CN204024854U - A kind of sphere convergence binary vector spray cooling structure - Google Patents
A kind of sphere convergence binary vector spray cooling structure Download PDFInfo
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- CN204024854U CN204024854U CN201420464165.XU CN201420464165U CN204024854U CN 204024854 U CN204024854 U CN 204024854U CN 201420464165 U CN201420464165 U CN 201420464165U CN 204024854 U CN204024854 U CN 204024854U
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Abstract
A kind of sphere convergence binary vector spray cooling structure, it is characterized in that, comprise spherical cylindrical shell, spherical convergence adjustment sheet, spherical cylindrical shell and spherical convergence adjustment sheet adopt double side walls structure, spherical cylindrical shell maintains static, spherical convergence adjustment sheet slides around the centre of sphere at spherical cylinder lumen, and spherical convergence adjustment sheet has straight hole near the sidewall of hot combustion gas one side; On the sidewall of spherical cylindrical shell near combustion gas one side, have inclined hole.It is cooling that the utility model adopts the multiple high efficiency composition type of cooling to carry out jet pipe wall, and cooling air utilization ratio is high, can reduce cooling air consumption.During intermediateness, gas flows through from double-deck wall interlayer, utilizes fin structure strengthening convection current cooling, and cooling effectiveness is high, and it is cooling that internal face adopts air film simultaneously, good cooling results; During maximum rating, the gas of wall cooling passage impacts the heat exchange of many inclined holes to jet pipe hot junction wall, and many inclined holes wall has been strengthened the convection heat exchange of cooling blast and many inclined holes pars intramuralis, and heat transfer effect improves greatly.
Description
Technical field
The utility model relates to aeroengine jet pipe field, is mainly used in the wall cooling structure of aviation engine shaft symmetroid vector spray, is also applicable to other sphere with similar spheric structure cooling simultaneously.
Background technique
Sphere convergence binary vector spray is a kind of advanced person's multi-functional binary vector spray structure, this jet pipe converging portion is spherical, extending section is rectangle, runner directly occurs in venturi from circle to nonaxisymmetrical transition, cancel the runner of binary vector spray by the changeover portion of the circle side of turning, relied on sphere section around the rotation of the centre of sphere, to carry out the different conditions (Fig. 1) of adjustable jet tube.Because jet pipe inner flow passage profile is complicated, be subject to high-temperature fuel gas and easily produce thermal distortion, mechanism is rotated and be affected.Therefore need to take suitable cooling method to jet pipe wall, make flap temperature stabilization within the scope of material ability to bear, prevent the adjusting of excessive influence of thermal deformation nozzle throat area.Meanwhile, a key character of sphere convergence binary vector spray is to strengthen jet flow and Flow Field outside Gas Mixing in Cross flow, reduces infrared radiation.Jet pipe wall surface temperature is carried out cooling, to reduce its surface temperature, be conducive to reduce the infrared intensity of jet pipe, thereby meet the infrared stealth requirement of motor.
Model utility content
The purpose of this utility model is: propose a kind of sphere simple in structure convergence binary vector spray wall cooling structure.
The technical solution of the utility model is: a kind of sphere convergence binary vector spray wall cooling structure, comprises shape cylindrical shell 1, spherical convergence adjustment sheet 2.
Be specially: spherical cylindrical shell 1 and spherical convergence adjustment sheet 2 adopt double side walls structure, and spherical cylindrical shell 1 maintains static, and spherical convergence adjustment sheet 2 slides around the centre of sphere at spherical cylindrical shell 1 inner chamber, and spherical convergence adjustment sheet 2 has straight hole near the sidewall of hot combustion gas one side; On the sidewall of spherical cylindrical shell 1 near combustion gas one side, have inclined hole.It is characterized in that: the inclined hole on spherical cylindrical shell 1 is divided into 5～8 rows, 100～150 of sums vertically.Straight hole diameter on spherical convergence adjustment sheet 2 is φ 2～3mm, is divided into vertically 5～20 rows, and every row is along circumferentially uniform, and total number is 60～2000.
