Aircraft Propulsion, Volume 10
Aircraft Propulsion is an engineering textbook written for students in aerospace and mechanical engineering. The book covers aircraft gas turbine engine and rocket propulsion from its basic principles to more advanced treatments in engine components. Propulsion system integration with aircraft plays an important role in understanding propulsion and is thus addressed in the book. Extensive review material and derivations are intended to help students navigate through the subject with more ease. Over 100 examples and 300 problems are designed to practice the principles learned in jet propulsion and compliment learning through applications. In every engine component, issues related to manufacturing, material properties, temperature limitations and cooling are included to give students an appreciation for the broader scope of propulsion engineering than just aero-thermodynamics. Component matching and off-design analysis is detailed in a separate chapter to provide the physical and performance linkage between the components and their impact on aircraft engines. Principles of chemical rocket propulsion are presented in the context of single-stage to orbit propulsion needs of a rocket-based combined cycle vehicle. The broad treatment of the gas turbine engine cycles and components makes the book suitable as a reference for propulsion and turbomachinery engineers, gas turbine industry and professional development courses.
88 pages matching temperature ratio in this book
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Engine Thrust and Performance Parameters
18 other sections not shown
adiabatic efficiency aerodynamics afterburner airbreathing area ratio Assuming axial velocity axial-flow compressor blade row boundary layer burner bypass ratio calculate cascade centrifugal compressor choked coefficient combustor component compression compressor pressure ratio constant control volume coolant cooling cycle degree of reaction density diffuser downstream drag duct energy enthalpy equation exit Mach number FIGURE flight Mach number fluid friction fuel fuel-to-air ratio gas turbine gas turbine engine gross thrust heat transfer inlet Mach number isentropic kg/s Mach wave mass flow rate momentum nondimensional normal shock nozzle exit oblique shock off-design operation parameter perfectly expanded pressure rise propellant propulsive efficiency radial ramjet rocket rotor Schematic drawing scramjet shaft power shown in Fig solid specific impulse speed of sound stagnation stall static pressure static temperature stator subsonic swirl temperature ratio thermal efficiency total pressure loss total pressure ratio total temperature turbofan turbofan engine turbojet turbojet engine wall wave