CN202176550U - Intermediate stage guide vane of compressor for large-power gas turbine - Google Patents
Intermediate stage guide vane of compressor for large-power gas turbine Download PDFInfo
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- CN202176550U CN202176550U CN2011203219953U CN201120321995U CN202176550U CN 202176550 U CN202176550 U CN 202176550U CN 2011203219953 U CN2011203219953 U CN 2011203219953U CN 201120321995 U CN201120321995 U CN 201120321995U CN 202176550 U CN202176550 U CN 202176550U
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- 238000004364 calculation method Methods 0.000 description 4
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- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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- 230000002035 prolonged effect Effects 0.000 description 1
- 238000012932 thermodynamic analysis Methods 0.000 description 1
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Abstract
An intermediate stage guide vane of a compressor for a large-power gas turbine is provided. The guide vane of the compressor for the large-power gas turbine is provided to solve the problems of the prior intermediate stage guide vane of the compressor for the large-power gas turbine that the efficiency is low, the service life is short and the safety operation of the compressor is influenced. A vane working part and a vane root are formed integrally from the top to the bottom, a molded line of the vane working part is changed into a variable cross section twisted vane, shapes of cross sections along the vane height are different, the sectional area gradually reduces from the root part to the top part, and relative torsion exists between two neighboring cross sections. Geometrical data of the cross sections from the root part to the top part of the vane working part are listed as follows, the cross section height H1 from a cross section B-B to a cross section P-P is 0 to 274.320mm, the axial width B1 is 64.773 to 49.721mm, the chord length b is 73.053 to 58.622mm, the maximum thickness of the molded line Dmax is 8.215 to 5.926mm, the thickness DE of a part of an air outlet edge, which has a distance of h away from the air outlet edge, is 1.078 to 0.602mm, the h is 0.7mm, and the total height L1 of the vane working part is 244.881mm. The guide vane is used in compressors for large-power gas turbines.
Description
Technical field
The utility model relates to a kind of heavy duty gas turbine and uses the gas compressor guide vane.
Background technique
The gas compressor intergrade guide vane kind that present heavy duty gas turbine is used is single; Design method 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 is to be the problem that intergrade guide vane efficient low, working life lack and influence gas compressor safe operation of solution heavy duty gas turbine with gas compressor, and then the intergrade guide vane of a kind of heavy duty gas turbine with gas compressor is provided.
The utility model is to solve the problems of the technologies described above the technological scheme of taking to be: a kind of heavy duty gas turbine of the utility model is with the intergrade guide vane of gas compressor; It is made up of blade working part and blade root; Blade working part and blade root are processed one from top to bottom, and the molded lines of blade working part 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; Have relatively between adjacent two sections and reverse, blade working part is from the geometric data in the cross section at root to top: the depth of section H1 of section B-B P-P to the cross section is 0～274.320mm, and axial width B1 is 64.773～49.721mm; Chord length b is 73.053～58.622mm; Is 1.078～0.602mm apart from trailing edge 1-1 distance for the trailing edge thickness DE at h place, h=0.7mm wherein, and blade working total height L1 partly is 244.881mm; The bend angles alpha at section B-B place is 28.013 °, and molded lines maximum ga(u)ge Dmax is 8.215mm; The bend angles alpha at C-C place, cross section is 27.009 °, and molded lines maximum ga(u)ge Dmax is 7.867mm; The bend angles alpha at D-D place, cross section is 26.324 °, and molded lines maximum ga(u)ge Dmax is 7.561mm; The bend angles alpha at E-E place, cross section is 26.345 °, and molded lines maximum ga(u)ge Dmax is 7.647mm; The bend angles alpha at F-F place, cross section is 26.734 °, and molded lines maximum ga(u)ge Dmax is 7.872mm; The bend angles alpha at G-G place, cross section is 27.244 °, and molded lines maximum ga(u)ge Dmax is 7.617mm; The bend angles alpha at H-H place, cross section is 27.838 °, and molded lines maximum ga(u)ge Dmax is 7.209mm; The bend angles alpha at J-J place, cross section is 28.496 °, and molded lines maximum ga(u)ge Dmax is 7.063mm; The bend angles alpha at K-K place, cross section is 29.295 °, and molded lines maximum ga(u)ge Dmax is 7.628mm; The bend angles alpha at L-L place, cross section is 30.023 °, and molded lines maximum ga(u)ge Dmax is 7.759mm; The bend angles alpha at M-M place, cross section is 30.799 °, and molded lines maximum ga(u)ge Dmax is 6.940mm; The bend angles alpha at N-N place, cross section is 31.193 °, and molded lines maximum ga(u)ge Dmax is 6.630mm; The bend angles alpha at P-P place, cross section is 32.419 °, and molded lines maximum ga(u)ge Dmax is 5.926mm.
