Objective

Experience (* Years)

TOOLS

Hypermesh-17 & 19 (Knowledge on Hex Meshing).

Knowledge on Shell Meshing on Automotive BIW and Plastic parts.

ANSYS (APDL)19- Static Analysis, Modal Analysis,Thermal Stress Analysis

ABAQUS- Static Analysis, Thermal Stress Analysis, Buckling Analysis, Modal Analysis.

ISAMI EXPRESS TOOL.

Basic Level in Visual Basic Macros (VBA) using Excel.

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Key Skills

MEGHA RAO

+91-831******* / adh0n6@r.postjobfree.com

To pursue a highly challenging career, where I can apply my knowledge, acquire new skills, and contribute constructively towards the growth of the organization, accomplish significant competence, reputation and an enduring mutual success.

Academic Qualifications:

Course College University Passed out

year

Percentage %

B tech in

Aeronautical

Engg

Veltech University Veltech

University

2017 77

High School Kamaraj English

Medium School

CBSE 2013 63

Senior

Secondary

School

Kamaraj English

Medium School

CBSE 2011 83

Company : SG Aerospace India Private Limited, a Belcan Company. Duration : (13.01.20 -22.09.20) (9 MONTHS)

Role : Worked as a Trainee Stress Engineer.

Project #1: PREPARATION OF STATIC APPROVAL SHEET (SAS) OF AIRCRAFT REPAIR COMPONENTS.

Was involved in authoring the Static Approval Sheet (SAS) and the supporting documents for Daily Repair and ESG (Extended Service Goal) .We used to create the Static Pack, so that it is helpful for the level 2 Checker to go through our report.

Static Pack was created by initially by checking whether the type of job is ISQ or ESG, and then followed by the Damage Report.

Company : Gas Turbine Research Establishment (DRDO). Duration : (25.11.18 -10.01.20) – 1 years 2 months. Role : Worked as Project Engineer. (Stress)

Project #2 : HEXAMESHING OF HIGH PRESSURE COMPRESSOR 3RD AND 6TH STAGE ROTOR BLADE AND CARRIED OUT STATIC LINEAR ANALYSIS FOR DIFFERENT MECHANICAL LOAD CASES. (GHATAK ENGINE).

The Blade-Dovetail attachment was Hex meshed by maintaining quality parameters. Linear Stress Analysis was carried out in the model by applying the Mechanical Gas Loads and Omega at different Load Cases, with the help of Macros in ANSYS-APDL (18), to view the Stress and Mechanical Growth as Output.

Thermal Analysis was carried out using the Temperature Data’s provided by Heat Transfer Group. The scope was to know the Nodal Temperature Distribution at the different sections of Compressor Blade.

Thermal Stress Analysis was carried out by applying the Material properties, boundary conditions and by importing the Thermal history Data (.rth) as a load in Structural Analysis to obtain the Thermal Stress and deformation.

Finally, Structural -Thermal analysis were carried out by applying the Material properties, boundary condition and also by applying Mechanical loads and reading the thermal data in order to obtain the growth due to Structural and Thermal Loads. Project #3 : FE MODELLING OF FAN 2D AXISYMMETRIC ASSEMBLY. (KAVERI ENGINE) Meshing of complete Fan Assembly including first, second and third Stage including the shaft were modelled with 2D quad Plane Stress shell elements with quality parameter. Fine Mesh were given in Fillet and critical regions. The scope of this project was to build the FE model with flow through the mesh and setting up of Material property, boundary condition, calculation of Centrifugal loads and Coupling was given between two Flanges for Linear Stress Analysis, Thermal Stress and Structural-Thermal Analysis using the solver ANSYS-APDL AND ABAQUS.

