Gas turbine engine blade with inner meshed structure

A technology for engine blades and internal structures, applied in the direction of engine components, machines/engines, blade support components, etc., can solve problems such as low processing yield, inability to manufacture complex internal structures, reduce design and processing costs, and increase contact area, improve overall stress uniformity, and reduce the effect of design and processing costs

Inactive Publication Date: 2013-12-25
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0014] The airfoil, mortise, internal flow channel and grid structure of the cooling blade described in the present invention are all formed by additive manufacturing technology, and the processing technology is simple, which overcomes the shortcomings of low yield rate and inability to manufacture complex internal structures in traditional casting, and can Greatly reduce design and processing costs

Method used

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  • Gas turbine engine blade with inner meshed structure
  • Gas turbine engine blade with inner meshed structure
  • Gas turbine engine blade with inner meshed structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] Fig. 3 is a schematic diagram of cross-grid filling inside the hollow airfoil without diverter partitions, including airfoil 1 (Fig. 3(a)) and grid structure 2 (Fig. 3(b)). Both the thickness of the airfoil 1 and the periodic size of the substructure of the grid are 2 mm. After filling the grid structure, the internal heat exchange area of ​​the blade increases by ~130%. The simplified simulation calculation results show that under the same inlet cooling gas condition, the heat transfer capacity of the structure can be increased by 45%.

Embodiment 2

[0032] Figure 4a and Figure 4b It is the structural diagram of the cooling blade of the traditional DC clapboard. The partition plate 3 divides the channel into multiple cooling chambers 4, the cold air flows in from the blade root 5, then flows along the cooling chamber 4 to the blade tip 6, part of it flows out from the blade tip 6, and part of it passes through the gap between the partition plate 3 and the blade tip 6. The hole flows to the exhaust slot 7 on the trailing edge and flows out from the exhaust slot 7 .

[0033] Figure 5a and Figure 5b It is a schematic diagram of filling the grid structure in the cooling blade of the traditional DC baffle. The filling of the grid structure 8 does not change the design of the cooling blade flow channel, but only fills in the cooling cavity 4 formed by the partition plate 3, and the cold air flow direction does not change, and will still flow in the direction of the arrow marked in FIG. 4 . The wall thickness of the airf...

Embodiment 3

[0035] Fig. 6 is a schematic diagram of the grid structure filled in the interior part of the cooling blade of the traditional DC separator. The wall thickness of the airfoil is 1 mm, the internal space of the airfoil is 3-8 mm, and the grid structure 9 is filled in the inner wall of the airfoil and the side wall of the diversion partition. The thickness of the filled grid structure is 1 mm, and the periodic size of the substructure is 1 mm. The filling of the grid structure 9 does not change the flow channel design of the cooling blade, and the flow direction of the cold air does not change, and will still flow in the direction of the arrow marked in FIG. 4 . When the cold air flows through the flow channel, because the grid structure is only partially filled, the pressure drop of the cold air flow rate is less affected; at the same time, the filling height of the grid structure is equivalent to the height of the spoiler fins originally designed by the blade, which can destro...

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PUM

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Abstract

The invention discloses a gas turbine engine blade with an inner meshed structure. The blade is formed by SLM or EBM material increase manufacturing technology, and the inside of the blade is provided with a meshed structure. The meshed structure is composed of sub structures arraying in a three-dimensional periodic manner, and communicated channels are formed inside the communicated meshed structure to form multiple channel structures. All or parts of the meshed structures are filled into gaps among partitioning plates of the blade. By the aid of the inner meshed structure of the blade, heat exchange effect of cooling flow can be strengthened. A blade body, tenons, inner channels and the meshed structure are formed by the material increase manufacturing technology, machining process is simple, defects that finished product rate is low by traditional casting and machining and complex inner structure cannot be manufactured are overcome, and designing and machining cost can be reduced greatly.

Description

technical field [0001] The invention relates to the cooling technology of the high-temperature structural components of the gas turbine engine, and more specifically relates to the technology of improving the cooling efficiency of high-pressure turbine blades and guider blades in the aero-engine. Background technique [0002] In order to obtain higher thermal efficiency of modern gas turbine engines, the turbine inlet temperature has been continuously increased, which has far exceeded the melting point temperature of superalloy blade materials. For example, the working temperature of the second-generation single crystal superalloy used for high and low pressure turbine blades is 1070°C-1100°C, while the temperature before the turbine of the advanced aero-engine in service has reached 1300°C-1400°C. In such a high-temperature working environment, to ensure long-term stable operation of the blades, it is necessary to effectively cool the turbine blades, and at the same time re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
Inventor 彭徽郭洪波宫声凯徐惠彬
Owner BEIHANG UNIV
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