CN109707532A - A kind of bridging type active cooling structure - Google Patents
A kind of bridging type active cooling structure Download PDFInfo
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- CN109707532A CN109707532A CN201811518567.2A CN201811518567A CN109707532A CN 109707532 A CN109707532 A CN 109707532A CN 201811518567 A CN201811518567 A CN 201811518567A CN 109707532 A CN109707532 A CN 109707532A
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- active cooling
- cooling structure
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- bridging type
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- 238000001816 cooling Methods 0.000 title claims abstract description 43
- 230000001154 acute effect Effects 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims 1
- 230000008646 thermal stress Effects 0.000 abstract description 5
- 208000020442 loss of weight Diseases 0.000 abstract description 4
- 238000005457 optimization Methods 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 9
- 239000010410 layer Substances 0.000 description 9
- 239000012530 fluid Substances 0.000 description 5
- 238000007664 blowing Methods 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000002346 layers by function Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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- Exhaust Silencers (AREA)
Abstract
The invention belongs to thermal protection technology fields, and in particular to a kind of bridging type active cooling structure.Active cooling structure of the invention uses the thought of segment design, is made up of cooling structure unit tile style overlap joint, the cooling structure unit is class ripple struction, including the area Shang Da (1), plate area (2)；The area Shang Da (1) is in " wave crest " shape with flat end, is provided with impact air film hole (3) thereon；The plate area (2) is provided with inclined hole (4).Using structure of the invention realize structure loss of weight optimization, thermal protection and infrared stealth purpose, and avoid due to temperature distribution is non-uniform and cause itself thermal stress increase the problem of.
Description
Technical field
The invention belongs to thermal protection technology fields, and in particular to a kind of bridging type active cooling structure.
Background technique
Currently, in the design of infrared stealth and the thermal protection of aircrafts exhaust pipe, using double-deck injection cooling exhaust pipe ten
Divide common.Exhaust inner tube layer is generally designed to an entirety, due to having biggish temperature gradient between ectonexine, inside and outside
It will lead to many problems in the case where double-deck all loads.It is primarily present following problems:
(1) there are radial pressures for exhaust pipe for high temperature core flow, and special-shaped exhaust pipe can not because of shape
Reach self-balancing；
(2) the double-deck injection cooling structure is applied in Design of Exhaust Manifold, is connected between inside and outside two layers and all loads
In the case of, since there are biggish temperature differences to generate high temperature thermal stress between ectonexine, structural failure may finally be will lead to；
(3) apply has one to cannot be neglected defect in the longitudinal corrugated plate heat screen of engine flame tube, integrates cold
Certain waviness is presented along flow direction for effect, and temperature distribution is non-uniform and the thermal stress of itself is caused to increase；
(4) exhaust pipe is very big along axial heated situation difference, and the tolerable temperature of most of light materials is very low.Cause
This considers that the tolerable temperature of material has to be larger than the requirement of structure maximum temperature, and exhaust pipe " internal layer " is designed to a whole gesture
The cost of weight must be sacrificed.
Summary of the invention
The purpose of the present invention is: a kind of bridging type active cooling structure is designed, realizes thermal protection index and infrared stealth mesh
Target simultaneously, with solve loss of weight optimization and eliminate inside configuration thermal mismatching and high temperature thermal stress the technical issues of.
To solve this technical problem, the technical scheme is that
A kind of bridging type active cooling structure, the bridging type active cooling structure uses segment design thought, by leading
Dynamic cooling unit overlap joint composition, the active cooling cell are class ripple struction, including the area Shang Da 1, plate area 2；Described
The area Shang Da 1 is in " wave crest " shape with flat end, is provided with impact air film hole 3 thereon；The plate area 2 is tabular, under
End regions are provided with inclined hole 4, and the angle α of the axis of inclined hole 4 and airflow direction is acute angle；The end in plate area 2 and the area Shang Da 1
Flat end overlap joint is fixed together.
The axis of the inclined hole 4 and the angle α of airflow direction are acute angle.
4 position of inclined hole is in lower end area.
The diameter of the impact air film hole 3 is 5mm.
The diameter of the inclined hole 4 is 3mm；Angle α range is 20 °~30 °.
The overlapping mode is connected by the way of riveting.
