CN111042871A - Internal cooling structure of turbine movable blade - Google Patents
Internal cooling structure of turbine movable blade Download PDFInfo
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- CN111042871A CN111042871A CN201911258432.1A CN201911258432A CN111042871A CN 111042871 A CN111042871 A CN 111042871A CN 201911258432 A CN201911258432 A CN 201911258432A CN 111042871 A CN111042871 A CN 111042871A
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- shaped channel
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- cooling structure
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- 238000001816 cooling Methods 0.000 title claims abstract description 60
- 239000010432 diamond Substances 0.000 claims description 4
- 229910003460 diamond Inorganic materials 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000008878 coupling Effects 0.000 abstract description 4
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- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 11
- 230000000694 effects Effects 0.000 description 6
- 238000011161 development Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 3
- QNRATNLHPGXHMA-XZHTYLCXSA-N (r)-(6-ethoxyquinolin-4-yl)-[(2s,4s,5r)-5-ethyl-1-azabicyclo[2.2.2]octan-2-yl]methanol;hydrochloride Chemical compound Cl.C([C@H]([C@H](C1)CC)C2)CN1[C@@H]2[C@H](O)C1=CC=NC2=CC=C(OCC)C=C21 QNRATNLHPGXHMA-XZHTYLCXSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
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- 239000000463 material Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an internal cooling structure of a turbine movable vane, which comprises a U-shaped channel and a trapezoidal channel; the U-shaped channel comprises an integrally formed U-shaped channel inlet section, a U-shaped channel outlet section and a U-shaped channel top turning area, the U-shaped channel inlet section and the U-shaped channel outlet section are communicated through a plurality of connecting bridges, and the U-shaped channel outlet section and the trapezoidal channel are communicated through a plurality of jet holes; a plurality of oval ball sockets are arranged on the bottom surface of the U-shaped channel, and a plurality of fins are arranged in the trapezoidal channel; during working, a cooling working medium firstly enters the inlet section of the U-shaped channel to exchange heat with the surface of the channel, then flows into the outlet section of the U-shaped channel through the turning area at the top of the U-shaped channel and the connecting bridge, and is injected into the trapezoidal channel through the jet holes after finishing heat exchange with the wall surface of the U-shaped channel, and is laterally discharged after exchanging heat with the wall surface of the trapezoidal channel. The invention realizes the advantages of high heat transfer, low resistance, high adaptability and the like through multi-structure coupling.
Description
Technical Field
The invention belongs to the technical field of turbine cooling, and particularly relates to an internal cooling structure of a turbine movable vane.
Background
The development level of aeroengines and heavy-duty gas turbines is an important embodiment of national industrial strength, the design and manufacturing process of the aeroengines and heavy-duty gas turbines relates to a large number of key technologies, has obvious multidisciplinary cross fusion characteristics and is a huge system engineering, so that the development of 'two machines' is promoted to the height of national strategy in all world countries.
Increasing combustor gas temperature is an important way to increase the power and efficiency of aircraft engines and heavy duty gas turbines, and therefore gas turbines are constantly being developed with an increase in the gas temperature before the turbine. When a combustion engine runs, a turbine blade directly contacts with high-temperature gas, the front edge of the blade is impacted by the gas, a pressure surface and a suction surface show special heat load distribution characteristics in complex flow states such as flow separation and reattachment, areas such as a blade top and an end wall are also influenced by secondary flow, so that the working condition of the blade is extremely severe, and meanwhile, because the development of a blade material is seriously lagged behind the improvement of the gas temperature, the gas temperature of the current advanced combustion engine far exceeds the melting point of the blade material, the development of an efficient blade cooling technology is vital to the guarantee of safe and stable running of the turbine and even the whole combustion engine.
