CN210105928U - Novel impingement cooling turbulence structure - Google Patents
Novel impingement cooling turbulence structure Download PDFInfo
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- CN210105928U CN210105928U CN201920327957.5U CN201920327957U CN210105928U CN 210105928 U CN210105928 U CN 210105928U CN 201920327957 U CN201920327957 U CN 201920327957U CN 210105928 U CN210105928 U CN 210105928U
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- 238000001816 cooling Methods 0.000 title claims abstract description 37
- 230000007704 transition Effects 0.000 claims abstract description 5
- 239000000112 cooling gas Substances 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 3
- 238000012546 transfer Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 12
- 238000013461 design Methods 0.000 description 9
- 238000005457 optimization Methods 0.000 description 4
- 230000006872 improvement Effects 0.000 description 3
- 239000012809 cooling fluid Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
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Abstract
The utility model discloses a novel impingement cooling turbulence structure, which comprises an upper wall surface, a lower wall surface and a plurality of turbulence columns; the flow disturbing column is columnar, the upper end face and the lower end face of the flow disturbing column are ellipses with the same shape, the middle section between the upper end face and the lower end face is an ellipse with the area smaller than that of the upper end face, the cylindrical surface of the flow disturbing column is in curve transition from the upper end face and the lower end face to the middle section, and long axes of the upper end face, the lower end face and the middle section are all parallel; if the interference flow column is arranged between the upper wall surface and the lower wall surface, a cooling channel is formed between the upper wall surface and the lower wall surface. The cooling gas flows out of the channel after being subjected to enhanced heat exchange through the turbulent flow column group of the cooling channel. The utility model discloses a novel vortex column structure and combination method advantage lies in can make full use of cooling gas, reduces the pressure loss of cooling gas in the inside of high temperature part to can improve the regional heat transfer ability of vortex column.
Description
Technical Field
The utility model relates to a gas turbine, aeroengine high temperature part cooling and other fields that relate to impingement cooling especially relate to a novel impingement cooling vortex structure.
Background
The gas turbine engine is a main power source of the aircraft engine and is always the work core of the aircraft technicians, and the gas turbine engine mainly pushes turbine blades to rotate through high-temperature and high-pressure gas.
As is known from thermodynamic cycles, increasing the pre-turbine gas temperature increases the thermal cycle efficiency and thrust-to-weight ratio, and thus increasing the pre-turbine gas temperature is an important means of improving the performance of a gas turbine engine. Along with the continuous improvement of the gas temperature in front of the turbine, the heat bearing capacity of the turbine blade is tested seriously, and in order to ensure the efficient operation of the engine and the safe and reliable work of the turbine, the heat bearing capacity of the turbine blade needs to be continuously improved. It is common to start with the synthesis of new refractory materials and the development of efficient cooling techniques.
Currently, many efforts have been made to develop efficient cooling techniques, wherein the provision of turbulence columns is one of the effective measures for cooling turbine blades. The turbulence columns are arranged in the turbine disc, the cooling channel in the turbine blade and other parts, and when cooling fluid flows through the turbulence column groups, boundary layer separation is generated by cooling gas, so that the cooling effect of the gas is enhanced, and the purpose of cooling the turbine blade is achieved.
For the turbine disc and the turbine blades of the gas turbine, the turbolator column not only can play a role in enhancing heat exchange, but also can play a role in enhancing the structural strength of the part.
The existing impingement cooling turbulent flow structure has the following limitations:
the current commonly adopted turbulence column structure is a circular column, a drop-shaped column and the like, the circular column turbulence column has better heat exchange capacity, but the pressure loss of cooling fluid is larger; the pressure loss caused by the columnar turbulence columns of the water drops is low, but the heat exchange capacity of the columnar turbulence columns of the water drops is limited.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that to the defect that involves in the background art, provide a novel impingement cooling vortex structure, reduce gaseous pressure loss of cooling promptly, maximum improvement cooling capacity again.
The utility model discloses a solve above-mentioned technical problem and adopt following technical scheme:
a novel impact cooling turbulence structure comprises an upper wall surface, a lower wall surface and a plurality of turbulence columns;
the flow disturbing column is columnar, the upper end face and the lower end face of the flow disturbing column are ellipses with the same shape, the middle section between the upper end face and the lower end face is an ellipse with the area smaller than that of the upper end face, the cylindrical surface of the flow disturbing column is in curve transition from the upper end face and the lower end face to the middle section, and long axes of the upper end face, the lower end face and the middle section are all parallel;
and if the interference flow column is arranged between the upper wall surface and the lower wall surface, a cooling channel is formed between the upper wall surface and the lower wall surface. The cooling gas flows out of the channel after being subjected to enhanced heat exchange through the turbulent flow column group of the cooling channel.
