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

Abstract

The invention relates to a turbine outer ring connection assembly, a gas turbine engine and a connection method. The turbine outer ring connection assembly comprises a turbine outer ring extending piece and a mounting assembly. The turbine outer ring extending piece comprises a first rib plate and a second rib plate which extend outwards in the radial direction of a turbine outer ring and are adjacent in the axial direction, and the first rib plate and the second rib plate are provided with a first mounting hole and a second mounting hole correspondingly; the mounting assembly comprises a middle-layer casing, a cover plate and a connecting piece, the middle-layer casing comprises a middle-layer casing body, a third rib plate and a fourth rib plate, the third rib plate and the fourth rib plate extend inwards from the body in the radial direction and are adjacent in the axial direction, and the third rib plate and the fourth rib plate are provided with a third mounting hole and a fourth mounting hole respectively; the cover plate comprises a first cover plate and a second cover plate which are respectively provided with a fifth mounting hole and a sixth mounting hole; and the connecting piece comprises a first connecting piece and a second connecting piece.

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 ...

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Problems solved by technology

[0004] However, the difference in thermal expansion coefficient between CMC and superalloy materials will cause significant thermal deformation mismatch problems in the connection and installation structure between the CMC turbine outer ring component and the engine metal parts during the temperature change process, which will affect the component itself and the connection structure. Safety and reliability

[0005] 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 a setting would lead to Vibration bump problem

[0006] In the prior art, there is also a CMC turbine outer ring member and a metal middle casing that are connected face to face, but the inventor has found in practice that the CMC material is difficult to process into a plane with high flatness, so for CMC The outer ring of the turbine and the metal middle casing adopt a face-to-face connection structure. The design and manufacture of the outer ring components of the CMC turbine is difficult, the processing technology is complicated, and the manufacturing cost is high.

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