Engineer Project

RESUME

K.VISHESHWAR RAO

Objective:

Address:

C/O K.S.NAIDU To implement my skills, abilities, knowledge and

Plot.no:15 exercise the same for the benefit of my career and

Lake view Enclave, for the growth of organization.

Miyapur,Hyderabad,

PIN-500049.

Educational qualifications:

Phone:

+91-950******* B.Tech(Mechanical)-2012 (JNTU UNIVERSITY)

+91-998******* Turbomachinary Institute of Technology&science,

Patancheru,Hyderabad,

Email: 55%

*********@*****.*** Diploma(Mechanical)-2008 (SBTET)

Govt.Boys College, Nizamabad.

59%

Personal Details:

Father's Name: 10th Standard (SSC) - 2005

K.Suryanarayana Tagores Vidya Niketan High School,

Nizamabad.

59%

Date of Birth:

16-11-1987 Technical qualifications:

Nationality:

Indian Post Graduation Diploma in Computer Application.

AUTO CAD in Mechanical.

Languages Known:

English, Hindi, Telugu.

My strengths:

Self confidence.

Good communication skills.

Ability to work in group and as an individual.

Willingness to learn, adapt new technology in a very

short period time.

Experience:

Having one year experience as a Field Engineer in

CPP 2*18 MW in Thermax O&M

PROJECT DETAILS:

Title of the project : Computational Fluid Dynamics Analysis Of

Subsonic Nozzle.

Key words : Mass flow rate,Isentropic,Mach number.

Tools : Gambit and Fluent.

Abstract:

The purpose of goal of the project is numerical calculation of mass

flow rate of a nozzle. Here we are going to calculate the mass flow rate of

nozzle and output of the nozzle is being observed, by varying the input

parameters like mass,area,and density so on.

Nozzle is a device which accelerates the velocity of the fluid at the

expense of pressure. There are different types of nozzle which depend upon

flow properties like pressure, velocity and also density too. The smallest

section of nozzle is called as throat.

In ideal case, the flow through nozzle is isentropic. The chief use of

nozzle is to produce the jet stream or gas at high velocity to produce the

thrust for the propulsions of rocket motor and jet engine and to drive the

stream and gas. And show that the back pressure should be equal to

atmospheric pressure.

Initially, the dimensions of the nozzle are being calculated manually

using area velocity rule, the calculated dimensions are used to design and

analysis usig gambit and fluent and the result are analyzed.

Declaration:

I hereby declare that all the information

mentioned above is true to the best of my knowledge.

Date:

Place:

(K.Vishweshwar Rao)

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