RESUME

Praveen Moyya

Email: adhtsp@r.postjobfree.com Mobile no: +91-965*******

OBJECTIVE:

Seeking a position to utilize my skills and abilities in an industry that offers professional growth while being resourceful, innovative and flexible.

PROFESSIONAL SUMMARY:

Finite Element Analysis (FEA) Engineer with 3 years 8 months experience as Thermal & Structural analysis in Aircraft gas turbine engine.

Having very good quality of technical skills in the field of Computer aided engineering.

Ready to join immediately.

PROFESSIONAL EXPERTISE:

•Strong professional experience on Thermal analysis (steady state & transient) and structural analysis (linear, nonlinear (Material, Geometry, Contact) & fatigue (LCF/HCF)) of rotating/static components of aircraft gas turbine engines.

•Having good knowledge in Model analysis/Goodman assessment on airfoil blades to provide the structural substantiation against nonconformance.

•Good knowledge in Fracture life assessment & crack growth study at nonconformance locations.

Good knowledge on damages/repairs substantiation of aero engine components and closely working with the design team to provide a suitable repair solution.

Having good knowledge in Modelling, solving, convergence issues and debugging of the Thermal & Structural models in ANSYS.

•Strong knowledge on setup the thermal boundary conditions on aero engine components according to the environment physics.

•Expertise in Thermal Validation Process.

•Expert in substantiating results with hand calculations using Heat transfer correlations.

•Good experience on geometry preparation in UG and creating 2D & 3D finite element modes of aero engine components.

Good coordination with thermal, structural and design teams to understand the physics of the problem & offer simplified FEM solutions to the customer.

Good skills in developing Automation techniques using ADPL & Python scripting.

•Take full ownership of deliverables and perform technical review of the analysis.

•Experience in writing thermal & structural analysis documents and creating Standard Work Instructions.

•Development of cost reduction and process improvement ideas.

•Coordinate with internal teams as well as customers.

TOOL KNOWLEDGE:

CAE TOOLS : ANSYS (Classic & Workbench), Hypermesh,

CAD TOOLS : UNIGRAPHICS NX9

CYIENT In-House Tool : AUTOMODELER, BCON, UNIGRAPH, MUDS, FABL, PW life tool

PROGRAMMING LANGUAGES : Python, ANSYS(APDL), C

Operating Systems : Windows

Area of Expertise : Gas Turbine Engine Component Heat Transfer & Structural Analysis

PROJECTS EXECUTED FROM CYIENT:

COMPANY: CYIENT LTD, Hyderabad, India

Project-1: Thermal Analysis of 2D-Bearing Compartments (#3, #4, #5/6) – Pratt & Whitney Engines

The main objective of the task is to provide thermals to structures for lifing at various design phases. Steady and Transient Thermal Analysis is carried out on various Bearing Compartment models to evaluate the thermals for different conditions. Predicted the maximum oil wetted wall temperature inside the bearing compartments to check with in the ESW limits. Data match analysis is also carried out to validate the results. This task includes built the Finite element thermal model using UNIGRAPHICS and ANSYS. Generate the thermal boundary condition on various zones and simulate the oil & air flows, seal leakages, heat generations (Bearing/Pumping/Seal/Towershaft/Windage) inside the bearing compartment. Thermal analysis carried out using ANSYS by imposing all boundary conditions. These thermals are validated with engine data and delivered to the structures team to calibrate the durability of the components.

Project-2: Thermal Analysis of 3D #4, #5/6 service tubes - Pratt & Whitney Engines

The main objective of the task is to perform Operational and Soakback (engine shutdown condition) Thermal Analysis of service tubes to evaluate the thermals for different conditions and provide thermals to structures. Service tubes include Supply tube (supply the oil to #5/6 bearing compartment), Scavenge tube (drain the oil from #5/6 bearing compartment), Buffer tubes (to pressurise the compartment) and sector portion of bearing compartment. #4, #5/6 service tubes located at the Mid turbine frame, Turbine exhaust case respectively, so these service tubes experience high temperatures. This task includes built the Finite element thermal model using UNIGRAPHICS and ANSYS. Generate the thermal boundary condition on service tubes towards the gas path side. Simulate the oil & air flows inside service tubes and apply interface boundary conditions from 2D bearing compartment. This task includes complex simulation of stagnant oil present in the compartment by creating MASS 71 and LINK 34 during soakack period. These thermals are validated with engine data and delivered to the structures team to calibrate the durability of the components.