When jet pipe mediates state, between spherical convergence adjustment sheet and spherical cylindrical shell, overlap, now cooled gas flows between two-layer thin-walled, can carry out effective convection current to hot wall face cooling, on this external 1 spherical cylindrical shell and 2 spherical convergence adjustment sheets, form the cooling air film of one deck, can carry out air film to hot combustion gas cooling; And when jet pipe is during in Afterburning condition, spherical convergence adjustment sheet rotates forward, slide in the interlayer of spherical cylindrical shell, cooling air is flowed in the cooling channel of convergence adjustment sheet uniformly by spherical cylindrical shell interlayer, now gas first impacts straight hole by spherical convergence adjustment sheet, many inclined holes wall is impacted cooling, then from spherical cylindrical shell inclined hole, flow out, at hot side wall surface, form full coverage air film cooling.
The utility model has the advantages that: adopt the multiple high efficiency composition type of cooling to carry out jet pipe wall cooling, cooling air utilization ratio is high, can reduce cooling air consumption.During intermediateness, gas flows through from double-deck wall interlayer, utilizes fin structure strengthening convection current cooling, and cooling effectiveness is high, and it is cooling that internal face adopts air film simultaneously, good cooling results; During maximum rating, the gas of wall cooling passage impacts the heat exchange of many inclined holes to jet pipe hot junction wall, and many inclined holes wall has been strengthened the convection heat exchange of cooling blast and many inclined holes pars intramuralis, and heat transfer effect improves greatly.
Accompanying drawing explanation
The signal of Fig. 1 sphere convergence two-dimensional nozzle basic structure
Fig. 2 sphere convergence binary vector spray structure and type of cooling schematic diagram
Fig. 3 sphere convergence binary vector spray cooling channel partial enlarged drawing
Fig. 4 air film hole distributes and illustrates
Embodiment
Embodiment 1
Below the utility model is described in further details.Referring to Fig. 1～Fig. 3, the technical solution of the utility model is: a kind of sphere convergence binary vector spray wall cooling structure, comprises spherical cylindrical shell 1, spherical convergence adjustment sheet 2.
Be specially: spherical cylindrical shell 1 and spherical convergence adjustment sheet 2 adopt double side walls structure, and spherical cylindrical shell 1 maintains static, and spherical convergence adjustment sheet 2 slides around the centre of sphere at spherical cylindrical shell 1 inner chamber, and spherical convergence adjustment sheet 2 has straight hole near the sidewall of hot combustion gas one side; On the sidewall of spherical cylindrical shell 1 near combustion gas one side, have inclined hole.It is characterized in that: the inclined hole on spherical cylindrical shell 1 is divided into 5～8 rows, 100～150 of sums vertically.Straight hole diameter on spherical convergence adjustment sheet 2 is φ 2～3mm, is divided into vertically 5～20 rows, and every row is along circumferentially uniform, and total number is 60～2000;
When jet pipe mediates state, between spherical convergence adjustment sheet and spherical cylindrical shell, overlap, now cooled gas flows between two-layer thin-walled, can carry out effective convection current to hot wall face cooling, on this external 1 spherical cylindrical shell and 2 spherical convergence adjustment sheets, form the cooling air film of one deck, can carry out air film to hot combustion gas cooling; And when jet pipe is during in Afterburning condition, spherical convergence adjustment sheet rotates forward, slide in the interlayer of spherical cylindrical shell, cooling air is flowed in the cooling channel of convergence adjustment sheet uniformly by spherical cylindrical shell interlayer, now gas first impacts straight hole by spherical convergence adjustment sheet, many inclined holes wall is impacted cooling, then from spherical cylindrical shell inclined hole, flow out, at hot side wall surface, form full coverage air film cooling.
Claims (3)
1. a sphere is restrained binary vector spray cooling structure, it is characterized in that, comprise spherical cylindrical shell (1), spherical convergence adjustment sheet (2), spherical cylindrical shell (1) and spherical convergence adjustment sheet (2) adopt double side walls structure, spherical cylindrical shell (1) maintains static, spherical convergence adjustment sheet (2) slides around the centre of sphere at spherical cylindrical shell (1) inner chamber, and spherical convergence adjustment sheet (2) has straight hole near the sidewall of hot combustion gas one side; Spherical cylindrical shell (1) has inclined hole near on the sidewall of combustion gas one side.