When the turbine blade is cooled, the 'cold air' is usually extracted from the air compressor, and is conveyed to the interior of the turbine blade through the air system to perform flowing heat exchange, and then is discharged into main flow fuel gas from a gas film hole and a tail edge cleft seam on the surface of the blade, so that the turbine blade is cooled at the cost of the loss of working medium working capacity, the achievement of the highest cooling efficiency by the least cooling air is an important target of turbine cooling design, and related researchers and designers are required to continuously improve the heat transfer performance of a cooling structure in the turbine blade interior cooling design. Meanwhile, because the turbine blade has a special shape, the design of an internal cooling structure must be matched with the blade shape, and the rotating effect of the movable blade can obviously influence the internal heat transfer performance, which brings huge challenges to the design of the internal cooling structure of the turbine movable blade.
For the internal cooling of turbine blades, related researchers and designers have proposed a large number of cooling structures, but most of the cooling structures are designed based on independent cooling units, and the interaction between different cooling units and the matching performance of the cooling structures with key factors such as rotation are not considered. In view of the above situation, there is an urgent need for development of a turbine rotor blade internal cooling structure having higher cooling performance and better adaptability.
Disclosure of Invention
In order to solve the problems, the invention provides a turbine movable blade internal cooling structure, the structure design fully considers the movable blade rotation effect, the V-shaped arranged elliptical ball socket array is adopted, the rotation heat transfer capability is obviously enhanced through the coupling of a secondary flow structure, meanwhile, an arc connecting bridge structure is introduced into a U-shaped channel to reduce resistance loss, a cooling working medium is injected into a trailing edge trapezoidal channel through an impact hole to further strengthen the heat transfer performance, and the advantages of high heat transfer, low resistance, high adaptability and the like are realized through the multi-structure coupling.
The invention is realized by adopting the following technical scheme:
an internal cooling structure of a turbine movable blade comprises a U-shaped channel and a trapezoidal channel; the U-shaped channel comprises an integrally formed U-shaped channel inlet section, a U-shaped channel outlet section and a U-shaped channel top turning area which is communicated with the U-shaped channel inlet section and the U-shaped channel outlet section, the U-shaped channel inlet section and the U-shaped channel outlet section are communicated through a plurality of connecting bridges, and the U-shaped channel outlet section and the trapezoidal channel are communicated through a plurality of jet holes; a plurality of oval ball sockets are arranged on the bottom surface of the U-shaped channel, and a plurality of fins are arranged in the trapezoidal channel;
during working, a cooling working medium firstly enters the inlet section of the U-shaped channel to exchange heat with the surface of the channel, then flows into the outlet section of the U-shaped channel through the turning area at the top of the U-shaped channel and the connecting bridge, and is injected into the trapezoidal channel through the jet holes after finishing heat exchange with the wall surface of the U-shaped channel, and is laterally discharged after exchanging heat with the wall surface of the trapezoidal channel.
The invention is further improved in that the oval ball sockets are uniformly arranged on the bottom surfaces of the U-shaped channel inlet section and the U-shaped channel outlet section in a V-shaped arrangement mode.
The invention is further improved in that the included angle between the long axis of the oval ball socket and the wall surface of the channel is within the range of 10-80 degrees.
The invention is further improved in that the connecting bridge of the U-shaped channel is of an arc-shaped structure and is uniformly arranged along the radial direction of the U-shaped channel.
The invention is further improved in that the included angle between the tangent line of the connecting bridge at the inlet section and the outlet section of the U-shaped channel and the wall surface of the channel is 0-90 degrees.
The invention is further improved in that the jet holes are arranged on the side wall of the U-shaped channel outlet section and are uniformly arranged along the radial direction.
The invention further improves that the jet hole shape is in the form of one or more of a combination of a circle, an ellipse and a diamond in a square.
The invention is further improved in that the fins are arranged in the trapezoidal channel in a penetrating or intercepting manner, or are arranged in a row or a staggered row, or are arranged vertically or obliquely.
A further improvement of the invention is that the fin shape is in the form of a combination of one or more of a circle, an oval, a square and a diamond.
The invention is further improved in that the jet hole outlet is opposite to the first row of fins so as to obtain better impingement cooling performance.
