CN104729822A - Turbine blade wake simulating device - Google Patents
Turbine blade wake simulating device Download PDFInfo
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- CN104729822A CN104729822A CN201510020717.7A CN201510020717A CN104729822A CN 104729822 A CN104729822 A CN 104729822A CN 201510020717 A CN201510020717 A CN 201510020717A CN 104729822 A CN104729822 A CN 104729822A
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- turbine blade
- suction surface
- analogue means
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
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Abstract
The invention provides a turbine blade wake simulating device. The turbine blade wake simulating device is of a subtriangular bar-shaped structure with a horizontal cross section enclosed by a suction surface, a pressure surface and a back face, wherein the suction surface and the back face are planes, three protruding circular arcs are continuously formed in the portion, adjacent to the back face, on the pressure surface, the circular arcs are used for forming a wake forming side symmetry to the suction surface, the closer to the back face, the bigger the radiuses of the three circular arcs are, and meanwhile a main line is marked between the suction surface and the pressure surface. The turbine blade wake simulating device is applied to two-dimension cascade experiments, the turbine blade wake simulating device is a straight bar with a triangular cross section, the more targeted simulation on loading a low-pressure turbine blade after the load is too large can be achieved, wake similarity key indicators of x-direction velocity, y-direction velocity, x-direction velocity disturbance, y-direction velocity disturbance, shearing stress and wake width of a wake in a cascade two-dimension plane coordinate system are closer to the wake indicators of a real blade, and therefore, the wake of loading the low-pressure turbine blade after the load is too large can be simulated more accurately.
Description
Technical field
The invention belongs to civil aviation technical field, particularly relate to a kind of turbine blade wake analogue means.
Background technology
In current industrial society, gas turbine is widely used as aircraft power plant and terrestrial power generation equipment.In the gas turbine, vane rotary parts (such as pneumatic plant and turbine) are of paramount importance building blocks, and the efficiency therefore improving pneumatic plant and turbine has become the important process improving gas turbine performance.Cascade wind tunnel test is a kind of research vane rotary parts aeroperformance simply effective experiment method.In the gas turbine, the interference of rotor-stator is a kind of physical phenomenon existed all the time in the turbine course of work, in order to analyze the internal flow mechanism of turbine more accurately, truly, upstream blade last person mark must be studied on the impact of downstream blade in CASCADE EXPERIMENT.In order to simplify experimental facilities, save experiment equipment expense, the upstream blade last person mark of current two dimensional surface CASCADE EXPERIMENT replaces mainly through using the pole suitable with upstream blade trailing edge arc diameter.Although this approximate replacement versatility is comparatively strong, shortcoming then there is larger difference for the simulation of dissimilar blade wake passing.
Summary of the invention
In order to solve the problem, the object of the present invention is to provide a kind of can more accurately simulate superelevation load after load the turbine blade wake analogue means of low-pressure turbine blade tail.
In order to achieve the above object, turbine blade wake analogue means provided by the invention is the subtriangular rod-like structure that its lateral cross section is surrounded by suction surface, pressure face and the back side, wherein suction surface and the back side are plane, position adjacent with the back side on pressure face is formed with the circular arc of three projections continuously, for the formation of the tail with suction surface side symmetry, and the radius of three circular arcs is larger the closer to the back side, between suction surface and pressure face, indicate the always flow path direction rearwardly main line that extends of direction simultaneously.
Angle between described suction surface and main line is 2 °, and the angle between pressure face and main line is 8 °, and the angle between suction surface and pressure face is 10 °.
Angle between described suction surface and the back side is 82.5 °.
Angle between the tangent line of three described circular arcs and pressure face 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.
Turbine blade wake analogue means provided by the invention 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 surface coordinate system of leaf grating, these tail similarity leading indicators of x direction speed, y direction speed, x direction velocity disturbance, y direction velocity disturbance, shear stress and tail width more close to real blade, therefore, it is possible to load the tail of low-pressure turbine blade after more accurately simulating superelevation load.
Accompanying drawing explanation
Fig. 1 is turbine blade wake analogue means side view provided by the invention.
Fig. 2 is turbine blade wake analogue means stereographic map provided by the invention.
Embodiment
Below in conjunction with the drawings and specific embodiments, turbine blade wake analogue means provided by the invention is described in detail.
As shown in Figure 1 and Figure 2, turbine blade wake analogue means provided by the invention is the subtriangular rod-like structure that its lateral cross section is surrounded by suction surface L1, pressure face L3 and back side L4, wherein suction surface L1 and back side L4 is plane, position adjacent with back side L4 on pressure face L3 is formed with the circular arc 1 of three projections continuously, for the formation of the tail with suction surface L1 side symmetry, and the radius of three circular arcs 1 is larger the closer to back side L4, between suction surface L1 and pressure face L3, indicate the always flow path direction rearwardly main line 2 that extends of L4 direction simultaneously.
