Integral turbine outer ring connection structure and turbine engine

A connection structure, integral technology, applied in the direction of engine function, engine components, machine/engine, etc., can solve the problems of uneven thermal deformation of the outer ring of the turbine, and the thermal stress cannot be fully released, and achieves the guarantee of the turbine blade tip clearance, guarantee The effect of uniform performance and radial deformation

Active Publication Date: 2021-02-09
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology

[0008] The invention provides an integral turbine outer ring connection structure and a turbine engine to solve the technical problems that the thermal stress of the existing turbine outer ring connection structure cannot be completely released and the thermal deformation of the turbine outer ring is uneven

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  • Integral turbine outer ring connection structure and turbine engine

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Embodiment Construction

[0027] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0028] refer to figure 1 , the preferred embodiment of the present invention provides a kind of integral turbine outer ring connection structure, this connection structure comprises: turbine casing 1, turbine casing 1 is provided with support ring 2 and the turbine outer ring 3 that is connected with support ring 2, turbine A radial gap for releasing the thermal stress of the turbine outer ring 3 is provided between the outer ring 3 and the support ring 2, and a plurality of radial gaps are provided between the turbine outer ring 3 and the support ring 2 to buffer the radial deformation of the turbine outer ring 3 and make the turbine outer ring 3 radially deformed. An elastic member with more...

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Abstract

The invention discloses an integral turbine outer ring connection structure and a turbine engine. By leaving a certain radial gap between the turbine outer ring and the support ring, the radial and circumferential thermal stress of the turbine outer ring is released. The heat of the outer ring of the turbine is less transferred to the supporting ring, and the thermal deformation of the outer ring of the turbine will not be affected by the deformation of the supporting ring. Therefore, the matching and reliability of the outer ring of the turbine and the surrounding parts are good, which improves the performance of the outer ring of the turbine. and the service life of the surrounding parts; there is an elastic piece between the outer ring of the turbine and the support ring to buffer the radial deformation of the outer ring of the turbine, and to make the radial deformation of each position of the outer ring of the turbine uniform, effectively ensuring the turbine The blade tip clearance is uniform, thereby ensuring the performance of the turbine; in addition, the outer ring of the turbine is made of ceramic matrix composite material and a whole ring structure, which can withstand higher temperatures and reduce the leakage of high-pressure gas from the circumferential gap; compared with integrated The outer ring of the turbine is easy to replace after the outer ring of the turbine is damaged.

Description

technical field [0001] The invention relates to the field of turbine engines, in particular to an integral turbine outer ring connection structure. In addition, the present invention also relates to a turbine engine comprising the above integral turbine outer ring connection structure. Background technique [0002] At present, the temperature in front of the gas turbine engine and the ground gas turbine turbine has reached as high as 1600-2000K, which makes the gas turbine guide vanes, turbine outer ring, rotor blades and other parts that are directly in contact with the high-temperature and high-pressure gas become the parts with the worst working conditions in the engine. One of the components. For the gas turbine outer ring, it is not only an important stator part of the turbine flow channel, but also provides the most suitable clearance for the turbine rotor blade tip together with the turbine casing. Although the outer ring of the turbine is a stator part, it is also ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/04
CPCF01D9/04F05D2240/10F05D2260/231F05D2260/941
Inventor 陈竞炜徐鲁兵李志强蔡斌
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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