turbine blade

A technology of turbine blades and blades, which is applied in the direction of supporting components of blades, machines/engines, mechanical equipment, etc., can solve the problems of large thermal load, prone to local high temperature areas, etc., and achieve the effect of reducing the temperature level

Active Publication Date: 2019-09-17
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is to provide a turbine blade in order to overcome the defects in the prior art that the turbine blade bears a large heat load and is prone to local high-temperature regions.

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Embodiment Construction

[0026] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0027] In the following description, many specific details are set forth in order to fully understand the present invention, but the present invention can also be implemented in other ways than those described here, so the present invention is not limited by the specific embodiments disclosed below.

[0028] figure 1 It is a schematic diagram of the overall structure of the turbine blade of the present invention. figure 2 It is a schematic diagram of an exploded structure of a turbine blade of the present invention. image 3 is a radial cross-sectional view of the blade leading edge region in the turbine blade of the present invention. Figure 4 for image 3 Partial enlarged view of part A in middle. Figure 5 It is a sectional vi...

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Abstract

The invention provides a turbine blade which comprises a blade body and a blade tip. The blade tip is arranged above the blade body, a groove is formed in the blade tip, a cavity is formed in a front edge zone of the blade body, and the cavity extends in the radial direction of the turbine blade from a blade top of the turbine blade; an inner cavity is further formed in the front edge zone of the blade body and extends in the radial direction of the turbine blade from the blade top of the turbine blade, at least one cold air inlet hole is formed between the inner cavity and the cavity, a cold air exhaust hole is formed in the position, close to the blade top, of the cavity, so that cold air flows into the cavity from the inner cavity through the cold air inlet holes, heat convection is carried out on the inner wall face and the outer wall face of the cavity, and then the cold air is exhausted out from the cold air exhaust hole. According to the turbine blade, a novel blade tip cooling structure is adopted, the groove side wall and a blade top zone are cooled, and the temperature level of the groove side wall and the blade top zone is reduced. In this way, the blade tip zone of the turbine blade can be effectively cooled, and the temperature level of the blade tip zone can be reduced.

Description

technical field [0001] The invention relates to the field of gas turbine blade cooling, in particular to a turbine blade. Background technique [0002] In advanced aero-engines, the turbine blades mostly adopt a grooved tip structure to reduce the leakage of the tip clearance and improve the working efficiency of the turbine. For this structure, the cooling design of the tip of the blade and the side wall of the groove is limited. [0003] At present, the cooling of the tip area of ​​the turbine blade mainly relies on the cooling of the tip of the blade by the revolving channel inside the blade, and the cooling of the discrete film holes arranged on the pressure surface of the blade near the tip of the blade. The cold air in the internal revolving channel takes away part of the heat through convective heat exchange, and the cold air that flows out of the air film holes arranged on the pressure surface near the blade top area passes over the blade top to form a partial prote...

Claims

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Application Information

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Patent Type & AuthorityPatents(China)
IPC IPC(8): F01D5/18
Inventor张洪潘晴
OwnerAECC COMML AIRCRAFT ENGINE CO LTD