Turbine outer ring connection assembly, gas turbine engine and connection method

Abstract

The invention relates to a turbine outer ring connecting assembly, a gas turbine engine and a connecting method. The turbine outer ring connecting assembly comprises a turbine outer ring extending piece, the turbine outer ring extending piece comprises an upstream installation part and a downstream installation part which extend outwards in the radial direction of a turbine outer ring body and are adjacent in the axial direction, and the upstream installation part comprises a first rib plate and a first axial extending body extending towards the two axial sides from the first rib plate; the downstream mounting part comprises a second rib plate and a second axial extension body extending from the second rib plate to one axial side; and the first rib plate and the second rib plate are respectively provided with a first mounting hole and a second mounting hole. The mounting assembly comprises a middle bearing case, and the middle bearing case comprises a middle bearing case body and a first mounting part extending inwards from the body in the radial direction; the pressing piece comprises a first pressing piece and a second pressing piece; the connecting piece comprises a first connecting piece and a second connecting piece; an elastic piece and a mounting seat.

Description

technical field [0001] The invention relates to the field of gas turbine engines, in particular to a turbine outer ring connection assembly, a gas turbine engine and a connection method. Background technique [0002] Components of gas turbines often need to withstand extremely high temperatures, such as the outer ring of the turbine, which is the main turbine stationary part of the gas turbine, and it is subjected to a high ambient temperature in service. At present, the turbine outer ring components are mainly made of superalloy materials, but the strength and stiffness of the superalloy materials will decrease significantly under high temperature environment, which will affect the upper limit of the service temperature of the turbine outer ring components, and ultimately limit the overall performance of the gas turbine engine. [0003] The use of ceramic matrix composites (Ceramic Matrix Composite, CMC) instead of superalloy materials to prepare gas turbine engine turbine ...

AI Technical Summary

Problems solved by technology

In the prior art, in order to solve the problem of thermal deformation mismatch, a technical solution is adopted to reserve a gap in the connection and installation structure between the CMC turbine outer ring component and the metal parts of the engine during cold installation, but the inventors found that such an arrangement would lead to The problem of vibration and bumping

[0005] At the same time, the gap between the outer ring and the turbine rotor blades is small. When the engine generates abnormal unbalanced load or vibration, it is easy to scratch the outer ring and the tip of the rotor blade.

However, the hardness of ceramic matrix composite material is relatively high. If the outer ring of ceramic matrix composite material is used, once the friction between the outer ring and the rotor blade occurs, the damage of the outer ring of ceramic matrix composite material to the rotor blade will be greater than that of the traditional metal outer ring. ring is more serious

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