Impact of the Intake Vortex on the Stability of the Turbine Jet Engine Intake System
The article presents a numerical analysis of the intake system of a turbine jet engine in terms of parameter stability along its duct, following the occurrence of an intake vortex. This type of intake system is characterized by high susceptibility to intake vortex. In extreme cases, this type of phenomenon leads to the engine surge and even to the operation disruption (engine stalling). The article presents a developed model of the front part of the aircraft with an intake duct. The discretization process involved in the issue under consideration has been described. The airflow parameters corresponding to the conditions in such cases have been adopted and numerical calculations have been performed. The result is an intake vortex. Subsequently, significant cross sections in the intake system have been separated, on which the impact pressure distributions have been determined. The main part of the article is devoted to the analysis of pressure distributions. They have been subjected to quantitative analysis using the proposed pressure coefficient. The coefficient has provided quantitative information about the difference in pressure distributions for selected sections. The results obtained have provided information about mounting airflow instability in the flow duct caused by the intake vortex.
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I. Arif, S. Salamat, M. Ahmed, F. Qureshi and S. Shah, Comparative Flow Field Analysis of Boundary Layer, Diverter Intake and Diverterless Supersonic Intake Configuration, Journal of Applied Fluid Mechanics, Vol. 11, No. 4, pp. 1125-1131, 2018
Bravo-Mosquera P. D., MartinsAbdalla A., DaríoCerón-Muñoz H., Catalano F. M., Integration assessment of conceptual design and intake aerodynamics of a non-conventional air-to-ground fighter aircraft, Aerospace Science and Technology 86, p. 497-519, 2019.
Gil-Prietoa D., MacManusa D. G., Zachosa P. K., Bautistaa A., Assessment methods for unsteady flow distortion in aero-engine intakes, Aerospace Science and Technology, Volume 72, p. 292-304, January 2018.
H. A.J. G. Beik, S. H. Torabi, and H. B. Tabrizi, Stall Margin Improvement and Increase Pressure Ratio in Transonic Axial Compressor Using Circumferential Groove Casing Treatment, AUT J. Mech. Eng., vol. 3, no. 1, pp. 107-112, 2019
Jia W., Wu Y., Lei Y., Generation mechanism and aerodynamic characteristic modeling of ground vortex in crosswind condition, Aerospace Science and Technology, 99 10558, p.1-9, 2020.
Jia, Y., Liang, H., He, Q. et al. Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator, Flow Turbulence Combust, 2021.
I Liu H., Yi B., Wang C., Hui M.: Numerical simula¬tions on nacelle inlet ground vortex under cross¬wind conditions, Aeroengine; Nanjing, China, 43(6), 2017
Hassan, H., Gobran, M., El-Saied, A., Turbofan Engine Performance Deterioration Due To Fan Erosion, (2019) International Review of Aerospace Engineering (IREASE), 12 (2), pp. 93-100.
Hassan, H., Gobran, M., El-Azim, A., Performance Prediction for the Fan of the CF6-50 Turbofan Engine at the Off-Design Conditions, (2013) International Review of Aerospace Engineering (IREASE), 6 (1), pp. 9-17.
Kozakiewicz A., Frant M., The analysis of the gust impact on inlet vortex formation of fuselage-shielded inlet of a jet engine powered aircraft, English, Journal of Theoretical and Applied Mechanics JTAM, vol.51, no. 4, pp. 993-1002, Warsaw, Poland. 2013.
Yeung A, Vadlamani NR, Hynes T, Sarvankar S. Quasi 3D Nacelle Design to Simulate Crosswind Flows: Merits and Challenges. International Journal of Turbomachinery, Propulsion and Power, 4(3):25, 2019.
W. Zhang, S. Stapelfeldt, and M. Vahdati, Influence of the inlet distortion on fan stall margin at different rotational speeds, Aerosp. Sci. Technol., 2020.
Seddon J., Goldsmith E.L., Intake Aerodynamics, AIAA Education Series, 2nd ed., Virgina 1999.
Kozakiewicz A., Estimation of the operating point in order to optimize the geometry of the stockade compressor, Poznan University of Technology Publisher, Poznań 2013, pages: 138.
D. Gil-Prieto, D. G. MacManus, P. K. Zachos, A. Bautista, Assessment methods for unsteady flow distortion in aero-engine intakes, Aerospace Science and Technology, Volume 72, pp. 292-304, 2018.
Tanguy, D. G. MacManus, E. Garnier, P. G. Martin, Characteristics of unsteady total pressure distortion for a complex aero-engine intake duct, Aerospace Science and Technology, Volume 78, pp. 297-311, 2018.
Millot G., Raynal S., Laurencin A., Benefit of mesh adaptation vs. conventional CFD approach for nacelle aerodynamics with ground effect, Conference: NAFEMS France 2020.
Lumley J.L., Yaglom A.M.: A Century of Turbulence, Proc. VII European Turbulence Conference, Barcelona, 2000.
Wilcox D.C.: Turbulence modeling for CFD, 2000.
Anderson B. H., Study on Vortex Flow Control of Inlet Distortion, journal of propulsion and power, Vol. 8, No. 6, Nov.-Dec. 1992.
Arif I., Salamat S., Ahmed M., Qureshi F., Shah S., Comparative Flow Field Analysis of Boundary Layer Diverter Intake and Diverterless Supersonic Intake Configuration, Journal of Applied Fluid Mechanics, Vol. 11, No. 4, pp. 1125-1131, 2018.
Ibrahim I.H., Ng E.Y.K., Wong K., Flight Maneuverability Characteristics of the F-16 CFD and Correlation with its Intake Total Pressure Recovery and Distortion, Engineering Applications of Computational Fluid Mechanics, Vol. 5, No. 2, pp. 223-234, 2011.
Karlsson A., Fuchs L., Vortex systems and the interaction between an air inlet and the ground, ICAS 2000 CONGRESS, ICAO522, pp.522.1-522.10
Lotter K.W., Mackrodt P. A., Engine surge simulation in wind-tunel model inlet ducts, ICAS-88-4.11.4, ICAS and AIAA, pp. 1773-1788, 1988.
Kozakiewicz A., Development of a Model for the Intake Channel within a MRCA Turbine Engine in Order to Analyze Intake Vortex Phenomena, the Solid State Phenomena vols. 198 and 199, pp.188-193, Zurich, 2012, Switzerland.
Kozakiewicz A., Frant M., Numeric analysis of the intake vortex formation in the case of a double fuselage shielded inlet, Journal of Theoretical and Applied Mechanics, 52, 3, pp. 757-766, 2014, Warsaw, Poland.
Kozakiewicz A., Frant M., Kachel S., Analysis of impact of gust angle and velocity on the position of stagnation point, Advances in Science and Technology research, ASTRJ-01362-2020-02,14, 4, pp.49-57, 2020, Poland
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