A mechanical seal structure for a hypersonic aircraft air turbine assembly

Abstract

The invention discloses a mechanical sealing structure for an air turbine assembly of a hypersonic aircraft, comprising a metal bellows, a bellows support, a clamping base, a static ring, a moving ring, flexible graphite packing, a flexible graphite gasket, folding Flow plate and metal base; fuel for cooling is injected into the bearing cavity through the oil delivery hole, and flows around the baffle to enhance the flow and heat exchange in the area near the bellows parts; it flows into the bearing ring cavity along the interlayer between the shaft and the baffle Inside, and finally out of the bearing cavity. The metal support and the bellows are welded to fix the bellows, which can not only achieve a good sealing effect, but also ensure that the strength of the joint reaches the standard. The circumferential rotation is limited by the arrangement of grooves and convex teeth on the outer circle, and axial displacement compensation can be provided. The metal base clamps the silicon carbide moving ring to reduce the degree of eccentric movement. The sealing device has the characteristics of high working temperature and rotating speed upper limit, good cooling and heat exchange effect, low bearing working temperature and simple and reliable structure.

Description

technical field [0001] The invention relates to the technical field of mechanical seals, in particular to a mechanical seal structure for hypersonic aircraft air turbine components. Background technique [0002] At present, with the development of aerospace technology, the human demand for the ultimate speed of aircraft is increasing, and hypersonic aircraft has become a research hotspot and foreword in the field of aerospace. In the development process of hypersonic vehicles, propulsion power technology is the most critical technical support. When the design speed of the aircraft is greater than Mach 3, the traditional turbojet or turbofan engine can no longer be used as a power source, and the turbo-ram combined cycle has become the mainstream solution for hypersonic power. However, since the ramjet engine has no rotating parts, the traditional solution of driving the generator to generate electricity through the rotating shaft of the engine cannot be adopted. Therefore, ...

AI Technical Summary

Problems solved by technology

At the interface of the turbine-rotating-static system, the high-temperature gas working medium in the meridian flow channel invades the turbine rotating-static disc cavity, resulting in a high-temperature environment inside the cavity, and the conventional rubber ring-assisted mechanical seal structure is no longer applicable here

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