CN202048023U - Primary blade of large-sized high-rotation-speed air compressor - Google Patents
Primary blade of large-sized high-rotation-speed air compressor Download PDFInfo
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- CN202048023U CN202048023U CN2011200485004U CN201120048500U CN202048023U CN 202048023 U CN202048023 U CN 202048023U CN 2011200485004 U CN2011200485004 U CN 2011200485004U CN 201120048500 U CN201120048500 U CN 201120048500U CN 202048023 U CN202048023 U CN 202048023U
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Abstract
A primary blade of a large-sized high-rotation-speed air compressor relates to air compressor blades and solves the problems that the existing blade is unstable in quality and low in efficiency and causes affection to safety operation of the air compressor. A blade operating portion and a blade root of the primary blade are integrally forged from top to bottom, a moulded line of the blade operating portion forms a variable-section twisted blade, the sectional area is gradually reduced from the root to the top, each two adjacent sections are twisted relatively, and sectional geometric data of the blade operating portion from the root to the top includes: the height from the root sectional number to the top sectional number is 202.46mm, the axial width ranges from 98.225mm to 63.322mm, the chord length ranges from 103.107mm to 103.001mm, an air inlet angle ranges from 47.5163 degrees to 31.1145 degrees, the largest thickness of the moulded line ranges from 12.292mm to 4.816mm, and the thickness of an air outlet edge ranges from 1.568mm to 0.614mm. The primary blade is used for large-sized high-rotation-speed air compressors.
Description
Technical field
The utility model relates to a kind of compressor blade.
Background technique
Because the rotating speed of large-scale gas compressor is very high,, aspect Security, require more strict so require blade better at aspect of performances such as strength vibrations.Each side to the chopped-off head blade requires also further strict.Existing chopped-off head blade is subjected to structure influence quality instability, and efficient is low, and working life is short, has had a strong impact on the safe operation of gas compressor.
The model utility content
The purpose of this utility model is to be subjected to structure influence quality instability for solving existing chopped-off head blade, and efficient is low, and working life is short, influences the problem of gas compressor safe operation, and a kind of large-scale high rotating speed gas compressor chopped-off head blade is provided.
The utility model is made up of blade working part and blade root, blade working part and blade root die forging from top to bottom are integral, the molded lines of blade working part is the variable cross section twisted blade, sectional area is reduced gradually by root to top, have relatively between adjacent two sections and reverse, the geometric data in the blade working part cross section from root to the top: the height of the cross section that is positioned at root number to the cross section that is positioned at the top number is 202.46mm, axial width is 98.225～63.322mm, chord length is 103.107～103.001mm, flow inlet angle is 47.5163 °～31.1145 °, the molded lines maximum ga(u)ge is 12.292～4.816mm, and trailing edge thickness is 1.568～0.614mm.
The utility model has the advantages that: one, the utility model is in the full three dimensional design so that one dimension/standard three-dimensional/full three-dimensional is pneumatic, thermodynamic analysis calculates this chopped-off head blade, make the Security and the high efficiency of this compressor blade organically combine, guaranteed large-scale high rotating speed gas compressor unit energy safe and highly efficient operation under variable working condition, increased the stability of blade, improve blade efficiency, prolonged blade working life.Two, blade root is adopted the flute profile blade root, and it has the bearing capacity height, characteristics easy for installation.
Description of drawings
Fig. 1 is a plan view of the present utility model, and Fig. 2 is the left view of Fig. 1, and Fig. 3 is overlooking of Fig. 1, and Fig. 4 is the superimposed schematic representation of blade working part 1 each cross section tomography, and Fig. 5 is the schematic cross-section of blade working part 1.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1～Fig. 4, present embodiment is made up of blade working part 1 and blade root 2, blade working part 1 and blade root 2 die forging from top to bottom are integral, the molded lines of blade working part 1 is the variable cross section twisted blade, sectional area is reduced gradually by root to top, have relatively between adjacent two sections and reverse, the geometric data in the cross section of blade working part 1 from root to the top: the cross section A-A that is positioned at root to the height L of the cross section N-N that is positioned at the top be 202.46mm, axial width B is 98.225～63.322mm, chord length b is 103.107～103.001mm, flow inlet angle α is 47.5163 °～31.1145 °, molded lines maximum ga(u)ge T is 12.292～4.816mm, and trailing edge thickness δ is 1.568～0.614mm.Design can guarantee the best stress of rotor like this, and avoids peak stress occurring in each tooth root portion and supporting plane.