Project #4 : FE MODELLING OF LOW PRESSURE TURBINE ROTOR BLADE INCLUDING FIRTREE ATTACHED TO DISK.(STFE-SMALL TURBO FAN ENGINE) STFE. A sector of the whole model had been taken and meshed 8 nodded Hex elements. The contact areas of blade and dovetail were meshed with same mesh flow by quality parameters and fillets were finely meshed. The material property and Blade gas loads were assigned along with boundary conditions in order to perform the Explicit Static Analysis using the solver Abaqus and ANSYS-APDL.

Project #5 : FE MODELLING OF HIGH PRESSURE COMPRESSOR 6th STAGE STATOR BLADE MODEL.(GHATAK ENGINE).

Stator blade model was meshed using Hyper mesh 17. The quality parameters were Maintained. The material property and in boundary the blade was constrained at the top and Bottom . Explicit Linear stress analysis, Thermal stress and structural-thermal analysis were carried out as per the guidelines

KNOWLEDGE ON SHELL MESHING BIW AND PLASTIC OF PARTS

FE MODELLING OF BACK DOOR, UPPER BODY DOOR AND FRONTER OF CAR. The given model was cleaned up as per requirement.Meshing of complete part were modelled with 2D Shell elements with proper quality parameters, thickness and material property was assigned for the whole model.

FE MODELLING OF PLASTIC PART ‘D’ AND ‘P’ PILLAR OF CAR BODY PARTS. The given model was cleaned up ar per required criteria.Care for assigning thickness and make separate collector for each feature. Taken the mid surface for meshing. Finite element is built using Shell mesh of mixed elements. Compared the meshed model with cad model so that any missed part or feature could not be detected. Finally, checked the quality of the elements.

Company : Gas Turbine Research Establishment (DRDO). Duration : (02.11.17 -02.11.18) - 1 year.

Role : Worked as Graduate Apprentice Trainee.

Project #6 : FE MODELLING OF LOW PRESSURE COMPRESSOR 2ND STAGE DISK AND CARRIED OUT THE STATIC LINEAR AND NON LINEAR ANALYSIS. (KAVERI ENGINE) The Bladed-Disk (Blisk) model was meshed keeping in care about the cyclic symmetric parts. Same mesh flow was maintained at contact of Blade-Hub and Dovetail in order to carry out the analysis in APDL & Abaqus.

Project #7 : FE MODELLING OF TURBOCHARGER TURBINE AND COMPRESSOR IMPELLER FOR STATIC LINEAR ANALYSIS. (KAVERI ENGINE)

Cyclic Symmetric model of impeller was meshed with 8 noded hex elements and solved by Applying the boundary conditions in order to carry out the analysis.( ANSYS-APDL & ABAQUS).

ACADEMIC PROJECTS

NUMERICAL ANALYSIS OF VORTEX SHEDDING AROUND THE BLUFF BODIES AT DIFFERENT FLOW REGIMES. (ANSYS WORKBENCH (FLUENT). Description: It was found that vortex shedding for the base cylinder was more than the serrated Cylinder (comprised of different wavelengths).

INDUSTRIAL TRAINING

Completed 27days summer training from COMPOSIT TECHNOLOGY PARK on AIRCRAFT MATERIALS.

SUMMER TRAINING IN COLLEGE

Completed summer training from REGIONAL METEORLOGICAL CENTRE ON OBSERVATION ON VARIATION IN WEATHER.

CERTIFICATES

Completed course on CATIA V6 for 2 months.

Member of SEDS (SPACE EXPLORATION AND DEVELOPMENT IN SPACE). PERSONAL PROFILE

Fathers name M. Nageswara Ra

Date of birth - 25th June 1993.

Languages Known Hindi, English,Telugu .

Address - Ratri Niwas Colony, Port Blair, Andaman & Nicobar . I hereby declare that all the information mentioned above is true and correct to the best of my knowledge. DATE-

PLACE MEGHA

MINI PROJECTS

AIRCRAFT DESIGN PROJECT (ADP).

Description: Different data from AIRCRAFT DESIGN PROJECT 1 & 2 were collected and aircraft With new data was made with the equivalent parameters.

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