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 guide vane; Calculation accuracy is high, makes Security of the utility model and high efficiency organically combine, and has guaranteed ability safe and highly efficient operation under variable working condition; Increased the stability of blade; Improve blade efficiency, prolonged blade working life, guaranteed the gas compressor safe operation.
Description of drawings
Fig. 1 is the plan view of the utility model; Fig. 2 is the left view of Fig. 1, and Fig. 3 is the plan view of Fig. 1, and Fig. 4 is the superimposed schematic representation of each cross section tomography of blade working part 1 molded lines; Fig. 5 is blade profile parameters B1, b, the α of blade working part 1, the schematic representation of Dmax, and Fig. 6 is the I portion enlarged view of Fig. 5.
Embodiment
Embodiment one: combine Fig. 1～Fig. 6 that this mode of execution is described; A kind of heavy duty gas turbine of this mode of execution is with the intergrade guide vane of gas compressor, and it is made up of blade working part 1 and blade root 2, and blade working part 1 is processed one from top to bottom with blade root 2; The molded lines of blade working part 1 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; Blade working part 1 is from the geometric data in the cross section at root to top: the depth of section H1 of section B-B P-P to the cross section is 0～274.320mm; Axial width B1 is 64.773～49.721mm, and chord length b is 73.053～58.622mm, is 1.078～0.602mm apart from trailing edge 1-1 apart from the trailing edge thickness DE for the h place; H=0.7mm wherein, the total height L1 of blade working part 1 is 244.881mm; The bend angles alpha at section B-B place is 28.013 °, and molded lines maximum ga(u)ge Dmax is 8.215mm; The bend angles alpha at C-C place, cross section is 27.009 °, and molded lines maximum ga(u)ge Dmax is 7.867mm; The bend angles alpha at D-D place, cross section is 26.324 °, and molded lines maximum ga(u)ge Dmax is 7.561mm; The bend angles alpha at E-E place, cross section is 26.345 °, and molded lines maximum ga(u)ge Dmax is 7.647mm; The bend angles alpha at F-F place, cross section is 26.734 °, and molded lines maximum ga(u)ge Dmax is 7.872mm; The bend angles alpha at G-G place, cross section is 27.244 °, and molded lines maximum ga(u)ge Dmax is 7.617mm; The bend angles alpha at H-H place, cross section is 27.838 °, and molded lines maximum ga(u)ge Dmax is 7.209mm; The bend angles alpha at J-J place, cross section is 28.496 °, and molded lines maximum ga(u)ge Dmax is 7.063mm; The bend angles alpha at K-K place, cross section is 29.295 °, and molded lines maximum ga(u)ge Dmax is 7.628mm; The bend angles alpha at L-L place, cross section is 30.023 °, and molded lines maximum ga(u)ge Dmax is 7.759mm; The bend angles alpha at M-M place, cross section is 30.799 °, and molded lines maximum ga(u)ge Dmax is 6.940mm; The bend angles alpha at N-N place, cross section is 31.193 °, and molded lines maximum ga(u)ge Dmax is 6.630mm; The bend angles alpha at P-P place, cross section is 32.419 °, and molded lines maximum ga(u)ge Dmax is 5.926mm.
The guide vane structural design of this mode of execution can guarantee the best stress of rotor, and avoids peak stress occurring at root and supporting plane.