The beneficial effects of the present invention are: bridging type active cooling structure of the invention, using segment design, by cooling structure
Unit is overlapped by tile style and is formed, and is had the following beneficial effects:
(1) it is directly applied in the infrared stealth of exhaust pipe compared to by the double-deck injection cooling structure, " outer layer " is mainly negative
Bearing function and " internal layer " are blamed as just heat-insulating function layer.In the case where internal layer not load, avoid due to internal/external heating
High temperature thermal stress caused by uneven prevents structure thermal mismatching impaired；
(2) optimization is designed to longitudinal ripple wavy liner, using impacting gas at " wave crest " of ripple struction and thereon
The design of fenestra.Compared to " static pressure suction " gaseous film control, overflow heat exchange efficiency with higher.Meanwhile compared to longitudinal direction
Ripple heat screen, avoids the problem of temperature distribution is non-uniform；
(3) using the thought of " internal layer " initiating structure segment design, compared to by functional layer simple designs at an entirety,
Light material can be applied to the position not severe in heated situation.It is thereby achieved that the loss of weight of structure optimizes；
(4) for special-shaped jet pipe, ripple struction intensity with higher and wider bending critical load.Cause
This, " wave crest " design in the area Shang Da solves the problems, such as that special-shaped jet pipe can not self-balancing by radial force to a certain extent.
Detailed description of the invention
Fig. 1 overall structure diagram；
Fig. 2 active cooling cell schematic diagram；
Fig. 3 enlarged drawing X schematic diagram；
Fig. 4 enlarged drawing Y schematic diagram；
Fig. 5 assembling schematic diagram；
Fig. 6 operation principle schematic diagram.
Wherein, 1 be the area Shang Da, 2 be plate area, 3 be impact air film hole, 4 be inclined hole, X is on the right side of the area Shang Da 1 and plate area
The lap segment of end composition, Y are the inclined hole opened in plate area 2.
Specific embodiment
It is as follows that the present invention will be described in detail with reference to the accompanying drawings of the specification:
One, overall structure:
Bridging type active cooling structure of the invention use segment design thought, overall structure diagram as shown in Figure 1, by
Active cooling cell overlap joint composition, wherein active cooling cell schematic diagram is as shown in Fig. 2, the active cooling cell is class wave
Line structure, including the area Shang Da 1, plate area 2；The area Shang Da 1 is in " wave crest " shape with flat end, is provided with impact gas thereon
Fenestra 3；The plate area 2 is tabular, is provided with inclined hole 4, and the angle of the axis of inclined hole 4 and airflow direction in lower end area
α is acute angle, and enlarged drawing is as shown in Figure 4；The end in plate area 2 and the flat end overlap joint in the area Shang Da 1 are fixed together.It is described
Overlapping mode use riveting, enlarged drawing is as shown in Figure 3.The purpose of the flat segments of 2 right end of plate area: with it is adjacent
The left side area Shang Da of active cooling cell forms " complementation ", can keep the smooth of shape face in exhaust pipe as far as possible, reduction is to hair
The loss of motivation thrust.Meanwhile there are the lines of rabbet joint as cooling fluid enters high temperature between flat segments and the area Shang Da of adjacent cells
The runner of core flow.
The size of the impact air film hole 3 and inclined hole 4 under the premise of meeting cooling demand and is protected with parameters such as positions
Motor power loss reduction is demonstrate,proved, is calculated by numerical value and is determined with experimental method.
Two, design principle:
The active cooling structure is applied on special-shaped jet pipe, when structure is radially expanded effect by high temperature core flow, by
In ripple struction intensity with higher and wider bend loading, " wave crest " design can alleviate exhaust pipe can not self-balancing
Problem.In order to realize the loss of weight design of structure, segment design is carried out to the structure that cools of exhaust pipe, using special overlap joint
Mode links together various pieces.Since the thermal expansion coefficient between various pieces is different, special overlap joint design with it is upper
" wave crest " design for taking area 1 can partially remove the circumferential thermal mismatching problem with course.It corresponds to on engine flame tube
Longitudinal ripple wavy liner improve, the unit of the active cooling structure as exhaust pipe.2 right side of plate area of structural unit
End and the area Shang Da 1 overlapped using riveting, then by the bridging type active cooling structure by way of riveting with
Single layer is vented inside pipe wall connection, and specific assembling schematic diagram is as shown in Figure 5.Region between the active cooling structure and exhaust wall
For cold fluid pass, the air film impact opening 4 of natural bleed or by-pass air duct bleed from the area Shang Da 1 flow through the line of rabbet joint 6 subsequently into
High temperature core circulation road, and be attached to one layer of cooling air film trap heat of high temperature channel wall surface formation and enter exhaust pipe, and protect
Shield active cooling structure is not damaged by high temperature.Meanwhile another part cold fluid flows into height by being opened in the inclined hole 4 in plate area 2
Warm core circulation road is also attached to heat insulation and heat control on wall surface, and working principle is as shown in Figure 6.The size of air film hole and position for
Gas film cooling efficiency and motor power loss have relationship, under the premise of meeting cooling demand and guarantee that motor power damages
It loses minimum, can be calculated by numerical value and determine air blowing ratio and ratio of momentum with experimental method, to calculate its parameter, air blowing ratio and dynamic
The calculation for measuring ratio is as follows:
Air blowing ratio:
Ratio of momentum:
Wherein ρ represents the density of fluid, and v represents flow velocity, and g represents high temperature core flow, and c represents cold fluid.Air blowing ratio indicates
The close stream ratio of cold air and combustion gas, ratio of momentum then indicate the ratio of momentum of cold air and combustion gas, carry out after cold air injection with combustion gas quality with
The exchange of momentum, Film Cooling especially validity are largely dependent on the situation of both exchange process.Using CFD
Numerical simulation calculates the angle for determining air film hole axial direction and fluid flow direction between 20 °~30 °, and impact air film bore dia is 5mm,
Inclined hole diameter is 3mm, and acquired Film Cooling is best.
