Theory of aerospace propulsion / Pasquale M. Sforza

Von:

Sforza, Pasquale M [aut]

Resource type: Ressourcentyp: Buch (Online)Buch (Online)Sprache: Englisch Reihen: Elsevier aerospace engineering seriesVerlag: Oxford : Elsevier Science & Technology, c2012Auflage: Online-AusgBeschreibung: Online-Ressource (1 online resource (xviii, 684 p.)) : illISBN:

9781283293648
1283293641
9780123848895

Schlagwörter:

Andere physische Formen: 1856179125 | 9780123848895 | 9781856179126 | 1283293579 | Erscheint auch als: 9781856179126 Druck-AusgabeDDC-Klassifikation:

629.1/1 23
629.11

LOC-Klassifikation:

TL709

Online-Ressourcen:

Zugang im Netz des KIT

Zusammenfassung: Readers of this book will be able to: utilize the fundamental principles of fluid mechanics and thermodynamics to analyze aircraft engines, understand the common gas turbine aircraft propulsion systems and be able to determine the applicability of each, perform system studies of aircraft engine systems for specified flight conditions, perform preliminary aerothermal design of turbomachinery components, and conceive, analyze, and optimize competing preliminary designs for conventional and unconventional missions. Early coverage of cycle analysis provides a systems perspective, and offers context for the chapters on turbomachinery and components Broader coverage than found in most other books - including coverage of propellers, nuclear rockets, and space propulsion - allows analysis and design of more types of propulsion systems In depth, quantitative treatments of the components of jet propulsion engines provides the tools for evaluation and component matching for optimal system performance Worked examples and end of chapter exercises provide practice for analysis, preliminary design, and systems integration.Zusammenfassung: Front Cover -- Theory of Aerospace Propulsion -- Copyright -- Contents -- Preface -- Chapter 1 - Idealized Flow Machines -- 1.1 Conservation Equations -- 1.2 Flow Machines with No Heat Addition: The Propeller -- 1.3 Flow Machines with P = 0 and Q = Constant: The Turbojet, Ramjet, and Scramjet -- 1.4 Flow Machines with P = 0, Q = Constant, and A0 = 0: The Rocket -- 1.5 The Special Case of Combined Heat and Power: The Turbofan -- 1.6 Force Field for Air-Breathing Engines -- 1.7 Conditions for Maximum Thrust -- 1.8 Example: Jet and Rocket Engine Performance -- 1.9 Nomenclature -- Reference -- Chapter 2 - Quasi-One-Dimensional Flow Equations -- 2.1 Introduction -- 2.2 Equation of State -- 2.3 Speed of Sound -- 2.4 Mach Number -- 2.5 Conservation of Mass -- 2.6 Conservation of Energy -- 2.7 Example: Heating Values for Different Fuel-Oxidizer Combinations -- 2.8 Conservation of Species -- 2.9 Conservation of Momentum -- 2.10 Impulse Function -- 2.11 Stagnation Pressure -- 2.12 Equations of Motion in Standard Form -- 2.13 Example: Flow in a Duct with Friction -- 2.14 Nomenclature -- References -- Chapter 3 - Idealized Cycle Analysis of Jet Propulsion Engines -- 3.1 Introduction -- 3.2 General Jet Engine Cycle -- 3.3 Ideal Jet Engine Cycle Analysis -- 3.4 Ideal Turbojet in Maximum Power Take-Off -- 3.5 Ideal Turbojet in High Subsonic Cruise in The Stratosphere -- 3.6 Ideal Turbojet in Supersonic Cruise in The Stratosphere -- 3.7 Ideal Ramjet in High Supersonic Cruise in The Stratosphere -- 3.8 Ideal Turbofan in Maximum Power Take-Off -- 3.9 Ideal Turbofan in High Subsonic Cruise in The Stratosphere -- 3.10 Ideal Internal Turbofan in Supersonic Cruise in The Stratosphere -- 3.11 Real Engine Operations -- 3.12 Nomenclature -- 3.13 Exercises -- References -- Chapter 4 - Combustion Chambers for Air-Breathing Engines -- 4.1 Combustion Chamber Attributes.PPN: PPN: 809436183Package identifier: Produktsigel: ZDB-26-MYL | ZDB-30-PAD | ZDB-30-PQE

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