CN106122107A - Complex bend stator blade for multi stage axial flow compressor - Google Patents
Complex bend stator blade for multi stage axial flow compressor Download PDFInfo
- Publication number
- CN106122107A CN106122107A CN201610802569.9A CN201610802569A CN106122107A CN 106122107 A CN106122107 A CN 106122107A CN 201610802569 A CN201610802569 A CN 201610802569A CN 106122107 A CN106122107 A CN 106122107A
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- stator blade
- blade
- leaf
- axial flow
- tip
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to gas turbine technology field, particularly relate to a kind of complex bend stator blade for multi stage axial flow compressor, including stator blade main body, stator blade main body includes blade root, leaf central part and leaf tip, leaf central part is between blade root and leaf tip, the center of gravity of leaf central part amasss folded axis radially extending along multi stage axial flow compressor main shaft, and blade root is the most curved to suction surface, and leaf tip is to pressure face recurvation.Employing blade root is the most curved, the form of leaf tip recurvation, when being applied to multi stage axial flow compressor, stator blade root flow separation, balance stator blade exhibition can be significantly improved to power load distributing, raising stator blade stall margin, minimizing stationary blade loss, and the stable operation range across sound movable vane tip can be extended, thus reduce flow losses in whole exhibition to scope, extend the stall margin across sound level.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of complex bend for multi stage axial flow compressor quiet
Leaf.
Background technology
Existing gas turbine blower commonly used three dimendional blade designing technique, i.e. by changing the long-pending folded axle of the center of gravity of blade
Line or each cross section realize the geometric formats such as blade is curved, plunder relative to blade profile feature, thus effectively control the strong three-dimensional within compressor
Flowing, reduces flow losses, delays flow separation, improves compressor efficiency and stall margin.But due to compressor interior three-dimensional
The complexity of Viscous Flow, flexural tensile elastic modulus obtains the explanation determined the most not yet to the Influencing Mechanism of flowing.
The zigzag grain boundary used in gas turbine blower at present all uses blade root and the most curved geometric format of blade tip, i.e.
After bending, suction surface is concave surface, thus produces " C " type pressure distribution that in blade root and blade tip static pressure height, leaf, static pressure is low so that two
Mental retardation air-flow region radial migration in leaf of end, improves the corner region flow of petiolarea.But, blade root and blade tip is the most curved can deteriorate
Flowing in leaf so that in leaf, area loss increases, and the most curved angle of attack also resulting in blade root and blade tip increases, and is unfavorable for this
The stall margin in region.The form of recurvation is that after bending, pressure face is concave surface, and recurvation can be played and the most curved opposite effect, can
Order about mental retardation air-flow from leaf, flow to two ends, thus improve the flowing in region in leaf, simultaneously by reducing the negative of blade root and blade tip
Lotus reduces upstream movable vane outlet back-pressure, reduces upstream movable vane load.But owing to using zigzag grain boundary at present primarily to control
Corner region flow processed separates, and therefore recurvation is not applied in gas turbine blower.
Summary of the invention
The technical problem to be solved in the present invention is to provide one can balance stator blade exhibition to power load distributing, raising stator blade stall
Nargin, the complex bend stator blade for multi stage axial flow compressor of minimizing stationary blade loss, to overcome the drawbacks described above of prior art.
In order to solve above-mentioned technical problem, the present invention adopts the following technical scheme that a kind of for multi stage axial flow compressor
Complex bend stator blade, including stator blade main body, stator blade main body includes blade root, leaf central part and leaf tip, and leaf central part is positioned at blade root
And between leaf tip, the center of gravity of leaf central part amasss folded axis radially extending along multi stage axial flow compressor main shaft, and blade root is to suction
Face is the most curved, and leaf tip is to pressure face recurvation.
Preferably, the height of blade root is the 15%-25% of stator blade body height.
Preferably, the height of leaf tip is the 15%-25% of stator blade body height.
Preferably, the angle between pressure face and the hub outside surface at blade root is 10 °-30 °.
Preferably, the angle between suction surface and the cylinder surfaces at leaf tip is 5 °-20 °.
Preferably, all seamlessly transit between blade root, leaf central part and leaf tip.
Preferably, the transitional region between blade root, leaf central part and leaf tip all uses fairing processing.
