CN107829840A - Axial symmetry plug nozzle support plate cooling structure and there is its aero-engine - Google Patents
Axial symmetry plug nozzle support plate cooling structure and there is its aero-engine Download PDFInfo
- Publication number
- CN107829840A CN107829840A CN201711103243.8A CN201711103243A CN107829840A CN 107829840 A CN107829840 A CN 107829840A CN 201711103243 A CN201711103243 A CN 201711103243A CN 107829840 A CN107829840 A CN 107829840A
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- China
- Prior art keywords
- support plate
- plug
- wall
- cooling structure
- cooling
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to aero-engine spray bar technology field, specifically provide axial symmetry plug nozzle support plate cooling structure, one end of jet pipe support plate is with starting machine drum body to be connected, the other end and plug cone connection, jet pipe support plate includes outer wall and inwall, cooling duct is formed between outer wall and inwall, outer wall is provided with multiple rows of air film hole, the quantity of air film hole increases with close to plug cone, multiple rows of turbulence columns are provided with cooling duct, the both ends of turbulence columns are connected with outer wall and inwall respectively, and the quantity of turbulence columns increases with close to plug cone.The present invention is high according to temperature in center, the low situation of sleeve wall surface temperature, to efficiently being cooled down by paracentral position, simply cooled down close to the position of sleeve, it is different according to pressure, surface pressure is big windward for plug cone, increase cooling effect only with turbulence columns, lee face adds air film hole cooling, using the different types of cooling, reach saving air conditioning quantity, the purpose efficiently cooled down.
Description
Technical field
The present invention relates to aero-engine spray bar technology field, more particularly to axial symmetry plug nozzle support plate cooling structure and
With its aero-engine.
Background technology
Plug nozzle has the advantages that high blow down ratio and high Stealth Fighter, and application prospect is extensive.But in axial symmetry plug nozzle,
Plug cone support plate is washed away by incoming high-temperature fuel gas, and wall surface temperature is very high, often exceeds material heat resisting temperature, causes ablation, influences
Lance life, and support plate mechanism small volume, cooling structure is difficult, cooling effect is low.Limited by support plate wall surface temperature is too high, sternly
Jet pipe and host performance are have impact on again.
The pneumatic and temperature conditions of existing axial plug nozzle burst diaphragm cone support plate cooling scheme and uncombined jet pipe, which optimizes, to be set
Meter, it has the disadvantage that：
1) gas flow temperature and pressure distribution are uneven in jet pipe, relatively low close to sleeve portion temperature, and center temperature is high,
That is the Temperature Distribution of plug cone branch plate surface is widely different, and existing cooling technology is cold according to actual conditions progress differentiation
But, causing plug to bore, support plate surface temperature difference is big, and thermal stress is big；
2) plug cone support plate windward side and lee face pressure gap are huge, and existing cooling structure makes the utilization of no differentiation
Gas is cooled down, the waste of air conditioning quantity is caused, could not efficiently cool down；
3) branch harden structure is small, and suffered impulsive force is big, and thermic load is big, and simple cooling technology does not consider its structure
The factors such as intensity.
The content of the invention
To overcome at least one defect existing for above-mentioned prior art, the invention provides axial symmetry plug nozzle support plate is cold
But structure, one end of jet pipe support plate with starting machine drum body to be connected, the other end with plug cone connection, the jet pipe support plate include outer wall and
Inwall, forms cooling duct between the outer wall and the inwall, the outer wall is provided with multiple rows of air film hole, the number of the air film hole
Amount increases with being bored close to the plug.
Preferably, be provided with multiple rows of turbulence columns in the cooling duct, the both ends of the turbulence columns respectively with the outer wall and
The inwall connection, and the quantity of the turbulence columns increases with being bored close to the plug.
Preferably, the jet pipe support plate be circumferentially distributed in it is described start between machine drum body and the plug cone, its quantity is 3~
8.
Preferably, the air film hole is distributed in wrong row, and its quantity is 34~56.
Preferably, the turbulence columns are distributed in wrong row, and its quantity is 40~60.
Present invention also offers aero-engine, and it includes above-mentioned axial symmetry plug nozzle support plate cooling structure.
