Combustion Systems

Combustion chambers are a critical component of gas turbine and rocket propulsion systems, serving as the interface between the release of chemical energy and the engine’s thermodynamic cycle. This chapter presents a comprehensive treatment of combustion-chamber fundamentals, including flow aerodynamics, fuel–air mixing, flame stabilization, ignition, and heat-release mechanisms under subsonic and high-pressure operating conditions. Classical combustor configurations—such as can, annular, and can-annular designs—are reviewed alongside modern low-emission concepts, including Double Annular Combustors (DAC) and Twin Annular Pre-Swirling (TAPS) systems. Emphasis is placed on the mechanisms of emissions formation (NO ₓ , CO, UHC, soot) and the strategies employed to meet increasingly stringent environmental regulations. The chapter further examines thermal management techniques, liner cooling methods, and material selection, highlighting the roles of nickel- and cobalt-based superalloys, thermal barrier coatings, and emerging ceramic-matrix composites. Performance assessment is complemented by exergy analysis to quantify irreversibilities in the combustion process. Finally, the chapter discusses the impact of Sustainable Aviation Fuels and the growing application of artificial intelligence for combustion optimization, fault detection, and durability enhancement, providing insight into future combustion-chamber technologies and design trends. The combustion features of fossil-fuel- and electric-powered aircraft are also discussed.