ARUN KUMAR C

4/38, SALANGUKARA STREET, PARANGIPETTAI, CUDDALORE,

TAMILNADU, INDIA-608502 MOBILE: +919994864142 EMAIL:arunhoc.kumar16@outlook.com

WORK EXPERIENCE

ASSOCIATE ENGINEER, DEC 2015 – till date

FLUDYN ADVANCED TECHNOLOGY CENTER-CRI PUMPS,

COIMBATORE, TAMILNADU, INDIA.

Theoretical Design and CFD Analysis of Industrial and Domestic Pumps.

RESEARCH ASSOCIATE, JUNE 2014 – NOV 2015. PARK RESEARCH CENTRE, COIMBATORE, TAMILNADU, INDIA.

Worked in research project funded by DRDO Theoretical Design and CFD analysis of Pumps and Turbines

RESEARCH ASSISTANT, SEP 2011 - SEP 2012 PARK RESEARCH CENTRE, COIMBATORE, TAMILNADU, INDIA.

Experimental and CFD analysis

Surface flow visualization techniques

Plane laser induced fluorescent smoke flow visualization

Wind Tunnel Testing and Measurements

SOFTWARE SKILLS

ANSYS WORKBENCH ,

ANSYS CFX, FLUENT, ICEMCFD

CF TURBO, BLADE DESIGN

ANSYS DESIGN MODELER

STAR CCM+

SOLIDWORKS

CATIA V5(PART DESIGN, ASSEMBLY DESIGN,DRAFTING)

LABVIEW,MATLAB (INTERMEDIATE LEVEL)

RESEARCH PROJECT

1. DESIGN AND CFD ANALYSIS OF CENTRIFUGAL PUMP DESCRIPTION: CFD analysis of a Single and Multistage centrifugal pump was done for a specified boundary condition. The CAD model was meshed using ICEM CFD and was analysed in ANSYS CFX by specifying the design conditions, and the results were satisfactory and meeting the Customer Requirement.

2. DESIGN AND CFD ANALYSIS OF AXIAL PUMP DESCRIPTION: The design conditions for designing an axial pump were provided. Based on the design conditions a pump was designed, modeled in CATIA V5 and the pump characteristics were analysed using ANSYS CFX. Two different blade profiles were chosen to design the pump (10C4, and GO 428) and the pump characteristics obtained from CFD analysis were satisfactory.

3. DESIGN AND CFD ANALYSIS OF PUMPJET PROPULSOR DESCRIPTION: The project deals with the design of a pumpjet propulsor for a submarine. Two Axisymmetric streamlined bodies of different slenderness from DAVID TAYLOR MODEL BASIN reports were selected and computed for various Reynolds number using ANSYS CFX and compared with the experimental results. Having gained confidence, computations were carried out for an actual three dimensional submarine with control surface and the coning tower. The computed drag was 12% lower than the extrapolated experimental results which were done at relatively low Reynolds numbers in a towing tank (given by NSTL). Having computed the drag the velocity variation at the boat tail part of the submarine was extracted. The circumferential averaged velocity variation was calculated at various radius locations for the boat tail part accounting for the boundary layers on the control surface.

4. LOW REYNOLDS NUMBER PERFORMANCE OF SMALL ENGINE

TURBINE DESCRIPTION: Low Reynolds number performance of a typical small helicopter engine blade was tested in a low speed cascade wind tunnel. The pressure distribution and the wake profiles were measured at various incidences and for varying Reynolds numbers. When the Reynolds number was decreased the laminar separation bubble on the suction side of the blade increased both in stream wise and wall normal directions accounting for higher losses. It was observed that irrespective of the incidence angle there exist a critical Reynolds number, below which there was a sudden rise in the profile loss. This project was funded by Aeronautical Research and Development Board (AR&DB, India) and was done at PARK Research Centre.

M.E PROJECT: OPTIMIZATION OF INTERNALCOOLING CONFIGURATION IN A NOZZLE GUIDE VANE. DESCRIPTION: The main aim of this project is to reduce the temperature of the turbine blade by increasing heat transfer between the blade and the cold air. Turbine blade inter part is split into four channel and the ribs turbulator is placed in the leading edge channel because temperature is higher in that region. Rib Turbulator are used to reduce pressure and separate the flow inside the blade and it also increase the optimum heat transfer. B.E PROJECT: DESIGN AND ANALYSIS OF SOLID ROCKET MOTOR CASING DESIGN FOR A SATELLITE LAUNCH VEHICLE DESCRIPTION: The main theme of our project is to design a solid rocket motor case, its dome structure and its attachment. To design of solid rocket motor case, some assumptions are considered based on advantage and disadvantage. In this project, we selected the cylindrical case as a design structure. Torispherical dome and Segment joint straight pin attachment used in the conceptual design of the solid rocket motor case. We selected MARAGING STEEL grade250 material for the entire design case.

EDUCATIONAL QUALIFICATION

MASTER OF ENGINEERING IN AERONAUTICAL, JUNE 2014 CGPA -7.43/10 (First class)

ANNA UNIVERSITY, CHENNAI, TAMILNADU, INDIA. BACHELOR OF ENGINEERING IN AERONAUTICAL, JUNE 2011

CGPA - 7.0/10 (First class) ANNA UNIVERSITY, COIMBATORE, TAMILNADU, INDIA. HIGHER SECONDARY COURSE, APRIL 2007 Percentage - 85/100 (First class) KRISHNASAMY MATRICULATION SCHOOL, CUDDALORE, TAMILNADU, INDIA. SSLC, APRIL 2005

Percentage - 70/100 (First class) SEVAMANDIR MATRICULATION SCHOOL, CUDDALORE, TAMILNADU, INDIA.

EXTRACURRICULAR ACTIVITIES

Secured first place in SDAT district Hockey tournament. Secured first place in Coimbatore Zonal Hockey Championship Secured first place in Zonal Hockey tournament conducted by Anna university.

REFERENCES

Dr.A.P.HARAN (Group Director, Afterburner Division, GTRE, Bangalore (Retd.), Head of Aeronautical Engineering,

Park College of Engineering, Coimbatore. Phone no: 09789452202 Email:ap_haran@rediffmail.com