Axial symmetry plug nozzle support plate cooling structure provided by the invention and there is its aero-engine, have has as follows
Beneficial effect：
1st, plug cone support plate surface temperature is effectively reduced, ensures that plug cone support plate is not ablated, ensures jet pipe safety；
2nd, it is high according to temperature in center, the low situation of sleeve wall surface temperature, to efficiently being cooled down by paracentral position,
Simply cooled down close to the position of sleeve, different according to pressure, surface pressure is big windward for plug cone, increases cooling effect only with turbulence columns
Fruit, lee face add air film hole cooling, using the different types of cooling, reach saving air conditioning quantity, the purpose efficiently cooled down.
Brief description of the drawings
Embodiment below with reference to accompanying drawing description is exemplary, it is intended to for the explanation and illustration present invention, and can not be managed
Solve as the limitation to protection scope of the present invention.
Fig. 1 is the schematic perspective view of support plate cooling structure provided by the invention；
Fig. 2 is Fig. 1 top view；
Fig. 3 is Fig. 1 vertical view cutaway drawing；
Fig. 4 is the partial enlarged drawing inside support plate cooling structure provided by the invention；
Fig. 5 is the structural representation that the present invention applies in aero-engine.
Reference：
10 jet pipe support plates
11 outer walls
12 inwalls
20 cooling ducts
30 air film holes
40 turbulence columns
80 start machine drum body
90 plug cones
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.
It should be noted that：In the accompanying drawings, from beginning to end same or similar label represent same or similar element or
Element with same or like function.Described embodiment is part of the embodiment of the present invention, rather than whole implementation
Example, in the case where not conflicting, the feature in embodiment and embodiment in the application can be mutually combined.Based in the present invention
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made,
Belong to the scope of protection of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of and describes the present invention and simplify description, rather than indicates or imply meaning
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention be protected
Protect the limitation of scope.
Herein, " schematic " expression " serving as example, example or explanation ", will should not be described herein as " showing
Any diagram, the embodiment of meaning property " are construed to a kind of preferred or more advantageous technical scheme.
As shown in Figures 1 and 2, the invention provides axial symmetry plug nozzle support plate cooling structure, including jet pipe support plate 10,
With starting machine drum body 80 to be connected, the other end is connected with plug cone 90 for one end of jet pipe support plate 10, and jet pipe support plate 10 is circumferential to be distributed in hair
Between motivation cylinder 80 and plug cone 90, its quantity is 3~8.
As shown in Figures 2 and 3, jet pipe support plate 10 includes outer wall 11 and inwall 12, is formed between outer wall 11 and inwall 12 cold
But passage 20, outer wall 11 are provided with multiple rows of air film hole 30, and being often vented fenestra 30 includes multiple air film holes 30, and cooling gas is logical by cooling down
The top of road 20 enters to be cooled down to jet pipe support plate 10, and is flowed out from air film hole 30.Due to the regional temperature closer to plug cone 90
It is higher, more need to cool down, therefore the quantity of air film hole 30 increases with boring 90 close to plug in the present invention, i.e., on jet pipe support plate 10
For air film hole 30 closer to plug cone 90, air film hole 30 is more intensive, and percent opening is bigger, is often vented the quantity of air film hole 30 that fenestra 30 includes
More, air film hole 30 is distributed in wrong row, and its quantity is 34~56.By taking different coolings to plug cone support plate different zones
Mode, solve plug cone support plate surface temperature inequality situation, and saving air conditioning quantity is reached with this, the purpose efficiently cooled down.
As shown in Figures 2 and 4, in one of embodiment provided by the invention, multiple rows of disturb is provided with cooling duct 20
Fluidization tower 40, the both ends of turbulence columns 40 are connected with outer wall 11 and inwall 12 respectively, and the quantity of turbulence columns 40 with close to plug bore 90 and
Increase, turbulence columns 40 are more intensive closer to plug cone 90, and the quantity of turbulence columns 40 that often row's turbulence columns 40 include is more, is reached with this
Increase the purpose of cooling effectiveness.Turbulence columns 40 are distributed in wrong row, and its quantity is 40~60.
As shown in figure 5, present invention also offers aero-engine, it includes above-mentioned axial symmetry plug nozzle support plate and cooled down
Structure, engine jet pipe is cooled down by the support plate cooling structure.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (6)
1. axial symmetry plug nozzle support plate cooling structure, it is characterised in that：One end of jet pipe support plate (10) is with starting machine drum body
(80) connect, the other end is connected with plug cone (90), and the jet pipe support plate (10) includes outer wall (11) and inwall (12), the outer wall
(11) cooling duct (20) are formed between the inwall (12), the outer wall (11) is provided with multiple rows of air film hole (30), the gas
The quantity of fenestra (30) increases with (90) are bored close to the plug.
