By Tarit Bose
Airbreathing Propulsion covers the physics of combustion, fluid and thermo-dynamics, and structural mechanics of airbreathing engines, together with piston, turboprop, turbojet, turbofan, and ramjet engines. End-of-chapter workouts enable the reader to perform the elemental ideas at the back of airbreathing propulsion, and the incorporated PAGIC laptop code may help the reader to envision the relationships among the functionality parameters of alternative engines. quite a lot of information have on many alternative piston, turbojet, and turboprop engines were compiled for this ebook and are incorporated as an appendix. This textbook is perfect for senior undergraduate and graduate scholars learning aeronautical engineering, aerospace engineering, and mechanical engineering.
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Additional info for Airbreathing Propulsion: An Introduction
A schematic sketch of a piston engine is shown in Fig. 1, in which TDC and BDC refer to the top dead center and bottom dead center, respectively, as per the convention to describe extreme positions of a vertically operating piston. Further, V c is the clearance volume, V d is the displacement volume, and the sum of the two, V t ¼ V c þ V d, is the total volume. The diameter of the cylinder is D, known as the bore; the length of the cylinder that is traversed by the piston is the stroke length, or stroke.
On the other hand, for the minimum compression ratio, the heat added ¼ heat rejected is nonzero, but both the work output and the thermodynamic efficiency are zero. For a proper understanding of turboprop engines, the data on manufactured engines given in Appendix may be studied. 2 Jet Engines So far we have discussed engines that operate at comparatively low flight speeds, so that the static and stagnation states of air can be considered to be the same. Jet engines, including ramjets, straight turbojets, bypass jets, and fanjets not only operate at higher flight speeds than the propeller-driven engines, but they also have to develop high jet speeds at the exit nozzle.
Chapter 2 Thermodynamic Ideal Cycle Analysis In studying an ideal cycle relevant to aircraft propulsion, one can have a good insight into the relevant important parameters that give the performance parameters of a given system. For such a study, the following assumptions are usually taken: 1. Compression and expansion processes are isotropic. 2. The working fluid is a perfect gas with a constant specific heat and a constant adiabatic exponent. 3. The fuel mass added to air is neglected, and heat is added as if it is from an external source.