CN202108784U - Secondary-primary impeller of compressor with phi 762 hub diameter - Google Patents
Secondary-primary impeller of compressor with phi 762 hub diameter Download PDFInfo
- Publication number
- CN202108784U CN202108784U CN201120171988XU CN201120171988U CN202108784U CN 202108784 U CN202108784 U CN 202108784U CN 201120171988X U CN201120171988X U CN 201120171988XU CN 201120171988 U CN201120171988 U CN 201120171988U CN 202108784 U CN202108784 U CN 202108784U
- Authority
- CN
- China
- Prior art keywords
- blade
- section
- working part
- blade working
- axial width
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A secondary-primary impeller of a compressor with a phi 762 hub diameter relates to a secondary-primary impellor of a compressor, and aims at solving the problems that the existing secondary-primary impeller of the compressor with the phi 762 hub diameter has low efficiency and short service life and influences the safety running of the compressor. The geometrical data of the section from being near to the root to the top of the working part of the impeller is as follows: the height of the section A-A to the section J-J ranges from 0 to 146.68mm, the axial width ranges from 70.029mm to 49.406mm, the chord length ranges from 73.561mm to 73.615mm, the axial width ranges 70.029mm to 49.406mm, the air inlet angle ranges from 46.727 degrees to 33.281 degrees, the installation angle ranges from 70.931 degrees to 41.609 degrees, the largest thickness of a shaped line ranges from 8.592mm to 3.929mm, the thickness of an air outlet edge ranges from 0.510mm to 0.235mm, and the overall height of the working part of the impeller is 146.18cm. The secondary-primary impeller is applicable to the compressor.
Description
Technical field
The utility model relates to a kind of gas compressor time chopped-off head blade.
Background technique
Hub diameter is that the gas compressor time chopped-off head blade design method of Φ 762 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 the utility model provides the gas compressor time chopped-off head blade that a kind of hub diameter is Φ 762, is to solve present hub diameter that the gas compressor time chopped-off head blade efficiency of Φ 762 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: said blade comprises blade working part and blade root; Blade working part and blade root are processed one from top to bottom; The molded lines of blade working part is the variable cross section twisted blade; Different along the blade height sectional shape, sectional area is reduced by root to top gradually, has relatively between adjacent two sections and reverses; It is characterized in that the geometric data of blade working part from the cross section at root to top: the depth of section of section A-A J-J to the cross section is 0～146.68mm; Axial width is 70.029～49.406mm, and chord length is 73.561～73.615mm, and flow inlet angle is 46.727 °～33.281 °; Established angle is 70.931 °～41.609 °; The molded lines maximum ga(u)ge is 8.592～3.929mm, and trailing edge thickness is 0.510～0.235mm, and the total height of blade working part is 146.18cm.
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 time chopped-off head blade; Calculation accuracy is high; Make the Security and the high efficiency of the utility model organically combine, guaranteed ability 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 the plan view of the utility model; Fig. 2 is the left view of Fig. 1; Fig. 3 is overlooking 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 B, b, α, B
y, T, δ schematic representation.
Embodiment
Embodiment one: combine Fig. 1-Fig. 5 that this mode of execution is described; The blade of this mode of execution comprises blade working part 1 and blade root 2; Blade working part 1 is processed one from top to bottom with blade root 2, and the molded lines of blade working part 1 is the variable cross section twisted blade, and is different along the blade height sectional shape; Sectional area is reduced by root to top gradually, has relatively between adjacent two sections and reverses; It is characterized in that the geometric data of blade working part 1 from the cross section at root to top: the depth of section h of section A-A J-J to the cross section is 0～146.68mm; Axial width Q is 70.029～49.406mm; Chord length b is 73.561～73.615mm; Flow inlet angle α is 46.727 °～33.281 °, established angle B
yBe 70.931 °～41.609 °, molded lines maximum ga(u)ge T is 8.592～3.929mm, and trailing edge thickness δ is 0.510～0.235mm, and the total height L of blade working part 1 is 146.18cm.
