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Heavy-duty gas turbine high-vortex tip clearance control structure

A gas turbine and control structure technology, which is applied to mechanical equipment, engine components, machines/engines, etc., can solve problems such as unstable operation of gas turbines and affect the safe operation of gas turbines, and achieve the effect of reducing blade tip clearance and saving costs

Inactive Publication Date: 2015-10-07
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Reducing the value of the high-vortex tip clearance can effectively improve the economy of the gas turbine, but if the high-vortex tip clearance is too small, it is easy to cause blade tip rubbing and affect the safe operation of the gas turbine
[0003] Gas turbines are often subjected to varying loads, not only during start-up, but also during continuous operation, which can lead to unstable operation of the gas turbine, especially when the components are deformed due to temperature

Method used

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  • Heavy-duty gas turbine high-vortex tip clearance control structure

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Embodiment Construction

[0022] The present invention will be further described below in conjunction with accompanying drawing:

[0023] Such as figure 1 As shown, the high-vortex blade tip clearance control structure of a heavy-duty gas turbine includes a full-ring outer shell 2 installed on the cylinder 1, and a full-ring shell 3 that is sleeved on the outside of the full-ring shell 2. The full-ring shell 3 and the whole There is a gap 4 between the ring casings 2, and a gap 5 is opened at the left end of the whole ring casing 3, the gap 5 communicates with the gap 4, and the gap 4 forms a cooling air flow channel. Preferably, the left end of the whole ring housing 3 is evenly provided with a plurality of notches 5 along the circumferential direction. In this embodiment, the left end of the whole ring housing 3 is evenly provided with 10 notches 5 along the circumferential direction.

[0024] The whole-ring outer casing 2 is facing the high-vortex blade tip, and the thermal deformation of the whole...

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Abstract

The invention discloses a heavy-duty gas turbine high-vortex tip clearance control structure. The structure comprises a whole ring shell (2) arranged on an air cylinder (1) and further comprises a whole ring shell hood (3) arranged outside the whole ring shell (1) in a sleeving mode. A gap (4) is formed between the whole ring shell hood (3) and the whole ring shell body (2). The left end of the whole ring shell hood (3) is provided with an opening (5). The opening (5) is communicated with the gap (4). The gap (4) forms a cooling air flow channel. The heavy-duty gas turbine high-vortex tip clearance control structure has the advantages that according to the heat-expansion and cold-contraction principle, the thermal deformation of a stator component is controlled, the heat capacity of components is deployed, and the heat reaction speed of all the components is controlled, so that a proper minimum safety operation tip clearance is obtained.

Description

technical field [0001] The invention relates to the technical field of gas turbine structure design, in particular to a high-vortex blade tip clearance control structure of a heavy-duty gas turbine. Background technique [0002] The high vortex tip clearance of a heavy-duty gas turbine has a great influence on the economical improvement and safe operation of the gas turbine. Reducing the value of the high-vortex blade tip clearance can effectively improve the economy of the gas turbine, but if the high-vortex blade tip clearance is too small, it is easy to cause blade tip rubbing and affect the safe operation of the gas turbine. [0003] Gas turbines are often subjected to varying loads, not only during start-up, but also during continuous operation, which can lead to unstable operation of the gas turbine, especially when components are deformed due to temperature. [0004] In the prior art, in order to control the change of the high-turbine blade tip clearance and keep the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D11/24
Inventor 马凤柯赵永建任立新
Owner AECC SHENYANG ENGINE RES INST
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