CN202065239U - Interstage blade of air compressor with hub diameter of phi 616 - Google Patents
Interstage blade of air compressor with hub diameter of phi 616 Download PDFInfo
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- CN202065239U CN202065239U CN2011201720266U CN201120172026U CN202065239U CN 202065239 U CN202065239 U CN 202065239U CN 2011201720266 U CN2011201720266 U CN 2011201720266U CN 201120172026 U CN201120172026 U CN 201120172026U CN 202065239 U CN202065239 U CN 202065239U
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Abstract
The utility model discloses an interstage blade of an air compressor with a hub diameter of phi 616, which relates to the air compressor interstage blade. The problem that a traditional interstage blade of the air compressor with the hub diameter of phi 616 has low efficiency and a short service life and the problem that the safe running of an air compressor is affected. The cross section of a working part of the blade from the root part to the top part has the following geometric data that: the height of the cross sections from the cross section A-A to the cross section F-F is 4.99m to 68.06mm; the axial width is 35.929mm to 28.665mm; the chord length is 39.722mm to 39.723mm; the air inlet angle is 44.192 degrees to 31.768 degrees; the mounting angle is 63.483 degrees to 45.226 degrees; the maximal thickness of a moulded line is 4.640mm to 3.245mm; the air outlet side thickness is 0.273mm to 0.192mm; and the total height of the blade working part is 68.79cm. The interstage blade of the air compressor with the hub diameter of phi 616 is applied to the air compressor.
Description
Technical field
The utility model relates to a kind of gas compressor intergrade blade.
Background technique
Hub diameter is that the gas compressor intergrade blade design method of Φ 616 is original, and calculation accuracy is lower, can't carry out accurate Pneumatic Calculation and Flow Field Calculation, thereby make blade profile design not fairing, 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 provides the gas compressor intergrade blade that a kind of hub diameter is Φ 616, is to solve present hub diameter that the gas compressor intergrade blade efficiency of Φ 616 is low, working life short, influences the problem of gas compressor safe operation.
The utility model is to solve the problems of the technologies described above the technological scheme of taking to be: described blade comprises blade working part and blade root, blade working part and blade root are made one from top to bottom, the molded lines of blade working part is the variable cross section twisted blade, along blade height sectional shape difference, sectional area is reduced gradually by root to top, has relatively between adjacent two sections and reverses; The geometric data of blade working part from close root to the cross section at top: section A-A to the depth of section of cross section F-F is 4.99m～68.06mm, axial width is 35.929～28.665mm, chord length is 39.722～39.723mm, flow inlet angle is 44.192 °～31.768 °, established angle is 63.483 °～45.226 °, the molded lines maximum ga(u)ge is 4.640～3.245mm, and trailing edge thickness is 0.273～0.192mm, and the total height of blade working part is 68.79cm.
The utlity model has following beneficial effect: the utility model is with one dimension, accurate three-dimensional, complete three-dimensional pneumatic, full three dimensional design that thermodynamic analysis calculates this intergrade blade, the calculation accuracy height, make Security of the present utility model and high efficiency organically combine, guaranteed energy safe and highly efficient operation under variable working condition, increased the stability of blade, improve blade efficiency, prolonged blade working life.
Description of drawings
Fig. 1 is a plan view of the present utility model; Fig. 2 is the left view of Fig. 1; Fig. 3 is the plan view of Fig. 1; Fig. 4 is the superimposed schematic representation of blade working each cross section tomography of part; Fig. 5 is blade profile parameters Q, b, α, β
y, T, δ schematic representation.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1-Fig. 5, the described blade of present embodiment comprises blade working part 1 and blade root 2, blade working part 1 and blade root 2 are made one from top to bottom, the molded lines of blade working part 1 is the variable cross section twisted blade, along blade height sectional shape difference, sectional area is reduced gradually by root to top, has relatively between adjacent two sections and reverses; Blade working part 1 near root to the geometric data in the cross section at top: section A-A to the depth of section H of cross section F-F be 4.99m～68.06mm, axial width Q is 35.929～28.665mm, chord length b is 39.722～39.723mm, flow inlet angle α is 44.192 °～31.768 °, established angle β
yBe 63.483 °～45.226 °, molded lines maximum ga(u)ge T is 4.640～3.245mm, and trailing edge thickness δ is 0.273～0.192mm, and the total height L of blade working part 1 is 68.79cm.Other compositions and annexation are identical with embodiment one.