Embodiment two: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of blade working part 1 section A-A of this mode of execution is 6.64mm, and the axial width Q of the pairing blade working part 1 in this position is that 70.029mm, chord length b are that 73.561mm, flow inlet angle α are 46.727 °, established angle B
yBe that 70.931 °, molded lines maximum ga(u)ge T are that 8.592mm, trailing edge thickness δ are 0.510mm.Other compositions and annexation are identical with embodiment one.
Embodiment three: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of blade working part 1 section B-B of this mode of execution is 22.20mm, and the axial width Q of the pairing blade working part 1 in this position is that 68.330mm, chord length b are that 73.559mm, flow inlet angle α are 50.093 °, established angle B
yBe that 67.039 °, molded lines maximum ga(u)ge T are that 8.064mm, trailing edge thickness δ are 0.478mm.Other compositions and annexation are identical with embodiment one.
Embodiment four: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section C-C of this mode of execution is 37.76mm, and the axial width Q of the pairing blade working part 1 in this position is that 66.295mm, chord length b are that 73.558mm, flow inlet angle α are 49.837 °, established angle B
yBe that 63.154 °, molded lines maximum ga(u)ge T are that 7.560mm, trailing edge thickness δ are 0.447mm.Other compositions and annexation are identical with embodiment one.
Embodiment five: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section D-D of this mode of execution is 53.32mm, and the axial width Q of the pairing blade working part 1 in this position is that 64.094mm, chord length b are that 73.559mm, flow inlet angle α are 44.155 °, established angle B
yBe that 59.481 °, molded lines maximum ga(u)ge T are that 7.013mm, trailing edge thickness δ are 0.419mm.Other compositions and annexation are identical with embodiment one.
Embodiment six: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section E-E of this mode of execution is 68.88mm, and the axial width Q of the pairing blade working part 1 in this position is that 61.681mm, chord length b are that 73.561mm, flow inlet angle α are 45.682 °, established angle B
yBe that 55.933 °, molded lines maximum ga(u)ge T are that 6.504mm, trailing edge thickness δ are 0.385mm.Other compositions and annexation are identical with embodiment one.
Embodiment seven: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section F-F of this mode of execution is 84.44mm, and the axial width Q of the pairing blade working part 1 in this position is that 59.218mm, chord length b are that 73.560mm, flow inlet angle α are 36.620 °, established angle B
yBe that 52.647 °, molded lines maximum ga(u)ge T are that 5.969mm, trailing edge thickness δ are 0.354mm.Other compositions and annexation are identical with embodiment one.
Embodiment eight: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section G-G of this mode of execution is 100.00mm, and the axial width Q of the pairing blade working part 1 in this position is that 56.874mm, chord length b are that 73.565mm, flow inlet angle α are 37.385 °, established angle B
yBe that 49.770 °, molded lines maximum ga(u)ge T are that 5.482mm, trailing edge thickness δ are 0.327mm.Other compositions and annexation are identical with embodiment one.
Embodiment nine: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section H-H of this mode of execution is 115.56mm, and the axial width Q of the pairing blade working part 1 in this position is that 54.340mm, chord length b are that 73.568mm, flow inlet angle α are 38.811 °, established angle B
yBe that 46.850 °, molded lines maximum ga(u)ge T are that 4.936mm, trailing edge thickness δ are 0.293mm.Other compositions and annexation are identical with embodiment one.
Embodiment ten: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section I-I of this mode of execution is 131.12mm, and the axial width Q of the pairing blade working part 1 in this position is that 51.915mm, chord length b are that 73.562mm, flow inlet angle α are 34.090 °, established angle B
yBe that 44.240 °, molded lines maximum ga(u)ge T are that 4.421mm, trailing edge thickness δ are 0.261mm.Other compositions and annexation are identical with embodiment one.
Embodiment 11: combine Fig. 1 and Fig. 4 that this mode of execution is described; The depth of section h of the blade working part 1 cross section J-J of this mode of execution is 146.68mm, and the axial width Q of the pairing blade working part 1 in this position is that 49.406mm, chord length b are that 73.615mm, flow inlet angle α are 33.281 °, established angle B
yBe that 41.609 °, molded lines maximum ga(u)ge T are that 3.929mm, trailing edge thickness δ are 0.235mm.Other compositions and annexation are identical with embodiment one.
