Adjustable binary engine passage sealing mechanism based on magnetic transmission

Abstract

The invention discloses an adjustable binary engine passage sealing mechanism based on magnetic transmission. The adjustable binary engine passage sealing mechanism based on magnetic transmission comprises a sealing outer cover, adjustable wall boards, hinges, a magnetic transmission device, a lead screw, a lead screw nut, a swing connecting rod and a fixed base. The adjustable wall boards and a passage body are connected through the corresponding hinges, and the adjustable wall boards are connected through the corresponding wall boards. The fixed base is arranged on the adjustable wall boardin the middle of a passage. The magnetic transmission device is divided into two parts separately mounted on the inner side and the outer side of the sealing outer cover. The part, located on the inner side of the sealing outer cover, of the magnetic transmission device is connected with the lead screw. One end of the swing connecting rod is fixedly connected with the lead screw nut, and the otherend of the swing connecting rod is movably connected with the fixed base on the corresponding adjustable wall board. The part, located on the outer side, of the magnetic transmission device drives the part on the inner side of the sealing outer cover to synchronously rotate in a non-contact mode through a magnetic belt. The lead screw nut linearly moves on the lead screw. The swing connecting roddrives the adjustable wall boards in linkage to achieve geometric adjustment of the passage. By adoption of the adjustable binary engine passage sealing mechanism based on magnetic transmission, geometric adjustment of the engine passage is achieved, and airtightness is ensured.

Description

technical field [0001] The invention belongs to the technical field of aerospace engines, and in particular relates to a binary seal adjustable mechanism, which is suitable for rocket ramming combined cycle engines. Background technique [0002] The rocket ramjet combined cycle engine (RBCC) organically combines the advantages of the rocket engine and the ramjet engine, and is one of the best combined powers to achieve large airspace, wide Mach number and high-speed and high-maneuvering flight. In order to make the engine have better propulsion performance on the entire flight trajectory, it is necessary to change the flow path structure of the engine under different working environment conditions, that is, to realize the geometrical adjustment of the flow path in the engine, such as figure 1 shown. However, the traditional power and transmission structure has major defects such as structural sealing and system quality, especially the contradiction between geometrical adjus...

AI Technical Summary

Problems solved by technology

In the research of RBCC engines at home and abroad, most engine combustion chambers adopt fixed geometric results, but this cannot achieve the goal of RBCC engines with optimal performance under wide Mach number (subsonic-supersonic-hypersonic) flow conditions and need

In order to achieve this goal, some research institutions at home and abroad have carried out exploratory research on the geometric adjustment of the flow channel of the combustion chamber, but without exception, the research has been hindered due to the inability to overcome the sealing problem.

The realization of the sealing of these researches basically adopts the scheme of applying external force on the sealing material between the relatively moving wall plates, but there are two major defects in this scheme: first, this kind of sealing scheme is essentially It belongs to the static sealing method, and it is difficult to guarantee the sealing performance after the frequent repetitive relative movement of the structure. Moreover, the deformation of the components subjected to high temperature loads such as the combustion chamber makes the sealing more difficult to achieve; secondly, in order to ensure For sealing, a huge positive pressure needs to be exerted between two structural parts that move relative to each other, so that the power device needs to provide huge power to offset the sliding resistance to achieve the relative movement of the two

It can be said that the contradiction between the adjustable flow channel geometry and the sealing performance has become one of the main difficulties hindering the expansion of the working range of RBCC engines and ramjet engines

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