Casing structure between aero-engine turbines

Abstract

The invention provides a casing structure between aero-engine turbines. The casing structure comprises an overall force bearing frame and a heat insulation fairing assembly. The overall force bearing frame comprises an outer casing, a double-layer inner casing and an inclined supporting plate, the outer casing is provided with an air entraining heat preservation cavity and a pipeline mounting seat at intervals in the circumferential direction, the double-layer inner casing is provided with an air collection cavity, penetrates through the air collection cavity and is provided with a pipeline bayonet socket, and the inclined supporting plate is connected with the air entraining heat preservation cavity and the air collection cavity. The heat insulation fairing assembly comprises an axial split type rectification guide vane assembly and an integrated rectification guide vane, the integrated rectification guide vane wraps the outer side of the double-layer pipeline, and the axial split type rectification guide vane assembly wraps the outer side of the inclined supporting plate; the inner layer of the double-layer pipeline is used for conveying lubricating oil or an oil-gas mixture, the outer layer of the double-layer pipeline is used for conveying sealing gas, and the double-layer pipeline penetrates through the overall force bearing frame in the radial direction; and the double-layer pipeline is respectively connected with a second external pipeline and a third external pipeline; the second external pipeline is used for circulating sealing bleed air for sealing a bearing cavity with lower temperature; and the third external pipeline is used for circulating lubricating oil or the oil-gas mixture.

Description

technical field [0001] The application belongs to the technical field of aero-engines, in particular to an aero-engine inter-turbine case structure. Background technique [0002] The fulcrum of the aero-engine behind the high-pressure rotor is usually supported by the inter-turbine casing without inter-shaft bearings. Most of the corresponding inter-turbine casings are of split assembly structure, passing through the main channel where the inter-turbine casing is located to lead to the internal bearings Most of the oil supply, oil return, ventilation and other functional pipelines of the cavity are also arranged in the inner cavity of the supporting plate of the casing between the turbines. When arranging the inter-turbine casing, according to the layout of the internal bearing cavity of the inter-turbine casing, multiple sets of functional channels such as oil supply, oil return, ventilation, bearing cavity sealing and bleed air, and testing are required; the inter-turbine ...

AI Technical Summary

Problems solved by technology

[0004] 1) Technical aspects: first, the radial straight struts used in the prior art are washed by the low-temperature outer culvert airflow outside the turbine casing and wrapped by the high-temperature gas that cools the heat-insulated fairing inside, and the straight struts should deal with The ability of thermal deformation inconsistency is poor; second, cracks are likely to occur at the junction of the head of the support plate and the outer casing due to thermal deformation inconsistency; third, the existing technical solutions cannot meet the requirements of cooling the heat shield Conditions when the gas temperature exceeds the oil/gas coking boundary;

[0005] 2) In terms of cost, the structure in the existing technical solution is prone to cra

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