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High-pressure inlet guide blade of gas compressor for gas turbine

A technology for gas turbines and compressors, which is applied to machines/engines, liquid fuel engines, and components of pumping devices for elastic fluids, etc., can solve problems such as short service life, low work efficiency, and affecting the safe operation of compressors, etc. Achieve the effect of prolonging service life, improving work efficiency and increasing stability

Inactive Publication Date: 2013-12-25
HARBIN TURBINE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problems of low working efficiency, short service life and influence on the safe operation of the compressor high-pressure inlet guide vane for the existing gas turbine, and further provide a high-pressure inlet guide vane for the gas turbine compressor

Method used

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  • High-pressure inlet guide blade of gas compressor for gas turbine
  • High-pressure inlet guide blade of gas compressor for gas turbine
  • High-pressure inlet guide blade of gas compressor for gas turbine

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specific Embodiment approach 1

[0018] Specific implementation mode one: combine Figure 1-Figure 6 Describe this embodiment, the high-pressure inlet guide vane of a kind of gas turbine compressor of this embodiment includes blade working part 1 and blade root 2, and blade root 2 and blade working part 1 are sequentially made into one from top to bottom, and described blade The working part 1 is a twisted blade with variable cross-section, and the height and cross-sectional shape of the working part 1 of the blade are different. The cross-sectional area of ​​the working part 1 of the blade gradually decreases from the root to the top. The total height L0 is 72.800mm. The root to the top of the blade working part 1 is divided into nine sections: A-A, B-B, C-C, D-D, E-E, F-F, G-G, H-H and I-I. The section height h from section A-A to section I-I is 5.500~ 81.500mm, the chord length b is 50.022~50.036mm, the installation angle β is 73.609°~69.187°, the maximum thickness δ of the molding line is 4.499~2.820mm, a...

specific Embodiment approach 2

[0029] Specific implementation mode two: combination figure 1 and figure 2 The present embodiment will be described. The blade root 2 of the present embodiment is a dovetail-shaped blade root. With such an arrangement, the blades can be easily assembled while ensuring that the overall structural dimensions of the blades meet the design requirements. Other components and connections are the same as those in the first embodiment.

specific Embodiment approach 3

[0030] Specific implementation mode three: combination figure 1 and image 3 The present embodiment will be described. The width W of the blade root 2 in the present embodiment is 58.000 mm. Such setting, this structure enables the blade to be firmly installed into the wheel rim, and is convenient to be axially installed into the wheel groove. Such a size has a large load-bearing area, which is safe and reliable. Other components and connections are the same as those in the second embodiment.

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Abstract

The invention discloses a high-pressure inlet guide blade of a gas compressor for a gas turbine, and relates to a high-pressure inlet guide blade. A blade root and a blade working portion of the high-pressure inlet guide blade are integrally manufactured from top to bottom, the blade working portion comprises a variable-section twisted blade, the shapes of sections of the blade working portion are different from one another along the height direction of the blade, the sectional area of the blade working portion is gradually reduced from the root to the top of the blade working portion, and relative torsion can be generated between each two adjacent sections; geometric data of the sections of the blade working portion from the root to the top of the blade working portion include that heights of the sections with section numbers from A-A to I-I range from 5.500mm to 81.500mm, chord lengths b of the sections with the section numbers from A-A to I-I range from 50.022mm to 50.036mm, mounting angles beta of the sections with the section numbers from A-A to I-I range from 73.609 degrees to 69.187 degrees, the maximum line thicknesses delta of the sections with the section numbers from A-A to I-I range from 4.499mm to 2.820mm, thicknesses C of gas outlet sides separated from corresponding gas outlet sides by distances L1 of 1mm range from 0.621mm to 0.506mm, and the total height L0 of the blade working portion is 72.800mm. The high-pressure inlet guide blade has the advantage that problems that an existing high-pressure inlet guide blade of a gas compressor for a gas turbine is low in work efficiency and short in service life and the safety running of the gas compressor is affected can be solved. The high-pressure inlet guide blade is applied to the gas compressor for the gas turbine.

Description

technical field [0001] The invention relates to a first-stage guide vane of a turbine, in particular to a high-pressure inlet guide vane of a gas turbine compressor. Background technique [0002] At present, the high-pressure inlet guide blades of gas turbines used in gas turbines have a single variety, primitive design methods, low calculation accuracy, and cannot perform accurate aerodynamic calculations and flow field calculations, resulting in uneven blade profile design, low work efficiency, and short service life. Has seriously affected the economy and safety of the compressor. Contents of the invention [0003] The object of the present invention is to solve the problems of low working efficiency, short service life and influence on the safe operation of the existing compressor high-pressure inlet guide vane for gas turbine, and further provide a high-pressure inlet guide vane for gas turbine compressor. [0004] The technical scheme of the present invention is: a ...

Claims

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Application Information

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IPC IPC(8): F04D29/38
Inventor 张秋鸿张宏涛梁培培杨艳吴爽新刘强张春梅陈洪港
Owner HARBIN TURBINE
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