An ejector air intake design method for a novel rocket-based combined-cycle rocket nozzle

Abstract

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Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

“…1) is based on the work of Cerantola [31] and Waung [32] and consists of two separate flowpaths: the supersonic expansion of hot rocket gases and the entrainment of atmospheric air. These two streams are then mixed within a duct for further combustion and expansion within the remainder of the engine (downstream of plane 3 in Fig.…”

Simulation of a rocket base combined cycle exchange inlet at subsonic conditions

“…After designing the rocket flow path geometry for the exchange inlet, Cerantola ran several simulations using Ansys CFX for a particular set of rocket parameters [26]. Waung, after designing the intake that houses the rocket flow path, used the panel method and computational fluid dynamics (CFD) to look at the entrainment ratio of the exchange inlet [27].…”

“…In this study, the parameters found in Waung are used because it produces a rocket flow path with performance similar to that of LE-7A, a Japanese first stage booster rocket [27]. Thus the goal of this research is to look into the ejector effect and study the rocket air interactions within the mixing duct in order to shorten its length.…”

“…The Mach number distribution is created using the theory described in Etele [28] and reproduces the performance of the LE-7A booster rocket. The LE-7A is part of the first stage for the H-IIA rocket from Japan [27].…”

“…A structured grid is used for the simulations and is shown in Figure 14. At the inlet of the chamber, the total pressure and total temperature are specified as 121 [MPa] and 3660[K] to resemble the performance of the LE-7A booster rocket [27].…”