| タイトル | Flow interaction experiment. Volume 2: Aerothermal modeling, phase 2 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940017110 |
| 著者（英） | Sullivan, J. P.; Murthy, S. N. B.; Nikjooy, M.; Mongia, H. C. |
| 著者所属（英） | General Motors Corp. |
| 発行日 | 1993-11-01 |
| 言語 | eng |
| 内容記述 | An experimental and computational study is reported for the flow of a turbulent jet discharging into a rectangular enclosure. The experimental configurations consisting of primary jets only, annular jets only, and a combination of annular and primary jets are investigated to provide a better understanding of the flow field in an annular combustor. A laser Doppler velocimeter is used to measure mean velocity and Reynolds stress components. Major features of the flow field include recirculation, primary and annular jet interaction, and high turbulence. A significant result from this study is the effect the primary jets have on the flow field. The primary jets are seen to create statistically larger recirculation zones and higher turbulence levels. In addition, a technique called marker nephelometry is used to provide mean concentration values in the model combustor. Computations are performed using three levels of turbulence closures, namely k-epsilon model, algebraic second moment (ASM), and differential second moment (DSM) closure. Two different numerical schemes are applied. One is the lower-order power-law differencing scheme (PLDS) and the other is the higher-order flux-spline differencing scheme (FSDS). A comparison is made of the performance of these schemes. The numerical results are compared with experimental data. For the cases considered in this study, the FSDS is more accurate than the PLDS. For a prescribed accuracy, the flux-spline scheme requires a far fewer number of grid points. Thus, it has the potential for providing a numerical error-free solution, especially for three-dimensional flows, without requiring an excessively fine grid. Although qualitatively good comparison with data was obtained, the deficiencies regarding the modeled dissipation rate (epsilon) equation, pressure-strain correlation model, and the inlet epsilon profile and other critical closure issues need to be resolved before one can achieve the degree of accuracy required to analytically design combustion systems. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 94N21583
NASA-CR-189192-VOL-2
E-8180-VOL-2
EDR-16026
NAS 1.26:189192-VOL-2 |
| 権利 | No Copyright |
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