Abstract
This chapter handles the three stationary modules in air-breathing engines, namely, inlets, combustors, and nozzles. Firstly, different methods of installation for turbojet/turbofan engines of civil transports are discussed. Next, methods of installation for turboprop engines are described. Next installation of turbojet and turbofan powering military airplanes is described. Methods for installing turboshaft engines to helicopters are discussed. Rockets also are powered by either turboshaft or turbofan engines for sustained flight. Its methods of installation are also discussed. Both subsonic and supersonic intakes are discussed. Pressure recovery and thermal efficiency of intakes are important parameters in both subsonic and supersonic intakes. A case study of intake of high-bypass ratio turbofan is discussed in details. The three types of combustion chambers, namely, can, can-annular, and annular types, are analyzed. The construction of combustion chamber is outlined. The chemistry of combustion is discussed. The design of diffuser in combustors is thoroughly given. Finally the exhaust system is classified. Convergent and convergent–divergent (C–D) nozzles are analyzed. A case study of the exhaust system including both fan and core nozzles are analyzed.
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El-Sayed, A.F. (2016). Stationary Modules Intakes, Combustors, and Nozzles. In: Fundamentals of Aircraft and Rocket Propulsion. Springer, London. https://doi.org/10.1007/978-1-4471-6796-9_8
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DOI: https://doi.org/10.1007/978-1-4471-6796-9_8
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