CN106122107B - Complex bend stator blade for multi stage axial flow compressor - Google Patents
Complex bend stator blade for multi stage axial flow compressor Download PDFInfo
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- CN106122107B CN106122107B CN201610802569.9A CN201610802569A CN106122107B CN 106122107 B CN106122107 B CN 106122107B CN 201610802569 A CN201610802569 A CN 201610802569A CN 106122107 B CN106122107 B CN 106122107B
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- leaf
- stator blade
- blade
- blade root
- tip
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Classifications
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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 technical field of gas turbine, more particularly 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, center of gravity long-pending folded axle line the radially extending along multi stage axial flow compressor main shaft of leaf central part, blade root is just curved to suction surface, and leaf tip is to pressure face recurvation.Just curved using blade root, leaf tip recurvation form, when applied to multi stage axial flow compressor, it can significantly improve stator blade root flow separation, balance stator blade is opened up to power load distributing, improves stator blade stall margin, reduction stationary blade loss, and the stable operation range of across sound movable vane tip can be extended, to entirely open up to range reduction flow losses, the stall margin across sound level is extended.
Description
Technical field
The present invention relates to technical field of gas turbine more particularly to a kind of complex bend for multi stage axial flow compressor are quiet
Leaf.
Background technique
Existing gas turbine blower generallys use three dimendional blade designing technique, i.e. the center of gravity long-pending folded axle by changing blade
The geometric formats such as line or each section are curved with respect to blade profile feature realization blade, plunder, to effectively control the strong three-dimensional inside 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 do not obtain determining explanation to the Influencing Mechanism of flowing yet at present.
The zigzag grain boundary used in gas turbine blower is all made of the just curved geometric format of blade root and blade tip at present, i.e.,
Suction surface is concave surface after bending, so that " C " type pressure distribution that static pressure is low in blade root and blade tip static pressure height, leaf is generated, so that two
The region the low energy air-flow Xiang Yezhong radial migration at end, improves the corner region flow of petiolarea.But blade root and blade tip are just curved to be deteriorated
Flowing in leaf is unfavorable for this so that area loss increases in leaf, and the just curved angle of attack increase for also resulting in blade root and blade tip
The stall margin in region.The form of recurvation is that pressure face is concave surface after being bent, and recurvation can play and just curved opposite effect, can
Low energy air-flow is driven to flow to both ends from leaf, so as to improve the flowing in region in leaf, while by reducing the negative of blade root and blade tip
Lotus exports back-pressure to reduce upstream movable vane, reduces upstream movable vane load.But due to using zigzag grain boundary at present primarily to control
Corner region flow separation processed, therefore recurvation is not applied in gas turbine blower.
Summary of the invention
Stator blade can be balanced the technical problem to be solved in the present invention is to provide one kind to open up to power load distributing, raising stator blade stall
Nargin, the complex bend stator blade for multi stage axial flow compressor for reducing stationary blade loss, to overcome the drawbacks described above of the prior art.
In order to solve the above-mentioned technical problem, the present invention adopts the following technical scheme: it is a kind of for multi stage axial flow compressor
Complex bend stator blade, including stator blade main body, stator blade main body include blade root, leaf central part and leaf tip, and leaf central part is located at blade root
Between leaf tip, center of gravity long-pending folded axle line the radially extending along multi stage axial flow compressor main shaft of leaf central part, blade root is to suction
Face is just 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 pressure face at blade root and the angle between hub outside surface are 10 ° -30 °.
Preferably, the angle between the suction surface and cylinder surfaces at leaf tip is 5 ° -20 °.
Preferably, it is seamlessly transitted between blade root, leaf central part and leaf tip.
Preferably, the transitional region between blade root, leaf central part and leaf tip is all made of fairing processing.
