Abstract
Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.
Highlights
Introduction to Hypersonic Aircrafts and CombinedPropulsionIn 1946, Professor Hsue-shen Tsien [1] first proposed the concept of hypersonic velocity in his article Similarity Laws of Hypersonic Flows, and presented some peculiar properties of hypersonic flows
The results show that the oxygen/fuel ratio, spray distance, and particle size distribution are the important parameters to prepare an ideal adhesive layer. In this experiment, the oxidation of the three spraying processes, i.e., hyper velocity air plasma spray (HV-Air plasma spray (APS)) [53], low pressure plasma spray (LPPS) [54], and hyper velocity oxygenated fuel spray (HVOF) [55], were compared horizontally in a high temperature environment, Figure 10a shows a comparison of the oxide scales formed on 0.6 mm thick freestanding specimens of coating
In terms of preparation, exploring new technologies based on previous APS and physical vapor deposition technologies will be one of the research focuses in the future, e.g., how the performance of thermal barrier coating in high temperature and oxidation resistance can be optimized by SPS and plasma activated electron beam physical vapor deposition
Summary
In 1946, Professor Hsue-shen Tsien [1] first proposed the concept of hypersonic velocity in his article Similarity Laws of Hypersonic Flows, and presented some peculiar properties of hypersonic flows. Hypersonic aircrafts put a very high requirement on their aero-engines. The mission requirements of aero-engines in the hypersonic field cannot be met by any single form of power for propulsion. The combined propulsion technology is an organic combination of the liquid rocket engine, turbine engine technology, and the ramjet technology. RBCC is a propulsion system model that combines the advantages of the rocket motor with a high thrust-weight ratio and the ramjet with a high specific impulse [7]. TBCC refers to the power plant in which a turbine engine and other types of engines are combined [9]. The thermal protection and management of the propulsion system of hypersonic aircrafts explored in this study were based on the combined-cycle propulsion system model
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