CN103470534A - High-pressure inlet guide blade of gas compressor for gas turbine - Google Patents
High-pressure inlet guide blade of gas compressor for gas turbine Download PDFInfo
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- CN103470534A CN103470534A CN2013103728196A CN201310372819A CN103470534A CN 103470534 A CN103470534 A CN 103470534A CN 2013103728196 A CN2013103728196 A CN 2013103728196A CN 201310372819 A CN201310372819 A CN 201310372819A CN 103470534 A CN103470534 A CN 103470534A
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Abstract
The invention discloses a high-pressure inlet guide blade of a gas compressor for a gas turbine, and relates to a high-pressure inlet guide blade. A blade root and a blade working portion of the high-pressure inlet guide blade are integrally manufactured from top to bottom, the blade working portion comprises a variable-section twisted blade, the shapes of sections of the blade working portion are different from one another along the height direction of the blade, the sectional area of the blade working portion is gradually reduced from the root to the top of the blade working portion, and relative torsion can be generated between each two adjacent sections; geometric data of the sections of the blade working portion from the root to the top of the blade working portion include that heights of the sections with section numbers from A-A to I-I range from 5.500mm to 81.500mm, chord lengths b of the sections with the section numbers from A-A to I-I range from 50.022mm to 50.036mm, mounting angles beta of the sections with the section numbers from A-A to I-I range from 73.609 degrees to 69.187 degrees, the maximum line thicknesses delta of the sections with the section numbers from A-A to I-I range from 4.499mm to 2.820mm, thicknesses C of gas outlet sides separated from corresponding gas outlet sides by distances L1 of 1mm range from 0.621mm to 0.506mm, and the total height L0 of the blade working portion is 72.800mm. The high-pressure inlet guide blade has the advantage that problems that an existing high-pressure inlet guide blade of a gas compressor for a gas turbine is low in work efficiency and short in service life and the safety running of the gas compressor is affected can be solved. The high-pressure inlet guide blade is applied to the gas compressor for the gas turbine.
Description
Technical field
The present invention relates to a kind of turbine chopped-off head stator, be specifically related to the high-pressure inlet guide vane of a kind of gas turbine with gas compressor.
Background technique
The gas compressor high-pressure inlet guide vane kind that gas turbine is used at present is single, design method is original, calculation accuracy is lower, can't carry out accurate Pneumatic Calculation and Flow Field Calculation, thereby make blade profile design not fairing, inefficiency, working life is short, has had a strong impact on Economy and the Security of gas compressor.
Summary of the invention
The objective of the invention is in order to solve gas compressor high-pressure inlet guide vane inefficiency that existing gas turbine uses, working life is short and affect the problem of gas compressor safe operation, and then provides the high-pressure inlet guide vane of a kind of gas turbine with gas compressor.
Technological scheme of the present invention is: a kind of gas turbine comprises blade working part and blade root with the high-pressure inlet guide vane of gas compressor, blade root and blade working part are made one from top to bottom successively, described blade working is partly the variable cross section twisted blade, and the height sectional shape difference of blade working part, the cross-section area of blade working part is reduced gradually by root to top, there is relative torsion between adjacent two sections, the total height of blade working part is 72.800mm, root to the top of blade working part is divided into A-A, B-B, C-C, D-D, E-E, F-F, G-G, nine cross sections of H-H and I-I, section A-A to the depth of section of cross section I-I is 5.500～81.500mm, chord length is 50.022～50.036mm, established angle is 73.609 °～69.187 °, the molded line maximum ga(u)ge is 4.499～2.820mm, the trailing edge thickness that is the 1mm place apart from the trailing edge distance is 0.621～0.506mm,
The depth of section of the section A-A of blade working part is 5.500mm, and the chord length of the corresponding blade working part in this position is that 50.022mm, established angle are that 73.609 °, molded line maximum ga(u)ge are 4.499mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.621mm;
