Associate Engineer
GKN AEROSPACE ENGINE SYSTEMS INDIA PRIVATE LIMITED
Total des années d'expérience :9 years, 5 Mois
Gas turbine product simulation. Structural Simulation .NC Substation and material saving leading to better financial saving.
Analysis of Gas Turbine Engine Component
• Forecasting Material requirements for upcoming planned tasks in Line Maintenance & Base Checks.
• Generation of Work packages for Line accomplishable tasks.
• Generation of Component work orders for accomplishment of tasks for spares on shelf.
• Staggering the Maintenance tasks to ensure a sustainable Material Support.
• Closely monitoring replacement of Rotables to ensure maximum utilization of Rotables to their optimum or determined life, which in turn ensures timely replacement and return of contracted Rotables.
• Analyzing Material consumption for complied Base Checks & Line tasks to understand the trend and further optimize material preloading.
• Establishing the Material and tool requirements for a particular task by reading the applicable Maintenance Documents (AD, SB, AMM Etc.).
• Establishing Material requirements for setting up of a new line maintenance station and positioning the same as per the approval desired for the new station.
Recent Projects
* Data migration from RAL to AMOS
* Procurement of various tool and Commercial Items to ensure
smooth Running of the Cargo stores stock and airlines
* Data Analysis of various freight forwarders to determine the
best and most economical one with regards to cost.
* Tire data analysis to determine the average landing obtained
for the various vendor for claiming any unwanted Loss
* Relative net cost estimation of the current fleet for various
tires to obtain the comparatively cheapest ones which has
been successfully utilized currently to gain maximum profit
Papers Presented :
1. T. Varghese Mathew1 and Sharanappa V. Sajjan2, “Time Domain Aeroelastic Analysis of an Aerofoil” CFD Annual Symposium, 2015.
2. Vasanth Dhanagopal1, T. Varghese Mathew2 and Sharanappa V. Sajjan3 “Time Domain Flutter Analysis of the AGARD 445.6 Wing” CFD Annual Symposium, 2016
Work Summary :
2 DOF rigid body flutter of a typical wing section as well as flutter analysis of a deformable AGARD 445.6 wing was carried out by using time domain fully coupled SU2 software at National Aerospace Laboratory- CTFD Division, Council of Scientific Research, India).
Rigid Body Flutter of Isogai wing Section\[NACA 64a010 Airfoil\]
Fully Implicit time marching scheme is utilized for flutter boundary determination of NACA-64A010, typical wing section of Isogai wing .Unsteady RANS equations are used to determine the flow parameters. The implicit RAN's equation is coupled to the governing structural equation of motion. Dual Time Stepping is used for achieving better convergence in each time step. The response of the wing section to the flow fluctuation is used to determine the critical flutter values at each mach number The results are utilized to distinguish the stable, unstable as well as critical mach number domain at each mach number along with the transonic dip region in the Mach Number V/s Flutter index curve
Agard 445.6 Deformable Wing Flutter Analysis
Flutter analysis was carried out determine the critical flutter index for the Agard 445.6 deformable wing at Mach No.0.499 & 0.678.Pointwise Software is utilized for building the required Su2 mesh file format by building the CFD and Structural domain separately and later combined into a single file manually by carefully editing and adding mesh file parameters which also includes markers like Izone which provides Su2 details about the zone number (1=fluid, 2=solid)
Newmarks time marching Implicit scheme is utilized for determining the Displacement, velocity and acceleration at each nodal point of the wing . the results obtained are in agreement with the available experimental data
Objective:
1. Obtain flutter index V/s Mach number graph within transonic flight regime ( 0.7 to 0.95 Mach) for ISOGAI wing
2. Steady state analysis of AGARD 445.6 wing and NACA 64a010 Airfoil using su2 Simulation code
Responsibility :
• Mesh Generation using Hypermesh Software
• Thermal Stress Analysis
• Prediction of nodal temperatures of bodies (turbine, combustor casing ) subjected to hot flow
• Post-processing And Report Generation
Projects
• Jet Pipe Liner Thermal Analysis
• Turbine casing Stress Analysis
• Fan Split Casing Analysis
• Exhaust frame thermal Analysis
Responsibility :
• Domain Discretization of provided CAD model
• Analysis in ANSYS mechanical APDL
• Result validation and preparation of reports
• Mesh Generation Using Hypermesh
Projects
• Exhaust Cone Stress Analysis
• Debris Guard Stress Analysis
• Engine Casing Buckling Analysis