Jet Propulsion: A Simple Guide to the Aerodynamic and Thermodynamic Design and Performance of Jet EnginesCambridge University Press, 14 Αυγ 2003 This is the second edition of Cumpsty's excellent self-contained introduction to the aerodynamic and thermodynamic design of modern civil and military jet engines. Through two engine design projects, first for a new large passenger aircraft, and second for a new fighter aircraft, the text introduces, illustrates and explains the important facets of modern engine design. Individual sections cover aircraft requirements and aerodynamics, principles of gas turbines and jet engines, elementary compressible fluid mechanics, bypass ratio selection, scaling and dimensional analysis, turbine and compressor design and characteristics, design optimization, and off-design performance. The book emphasises principles and ideas, with simplification and approximation used where this helps understanding. This edition has been thoroughly updated and revised, and includes a new appendix on noise control and an expanded treatment of combustion emissions. Suitable for student courses in aircraft propulsion, but also an invaluable reference for engineers in the engine and airframe industry. |
Περιεχόμενα
TheCreationof | |
The Gas Turbine Cycle | |
The Principle and Layoutof Jet Engines | |
Compressors and Turbines | |
Component Characteristics 12 Engine MatchingOffdesign Part 3 Design of Enginesfor a New Fighter Aircraft | |
Lift Drag andthe Effectsof Manoeuvring | |
Άλλες εκδόσεις - Προβολή όλων
Jet Propulsion: A Simple Guide to the Aerodynamic and Thermodynamic Design ... N. A. Cumpsty Περιορισμένη προεπισκόπηση - 2003 |
Συχνά εμφανιζόμενοι όροι και φράσεις
____________________________________________________ Exercises aerodynamic afterburner altitude ambient andthe assumed atthe axial blade bypass ratio bypass stream bythe calculations Chapter choked combat combustion combustor component compression compressor and turbine compressor delivery temperature constant core compressor cruise design point downstream drag effect energy equal equation exit fan pressure ratio fighter aircraft Figure flight Mach number flight speed fromthe gas turbine gross thrust high bypass HP compressor increase inlet stagnation International Standard Atmosphere inthe isentropic efficiency isthe itis jet engine jet velocity lift coefficient loss LP turbine mass flow rate maximum mixed noise non nondimensional mass flow normally offdesign ofthe onthe outlet overall pressure ratio polytropic efficiency propelling nozzle reduced rotational speed rotor sealevel shaft shown shows specific fuel consumption specific thrust stages stagnation pressure stagnation temperature stator temperature ratio thatthe theengine thefan theLP thepressure theturbine tobe tothe tropopause turbine inlet temperature turbojet weight wing withthe