The depth of section of the section B-B of blade working part is 13.500mm, and the chord length of the corresponding blade working part in this position is that 50.023mm, established angle are that 73.165 °, molded line maximum ga(u)ge are 4.324mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.606mm;
The depth of section of the cross section C-C of blade working part is 23.500mm, and the chord length of the corresponding blade working part in this position is that 50.026mm, established angle are that 72.628 °, molded line maximum ga(u)ge are 4.103mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.589mm;
The depth of section of the cross section D-D of blade working part is 33.500mm, and the chord length of the corresponding blade working part in this position is that 50.027mm, established angle are that 72.054 °, molded line maximum ga(u)ge are 3.879mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.573mm;
The depth of section of the cross section E-E of blade working part is 43.500mm, and the chord length of the corresponding blade working part in this position is that 50.028mm, established angle are that 71.489 °, molded line maximum ga(u)ge are 3.659mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.558mm;
The depth of section of the cross section F-F of blade working part is 53.500mm, and the chord length of the corresponding blade working part in this position is that 50.030mm, established angle are that 70.899 °, molded line maximum ga(u)ge are 3.439mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.543mm;
The depth of section of the cross section G-G of blade working part is 63.500mm, and the chord length of the corresponding blade working part in this position is that 50.032mm, established angle are that 70.330 °, molded line maximum ga(u)ge are 3.214mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.528mm;
The depth of section of the cross section H-H of blade working part is 73.500mm, and the chord length of the corresponding blade working part in this position is that 50.035mm, established angle are that 69.709 °, molded line maximum ga(u)ge are 2.994mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.512mm;
The depth of section of the cross section I-I of blade working part is 81.500mm, and the chord length of the corresponding blade working part in this position is that 50.036mm, established angle are that 69.187 °, molded line maximum ga(u)ge are 2.820mm, apart from the trailing edge distance, being the 1mm place, trailing edge thickness is 0.506mm.
The present invention compared with prior art has following effect:
1. the present invention is calculating the full three dimensional design of this high-pressure inlet guide vane with three-dimensional/full three-dimensional pneumatic of one dimension/standard, thermodynamic analysis, calculation accuracy is high, make high-pressure inlet guide vane of the present invention Security and high efficiency organically combine, guaranteed energy safe and highly efficient operation under the variable working condition of high-pressure inlet guide vane, increased the stability of blade, improved blade working efficiency, blade working efficiency is compared existing blade working efficiency and has been improved 3 percentage points; Blade of the present invention has extended working life.
2. compare the working life of blade of the present invention and extended 40%～60% existing working life.
The accompanying drawing explanation
Fig. 1 is plan view of the present invention, Fig. 2 is the left view of Fig. 1, Fig. 3 is that (in figure, X represents blade working part two-dimensional coordinate X-axis for the plan view of Fig. 1, Y represents blade working part two-dimensional coordinate Y-axis), Fig. 4 is the superimposed schematic diagram of vane type line part 1 each cross section tomography, Fig. 5 is the schematic diagram of blade working partial display blade profile parameters b, β, D1, L1, δ, and Fig. 6 is the enlarged view of Fig. 5 at the I place.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1-Fig. 6, a kind of gas turbine of present embodiment comprises blade working part 1 and blade root 2 with the high-pressure inlet guide vane of gas compressor, blade root 2 and blade working part 1 are made one from top to bottom successively, described blade working part 1 is the variable cross section twisted blade, and the height sectional shape difference of blade working part 1, the cross-section area of blade working part 1 is reduced gradually by root to top, there is relative torsion between adjacent two sections, the total height L0 of blade working part 1 is 72.800mm, the root of blade working part 1 to top is divided into A-A, B-B, C-C, D-D, E-E, F-F, G-G, nine cross sections of H-H and I-I, section A-A to the depth of section h of cross section I-I be 5.500～81.500mm, chord length b is 50.022～50.036mm, established angle β is 73.609 °～69.187 °, molded line maximum ga(u)ge δ is 4.499～2.820mm, the trailing edge thickness D1 that is the 1mm place apart from trailing edge distance L 1 is 0.621～0.506mm,
