Numerical studies of nozzle thrust characteristics of supersonic civil aircraft by computational gas dynamics method

DOI: 10.34759/vst-2019-4-7-16

Аuthors

Gorbovskoi V. S.^*, Kazhan A. V., Kazhan V. G., Shenkin A. V.

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: vgorbovskoy@mail.ru

Abstract

One of the most urgent problem while developing a new generation supersonic civil aircraft is ecologic requirements ensuring, including the community noise level near the airport. It requires developing and studying new technical solutions ensuring both low nozzle thrust losses level at all flight modes and reduction of jet flow velocity to decrease its noise level at the take-off/landing modes. One of the possible trends for this problem solving is mixer-ejector type nozzle application on the supersonic civil aircraft. Its operation principle consists in the fact that at the take­off mode with sound absorption, the hot jet is split into smaller jets by the multi-lobe nozzle. The increased surface area of the ruffled jet intensifies its mixing with atmospheric air, and reduces the length of the mixing layer initial section. The mixed jet velocity in the nozzle outlet section reduces, and thus the effect of acoustic suppression is achieved. Mixing zone shielding by the tail part elements of the airframe allows additional enhancing of acoustic suppression. At the flight modes without acoustic suppression the mixer- ejector type nozzle transforms into conventional supersonic nozzle with much higher thrust characteristics.

To reduce time and financial costs at the preliminary design stages, it is expedient to employ computational methods, ensuring high level of confidence. Modern software for fluid numerical modelling are applicable for solving a wide class of problems. However, refinement of flow numerical modelling technique is necessary for solving concrete problem. In the presented work, rational parameters for computing and computational grids were selected.

Modern Computational Fluid Dynamics (CFD) software allows solving a wide class of problems. However, refinement of flow numerical modelling technique is necessary for solving concrete problem. In the presented work, rational parameters for computing and computational grids were selected to study physics of the flow and obtain integral characteristics of the nozzle, such as mixer-ejector nozzle, at the take-off, landing, transonic and supersonic flight regimes. This method is employed to predict the nozzle thrust losses with ANSYS CFX commercial CFD code of Reynolds- averaged Navier-Stokes equation numerical solution. The numerical study of losses in mixer-ejector nozzle with active system of acoustic suppression at the take­off and landing modes are performed, and obtained results are validated by the experimental data. The accuracy of validation does not exceed 0.5% of the ideal thrust losses at all flight modes.

Keywords:

nozzle of civil supersonic aircraft, jet engine noise reduction, nozzle thrust losses, computational fluid dynamics, numerical study of nozzle thrust characteristics

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