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 °, and the angle between suction surface L1 and pressure face L3 is 10 °.
Angle between described suction surface L1 and back side L4 is 82.5 °.
Described suction surface length L1 is the characteristic length of analogue means, and this length is by the reynolds number Re of analogue means
ddetermine, Re
ddefinition like this:
Wherein U is cascade wind tunnel inlet velocity, and μ is the kinematic viscosity of air.By Re
dcontrol in the scope of 1000-3000, determine suction surface length L1 with this.
Angle between the tangent line of three described circular arcs 1 and pressure face L3 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.
Now turbine blade wake analogue means using method provided by the invention is described below: the main line 2 on turbine blade wake analogue means provided by the invention is positioned over the position parallel with incoming flow, carry out flow path direction to mark by letter U under the two dimensional surface coordinate system of the leaf grating shown in Fig. 1, the costa 3 of straight rod is in 90 ° with incoming flow.
Claims (5)
1. a turbine blade wake analogue means, it is characterized in that: it is for its lateral cross section is by suction surface (L1), the subtriangular rod-like structure that pressure face (L3) and the back side (L4) surround, wherein suction surface (L1) and the back side (L4) are plane, the upper position adjacent with the back side (L4) of pressure face (L3) is formed with the circular arc (1) of three projections continuously, for the formation of the tail with suction surface (L1) side symmetry, and the radius of three circular arcs (1) is larger the closer to the back side (L4), indicate the main line (2) of an always flow path direction rearwardly direction extension between suction surface (L1) and pressure face (L3) simultaneously.
2. turbine blade wake analogue means according to claim 1, it is characterized in that: the angle between described suction surface (L1) and main line (2) is 2 °, angle between pressure face (L3) and main line (2) is 8 °, and the angle between suction surface (L1) and pressure face (L3) is 10 °.
3. turbine blade wake analogue means according to claim 1, is characterized in that: the angle between described suction surface (L1) and the back side (L4) is 82.5 °.
4. turbine blade wake analogue means according to claim 1, is characterized in that: the angle between the tangent line of three described circular arcs (1) and pressure face (L3) is 5.0 °.
5. turbine blade wake analogue means according to claim 1, is characterized in that: the length (L2) of described turbine blade wake analogue means is equal to or slightly lower than the width of experimental wind tunnel.
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 |
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| 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 |
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| CN104729822A true CN104729822A (en) | 2015-06-24 |
| CN104729822B CN104729822B (en) | 2017-08-11 |
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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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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441782A (en) * | 2016-10-21 | 2017-02-22 | 大连理工大学 | Reciprocating blade wake generator |
| CN108036917A (en) * | 2017-12-15 | 2018-05-15 | 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 |
| WO2020237850A1 (en) * | 2019-05-27 | 2020-12-03 | 合肥工业大学 | Bionic airfoil blade |
| CN112179671A (en) * | 2020-09-30 | 2021-01-05 | 中国科学院工程热物理研究所 | Low-pressure turbine annular cascade test bed with unsteady wake simulation function |
| CN112197922A (en) * | 2020-08-25 | 2021-01-08 | 中国航发湖南动力机械研究所 | Turbine blade vibration fatigue simulation piece and design method thereof |
Citations (3)
| 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 |
| 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 (3)
| 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 |
| WO2014104978A1 (en) * | 2012-12-28 | 2014-07-03 | Nanyang Technological University | A turbine |
Non-Patent Citations (2)
| Title |
|---|
| 张玲 等: "非定长尾迹宽度对动叶传热影响的数值研究", 《中国电机工程学报》 * |
| 杨荣菲 等: "上游尾迹入射角对压气机叶片负荷的影响", 《航空动力学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441782A (en) * | 2016-10-21 | 2017-02-22 | 大连理工大学 | Reciprocating blade wake generator |
| CN106441782B (en) * | 2016-10-21 | 2018-12-18 | 大连理工大学 | A kind of reciprocating blade wake passing generator |
| CN108036917A (en) * | 2017-12-15 | 2018-05-15 | 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 |
| 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 |
| WO2020237850A1 (en) * | 2019-05-27 | 2020-12-03 | 合肥工业大学 | Bionic airfoil blade |
| CN112197922A (en) * | 2020-08-25 | 2021-01-08 | 中国航发湖南动力机械研究所 | Turbine blade vibration fatigue simulation piece and design method thereof |
| CN112179671A (en) * | 2020-09-30 | 2021-01-05 | 中国科学院工程热物理研究所 | Low-pressure turbine annular cascade test bed with unsteady wake simulation function |
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|---|---|
| CN104729822B (en) | 2017-08-11 |
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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 |