CN203570363U - Second-stage moving vane suitable for fuel machine turbine with level of 20 WM-30 WM - Google Patents
Second-stage moving vane suitable for fuel machine turbine with level of 20 WM-30 WM Download PDFInfo
- Publication number
- CN203570363U CN203570363U CN201320665598.7U CN201320665598U CN203570363U CN 203570363 U CN203570363 U CN 203570363U CN 201320665598 U CN201320665598 U CN 201320665598U CN 203570363 U CN203570363 U CN 203570363U
- Authority
- CN
- China
- Prior art keywords
- section
- working part
- blade working
- moving vane
- machine turbine
- 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
- 239000000446 fuel Substances 0.000 title abstract 6
- 238000002485 combustion reaction Methods 0.000 claims description 17
- 230000000694 effects Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012932 thermodynamic analysis Methods 0.000 description 1
- 238000003325 tomography Methods 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model relates to a moving vane suitable for a fuel machine turbine with the level of 20 WM-30 WM, in particular to a second-stage moving vane suitable for a fuel machine turbine with the level of 20 WM-30 WM. The problem that a working part of an existing second-stage moving vane of a fuel machine turbine with the level of 20 WM-30 WM is high in profile loss and poor in heat exchanging effect, so that the existing second-stage moving vane of the fuel machine turbine with the level of 20 WM-30 WM is low in air power efficiency and short in service life, and turbine safe operation is affected is solved. The geometric data of sections from the position close to the root portion to the top portion of a working part of the vane are that the section height of a section A-A to a section G-G is 0 mm-110.50 mm, the axial width is 30.100 mm-39.013 mm, the chord length is 40.285 mm-40.985mm, the air inlet angle is 40.400 degrees -43.810 degrees, the mounting angle is 46.959 degrees-72.333 degrees, the molded line maximum thickness is 8.386 mm- 11.469mm, the air outlet side thickness is 0.800 mm, and the total height L of the working part of the vane is 110.56 mm. The second-stage moving vane is used on the fuel machine turbine with the level of 20 WM-30 WM.
Description
Technical field
The utility model relates to a kind of combustion machine turbine moving blade of the 20-30WM of being applicable to grade.
Background technique
In recent years, high efficiency gas turbine (gas turbine) improves gradually combustor exit temperature and makes great efforts to improve the cooling of various turbine components.Working portion (profile loss is large and heat transfer effect is poor) due to the combustion machine turbine second level moving vane of existing 20-30WM grade, makes the combustion machine turbine second level moving vane aerodynamic efficiency of existing 20-30WM grade low, working life is short, affect turbine safe operation.
Model utility content
The purpose of this utility model is to provide a kind of combustion machine turbine second level moving vane of the 20-30WM of being applicable to grade, to solve the working portion (profile loss is large and heat transfer effect is poor) due to the combustion machine turbine second level moving vane of existing 20-30WM grade, make the combustion machine turbine second level moving vane aerodynamic efficiency of existing 20-30WM grade low, working life is short, affect the problem of turbine safe operation.
The utility model is to address the above problem the technological scheme of taking to be: the combustion machine turbine second level moving vane of a kind of 20-30WM of being applicable to grade of the present utility model, described blade comprises blade working part, upper end wall and lower end wall, upper end wall, blade working part and lower end wall are cast as one from top to bottom, the molded line of blade working part is variable cross section twisted blade, different along blade height sectional shape, sectional area is increased gradually by root to top, between adjacent two sections, there is relative torsion, air inlet side is not reversed, and the side of giving vent to anger is reversed; 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 G-G is 0～110.50mm, axial width is 30.100～39.013mm, chord length is 40.285～40.985mm, flow inlet angle is 40.400 °～43.810 °, established angle is 46.959 °～72.333 °, molded line maximum ga(u)ge is 8.386～11.469mm, and trailing edge thickness is 0.800mm, and the total height L of blade working part is 110.50mm.
The utility model compared with prior art has following beneficial effect: moving vane of the present utility model is with one dimension, accurate three-dimensional, full three-dimensional pneumatic, thermodynamic analysis calculates the full three dimensional design of this second level moving vane, calculation accuracy is high, Security and the high efficiency of moving vane of the present utility model are organically combined, guaranteed energy safe and highly efficient operation under variable working condition, improved the aerodynamic efficiency of blade, extended blade working life, according to statistics, the relative prior art of aerodynamic efficiency of blade improves 2% to 5%, the working life of blade, relatively existing blade improved 1.5 to 1.8 times.
Accompanying drawing explanation
Fig. 1 is plan view of the present utility model, Fig. 2 is the left view of Fig. 1, and Fig. 3 is the superimposed schematic diagram of blade working each cross section tomography of part, and Fig. 4 means the schematic diagram of blade profile parameters Q, b, β y, Dmax, Fig. 5 is the local enlarged diagram in I place of Fig. 4, and Fig. 6 is the local enlarged diagram in J place of Fig. 4.
