Magdy S. Attia
Dr. Attia joined the Aerospace Engineering Department faculty in 2004 where he teaches and conducts research in the area of Jet Propulsion. He also manages the Gas Turbine Lab with approximately $2.5M in funded research since inception in 2005.
Areas of interest include: Applied Propulsion Research, Compressor and Turbine aerodynamics, Lean engineering and innovative problem solving methods.
Current and past projects include:
- Pulsed Detonation Gas Turbine Engine cycles: theory and development.
- Conceptual studies in Large Engine Transportability
- Investigation of the Horse Shoe Vortex in axial turbine cascades with optimized means of eliminating the HSV.
- Modular compressors: enhancing the compressors LCC picture via Lean Engineering-based design of multi-stage axial compressors.
- Hybrid vortex solutions to the radial equilibrium condition
- Investigation of alternative designs to thrust reversers in high bypass turbofans.
- Feasibility study of the Re-Engine of a Very Light Jet
- Mathematical model (with GUI) for ice buildup in APU compartments and affect on optical fire detection
- Semi-Viscous method for predicting design and off-design performance in axial compressors (an alternative to the S1-S2 method)
- Ph.D. - Doctor of Philosophy in Mechanical Engineering, Texas A&M University System : College Station
- M.S. - Master of Science in Mechanical Engineering, Texas A&M University System : College Station
- B.S. - Bachelor of Science in Aerospace Engineering, Texas A&M University System : College Station
AE 440: Air-Breathing Propusion Component Design
AE 499: Special Topics in Aerospace Engineering
AE 650: Special Topics in Aerodunamic and Propulsion Engineering
Attia, M., 'Semiviscous Method for Compressor Performance Prediction', AIAA-Journal of Propulsion and Power, 2005, Vol. 21, No. 5, pp 792-796
Attia, M., 'A Semi-Viscous Method for Designing Axial Compressors', AIAA 2005-4540, presented at the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Tucson, Arizona, July 10-13, 2005
Attia, M., 'A Semi-Viscous Method for Compressor Performance Prediction', AIAA 2004-3412, presented at the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Ft. Lauderdale, Florida, July 11-14, 2004
Schobeiri, M.T, and Attia, M., "Active Aerodynamic Control of Multi-stage Axial Compressor Instability and Surge by Dynamically Adjusting the Stator Blades", AIAA-Journal of Propulsion and Power, 2003, Vol. 19, No. 2, pp 312-317
Schobeiri, M. T., and Attia, M., "Advances in Nonlinear Dynamic Engine Simulation Technology," ASME 96-GT-392, presented at the International Gas Turbine and Aero-Engine Congress and Exposition, Birmingham, UK, June 10- 13, 1996.
Schobeiri, M. T., and Attia, M., "Zur Entwicklung von Berechnungsverfahren zur Simulation Dynamischen Verhaltens von Strahltriebwerken und Station''ren Gasturbinenanlagen", (A Computational Method for Dynamic Simulation of Aero- and Stationary Gas Turbine Engines), Zeitschrift f''r Flugwissenschaften und Wetraumforschung (Journal of Flight Sciences and Space Research), Berlin, 20, (1996), pp. 227-238.
Attia, M., and Schobeiri, M. T. "A New Method for the Prediction of Compressor Performance Maps Using One-Dimensional Row-by-Row Analysis", ASME paper 95-GT-434, presented at the IGTI-ASME Turbo Expo, Houston, Texas, June 5-8, 1995.
Schobeiri, M. T., Attia, M., and Lippke, C., "Nonlinear Dynamic Simulation of Single and Multi-Spool Core Engines, Part (I): Computational Method", AIAA Journal of Propulsion and Power, November 1994, Vol. 10, No. 6, pp. 855-862.
Schobeiri, M. T., Attia, M., and Lippke, C., "Nonlinear Dynamic Simulation of Single and Multi-Spool Core Engines, Part (II): Simulation, Code Validation", AIAA Journal of Propulsion and Power, November 1994, Vol. 10, No. 6, pp. 863-867.
Schobeiri, M., Attia, M., and Lippke, C., "GETRAN: A Generic, Modularly Structured Computer Code for Simulation of Aero- and Power Generation Gas Turbine Engines", ASME Journal of Engineering for Gas Turbines and Power, July 1994, Vol. 116, pp. 483-494.
Schobeiri, T., and Attia, M., "Row-by-Row Performance Calculation Method for Turbines", AIAA Journal of Propulsion and Power, 1992 Vol.8, pp. 823-828.
Assistant Professor, 2004 - present
Department of Aerospace Engineering
Embry Riddle Aeronautical University, Daytona Beach, Florida
' Engaged in research and education in the field of gas turbine engines.
' Taught graduate and senior level courses in the field of Aerodynamics and Thermodynamics of Gas Turbine Engines, and Detailed Design of Gas Turbine Engine Components, as well as special topics in axial compressor and turbine aero and thermodynamics.
' Supervisor of the Gas Turbine Laboratory including a donated CF6-6 High Bypass Turbofan Engine (40,000 lbs T.O. Thrust), with 6 graduate research assistants, as well as a comprehensive suite of NASA, USAF, and commercial design codes.
' Research areas include compressor and Turbine aerodynamics and Thermodynamics, as well as design systems.