Compared with prior art, the present invention has the most progressive: employing blade root is the most curved, the form of leaf tip recurvation,
When being applied to multi stage axial flow compressor, it is possible to significantly improve stator blade root flow separation, balance stator blade is opened up to power load distributing, raising
Stator blade stall margin, reduce stationary blade loss, and the stable operation range across sound movable vane tip can be extended, thus whole exhibition to
Scope reduces flow losses, extends the stall margin across sound level.
Accompanying drawing explanation
Fig. 1 is the perspective view of the complex bend stator blade for multi stage axial flow compressor of the embodiment of the present invention.
Fig. 2 is the long-pending folded axis signal of center of gravity of the complex bend stator blade for multi stage axial flow compressor of the embodiment of the present invention
Figure.
In figure:
100, stator blade main body
101, the long-pending folded axis of center of gravity of blade root 101a, blade root
102, the long-pending folded axis of center of gravity of leaf central part 102a, leaf central part
103, the long-pending folded axis of center of gravity of leaf tip 103a, leaf tip
A, suction surface B, pressure face
C, hub outside surface D, cylinder surfaces
Detailed description of the invention
Below in conjunction with the accompanying drawings the detailed description of the invention of the present invention is described in further detail.These embodiments are only used for
The present invention is described, and not limitation of the present invention.
In describing the invention, it should be noted that term " " center ", " longitudinally ", " laterally ", " on ", D score,
Orientation or the position relationship of the instruction such as "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description rather than instruction or dark
The device or the element that show indication must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that right
The restriction of the present invention.Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint relatively
Importance.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " is installed ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be fixing connection, it is also possible to be to removably connect, or be integrally connected；Can
To be mechanical connection, it is also possible to be electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood as the case may be
Concrete meaning in the present invention.
As depicted in figs. 1 and 2, the present invention is for a kind of embodiment of the complex bend stator blade of multi stage axial flow compressor.
As it is shown in figure 1, the complex bend stator blade of the present embodiment includes that stator blade main body 100, stator blade main body 100 include blade root
101, leaf central part 102 and leaf tip 103, leaf central part 102 is between blade root 101 and leaf tip 103.
As in figure 2 it is shown, well known to a person skilled in the art, in actual applications, stator blade main body 100 is located at the wheel of compressor
Between hub and cylinder, and blade root 101 is connected with hub outside surface C, and leaf tip 103 is connected with cylinder surfaces D.Stator blade main body
100 exist down suction surface A and pressure face B.
In the present embodiment, the center of gravity of leaf central part 102 is amassed folded axis 102a and is prolonged along the radial direction of multi stage axial flow compressor main shaft
Stretching, the radial direction of multi stage axial flow compressor main shaft is i.e. to be pointed to the direction of cylinder by the wheel hub of compressor, as shown in coordinate in Fig. 2.
Blade root 101 is the most curved to suction surface A, i.e. blade root 101 Off-Radial bends towards suction surface A, makes blade root
Suction surface A at 101 is to acutangulate between pressure face B and hub outside surface C at concave surface, blade root 101.Blade root 101
The long-pending folded axis 101a of center of gravity towards suction surface A Off-Radial with become angle α between hub outside surface C, this angle α is blade root
The angle between pressure face B and hub outside surface C at 101.Angle α can be set to 10 °-30 °, it is preferable that in the present embodiment
Angle α is set to 20 °.
Leaf tip 103 is to pressure face B recurvation, i.e. leaf tip 103 Off-Radial bends towards pressure face B, makes leaf tip
Pressure face B at 103 is to acutangulate between the suction surface A at concave surface, leaf tip 103 and cylinder surfaces D.Leaf tip 103
The long-pending folded axis 103a of center of gravity towards pressure face B Off-Radial with become angle β between cylinder surfaces D, this angle β is leaf tip
The angle between suction surface A and cylinder surfaces D at 103.Angle β can be set to 5 °-20 °, it is preferable that the folder in the present embodiment
Angle beta is set to 15 °.
Further, as in figure 2 it is shown, the height of stator blade main body 100 is h, the height of blade root 101 is h1, leaf tip 103
It is highly h2.The height h1 of blade root 101 can be set to the 15%-25% of stator blade main body 100 height h, and the height of leaf tip 103 can
It is set to the 15%-25% of stator blade main body 100 height h.Preferably, in the present embodiment, the height h1 of blade root 101 is set to stator blade
The 20% of main body 100 height h, the height of leaf tip 103 is set to the 20% of stator blade main body 100 height h.
