Gas Turbine

Modi Brijesh Dilipkumar

Personal Profile

DOB: **/05/1995

Address: Gujarat

Contact: *****************@*****.*** 735-***-****)

An inquisitive, passionate and hardworking Aerospace Engineer with a strong background in Aerodynamics, Aerospace propulsion and Turbulence Armed with Master’s degree in Aerospace Engineering and a Bachelor’s degree in Aeronautical Engineering.

Seeking a suitable engineering position to utilize my technical knowledge and Experience in a challenging working environment that offers opportunities for career growth while becoming a valuable asset to the organization.

SKILLS

Hard skills:

Design software: Ansys(1D & 2D), Turbogrid,

ICEMCFD, Fluent, Simulink, CATIA, Solid

WORKS,MATLAB, Hypermesh.

Proficiency in MS word, Excel, PowerPoint

Programming language: C, C++, Python

Operating system: Windows XP/Vista//7/8/10, DOS

Soft skills: Integrity, Effective communication, Adaptability, Willingness to learn, Empathy AREA OF INTEREST

Aircraft Propulsion Design of Compressor and Turbine Rocket Propulsion Fluid mechanics Aerodynamics Computational Fluid Dynamics Structures Composite Flight Mechanics Blade Element Theory Gas Turbine theory Engineering Math Thermodynamics Fundamental Of turbomachines Avionics Aviation Management Theory Of heat Transfer Aircraft Design

Space Dynamics.

EDUCATION

IIT Kharagpur

MTech [cgpa :8.42/10]

Related coursework:

Computational fluid dynamics

Advance gas dynamics

Unsteady Aerodynamics

Advance Gas Turbine Theory

Design Of compressor and Turbines

Propeller Theory

Computation Laboratory [c++]

SVIT Vasad

B.E [cgpa 8.67/10]

Related coursework:

Aerodynamics

Aircraft Propulsion

Aircraft Structures

Flight Mechanics

K.K Gothi High School

Higher Secondary school [Percentage :70]

K.K Gothi High School

Secondary school [Percentage :89]

June 2021

May 2017

May 2013

April 2011

ACADEMIC PROJECTS

Numerical Simulation of Turbine Blade Boundary Layer with Heat Transfer and Thermal Analysis of a Cooled Turbine Blade CSIR-NAL

• The boundary layer development and convective heat transfer on transonic turbine nozzle vanes are investigated using a compressible Navier-Stokes code with three low-Reynolds-number k- e models.

• Predictions from a parabolic boundary layer code are included for comparison with those from the elliptic Navier- Stokes code. The present study indicates that the turbine external heat transfer, under real engine conditions, can be predicted well by the Navier-Stokes procedure with the low-Reynolds-number k- e models employed.

• Using Computational Fluid Dynamic (CFD), a gas turbine with an air-cooled blade was analyzed thermally. An increase in gas temperature by 100 C resulted in 50-100 C increase in metal temperature, while, an increase in coolant temperature by 100 C resulted in an average 50 C increase in blade temperature. The results also show a temperature difference in blade metal of 250 - 450 C between the leading and trailing edges. So that we can extract more work from the turbine at lower RPM also. That increases overall performance of Engine.

Numerical Investigations on LP Turbine Nozzle Blade to minimize the Tip clearance losses MTech Project IIT Kharagpur

• Numerical analysis is carried out on Nozzle vane having annular cascade using ICEM CFD software. Numerical study done here by applying 2mm tip clearance on nozzle blade.

• The blade passage of axial turbine is very complicated mainly due to the presence of high freestream turbulence intensity, wall effect and unsteady upstream wake, which in turn lead to flow transition, formation of laminar separation bubble and secondary flow streams on the blade surface.

• Special attention is paid to the 3D structure of the tip leakage flow Leakage flow through the turbine blade tip clearance causes a strong leakage vortex near the suction side of the blade.

