Beschreibung
This study has two declared aims: it presents the theoretical basis for a provably ideal comparative process for relaxing flows (ICP) and jus tifies its application to jet and, in particular, rocket engines. This will be treated in two parts. Part I offers a status quo report on current calculation methods, and compiles and explains briefly the most important data on selected pro minent rocket engines. Starting from the phenomenology of the dynamical and physico-chemical conversion processes in the fuel-oxidizer fluid mixture and in the burned gases, the ideal thermodynamic comparative process is then derived - as a defined sequential change of states in the system. In order to render this comparative process readily under standable, it is first applied to an appropriate model gas using alge braic equations for all relevant parameters. This model gas undergoes energy conversion processes without forfeiting the simplicity of pre sentation typical of classical gas dynamics. Above all, examination of this model offers proof that it is generally impermissible to use, as is done in practice, the familiar isentropic equation for flow changes of state continuously propagated in flow tube theory. Elementary calculations immediately indicate essential attributes which are also typical for relaxing, multicomponent, one-phase systems, such as the significant 'pressure drop phenomenon' or the establishment of the steady mass flow rate as an 'eigenvalue' of the comparative pro cess. Their relevance to the RE theory is stressed.
Autorenporträt
InhaltsangabeSynopsis.- One (I): Optimal Comparative Process for Rocket Engines.- 1. Description of the Problem.- 1.1 Introduction.- 1.2 NASA Comparative Processes.- 2. Definition of an Ideal Comparative Process.- 2.1 Process Phenomenology in a Rocket Engine.- 2.2 Comparative Process for Relaxing Flows.- 3. Classical Gas Dynamics of the ICP.- 3.1 Relaxing Model Gas as System.- 3.2 Flow Tube Theory with Conversion Processes.- 3.3 Sequence of States.- 4. Design Criteria for Rocket Engines.- 4.1 Design Procedure.- 4.2 Influences of Real Flows.- 5. Summary I.- Two (II): Thermofluiddynamics of Rocket Propulsion.- 1. Problems with the NASA-Methods.- 1.1 Intentions of the NASA-Lewis Code.- 1.2 AFC Method.- 1.3 FAC Method and Prozan's Procedure.- 1.4 Evaluation of the NASA Methods.- 1.5 Matching Procedures.- 1.6 General Commentary.- 2. Basic Principles of the Alternative Theory.- 2.1 Introduction and Reference to the Microphysical Fundamentals.- 2.2 Forms of Energy and Gibbs Fundamental Equation.- 2.3 Gibbs-Duhem Equation, Process and Realization.- 2.4 Axioms of the Traditional Continuum Theories: a Commentary.- 2.5 Significant Results of the Alternative Theory: an Outline.- 3. The Munich Method.- 3.1 Preliminary Remarks.- 3.2 Changes of State in the Combustion Chamber.- 3.3 Speed of Sound in Chemically-reacting Gas Mixtures.- 3.4 Stoichiometric Matrix of the LH-LOX Equilibrium Combustion.- 3.5 Nozzle Differential Equation; Mass Flow Eigenvalue.- 3.6 Nozzle Exit State: Problems of Numerical Computation.- 3.7 Regenerative Cooling: Attempts towards a Modeling.- 4. Test of the MM with Data from LH-LOX Rocket Engines.- 4.1 Problems of Assessment.- 4.2 MM in Comparison with the Lewis Code and Test Data.- 4.3 Variable Mixture Ratios and Reusability.- 4.4 Influence of the Operating Parameters on Flow States.- 5. Summary Part II.- List of Relevant Symbols.- Appendix 1: Thermodynamic Analysis of the Simplified Model Gas.- Appendix 2: Properties of State of Polynary Fluid Mixtures.- Notes.- Index of Names.
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Springer Basel AG in Springer Science + Business Media
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E-Mail: juergen.hartmann@springer.com