Embodiment 12: combine Fig. 1 and Fig. 4 that this mode of execution is described, the blade root 2 of this mode of execution is the flute profile blade root, and the axial width W of blade root 2 is 73mm, and the total height K of blade root 2 is 35.1mm.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 (10)
1. the hub diameter gas compressor time chopped-off head blade that is Φ 762; Said blade comprises blade working part (1) and blade root (2); Blade working part (1) and blade root (2) are processed one from top to bottom, and the molded lines of blade working part (1) is the variable cross section twisted blade, and be different along the blade height sectional shape; Sectional area is reduced by root to top gradually, has relatively between adjacent two sections and reverses; It is characterized in that blade working part (1) is from the geometric data near the cross section at root to top: the depth of section (h) of section A-A J-J to the cross section is 6.64m～146.68mm; Axial width (Q) is 70.029～49.406mm; Chord length (b) is 73.561～73.615mm; Flow inlet angle (α) is 46.727 °～33.281 °, established angle (B
y) be 70.931 °～41.609 °, molded lines maximum ga(u)ge (T) is 8.592～3.929mm, and trailing edge thickness (δ) is 0.510～0.235mm, and the total height (L) of blade working part (1) is 146.18cm.
2. according to the said hub diameter of claim 1 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) section A-A is 6.64mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 70.029mm, chord length (b) are 46.727 °, established angle (B for 73.561mm, flow inlet angle (α)
y) be that 70.931 °, molded lines maximum ga(u)ge (T) are 0.510mm for 8.592mm, trailing edge thickness (δ).
3. be the gas compressor time chopped-off head blade of Φ 762 according to claim 1 or 2 said hub diameters; The depth of section (h) that it is characterized in that blade working part (1) section B-B is 22.20mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 68.330mm, chord length (b) are 50.093 °, established angle (B for 73.559mm, flow inlet angle (α)
y) be that 67.039 °, molded lines maximum ga(u)ge (T) are 0.478mm for 8.064mm, trailing edge thickness (δ).
4. according to the said hub diameter of claim 3 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) cross section C-C is 37.76mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 66.295mm, chord length (b) are 49.837 °, established angle (B for 73.558mm, flow inlet angle (α)
y) be that 63.154 °, molded lines maximum ga(u)ge (T) are 0.447mm for 7.560mm, trailing edge thickness (δ).
5. according to the said hub diameter of claim 4 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) cross section D-D is 53.32mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 64.094mm, chord length (b) are 44.155 °, established angle (B for 73.559mm, flow inlet angle (α)
y) be that 59.481 °, molded lines maximum ga(u)ge (T) are 0.419mm for 7.013mm, trailing edge thickness (δ).
6. according to the said hub diameter of claim 5 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) cross section E-E is 68.88mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 61.681mm, chord length (b) are 45.682 °, established angle (B for 73.561mm, flow inlet angle (α)
y) be that 55.933 °, molded lines maximum ga(u)ge (T) are 0.385mm for 6.504mm, trailing edge thickness (δ).
7. according to the said hub diameter of claim 6 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) cross section F-F is 84.44mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 59.218mm, chord length (b) are 36.620 °, established angle (B for 73.560mm, flow inlet angle (α)
y) be that 52.647 °, molded lines maximum ga(u)ge (T) are 0.354mm for 5.969mm, trailing edge thickness (δ).
8. according to the said hub diameter of claim 7 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) cross section G-G is 100.00mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 56.874mm, chord length (b) are 37.385 °, established angle (B for 73.565mm, flow inlet angle (α)
y) be that 49.770 °, molded lines maximum ga(u)ge (T) are 0.327mm for 5.482mm, trailing edge thickness (δ).