The invention has at least the following beneficial technical effects:
according to the internal cooling structure of the turbine movable blade, the mode that the U-shaped channel in the chord region of the blade and the trapezoidal channel in the tail edge region of the blade are combined is adopted, a cooling working medium continuously enters the trapezoidal channel to play a cooling role after heat exchange is completed in the U-shaped channel, the cooling potential of the working medium is fully utilized, the coupling effect of the U-shaped channel and the trapezoidal channel is considered, and the internal efficient cooling of the turbine movable blade is finally realized;
furthermore, the elliptical ball socket has the advantages of high heat transfer and low resistance cooling performance, only generates small resistance loss while realizing enhanced heat transfer, and simultaneously increases the heat transfer area;
furthermore, the introduction of the connecting bridge can lead the cooling working medium to flow into the outlet section of the U-shaped channel in a distributed manner, and relieve the gathering and extrusion phenomenon of the working medium in the turning area at the top of the U-shaped channel, so that the flow resistance loss in the channel can be obviously reduced, and in addition, the structure also increases the heat transfer area and can improve the heat transfer effect;
furthermore, a cooling working medium which completes heat exchange in the U-shaped channel impacts the surface of the first row of fins of the trapezoidal channel through the jet holes, remarkable impact-enhanced heat transfer performance can be obtained, and then fluid disturbance is enhanced through cylindrical streaming, so that the cooling performance of the trailing edge trapezoidal channel is improved.
According to the internal cooling structure of the turbine movable blade, the cooling coupling of the U-shaped channel in the chord region and the trapezoidal channel in the tail edge region of the movable blade is realized through the jet holes, the transverse secondary flow caused by rotation is enhanced by adopting the V-shaped elliptical ball socket structure, the cooling performance advantages of high heat transfer and low flow resistance are realized by combining the U-shaped channel connecting bridge, and the internal cooling structure of the turbine movable blade has excellent comprehensive cooling performance.
Drawings
FIG. 1 is an overall three-dimensional view of the internal cooling structure of a turbine bucket;
FIG. 2 is a bottom view of the internal cooling structure of the turbine bucket;
FIG. 3 is a schematic diagram of the arrangement of the oval ball socket and the connecting bridge in the U-shaped channel;
FIG. 4 is a side view of the internal cooling structure of the turbine bucket and a schematic view of the transverse secondary flow;
description of reference numerals:
1 is U type passageway, 2 is U type passageway inlet section, 3 is U type passageway outlet section, and 4 are trapezoidal passageways, and 5 is U type passageway top turn district, 6 are the connecting bridge, and 7 are the jet orifice, and 8 are oval ball socket, and 9 are the fin.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples.
Referring to fig. 1 and 2, the internal cooling structure of the turbine movable blade mainly comprises a U-shaped channel 1 and a trapezoidal channel 4, wherein a U-shaped channel inlet section 2 and a U-shaped channel outlet section 3 of the U-shaped channel 1 are communicated with a plurality of connecting bridges 6 through a U-shaped channel top turning area 5, and the U-shaped channel outlet section 3 and the trapezoidal channel 4 are communicated through a plurality of jet holes 7. A plurality of oval ball socket 8 structures are arranged on the bottom surface of the U-shaped channel 1, and a plurality of fin 9 structures are arranged in the trapezoidal channel 4.
The jet holes 7 are arranged on the side wall of the U-shaped channel outlet section 3 and are uniformly arranged along the radial direction, and the shapes of the jet holes 7 can be circular, oval, square, rhombic or the combination of multiple basic shapes; the fins 9 are arranged in the trapezoidal channel 4 in a penetrating or cutting mode, can be arranged in a row or a staggered row, can be arranged vertically or obliquely, and the shape of the fins 9 can be circular, oval, square, rhombic or a combination of a plurality of basic shapes. The outlet of the jet hole 7 is opposite to the first row of fins 9 so as to obtain better impingement cooling performance.
