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A turbine blade with oblique downward blowing film cooling holes

A technology of turbine blade and air film cooling, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve the problems of air film detaching from the wall surface and increased consumption of cold air, so as to avoid wasting cold air and reduce the amount of cooling used. , good cooling effect

Inactive Publication Date: 2018-07-10
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to overcome the deficiencies in the prior art that cause the gas film to detach from the wall downstream of the outlet of the obliquely downward-blown air film hole and increase the consumption of cold air, the present invention proposes a turbine with an obliquely downward-blown air film cooling hole. blade

Method used

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  • A turbine blade with oblique downward blowing film cooling holes
  • A turbine blade with oblique downward blowing film cooling holes
  • A turbine blade with oblique downward blowing film cooling holes

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0016] This embodiment is a turbine blade with cooling holes. The turbine blade is a gas turbine turbine blade, and its blade shape adopts the prior art. Three oblique down-blowing air film holes are evenly distributed in the area L of 15%-75% chord length on the pressure surface of the turbine blade, and each oblique down-blowing air film hole is located on the pressure surface of the turbine blade. The orifices are all located in the area L described.

[0017] The center distance p of the orifices of each oblique downward blowing type air film hole located on the pressure surface of the turbine blade is 30% of the pressure surface chord length Cps. When the hole spacing p is determined, the required oblique downward blowing can be obtained. The number of air film pores. In this embodiment, the oblique down-blown air film holes are distributed at 15%, 45%, and 75% of the chord length from the leading edge.

[0018] The position of the center of the orifice of each oblique ...

Embodiment 2

[0021] This embodiment is a turbine blade with cooling holes. The turbine blade is a gas turbine turbine blade, and its blade shape adopts the prior art. In the area L of 15% to 75% chord length on the pressure surface of the turbine blade, there are 6 oblique downward blowing air film holes uniformly distributed, and each oblique downward blowing air film hole is located on the pressure surface of the turbine blade. The orifices are all located in the area L described.

[0022] The center distance p of the orifices of each oblique downward blowing type gas film hole located on the pressure surface of the turbine blade is 10% of the pressure surface chord length Cps. When the hole spacing p is determined, the required oblique downward blowing can be obtained. The number of air film pores. In this embodiment, the oblique down-blown air film holes are distributed at 15%, 25%, 35%, 45%, 55%, 65% and 75% of the chord length from the leading edge.

[0023] The position of the ce...

Embodiment 3

[0026] This embodiment is a turbine blade with cooling holes. The turbine blade is a gas turbine turbine blade, and its blade shape adopts the prior art. In the area L of 15% to 75% chord length on the pressure surface of the turbine blade, there are 4 oblique downward blowing air film holes uniformly distributed, and each oblique downward blowing air film hole is located on the pressure surface of the turbine blade. The orifices are all located in the area L described.

[0027] The center distance p of the orifices of each oblique downward blowing type air film hole located on the pressure surface of the turbine blade is 20% of the pressure surface chord length Cps. When the hole spacing p is determined, the required oblique downward blowing can be obtained. The number of air film pores. In this embodiment, the oblique downward blowing air film holes are distributed at 15%, 35%, 55% and 75% of the chord length from the leading edge.

[0028]The position of the orifice of e...

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Abstract

Disclosed is a turbine blade with obliquely downward blowing type air film cooling holes. A plurality of obliquely downward blowing type air film holes are distributed in 15%-75% of a pressure surface chord region L on the pressure surface of the turbine blade. The position h of the center of the orifice of each obliquely downward blowing type air film hole is equal to 5%H. The orifice of the other end of each obliquely downward blowing type air film hole communicates with a cold air inlet cavity of the turbine blade. The various obliquely downward blowing type air film holes are oblique in the flow direction of the turbine blade to form an inclined angle alpha in the flow direction; and meanwhile, the obliquely downward blowing type air film holes are oblique downwards in the span direction to form an inclined angle beta in the span direction. By the obliquely downward blowing type air film hole row involved in the invention, the air film cooling effect can be good under small blowing ratio. Through CFD numerical simulation, the turbine blade with the obliquely downward blowing type air film cooling holes can totally cover the region of the pressure surface of an end wall under the condition that the overall blowing ratio is 0.5, and the average air film cooling efficiency is not lower than 0.2. Compared with the conventional pressure surface side end wall cooling method, the turbine blade with the obliquely downward blowing type air film cooling holes has the characteristic that the use amount of cold air is reduced by 30% at least.

Description

technical field [0001] The invention relates to the technical field of gas turbine turbine blades, in particular to an oblique downward blowing gas film hole row arranged on the pressure surface of a stationary blade, which is used to cool part of the end wall area that is difficult to be effectively cooled by conventional end wall cooling technology. Background technique [0002] Film cooling is a cooling technology applied to gas turbine blades, that is, high-pressure cold air is extracted from the last stage of the compressor and transported to the inner channel of the blade. The oblique downward blowing air film hole is sprayed out, and this cold air adheres to the vicinity of the wall surface, forming a cold air film with a lower temperature, isolating the wall surface from the high-temperature gas, and taking away part of the radiant heat of the high-temperature gas or bright flame to the wall surface, Therefore, it has a good protective effect, so as to achieve the pu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 刘存良王瑞东
Owner NORTHWESTERN POLYTECHNICAL UNIV