CN109931114A - A kind of novel impinging cooling turbulence structure - Google Patents
A kind of novel impinging cooling turbulence structure Download PDFInfo
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- CN109931114A CN109931114A CN201910196357.4A CN201910196357A CN109931114A CN 109931114 A CN109931114 A CN 109931114A CN 201910196357 A CN201910196357 A CN 201910196357A CN 109931114 A CN109931114 A CN 109931114A
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- cooling
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- 238000001816 cooling Methods 0.000 title claims abstract description 34
- 230000007704 transition Effects 0.000 claims abstract description 4
- FWQHNLCNFPYBCA-UHFFFAOYSA-N fluoran Chemical compound C12=CC=CC=C2OC2=CC=CC=C2C11OC(=O)C2=CC=CC=C21 FWQHNLCNFPYBCA-UHFFFAOYSA-N 0.000 claims description 11
- 239000000112 cooling gas Substances 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 238000005243 fluidization Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 238000012913 prioritisation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000012809 cooling fluid Substances 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 239000002253 acid Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses a kind of novel impinging cooling turbulence structures, include upper wall surface, lower wall surface and several turbulence columns；Turbulence columns are in the form of a column, end face, lower end surface are the identical ellipse of shape thereon, middle section between upper surface, lower end surface is the ellipse that area is less than upper surface, and the cylinders of turbulence columns is by upper surface, lower end surface to middle section curved transition, and upper surface, lower end surface, the long axis of middle section are parallel；Several turbulence columns are arranged between upper wall surface, lower wall surface, so that forming cooling duct between upper wall surface, lower wall surface.After cooling gas carries out enhanced heat exchange by the turbulence columns group of cooling duct, flow pass.Novel flow-disturbing rod structure of the invention and combined method advantage are to can make full use of cooling gas, the pressure loss of the reduction cooling gas inside high-temperature component, and can improve the exchange capability of heat of flow-disturbing columnar region.
Description
Technical field
The present invention relates to gas turbine, high-temperature unit of aircraft engine is cooling and other are related to the field of impinging cooling,
More particularly to a kind of novel impinging cooling turbulence structure.
Background technique
Major impetus source of the gas turbine as aero-engine, is always the working centre of aeronautical technology personnel, combustion
Gas eddy turbine mainly pushes turbo blade rotation by high-temperature high-pressure fuel gas.
By thermodynamic cycle it is found that improving turbine entrance temperature temperature can be improved the efficiency of cycle and thrust ratio, therefore
Improving turbine entrance temperature temperature is to improve the important means of gas-turbine unit performance.It is continuous with turbine entrance temperature temperature
It improves, the hot ability to bear of turbo blade receives acid test, and in order to guarantee engine high-efficiency operation, turbine is safe and reliable
Work, needs to be continuously improved the hot ability to bear of turbo blade.It is usually efficient cold from new heat-resisting material and exploitation is synthesized
But technology is set out.
Currently, the exploitation of efficient cooling technology has been achieved with many achievements, being provided with turbulence columns is that turbo blade is cold
But one of effective measures.Turbulence columns are arranged inside the turbine disk, the positions such as turbo blade internal cooling channel, cooling fluid stream
When through turbulence columns group, cooling gas generates boundary layer separation and reaches cooling turbine bucket to enhance the cooling effect of gas
Purpose.
For Gas Turbine disk and turbo blade, the setting of turbulence columns can not only play enhancing heat exchange
Effect, but also the structural strength for enhancing the component can be played.
There is following limitation in existing impinging cooling turbulence structure:
The flow-disturbing rod structure currently generallyd use is circular columns, water-drop-shaped column etc., and circular cylindrical shape turbulence columns have preferable heat exchange
Ability, but the cooling fluid pressure loss is larger；The water droplet column turbulence columns bring pressure loss is lower, but its exchange capability of heat
It is restricted.
Summary of the invention
The technical problem to be solved by the present invention is to provide a kind of Novel flushing for defect involved in background technique
Cooling turbulence structure is hit, that is, reduces the pressure loss of cooling gas, and improves cooling capacity to the greatest extent.
The present invention uses following technical scheme to solve above-mentioned technical problem:
A kind of novel impinging cooling turbulence structure includes upper wall surface, lower wall surface and several turbulence columns；
The turbulence columns are in the form of a column, thereon end face, lower end surface be the identical ellipse of shape, between upper surface, lower end surface in cut
Face is the ellipse that area is less than upper surface, and the cylinders of turbulence columns is by upper surface, lower end surface to middle section curved transition, and upper end
Face, lower end surface, the long axis of middle section are parallel；
Several turbulence columns are arranged between upper wall surface, lower wall surface, so that forming cooling duct between upper wall surface, lower wall surface.