Embodiment two: combine Fig. 1, Fig. 4, Fig. 5 and Fig. 6 that this mode of execution is described; The depth of section H1 of the blade working part 1 of this mode of execution is respectively: the axial width B1 of the blade working part 1 of 67.056mm, 140.208mm, 213.36mm, 247.371mm place correspondence respectively is: 62.469mm, 58.296mm, 53.841mm, 51.595mm; Pairing chord length b respectively is: 69.424mm, 65.633mm, 61.804mm, 60.004mm; Pairing bend angles alpha respectively is: 26.345 °, 27.838 °, 30.023 °, 31.193 °; Molded lines maximum ga(u)ge Dmax respectively is 7.647mm, 7.209mm, 7.759mm, 6.63mm, and the trailing edge thickness DE for the h place respectively is apart from trailing edge 1-1 distance: 0.972mm, 0.84mm, 0.715mm, 0.648mm.Adopt the said structure parameter, when the contour structure size that guarantees blade meets design requirement, blade is assembled easily.Other is identical with embodiment one.
Embodiment three: combine Fig. 1 and Fig. 3 that this mode of execution is described, the width W of the blade root 2 of this mode of execution is 73.152mm, and the total height K1 of blade root 2 is 21.793mm.This structure makes the blade ability easy for installation, safe and reliable.Other is identical with embodiment one or two.
The blade root 2 of this mode of execution is the rectangle blade root, directly inserts in the circumferential groove of cylinder.
Concrete parameter in each cross section such as following table:
Claims (3)
1. a heavy duty gas turbine is with the intergrade guide vane of gas compressor, and it is made up of blade working part (1) and blade root (2), and blade working partly (1) and blade root (2) is processed one from top to bottom; The molded lines of blade working part (1) 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: blade working part (1) is from the geometric data in the cross section at root to top: the depth of section (H1) of section B-B P-P to the cross section is 0～274.320mm; Axial width (B1) is 64.773～49.721mm, and chord length (b) is 73.053～58.622mm, is 1.078～0.602mm apart from trailing edge (1-1) apart from the trailing edge thickness (DE) for the h place; H=0.7mm wherein, the total height (L1) of blade working part (1) is 244.881mm; The bending angle at section B-B place (α) is 28.013 °, and molded lines maximum ga(u)ge (Dmax) is 8.215mm; The bending angle (α) at C-C place, cross section is 27.009 °, and molded lines maximum ga(u)ge (Dmax) is 7.867mm; The bending angle (α) at D-D place, cross section is 26.324 °, and molded lines maximum ga(u)ge (Dmax) is 7.561mm; The bending angle (α) at E-E place, cross section is 26.345 °, and molded lines maximum ga(u)ge (Dmax) is 7.647mm; The bending angle (α) at F-F place, cross section is 26.734 °, and molded lines maximum ga(u)ge (Dmax) is 7.872mm; The bending angle (α) at G-G place, cross section is 27.244 °, and molded lines maximum ga(u)ge (Dmax) is 7.617mm; The bending angle (α) at H-H place, cross section is 27.838 °, and molded lines maximum ga(u)ge (Dmax) is 7.209mm; The bending angle (α) at J-J place, cross section is 28.496 °, and molded lines maximum ga(u)ge (Dmax) is 7.063mm; The bending angle (α) at K-K place, cross section is 29.295 °, and molded lines maximum ga(u)ge (Dmax) is 7.628mm; The bending angle (α) at L-L place, cross section is 30.023 °, and molded lines maximum ga(u)ge (Dmax) is 7.759mm; The bending angle (α) at M-M place, cross section is 30.799 °, and molded lines maximum ga(u)ge (Dmax) is 6.940mm; The bending angle (α) at N-N place, cross section is 31.193 °, and molded lines maximum ga(u)ge (Dmax) is 6.630mm; The bending angle (α) at P-P place, cross section is 32.419 °, and molded lines maximum ga(u)ge (Dmax) is 5.926mm.
