CN202073835U - First-stage blade of compressor with phi564 hub diameter - Google Patents
First-stage blade of compressor with phi564 hub diameter Download PDFInfo
- Publication number
- CN202073835U CN202073835U CN2011201742354U CN201120174235U CN202073835U CN 202073835 U CN202073835 U CN 202073835U CN 2011201742354 U CN2011201742354 U CN 2011201742354U CN 201120174235 U CN201120174235 U CN 201120174235U CN 202073835 U CN202073835 U CN 202073835U
- Authority
- CN
- China
- Prior art keywords
- blade
- working part
- root
- compressor
- section
- 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
The utility model discloses a first-stage blade of a compressor with a phi564 hub diameter, which relates to a compressor blade and aims to solve the problems that the first-stage blade of the compressor with the phi564 hub diameter has low efficiency and a short service life, and the safe operation of the compressor is influenced. The blade comprises a blade working part and a blade root. The blade working part and the blade root are stamped into a whole from top to bottom; the mold line of the blade working part is a variable cross-section twisted blade; the cross sections are different in shape along the height of the blade; the area of the cross sections is gradually reduced from the root part to the top part; the two adjacent cross sections are relatively twisted; and the geometric data of the cross sections of the blade working part from the root part to the top part are shown as follows: the height of a cross section (A-A) to a cross section (I-I) is 4.555-96.715mm, the axial width is 51.471-37.593mm, the chord length is 54.454-54.455mm, a flow inlet angle is 50.328-31.503 degrees, a setting angle is 69.683-43.005 degrees, the maximum thickness of the mold line is 6.369-3.267mm, the thickness of an air outlet edge is 0.377-0.194mm, and the total height of the blade working part is 98.37cm. The first-stage blade of the compressor with the phi564 hub diameter is used for the compressor with the phi564 hub diameter.
Description
Technical field
The utility model relates to a kind of compressor blade.
Background technique
Hub diameter is that the gas compressor chopped-off head blade design method of Φ 564 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 is that the problem that lack and influence the gas compressor safe operation working life is the gas compressor chopped-off head blade of Φ 564 and a kind of hub diameter is provided for the solution hub diameter is that Φ 564 chopped-off head blade efficiencies are low.
The utility model is to address the above problem the technological scheme of taking to be: the gas compressor chopped-off head blade that a kind of hub diameter of the present utility model is Φ 564 is made up of 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, have relatively between adjacent two sections and reverse, the geometric data in blade working part cross section from root to the top: cross section A-A to the depth of section of cross section I-I be 4.555～96.715mm, axial width is 51.471～37.593mm, chord length is 54.454～54.455mm, flow inlet angle is 50.328 °～31.503 °, established angle is 69.683 °～43.005 °, the molded lines maximum ga(u)ge is 6.369～3.267mm, trailing edge thickness is 0.377～0.194mm, and the total height of blade working part is 98.37cm.
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 that hub diameter is gas compressor energy safe and highly efficient operation under variable working condition of Φ 564, 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 each cross section tomography of blade working part 1 molded lines, and Fig. 5 is that blade working partly shows blade profile parameters W1, b, α, β
y, T, δ schematic representation.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1～Fig. 5, a kind of hub diameter of present embodiment is that the gas compressor chopped-off head blade of Φ 564 is made up of 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, 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: cross section A-A to the depth of section L1 of cross section I-I be 4.555～96.715mm, axial width W1 is 51.471～37.593mm, chord length b is 54.454～54.455mm, flow inlet angle α is 50.328 °～31.503 °, established angle β
yBe 69.683 °～43.005 °, molded lines maximum ga(u)ge T is 6.369～3.267mm, and trailing edge thickness δ is 0.377～0.194mm, and the total height L of blade working part 1 is 98.37cm.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 and Fig. 5, the axial width W1 that the height L1 of the blade working part 1 of present embodiment is respectively the blade working part 1 of 16.07mm, 50.75mm, 83.435mm place correspondence respectively is: 50.140mm, 45.014mm, 39.426mm, pairing chord length b respectively is: 54.454mm, 54.455mm, 54.458mm, pairing flow inlet angle α respectively is: 50.587 °, 40.640 °, 31.608 °, and pairing established angle β
yRespectively be: 65.799 °, 54.700 °, 45.627 °, pairing molded lines maximum ga(u)ge T respectively is: 5.981mm, 4.799mm, 3.651mm, pairing trailing edge thickness δ respectively is: 0.355mm, 0.286mm, 0.217mm.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 present embodiment is described, the blade root 2 of present embodiment is the flute profile blade root, and the axial width W2 of blade root 2 is 54mm, and the total height K of blade root 2 is 30mm.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. gas compressor chopped-off head blade that hub diameter is Φ 564, this blade is made up of 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, 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: cross section A-A to the depth of section (L1) of cross section I-I be 4.555～96.715mm, axial width (W1) is 51.471～37.593mm, chord length (b) is 54.454～54.455mm, flow inlet angle (α) is 50.328 °～31.503 °, established angle (β
y) be 69.683 °～43.005 °, molded lines maximum ga(u)ge (T) is 6.369～3.267mm, and trailing edge thickness (δ) is 0.377～0.194mm, and the total height (L) of blade working part (1) is 98.37cm.
