A multi-ring heat exchanger and a propulsion system and method based on the multi-ring heat exchanger

Abstract

The invention discloses a multi-ring heat exchanger and a propulsion system and a method based on the multi-ring heat exchanger. The system is composed of an air inlet, a compressor, a multi-loop heatexchanger and a tail nozzle. A multi-ring heat transfer structure includes a spoiler fin, an insulated outer wall, a cooling aerodynamic chamber, and a heating fluid conduit, wherein the heating fluid conduit may optionally be provided with a fluid heating inlet conduit and a fluid heating outlet conduit. The invention utilizes clean and high-efficiency energy, adopts the multi-ring chamber structure that heat exchange and propulsion simultaneously reach the best, and after adding the continuous heat source, the invention can provide the continuous propulsion power satisfying the dual modes of stable cruise and afterward propulsion. The propulsion system of the optional closed thermodynamic cycle is safer and has less impact on the environment and the public. The application of multi-loopheat exchanger structure makes the fuel carrying capacity reduced and the system load ratio increased, which is an optimization improvement to the existing propulsion system. The propulsion system can adapt to the requirements of a variety of scale tasks, and has a greater application prospect.

Description

technical field [0001] The invention relates to the field of nuclear propulsion, in particular to a multi-ring heat exchanger and a propulsion system and method based on the multi-ring heat exchanger. Background technique [0002] For the propulsion system, the current problem is that fast start-up and stable cruising are important external indicators for judging the performance of the propulsion system engine. If the fuel supply is too fast, the compressor surge may occur, resulting in fuel-rich flameout in the combustion chamber. A rapid increase in temperature may lead to overheating of the system, and these limiting factors severely restrict the rapid increase in temperature before the vortex. In order to achieve continuous and stable heat transfer adjustment of the engine, the use of multi-annular heat exchangers instead of combustion chambers can provide a stable energy source for the propulsion system. The multi-annular heat exchanger can convert the unstable and vio...

AI Technical Summary

Problems solved by technology

[0002] For the propulsion system, the current problem is that fast start-up and stable cruising are important external indicators for judging the performance of the propulsion system engine. If the fuel supply is too fast, the compressor surge may occur, resulting in fuel-rich flameout in the combustion chamber. The rapid increase in temperature may lead to overheating of the system, these limiting factors seriously restrict the rapid increase in temperature before the vortex

[0004] Compared with the existing technology, the conventional nuclear propulsion system reactor can only be arranged separately outside the propulsion system, limited by the poor heat transfer capacity of the gas-cooled core and the critical requirements of the core, the reactor is bulky and heavy

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