After cooling gas carries out enhanced heat exchange by the turbulence columns group of cooling duct, flow pass.
As a kind of novel further prioritization scheme of impinging cooling turbulence structure of the present invention, the fluoran stream surface of the turbulence columns
Several through-holes are equipped with, the direction of the through-hole is identical with direction of flow.
As a kind of novel further prioritization scheme of impinging cooling turbulence structure of the present invention, one in several turbulence columns
The fluoran stream surface of part turbulence columns is identical with direction of flow equipped with several through-holes, the direction of through-hole, and another part turbulence columns are met
Through-hole is not set on stream interface.
As a kind of novel further prioritization scheme of impinging cooling turbulence structure of the present invention, the turbulence columns through-hole is being disturbed
The fluoran stream surface of fluidization tower is uniformly distributed, and the long axis direction of turbulence columns upper surface is identical with direction of flow.
As a kind of novel further prioritization scheme of impinging cooling turbulence structure of the present invention, the cylinder curved surface edge of turbulence columns
Flowing to radius is 11.1a, and extending to radius is 19.8b, and upper surface, lower end surface length semiaxis ratio are 4a:2.25b, middle section
Length semiaxis ratio is 2.8a:1.6b, and turbulence columns are 17a along spacing is flowed to, and horizontal spacing 16.5b, a, b are preset
Length threshold, and 4a is greater than 2.25b.
The invention adopts the above technical scheme compared with prior art, has following technical effect that
1. the turbulence columns type mainly used cannot be considered in terms of heat exchange for straight cylinder for general impinging cooling
It is required of both ability and the pressure loss.
2. the turbulence columns of crescent shape elliptic design, section is ellipse, meets airflow design, and cylinder is using bent
Face design, reduces the front face area of turbulence columns, therefore reduce the pressure loss of cooling gas, the pressure loss is more cylindrical
Turbulence columns are reduced,；By being averaged the calculating of nusselt number to bottom surface on channel, the average nusselt number of type design is high
In the average nusselt number of round turbulence columns and oval turbulence columns, i.e., its exchange capability of heat is higher than round turbulence columns and ellipse is disturbed
Fluidization tower.
3. the turbulence columns of the crescent shape elliptic design of partially perforation, to above-mentioned turbulence columns fluoran stream surface aperture, to cooling air
Body further shunts, and largely reduces the pressure loss of gas, and the more cylindrical turbulence columns pressure loss reduces degree most
Greatly, the more cylindrical turbulence columns of exchange capability of heat increase.
4. the turbulence columns of the crescent shape ellipse turbulence columns Combination Design of crescent shape ellipse and partially perforation, pass through two
The permutation and combination of seed type turbulence columns, so that overall performance obtains comprehensive promotion.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is the structure top view that turbulence columns of the present invention are respectively provided with through-hole；
Fig. 3 is the structural schematic diagram that turbulence columns of the present invention are respectively provided with through-hole；
Fig. 4 is the structural schematic diagram of a part of turbulence columns setting through-hole of the present invention；
Fig. 5 is the structural schematic diagram of the turbulence columns of not set through-hole in the present invention；
Fig. 6 is the structural schematic diagram of the turbulence columns in the present invention provided with through-hole.
In figure, 1- channel outlet, the hole in 2- turbulence columns, 3- feeder connection, crescent shape ellipse turbulence columns 4- with holes,
5- crescent shape ellipsoidal structure turbulence columns.
Specific embodiment
Technical solution of the present invention is described in further detail with reference to the accompanying drawing:
The present invention can be embodied in many different forms, and should not be assumed that be limited to the embodiments described herein.On the contrary, providing
These embodiments are thoroughly and complete to make the disclosure, and will give full expression to the scope of the present invention to those skilled in the art.
In the accompanying drawings, for the sake of clarity it is exaggerated component.
The invention discloses a kind of novel impinging cooling turbulence structures, include upper wall surface, lower wall surface and several turbulence columns；Such as
Shown in Fig. 5, turbulence columns are in the form of a column, thereon end face, lower end surface be the identical ellipse of shape, between upper surface, lower end surface in cut
Face is the ellipse that area is less than upper surface, and the cylinders of turbulence columns is by upper surface, lower end surface to middle section curved transition, and upper end
Face, lower end surface, the long axis of middle section are parallel；Several turbulence columns are arranged between upper wall surface, lower wall surface, so that upper wall
Cooling duct is formed between face, lower wall surface.After cooling gas carries out enhanced heat exchange by the turbulence columns group of cooling duct, outflow is logical
Road.