The depth of section h of the section A-A of blade working part 1 is 5.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.022mm, established angle β are that 73.609 °, molded line maximum ga(u)ge δ are 4.499mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.621mm;
The depth of section h of the section B-B of blade working part 1 is 13.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.023mm, established angle β are that 73.165 °, molded line maximum ga(u)ge δ are 4.324mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.606mm;
The depth of section h of the cross section C-C of blade working part 1 is 23.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.026mm, established angle β are that 72.628 °, molded line maximum ga(u)ge δ are 4.103mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.589mm;
The depth of section h of the cross section D-D of blade working part 1 is 33.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.027mm, established angle β are that 72.054 °, molded line maximum ga(u)ge δ are 3.879mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.573mm;
The depth of section h of the cross section E-E of blade working part 1 is 43.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.028mm, established angle β are that 71.489 °, molded line maximum ga(u)ge δ are 3.659mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.558mm;
The depth of section h of the cross section F-F of blade working part 1 is 53.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.030mm, established angle β are that 70.899 °, molded line maximum ga(u)ge δ are 3.439mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.543mm;
The depth of section h of the cross section G-G of blade working part 1 is 63.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.032mm, established angle β are that 70.330 °, molded line maximum ga(u)ge δ are 3.214mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.528mm;
The depth of section h of the cross section H-H of blade working part 1 is 73.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.035mm, established angle β are that 69.709 °, molded line maximum ga(u)ge δ are 2.994mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.512mm;
The depth of section h of the cross section I-I of blade working part 1 is 81.500mm, and the chord length b of the corresponding blade working part 1 in this position is that 50.036mm, established angle β are that 69.187 °, molded line maximum ga(u)ge δ are 2.820mm, apart from trailing edge distance L 1, being the 1mm place, trailing edge thickness D1 is 0.506mm.
In Fig. 3 of present embodiment, J means the caput symmetry plane, and the N in Fig. 5 means the cross section barycenter.
Embodiment two: in conjunction with Fig. 1 and Fig. 2, present embodiment is described, the blade root 2 of present embodiment is the dove-tail form blade root.So arrange, when the contour structure size that guarantees blade meets design requirement, also can make blade easily assemble.Other composition and annexation are identical with embodiment one.
Embodiment three: in conjunction with Fig. 1 and Fig. 3, present embodiment is described, the width W of the blade root 2 of present embodiment is 58.000mm.So arrange, this structure makes the blade wheel rim of packing into securely, is convenient to axially pack into race, and such size loaded area is large, safe and reliable.Other composition and annexation are identical with embodiment two.
Embodiment four: in conjunction with Fig. 1 and Fig. 2, present embodiment is described, the height k of the blade root 2 of present embodiment is 5.7000mm.So arrange, this structure makes the blade wheel rim of packing into securely, is convenient to axially pack into race, and such size loaded area is large, safe and reliable.Other composition and annexation are identical with embodiment two.
Although the present invention discloses as above with preferred embodiment; yet not of the present invention in order to limit; those skilled in the art can also do other variations in spirit of the present invention; and be applied in the NM field of the present invention; certainly, these variations of doing according to spirit of the present invention all should be included in the present invention's scope required for protection.