Embodiment two: present embodiment is described in conjunction with Fig. 1～Fig. 4, the axial width B that the height L of the blade working part 1 of present embodiment is respectively the blade working part 1 of 40.49mm, 101.23mm, 161.97mm place correspondence respectively is: 92.472mm, 81.926mm, 70.727mm, pairing chord length b respectively is: 102.994mm, 102.985mm, 102.977mm, pairing flow inlet angle α respectively is: 46.0484 °, 41.459 °, 36.04 °, and pairing established angle β
yRespectively be: 63.053 °, 51.941 °, 42.721 °, pairing molded lines maximum ga(u)ge T respectively is: 10.964mm, 8.612mm, 6.312mm, pairing trailing edge thickness δ respectively is: 1.384mm, 1.094mm, 0.804mm.Adopt the said structure parameter, when the contour structure size that guarantees blade meets design requirement, blade is assembled easily.Other composition and annexation are identical with embodiment one.
Embodiment three: in conjunction with Fig. 1 and Fig. 2 present embodiment is described, the blade root 2 of present embodiment is the flute profile blade root, and the axial width W of blade root 2 is 102mm, and the total height K of blade root 2 is 66.58mm, the race of tangentially packing into.This structure makes the blade wheel rim of packing into securely, and assembling is stable, safe and reliable.Other composition and annexation are identical with embodiment one or two.
Concrete parameter in each cross section such as following table:
Claims (3)
1. one kind large-scale high rotating speed gas compressor chopped-off head blade, it is made up of blade working part (1) and blade root (2), blade working part (1) and blade root (2) die forging from top to bottom are integral, the molded lines of blade working part (1) is the variable cross section twisted blade, sectional area is reduced gradually by root to top, have relatively between adjacent two sections and reverse, it is characterized in that: the geometric data in blade working part (1) cross section from root to the top: the height (L) of number (N-N) is 202.46mm to the cross section that is positioned at the top in the cross section number (A-A) that is positioned at root, axial width (B) is 98.225～63.322mm, chord length (b) is 103.107～103.001mm, flow inlet angle (α) is 47.5163 °～31.1145 °, molded lines maximum ga(u)ge (T) is 12.292～4.816mm, and trailing edge thickness (δ) is 1.568～0.614mm.
2. according to the described a kind of large-scale high rotating speed gas compressor chopped-off head blade of claim 1, it is characterized in that: the height (L) of blade working part (1) is respectively 40.49mm, 101.23mm, 161.97mm the axial width (B) of the blade working of place correspondence part (1) respectively is: 92.472mm, 81.926mm, 70.727mm, pairing chord length (b) respectively is: 102.994mm, 102.985mm, 102.977mm, pairing flow inlet angle (α) respectively is: 46.0484 °, 41.459 °, 36.04 °, pairing established angle (β y) respectively is: 63.053 °, 51.941 °, 42.721 °, pairing molded lines maximum ga(u)ge (T) respectively is: 10.964mm, 8.612mm, 6.312mm pairing trailing edge thickness (δ) respectively is: 1.384mm, 1.094mm, 0.804mm.
3. according to claim 1 or 2 described a kind of large-scale high rotating speed gas compressor chopped-off head blades, it is characterized in that: blade root (2) is the flute profile blade root, and the axial width (W) of blade root (2) is 102mm, and the total height (K) of blade root (2) is 66.58mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200485004U CN202048023U (en) | 2011-02-25 | 2011-02-25 | Primary blade of large-sized high-rotation-speed air compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200485004U CN202048023U (en) | 2011-02-25 | 2011-02-25 | Primary blade of large-sized high-rotation-speed air compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202048023U true CN202048023U (en) | 2011-11-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200485004U Expired - Lifetime CN202048023U (en) | 2011-02-25 | 2011-02-25 | Primary blade of large-sized high-rotation-speed air compressor |
Country Status (1)
| Country | Link |
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| CN (1) | CN202048023U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103498813A (en) * | 2013-05-23 | 2014-01-08 | 哈尔滨汽轮机厂有限责任公司 | Low-pressure first-stage moving blade of gas compressor of gas turbine |
| CN103511001A (en) * | 2013-07-11 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | Turbine first-stage guide vane used for heavy type medium-and-low heat value combustion engine |
-
2011
- 2011-02-25 CN CN2011200485004U patent/CN202048023U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103498813A (en) * | 2013-05-23 | 2014-01-08 | 哈尔滨汽轮机厂有限责任公司 | Low-pressure first-stage moving blade of gas compressor of gas turbine |
| CN103498813B (en) * | 2013-05-23 | 2016-08-10 | 哈尔滨汽轮机厂有限责任公司 | A kind of low pressure chopped-off head moving vane of 20-30MW grade gas turbine compressor |
| CN103511001A (en) * | 2013-07-11 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | Turbine first-stage guide vane used for heavy type medium-and-low heat value combustion engine |
| CN103511001B (en) * | 2013-07-11 | 2015-04-22 | 哈尔滨汽轮机厂有限责任公司 | Turbine first-stage guide vane used for heavy type medium-and-low heat value combustion engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20111123 |
|
| CX01 | Expiry of patent term |