• Due to that tip desensitization technique used to decrease effect of leakage flow from tip clearance & also performance of blade in off design condition computationally analyzed. Design of Turbocharge System for an Existing Gas Engine Research Project

• A turbocharge system has to be designed and manufactured to fit an existing gasoline engine.

• to minimize turbo lag, the intake and exhaust breathing capacities of an engine must be matched to the exhaust and intake airflow capabilities of the turbocharger.

• Turbochargers deliver more power output and a greater torque, which in turns improve their vehicle performance on the road. And main Components of Turbocharge design system is: Turbine, compressor and connecting shaft.

Experimental Analysis & Manufacturing of Subsonic Wind Tunnel to decrease profile losses BTech Project

Umang Jani SVIT, VASAD

• Experimental and Numerical analysis on subsonic wind tunnel having 0.5 Mach by using different designing

& analyzing software, to make it easier & more effective (reduce losses) & also reduce cost of manufacturing by using composites.

• The test object is instrumented with suitable sensors (LOAD CELL) to measure aerodynamic forces, pressure distribution, or other aerodynamic-related characteristics. the interaction between the road and the vehicle plays a significant role, and this interaction must be taken into consideration when interpreting the test results.

ACHIEVEMENTS

• GATE 2018 qualified – All India Rank 129.

• Selected for National Conference on “MANUFACTURING OF SUBSONIC WIND TUNNEL”. CERTIFICATIONS

• Awarded course completion Certification in C++ & Python by Solo Learn.

• Awarded course completion Certification in “Complete Altair Hypermesh & Optistruct Course”

• Six Sigma Yellow Belt Certificate

EXPERIENCE

Development Professional Siemens Energy Dec 2023 (Working)

• Involved in the development and analysis of small and large gas turbine engines used for power generation.

• Conducted overall engine performance evaluations using various real gases, including hydrogen (H ), carbon dioxide (CO ), and nitrogen (N ).

• Performed in-depth analysis of the Secondary Airflow System (SAS) to enhance gas turbine performance and ensure component protection.

Engineering Analyst RR-Infosys June 2022 – Dec 2023

• Working on Trent XWB-84EP RR engine component thermal simulation of HPT & LPT to extract HTC.

• Numerical Analysis & Designing of turbomachines technology having aerothermal difficulties in off design performance like compressor, turbine etc.

• Performance Analysis, Thermal paint Analysis, Internal & External Cooling of turbine blades.

• Specially in engine, Turbine cooling network development to enhance overall performance of engine in different operating conditions & compressor aerodynamic performance analysis in off design conditions. Project Associate – II CSIR-NAL Nov 2021 – May 2022

• Designing & Overall performance analysis of KAVERI & Small Gas turbine Engine used for Defense.

• Numerical Simulation of Turbine Blade Boundary Layer and Heat Transfer Assessment of Turbulence Models effect during CFD.

• Analyzing & designing of micro gas turbine & small gas turbine engines used for Ballistic Missiles & UAV.

• Thermal Analysis of a Cooled Turbine Blade in VTTR Lab of CSIR-NAL. Project Assistant IIT Kharagpur March 2020- May 2021

• Research project was numerical & Experimental simulation-based project.

• Designed blade having Annular cascade profile by using ICEM CFD. Simulation done in Ansys.

• Appropriate results of modified blade design after getting Blade tip contouring on Stator blade. Which increases overall performance of the blade.

CFD Engineer LITHOERA Technology Pvt Ltd. July 2017- Dec 2018

• Responsibilities include analyzing products for fluid mechanics and applications, making recommendations for wide range of simulation findings & conducting applied research and optimization of computational methods.

• Interpretation of CFD results to assist in design modifications and to promote products in technical publication department, modelling of Air-frame structures and UAV. Project Intern AAA Jun 2015- May 2016

• Designed a flap & manufactured. it was connecting by using cable control system & Composite materials in maintenance department.

• Experience getting on piston prop engine having on two setter Cessna Aircraft.

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