The cooling working medium firstly enters the inlet section 2 of the U-shaped channel to exchange heat with the surface of the channel, then flows into the outlet section 3 of the U-shaped channel through the turning area 5 at the top of the U-shaped channel and the connecting bridge 6, and is injected into the trapezoidal channel 4 through the jet hole 7 after finishing heat exchange with the wall surface of the U-shaped channel 1, and is laterally discharged after exchanging heat with the wall surface of the trapezoidal channel 4.
Referring to fig. 2 and 3, the oval ball socket 8 is uniformly arranged on the bottom surfaces of the U-shaped channel inlet section 2 and the U-shaped channel outlet section 3 in a V-shaped arrangement manner, and the included angle between the long axis of the oval ball socket 8 and the wall surface of the channel is preferably in the range of 10-80 °. The connecting bridge 6 of the U-shaped channel 1 is of an arc-shaped structure and is uniformly arranged along the radial direction of the U-shaped channel 1, and the included angle between the tangent line of the connecting bridge 6 at the inlet section 2 and the outlet section 3 of the U-shaped channel and the wall surface of the channel is preferably 0-90 degrees.
Referring to fig. 4, the structure of the transverse secondary flow generated by the rotation action in the U-shaped channel 1 is represented in the U-shaped channel inlet section 2 as: from the leading edge face to the trailing edge face, at the U-shaped channel outlet section 3, it behaves as: from the trailing edge face to the leading edge face. The V-shaped arranged elliptical ball socket 8 structure is designed according to the characteristics, so that the elliptical ball socket 8 generates a transverse secondary flow structure with the same rotating effect, and the transverse secondary flow strength is enhanced by the superposition of the two structures, thereby enhancing the heat transfer performance of the channel and obtaining a better cooling effect.
Claims (10)
1. The internal cooling structure of the turbine movable blade is characterized by comprising a U-shaped channel (1) and a trapezoidal channel (4); wherein,
the U-shaped channel (1) comprises an integrally formed U-shaped channel inlet section (2), a U-shaped channel outlet section (3) and a U-shaped channel top turning area (5) for communicating the U-shaped channel inlet section (2) with the U-shaped channel outlet section (3), the U-shaped channel inlet section (2) and the U-shaped channel outlet section (3) are communicated through a plurality of connecting bridges (6), and the U-shaped channel outlet section (3) and the trapezoidal channel (4) are communicated through a plurality of jet holes (7); a plurality of oval ball sockets (8) are arranged on the bottom surface of the U-shaped channel (1), and a plurality of fins (9) are arranged in the trapezoidal channel (4);
during operation, a cooling working medium firstly enters the inlet section (2) of the U-shaped channel to exchange heat with the surface of the channel, then flows into the outlet section (3) of the U-shaped channel through the turning area (5) at the top of the U-shaped channel and the connecting bridge (6), and is injected into the trapezoidal channel (4) through the jet holes (7) after heat exchange with the wall surface of the U-shaped channel (1), and is laterally discharged after heat exchange with the wall surface of the trapezoidal channel (4).
2. The internal cooling structure for turbine rotor blades according to claim 1, wherein oval ball sockets (8) are uniformly arranged on the bottom surfaces of the U-shaped channel inlet section (2) and the U-shaped channel outlet section (3) in a V-shaped arrangement.
3. The internal cooling structure of the turbine rotor blade as claimed in claim 1, wherein the angle between the major axis of the oval ball socket (8) and the wall surface of the passage is in the range of 10-80 °.
4. The internal cooling structure for turbine rotor blades according to claim 1, wherein the connecting bridges (6) of the U-shaped channel (1) are of a circular arc structure and are uniformly arranged along the radial direction of the U-shaped channel (1).
5. The internal cooling structure for turbine rotor blades according to claim 1, wherein the included angle between the tangent of the connecting bridge (6) at the inlet section (2) and the outlet section (3) of the U-shaped channel and the wall surface of the channel is in the range of 0-90 degrees.
