Liquid rocket engine multi-layer active cooling device capable of achieving liquid-gas separation

Abstract

The invention discloses a liquid rocket engine multi-layer active cooling device capable of achieving liquid-gas separation. The liquid rocket engine multi-layer active cooling device comprises a cooling device, a matched oil path and gas path signal transmission device. The cooling device comprises a cooling wall, and three stages of spiral cooling flow pipes are embedded in the entity of the cooling wall from inside to outside in the radial direction; the three stages of spiral cooling flow pipes are spiral, have equal screw pitches and 14-16 sections, are uniformly distributed in the radial direction, are equal in spacing and are mutually independent; the two ends of the three stages of spiral cooling flow pipes are communicated with three inlets and three outlets to two end surfaces of the cooling wall; and the matched oil path and gas path signal transmission device comprises a pressure stabilizing oil rail, a filter, a liquid-gas separator and a gas storage device which are all connected with a sensing execution and electric control unit. According to the liquid rocket engine multi-layer active cooling device capable of achieving liquid-gas separation, through the design of the three-stage spiral embedded flow pipes, the requirement for disposable utilization of rocket cooling equipment is met, the working time of the cooling equipment can be effectively prolonged, and the overall failure of the cooling device is delayed. The liquid rocket engine multi-layer active cooling device is safe and reliable, and is matched with the development direction of the current processing technology.

Description

technical field [0001] The invention relates to the technical field of space launch anti-insulation devices, relates to an active cooling device for a liquid rocket engine using a three-stage helical inlaid flow tube for cooling, and in particular relates to a liquid rocket engine with its own Liquid-gas separation device and active cooling device using three-stage spiral inlaid flow tube for cooling. Background technique [0002] The instantaneous temperature of space vehicles such as rockets and space shuttles during ignition will reach 3000-4000K. Depending on the flow field, the type of fuel used, and the specific chemical reaction conditions, the local temperature may be higher. Flames and gas streams have temperatures well in excess of the melting temperatures of most common metals and alloys, causing rapid failure of combustor and cooling devices. Therefore, an effective cooling scheme is of great significance for delaying the failure of the aerospace engine and ensu...

AI Technical Summary

Problems solved by technology

At present, the two commonly used processing methods of cooling pipes include milling groove type and welded tube bundle type, among which the milling groove type cooling pipe is not conducive to ensuring the action time of the coolant, and at the same time has a great impact on the overall strength, and cannot guarantee the uniformity of cooling; The welded tube bundle type has extremely high requirements on the processing technology. With the change of the cross-sectional area of ​​the nozzle, it is necessary to process a variable-diameter pipe. At the same time, the thin-walled structure cannot withstand the high pressure of the active cooling coolant, and the ability to withstand the change of phase change pressure is even greater. weak

[0006] At present, regenerative active cooling technology has been partially applied to scramjet engines, but it is still in the basic research stage in the fields of heat transfer and reaction kinetics, and no relevant patents have been reported at present, and there are relatively few application reports on related equipment. limited

At the same time, research on the application of this technology on rockets is quite limited

Images