Numerical Simulation of Film Cooling in Hypersonic Flows

Yang, Xin; Badcock, K. J.; Richards, B. E.; Barakos, George N.

doi:10.2514/6.2003-3631

Cited by 5 publications

(3 citation statements)

References 27 publications

(22 reference statements)

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“…The relationship between the objective functions and design variables are obtained by using Curve fitting. This method (CFM) is usually applied for analyzing the results of numerical and experimental studies in film cooling technique [28][29][30][31]. The optimum design point can be detected by the following curve fittings equations:…”

Section: Resultsmentioning

confidence: 99%

Multi-objective optimization of three rows of film cooling holes by genetic algorithm

2021

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Aero-thermal optimization on multi-rows of film cooling over a flat plate has been performed to optimize the inclination angles. Hence three cylindrical holes with injection angles of ?, ?, and ? have been considered. The cooling hole has a 3 mm diameter and an inclined angle between 25 to 35 degrees. Numerical simulations were performed at a fixed density ratio of 1.25 and blowing ratio of 0.5. The control-volume method with a SIMPLEC algorithm has been used to solve the steady-state RANS equations with SST k-? turbulent model. The injection angles of the holes are selected as the design variables to perform the optimization of three rows of film cooling. In order to evaluate the performance of holes arrangement, two objective functions are defined based on aerodynamic losses and adiabatic film cooling effectiveness. The curve fitting method (CFM) is used to find the optimal point of objective functions. The optimizations have been performed using the genetic algorithm (GA) method. Results of the present study show that the best performance of three rows of cooling holes was achieved in inclined angles 25.45, 32.85 and 33.1.

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Section: Resultsmentioning

confidence: 99%

Multi-objective optimization of three rows of film cooling holes by genetic algorithm

2021

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“…With these models, the prediction of the flow field is supported with more physical background. The earlier numerical studies [18,19] are mainly based on the Reynolds Averaged Navier Stokes equations for kinds of flow conditions, and several turbulence models have been tested. In recent years, the large edgy simulation method has been developed rapidly, and begins to be applied to the prediction of the film cooling problem.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on supersonic film cooling on the surface of a blunt body in hypersonic flow

Fu¹,

Yi²,

Wang³

et al. 2014

Chinese Phys. B

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The experimental study focuses on the heat flux on a double cone blunt body in the presence of tangential-slot supersonic injection into hypersonic flow. The tests are conducted in a contoured axisymmetric nozzle with Mach numbers of 7.3 and 8.1, and the total temperature is about 900 K. The injection Mach number is 3.2, and total temperature is 300 K. A constant voltage circuit is developed to supply the temperature detectors instead of the normally used constant current circuit. The schlieren photographs are presented additionally to visualize the flow and help analyze the pressure relationship between the cooling flow and the main flow. The dependence of the film-cooling effectiveness on flow parameters, i.e. the blow ratio, the convective Mach number, and the attack angle, is determined. A semi-empirical formula is tested by the present data, and is improved for a better correlation.

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“…Peng and Jiang 19 have also studied shock waves effects on film cooling, using nitrogen, methane and helium as coolants. Yang et al 20 have studied both laminar and turbulent film cooling. Recent work by Martelli et al 21 has numerically investigated SSFC in an advanced dual-bell nozzle design.…”

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confidence: 99%

Validation of Supersonic Film Cooling Modeling for Liquid Rocket Nozzle Applications

Ruf¹

2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Supersonic film cooling (SSFC) of nozzles has been used in several liquid rocket engine designs, and is being applied to the nozzle extension of the J-2X upper stage engine now under development. Due to the large size and challenging thermal load of the nozzle extension, there was a critical need to assess the accuracy of CFD models in representative SSFC flowfields. This paper reports results from a CFD analysis of SSFC experiments performed at Calspan in the late 1980s and early 1990s. 2-D and 3-D CFD simulations of flat plate heating, coolant nozzle flow, and film cooling flowfields are discussed and compared with the experimental data. For the film cooling cases studied, the 3-D simulations predict the initial mixing of the coolant and freestream in the adiabatic cooling region reasonably well. However, the CFD simulations generally predict faster mixing in the developed flow region of the flowfield than indicated by the experimental data. Hence, from an engineering perspective, the CFD tool and modeling assumptions used are conservative.

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Numerical Simulation of Film Cooling in Hypersonic Flows

Cited by 5 publications

References 27 publications

Multi-objective optimization of three rows of film cooling holes by genetic algorithm

Multi-objective optimization of three rows of film cooling holes by genetic algorithm

Experimental study on supersonic film cooling on the surface of a blunt body in hypersonic flow

Validation of Supersonic Film Cooling Modeling for Liquid Rocket Nozzle Applications

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