2. the gas compressor chopped-off head blade that is Φ 564 according to the described a kind of hub diameter of claim 1, it is characterized in that: the axial width (W1) that the height (L1) of blade working part (1) is respectively the blade working part (1) of 16.07mm, 50.75mm, 83.435mm place correspondence respectively is: 50.140mm, 45.014mm, 39.426mm, pairing chord length (b) respectively is: 54.454mm, 54.455mm, 54.458mm, pairing flow inlet angle (α) respectively is: 50.587 °, 40.640 °, 31.608 °, and pairing established angle (β
y) respectively be: 65.799 °, 54.700 °, 45.627 °, pairing molded lines maximum ga(u)ge (T) respectively is: 5.981mm, 4.799mm, 3.651mm, pairing trailing edge thickness (δ) respectively is: 0.355mm, 0.286mm, 0217mm.
3. the gas compressor chopped-off head blade that is Φ 564 according to claim 1 or 2 described a kind of hub diameters, it is characterized in that: blade root (2) is the flute profile blade root, and the axial width (W2) of blade root (2) is 54mm, and the total height (K) of blade root (2) is 30mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201742354U CN202073835U (en) | 2011-05-27 | 2011-05-27 | First-stage blade of compressor with phi564 hub diameter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201742354U CN202073835U (en) | 2011-05-27 | 2011-05-27 | First-stage blade of compressor with phi564 hub diameter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202073835U true CN202073835U (en) | 2011-12-14 |
Family
ID=45111939
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201742354U Expired - Lifetime CN202073835U (en) | 2011-05-27 | 2011-05-27 | First-stage blade of compressor with phi564 hub diameter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202073835U (en) |
-
2011
- 2011-05-27 CN CN2011201742354U patent/CN202073835U/en not_active Expired - Lifetime
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202176549U (en) | Secondary first-stage blade for air compressor of high power combustion gas turbine | |
| CN202091251U (en) | Intermediate blade of compressor with hub with diameter of phi 940 | |
| CN202176548U (en) | Intermediate blade of air compressor used for high power gas turbine | |
| CN202209313U (en) | First-level blade of gas compressor used for high-power gas turbine | |
| CN201581936U (en) | Special last-stage vane for large-scale 60Hz turbine | |
| CN102168687B (en) | Compressor first-stage blade with hub diameter of phi 762 | |
| CN102359397B (en) | 1300mm moving blade of final stage for full-rotary-speed steam turbine | |
| CN202176550U (en) | Intermediate stage guide vane of compressor for large-power gas turbine | |
| CN202065242U (en) | Intermediate stage blade of air compressor with hub diameter of Phi 762 | |
| CN202065243U (en) | Air compressor first-stage blade with hub diameter of phi 616 | |
| CN202091249U (en) | Intermediate-stage blade of gas compressor with hub diameter of Phi 564mm | |
| CN203067350U (en) | Chlorine centrifugal compressor impeller | |
| CN202073835U (en) | First-stage blade of compressor with phi564 hub diameter | |
| CN202371174U (en) | Labyrinth seal | |
| CN201103419Y (en) | Second last blade of macrotype supercritical air cooling turbine | |
| CN202048023U (en) | Primary blade of large-sized high-rotation-speed air compressor | |
| CN202250249U (en) | 1300mm final stage moving blade for full rotary speed steam turbine | |
| CN102979582A (en) | 712.5 mm last-stage moving blade used for high power combined-cycle steam turbine | |
| CN204164031U (en) | A kind of impeller of centrifugal air compressor | |
| CN202065241U (en) | First-stage blade of air compressor with hub diameter of phi 762 | |
| CN202091254U (en) | Primary blade of gas compressor with hub diameter of [phi] 940 | |
| CN202091253U (en) | Intermediate blade of gas compressor with hub diameter of [phi] 658 | |
| CN202065239U (en) | Interstage blade of air compressor with hub diameter of phi 616 | |
| CN103362867A (en) | Variable chamfer structure of unshrouded impeller | |
| CN209780968U (en) | 540mm secondary final stage moving blade for full-speed thermal power steam 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: 20111214 |