Stator blade mounting structure

Abstract

The invention relates to a stator blade mounting structure which can be applied to the fields of ground gas turbines, aero-engines and the like. The stator blade mounting structure comprises stator blades with a pressing plate, inner and outer ring light elastic parts, inner and outer ring casings and an outer ring pressing hoop. Through the parts, the single blade dismantling function of the stator blades can be achieved. As the light elastic parts are adopted, assembling and positioning of the whole-ring stator blades are achieved through the cold-state interference magnitude of the light elastic parts and the inner and outer ring blade profiles of the blades. Under an assembly state, the stator blade mounting structure has certain rigidity and can transfer aerodynamic torque of the stator blades to the corresponding position of a casing mounting edge. By means of the structure, the weight of the ground gas turbines and the aero-engines can be remarkably reduced. The maintainabilityof the stator blades is improved while the machining difficulty of the stator blades is lowered, and the single blade dismantling function of the blades is achieved. Through the structure, under the excitation action force of mainstream unsteady airflow in a channel, the risk of self-excited vibration of the stator blades can be reduced.

Description

technical field [0001] The invention relates to a blade installation structure used in the fields of ground gas turbines, aeroengines, etc., in particular to a lightweight, vibration-damping and detachable stator blade installation structure. This structure can meet the needs of sealing and positioning structure design of stator blades, inner and outer ring (non) force transmission casings or (non) force bearing casings and stator blade end areas in such mechanical structures, and meet the needs of stator blades in the mainstream Design requirements for vibration reduction under the action of unsteady airflow excitation force. Background technique [0002] In the structural design process of double-duct or multi-duct aviation turbofan engines or gas turbines with double ducts, the processing and installation structure methods of the stator components of the low-pressure compression system often adopt the integrated processing of the stator vanes and the inner and outer ring ...

AI Technical Summary

Problems solved by technology

It is not difficult to see that the stator casing assembly using the above processing method is very difficult to process and the cost is too high

In addition, during the operation of the engine or gas turbine, if there is a problem with one or several stator blades, the casing assembly where the entire stator blade is located will inevitably need to be overhauled or directly scrapped

This causes the maintenance cost of the engine or gas turbine to be too high, which is extremely unfavorable for improving the competitiveness of the engine

[0003] The existing integrated structure of the stator blade and the casing mainly has the difficulties of sealing the position of the type hole, the difficulty of disassembling and repairing the single blade or the difficulty in structural design, the difficulty of achieving precise positioning of the single blade in the assembly, and the difficulty of the stator blade when the air flow stimulates it. Under the action of vibration force, problems such as forced vibration are easy to occur, which seriously restricts the development of the engine

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