Embodiment
Embodiment one: illustrate in conjunction with Fig. 1 to Fig. 6, a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade of present embodiment, described blade comprises blade working part 1, upper end wall 2 and lower end wall 3, upper end wall 2, blade working part 1 and lower end wall 3 are cast as one by under upper, the molded line of blade working part 1 is variable cross section twisted blade, different along blade height sectional shape, sectional area is increased gradually by root to top, between adjacent two sections, there is relative torsion, air inlet side is not reversed, and the side of giving vent to anger is reversed; 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 G-G be 0～110.50mm, axial width Q is 30.100～39.013mm, chord length b is 40.285～40.985mm, flow inlet angle α is 40.400 °～43.810 °, established angle β y is 46.959 °～72.333 °, molded line maximum ga(u)ge Dmax is 8.386～11.469mm, and trailing edge thickness δ is 0.800mm, and the total height L of blade working part 1 is 110.50mm.
Embodiment two: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of blade working part 1 section A-A of present embodiment is 0.00mm, and the axial width Q of the corresponding blade working part 1 in this position is that 39.013mm, chord length b are that 40.939mm, flow inlet angle α are that 40.400 °, established angle β y are that 72.333 °, molded line maximum ga(u)ge Dmax are that 11.469mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment one.
Embodiment three: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of blade working part 1 section B-B of present embodiment is 16.50mm, and the axial width Q of the corresponding blade working part 1 in this position is that 37.443mm, chord length b are that 40.985mm, flow inlet angle α are that 41.357 °, established angle β y are that 68.801 °, molded line maximum ga(u)ge Dmax are that 10.913mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment one or two.
Embodiment four: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of blade working part 1 section B-B of present embodiment is 16.50mm, and the axial width Q of the corresponding blade working part 1 in this position is that 37.443mm, chord length b are that 40.985mm, flow inlet angle α are that 41.357 °, established angle β y are that 68.801 °, molded line maximum ga(u)ge Dmax are that 10.913mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment three.
Embodiment five: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 cross section D-D of present embodiment is 56.5mm, and the axial width Q of the corresponding blade working part 1 in this position is that 34.060mm, chord length b are that 40.030mm, flow inlet angle α are that 43.783 °, established angle β y are that 60.566 °, molded line maximum ga(u)ge Dmax are that 9.469mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment four.
Embodiment six: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 cross section E-E of present embodiment is 76.5mm, and the axial width Q of the corresponding blade working part 1 in this position is that 32.703mm, chord length b are that 40.390mm, flow inlet angle α are that 43.810 °, established angle β y are that 56.052 °, molded line maximum ga(u)ge Dmax are that 9.007mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment five.
Embodiment seven: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 cross section F-F of present embodiment is 96.50mm, and the axial width Q of the corresponding blade working part 1 in this position is that 30.966mm, chord length b are that 40.285mm, flow inlet angle α are that 42.398 °, established angle β y are that 51.955 °, molded line maximum ga(u)ge Dmax are that 8.517mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment six.
Embodiment eight: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 cross section G-G of present embodiment is 110.50mm, and the axial width Q of the corresponding blade working part 1 in this position is that 30.100mm, chord length b are that 40.288mm, flow inlet angle α are that 43.041 °, established angle β y are that 49.924 °, molded line maximum ga(u)ge Dmax are that 8.386mm, trailing edge thickness δ are 0.800mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment seven.
Claims (8)
1. a combustion machine turbine second level moving vane that is applicable to 20-30WM grade, described blade comprises blade working part (1), upper end wall (2) and lower end wall (3), upper end wall (2), blade working part (1) and lower end wall (3) are cast as one from top to bottom, the molded line of blade working part (1) is variable cross section twisted blade, different along blade height sectional shape, sectional area is increased gradually by root to top, between adjacent two sections, has relative torsion; 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 G-G is 0～110.50mm, axial width (Q) is 30.100～39.013mm, chord length (b) is 40.285～40.985mm, flow inlet angle (α) is 40.400 °～43.810 °, established angle (β y) is 46.959 °～72.333 °, molded line maximum ga(u)ge (Dmax) is 8.386～11.469mm, trailing edge thickness (δ) is 0.800mm, and the total height (L) of blade working part (1) is 110.50mm.
2. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 1, it is characterized in that: the depth of section (h) of blade working part (1) section A-A be 0.00mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 39.013mm, chord length (b) are that 40.939mm, flow inlet angle (α) are that 40.400 °, established angle (β y) are that 72.333 °, molded line maximum ga(u)ge (Dmax) are that 11.469mm, trailing edge thickness (δ) are 0.800mm.
3. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 1 and 2, it is characterized in that: the depth of section (h) of blade working part (1) section B-B be 16.50mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 37.443mm, chord length (b) are that 40.985mm, flow inlet angle (α) are that 41.357 °, established angle (β y) are that 68.801 °, molded line maximum ga(u)ge (Dmax) are that 10.913mm, trailing edge thickness (δ) are 0.800mm.
4. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 3, it is characterized in that: the depth of section (h) of blade working part (1) cross section C-C be 36.50mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 35.761mm, chord length (b) are that 40.439mm, flow inlet angle (α) are that 43.046 °, established angle (β y) are that 64.730 °, molded line maximum ga(u)ge (Dmax) are that 10.178mm, trailing edge thickness (δ) are 0.800mm.
5. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 4, it is characterized in that: the depth of section (h) of blade working part (1) cross section D-D be 56.5mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 34.060mm, chord length (b) are that 40.030mm, flow inlet angle (α) are that 43.783 °, established angle (β y) are that 60.566 °, molded line maximum ga(u)ge (Dmax) are that 9.469mm, trailing edge thickness (δ) are 0.800mm.
6. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 5, it is characterized in that: the depth of section (h) of blade working part (1) cross section E-E be 76.5mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 32.703mm, chord length (b) are that 40.390mm, flow inlet angle (α) are that 43.810 °, established angle (β y) are that 56.052 °, molded line maximum ga(u)ge (Dmax) are that 9.007mm, trailing edge thickness (δ) are 0.800mm.
7. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 6, it is characterized in that: the depth of section (h) of blade working part (1) cross section F-F be 96.50mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 30.966mm, chord length (b) are that 40.285mm, flow inlet angle (α) are that 42.398 °, established angle (β y) are that 51.955 °, molded line maximum ga(u)ge (Dmax) are that 8.517mm, trailing edge thickness (δ) are 0.800mm.
8. a kind of combustion machine turbine second level moving vane that is applicable to 20-30WM grade according to claim 7, it is characterized in that: the depth of section (h) of blade working part (1) cross section G-G be 110.50mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 30.100mm, chord length (b) are that 40.288mm, flow inlet angle (α) are that 43.041 °, established angle (β y) are that 49.924 °, molded line maximum ga(u)ge (Dmax) are that 8.386mm, trailing edge thickness (δ) are 0.800mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320665598.7U CN203570363U (en) | 2013-10-28 | 2013-10-28 | Second-stage moving vane suitable for fuel machine turbine with level of 20 WM-30 WM |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320665598.7U CN203570363U (en) | 2013-10-28 | 2013-10-28 | Second-stage moving vane suitable for fuel machine turbine with level of 20 WM-30 WM |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203570363U true CN203570363U (en) | 2014-04-30 |
Family
ID=50538097
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320665598.7U Expired - Lifetime CN203570363U (en) | 2013-10-28 | 2013-10-28 | Second-stage moving vane suitable for fuel machine turbine with level of 20 WM-30 WM |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203570363U (en) |
-
2013
- 2013-10-28 CN CN201320665598.7U patent/CN203570363U/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 | |
| CN202176548U (en) | Intermediate blade of air compressor used for high power gas turbine | |
| CN110043327A (en) | A kind of discontinuous rib inside cooling structure for turbine blade of gas turbine | |
| CN202176550U (en) | Intermediate stage guide vane of compressor for large-power gas turbine | |
| CN105401982A (en) | Tail-stage movable blade body structure for half-rotating-speed nuclear turbine | |
| CN203570363U (en) | Second-stage moving vane suitable for fuel machine turbine with level of 20 WM-30 WM | |
| CN103557034B (en) | Second stage guide vane applicable to turbine of heavy low calorific value fuel machine | |
| CN203476402U (en) | Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine | |
| CN204060805U (en) | A kind of turbine third level guide vane for lower calorific value combustion engine in heavy type | |
| CN203476791U (en) | Low-pressure inlet rotating guide vane of gas compressor for gas turbine | |
| CN203452854U (en) | First-stage moving blade suitable for 20-30WM grade combustion engine turbine | |
| CN107605667A (en) | A kind of modularization pneumatic equipment bladess part synergy design method | |
| CN103510999B (en) | Turbine secondary moving blade applicable to heavy-duty gas turbine | |
| CN104295324B (en) | A kind of for the turbine third level guide vane of low heat value combustion engine in heavy type | |
| CN103510998B (en) | First-grade moving blade suitable for worm wheel of 20-30WM grade gas turbine | |
| CN205689247U (en) | A kind of novel high-pressure turbine rotor blade air cooling structure | |
| CN204060802U (en) | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type | |
| CN203515682U (en) | Gas turbine second-stage guide vane applicable to 20-30MW class | |
| CN203453114U (en) | High-pressure intermediate-stage guide blade of air compressor for combustion gas turbine | |
| CN203420740U (en) | Low pressure intergrade guide vane of gas turbine used compressor | |
| CN203531975U (en) | First-stage guide blade for 20-30MW-level gas turbine | |
| CN104265375B (en) | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type | |
| CN203394858U (en) | High-pressure inlet guide vane of gas compressor for gas turbine | |
| CN202065239U (en) | Interstage blade of air compressor with hub diameter of phi 616 | |
| 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 |
Granted publication date: 20140430 |
|
| CX01 | Expiry of patent term |