2. according to the intergrade guide vane of the said a kind of heavy duty gas turbine of claim 1 with gas compressor; It is characterized in that: the depth of section (H1) of blade working part (1) is respectively: the axial width (B1) of the blade working part (1) of 67.056mm, 140.208mm, 213.36mm, 247.371mm place correspondence respectively is: 62.469mm, 58.296mm, 53.841mm, 51.595mm; Pairing chord length (b) respectively is: 69.424mm, 65.633mm, 61.804mm, 60.004mm; Pairing bending angle (α) respectively is: 26.345 °, 27.838 °, 30.023 °, 31.193 °; Molded lines maximum ga(u)ge (Dmax) respectively is 7.647mm, 7.209mm, 7.759mm, 6.63mm, and the trailing edge thickness DE for the h place respectively is apart from trailing edge (1-1) distance: 0.972mm, 0.84mm, 0.715mm, 0.648mm.
According to claim 1 or 2 said a kind of heavy duty gas turbines with the intergrade guide vane of gas compressor, it is characterized in that: the width (W) of blade root (2) is 73.152mm, and the total height (K1) of blade root (2) is 21.793mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203219953U CN202176550U (en) | 2011-08-30 | 2011-08-30 | Intermediate stage guide vane of compressor for large-power gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203219953U CN202176550U (en) | 2011-08-30 | 2011-08-30 | Intermediate stage guide vane of compressor for large-power gas turbine |
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| CN202176550U true CN202176550U (en) | 2012-03-28 |
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| CN2011203219953U Expired - Lifetime CN202176550U (en) | 2011-08-30 | 2011-08-30 | Intermediate stage guide vane of compressor for large-power gas turbine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103206409A (en) * | 2013-04-16 | 2013-07-17 | 哈尔滨汽轮机厂有限责任公司 | First-stage moving blades of transonic compressors for high-speed gas turbines |
| 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 |
| CN103423193A (en) * | 2013-04-18 | 2013-12-04 | 哈尔滨汽轮机厂有限责任公司 | A sub-first-stage blade for a transonic compressor on a high-speed gas turbine |
| CN103470310A (en) * | 2013-08-30 | 2013-12-25 | 哈尔滨汽轮机厂有限责任公司 | Low-pressure intermediate-stage guide blade of gas compressor for gas turbine |
| CN103511344A (en) * | 2013-09-23 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | High-pressure intermediate-stage guide blade of gas compressor for combustion gas turbine |
| CN113260793A (en) * | 2019-01-14 | 2021-08-13 | 赛峰飞机发动机公司 | Aerodynamic arm for an aircraft turbine engine casing |
-
2011
- 2011-08-30 CN CN2011203219953U patent/CN202176550U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103206409A (en) * | 2013-04-16 | 2013-07-17 | 哈尔滨汽轮机厂有限责任公司 | First-stage moving blades of transonic compressors for high-speed gas turbines |
| CN103423193A (en) * | 2013-04-18 | 2013-12-04 | 哈尔滨汽轮机厂有限责任公司 | A sub-first-stage blade for a transonic compressor on a high-speed gas turbine |
| 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 |
| CN103470310A (en) * | 2013-08-30 | 2013-12-25 | 哈尔滨汽轮机厂有限责任公司 | Low-pressure intermediate-stage guide blade of gas compressor for gas turbine |
| CN103511344A (en) * | 2013-09-23 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | High-pressure intermediate-stage guide blade of gas compressor for combustion gas turbine |
| CN113260793A (en) * | 2019-01-14 | 2021-08-13 | 赛峰飞机发动机公司 | Aerodynamic arm for an aircraft turbine engine casing |
| EP3911860A1 (en) * | 2019-01-14 | 2021-11-24 | Safran Aircraft Engines | Aerodynamic arm for an aircraft turbine engine casing |
| CN113260793B (en) * | 2019-01-14 | 2024-01-16 | 赛峰飞机发动机公司 | Aerodynamic arm for aircraft turbine engine casing |
| US12180856B2 (en) | 2019-01-14 | 2024-12-31 | Safran Aircraft Engines | Aerodynamic arm for an aircraft turbine engine casing |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120328 |
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| CX01 | Expiry of patent term |