Project-3: Integrated 2D/3D Thermal Analysis of #4 Bearing Compartment and Service Tubes - Pratt & Whitney Engines

The main objective of the task is to develop a new process for generating integrated 2D/3D FE model for #4 bearing compartment with all service tubes. Perform thermal analysis to capture circumferential temperature variation in the torque box cavity, forward buffer duct and bearing support. Integrated 2D/3D FE modelling combines bearing compartment and five different service tubes FE models into one integrated 2D/3D FE model. All service tubes, Mid Turbine Frame ID case, I-Rod pads and Forward buffer duct as 3D and all rotating components in the bearing compartment as 2D. Performing integrated 2D/3D thermal analysis captured circumferential gradients on bearing support, torque box cavity and buffer air in buffer ducts. In this analysis accurately capture the air and oil flow effects through service tubes on the bearing support. Performing one compartment and all service tubes in a single model will give precise thermal gradients.

Project-4: Calculation of View Factors using Radiosity Solver Method

The main objective of the task is to calculate view factors from hot surface to cold surface based on Radiosity method. In Mid Turbine Frames cavities, radiation plays more dominant role compared to convection. For calculating view factors, built thermal FE model having hot surfaces (vanes & Mid Turbine ID Platform) and cold surfaces (Heat shield of service tube & Mid Turbine Frame ID Case). Thermal model divided by enclosures with hot and cold surfaces. In Radiosity solver method, defining properties like emissivity and Stefen boltzmann constant to respective surfaces and defining radiosity solver options will generate view factors for respective surfaces. While doing data match task, there are no assumptions of view factors on service tubes and MTF ID case and radiation modelled accurately.

Project-5: Durability - LPC IBR Nonconformance - Pratt & Whitney Engines

The main objective of the project is to evaluate the effect of nonconformance at critical time point on the entire Integrated Blade Rotor (IBR). These types of models are analysed to check the strength, fatigue (LCF/HCF) and fracture life at the nonconformance location. These NC models checked with the design team to provide a suitable repair solution. The certification 2D global models are used for the validation of the nonconformance models. The 2D modelling is done using in-house tools which are used for understanding the behaviour of rotor like displacements, strength assessments & life for all critical axisymmetric features and 3D sub modelling is done for the non-axisymmetric regions. Thermals, loads, pressures and cut boundary conditions for 3D sub model mapped from 2D global model respective critical time points. Detailed result Summary for 2D & 3D Models are done along with the inputs and conclusions. Calculate stress concentration factor at damage location compared to nominal model. Perform the fatigue life (LCF/HCF) & fracture life assessment at nonconformance locations to check within the ESW limits. Providing detailed results reports as per the requirements of the client.

Project-6: Prestress static & Model analysis of LPC IBR Nonconformance- Pratt & Whitney Engines

The main objective of the project is to evaluate the natural frequencies & Goodman assessment for IBR nonconformances to know the structural substantial impact on airfoil vibratory characteristics and impact on engine system mistunning. This task includes removing the damage completely and creating new nonconformance blend geometry by design team. Remesh the geometry at damage location using hypermesh and run the prestress & model analysis by applying thermals, pressures & speed. Calculate stress concentration factor at damage location compared nominal model. Compare the natural frequency and mode shapes with nominal model. Extract the dynamic stress for each mode and identify the critical modes based on peak stress near nonconformance location. Calculate the Goodman margin for critical modes using steady stress, vibratory stress and stress concentration factor. Nonconformance results shows natural frequency change is negligibly small and having sufficient Goodman margin at damaged location then the damage is structurally acceptable. Providing detailed results reports as per the requirements of the customer.

EDUCATIONAL QUALIFICATION:

•MASTER OF Technology (Heat Transfer in Energy system) from Andhra University College of Engineering-2016, Visakhapatnam, Andhra Pradesh, 7.79 CGPA.

•BACHELOR OF Technology (Mechanical Engineering) from Jawaharlal Nehru Technological University-2013, Kakinada, Andhra Pradesh, 66.56%

•Intermediate (Mathematics, Physics, Chemistry) from Narayana Junior College-2009, Board of Intermediate Education, Visakhapatnam, Andhra Pradesh, 94.2%

•SSC from Z P High School-2007, Board of Secondary Education, Srikakulam, Andhra Pradesh, 90.16%

PERSONAL SKILLS:

•Good communication and analytical skills.

•Vibrant team member, also comfortable in working individually.

•Highly committed and involved in any assignments undertaken.

•Excellent work ethics, self-motivated, and quick learner.

DECLARATION:

I hereby declare that the particulars of information and facts stated herein above are true to the best of my knowledge and belief.

Date: 13/11/2020 (Praveen Moyya)

PERSONAL DETAILS:

Name : Praveen Moyya

Date of Birth : 16th June 1992

Father’s name : Asiranna Moyya

Passport No : P1723547 (Expires on October 2026)

Mobile : 965-***-****

Email ID : adhtsp@r.postjobfree.com

Permanent address : House No 1-59, Miyapur New Colony, Miyapur,

Hyderabad, Telangana – 500049

Sex : Male

Marital status : Single

Nationality : Indian

Languages known : English, Telugu, Hindi

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