Loading...
Search for:
flow-distortion
0.009 seconds
Dynamic Performance Simulation of a Turbofan Engine with Inlet Flow Distortion
, M.Sc. Thesis Sharif University of Technology ; Ghorbanian, Kaveh (Supervisor)
Abstract
Turbofan engines are widely employed as the propulsion unit in commercial aircrafts. Turbofan engines may experience inlet flow distortion during their operation which may alter the performance magnitude and stability of the engines. In this research, an object-oriented (modular) model for turbofan engine components is developed by using Simulink/Matlab. Through the integration of the 1D models and the related thermodynamic equations for the engine components, the engine design point is determined. The off-design performance matching across the different components is established by scaling the characteristics and incorporating matrix iteration method. The spool dynamics is used to simulate...
Performance investigation of a supersonic air intake in presence of boundary-layer bleed
, Article 32nd AIAA Applied Aerodynamics Conference ; June , 2014 ; Javad Sepahi, Y ; Daliri, A ; Sharif University of Technology
Abstract
The performance of an axisymmetric supersonic mixed-compression air intake has been investigated experimentally. The intake has been designed for free stream Mach number of 2.0. This study has two main goals, firstly to investigate the performance of the intake without boundary-layer bleed in design and off-design conditions and secondly to study the effects of a slot bleed on the intake performance. The intake has been tested at free stream Mach numbers of 1.8, 2.0, and 2.2 and zero degree angle of attack. Total pressure recovery (TPR), mass flow ratio (MFR) and flow distortion (FD) have been selected parameters to assess the intake performance. The bleed slot is located upstream of the...
Numerical simulation and parametric study of a supersonic intake
, Article Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering ; Volume 227, Issue 3 , January , 2013 , Pages 467-479 ; 09544100 (ISSN) ; Younsi, J. S ; Farahani, M ; Masoud, A ; Sharif University of Technology
2013
Abstract
A computational fluid dynamics code was developed to compute the flow inside and around a supersonic external compression axisymmetric intake. The code solves the Reynolds-averaged Navier-Stokes equations using an explicit finite volume method in a structured grid and uses the Baldwin-Lomax algebraic model to compute the turbulent viscosity coefficient. Experiments were performed to validate the predicted results and good agreements are achieved. In the next part of the research, a parametric study was undertaken using the designed base case at a constant Mach number of 2 and at 0° angle of attack. The effects of various important parameters such as free stream Mach number, spike deflection...
Performance investigation of a supersonic air intake in the presence of the boundary layer suction
, Article Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering ; Volume 229, Issue 8 , 2015 , Pages 1495-1509 ; 09544100 (ISSN) ; Sepahi Younsi, J ; Daliri, A ; Sharif University of Technology
SAGE Publications Ltd
2015
Abstract
The performance of a supersonic mixed compression air intake has been investigated experimentally. The intake is of axisymmetric one and has been designed for a free stream Mach number of 2.0. The present work has two main goals, first to investigate the performance of the intake without boundary layer bleed at design and at off-design conditions and second to study the effects of a bleed slot on the intake performance. The intake has been tested at free stream Mach numbers of 1.8, 2.0, and 2.2 and at zero degrees angle of attack. Total pressure recovery, mass flow ratio, and flow distortion have been selected to assess the intake performance. The bleed slot is located upstream of the intake...
Geometrical scaling effects on supersonic inlet performance
, Article ASME 2017 International Mechanical Engineering Congress and Exposition, IMECE 2017, 3 November 2017 through 9 November 2017 ; Volume 1 , 2017 ; 9780791858349 (ISBN) ; Soltani, M. R ; Khajeh Fard, A ; ASME ; Sharif University of Technology
American Society of Mechanical Engineers (ASME)
2017
Abstract
The effects of geometrical scaling on a supersonic external compression axisymmetric inlet are investigated. Various lower and higher geometrical scales of supersonic inlet are considered as the case studies. The inlet flow is simulated numerically using RANS solver along with the SST k-w turbulence model. The numerical results are in an acceptable agreement with the NACA experimental data at free stream Mach number of 1.79 and at zero angle of attack. The results show that the static pressure distribution of the inlet flow experiences some differences for various scales especially at the regions of the flow entrance and throat area. The mean flow Mach number and the mass flow rate at the...