CN220015272U - Gas turbine cooling blade for enhancing heat exchange - Google Patents
Gas turbine cooling blade for enhancing heat exchange Download PDFInfo
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- CN220015272U CN220015272U CN202320935253.2U CN202320935253U CN220015272U CN 220015272 U CN220015272 U CN 220015272U CN 202320935253 U CN202320935253 U CN 202320935253U CN 220015272 U CN220015272 U CN 220015272U
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- heat exchange
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- cavity
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- 238000001816 cooling Methods 0.000 title claims abstract description 64
- 230000002708 enhancing effect Effects 0.000 title abstract description 4
- 230000001965 increasing effect Effects 0.000 claims description 13
- 230000000694 effects Effects 0.000 abstract description 7
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 239000000306 component Substances 0.000 description 5
- 238000009826 distribution Methods 0.000 description 4
- 238000002679 ablation Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
Abstract
The utility model discloses a turbine cooling blade of a gas turbine for enhancing heat exchange, which comprises an outer frame, wherein the front end of the inner part of the outer frame is provided with a cavity, a plurality of flow channels are sequentially arranged in the outer frame and positioned at the tail end of the cavity along the height direction, and the front sides of the flow channels are communicated with the cavity through air inlets; and each group of the runners is internally provided with an air heat exchange assembly, the tail ends of the air heat exchange assemblies are blade tail edges, and the blade tail edges are positioned at the rear end of the outer frame. According to the utility model, the plurality of flow channels are arranged, the air heat exchange assembly is arranged in each flow channel, the tail end of the air heat exchange assembly is provided with the cooling hole, and the air heat exchange assembly in the air heat exchange assembly can enable cold air to enter the plurality of flow channels to independently perform heat exchange treatment, and the plurality of flow channels independently operate to improve the heat exchange efficiency, increase the heat exchange area, enhance the disturbance of cooling air and realize the efficient and uniform cooling effect on the blades.
Description
Technical Field
The utility model relates to the technical field of gas turbines, in particular to a gas turbine cooling blade for enhancing heat exchange.
Background
The turbine is a core component of the heavy-duty gas turbine, and the working condition of the turbine blade serving as a main working element is very severe, so that the turbine blade is not only required to bear a high-temperature environment of thousands of DEG C, but also is in a high-speed rotation state for a long time, and therefore, the safety and the reliability of the turbine blade are important preconditions for the safe operation of the heavy-duty gas turbine.
At present, the temperature of a turbine blade of a heavy-duty gas turbine is reduced by combining an internal cooling cavity with external air film cooling, so that the deformation or ablation of blade metal at high temperature is prevented. For gas turbine blades, when the blade profile has a certain bending torque along the blade height direction, the assembly difficulty of the bushing is high, so that a radial cooling mode is generally adopted, namely, the blade enters a serpentine channel from the upper end wall and then is discharged from the tail edge cooling hole. However, the turbine blade with the serpentine cooling channel has the problems that the tail end of the channel is not cooled in place, the cooling wind of the tail edge cooling hole is distributed unevenly, and the like, so that the temperature distribution of the position of the blade close to the upper end wall and the lower end wall is uneven, the service life of the blade is influenced, and the safe operation of the gas turbine is seriously endangered.
Disclosure of Invention
The technical problems to be solved by the utility model are as follows: how to solve the problem that the temperature distribution of the blade is uneven due to the fact that the tail end of a channel of the existing turbine blade is not cooled in place.
In order to solve the technical problems, the utility model provides the following technical scheme:
the gas turbine cooling blade comprises an outer frame, wherein a cavity is formed in one side of the inner part of the outer frame, a plurality of flow channels are sequentially formed in the outer frame and positioned on one side of the cavity along the height direction, the flow channels are communicated with the cavity through air inlets, and an air heat exchange component is arranged in each flow channel; the other side of the outer frame is provided with a blade tail edge, and the blade tail edge is positioned at the rear end of the outer frame, wherein a plurality of cooling holes are arranged on the blade tail edge along the height direction of the blade tail edge, and the cooling holes are communicated with a plurality of flow channels.