2. sphere according to claim 1 is restrained binary vector spray cooling structure, it is characterized in that, the straight hole diameter on described spherical convergence adjustment sheet (2) is φ 2～3mm, is divided into vertically 5～20 rows, every row is along circumferentially uniform, and total number is 60～2000.
3. sphere convergence binary vector spray cooling structure according to claim 1, is characterized in that, the inclined hole on described spherical cylindrical shell (1) is divided into 5～8 rows, 100～150 of sums vertically.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420464165.XU CN204024854U (en) | 2014-08-17 | 2014-08-17 | A kind of sphere convergence binary vector spray cooling structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420464165.XU CN204024854U (en) | 2014-08-17 | 2014-08-17 | A kind of sphere convergence binary vector spray cooling structure |
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| CN204024854U true CN204024854U (en) | 2014-12-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420464165.XU Expired - Fee Related CN204024854U (en) | 2014-08-17 | 2014-08-17 | A kind of sphere convergence binary vector spray cooling structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104863750A (en) * | 2015-05-07 | 2015-08-26 | 南京航空航天大学 | Impingement and air-film cooling structure adopting variable-hole array pitches used for wall surface of jet tube |
| CN109184947A (en) * | 2018-10-11 | 2019-01-11 | 西北工业大学 | A kind of Integral rotary convergence vector spray |
| CN109882314A (en) * | 2019-03-08 | 2019-06-14 | 西北工业大学 | The double wall cooling structure with transverse wave impact orifice plate for vector spray |
| CN111577481A (en) * | 2020-05-26 | 2020-08-25 | 中国航发沈阳发动机研究所 | Cooling channel structure suitable for binary stealthy spray tube |
| CN113107705A (en) * | 2021-04-08 | 2021-07-13 | 西北工业大学 | double-S-shaped bent contraction and expansion spray pipe with infrared suppression measure |
| CN113217225A (en) * | 2021-06-21 | 2021-08-06 | 中国航发沈阳发动机研究所 | Binary spray pipe structure for injecting cold air in engine compartment |
| CN113482796A (en) * | 2021-06-01 | 2021-10-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Spray pipe configuration of rib structure of discontinuous mixed support plate |
-
2014
- 2014-08-17 CN CN201420464165.XU patent/CN204024854U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104863750A (en) * | 2015-05-07 | 2015-08-26 | 南京航空航天大学 | Impingement and air-film cooling structure adopting variable-hole array pitches used for wall surface of jet tube |
| CN109184947A (en) * | 2018-10-11 | 2019-01-11 | 西北工业大学 | A kind of Integral rotary convergence vector spray |
| CN109882314A (en) * | 2019-03-08 | 2019-06-14 | 西北工业大学 | The double wall cooling structure with transverse wave impact orifice plate for vector spray |
| CN109882314B (en) * | 2019-03-08 | 2021-09-10 | 西北工业大学 | Double-walled cooling structure with transverse corrugated impingement orifice plate for a vectoring nozzle |
| CN111577481A (en) * | 2020-05-26 | 2020-08-25 | 中国航发沈阳发动机研究所 | Cooling channel structure suitable for binary stealthy spray tube |
| CN111577481B (en) * | 2020-05-26 | 2022-11-22 | 中国航发沈阳发动机研究所 | Cooling channel structure suitable for binary stealthy spray tube |
| CN113107705A (en) * | 2021-04-08 | 2021-07-13 | 西北工业大学 | double-S-shaped bent contraction and expansion spray pipe with infrared suppression measure |
| CN113482796A (en) * | 2021-06-01 | 2021-10-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Spray pipe configuration of rib structure of discontinuous mixed support plate |
| CN113482796B (en) * | 2021-06-01 | 2022-09-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Spray pipe configuration of rib structure of discontinuous mixed support plate |
| CN113217225A (en) * | 2021-06-21 | 2021-08-06 | 中国航发沈阳发动机研究所 | Binary spray pipe structure for injecting cold air in engine compartment |
| CN113217225B (en) * | 2021-06-21 | 2022-06-07 | 中国航发沈阳发动机研究所 | Binary spray pipe structure for injecting cold air in engine compartment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141217 Termination date: 20160817 |