Heat transfer characteristics of H2/O2-combustion chambers

Froehlich, A.; Popp, M.; Schmidt, G.; Thelemann, D.

doi:10.2514/6.1993-1826

Cited by 35 publications

(17 citation statements)

References 3 publications

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“…For the present problem, a one-dimensional coolant flow model was employed [5] evaluating the coolant side heat transfer coefficient from a standard Nusselt-correlation (eq. 8) with proper modifications (f cs ) for the efficiency of the cooling fins and the curvature of the cooling channels.…”

Section: Wall Heat Transfer Simulationmentioning

confidence: 99%

Cryogenic rocket calorimeter chamber experiments and heat transfer simulations

Preclik

Wiedmann

Oechslein

et al. 1998

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Accurate information on the heat transfer evolution along the hot gas wall of a rocket chamber is a crucial prerequisite for optimizing an engine's regenerative cooling circuit design. To improve Dasa's available data basis in this field, a calorimeter model combustor was developed and tested. The main objective of these experiments was to characterize the heat transfer behaviour of different co-axial injection element configurations under various operational conditions (P c : 100-=-120 bar, O/F: 6.0-^7.6) first without and then with gaseous hydrogen wall film cooling.The experimental results disclosed that the co-axial injection designs under investigation produce local wall heat loads that differ up to 25 percent. These differences in heat transfer become more apparent at axial distances of about 100 mm from the injector and beyond. An important finding was also that hydrogen wall film cooling employing the present slot injection principle is in fact much more effective when compared to wall element mixture ratio trimming under similar operational conditions.A major interest of the current program was finally, to apply Dasa's axisymmetric, Euler/Lagrange CFD-code CryoROC to the calorimeter chamber tests and assess its capability in this field. In doing so, it turned out that basically two parameters are sufficient to adapt the simulation to the experiment of interest, i.e. a characteristic droplet size distribution parameter, which mainly affects the axial build-up of the wall heat flux, and a global scaling factor for fine tuning of the observed wall heat flux level. The CryoROC results also demonstrated that a realistic simulation the wall heat transfer problem in a cryogenic rocket engine requires to * Senior Member AIAA

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Section: Wall Heat Transfer Simulationmentioning

confidence: 99%

Cryogenic rocket calorimeter chamber experiments and heat transfer simulations

Preclik

Wiedmann

Oechslein

et al. 1998

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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“…Moreover, a straight portion of length L = 40 cm is considered and the channel surface is considered smooth. The mass §ow rate and the inlet conditions of the hydrogen §ow and the hot-gas-side wall temperature are selected accord- [5,14]: ' m = 92.8 g/s, T in = 75 K, p in = 130 bar, and T w,hg = 800 K. Hydrogen thermodynamic behavior is described by means of the modi¦ed Benedict Webb Rubin equation of state [15] for both solvers. The 3D CFD solution has been veri¦ed by a grid convergence analysis that has been presented in [16].…”

Section: Validation Of the Modelmentioning

confidence: 99%

Evolution of cooling-channel properties for varying aspect ratio

Pizzarelli

Nasuti

Onofri

2016

Progress in Propulsion Physics

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A trade-o¨analysis is performed on a cooling channel system representative of liquid rocket engine cooling systems. This analysis requires multiple cooling channel §ow calculations which are performed by means of a proper numerical approach, referred to as quasi-two-dimensional (2D) model. This model, which is suited to high-aspect-ratio cooling channels (HARCC), permits to have a fast prediction of both the coolant §ow evolution and the temperature distribution along the whole cooling channel structure. Before using the quasi-2D model for the trade-oä nalysis, its validation by comparison with computational §uid dynamics (CFD) results is presented and discussed. The results show that the pump power required to overcome losses in the cooling circuit can be minimized selecting a channel shaped with a suitably high aspect ratio.

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“…The RCFS-II presents an upgraded version of the well-known RCFS code [1]. In order to meet the growing requirements in terms of reliability and also with respect to new propellant combinations like LOx CH 4 , signi¦cant improvements were required.…”

Section: General Heat Transfer Approachmentioning

confidence: 99%

Improved heat transfer prediction engineering capabilities for rocket thrust chamber layout

Maeding¹,

Wiedmann²,

Quering³

et al. 2011

Progress in Propulsion Physics

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The demand for a more comprehensive engineering tool for design and parametric investigations of thrust-chamber relevant heat transfer is pushing the improvement of coolant and hot gas side prediction tools. Regenerative Coolant Flow Simulation (RCFS) [1], Astrium in-house developed one-dimensional (1D) tool to compute hot gas and coolant side heat transfer in a coupled approach, is based on the hot gas side Cinjarew approach which has its origin in the late 1960s. This tool was used as a starting basis for the development and validation of a further improved method. Over the past years, Astrium Space Transportation (ST) has continuously expanded the knowledge in this ¦eld. In addition, subscale hot ¦rings, using di¨erent propellant combinations and injection conditions, relevant to open and closed cycle applications, were used for the second RCFS generation ¡ the RCFS-II.

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Heat transfer characteristics of H2/O2-combustion chambers

Cited by 35 publications

References 3 publications

Cryogenic rocket calorimeter chamber experiments and heat transfer simulations

Cryogenic rocket calorimeter chamber experiments and heat transfer simulations

Evolution of cooling-channel properties for varying aspect ratio

Improved heat transfer prediction engineering capabilities for rocket thrust chamber layout

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