Direct Formulation of Bipropellant Thruster Performance for Quantitative Cold-Flow Diagnostic

Abstract

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Unsteady Stream-Tube Model for Pulse Performance of Bipropellant Thrusters

“…The oxidizer and fuel sprays mix in the streamtube of "Main-1", the oxidizer or fuel spray exists in "Main-2", and the film cooling fuel flows in "Film". The local mixture ratio of 𝑀 R𝑖 and flow-rate ratio 𝐹 R𝑖 in each streamtube are given as direct functions of the injection conditions of 𝑀 R , 𝐹 c , and Λ, as summarized in Table 1 [32]. We use 𝑀 R = 100 as an alternative value of 𝑀 R = ∞.…”

“…Following on from those studies, the present authors clarified a non-dimensional number governing the non-uniform mixture ratio occurring inside a thrust chamber, successfully formulating 𝑐 * and 𝐼 sp for any mixture ratio as a direct function of injection conditions during steady operation [31,32]. As a next step, it was hoped that a physics-based theoretical model useful for predicting pulse performance could be established.…”

Evaporation of Three-Dimensional Wavy Liquid Film Entrained by Turbulent Gas Flow

“…The conventional model doesn't consider the entrainment nor the film waviness, corresponding with = 0 and = 1. The liquid film eventually fully vaporizes and self-decomposes, contributing to the chamber pressure and performance [21,43].…”

“…Based on the verified stratified stream tube assumption for the combustion gas flow inside rocket engines [21,43], the self-decomposing gas of liquid film covers the liquid film surface; thus, we use as the self-decomposing temperature of the fuel. Nominal conditions providing and are = 1.6 in the 10N case and = 1MPa in the 500N case.…”

“…For a liquid rocket engine combustion chamber employing the film cooling technique [1,2,7,19,20], minimizing the coolant flow rate is desired to improve the performance of characteristic velocity and specific impulse [3,19,21] with achieving the sufficient heat resistance. Liquid fuel jets are often ejected on the inner surface of the combustion chamber in a bipropellant thruster below the critical pressure of propellants, followed by the propagating liquid film covering the wall.…”