NUMERICAL INVESTIGATION OF TRAPPED VORTEX COMBUSTOR

NUMERICAL INVESTIGATION OF TRAPPED VORTEX COMBUSTOR

A new combustor concept referred as the trapped vortex combustor (TVC) employs a vortex that is trapped inside a cavity to stabilize the flame. The cavity is formed between two axis-symmetric disks mounted in tandem. 

TVC offers many advantages when compared to conventional swirl stabilizers. In the present work, numerical investigation of cold flow (non-reacting) through 3D trapped vortex combustor will be performed.

 Commercial CFD software Fluent has been used for this study. The other main objective of our study will be to evaluate the performance and combustion stability of trapped vortex combustor when the fuel-air ratios are varied. 

This will in turn lead to change in diameter of air injection holes present at the cavity walls. For different fuel-air ratios, diameters will be calculated from one dimensional continuity equation.

CFD ANALYSIS FOR HIGH-LIFT CONFIGURATION TO CAPTURE AERODYNAMIC COEFFICIENT

 CFD ANALYSIS FOR HIGH-LIFT CONFIGURATION TO CAPTURE AERODYNAMIC COEFFICIENT

The sizing and efficiency of an aircraft is largely determined by the performance of its high-lift system. Subsonic civil transports most often use deployable multi-element aerofoils to achieve the maximum-lift requirements for landing, as well as the high lift-to-drag ratios for take-off. However, these systems produce very complex flow fields which are not fully understood by the scientific community. In order to compete in today's market place, aircraft manufacturers will have to design better high-lift systems. As part of this effort, computational aerodynamic tools are being used to provide preliminary flowfield information for instrumentation development, and to provide additional insight during the data analysis and interpretation process. Flow computation around a simplified three element high lift configuration without the fuselage and a realistic high lift configuration with fuselage are performed to study flow near wing-fuselage junction and also determine the flow separation with angle of attack.

CFD ANALYSIS USING DIFFERENT MESHING SCHEMES

CFD ANALYSIS USING DIFFERENT MESHING SCHEMES

The multigrid algorithm is an extremely efficient method of approximating the solution to a given problem. The functions involved in the calculations are all discrete, or discontinuous, 

The algorithm's efficiency lies in the fact that once an approximate solution to the problem is found its accuracy can be improved using calculations on increasingly sparse grids which require less processing power. 

In this project the theory behind the multigrid algorithm was studied and a computer analysis was done in solving the problem of natural convection. 

Stream function-Vorticity approach and the Bossinesq approximation were used in the analysis. Also, the same problem was solved using the Multigrid algorithm using Fluent software. The results obtained were matched with the analytical results.

COLD FLOW ANALYSIS OF SCRAMJET ENGINE

COLD FLOW ANALYSIS OF SCRAMJET ENGINE

The combined analytical and computational analysis is carried on the scramjet engine design. Numerical turbulence model is verified for better prediction of results computationally.

 Then Computational analysis is carried out for different ramp at inlet to obtain efficient intake. Factors considered are total pressure loss, entropy change, pressure ratio and temperature ratio in analysis of different ramp design. 

Furthermore a flow field prediction of complete scramjet engine with cold flow is carried out computationally. 

Then solution of separation bubble by including circular slit inside isolator is tested computationally. Circular slit is modified for minimum temperature and turbulent kinetic energy inside isolator section.

AERODYNAMIC ANALYSIS OF WIND TURBINE BLADE

AERODYNAMIC ANALYSIS OF WIND TURBINE BLADE

Computational Fluid Dynamics (CFD) software was used to compare the performance of a wind turbine blade. The geometry was simplified to 2D airfoils and the surrounding flow field. 

It was found that the lift/drag characteristics of the two airfoils across a range of angles of attack were virtually identical, meaning that the torque force exerted on the wind turbine blades would also be identical and therefore as would the power outputs of the two turbines.

 However, the simple model ignored a number of important issues, such as 3D effects on the idealized blade geometry. Further modelling and/or experimental validation work is needed to increase confidence in the quality of the results.