Engineer Quality Assurance

HARINKUMAR PATEL

*** ***** **** *****, ********, TX 75098 Cell: 469-***-**** **********.*****@***.***.***

EDUCATION:

Master of Science in Aerospace Engineering (GPA 3.63): University of Texas at Arlington, TX [2016]

Thesis: Parametric cycle analysis of Adaptive Cycle Engine using NPSS.

Bachelor’s in Aerospace Engineering: MVJ College of Engineering (MVJCE), Bangalore, India [2014]

Research: Flame stabilization of Stagnation Point Reverse flow(SPRF) Combustor.

CORE COMPETENCIES:

Rocket Propulsion, Air Breathing Propulsion, Hypersonic Propulsion, Propulsion cycle analysis, Optimum operating parameters.

Structures, Aerodynamics, Thermodynamics, Gas dynamics, Heat Transfer, Fluid Mechanics.

Aerospace systems, Control Engineering, Aircraft performance, Vibration, Computer-aided Design drawing

Finite Element Analysis (FEA), Computational Fluid Dynamics (CFD), Composites, and Design of Machine Elements.

Mechanical Design (CAD/CAE), Engineering Drawings, Sheet Metal Designing, BOM (Bill of materials), ASME Y14.5 GD&T.

Material Testing, foundry and forging, material science, numerical methods.

TECHNICAL SKILLS:

CAD/FEA/CAE :

Solid Edge (V18, V19), SolidWorks, Numerical Propulsion System Simulation (NPSS), ANSYS, MATLAB, CATIA-V5, ANSYS Fluent 14.5, Siemens NX, ICM-CFD, LabVIEW, Mathematica, Simulink

Programming :

Basic C, Visual Basic, Oracle, C++, CMM

General Skills :

Microsoft Office (Access, Excel, Outlook, PowerPoint, Word), Photoshop

EXPERIENCE:

Quality/Manufacturing Engineer Rave Gears, Seguin, Texas, USA [Jan 2017 – Dec 2017]

Gained hands-on shop-floor experience with moderate to complex measurement systems.

Worked with GD&T and developed CMM programs for different manufacturing models.

Designed, installed and evaluated the systems, procedures and statistical techniques of quality assurance process.

Perform tasks of designing, testing methodology, mechanism and equipment of aerospace systems.

Handled responsibilities of developing and formulating quality assurance policies and procedures.

Coordinated with engineering staff on quality related issues.

Responsible for conducting training sessions on quality assurance tools and concepts for junior engineers.

Handled tasks of analyzing quality data and provide recommendations on revision of specifications, when indicated.

Maintained a quality program for multiple department, quality assurance, root cause corrective action and return material authorization, problem solving, risk evaluation and mitigation, failure analysis, cost reduction, scrap reduction, continuous improvement, statistical process control, operation tanning, customer requirement interpretation and implementations, first article inspection, assist with customer audits.

Production Engineer Chalthan Sugar Factory, Gujarat, India [Jul 2016 – Dec 2016]

Made decision upon prioritizing the part that is critical and required at the earliest

Provided support to senior engineer in the maintenance of equipment like boiler, turbines, distillation tower, heavy duty pumps, storage tanks, belt conveyors

Carried out audit for inventory of the parts that are frequently required when the factory is functional, responsible to monitor sugar production with continuous feeding of raw material without any interruptions to the production, continuous monitoring of boiler pressure and maintain at desired level.

Graduate Teaching Assistant University of Texas at Arlington, TX [Jan 2016 – May 2017]

Attended lectures, transcribed and provided notes to students, tracked attendance, proctored and graded exams, entered and maintained grades, and provided review preparation for final exam.

Held weekly office hours to provide tutoring, counseling, or assistance to students in need.

Proved an approachable teaching assistant, enhancing learning via real world/academic experiences and examples

Enforced all University policies and procedures

Obtained and protected information regarding student's disabilities and facilitated appropriate accommodations in the classroom.

