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Porous metal vane coupling design method

A technology of porous metal and design method, which is applied to the supporting elements of blades, mechanical equipment, components of pumping devices for elastic fluids, etc. The effect of cooling air volume, improving performance and service life, and increasing specific strength

Inactive Publication Date: 2013-03-27
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Also for aero-engines or gas turbines, another important component, the high-pressure turbine, needs efficient cooling to ensure that the turbine components can withstand high-temperature gas and work for a long time. At present, many efficient cooling methods have been developed at home and abroad, but the inside of the turbine blades The cooling channel of the cooling channel is very complicated, resulting in difficult processing, complicated process and low yield

Method used

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  • Porous metal vane coupling design method
  • Porous metal vane coupling design method
  • Porous metal vane coupling design method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0014] Embodiment 1: The method is used in the design process of the blade of turbomachinery, which includes the following steps:

[0015] 1) Perform blade aerodynamic design;

[0016] 2) select the porosity to carry out the design of the sandwich body of the porous metal blade;

[0017] 3) Conduct strength and vibration analysis on porous metal blades;

[0018] 4) Processing the sandwich body;

[0019] 5) Process the outer lining of the blade;

[0020] 6) Check and check the porous metal blade, and repeat the above steps until the design is completed.

Embodiment 2

[0021] Embodiment 2: the method is used for the design process of fan or compressor blade, and it comprises the steps:

[0022] 1) Carry out the aerodynamic design of the fan / compressor blade, and obtain the velocity triangle, aerodynamic parameters, stage parameters and total parameters of each blade outlet along the radial section according to the overall performance requirements of the aero-engine / gas turbine; then complete the blade type Surface modeling and airfoil stacking, and finally the design results obtained through the calculation and analysis of the full three-dimensional viscous flow field are checked. If the requirements are not met, the above process is repeated until the aerodynamic performance requirements are met; Styling means to achieve advanced aerodynamic performance indicators;

[0023] 2) The fan or compressor blade that step 1) is obtained is carried out the analysis of solid metal blade intensity, according to strength analysis result, select porosit...

Embodiment 3

[0028] Embodiment 3: the method is used for the design process of turbine blade, and it comprises the steps:

[0029] 1) Carry out the aerodynamic design of the turbine blades, and obtain the velocity triangle, aerodynamic parameters, stage parameters and total parameters of each blade outlet along the radial section according to the overall performance requirements of the components of the aero-engine / gas turbine; then complete the blade surface modeling, The airfoils are stacked, and finally the design results obtained through the calculation and analysis of the full three-dimensional viscous flow field are checked. If the requirements are not met, the above process is repeated until the aerodynamic performance requirements are met; The aerodynamic performance index;

[0030] 2) Analyze the blade cooling and heat transfer characteristics of traditional metal materials for the blade obtained in step 1). According to the required blade cooling efficiency, design the porosity d...

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Abstract

The invention relates to a design method for porous metal blade. The method combines porous metal material with design of blade and the manufacturing process. By the high specific strength characteristic of porous metal material and adjusting porosity of said material, blade coupling design of process, strength, vibration, and pneumatic thermal force is carried out so as to improve the specific strength of blade and satisfy the flow control demand of blade boundary layer. The method conquers the lack of solid or hollow blade in prior technology. The good performance of porous metal material is used. Blade material characteristic, strength, vibration and pneumatic thermal force performance are considered in synthesis. The coupling design method for blade process, strength, vibration, pneumatic thermal force of porous metal is provided and part performance of aeroengine and gas turbine can be improved greatly. At the same time the invention provides a blade designed by the method, aeroengine and gas turbine comprising blade mentioned above.

Description

technical field [0001] The invention relates to a blade design method, in particular to a method for designing and manufacturing blades of turbine components in aeroengines or gas turbines; the invention also relates to blades designed by the method and turbomachines including the blades. Background technique [0002] In the design of modern turbomachinery, the three-dimensional modeling methods of the blades have been more and more widely used, and these methods have further improved the performance of the turbomachine. Taking the fan aerodynamic design as an example, improving the aerodynamic load, efficiency and stable working range of the fan has become the goal pursued by advanced fan design. Among them, the method of increasing the aerodynamic load includes: increasing the tangential velocity of the rotor blade tip, but since the centrifugal force borne by the rotating blade is proportional to the product of the blade mass, rotating speed and radius, when the rotor rot...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14F04D29/30
Inventor 邹正平徐力平刘火星叶建
Owner BEIHANG UNIV
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