According to the utility model, the plurality of flow channels are arranged, the air heat exchange assembly is arranged in each flow channel, the tail end of the air heat exchange assembly is provided with the cooling holes, and the air heat exchange assembly in the air heat exchange assembly can enable cold air to enter the plurality of flow channels to independently perform heat exchange treatment, so that the plurality of flow channels independently operate to improve the heat exchange efficiency, uniformly act on the tail ends of the blades, simultaneously, the heat exchange area is increased, the disturbance of cooling air is enhanced, the efficient and uniform cooling effect on the blades is realized, and the problems of nonuniform cooling air distribution of the cooling holes of the tail edges of the traditional blades are also solved.
As a further scheme of the utility model: the cavity is of an inverted trapezoid structure, and a cold air through hole is formed in the bottom of the cavity.
As a further scheme of the utility model: the plurality of flow channels comprise a first flow channel, a second flow channel, a third flow channel and a fourth flow channel, wherein the first flow channel, the second flow channel, the third flow channel and the fourth flow channel are sequentially distributed from bottom to top, and the internal height is sequentially increased from bottom to top; the number of air inlets at the front sides of the first flow channel, the second flow channel, the third flow channel and the fourth flow channel is gradually increased.
As a further scheme of the utility model: the air heat exchange assembly comprises rib plates, rib columns and a flow dividing baffle plate, wherein the rib columns are arranged close to the tail edges of the blades, the flow dividing baffle plate is arranged on one side, back to the tail edges, of the rib columns, and the rib plates are arranged on one side, back to the tail edges of the blades, of the flow dividing baffle plate.
As a further scheme of the utility model: the rib plates are provided with a plurality of rib plates, the rib plates are distributed in a staggered mode, and wind passing through the rib plates passes through in a serpentine shape.
As a further scheme of the utility model: and one side of each rib plate facing the cavity is provided with a plurality of stop blocks with raised surfaces.
As a further scheme of the utility model: the flow dividing baffle is provided with a plurality of flow dividing baffles, the flow dividing baffles are vertically distributed, and a gap is reserved between every two adjacent flow dividing baffles.
Compared with the prior art, the utility model has the beneficial effects that:
firstly, by arranging a plurality of flow channels, each flow channel is internally provided with an air heat exchange component, the tail end of each air heat exchange component is provided with a cooling hole, and by arranging a plurality of flow channels, the air heat exchange components in the air heat exchange components can enable cold air to enter the plurality of flow channels to independently perform heat exchange treatment, and the plurality of flow channels independently operate to improve the heat exchange efficiency, increase the heat exchange area, enhance the disturbance of cooling air and realize the efficient and uniform cooling effect on the blades;
secondly, the cavity is arranged into an inverted trapezoid structure, the air flow can be increased by increasing the space above the cavity, and more cold air is arranged above the cavity to exchange heat; meanwhile, cross-distributed rib plates are arranged in each flow passage, and wind passing through the plurality of rib plates passes through in a serpentine shape, so that disturbance of cooling air is enhanced, turbulence is formed, and heat exchange efficiency is improved;
finally, the flow channel is internally provided with the flow dividing baffle at the rear side of the rib plate, and the rear side of the flow dividing baffle is also provided with a plurality of rib columns, wherein the flow dividing baffle can divide cold air, so that air flowing in the flow channel can form a uniform through flow effect, can be divided into a plurality of sections to flow out of the flow dividing baffle, and then flows out after passing through the corresponding rib columns, thereby increasing the heat exchange area and improving the efficient and uniform cooling effect on the blades.