As the utility model relates to a novel further optimization scheme of impingement cooling vortex structure, be equipped with a plurality of through-holes on the incident flow face of vortex post, the direction and the incoming flow direction of through-hole are the same.
As a novel further optimization scheme of impingement cooling vortex structure, if the direction that is equipped with a plurality of through-holes, through-hole on the incident flow face of some vortex post is the same with the incoming flow direction in the vortex post, do not establish the through-hole on the incident flow face of another part vortex post.
As the utility model relates to a novel further optimization scheme of impingement cooling vortex structure, the vortex post through-hole is at the upstream face evenly distributed of vortex post, and the major axis direction and the incoming flow direction of vortex post up end are the same.
As a further optimization scheme of the novel impact cooling flow disturbing structure, the radius of the cylindrical surface of the flow disturbing column along the flow direction is 11.1a, the radius along the span direction is 19.8b, the length-to-short semi-axis ratio of the upper end surface and the lower end surface is 4a:2.25b, the length-to-short semi-axis ratio of the middle section is 2.8a:1.6b, the distance of the flow disturbing column along the flow direction is 17a, the transverse distance is 16.5b, a and b are preset length thresholds, and 4a is larger than 2.25 b.
The utility model adopts the above technical scheme to compare with prior art, have following technological effect:
1. for general impingement cooling, the turbulence column mainly adopted by the impingement cooling is a straight column, and the requirements of both heat exchange capacity and pressure loss cannot be met.
2. The cross section of the turbulence column with the crescent-shaped oval design is oval, the turbulence column conforms to the streamline design, and the cylindrical surface adopts the curved surface design, so that the windward area of the turbulence column is reduced, the pressure loss of cooling gas is reduced, and the pressure loss of the turbulence column is reduced compared with that of a cylindrical turbulence column; through the calculation of the average Nurseel number of the upper bottom surface and the lower bottom surface of the channel, the average Nurseel number of the design is higher than that of the circular flow disturbing columns and the elliptical flow disturbing columns, namely the heat exchange capability of the design is higher than that of the circular flow disturbing columns and the elliptical flow disturbing columns.
3. The turbulence column of the crescent oval design of local trompil to the trompil of above-mentioned turbulence column incident flow face, further shunts cooling gas, the great reduction gaseous loss of pressure, and the reduction degree is the biggest than cylindrical turbulence column loss of pressure, and its heat transfer ability improves to some extent than cylindrical turbulence column.
4. The turbulence column is designed by combining the crescent elliptic turbulence columns with local holes, and the overall performance is comprehensively improved by the arrangement and combination of the two types of turbulence columns.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
FIG. 2 is a top view of the structure of the turbulence columns of the present invention with through holes;
FIG. 3 is a schematic structural view of the turbulence columns of the present invention with through holes;
FIG. 4 is a schematic structural view of a part of the turbulence column of the present invention with through holes;
FIG. 5 is a schematic structural view of a turbulent flow column without through holes in the present invention;
fig. 6 is a schematic structural view of the turbulent flow column provided with the through hole in the present invention.
In the figure, 1-channel outlet, 2-hole on the turbulence column, 3-channel inlet, 4-crescent elliptic turbulence column with hole, and 5-crescent elliptic structure turbulence column.
Detailed Description
The technical scheme of the utility model is further explained in detail with the attached drawings as follows:
the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
The utility model discloses a novel impingement cooling turbulence structure, which comprises an upper wall surface, a lower wall surface and a plurality of turbulence columns; as shown in fig. 5, the turbulence column is in a column shape, the upper end surface and the lower end surface of the turbulence column are ellipses with the same shape, the middle section between the upper end surface and the lower end surface is an ellipse with an area smaller than that of the upper end surface, the cylindrical surface of the turbulence column is in curve transition from the upper end surface and the lower end surface to the middle section, and the long axes of the upper end surface, the lower end surface and the middle section are all parallel; and if the interference flow column is arranged between the upper wall surface and the lower wall surface, a cooling channel is formed between the upper wall surface and the lower wall surface. The cooling gas flows out of the channel after being subjected to enhanced heat exchange through the turbulent flow column group of the cooling channel.