6. The turbine blade internal cooling structure as claimed in claim 1, wherein the jet holes (7) are arranged on the side wall of the U-shaped channel outlet section (3) and are uniformly arranged in the radial direction.
7. The turbine bucket internal cooling structure as claimed in claim 1, wherein the jet holes (7) are in the form of one or more of a combination of a circle, an ellipse and a diamond in a square.
8. The turbine bucket internal cooling structure according to claim 1, wherein the fins (9) are arranged in the trapezoidal channel (4) in a penetrating or intercepting manner, or are arranged in a row or a staggered row, or are arranged vertically or obliquely.
9. A turbine bucket internal cooling structure according to claim 1, wherein the fins (9) are in the form of one or more of a combination of circles, ovals, squares and diamonds.
10. The internal cooling structure of a turbine bucket according to claim 1, characterized in that the outlet of the jet hole (7) is opposite to the first row of fins (9) to obtain better impingement cooling performance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911258432.1A CN111042871A (en) | 2019-12-10 | 2019-12-10 | Internal cooling structure of turbine movable blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911258432.1A CN111042871A (en) | 2019-12-10 | 2019-12-10 | Internal cooling structure of turbine movable blade |
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| CN111042871A true CN111042871A (en) | 2020-04-21 |
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| CN201911258432.1A Pending CN111042871A (en) | 2019-12-10 | 2019-12-10 | Internal cooling structure of turbine movable blade |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6227804B1 (en) * | 1998-02-26 | 2001-05-08 | Kabushiki Kaisha Toshiba | Gas turbine blade |
| CN102102543A (en) * | 2011-03-11 | 2011-06-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN103061823A (en) * | 2012-12-29 | 2013-04-24 | 西安交通大学 | Lacing hole structure of turbine blade and loose lacing wire installation structure of the same turbine blade |
| CN106168143A (en) * | 2016-07-12 | 2016-11-30 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket |
| CN106795770A (en) * | 2014-08-27 | 2017-05-31 | 西门子股份公司 | Turbo blade and turbine |
| CN106870015A (en) * | 2017-04-26 | 2017-06-20 | 哈尔滨工业大学 | A kind of labyrinth type internal cooling structure for high-temperature turbine movable vane trailing edge |
| WO2017216225A1 (en) * | 2016-06-17 | 2017-12-21 | Siemens Aktiengesellschaft | Turbine blade with cooled blade platform |
| CN211008773U (en) * | 2019-12-10 | 2020-07-14 | 西安交通大学 | Internal cooling structure of turbine movable blade |
-
2019
- 2019-12-10 CN CN201911258432.1A patent/CN111042871A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6227804B1 (en) * | 1998-02-26 | 2001-05-08 | Kabushiki Kaisha Toshiba | Gas turbine blade |
| CN102102543A (en) * | 2011-03-11 | 2011-06-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN103061823A (en) * | 2012-12-29 | 2013-04-24 | 西安交通大学 | Lacing hole structure of turbine blade and loose lacing wire installation structure of the same turbine blade |
| CN106795770A (en) * | 2014-08-27 | 2017-05-31 | 西门子股份公司 | Turbo blade and turbine |
| WO2017216225A1 (en) * | 2016-06-17 | 2017-12-21 | Siemens Aktiengesellschaft | Turbine blade with cooled blade platform |
| CN106168143A (en) * | 2016-07-12 | 2016-11-30 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket |
| CN106870015A (en) * | 2017-04-26 | 2017-06-20 | 哈尔滨工业大学 | A kind of labyrinth type internal cooling structure for high-temperature turbine movable vane trailing edge |
| CN211008773U (en) * | 2019-12-10 | 2020-07-14 | 西安交通大学 | Internal cooling structure of turbine movable blade |
Non-Patent Citations (1)
| Title |
|---|
| 刘钊等: "燃气轮机透平叶片传热和冷却研究:内部冷却", 热力透平, vol. 42, no. 04, 31 December 2013 (2013-12-31) * |
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