CN104729822B - A kind of turbine blade wake analogue means - Google Patents
A kind of turbine blade wake analogue means Download PDFInfo
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- CN104729822B CN104729822B CN201510020717.7A CN201510020717A CN104729822B CN 104729822 B CN104729822 B CN 104729822B CN 201510020717 A CN201510020717 A CN 201510020717A CN 104729822 B CN104729822 B CN 104729822B
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- suction surface
- turbine blade
- back side
- tail
- pressure face
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Abstract
A kind of turbine blade wake analogue means.It is the subtriangular rod-like structure that its lateral cross section is surrounded by suction surface, pressure face and the back side, suction surface and the back side are plane, the position adjacent with the back side is formed continuously the circular arc of three projections on pressure face, for being formed and the symmetrical tail in suction surface side, and three arc radius are bigger closer to the back side, while indicating a main line between suction surface and pressure face.The turbine blade wake analogue means of the present invention is tested applied to TWO-DIMENSIONAL CASCADE, the device is a straight rod with triangle section, it can load low-pressure turbine blade after more targeted simulation superelevation load, and under the two-dimensional plane coordinate system of leaf grating, these tail similarity leading indicators of x directions speed, y directions speed, x directions velocity disturbance, y directions velocity disturbance, shear stress and the tail width of tail is more nearly real blade, therefore the tail of low-pressure turbine blade can be loaded after more accurate simulation superelevation load.
Description
Technical field
The invention belongs to civil aviation technical field, more particularly to a kind of turbine blade wake analogue means.
Background technology
In current industrial society, gas turbine has obtained extensive as aircraft power plant and terrestrial power generation equipment
Using.In the gas turbine, impeller rotary part (such as compressor and turbine) is mostly important building block, therefore is improved
The efficiency of compressor and turbine turns into the important process for improving gas turbine performance.Cascade wind tunnel test is a kind of research impeller
The simply effective experiment method of rotary part aeroperformance.In the gas turbine, the interference of rotor-stator is impeller
A kind of physical phenomenon existed all the time in the machine course of work, for more accurate, truly analysis turbine internal flow machine
Reason, must study influence of the upstream blade last person mark to downstream blade in CASCADE EXPERIMENT.In order to simplify experimental facilities, save real
Test equipment expense, the upstream blade last person mark of current two dimensional surface CASCADE EXPERIMENT it is main by using with upstream blade trailing edge circular arc
Diameter suitable pole is replaced.Although this approximate replacement versatility is stronger, have the disadvantage for different type blade wake passing
Simulation then there is larger difference.
The content of the invention
, can be after more accurate simulation superelevation load it is an object of the invention to provide one kind in order to solve the above problems
Load the turbine blade wake analogue means of low-pressure turbine blade tail.
In order to achieve the above object, the turbine blade wake analogue means that the present invention is provided is its lateral cross section by suction
The subtriangular rod-like structure that face, pressure face and the back side are surrounded, wherein suction surface and the back side are plane, with the back of the body on pressure face
The adjacent position in face is formed continuously the circular arc of three projections, for being formed and the symmetrical tail in suction surface side, and three circles
The radius of arc is bigger closer to the back side, while indicating one between suction surface and pressure face, from direction of flow, rearwardly direction extends
Main line.
Angle between described suction surface and main line is 2 °, and the angle between pressure face and main line is 8 °, suction surface with
Angle between pressure face is 10 °.
Angle between described suction surface and the back side is 82.5 °.
Angle between the tangent line and pressure face of three described circular arcs is 5.0 °.
The length of described turbine blade wake analogue means is equal to or slightly lower than the width of experimental wind tunnel.
The turbine blade wake analogue means that the present invention is provided is a straight rod with triangle section, and it can more be directed to
Low-pressure turbine blade is loaded after property simulation superelevation load, and under the two-dimensional plane coordinate system of leaf grating, x directions speed, y directions
Speed, x directions velocity disturbance, y directions velocity disturbance, shear stress and tail width these tail similarity leading indicators are more
Close to real blade, therefore, it is possible to load the tail of low-pressure turbine blade after more accurate simulation superelevation load.
Brief description of the drawings
The turbine blade wake analogue means side view that Fig. 1 provides for the present invention.
The turbine blade wake analogue means stereogram that Fig. 2 provides for the present invention.
Embodiment
The turbine blade wake analogue means that the present invention is provided is carried out specifically with specific embodiment below in conjunction with the accompanying drawings
It is bright.
As shown in Figure 1 and Figure 2, the turbine blade wake analogue means that provides of the present invention for its lateral cross section by suction surface L1,
The subtriangular rod-like structure that pressure face L3 and back side L4 are surrounded, wherein suction surface L1 and back side L4 are plane, pressure face
The upper positions adjacent with back side L4 of L3 is formed continuously the circular arc 1 of three projections, for being formed and the symmetrical tail in suction surface L1 sides
Mark, and the radius of three circular arcs 1 is bigger closer to back side L4, while indicating one between suction surface L1 and pressure face L3 always
Flow the direction main line 2 that rearwardly L4 directions extend.
Angle between described suction surface L1 and main line 2 is 2 °, and the angle between pressure face L3 and main line 2 is 8 °, is inhaled
Angle between power face L1 and pressure face L3 is 10 °.
