Title

Jet engine

Publication Date

1-1-2007

Document Type

Dissertation/Thesis

First Advisor

Payvar, Parviz||Song, Shin-Min

Degree Name

B.S. (Bachelor of Science)

Department

Department of Mechanical Engineering

Abstract

A turbocharger designed to increase intake pressure of an internal combustion engine using the hot exhaust gas has two of the four major components of a simple turbojet engine. The turbine side of the turbocharger can be used as the turbine of a jet engine, which is directly coupled to the compressor. The other two components of a turbojet engine are the combustion chamber and the exhaust nozzle. The combustion chamber will take the compressed air from the compressor and increase the energy of the air by making an air fuel mixture and combusting it. Part of the energy from the hot gas is used to drive the turbine and thus compressor. The still hot gas leaves the turbine and flows through a nozzle which converts much of the energy into kinetic energy. The velocity differential between the air entering the system and the air exiting the system produces a net force, or thrust. The design of the combustion chamber is the main focus of the project as it involves the most amount theory and design. The combustion chamber must maximize heat energy gain in as little space as possible while preventing the system from overheating. The way the fuel air mixture combusts must be taken into account, if the combustion chamber is not designed properly the flame will not be stable and combustion will cease.

Comments

Includes bibliographical references.

Extent

35 pages, 12 unnumbered pages

Language

eng

Publisher

Northern Illinois University

Rights Statement

In Copyright

Rights Statement 2

NIU theses are protected by copyright. They may be viewed from Huskie Commons for any purpose, but reproduction or distribution in any format is prohibited without the written permission of the authors.

Media Type

Text

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