on the external shell. Two alternate materials, steel 1006 and copper, were therefore assessed with the results indicating that steel sections on the external shell resulted in the best thermal-structural response of the payload. NomenclatureSubscripts amb = ambient r = radiative m = melting y = yield T = tensile 0 = initial

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Experimental Investigations on Transpiration Cooling for Scramjet Applications Using Different Coolants

Cited by 82 publications

References 20 publications

Systems Analysis of a LOX/LH2 Rocket Engine with a Transpiration-Cooled Ceramic Thrust-Chamber

Systems Analysis of a LOX/LH2 Rocket Engine with a Transpiration-Cooled Ceramic Thrust-Chamber

Mathematical modeling of transpiration cooling in cylindrical domain

Aerothermal–Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Ascent

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