AE334 Propulsion Systems I

Course Description :
Introduction to propulsion systems. Aerothermodynamics of propulsions systems (Carnot, Brayton, Otto cycles; Mixtures; Combustion; Equilibrium and Dissociation). Reciprocating engines. Rocket Engines. Ideal engine cycle analysis.

Prerequisite(s):
AE231 Thermodynamics

Textbook(s) and/or Other Required Material:
Gordon C. Oates, "Aerothermodynamics of Gas Turbine and Rocket Propulsion" AIAA Education Series, 1984.

The following books are the excellent sources of reference.
P. Hill and C. Peterson, ''Mechanics and Thermodynamics of Propulsion'' Second Edition, Addision Wesley Publishing Company, 1992 J. L Kerrebrock, ''Aircraft Engines and Gas Turbines'' The MIT Press, 1987
J. D. Mattingly, ''Elements of Gas Turbine Propulsion'' McGraw-Hill,Inc. 1996
R. D. Archer and M. Saarlas," An Introduction to Aerospace Propulsion" Prentice Hall, Inc. 1996

Course Objectives:
This course completes uncovered topics of thermodynamics applied to propulsion systems and gives basic notions of propulsion systems used in aeronautics. It also enables students to apply their aerothermodynamics knowledge to aerospace propulsion systems such as reciprocating and rocket engines. Another objective of this course is to train student to do experiments.

Topics Covered:
1. Introduction - 0.5 weeks
2. Basic Thrust Equations - 1.5 weeks
3. Propellers, Fans and Rotors - 2 weeks
4. Aerospace Propulsion Thermodynamic Cycles - 3 weeks
5. Reacting Mixtures and Combustion - 3 weeks
6. Gas Turbines - 2 weeks
7. Ramjet and Scramjets - 2 weeks
8. Rockets - 2 weeks

Class/Laboratory Schedule:
The course has three lecture hours and two laboratory hours.

Homework, Quizzes and Projects:
Regular homework will be given.
Quizzes will be given.
A project will be assigned.

Computer Usage: Homework and project will require computer applications.
Laboratory Work:
1. Determination of boiler efficiency
2. Determination of isentropic efficiency of an impulse turbine
3. Determination of flame stability and flame speed
4. Determination of nozzle efficiency
5. Determination of thrust of a ramjet engine

Contribution of Course to Meeting the Professional Component:
Mathematics and Basic Sciences: None
Engineering Design: None
Engineering Sciences: 3 credits
Humanities and Social Sciences: None

Relationship of Course to Program Objectives:
The course intends to satisfy the first, second and third objectives of the Department of Aerospace Engineering.

Prepared By:
Sinan Eyi
11-26-1999