Performance Evaluation of Adaptive Cycle Engine

Numerical simulation of a variable cycle aircraft engine was performed using Numerical Propulsion System Simulation (NPSS) software to evaluate the performance of the new adaptive cycle engine and determine how the engine will operate for different flight conditions.

Optimum values of Turbine Entry Temperature(TET), Fan Pressure ratio, Compressor Pressure ratio were obtained for design conditions.

Off-design performance for low altitude dash and high-altitude cruse were obtained.

Different mixer combinations were taken into consideration.

Designed a Gas turbine system (High-bypass turbofan) and Dual-mode scram jet propulsion engine.

Design a High-Bypass, twin-spool turbofan engine cycle for a commercial transport aircraft to meet the mission requirement of flight traveling at 40,000 ft at Mach of 0.9 and range of 11000 Km and take-off thrust of 100,000lbf.

Gas Turbine system was designed using NPSS and MATLAB;

Researched best values performance parameters: operating Turbine Entry Temperature (TET), Pressure Ratio, Bypass ratio and fan pressure ratio.

Transient mode analysis for the engine was also performed and variation of fuel flow rate, air flow rate, RPM, TET, and thrust with time was studied.

Design a dual-mode scramjet propulsion system for a hypersonic cruise vehicle with a payload mass of 1000 kg and an operational range of 2000 km.

Dual-mode scram jet engine was designed using Hypersonic Airbreathing Propulsion (HAP) software, calculations and Excel. Calculations for both hydrocarbon and hydrogen fuel were done.

Hypersonic inlet and combustion chamber, nozzle were made and analyzed using HAP and MATLAB respectively.

Researched the effects of different parameters for the flight to obtain max specific thrust and low specific fuel consumption values.

Values for design and off-design performance of an engine were obtained.

Different types of Rocket nozzles

Led a team in studied several nozzle concepts that promise a gain in performance over existing conventional nozzles,

Advantages, disadvantages and operation of different types of rocket nozzle designs were studied.

Studied different propellant and propellant compatible materials for use in cryogenic and high temperature environments.

Led team members through group projects; prioritized and assigned tasks, coordinated meetings and communications, and interfaced with vendors to purchase materials

Studied the effect of nozzle material on pressure and thrust variation in liquid propulsion system

Determined pressure and thrust as a function of time for no throat erosion in liquid propulsion system.

Measured and compared the values of thrust and pressure for three different nozzle configurations: Base line with slug ater the grains, printed nozzle with slug after the grain and base line nozzle with slug before the grain.

Concluded that nozzles made by additive manufacturing does not give the same projected results as that of by conventional method.

Flame stabilization of stagnation point reverse flow combustor

Numerical simulations were performed using a commercial CFD code to evaluate the performance, mixing and combustion characteristics of the SPRF combustor.

Pressure, velocity and temperature values were obtained for different combinations.

The results were calculated for 2D model, for different boundary condition and the best preferable condition obtained were used for simulating 3D model.

Uncontrolled flow analysis was performed on 3D model to know how actually the flow will propagate inside the stagnation point reverse flow combustor.

The 2D and 3D models were made using Ansys fluent and Catia v5 respectively. Flow analysis was done using Fluent.

Designing in Catia, Ansys and SolidWorks,

Designed and performed stress analysis of bulkhead using SolidWorks and ANSYS

Designed an airplane, engine fan, turbine, etc. using SolidWorks and Catia V5

Able to read and interpret basic mechanical drawings and electrical schematics

PUBLICATION:

performance evaluation and Flame stabilization of stagnation point reverse flow combustor, International Journal of Research in Engineering and Technology(IJRIT) (eISSN: 2319-1163 pISSN: 2321-7308)

MEMBERSHIP:

American Society of Mechanical Engineers (ASME)

American Institute of Aeronautics and Astronautics (AIAA)

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