Drawings
FIG. 1 is a schematic view of a gas turbine cooling blade with enhanced heat transfer in accordance with an embodiment of the present utility model;
FIG. 2 is a plan view of FIG. 1 in accordance with an embodiment of the present utility model;
FIG. 3 is a rear view of the embodiment of the present utility model shown in FIG. 1;
reference numerals illustrate: 1. rib plates; 2. an air inlet; 3. a cold air through hole; 4. a cooling hole; 5. blade trailing edge; 6. rib columns; 7. a shunt baffle; 8. a fourth flow passage; 9. a third flow passage; 10. a second flow passage; 11. a first flow passage; 12. a cavity; 13. and an outer frame.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions in the embodiments of the present utility model will be clearly and completely described in the following in conjunction with the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1, 2 and 3, a heat exchange enhancement gas turbine cooling blade comprises a rib plate 1, an air inlet 2, a cold air through hole 3, a cooling hole 4, a blade tail edge 5, a rib post 6, a split baffle 7, a fourth flow passage 8, a third flow passage 9, a second flow passage 10, a first flow passage 11, a cavity 12 and an outer frame 13, wherein the outer frame 13 is of a whole frame-shaped structure, four corner positions are provided with connecting parts, and the inner left end of the outer frame 13 (the front-back, up-down, left-right position relation related to the utility model is based on the reference standard of fig. 1, the position relation is not limited by the explanation reference, and the actual installation is based on the field condition) is provided with a cavity 12;
the right side of cavity 12 is from down upwards equipped with first runner 11, second runner 10, third runner 9 and fourth runner 8 in proper order, and four runners all communicate with cavity 12, and every runner inner structure is the same, and the difference is only in the size difference, and every runner is inside to be equipped with floor 1, split flow baffle 7 and rib post 6 in proper order from front to back, and the end of outer frame 13 sets up blade trailing edge 5, and arranges a plurality of cooling holes 4 along its direction of height on the blade trailing edge 5, and this cooling hole 4 communicates with four runners.
Referring to fig. 1 and 2, rib plates 1 are arranged in each flow channel, a plurality of rib plates 1 in each flow channel are arranged, the rib plates 1 are distributed in a staggered manner, wind passing through the rib plates 1 passes through in a serpentine shape, namely, the top of one rib plate 1 of two adjacent rib plates 1 is fixed to the top wall of the corresponding flow channel, the bottom of the other rib plate 1 is fixed to the bottom wall of the corresponding flow channel (as shown in fig. 1 and 2), and the number of rib plates 1 is particularly set;
furthermore, one side of each rib plate 1 facing the cavity 12 is provided with a plurality of surface protruding stop blocks, so that when cooling air passes through the rib plates 1, the cooling air passes through the stop blocks, and the staggered rib plates 1 with the protruding surfaces can enhance disturbance of the cooling air, so that the cooling air forms turbulence and heat exchange is enhanced.
Referring to fig. 1 and 2, each flow channel is further provided with a rib column 6 and a flow dividing baffle 7, wherein one side of the rib plate 1, which is away from the cavity 12, is provided with the flow dividing baffle 7, one side of the flow dividing baffle 7, which is away from the cavity 12, is provided with the rib column 6, cooling air coming out from the rib plate 1 can be divided again through the flow dividing baffle 7, flows out from the rib column 6 after being divided, and finally is discharged from the cooling hole 4 on the blade trailing edge 5.
Furthermore, the plurality of the diversion baffles 7 are arranged vertically, namely, the diversion baffles 7 are arranged along the height direction of the utility model, gaps are reserved between two adjacent diversion baffles 7, the diversion baffles 7 can evenly divert cooling air from the rib plate 1 and then act on the rib columns 6, and the cooling air flows from the rib columns 6, so that the heat exchange area is increased, the efficient and uniform cooling effect on the blades is improved, and the number of the rib columns 6 is also arranged in a plurality, the rib columns 6 are distributed in a matrix form, and the number of the rib columns 6 and the diversion baffles 7 is specifically arranged according to practical conditions.
Referring to fig. 1, the first flow passage 11, the second flow passage 10, the third flow passage 9, and the fourth flow passage 8 are distributed in order from bottom to top, and the internal height increases in order from bottom to top; the number of intake ports 2 communicating with the cavity 12 on the left side of the first flow passage 11, the second flow passage 10, the third flow passage 9, and the fourth flow passage 8 gradually increases; the shape of the corresponding cavity 12 is also determined along with four runners, the cavity 12 is of an inverted trapezoid structure, the bottom of the cavity 12 is provided with cold air through holes 3, the cold air through holes 3 at the bottom are used for discharging cold air for heat exchange, after the cold air enters the cavity 12, the cold air enters the corresponding runners through the air inlet 2 and then carries out heat exchange treatment on the corresponding runners, the cavity 12 is arranged into the inverted trapezoid structure, the air flow can be increased by increasing the space above the cavity 12, and more cold air is arranged above the cold air to exchange heat.
