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Turbine blade partition rib parametric modeling method

A kind of turbine blade, parametric technology, applied in the direction of blade support elements, electrical digital data processing, special data processing applications, etc., can solve problems such as unfavorable bending and twisted blade layout, achieve refined cooling air flow, good cooling effect, Optimizing the effect of placement

Inactive Publication Date: 2013-08-14
BEIHANG UNIV
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  • Description
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Problems solved by technology

[0006] (1) The cross-sectional shape is simple, which is not conducive to the arrangement in the curved and twisted blades;

Method used

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  • Turbine blade partition rib parametric modeling method
  • Turbine blade partition rib parametric modeling method
  • Turbine blade partition rib parametric modeling method

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Embodiment Construction

[0041] The present invention will be further described below in conjunction with accompanying drawing.

[0042] The parametric modeling method of the turbine blade partition rib of the present invention is based on the UG environment and is realized through the following steps, such as image 3 Shown:

[0043] Step 1: Start UG, and import the solid file of the inner shape of the turbine blade;

[0044] Open the modeling module in UG and import the existing turbine blade internal shape entity file; make the origin O in the UG absolute coordinate system O(x,y,z) be on the axis of the turbine engine, the positive direction of the Z axis is in the direction of the blade height, and the X The positive direction of the axis is from front to rear along the centerline of the engine, and the positive direction of the Y-axis is determined according to the right-hand rectangular coordinate system, such as Figure 4 shown.

[0045] Step 2: Select n reference points longitudinally from ...

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Abstract

The invention discloses a turbine blade partition rib parametric modeling method. The method sequentially includes the steps: importing a blade inner model entity into a UG (unigraphics); selecting n datum points longitudinally from the blade inner model entity; 1, establishing a datum plane; 2, establishing a fixed datum plane; 3, rotating the datum plane by alpha degrees to obtain a reference datum and an alpha expression; 4, creating a sketch inside the datum plane, creating a rectangular cross-section wireframe in the sketch and an expression of length and width of the rectangular cross-section wireframe; 5, sweeping n rectangular cross-section wireframes to generate a partition rib tool body; 6, performing Boolean subtraction for the partition rib tool body and the blade inner model entity to obtain a blade inner model entity with a partition rib anti-phase characteristic; repeating the steps to generate a blade inner model entity with m partition rib anti-phase characteristics; and importing a blade outer model entity into the UG to subtract the blade inner model entity with the m partition rib anti-phase characteristics to obtain a turbine blade with m partition ribs. By the method, straight or cambered partition rib parametric modeling can be performed quickly and accurately.

Description

technical field [0001] The invention relates to the technical field of turbine blade design, and specifically relates to a parametric modeling method for a partition rib (also known as a partition wall) of a turbine blade, which is applicable to the modeling of straight and twisted partition ribs. Background technique [0002] Turbine engines are widely used in aviation, ships, and large engineering vehicles. Increasing the temperature before the turbine is an important measure to increase the thrust of the engine. However, the temperature before the turbine is limited by the tolerance of the turbine blade material. Therefore, it is of great significance to refine the cooling air and enhance the cooling effect of the cooling gas on the turbine blades to improve the efficiency of the turbine engine. [0003] Air-mode cooling and internal flow cooling are the main cooling methods for turbine blades, such as figure 1 As shown, the cold air enters the interior of the turbine bl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18G06F17/50
Inventor 席平杨炯张宝源胡毕富唐家鹏
Owner BEIHANG UNIV
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