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Secondary first-stage blade for transonic compressor on high-speed gas turbine

A gas turbine, transonic technology, applied to parts of pumping devices for elastic fluids, machines/engines, liquid fuel engines, etc., can solve the hidden dangers of compressor operation, low calculation and manufacturing accuracy, and large blade wear, etc. problem, to achieve the effect of improving efficiency, improving work efficiency and increasing service life

Inactive Publication Date: 2013-12-04
HARBIN TURBINE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The invention provides a sub-primary blade for a transonic compressor on a high-speed gas turbine to solve the problem that the sub-prime blade of a transonic compressor used in a high-speed gas turbine has low calculation and manufacturing accuracy. The wear and tear is relatively large, not only the work efficiency is low, but also the service life is short. At the same time, it leaves a safety hazard for the operation of the compressor.

Method used

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  • Secondary first-stage blade for transonic compressor on high-speed gas turbine
  • Secondary first-stage blade for transonic compressor on high-speed gas turbine
  • Secondary first-stage blade for transonic compressor on high-speed gas turbine

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specific Embodiment approach 1

[0007] Specific implementation mode one: combine figure 1 , figure 2 , image 3 , Figure 4 with Figure 5 This embodiment is described. In this embodiment, a sub-first-stage blade for a transonic compressor on a high-speed gas turbine is described. The blade includes a blade working part 1 and a blade root 2, and the blade working part 1 and blade root 2 are composed of From top to bottom, the cross-sectional area of ​​the blade working part 1 decreases gradually from the root to the top. The profile of the blade working part 1 is a twisted blade with variable cross-section. The total height L is 146.22 mm, the axial width B of the blade working part 1 varies from the root of the blade working part 1 to the top of the blade working part 1, and the variation range is 71.12 mm to 40.06 mm, and the chord length of the cross section of the blade working part 1 is It is b, the variation range of b is 74.55mm~79.72mm, the bending angle is α, the variation range of α is 17.667°...

specific Embodiment approach 2

[0008] Specific implementation mode two: combination figure 1 , image 3 , Figure 4 , Figure 5 with Image 6 To illustrate this embodiment, the section heights H of the blade working part 1 described in this embodiment are 38.75mm, 79.39mm, 122.57mm, and 151.83mm respectively, and the corresponding axial widths B of the blade working part 1 are respectively 62.35mm and 53mm respectively. . The maximum thickness Dmax of the molding line is 8.30mm, 5.15mm, 2.69mm, 2.38mm, and the corresponding thickness DE of the air outlet edge at the distance F from the air outlet edge is 1.05mm, 0.61mm, 0.41mm, 0.34mm. The above structure is adopted Parameters, while ensuring that the shape and size of the blade meet the design requirements, it can also make the blade easy to assemble, and other components and connections are the same as in the first embodiment.

specific Embodiment approach 3

[0009] Specific implementation mode three: combination figure 1 , figure 2 with image 3 Describe this embodiment, the total height of the blade root 2 in this embodiment is K, K=13.67mm, the blade root 2 is a helical fir tree-shaped blade root, and the axial width of the blade root 2 is W, W=81.53mm , with the above-mentioned structure, the blade can be firmly loaded into the rim, and the assembly is stable, safe and reliable, and the other components and connections are the same as those in the first embodiment.

[0010] The specific parameters of each section are as follows:

[0011] section

[0012] B——B0

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Abstract

The invention belongs to the field of gas turbine blades, and relates to a secondary first-stage blade for a transonic compressor on a high-speed gas turbine. The problems that due to computing and manufacturing accuracy, a secondary first-stage blade of a transonic compressor for an existing high-speed gas turbine is high in wear, low in working efficiency and short in service life and causes security risk to running of the compressor are solved. A blade working portion and a blade root are made into a whole from top to bottom, the overall height L of the working portion is 146.22mm, the axial width B of the root of the blade working portion is 70.46mm, a variation range of the axial width B of the blade working portion is within 71.12mm-40.06mm, a variation range of chord length b of a cross section of the blade working portion is within 74.55mm-79.72mm, a variation range of a bending angle alpha is within 17.667 degrees-59.508 degrees, a variation range of the maximum thickness Dmax of a profile is 8.46-2.38mm, and the thickness DE of the position, 0.7mm away from an air outing edge, of the air outing edge is 1.59-0.34mm.

Description

technical field [0001] The invention relates to a sub-first-stage blade of a transonic compressor, which belongs to the field of compressor blades. Background technique [0002] The current high-speed (rotation speed between 8000-10000n / min) gas turbines used in transonic (some supersonic, some subsonic) sub-first stage compressor blades have a single variety and primitive design methods, which cannot be used for accurate aerodynamic calculation and flow. Therefore, the calculation and manufacturing accuracy is low, so that the design of the blade surface is not smooth, and the wear of the blade is relatively large during use, which not only has low work efficiency, but also has a short service life. Hidden danger. Contents of the invention [0003] The invention provides a sub-primary blade for a transonic compressor on a high-speed gas turbine to solve the problem that the sub-prime blade of a transonic compressor used in a high-speed gas turbine has low calculation and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/26
Inventor 张秋鸿张宏涛张成义王玲冯永志张春梅赵俊明姜东坡席会杰王颖李昕黄揆张连杰
Owner HARBIN TURBINE
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