JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

Pre-Requisites

Aerodynamics, Aircraft Performance, Aircraft Propulsion

Course Objectives:

• Perform parametric and performance analysis of aircraft engines to achieve engine performance requirements identified in constraint and mission analysis.
• Describe the fundamental thermodynamic and gas dynamic principles used in the parametric analysis and performance analysis of aero engines.
• Explain the fundamental design tools used for analysis and preliminary design of main burner and afterburner, fundamental design tools used for analysis and preliminary design of inlet and nozzle.
• Demonstrate, Analyze and choose appropriate materials used in rockets& missiles, mission and weight requirements.

Course Outcomes:

• Engine design requirements and selection criteria

UNIT - I

Fundamentals Of Engine Design: Engine design roadmap, preliminary propulsion design sequence, basic definitions, unit conversions, standard atmosphere, compressible flow equations, mission profile, performance requirements and constraints, desired capabilities.

UNIT - II

Constraint Analysis And Mission Analysis: Concept, design tools, preliminary estimates for constraint analysis, examples of constraint analysis, selection of preliminary design point, complete constraint boundary conditions, constant speed climb, horizontal acceleration, climb and acceleration, takeoff acceleration, constant altitude and speed cruise, constant altitude and speed turn, best subsonic cruise Mach number and altitude, liter, warm-up, takeoff rotation, constant energy height maneuver, general determination of takeoff weight, example and sample mission analysis

UNIT - III

Engine Selection: Parametric cycle analysis, station numbering, gas model, component efficiencies, engine performance analysis, computational inputs and outputs, finding plausible solutions. Parametric and performance behaviors, examples, integrated results, design choices, performance cycle analysis, component performance analysis, iterative solution scheme, component behavior.

UNIT - IV

Engine Sizing: Subsonic inlets, supersonic inlets, nozzles, drag, sizing, constraints, selecting number of engines, final reprise, engine system design, engine static structure, starting, overall operation.

UNIT - V

Engine Component Operation: Operation lines, fan and compressor aerodynamics, turbine aerodynamics, engine life, high pressure and low-pressure turbine design, combustion system components, combustion process, fuels, and ignition, afterburners, sample inlet and exhaust nozzle design.

TEXT BOOK:

• 1. Mattingly J.D., Heiser W.H., Pratt D.T., ―Aircraft Engine Designǁ, AIAA ES, 2nd Edition, 2002.

REFERENCE BOOKS:

• 1. Mathur, M., and Sharma, R.P., ― Gas Turbines and Jet and Rocket Propulsionǁ, Standard Publishers, New Delhi 1998
• 2. Cornelisse, J.W., ―Rocket Propulsion and Space Dynamicsǁ, J.W., Freeman & Co. Ltd., London, 1982
• 3. Parker, E.R., ―Materials for Missiles and Spacecraftǁ, McGraw-Hill Book Co. Inc., 1982