As shown in Figure 1, cooling air-flow enters turbulence columns group from right channel mouth, turbulence columns area designed by Fig. 1 is flowed through, is disturbed
Fluidization tower circumferential surface is surface blending, and the cylinder curved surface of turbulence columns is 11.1a along radius is flowed to, and extending to radius is 19.8b, upper end
Face, lower end surface length semiaxis ratio are 4a:2.25b, and the length semiaxis ratio of middle section is 2.8a:1.6b, and turbulence columns edge flows to spacing
For 17a, horizontal spacing 16.5b.As a result, it has been found that: in the identical situation of primary condition, compared to cylindrical turbulence columns, figure one
Design can reduce 33% pressure loss, and 7% exchange capability of heat can be improved.
As shown in Fig. 2, Fig. 3, Fig. 6, the fluoran stream surface of turbulence columns is equipped with several through-holes, the direction of through-hole and direction of flow phase
Together.The opening diameter of through-hole is 0.5b, and it is 5b along turbulence columns short transverse, that through-hole, which is 2b along oval semi-minor axis direction spacing,
It is symmetrical.The result shows that: pressure loss caused by the design more cylindrical turbulence columns and oval turbulence columns respectively
The pressure loss reduce 42% and 25%；The more cylindrical turbulence columns of its exchange capability of heat improve 3%, but compared with oval turbulence columns
Exchange capability of heat decreases.
The present invention can also use another way: the fluoran stream surface of a part of turbulence columns is equipped with several in several turbulence columns
Through-hole, the direction of through-hole are identical with direction of flow, do not set through-hole on the fluoran stream surface of another part turbulence columns；Turbulence columns through-hole is being disturbed
The fluoran stream surface of fluidization tower is uniformly distributed, and the long axis direction of turbulence columns upper surface is identical with direction of flow.As shown in figure 4, passing through row
Column two kinds of flow-disturbing rod structures of combination, so that overall performance reaches optimum value, preceding two rows turbulence columns select the flow-disturbing for referring to Fig. 6 type
Column, it is rear two rows of using the turbulence columns for referring to Fig. 5 type.The result shows that: pressure loss caused by the design is more cylindrical to disturb
Fluidization tower reduces 36%, and exchange capability of heat improves 18%.
Those skilled in the art can understand that unless otherwise defined, all terms used herein (including skill
Art term and scientific term) there is meaning identical with the general understanding of those of ordinary skill in fields of the present invention.Also
It should be understood that those terms such as defined in the general dictionary should be understood that have in the context of the prior art
The consistent meaning of meaning will not be explained in an idealized or overly formal meaning and unless defined as here.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not limited to this hair the foregoing is merely a specific embodiment of the invention
Bright, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (5)
1. a kind of novel impinging cooling turbulence structure, which is characterized in that include upper wall surface, lower wall surface and several turbulence columns；
The turbulence columns are in the form of a column, thereon end face, lower end surface be the identical ellipse of shape, between upper surface, lower end surface in cut
Face is the ellipse that area is less than upper surface, and the cylinders of turbulence columns is by upper surface, lower end surface to middle section curved transition, and upper end
Face, lower end surface, the long axis of middle section are parallel；
Several turbulence columns are arranged between upper wall surface, lower wall surface, so that forming cooling duct between upper wall surface, lower wall surface.
2. novel impinging cooling turbulence structure according to claim 1, which is characterized in that on the fluoran stream surface of the turbulence columns
Equipped with several through-holes, the direction of the through-hole is identical with direction of flow.
3. novel impinging cooling turbulence structure according to claim 1, which is characterized in that one in several turbulence columns
Divide the fluoran stream surface of turbulence columns identical with direction of flow equipped with several through-holes, the direction of through-hole, another part turbulence columns meet stream
Through-hole is not set on face.
4. novel impinging cooling turbulence structure according to claim 2, which is characterized in that the turbulence columns through-hole is in flow-disturbing
The fluoran stream surface of column is uniformly distributed, and the long axis direction of turbulence columns upper surface is identical with direction of flow.