2. support plate cooling structure according to claim 1, it is characterised in that：Multiple rows of disturb is provided with the cooling duct (20)
Fluidization tower (40), the both ends of the turbulence columns (40) are connected with the outer wall (11) and the inwall (12) respectively, and the flow-disturbing
The quantity of post (40) increases with (90) are bored close to the plug.
3. support plate cooling structure according to claim 2, it is characterised in that：The jet pipe support plate (10) is circumferentially distributed in institute
State and start between machine drum body (80) and the plug cone (90), its quantity is 3~8.
4. support plate cooling structure according to claim 2, it is characterised in that：The air film hole (30) is distributed in wrong row, its
Quantity is 34~56.
5. support plate cooling structure according to claim 2, it is characterised in that：The turbulence columns (40) are distributed in wrong row, its
Quantity is 40~60.
6. aero-engine, it is characterised in that：It includes the axial symmetry plug as described in any claim in claim 1 to 5
Formula jet pipe support plate cooling structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711103243.8A CN107829840A (en) | 2017-11-10 | 2017-11-10 | Axial symmetry plug nozzle support plate cooling structure and there is its aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711103243.8A CN107829840A (en) | 2017-11-10 | 2017-11-10 | Axial symmetry plug nozzle support plate cooling structure and there is its aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107829840A true CN107829840A (en) | 2018-03-23 |
Family
ID=61654130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711103243.8A Pending CN107829840A (en) | 2017-11-10 | 2017-11-10 | Axial symmetry plug nozzle support plate cooling structure and there is its aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107829840A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110501135A (en) * | 2019-08-22 | 2019-11-26 | 西安交通大学 | Become Mach number molded line wind-tunnel high temperature jet pipe wall array type enhanced heat exchange cooling structure |
| CN113357044A (en) * | 2021-05-23 | 2021-09-07 | 中国航发沈阳发动机研究所 | Inner cone with flow guide support plate |
| CN114877374A (en) * | 2022-04-21 | 2022-08-09 | 南京航空航天大学 | Integrated afterburning support plate and afterburning chamber using same |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102200034A (en) * | 2010-03-08 | 2011-09-28 | 通用电气公司 | Preferential cooling of gas turbine nozzles |
| CN203175702U (en) * | 2013-03-04 | 2013-09-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Central cone cooling structure of plug type axially-symmetrical spay tube |
| CN103362650A (en) * | 2012-04-01 | 2013-10-23 | 中航商用航空发动机有限责任公司 | Cooling system and method of aero-engine |
| CN106801649A (en) * | 2017-01-23 | 2017-06-06 | 中国航发沈阳发动机研究所 | A kind of plug axisymmetric nozzle |
| CN106870200A (en) * | 2017-02-16 | 2017-06-20 | 中国航发沈阳发动机研究所 | A kind of axial symmetry plug nozzle of subregion cooling |
-
2017
- 2017-11-10 CN CN201711103243.8A patent/CN107829840A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102200034A (en) * | 2010-03-08 | 2011-09-28 | 通用电气公司 | Preferential cooling of gas turbine nozzles |
| CN103362650A (en) * | 2012-04-01 | 2013-10-23 | 中航商用航空发动机有限责任公司 | Cooling system and method of aero-engine |
| CN203175702U (en) * | 2013-03-04 | 2013-09-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Central cone cooling structure of plug type axially-symmetrical spay tube |
| CN106801649A (en) * | 2017-01-23 | 2017-06-06 | 中国航发沈阳发动机研究所 | A kind of plug axisymmetric nozzle |
| CN106870200A (en) * | 2017-02-16 | 2017-06-20 | 中国航发沈阳发动机研究所 | A kind of axial symmetry plug nozzle of subregion cooling |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110501135A (en) * | 2019-08-22 | 2019-11-26 | 西安交通大学 | Become Mach number molded line wind-tunnel high temperature jet pipe wall array type enhanced heat exchange cooling structure |
| CN113357044A (en) * | 2021-05-23 | 2021-09-07 | 中国航发沈阳发动机研究所 | Inner cone with flow guide support plate |
| CN114877374A (en) * | 2022-04-21 | 2022-08-09 | 南京航空航天大学 | Integrated afterburning support plate and afterburning chamber using same |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20180323 |