' LEAN Enterprise Lecturer and Trainer. Certified Instructor in 'LEAN Enterprise Value' principles by the 'LEAN Aerospace Consortium'; a consortium of all major Aerospace companies and MIT (Massachusetts Institute of Technology). Trained employees at the Rolls-Royce Corporation, Indianapolis, Indiana, in Lean Enterprise Value.
Senior Design Engineer, 1998 - 2003
Siemens Power Generation, Orlando, Florida
' ATS Compressor 'depressed-inlet-pressure' Test Data Analysis. The ATS compressor was tested (DOE funded project) at the Philadelphia Naval Shipyard at a depressed inlet pressure. Conducted a performance prediction calculation of the ATS compressor at that inlet pressure using the 'Viscous Method (mentioned below)'. The prediction was within the measurement accuracy.
' W501FD Empire Test Data Analysis. Analyzed the Empire test data of the W501FD compressor, and compared with prediction.
' Lead Aerodynamic consultant for the upgrade of the W501D5 compressor. Duties involved consulting and cooperating with the Modifications and Upgrades group to design a cost-effective upgrade for the W501D5 by redesigning only the front stages and maintaining retrofittability. Furthermore, the customer ability to use 'wet compression' was not to be hindered.
' Conceptual development of the next generation family of compressors. This set of studies involved researching a new airfoil shape, investigation of a design of a low stage count highly loaded compressor, investigation of modularly upgradeable compressor designs, as well as investigating cantilever diaphragm designs.
' Compressor Design Methods. From within the design systems group, given the global responsibility of ensuring that the in-house developed compressor design codes are performing properly. Duties included algorithms development, validation, creating of test cases, user manuals, compiling training materials, and performing global training (at US and German sites).
Senior Design Engineer, 1995 - 1998
Westinghouse Electric Corporation, Orlando, Florida
' Aerodynamic Blading Designer for the W501G and ATS Compressors. Duties included section design for optimal design point performance as well as off-design performance, stacking, and 3D CFD.
' Aerodynamic Blading Designer for the ATS Turbine. Designed the 4th stage blade and vane. Duties included section design for optimal design point performance as well as off-design performance, stacking, and 3D CFD.
' Co-developed a multi-discipline method for fast tuning of compressor (and turbine) airfoils using Strain Energy and Kinetic Energy contours. The combination of SE and KE contours plots lead to a better understanding of the modal behavior of the airfoil for each mode, independently, providing for the ability to manipulate the airfoil to affect a particular mode without impacting neighboring modes. As a result, tuning complex shrouded airfoils became much more efficient.
' Meanline and S1-S2 compressor analysis calculations. Duties included the modeling and understanding of all of the Westinghouse compressors (AA, B series, D4, D5, D5A, FA, FC, G, and ATS). Each compressor was analyzed using a combination of 2D Blade-to-Blade code and a streamline curvature code. The impact of each aerodynamic feature was studied using 'sensitivity studies'. Features studied included: Hade angles, airfoil count, re-stagger, radial distribution of total pressure, IGV design, OGV design and its impact on diffuser performance, diffuser shapes, bleeds, and ID and OD contour shapes.
' Developed the 'Viscous Analysis Method': a method to predict the performance of axial compressors. This method involves the combination of 3D CFD with a throughflow code. The method was validated against W501FC and W501D5 shop test data, as well as ATS 'depressed-inlet-pressure' shop test data. In each case, the performance prediction was within the measurement uncertainty (see publications).
' Developed the 'Viscous Design Method': a method to design axial compressors. This method involves the combination of 3D CFD with a throughflow code to systematically design 3D airfoils, and is an extension of the previously mentioned work.
' Lead aerodynamicist for the upgrade of the W501F compressor, later known as the W501FD. My task was to maintain retrofittability but still increase mass flow and efficiency. Employing the 'Viscous Design Method', 3D airfoil shapes were used to achieve the target.
Research Associate, 1989 - 1995
Turbomachinery Laboratory, Texas A&M University, College Station, Texas
' Development of axial compressor and turbine models: this was a research project funded by NASA-Lewis (now NASA-Glenn) (contract NAG-1144) to create a complete engine performance code. GETRAN is a modular code for the simulation of design and off-design performance of Gas Turbine Engines (see publications). Duties were primarily the writing of the Compressor and Turbine modules, which were also spun-off as individual stand-alone simulation codes. In addition, given responsibility for overall integration of the other modules, calibration and validation of the overall code. Conducted cycle studies, shutdown and start-up studies, loss-of-load studies, trip studies, as well as numerical integration, compiling, literature surveys, and code debugging.
Memberships and Credentials
- Member, AIAA – American Institute of Aeronautics and Astronautics
- Member, ASME – American Society of Mechanical Engineers
- Member, Sigma Gamma Tau – American Honors Society in Aerospace Engineering
Awards, Honors and Recognitions
Patent No. 6,079,197, June 27, 2000
Title: High Temperature Compression and Reheat Gas Turbine Cycle and Related Method.
RESEARCH GRANTS & AWARDS
' National Science Foundation ($770,000) proposal entitled 'A Large Beowulf Computer Cluster for Across-Discipline Research and Education at Embry-Riddle Aeronautical University', with M. Hickey, and C. Herbster. Purchased and installed a 265-processor, 2.2 GHz, 64-bit application capable supercomputer, 2004.
' Recipient of the 1997 George Westinghouse Signature Award of Excellence