Compared with prior art, the present invention has significant progress: just curved using blade root, leaf tip recurvation form,
When applied to multi stage axial flow compressor, stator blade root flow separation can significantly improve, balance stator blade is opened up to power load distributing, improved
Stator blade stall margin reduces stationary blade loss, and can extend the stable operation range of across sound movable vane tip, thus entirely open up to
Range reduces flow losses, extends the stall margin across sound level.
Detailed description of the invention
Fig. 1 is the schematic 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 center of gravity long-pending folded axle line signal 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 center of gravity long-pending folded axle line of blade root 101a, blade root
102, the center of gravity long-pending folded axle line of leaf central part 102a, leaf central part
103, the center of gravity long-pending folded axle line of leaf tip 103a, leaf tip
A, suction surface B, pressure face
C, hub outside surface D, cylinder surfaces
Specific embodiment
Specific embodiments of the present invention will be described in further detail with reference to the accompanying drawing.These embodiments are only used for
Illustrate the present invention, and not limitation of the present invention.
In the description of the present invention, it should be noted that term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
Limitation of the invention.In addition, term " first ", " second " are used for description purposes only, it is not understood to indicate or imply opposite
Importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.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, a kind of embodiment of the present invention for the complex bend stator blade of multi stage axial flow compressor.
As shown in Figure 1, the complex bend stator blade of the present embodiment includes stator blade main body 100, stator blade main body 100 includes 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 shown in Fig. 2, well known to a person skilled in the art in practical applications, stator blade main body 100 is set to the wheel of compressor
Between hub and cylinder, and blade root 101 is connect with hub outside surface C, and leaf tip 103 is connect with cylinder surfaces D.Stator blade main body
100 have suction surface A and pressure face B in the operating condition.
In the present embodiment, the center of gravity long-pending folded axle line 102a of leaf central part 102 prolongs along the radial direction of multi stage axial flow compressor main shaft
It stretches, the radial direction of multi stage axial flow compressor main shaft is to be by the direction of the wheel hub direction cylinder of compressor, as shown in coordinate in Fig. 2.
Blade root 101 is just curved to suction surface A, i.e. 101 Off-Radial of blade root bends towards suction surface A, makes blade root
Suction surface A at 101 is at an acute angle between the pressure face B and hub outside surface C at concave surface, blade root 101.Blade root 101
For center of gravity long-pending folded axle line 101a towards suction surface A Off-Radial and at angle α between hub outside surface C, which is blade root
Angle between pressure face B at 101 and hub outside surface C.Angle α can be set as 10 ° -30 °, it is preferable that in the present embodiment
Angle α is set as 20 °.
Leaf tip 103 bends to pressure face B recurvation, i.e. 103 Off-Radial of leaf tip towards pressure face B, makes leaf tip
Pressure face B at 103 is at an acute angle between the suction surface A and cylinder surfaces D at concave surface, leaf tip 103.Leaf tip 103
For center of gravity long-pending folded axle line 103a towards pressure face B Off-Radial and at angle β between cylinder surfaces D, angle β is leaf tip
Angle between suction surface A at 103 and cylinder surfaces D.Angle β can be set as 5 ° -20 °, it is preferable that the folder in the present embodiment
Angle beta is set as 15 °.
Further, as shown in Fig. 2, the height of stator blade main body 100 is h, the height of blade root 101 is h1, leaf tip 103
Height is h2.The height h1 of blade root 101 can be set as the 15%-25% of 100 height h of stator blade main body, and the height of leaf tip 103 can
It is set as the 15%-25% of 100 height h of stator blade main body.Preferably, in the present embodiment, the height h1 of blade root 101 is set as stator blade
The 20% of 100 height h of main body, the height of leaf tip 103 are set as the 20% of 100 height h of stator blade main body.
Further, it is seamlessly transitted between blade root 101, leaf central part 102 and leaf tip 103.Preferably, in the present embodiment
Blade root 101, the transitional region between leaf central part 102 and leaf tip 103 be all made of fairing processing.