Embodiment two: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the depth of section H of blade working part 1 section A-A of present embodiment is 4.99mm, and the axial width Q of the pairing blade working part 1 in this position is that 35.929mm, chord length b are that 39.722mm, flow inlet angle α are 44.192 °, established angle β
yBe that 63.483 °, molded lines maximum ga(u)ge T are that 4.640mm, trailing edge thickness δ are 0.273mm.Other compositions and annexation are identical with embodiment one.
Embodiment three: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the depth of section H of blade working part 1 section B-B of present embodiment is 17.56mm, and the axial width Q of the pairing blade working part 1 in this position is that 34.688mm, chord length b are that 39.719mm, flow inlet angle α are 42.803 °, established angle β
yBe that 59.587 °, molded lines maximum ga(u)ge T are that 4.348mm, trailing edge thickness δ are 0.260mm.Other compositions and annexation are identical with embodiment one.
Embodiment four: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the depth of section H of the blade working part 1 cross section C-C of present embodiment is 30.18mm, and the axial width Q of the pairing blade working part 1 in this position is that 33.274mm, chord length b are that 39.720mm, flow inlet angle α are 43.506 °, established angle β
yBe that 55.685 °, molded lines maximum ga(u)ge T are that 4.072mm, trailing edge thickness δ are 0.242mm.Other compositions and annexation are identical with embodiment one.
Embodiment five: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the depth of section H of the blade working part 1 cross section D-D of present embodiment is 42.18mm, and the axial width Q of the pairing blade working part 1 in this position is that 31.799mm, chord length b are that 39.721mm, flow inlet angle α are 39.696 °, established angle β
yBe that 52.013 °, molded lines maximum ga(u)ge T are that 3.790mm, trailing edge thickness δ are 0.225mm.Other compositions and annexation are identical with embodiment one.
Embodiment six: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the depth of section H of the blade working part 1 cross section E-E of present embodiment is 55.44mm, and the axial width Q of the pairing blade working part 1 in this position is that 30.229mm, chord length b are that 39.722mm, flow inlet angle α are 35.419 °, established angle β
yBe that 48.490 °, molded lines maximum ga(u)ge T are that 3.514mm, trailing edge thickness δ are 0.209mm.Other compositions and annexation are identical with embodiment one.
Embodiment seven: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the depth of section H of the blade working part 1 cross section F-F of present embodiment is 68.06mm, and the axial width Q of the pairing blade working part 1 in this position is that 28.665mm, chord length b are that 39.723mm, flow inlet angle α are 31.768, established angle β
yBe that 45.226 °, molded lines maximum ga(u)ge T are that 3.245mm, trailing edge thickness δ are 0.192mm.Other compositions and annexation are identical with embodiment one.
Embodiment eight: in conjunction with Fig. 1 and Fig. 4 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 37.45mm, and the total height K of blade root 2 is 28.09mm.Blade root 2 is adopted the flute profile blade root, and it has the bearing capacity height, characteristics easy for installation.Other compositions and annexation are identical with embodiment one.
Claims (8)
1. gas compressor intergrade blade that hub diameter is Φ 616, described blade comprises blade working part (1) and blade root (2), blade working part (1) and blade root (2) are made one from top to bottom, the molded lines of blade working part (1) is the variable cross section twisted blade, along blade height sectional shape difference, sectional area is reduced gradually by root to top, has relatively between adjacent two sections and reverses; It is characterized in that the geometric data of blade working part (1) from close root to the cross section at top: section A-A to the depth of section (H) of cross section F-F is 4.99mm～68.06mm, axial width (Q) is 35.929～28.665mm, chord length (b) is 39.722～39.723mm, flow inlet angle (α) is 44.192 °～31.768 °, established angle (β
y) be 63.483 °～45.226 °, molded lines maximum ga(u)ge (T) is 4.640～3.245mm, and trailing edge thickness (δ) is 0.273～0.192mm, and the total height (L) of blade working part (1) is 68.79cm.