As shown in FIG. 1, cooling air flow enters the turbulence column group from the right channel port and flows through the turbulence column region designed in FIG. 1, the circumferential surface of the turbulence column is in curved surface transition, the radius of the cylindrical surface of the turbulence column along the flow direction is 11.1a, the radius along the span direction is 19.8b, the length-to-short semi-axis ratio of the upper end surface to the lower end surface is 4a:2.25b, the length-to-short semi-axis ratio of the middle section is 2.8a:1.6b, the distance of the turbulence column along the flow direction is 17a, and the transverse distance is 16.5 b. As a result, it was found that: under the same initial conditions, the design of fig. 1 can reduce the pressure loss by 33% and improve the heat exchange capacity by 7% compared with the cylindrical turbulent flow column.
As shown in fig. 2, 3 and 6, the flow disturbing column is provided with a plurality of through holes on the incident flow surface, and the direction of the through holes is the same as the direction of the incoming flow. The diameter of the opening of each through hole is 0.5b, the distance between the through holes along the direction of the elliptical short semi-axis is 2b, the distance between the through holes along the direction of the height of the turbulence column is 5b, and the through holes are symmetrically distributed. The results show that: the pressure loss of the gas caused by the design is reduced by 42 percent and 25 percent respectively compared with the pressure loss of the cylindrical turbulence column and the elliptical turbulence column; the heat exchange capacity of the column is improved by 3% compared with that of a cylindrical turbulence column, but the heat exchange capacity is reduced compared with that of an elliptical turbulence column.
The utility model discloses another kind of mode can also be adopted: if the incident flow surface of one part of the turbulence columns is provided with a plurality of through holes, the direction of the through holes is the same as the incoming flow direction, and the incident flow surface of the other part of the turbulence columns is not provided with the through holes; the turbulence column through holes are uniformly distributed on the incident surface of the turbulence column, and the long axis direction of the upper end surface of the turbulence column is the same as the incoming flow direction. As shown in fig. 4, two types of spoiler structures are arranged and combined to optimize the overall performance, the spoiler structures of the first two rows are the spoiler structures of the type with reference to fig. 6, and the spoiler structures of the second two rows are the spoiler structures of the type with reference to fig. 5. The results show that: the gas pressure loss caused by the design is reduced by 36% compared with that of a cylindrical turbulent flow column, and the heat exchange capacity is improved by 18%.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (5)
1. A novel impact cooling turbulence structure is characterized by comprising an upper wall surface, a lower wall surface and a plurality of turbulence columns;
the flow disturbing column is columnar, the upper end face and the lower end face of the flow disturbing column are ellipses with the same shape, the middle section between the upper end face and the lower end face is an ellipse with the area smaller than that of the upper end face, the cylindrical surface of the flow disturbing column is in curve transition from the upper end face and the lower end face to the middle section, and long axes of the upper end face, the lower end face and the middle section are all parallel;
and if the interference flow column is arranged between the upper wall surface and the lower wall surface, a cooling channel is formed between the upper wall surface and the lower wall surface.
2. The novel impingement cooling flow-disturbing structure as claimed in claim 1, wherein the flow-disturbing column has a plurality of through holes on the flow-facing surface, and the through holes are arranged in the same direction as the incoming flow.
3. The novel impingement cooling flow-disturbing structure as claimed in claim 1, wherein if a plurality of through holes are provided on the incident flow surface of one part of the flow-disturbing columns, the direction of the through holes is the same as the direction of the incoming flow, and no through hole is provided on the incident flow surface of the other part of the flow-disturbing columns.
4. The novel impingement cooling flow-disturbing structure as claimed in claim 2, wherein the flow-disturbing pillar through holes are uniformly distributed on the flow-facing surface of the flow-disturbing pillar, and the long axis direction of the upper end surface of the flow-disturbing pillar is the same as the incoming flow direction.
5. The novel impingement cooling flow-disturbing structure as claimed in claim 4, wherein the radius of the cylindrical curved surface of the flow-disturbing column in the incoming flow direction is 11.1a, the radius in the spanwise direction is 19.8b, the length-to-short semi-axis ratio of the upper end surface to the lower end surface is 4a:2.25b, the length-to-short semi-axis ratio of the middle section is 2.8a:1.6b, the flow-disturbing column interval in the flow direction is 17a, the transverse interval is 16.5b, a and b are both preset length thresholds, and 4a is greater than 2.25 b.
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| CN201920327957.5U CN210105928U (en) | 2019-03-15 | 2019-03-15 | Novel impingement cooling turbulence structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109931114A (en) * | 2019-03-15 | 2019-06-25 | 南京航空航天大学 | A kind of novel impinging cooling turbulence structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109931114A (en) * | 2019-03-15 | 2019-06-25 | 南京航空航天大学 | A kind of novel impinging cooling turbulence structure |
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