The above-mentioned complex bend stator blade of the present embodiment be particularly suitable for multi stage axial flow compressor across sound level.Multistage axial flow pressure
Flow characteristics of the mechanism of qi across sound level are as follows: movable vane root inflow Mach number is low, insensitive to the angle of attack and outlet back pressure variation, and tip is logical
There are shock waves in road；Stator blade root inflow Mach number is high, and load weight is easy to appear root corner separation.Based on this feature, stator blade root
Root static pressure can be improved using just curved in portion, and low energy fluid is driven to flow into leaf, avoids being gathered in base region generation flowing point
From to reduce stator blade Root Losses, slowing down or eliminate the flow separation in the region, improve root stall nargin.Stator blade tip
Recurvation is used, although there is low energy fluid the trend migrated from Ye Zhongxiang blade tip to be not easy to send out since tip is light compared with root load
Raw flow separation；Also, recurvation further decreases stator blade tip load, so that across the sound movable vane outlet back pressure in upstream reduces,
To make the downward downstream of the passage shock of movable vane tip, be conducive to extend the stall margin across sound movable vane.Generally, stator blade
Root is just curved, tip recurvation, so that stator blade is opened up more uniform to power load distributing, rubs to reduce flowing radial migration bring
It wears mistake.
Therefore, just curved using blade root, leaf tip recurvation form the complex bend stator blade of the present embodiment is applied to multistage
When axial flow compressor, can significantly improve stator blade root flow separation, balance stator blade open up to power load distributing, improve stator blade stall it is abundant
Degree reduces stationary blade loss, and can extend the stable operation range of across sound movable vane tip, to flow entirely opening up to reduce to range
Dynamic loss, extends the stall margin across sound level.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and replacement can also be made, these are improved and replacement
Also it should be regarded as protection scope of the present invention.
Claims (3)
1. a kind of complex bend stator blade for multi stage axial flow compressor, including stator blade main body (100), which is characterized in that described
Stator blade main body (100) includes blade root (101), leaf central part (102) and leaf tip (103), and the leaf central part (102) is located at described
Between blade root (101) and the leaf tip (103), the center of gravity long-pending folded axle line (102a) of the leaf central part (102) is along described more
Grade axial flow compressor main shaft radially extends, and the blade root (101) is just curved to suction surface (A), and the leaf tip (103) is to pressure
Power face (B) recurvation；The angle between pressure face (B) and hub outside surface (C) at the blade root (101) is 10 ° -30 °, institute
Stating the angle between the suction surface (A) at leaf tip (103) and cylinder surfaces (D) is 5 ° -20 °；The blade root (101)
Height is the 15%-25% of stator blade main body (100) height, and the height of the leaf tip (103) is the stator blade main body
(100) 15%-25% of height.
2. the complex bend stator blade according to claim 1 for multi stage axial flow compressor, which is characterized in that the blade root
It is seamlessly transitted between portion (101), the leaf central part (102) and the leaf tip (103).
3. the complex bend stator blade according to claim 2 for multi stage axial flow compressor, which is characterized in that the blade root
Transitional region between portion (101), the leaf central part (102) and the leaf tip (103) is all made of 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 CN106122107A (en) | 2016-11-16 |
| CN106122107B true CN106122107B (en) | 2019-08-16 |
Family
ID=57271432
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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| CN (1) | CN106122107B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143384B (en) * | 2017-07-18 | 2019-02-15 | 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 (6)
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168688A (en) * | 2011-06-10 | 2011-08-31 | 罗钜 | Axial-flow compressor stator blade |
| EP2669475B1 (en) * | 2012-06-01 | 2018-08-01 | Safran Aero Boosters SA | S-shaped profile blade of axial turbomachine compressor, corresponding compressor and turbomachine |
-
2016
- 2016-09-05 CN CN201610802569.9A patent/CN106122107B/en active Active
Patent Citations (6)
| 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 |
| 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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| CN106122107A (en) | 2016-11-16 |
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