Further, all seamlessly transit between blade root 101, leaf central part 102 and leaf tip 103.Preferably, in the present embodiment
Blade root 101, leaf central part 102 and leaf tip 103 between transitional region all use fairing processing.
The above-mentioned complex bend stator blade of the present embodiment be particularly suited for multi stage axial flow compressor across sound level.Multistage axial flow pressure
Mechanism of qi across the flow performance of sound level is: movable vane root inflow Mach number is low, changes insensitive to the angle of attack and outlet back pressure, and tip leads to
There is shock wave in road；Stator blade root inflow Mach number is high, and root corner separation easily occurs in load weight.Based on this feature, stator blade root
Portion's employing is the most curved improves root static pressure, orders about low energy fluid and flows in leaf, it is to avoid be gathered in base region and flowing point occurs
From, thus reduce stator blade Root Losses, slow down or eliminate the flow separation in this region, improve root stall nargin.Stator blade tip
Use recurvation, although low energy fluid has the trend migrated to blade tip from leaf, but owing to tip relatively root load is light, be difficult to send out
Raw flow separation；Further, recurvation makes stator blade tip load reduce further so that upstream reduces across sound movable vane outlet back pressure,
So that the passage shock downstream of movable vane tip, be conducive to extension across the stall margin of sound movable vane.Generally, stator blade
Root is the most curved, tip recurvation so that stator blade exhibition is more uniform to power load distributing, thus rubbing of decreasing that flowing radial migration brings
Wear mistake.
Therefore, the blade root complex bend stator blade the most curved, leaf tip recurvation form that uses of the present embodiment is applied to multistage
During axial flow compressor, it is possible to significantly improve stator blade root flow separation, balance stator blade exhibition to power load distributing, improve stator blade stall abundant
Degree, minimizing stationary blade loss, and the stable operation range across sound movable vane tip can be extended, thus reduce stream in whole exhibition to scope
Dynamic loss, extends the stall margin across sound level.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For Yuan, on the premise of without departing from the technology of the present invention principle, it is also possible to make some improvement and replacement, these improve and replace
Also should be regarded as protection scope of the present invention.
Claims (7)
1. for a complex bend stator blade for multi stage axial flow compressor, including stator blade main body (100), it is characterised in that described
Stator blade main body (100) includes blade root (101), leaf central part (102) and leaf tip (103), and described leaf central part (102) is positioned at described
Between blade root (101) and described leaf tip (103), the long-pending folded axis (102a) of the center of gravity of described leaf central part (102) is along described many
Radially extending of level axial flow compressor main shaft, described blade root (101) is the most curved to suction surface (A), and described leaf tip (103) is to pressure
Power face (B) recurvation.
Complex bend stator blade for multi stage axial flow compressor the most according to claim 1, it is characterised in that described blade root
The height in portion (101) is the 15%-25% of described stator blade main body (100) height.
Complex bend stator blade for multi stage axial flow compressor the most according to claim 1, it is characterised in that described blade tip
The height in portion (103) is the 15%-25% of described stator blade main body (100) height.
Complex bend stator blade for multi stage axial flow compressor the most according to claim 1, it is characterised in that described blade root
Angle between pressure face (B) and the hub outside surface (C) at portion (101) place is 10 °-30 °.
Complex bend stator blade for multi stage axial flow compressor the most according to claim 1, it is characterised in that described blade tip
Angle between suction surface (A) and the cylinder surfaces (D) at portion (103) place is 5 °-20 °.
Complex bend stator blade for multi stage axial flow compressor the most according to claim 1, it is characterised in that described blade root
All seamlessly transit between portion (101), described leaf central part (102) and described leaf tip (103).