Angle between described suction surface L1 and back side L4 is 82.5 °.
Described suction surface L1 length L5 be analogue means characteristic length, the length by analogue means reynolds number ReD
To determine, ReDIt is defined as：
Wherein U is cascade wind tunnel inlet velocity, and μ is the kinematic viscosity of air.By ReDControl the scope 1000-3000
It is interior, suction surface L1 length L5 is determined with this.
Angle between the tangent line and pressure face L3 of three described circular arcs 1 is 5.0 °.
The length L2 of described turbine blade wake analogue means is equal to or slightly lower than the width of experimental wind tunnel.
The turbine blade wake analogue means application method that now present invention is provided is described below：The whirlpool that the present invention is provided
Main line 2 on impeller blade tail analogue means is positioned over and come the position of levelling row, direction of flow in the leaf grating shown in Fig. 1 two
Marked under dimensional plane coordinate system with letter U, the costa 3 of straight rod with it is in 90 ° to flow.
Claims (3)
1. a kind of turbine blade wake analogue means, it is lateral cross section by suction surface (L1), pressure face (L3) and the back side (L4)
The subtriangular rod-like structure surrounded, wherein suction surface (L1) and the back side (L4) are on plane, pressure face (L3) and the back side
(L4) adjacent position is formed continuously the circular arc (1) of three projections, for formation and the symmetrical tail in suction surface (L1) side, and
And the radius of three circular arcs (1) is bigger closer to the back side (L4), while indicating one between suction surface (L1) and pressure face (L3)
From the direction of flow main line (2) that rearwardly direction extends；
It is characterized in that：Angle between described suction surface (L1) and main line (2) is 2 °, pressure face (L3) and main line (2) it
Between angle be 8 °, the angle between suction surface (L1) and pressure face (L3) is 10 °.
2. turbine blade wake analogue means according to claim 1, it is characterised in that：Described suction surface (L1) and the back of the body
Angle between face (L4) is 82.5 °.
3. turbine blade wake analogue means according to claim 1, it is characterised in that：Three described circular arcs (1)
Angle between tangent line and pressure face (L3) is 5.0 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510020717.7A CN104729822B (en) | 2015-01-16 | 2015-01-16 | A kind of turbine blade wake analogue means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510020717.7A CN104729822B (en) | 2015-01-16 | 2015-01-16 | A kind of turbine blade wake analogue means |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104729822A CN104729822A (en) | 2015-06-24 |
| CN104729822B true CN104729822B (en) | 2017-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510020717.7A Active CN104729822B (en) | 2015-01-16 | 2015-01-16 | A kind of turbine blade wake analogue means |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441782B (en) * | 2016-10-21 | 2018-12-18 | 大连理工大学 | A kind of reciprocating blade wake passing generator |
| CN108036917B (en) * | 2017-12-15 | 2019-09-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of ram-air turbine wind tunnel test test method |
| CN110594072B (en) * | 2019-05-27 | 2020-10-23 | 合肥工业大学 | Bionic wing-shaped blade |
| CN112197922B (en) * | 2020-08-25 | 2022-03-25 | 中国航发湖南动力机械研究所 | Turbine blade vibration fatigue simulation piece and design method thereof |
| CN112179671B (en) * | 2020-09-30 | 2022-10-21 | 中国科学院工程热物理研究所 | Low-pressure turbine annular blade cascade test bed with unsteady wake simulation function |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1051069A (en) * | 1989-10-16 | 1991-05-01 | 西屋电气公司 | The impeller assembly that is used for the reaction turbine leaf grating |
| CN2328790Y (en) * | 1997-05-13 | 1999-07-14 | 北京全三维动力工程有限公司 | Rear loading static blade for tangential turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014104978A1 (en) * | 2012-12-28 | 2014-07-03 | Nanyang Technological University | A turbine |
-
2015
- 2015-01-16 CN CN201510020717.7A patent/CN104729822B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1051069A (en) * | 1989-10-16 | 1991-05-01 | 西屋电气公司 | The impeller assembly that is used for the reaction turbine leaf grating |
| CN2328790Y (en) * | 1997-05-13 | 1999-07-14 | 北京全三维动力工程有限公司 | Rear loading static blade for tangential turbine |
Non-Patent Citations (2)
| Title |
|---|
| 上游尾迹入射角对压气机叶片负荷的影响;杨荣菲 等;《航空动力学报》;20101231;第25卷(第12期);第2711-2715页 * |
| 非定长尾迹宽度对动叶传热影响的数值研究;张玲 等;《中国电机工程学报》;20141215;第34卷(第35期);摘要部分 * |
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| CN104729822A (en) | 2015-06-24 |
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Effective date of registration: 20240123 Address after: Room 1006, Huaying Building, Central Avenue, Tianjin Pilot Free Trade Zone (Airport Economic Zone), Dongli District, Tianjin, 300000 Patentee after: Tianjin Feilian Technology Co.,Ltd. Country or region after: China Address before: 300300 Tianjin city Dongli District North Road No. 2898 Patentee before: CIVIL AVIATION University OF CHINA Country or region before: China |
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