Claims (4)
1. the high-pressure inlet guide vane of gas compressor for a gas turbine, it comprises blade working part (1) and blade root (2), blade root (2) and blade working part (1) are made one from top to bottom successively, it is characterized in that: described blade working part (1) is the variable cross section twisted blade, and the height sectional shape difference of blade working part (1), the cross-section area of blade working part (1) is reduced gradually by root to top, there is relative torsion between adjacent two sections, the total height (L0) of blade working part (1) is 72.800mm, root to the top of blade working part (1) is divided into A-A, B-B, C-C, D-D, E-E, F-F, G-G, nine cross sections of H-H and I-I, section A-A to the depth of section (h) of cross section I-I is 5.500～81.500mm, chord length (b) is 50.022～50.036mm, established angle (β) is 73.609 °～69.187 °, molded line maximum ga(u)ge (δ) is 4.499～2.820mm, the trailing edge thickness (D1) that is the 1mm place apart from trailing edge distance (L1) is 0.621～0.506mm,
The depth of section (h) of the section A-A of blade working part (1) be 5.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.022mm, established angle (β) are that 73.609 °, molded line maximum ga(u)ge (δ) are 4.499mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.621mm;
The depth of section (h) of the section B-B of blade working part (1) be 13.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.023mm, established angle (β) are that 73.165 °, molded line maximum ga(u)ge (δ) are 4.324mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.606mm;
The depth of section (h) of the cross section C-C of blade working part (1) be 23.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.026mm, established angle (β) are that 72.628 °, molded line maximum ga(u)ge (δ) are 4.103mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.589mm;
The depth of section (h) of the cross section D-D of blade working part (1) be 33.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.027mm, established angle (β) are that 72.054 °, molded line maximum ga(u)ge (δ) are 3.879mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.573mm;
The depth of section (h) of the cross section E-E of blade working part (1) be 43.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.028mm, established angle (β) are that 71.489 °, molded line maximum ga(u)ge (δ) are 3.659mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.558mm;
The depth of section (h) of the cross section F-F of blade working part (1) be 53.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.030mm, established angle (β) are that 70.899 °, molded line maximum ga(u)ge (δ) are 3.439mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.543mm;
The depth of section (h) of the cross section G-G of blade working part (1) be 63.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.032mm, established angle (β) are that 70.330 °, molded line maximum ga(u)ge (δ) are 3.214mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.528mm;
The depth of section (h) of the cross section H-H of blade working part (1) be 73.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.035mm, established angle (β) are that 69.709 °, molded line maximum ga(u)ge (δ) are 2.994mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.512mm;
The depth of section (h) of the cross section I-I of blade working part (1) be 81.500mm, and the chord length (b) of the corresponding blade working part in this position (1) be that 50.036mm, established angle (β) are that 69.187 °, molded line maximum ga(u)ge (δ) are 2.820mm, apart from trailing edge, apart from (L1), being the 1mm place, trailing edge thickness (D1) is 0.506mm.
2. the high-pressure inlet guide vane of gas compressor for a kind of gas turbine according to claim 1, it is characterized in that: blade root (2) is the dove-tail form blade root.
3. the high-pressure inlet guide vane of gas compressor for a kind of gas turbine according to claim 2, it is characterized in that: the width (W) of blade root (2) is 58.000mm.
4. the high-pressure inlet guide vane of gas compressor for a kind of gas turbine according to claim 3, it is characterized in that: the height (k) of blade root (2) is 5.700mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103728196A CN103470534A (en) | 2013-08-23 | 2013-08-23 | High-pressure inlet guide blade of gas compressor for gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2013103728196A CN103470534A (en) | 2013-08-23 | 2013-08-23 | High-pressure inlet guide blade of gas compressor for gas turbine |
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| CN103470534A true CN103470534A (en) | 2013-12-25 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108425884A (en) * | 2017-02-14 | 2018-08-21 | 劳斯莱斯有限公司 | Gas-turbine unit fan blade |
| CN108425883A (en) * | 2017-02-14 | 2018-08-21 | 劳斯莱斯有限公司 | Gas-turbine unit fan blade |
| CN112983891A (en) * | 2021-03-24 | 2021-06-18 | 杭州汽轮动力集团有限公司 | Adjustable inlet guide vane of gas compressor of gas turbine |
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- 2013-08-23 CN CN2013103728196A patent/CN103470534A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108425884A (en) * | 2017-02-14 | 2018-08-21 | 劳斯莱斯有限公司 | Gas-turbine unit fan blade |
| CN108425883A (en) * | 2017-02-14 | 2018-08-21 | 劳斯莱斯有限公司 | Gas-turbine unit fan blade |
| CN108425884B (en) * | 2017-02-14 | 2020-12-29 | 劳斯莱斯有限公司 | Gas Turbine Engine Fan Blades |
| CN108425883B (en) * | 2017-02-14 | 2020-12-29 | 劳斯莱斯有限公司 | Gas turbine engine fan blade |
| CN112983891A (en) * | 2021-03-24 | 2021-06-18 | 杭州汽轮动力集团有限公司 | Adjustable inlet guide vane of gas compressor of gas turbine |
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Application publication date: 20131225 |