The specific operation principle of the utility model is as follows:
when the cooling blades exchange heat, cooling air enters from the cold air through holes 3, after entering the cavity 12, the cooling air enters into the first flow channel 11, the second flow channel 10, the third flow channel 9 and the fourth flow channel 8 through the air inlet 2, and the entering cooling air also has different sizes because of different inner sizes of the four flow channels, and the cooling air enters into the fourth flow channel 8 firstly passes through the rib plate 1 in a serpentine shape as an example because of the same inner structure of the four flow channels, so that the omnibearing heat exchange of the rib plate 1 is realized, the heat exchange area is increased at the raised part of the surface of the rib plate 1, the effective heat exchange can be realized, then the flow distribution of the cooling air is improved, the more uniform distribution of the air is realized, a plurality of cooling air strands enter into the rib columns 6, the disturbance of the cooling air is increased, then the cooling air acts on the blade tail edge 5, the cooling effect of cooling the blade tail edge 5 is further enhanced, and finally the cooling air is discharged from the cooling hole 4, so that the omnibearing heat exchange treatment of the turbine blades is realized.
The above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present utility model.
Claims (7)
1. The utility model provides a gas turbine cooling blade of intensive heat transfer, its characterized in that includes outer frame (13), cavity (12) have been seted up to one side of outer frame (13) inside, and wherein a plurality of runner has been seted up in proper order along the direction of height to the one side that just is located cavity (12) in outer frame (13), and a plurality of runner all communicates cavity (12) through air inlet (2), all is equipped with air heat exchange assembly in every group runner;
the other side of the outer frame (13) is provided with a blade tail edge (5), and the blade tail edge (5) is positioned at the rear end of the outer frame (13), wherein a plurality of cooling holes (4) are arranged on the blade tail edge (5) along the height direction of the blade tail edge, and the cooling holes (4) are communicated with a plurality of flow channels.
2. A heat exchange enhanced gas turbine cooling blade according to claim 1, wherein: the cavity (12) is of an inverted trapezoid structure, and a cold air through hole (3) is formed in the bottom of the cavity (12).
3. A heat exchange enhanced gas turbine cooling blade according to claim 1, wherein: the flow passages comprise a first flow passage (11), a second flow passage (10), a third flow passage (9) and a fourth flow passage (8), wherein the first flow passage (11), the second flow passage (10), the third flow passage (9) and the fourth flow passage (8) are distributed in sequence from bottom to top, and the internal height is increased in sequence from bottom to top;
the number of air inlets (2) at the front sides of the first flow passage (11), the second flow passage (10), the third flow passage (9) and the fourth flow passage (8) is gradually increased.
4. A heat exchange enhanced gas turbine cooling blade according to claim 1, wherein: the air heat exchange assembly comprises rib plates (1), rib columns (6) and a flow dividing baffle plate (7), wherein the rib columns (6) are arranged close to the tail edges (5) of the blades, the flow dividing baffle plate (7) is arranged on one side, back to the tail edges (5), of the rib columns (6), and the rib plates (1) are arranged on one side, back to the tail edges (5), of the flow dividing baffle plate (7).
5. A heat transfer enhanced gas turbine cooling blade according to claim 4, wherein: the rib plates (1) are provided with a plurality of rib plates (1), the rib plates (1) are distributed in a staggered mode, and wind passing through the rib plates (1) passes through in a serpentine shape.
6. A heat transfer enhanced gas turbine cooling blade according to claim 5, wherein: and one side of each rib plate (1) facing the cavity (12) is provided with a plurality of stop blocks with raised surfaces.
7. A heat transfer enhanced gas turbine cooling blade according to claim 4, wherein: the flow dividing baffles (7) are provided with a plurality of flow dividing baffles (7), the flow dividing baffles (7) are vertically distributed, and gaps are reserved between two adjacent flow dividing baffles (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320935253.2U CN220015272U (en) | 2023-04-21 | 2023-04-21 | Gas turbine cooling blade for enhancing heat exchange |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320935253.2U CN220015272U (en) | 2023-04-21 | 2023-04-21 | Gas turbine cooling blade for enhancing heat exchange |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220015272U true CN220015272U (en) | 2023-11-14 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320935253.2U Active CN220015272U (en) | 2023-04-21 | 2023-04-21 | Gas turbine cooling blade for enhancing heat exchange |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220015272U (en) |
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2023
- 2023-04-21 CN CN202320935253.2U patent/CN220015272U/en active Active
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