Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Gas turbine engine blade with inner meshed structure

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

Inactive Publication Date: 2015-03-04
BEIHANG UNIV
View PDF14 Cites 4 Cited by
  • 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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • 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...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
Inventor 彭徽郭洪波宫声凯徐惠彬
Owner BEIHANG UNIV
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com