5. novel impinging cooling turbulence structure according to claim 4, which is characterized in that the cylinder curved surface of turbulence columns is along next
Stream direction radius is 11.1a, and extending to radius is 19.8b, and upper surface, lower end surface length semiaxis ratio are 4a:2.25b, middle section
Length semiaxis ratio be 2.8a:1.6b, turbulence columns along flow to spacing be 17a, horizontal spacing 16.5b, a, b are to preset
Length threshold, and 4a be greater than 2.25b.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910196357.4A CN109931114A (en) | 2019-03-15 | 2019-03-15 | A kind of novel impinging cooling turbulence structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910196357.4A CN109931114A (en) | 2019-03-15 | 2019-03-15 | A kind of novel impinging cooling turbulence structure |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112178691A (en) * | 2020-10-27 | 2021-01-05 | 西北工业大学 | Double-wall cooling structure with air film hole hyperbolic turbulence column |
| CN113225997A (en) * | 2021-05-13 | 2021-08-06 | 西北工业大学 | Take enhancement of multistage cylindrical boss to strike heat transfer structure |
| CN113309578A (en) * | 2021-03-22 | 2021-08-27 | 南京航空航天大学 | Novel trough of belt turbulent flow post structure |
| CN114517921A (en) * | 2022-03-15 | 2022-05-20 | 西北工业大学 | Oil thrower with water drop type turbulence column |
| CN114838387A (en) * | 2022-04-28 | 2022-08-02 | 西北工业大学 | Oil thrower with impact jet flow disturbing column |
| CN115111944A (en) * | 2022-05-31 | 2022-09-27 | 哈尔滨工程大学 | Cylindrical turbulent flow type corrugated plate heat exchange structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120255311A1 (en) * | 2011-04-06 | 2012-10-11 | Yoshiaki Miyake | Cooling structure, gas turbine combustor and manufacturing method of cooling structure |
| CN102828781A (en) * | 2011-06-16 | 2012-12-19 | 中航商用航空发动机有限责任公司 | Fuel gas turbine cooling blade |
| CN107503801A (en) * | 2017-08-18 | 2017-12-22 | 沈阳航空航天大学 | A kind of efficiently array jetting cooling structure |
| CN108223022A (en) * | 2018-01-04 | 2018-06-29 | 沈阳航空航天大学 | A kind of turbulence structure in array jetting cooling |
| CN210105928U (en) * | 2019-03-15 | 2020-02-21 | 南京航空航天大学 | Novel impingement cooling turbulence structure |
-
2019
- 2019-03-15 CN CN201910196357.4A patent/CN109931114A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120255311A1 (en) * | 2011-04-06 | 2012-10-11 | Yoshiaki Miyake | Cooling structure, gas turbine combustor and manufacturing method of cooling structure |
| CN102828781A (en) * | 2011-06-16 | 2012-12-19 | 中航商用航空发动机有限责任公司 | Fuel gas turbine cooling blade |
| CN107503801A (en) * | 2017-08-18 | 2017-12-22 | 沈阳航空航天大学 | A kind of efficiently array jetting cooling structure |
| CN108223022A (en) * | 2018-01-04 | 2018-06-29 | 沈阳航空航天大学 | A kind of turbulence structure in array jetting cooling |
| CN210105928U (en) * | 2019-03-15 | 2020-02-21 | 南京航空航天大学 | Novel impingement cooling turbulence structure |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112178691A (en) * | 2020-10-27 | 2021-01-05 | 西北工业大学 | Double-wall cooling structure with air film hole hyperbolic turbulence column |
| CN113309578A (en) * | 2021-03-22 | 2021-08-27 | 南京航空航天大学 | Novel trough of belt turbulent flow post structure |
| CN113309578B (en) * | 2021-03-22 | 2022-04-05 | 南京航空航天大学 | Novel trough of belt turbulent flow post structure |
| CN113225997A (en) * | 2021-05-13 | 2021-08-06 | 西北工业大学 | Take enhancement of multistage cylindrical boss to strike heat transfer structure |
| CN114517921A (en) * | 2022-03-15 | 2022-05-20 | 西北工业大学 | Oil thrower with water drop type turbulence column |
| CN114838387A (en) * | 2022-04-28 | 2022-08-02 | 西北工业大学 | Oil thrower with impact jet flow disturbing column |
| CN115111944A (en) * | 2022-05-31 | 2022-09-27 | 哈尔滨工程大学 | Cylindrical turbulent flow type corrugated plate heat exchange structure |
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Application publication date: 20190625 |