RESUME

2016

2014

2013

2010

2008

MohdAzhar 07207871993, 09700745184

[email protected]

Linkedin.com/mohd-azhar

14-1-129/27/15P PADMAVATHI NAGAR BORABANDA HYDERABAD-500018

CONTACT

To join an organization that gives me an opportunity to showcase my designing skills and also helps me gain practical exposure in designing sector.

GOAL

EDUCATION

Master In Machine Design (72%)Auroras Scientific Technological and Research Academy, HYDERABADAffiliated to JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

Bachelor in Aeronautical Engineering (68%)Maheshwara Institute of Technology, MEDAKAffiliated to JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD Diploma in Manufacturing and Product DesignAlison.com

Board of Intermediate (64.7%)Sultan Ul Uloom Junior College, HYDERABAD Board of Secondary Education (73%)Nagar Juna High School, HYDERABAD

SKILLS

Teamwork

Communication

Self Motivated

Leadership

June 2016– September 2016November 2014 – May 2015

October2015– December 2015

MohdAzhar 07207871993, 09700745184

[email protected]



CONTACT

EXPERIENCE

GIS EngineerShraddha Technologies

CERTIFICATIONS

● AUTOCAD (CANTER CADD CENTRE, AMEERPET)

● CATIA V5 (CANTER CADD CENTRE, AMEERPET)

● ANSYS APDL (CANTER CADD CENTRE, AMEERPET)

● MS OFFICE (NI-MSME, YOUSUFGUDA)

● UG NX 9.0 (DESIGN TECH SYSTEMS, BANJARA HILLS AND SIEMENS)

● AcuSolve, AcuConsole, AcuFieldView (AEROTRIX, BANGALORE)

TPROFESSIONAL ATTRIBUTES

● A high standard of professionalism in my work

● The ability to remain calm and objective in all situations

● The ability to quickly identify and resolve client problems

● Able to work autonomously and in a team environment

● A good sense of humour and the willingness to be part of a team

InternshipDesign Tech System

Internship / Academic ProjectFrugal Technologies Private Limited

SS

MohdAzhar

CONTACT14-1-129/27/15P PADMAVATHI NAGAR BORABANDA HYDERABAD-500018

07207871993, 09700745184

[email protected]


PERSONAL PROFILE

NAME : MOHD AZHAR

FATHER NAME : MOHD GHOUSE

D O B : 02-07-1993

AGE : 23 YEARS

MARITAL STATUS : UNMARRIED

GENDER : MALE

RESIDENTIAL ADDRESS: 14-1-129/27/15P PADMAVATHI NAGAR BORABANDA

HYDERABAD

NATIVE : HYDERABAD

LANGUAGE KNOWN : ENGLISH, HINDI, TELUGU

EXPECTED SALARY : AS PER COMPANY NORMS

CELL NO : 7207871993, 9700745184

PASSPORT NUMBER : L6530074

I do here by confirm that the information furnish above is true to the best of

my knowledge and belief

DATE:

PLACE:

(MOHD AZHAR)

DECLARATION

MohdAzhar

CONTACT


07207871993, 09700745184

[email protected]


MTECH PROJECT

Aerodynamic Static Structural Analysis of VAWTIn this project a model for the evaluation of the energy performance and

aerodynamic forces acting on small straight bladed Darrius type vertical axis wind turbine depending on blade geometrical section has been developed, based on a analytical code coupled to a solid modelling software’s which was linked to FEA (Finite element analysis) & FVM (Finite volume method) of structural and CFD code for calculation of rotor performance.

Here the design of VAWT with NACA 0021 airfoil which is able to generate the max power of 63.71watt at velocity of air 6.0554m/s is an optimal design at rated 75 RPM. The above design has been studied with aerodynamic static structural analysis using ansys 16.0 which results to safe design without any potential failure in model.

The straight three bladed vertical axis wind turbine rotor is with 310 angle of attack in order to improve the performance of rotor. By changing rotor maintain the height and diameters of rotors the weight of rotor are significantly increase the weight without compromising the performance of the rotor. For this purpose aerodynamic static structural analysis in ANSYS of a straight blades VAWT rotor has been undertaken. Due to limitations on experimentations, aerodynamic approach has been used to quantify the wind load on the blades.

The main aim of this project is to design and analysis of an efficient Vertical Axis wind turbine, on the further application of this loads, structural behaviour of the rotor is obtained for a pre-determined set of operating conditions. The result form the analysis is compared with pre-existing once for the purpose of validation.

PAPER PUBLISHED

PAPER TITLE : Aerodynamics Static Structural Analysis of VAWT

JOURNAL : INTERNATIONAL JOURNAL OF SCIENTIFIC ENGINEERING AND TECHNOLOGY RESEARCH

PUBLISHED MONTH : SEPTEMBER 2016

PAPER (JOURNAL) LINK: http://ijsetr.com/issue.php?issue=ISSUE%2029&volume=Volume5

MohdAzhar

CONTACT14-1-129/27/15P PADMAVATHI NAGAR BORABANDA HYDERABAD-500018

07207871993, 09700745184

[email protected]


TECHNICAL SEMINAR

MAIN PROJECT

MINI PROJECT

Design and Analysis of Radial Turbine Flow behaviour is observed inside the turbine at different guide vane angles and got the maximum radial inflow turbine efficiency for all cases and comparison is done between theoretical efficiency. Characteristic curve is verified for all the different guide vane angles. For every case inlet velocity is changed as 10m/s, 7m/s, 4 m/s. Using CATIA V5 and ANSYS APDL software are used.

In a radial inflow turbine the flow enters the nozzle blades in the radial direction (or in the case of a swirl generating volute in the tangential direction). The flow enters the rotor blades in the radial direction, is turned in the rotor passage and exits along the axis of rotation.

Radial inflow turbines are suitable for many applications in ship, aircraft, space power systems, and other systems where compact power sources are required. They are also used in air liquefaction plants and have been employed in power generation units providing up to 2 megawatts of power for a variety of industrial applications, aiming to replace heavy diesel engines. Radial turbines have several advantages over an axial turbine..

Fabrication of Electronic IgnitersElectronic igniters are used as spark plugs which by increasing the

temperature it starts the engine by the use of battery attached to it through wires, so that it reduces the mechanical energy for starting the engine

Anti icing System of Aircraft Anti icing is a system which uses anti icing liquid over the surface of the aircraft so that there is no ice formation for a certain period of time. It is applied before the operation of the aircraft.

Anti-icing of aircraft is accomplished by applying a protective layer, using a viscous fluid called anti-ice fluid, over a surface to absorb the contaminate. All anti-ice fluids offer only limited protection, dependent upon frozen contaminant type and prevailing weather conditions. A fluid has failed when it no longer can absorb the contaminant and it essentially becomes a contaminant itself. Even water can be a contaminant in this sense, as it dilutes the anti-icing agent until it is no longer effective Preemptive, turned on before the flight enters icing conditions Includes: thermal heat, prop heat, pitot heat, fuel vent heat, windshield heat, fluid surface deicers, and propeller anti icing, wind shield anti icing, electro impulse deicing and boots

RESUME

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