9. according to the said hub diameter of claim 7 the gas compressor time chopped-off head blade of Φ 762; The depth of section (h) that it is characterized in that blade working part (1) cross section J-J is 146.68mm, and the axial width (Q) of the pairing blade working part in this position (1) is that 49.406mm, chord length (b) are 33.281 °, established angle (B for 73.615mm, flow inlet angle (α)
y) be that 41.609 °, molded lines maximum ga(u)ge (T) are 0.235mm for 3.929mm, trailing edge thickness (δ).
10. the gas compressor time chopped-off head blade that is Φ 762 according to the said a kind of hub diameter of claim 9 is characterized in that blade root (2) is the flute profile blade root, and the axial width (W) of blade root (2) is 73mm, and the total height (K) of blade root (2) is 35.1mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120171988XU CN202108784U (en) | 2011-05-26 | 2011-05-26 | Secondary-primary impeller of compressor with phi 762 hub diameter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120171988XU CN202108784U (en) | 2011-05-26 | 2011-05-26 | Secondary-primary impeller of compressor with phi 762 hub diameter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202108784U true CN202108784U (en) | 2012-01-11 |
Family
ID=45434220
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120171988XU Expired - Lifetime CN202108784U (en) | 2011-05-26 | 2011-05-26 | Secondary-primary impeller of compressor with phi 762 hub diameter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202108784U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103557034A (en) * | 2013-09-30 | 2014-02-05 | 哈尔滨汽轮机厂有限责任公司 | Second stage guide vane applicable to turbine of heavy low calorific value fuel machine |
-
2011
- 2011-05-26 CN CN201120171988XU patent/CN202108784U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103557034A (en) * | 2013-09-30 | 2014-02-05 | 哈尔滨汽轮机厂有限责任公司 | Second stage guide vane applicable to turbine of heavy low calorific value fuel machine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202176548U (en) | Intermediate blade of air compressor used for high power gas turbine | |
| CN202176549U (en) | Secondary first-stage blade for air compressor of high power combustion gas turbine | |
| CN202209313U (en) | First-level blade of gas compressor used for high-power gas turbine | |
| CN202091251U (en) | Intermediate blade of compressor with hub with diameter of phi 940 | |
| CN202176550U (en) | Intermediate stage guide vane of compressor for large-power gas turbine | |
| CN202108784U (en) | Secondary-primary impeller of compressor with phi 762 hub diameter | |
| CN203476791U (en) | Low-pressure inlet rotating guide vane of gas compressor for gas turbine | |
| CN202176551U (en) | Inlet rotatable guide vane of compressor for large-power gas turbine | |
| CN202065239U (en) | Interstage blade of air compressor with hub diameter of phi 616 | |
| CN202091249U (en) | Intermediate-stage blade of gas compressor with hub diameter of Phi 564mm | |
| CN202065242U (en) | Intermediate stage blade of air compressor with hub diameter of Phi 762 | |
| CN202065240U (en) | Air compressor first-stage blade with hub diameter of phi 658 | |
| CN202228426U (en) | First-stage guide blade of air compressor for high-power gas turbine | |
| CN202048023U (en) | Primary blade of large-sized high-rotation-speed air compressor | |
| CN203420930U (en) | High-pressure first-stage moving vane of gas compressor for gas turbine | |
| CN103557034B (en) | Second stage guide vane applicable to turbine of heavy low calorific value fuel machine | |
| CN202065243U (en) | Air compressor first-stage blade with hub diameter of phi 616 | |
| CN104235055B (en) | A kind of hydraulic model method for designing of big diameter elbow slurry circulating pump | |
| CN203453114U (en) | High-pressure intermediate-stage guide blade of air compressor for combustion gas turbine | |
| CN203476402U (en) | Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine | |
| CN202091253U (en) | Intermediate blade of gas compressor with hub diameter of [phi] 658 | |
| CN202091254U (en) | Primary blade of gas compressor with hub diameter of [phi] 940 | |
| CN202065241U (en) | First-stage blade of air compressor with hub diameter of phi 762 | |
| CN204060802U (en) | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type | |
| CN203308775U (en) | High-voltage intermediate-stage moving blade of gas compressor for gas turbine |
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: 20120111 |