Learning Objective:Obtain a working knowledge of gas turbine and rocket propulsion systems, applications, and components.
This course provides an overview of gas turbine and rocket propulsion systems and their analysis. It may serve as a prerequisite to AAE538 and AAE539 for students whose major or minor area of concentration is propulsion. Fall 2017 Syllabus
Topics Covered:Overview of propulsion applications; review of mechanics and thermodynamics of fluid flow; 1D isentropic and non-isentropic flow; gas turbine engine cycles and inlets, combustors, and nozzles; the rocket equation; rocket performance parameters and rocket design; liquid rocket engines, solid rocket motors, and their components; rocket nozzle design, combustor heat transfer, and combustion instability.
Prerequisites:Undergraduate training in compressible flows and thermodynamics.
Applied / Theory:50 / 50
Web Content:Syllabus, grades, lecture notes, homework assignments, and solutions.
Homework:Homework will be accepted via Blackboard.
Projects:A short paper (including some analysis) on a propulsion system of interest to the student is required.
Exams:Two two-hour midterm exams and a final exam.
Textbooks:Official textbook information is now listed in the Schedule of Classes. NOTE: Textbook information is subject to be changed at any time at the discretion of the faculty member. If you have questions or concerns please contact the academic department.
Required: Mechanics and Thermodynamics of Propulsion (2nd Edition), Philip Hill, Pearson, 2nd, ISBN:9780201146592