Engineer Design

NARENDER KUMAR BHARDWAJ

**** ******* ***, *** *****, CA 92129

Tel: 858-***-**** • Email: ********@*******.***

PROFESSIONAL EXPERIENCE

THERMAL PAINT TEMP. TECH., INC. - San Diego, CA Sept, 2009 – Present

Engineering Consultant - Thermal Paint Technology

• Provide thermal paint technology consultancy and solutions to problems related with the thermal painting process. (This consultancy work is carried out as required on part-time basis).

HAMILTON SUNDSTRAND - San Diego, CA May, 2005 – Sept, 2009

Staff Engineer – Product Design Department

• Thermal analysis of cold module of APS5000 using ANSYS program. Implementation of standard heat transfer analysis tools.

• Provided and implemented thermal paint technology for testing rotating components.

• Responsible for secondary flow modeling of all Hamilton Sundstrand engines including APS5000 for

Boeing 787 aircraft, T-62T-46-3 for Navy Helicopter project CH-53K, etc.

THERMAL PAINT TEMP. TECH., INC. - San Diego, CA June, 2004 – May, 2005

Engineering Consultant - Thermal Paint Technology

• Provide thermal paint technology consultancy and solutions to problems related with the thermal painting process.

MTU AERO ENGINE DESIGN, INC. - Rocky Hill, CT Sept, 2001 – June, 2004

Supervisor/Consultant - Performance Engineering, Secondary Air Systems and Aerodynamics

• Provided performance engineering support to MTU's subsidiary Vericor's industrial & marine engine product line (ex Honeywell engines) such as TF50A, ETF40B, ASE40 and ASE8 using Honeywell's FAST performance program. Responsibility included using FAST program to match production test data.

• Mapping surge margins of the MTU/Pratt & Whitney PW6000 HP compressor using Tecplot & Guide programs.

• Responsible for the design and analysis of the secondary flow system of the LP turbine of the PW6000 engine using the MTU Edgel program.

• Supporting the parent company MTU in Germany in improving thermal paint technology processes.

WILLIAMS INTERNATIONAL - Walled Lake, MI Jan, 2001 - Sept, 2001

Contract Engineer - Heat Transfer/Flow Systems

• Cooling design of gas turbine engine components like turbine parts and heat exchangers. Secondary cooling flow network design and analysis using FINESSE program.

• Failure Mode Effect & Critical Analysis (FMECA) work and Safety Analysis (Fault Tree) for FAA airworthiness certification for the APU of the Comanche helicopter engine program.

PRATT & WHITNEY - Hartford, CT 1999 - 2001

Project Engineer - Heat Transfer & Systems Group

• Development of the process and FE thermal analysis of 3D hot gas path structures of the PW6000 engine using ANSYS program. The development of the process involved leading a team of structural, aerodynamic and blade cooling engineers.

• Secondary cooling flow system analysis of airflows, pressures and temperatures of the PW6000 engine and nacelle using FABLE and BECON programs.

• Provided solutions to stop the secondary corrosion cracking (SCC) of rotating turbine blades of jet engines.

• Introduced and organized digital automation of thermal paint technology to analyze combustors and other hot gas path components.

SOLAR TURBINES - San Diego, CA 1990 - 1999

Principal Design Engineer - Aero-Thermal Dept. 1994 - 1999

• Implemented complete thermal paint technology including computer visual methods to determine metal temperatures of hot section components of gas turbines, saving 80% cost in testing and reducing test and analysis time by 2/3. The implementation of this technology involved setting up of a new laboratory, working in close contact with other technicians, test engineers and design engineers, and specifying test conditions and analysis of the test bed data.

• Registered 2 patents: i) The method and apparatus for producing surface temperature maps of thermal paint tested components using computer digital imaging methods, and ii) Ceramic turbine blade with a tip seal.

• Designed and implemented from scratch a very user friendly secondary cooling flow network computer program called FINESSE which included full heat transfer application capabilities including cooling of blades and nozzles, and undertook the responsibility to use this program to model airflow cycles and determine air mass flows, temperatures and pressures of the entire cooling flow networks of Mars, Taurus and Titan engines.

Senior Design Engineer - Aero-Thermal Dept. 1990 - 1994

• Introduced advance blade and nozzle guide vane cooling techniques to the Heat Transfer Section, and analyzed blade and nozzle guide vane test bed data. Responsible for all heat transfer issues related to the Mars production engine. Provided secondary flow network support to the engine.

• Responsible for providing labyrinth seal expertise and other types of sealing technology to reduce hot gas ingress into disc cavities and bearing areas. Implemented W seal concept to the company’s product line to reduce hot gas leakage and introduced brush seal technology.

ROLLS-ROYCE - Coventry, UK 1978 - 1990

Development Engineer - Development Dept. 1988 - 1990

• Planned and technically controlled, life assessment and defect investigations and provided in-depth analysis of faults or failures which impaired operational integrity of Olympus, Spey and RB-211 engines. The analysis included mechanical and other tests. Areas of failure covered were blade failures, combustor injector failures, oil leakage and disc cracks. Critically appraised all design schemes (mechanical and thermal) for standardization and devised, instigated and was responsible for methods of evaluation by theoretical analysis or practical tests. Specified coatings for turbine blades and vanes for operations in the sea environment.

Aero-Thermal Engineer - Technology Dept. 1980 - 1988

• Aerodynamic profile design of turbine blades and blade internal cooling geometry design using state-of-the-art airfoil cooling computer aided design techniques.

• Analyzed blade-cooling designs using multi-pass, impingement and film cooling techniques. Made turbine blade creep life and thermal paint assessments.

Performance Engineer - Performance Dept. 1978 - 1980

• Conducted project studies on new engine concepts including novel gas turbines cycles (such as combined cycle) to identify extensions to existing product range.

• Analyzed and interpreted test bed data on engine performance to verify that the required standards are achieved and to identified any problems and propose the necessary solutions.

EDUCATION

Master of Science in Gas Turbine Technology - Cranfield University, Bedford, UK

Bachelor of Science in Mechanical Engineering - Brighton Polytechnic, Brighton, UK.

Diploma in Management Studies - Coventry (Lanchester) Polytechnic, Coventry, UK.

PROFESSIONAL DEVELOPMENT

Leading & Managing Successful Teams, Boston University.

Coping with Change - Strategies for Excellence.

ANSYS Basic and ANSYS Thermal Analysis Courses, Hartford.

CFD (StarCD) Course with Some Hands on Experience in Modeling a Labyrinth Seal.

Howmet Casting Tooling Course at Cleveland, Ohio.

Design, Analysis and Prediction of Solar’s Primary Surface Recuperators.

Advance Seal Workshops at NASA Lewis Research Center.

Advance Flow Calculations for Internal Flow and Turbo-Machinery.

Gas Flow Measurements; RB-211 Engine Familiarization; Product Reliability Techniques.

Patran and Flotran; Unix; Fortran; Adobe PhotoShop; MS PowerPoint; Excel; Word.

Effective Technical Presentation; Patent & Trademark Strategy.

Decision Making Process.

US CITIZEN

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