2. according to the described hub diameter of claim 1 the gas compressor intergrade blade of Φ 616, the depth of section (H) that it is characterized in that blade working part (1) section A-A is 4.99mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 35.929mm, chord length (b) are 44.192 °, established angle (β for 39.722mm, flow inlet angle (α)
y) be that 63.483 °, molded lines maximum ga(u)ge (T) are 0.273mm for 4.640mm, trailing edge thickness (δ).
3. be the gas compressor intergrade blade of Φ 616 according to claim 1 or 2 described hub diameters, the depth of section (H) that it is characterized in that blade working part (1) section B-B is 17.56mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 34.688mm, chord length (b) are 42.803 °, established angle (β for 39.719mm, flow inlet angle (α)
y) be that 59.587 °, molded lines maximum ga(u)ge (T) are 0.260mm for 4.348mm, trailing edge thickness (δ).
4. according to the described hub diameter of claim 3 the gas compressor intergrade blade of Φ 616, the depth of section (H) that it is characterized in that blade working part (1) cross section C-C is 30.18mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 33.274mm, chord length (b) are 43.506 °, established angle (β for 39.720mm, flow inlet angle (α)
y) be that 55.685 °, molded lines maximum ga(u)ge (T) are 0.242mm for 4.072mm, trailing edge thickness (δ).
5. according to the described hub diameter of claim 4 the gas compressor intergrade blade of Φ 616, the depth of section (H) that it is characterized in that blade working part (1) cross section D-D is 42.18mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 31.799mm, chord length (b) are 43.506 °, established angle (β for 39.721mm, flow inlet angle (α)
y) be that 52.013 °, molded lines maximum ga(u)ge (T) are 0.225mm for 3.790mm, trailing edge thickness (δ).
6. according to the described hub diameter of claim 5 the gas compressor intergrade blade of Φ 616, the depth of section (H) that it is characterized in that blade working part (1) cross section E-E is 55.44mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 30.229mm, chord length (b) are 34.419 °, established angle (β for 39.722mm, flow inlet angle (α)
y) be that 48.490 °, molded lines maximum ga(u)ge (T) are 0.209mm for 3.514mm, trailing edge thickness (δ).
7. according to the described hub diameter of claim 6 the gas compressor intergrade blade of Φ 616, the depth of section (H) that it is characterized in that blade working part (1) cross section F-F be 68.06mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 28.665mm, chord length (b) are that 39.723mm, flow inlet angle (α) are 31.768, established angle (β
y) be that 45.226 °, molded lines maximum ga(u)ge (T) are 0.192mm for 3.245mm, trailing edge thickness (δ).
8. be the gas compressor intergrade blade of Φ 616 according to the described hub diameter of claim 7, it is characterized in that blade root (2) is the flute profile blade root, the axial width (W) of blade root (2) is 37.45mm, and the total height (K) of blade root (2) is 28.09mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201720266U CN202065239U (en) | 2011-05-26 | 2011-05-26 | Interstage blade of air compressor with hub diameter of phi 616 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201720266U CN202065239U (en) | 2011-05-26 | 2011-05-26 | Interstage blade of air compressor with hub diameter of phi 616 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202065239U true CN202065239U (en) | 2011-12-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201720266U Expired - Lifetime CN202065239U (en) | 2011-05-26 | 2011-05-26 | Interstage blade of air compressor with hub diameter of phi 616 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202065239U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103352871A (en) * | 2013-06-26 | 2013-10-16 | 哈尔滨汽轮机厂有限责任公司 | High-pressure middle-stage moving blade of gas compressor for gas turbine |
-
2011
- 2011-05-26 CN CN2011201720266U patent/CN202065239U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103352871A (en) * | 2013-06-26 | 2013-10-16 | 哈尔滨汽轮机厂有限责任公司 | High-pressure middle-stage moving blade of gas compressor for gas turbine |
| CN103352871B (en) * | 2013-06-26 | 2015-09-16 | 哈尔滨汽轮机厂有限责任公司 | A kind of high pressure intergrade moving vane of gas turbine gas compressor |
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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 | ||
| CX01 | Expiry of patent term |
Granted publication date: 20111207 |