Claims (6)
1. a kind of bridging type active cooling structure, it is characterised in that: the bridging type active cooling structure uses segment design
Thought, be made of active cooling cell overlap joint, the active cooling cell is class ripple struction, including the area Shang Da (1), flat
Plate area (2)；The area Shang Da (1) is in " wave crest " shape with flat end, is provided with impact air film hole (3) thereon；Described is flat
Plate area (2) is tabular, and is provided with inclined hole (4)；The end in plate area (2) and the flat end of the area Shang Da (1) are overlapped and are fixed.
2. bridging type active cooling structure according to claim 1, it is characterised in that: the axis of the inclined hole (4) with
The angle α of airflow direction is acute angle.
3. bridging type active cooling structure according to claim 1, it is characterised in that: described inclined hole (4) position is under
End regions.
4. bridging type active cooling structure according to any one of claims 1 to 3, it is characterised in that: the overlap joint is solid
Mode is determined for riveting.
5. bridging type active cooling structure according to any one of claims 1 to 3, it is characterised in that: the impact gas
The diameter of fenestra (3) is 5mm.
6. bridging type active cooling structure according to claim 2 or 3, it is characterised in that: the diameter of the inclined hole (4)
For 3mm；Angle α range is 20 °~30 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811518567.2A CN109707532A (en) | 2018-12-12 | 2018-12-12 | A kind of bridging type active cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811518567.2A CN109707532A (en) | 2018-12-12 | 2018-12-12 | A kind of bridging type active cooling structure |
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| Publication Number | Publication Date |
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| CN109707532A true CN109707532A (en) | 2019-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811518567.2A Pending CN109707532A (en) | 2018-12-12 | 2018-12-12 | A kind of bridging type active cooling structure |
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| Country | Link |
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| CN (1) | CN109707532A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111707473A (en) * | 2020-06-19 | 2020-09-25 | 中航工程集成设备有限公司 | Engine test run injection cylinder with tile type lining plate protection structure and design method thereof |
| CN114412645A (en) * | 2021-12-26 | 2022-04-29 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204176685U (en) * | 2014-09-26 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner |
| CN204227466U (en) * | 2014-09-26 | 2015-03-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber burner inner liner wall cooling structure |
| CN104896514A (en) * | 2015-05-13 | 2015-09-09 | 广东电网有限责任公司电力科学研究院 | Anti-vibration heat insulation wall of main combustion chamber of gas turbine |
| CN108959822A (en) * | 2018-08-01 | 2018-12-07 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of design method reducing the effect of heat structure built-in thermal stress |
-
2018
- 2018-12-12 CN CN201811518567.2A patent/CN109707532A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204176685U (en) * | 2014-09-26 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner |
| CN204227466U (en) * | 2014-09-26 | 2015-03-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber burner inner liner wall cooling structure |
| CN104896514A (en) * | 2015-05-13 | 2015-09-09 | 广东电网有限责任公司电力科学研究院 | Anti-vibration heat insulation wall of main combustion chamber of gas turbine |
| CN108959822A (en) * | 2018-08-01 | 2018-12-07 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of design method reducing the effect of heat structure built-in thermal stress |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111707473A (en) * | 2020-06-19 | 2020-09-25 | 中航工程集成设备有限公司 | Engine test run injection cylinder with tile type lining plate protection structure and design method thereof |
| CN114412645A (en) * | 2021-12-26 | 2022-04-29 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
| CN114412645B (en) * | 2021-12-26 | 2023-01-31 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
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Application publication date: 20190503 |
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