"Gas Turbine Aerothermodynamics and Performance Modeling"

A two-day short course in conjunction with Turbo Expo 2009

Saturday & Sunday, June 6-7, 2009
World Marriott Resort & Convention Center
Orlando, Florida

Overview and Objective
This interactive course provides review and reinforcement of relevant thermodynamic and aerodynamic concepts as applied to gas turbine engines, and performance calculation methods. The acquired knowledge and problem solving opportunity will enhance the participants’ ability to excel in various assignments in gas turbine design, development, and application. Participants will work out typical problems in the class during recitation sessions facilitated by the instructor. The course material has been evaluated by the Department of Mechanical and Aerospace Engineering of North Carolina State University. Special Notation: Participants are required to bring a scientific calculator to the class.

After completing the course the participants should be able to:

1. Apply aerothermodynamic concepts to the analysis of gas turbine engines
2. Analyze turbomachinery velocity diagrams and relate those to thermodynamic parameters
3. Appreciate the usefulness of the degree of reaction and the radial equilibrium equation
4. Comprehend the discipline of operability and combustor characteristics
5. Analyze cycle analysis problems in class on integrating the component performances to get the overall engine performance. Problems include both aircraft engine and shaft power cycles
6. Comprehend:
   1. The method of sizing the critical flow path areas at the design point
   2. The method of satisfying conservation laws to achieve cycle balance at off-design
   3. Tthe technique of the multivariable solver used in cycle models
   4. The various engine cycles in the power generation field

Instructor
Syed J. Khalid, Rolls-Royce North America, has an MSME (Purdue) and an ME (Aerospace, North Carolina State University). He has extensive experience in Gas Turbine Performance, Operability, Control System Design, and Installation Aerodynamics at General Electric, Pratt & Whitney, Rolls-Royce, Boeing, and Lockheed Martin. He has written 10 technical papers in his areas of expertise. He also holds 15 issued patents.

Who Should Attend
Engineers involved in the design, development, and application of gas turbine engines and turbo-machinery including those working for gas turbine/turbomachinery manufacturers, aircraft companies, and utilities.

Course Schedule

Saturday, June 6 8:00 a.m. to 5:00 p.m.
8:00 a.m. - 10:00 a.m.	1.0 Thermodynamics: Equation of State First Law on Conservation of Energy; Enthalpy, Internal Energy and Flow Work Steady-State, Steady Flow Process (SSSF) Illustrative Examples on Energy Balance in SSSF Processes in a Converging-Diverging Nozzle and Turbine Reversible Processes 2nd law and Entropy; Equations for Entropy Change Isentropic Property Relationships Illustrative Example on the Use of Isentropic Relationships Variable Specific Heats and Relative Pressure Illustrative Examples on the Use of Variable Specific Heat Illustrative Example of Gas Turbine Cycle Analysis Using Gas Tables
10:00 a.m. – 10:15 a.m.	Refreshment Break
10:15 a.m. – 10:45 a.m.	2.0 Propulsive Efficiency, Thermal Efficiency, and Overall Efficiency: Thrust Generation Principle and Function of Turbo-machinery Derivation of Efficiency Equations and Relationship with Specific Fuel Consumption (SFC) with illustrative Examples
10:45 a.m. – 11:45 a.m.	Recitation Session 1: Instructor facilitated problem solving session (Calculator Req’d)
11:45 a.m. – 12:30 p.m.	Group Lunch
12:30 p.m. – 2:00 p.m.	3.0 Compressible Flow: Conservation Equations for Mass, Momentum, and Energy Illustrative Examples on Conservation Equations Velocity of Sound Isentropic Flow through a Converging-Diverging Nozzle Non-dimensional Mass Flow Function Critical Pressure Ratio Effect of Varying Nozzle Exit Pressure Maximum Mass Flow Function Gas Velocity Variation with Area Change, Compressible Flow Functions Impulse Function Illustrative Example of a Propulsion Nozzle
2:00 p.m. – 2:30 p.m.	Recitation Session 2: Instructor facilitated problem solving session (Calculator Req’d)
2:30 p.m. – 2:45 p.m.	4. Generalized Gas Turbine Performance Parameters: Turbomachinery Corrected Parameters
2:45 p.m. – 3:00 p.m.	5.0 Energy Transfer in a Turbomachine: Velocity Diagram Analysis Illustrative Example of a Turbine
3:00 p.m. – 3:15 p.m.	Refreshment Break
3:15 p.m. – 5:15 p.m.	6.0 Basics of Compressor Aero Design: Velocity Diagram Analysis; T-s Diagram and Stage Efficiency Stage Characteristics Overall Compressor Map Simplified Map Representation in Computer Code Adiabatic and Polytropic Efficiencies Illustrative Example of Compressor Stage Design Radial Equilibrium Equation Introduction to Operability
Sunday, June 7, 2009 8:00 a.m. to 5:00 p.m.
8:00 a.m. – 8:30 a.m.	Recitation Session 4: Instructor Facilitated Compressor Stage Problem Solving
8:30 a.m. – 10:00 a.m.	7.0 Basics of Turbine Aero Design: Velocity Diagram Analysis; Degree of Reaction Illustrative Example of a Turbine Stage Aero Design Radial Variation of Velocity Triangles Adiabatic Efficiency and Polytropic Efficiency Overall Turbine Performance Maps
10:00 a.m. – 10:15 a.m.	Refreshment Break
10:15 a.m. – 10:45 a.m.	Recitation Session 5: Instructor Facilitated Turbine Stage Problem Solving
10:45 a.m. – 11:15 a.m.	8.0 Combustor Characteristics: Design Challenge Combustion Efficiency Pressure Loss Stability Pattern Factor
11:15 a.m. - 11:45 a.m.	9.0 Engine Sizing for Design Point and Off-Design Cycle Matching: Determination of Critical Flow Areas Requirements to Satisfy Conservation Equations
11:45 a.m. – 12:30 p.m.	Group Lunch
12:30 p.m. – 2:00 p.m.	9.0 Engine Sizing for Design Point and Off-Design Cycle Matching (cont’d): Compressor/Turbine Matching Turbojet Off-Design Calculations (Excel Spreadsheet Review) Mixed Flow Turbofan Design Point Calculation Mixing Plane Static Pressure Balance, Momentum Balance, Mixed Flow Properties Turbofan Design Point Calculation in Excel
2:00 p.m. – 3:00 p.m.	10. Off-Design Matching using Multivariable Solver: Mixed Flow Turbofan Independent Variables and Dependant Errors Newton’s 1D Iteration Method Illustrative Example Multi-variable Newton-Raphson Iteration Flow Chart Showing Updating of Independent Variable Guesses Step-By-Step Procedure for Off-Design Balancing of a Mixed Flow Turbofan Cycle
3:00 p.m. – 3:15 p.m.	Refreshment Break
3:15 p.m. – 3:45 p.m.	10. Off-Design Matching using Multivariable Solver: (continued)
3:45 p.m. – 4:45 p.m.	11. Overview of Power Generation Gas Turbine Cycles
4:45 p.m. – 5:00 p.m.	Course Wrap Up