Complex bend stator blade for multi stage axial flow compressor the most according to claim 6, it is characterised in that described blade root
Transitional region between portion (101), described leaf central part (102) and described leaf tip (103) all uses fairing processing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610802569.9A CN106122107B (en) | 2016-09-05 | 2016-09-05 | Complex bend stator blade for multi stage axial flow compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610802569.9A CN106122107B (en) | 2016-09-05 | 2016-09-05 | Complex bend stator blade for multi stage axial flow compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106122107A true CN106122107A (en) | 2016-11-16 |
| CN106122107B CN106122107B (en) | 2019-08-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610802569.9A Active CN106122107B (en) | 2016-09-05 | 2016-09-05 | Complex bend stator blade for multi stage axial flow compressor |
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| Country | Link |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143384A (en) * | 2017-07-18 | 2017-09-08 | 中国科学院工程热物理研究所 | A kind of compound angle air film hole layout structure of turbine rotor blade suction surface |
| CN108757565A (en) * | 2018-04-13 | 2018-11-06 | 哈尔滨工程大学 | A kind of compressor blade petiolarea structure based on scaling analysis |
| CN113569498A (en) * | 2021-07-26 | 2021-10-29 | 中国船舶重工集团公司第七0三研究所 | Design method for bent stator blade at end part of axial flow compressor |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3745629A (en) * | 1972-04-12 | 1973-07-17 | Secr Defence | Method of determining optimal shapes for stator blades |
| EP1462608A1 (en) * | 2003-03-27 | 2004-09-29 | Snecma Moteurs | Stator vane with double curvature |
| CN101476493A (en) * | 2007-11-09 | 2009-07-08 | 阿尔斯托姆科技有限公司 | Steam turbine |
| CN102168688A (en) * | 2011-06-10 | 2011-08-31 | 罗钜 | Axial-flow compressor stator blade |
| CN103452904A (en) * | 2012-06-01 | 2013-12-18 | 航空技术空间股份有限公司 | S-shaped profile blade of axial turbomachine compressor, corresponding compressor and turbomachine |
| CN103939150A (en) * | 2014-04-25 | 2014-07-23 | 西安交通大学 | Stationary blade structure lowering turbine stage air flow exciting force |
| CN104564841A (en) * | 2014-12-30 | 2015-04-29 | 哈尔滨汽轮机厂有限责任公司 | End bending joint bending static blade of multistage axial flow compressor |
| CN206017269U (en) * | 2016-09-05 | 2017-03-15 | 上海电气燃气轮机有限公司 | Complex bend stator blade for multi stage axial flow compressor |
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2016
- 2016-09-05 CN CN201610802569.9A patent/CN106122107B/en active Active
Patent Citations (8)
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|---|---|---|---|---|
| US3745629A (en) * | 1972-04-12 | 1973-07-17 | Secr Defence | Method of determining optimal shapes for stator blades |
| EP1462608A1 (en) * | 2003-03-27 | 2004-09-29 | Snecma Moteurs | Stator vane with double curvature |
| CN101476493A (en) * | 2007-11-09 | 2009-07-08 | 阿尔斯托姆科技有限公司 | Steam turbine |
| CN102168688A (en) * | 2011-06-10 | 2011-08-31 | 罗钜 | Axial-flow compressor stator blade |
| CN103452904A (en) * | 2012-06-01 | 2013-12-18 | 航空技术空间股份有限公司 | S-shaped profile blade of axial turbomachine compressor, corresponding compressor and turbomachine |
| CN103939150A (en) * | 2014-04-25 | 2014-07-23 | 西安交通大学 | Stationary blade structure lowering turbine stage air flow exciting force |
| CN104564841A (en) * | 2014-12-30 | 2015-04-29 | 哈尔滨汽轮机厂有限责任公司 | End bending joint bending static blade of multistage axial flow compressor |
| CN206017269U (en) * | 2016-09-05 | 2017-03-15 | 上海电气燃气轮机有限公司 | Complex bend stator blade for multi stage axial flow compressor |
Non-Patent Citations (1)
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| 陆华伟: ""带根部间隙的直、弯压气机静叶流场的实验"", 《推进技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143384A (en) * | 2017-07-18 | 2017-09-08 | 中国科学院工程热物理研究所 | A kind of compound angle air film hole layout structure of turbine rotor blade suction surface |
| CN108757565A (en) * | 2018-04-13 | 2018-11-06 | 哈尔滨工程大学 | A kind of compressor blade petiolarea structure based on scaling analysis |
| CN113569498A (en) * | 2021-07-26 | 2021-10-29 | 中国船舶重工集团公司第七0三研究所 | Design method for bent stator blade at end part of axial flow compressor |
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| Publication number | Publication date |
|---|---|
| CN106122107B (en) | 2019-08-16 |
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