CN206600840U - A kind of burner inner liner of combustion chamber - Google Patents
A kind of burner inner liner of combustion chamber Download PDFInfo
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- CN206600840U CN206600840U CN201621471088.6U CN201621471088U CN206600840U CN 206600840 U CN206600840 U CN 206600840U CN 201621471088 U CN201621471088 U CN 201621471088U CN 206600840 U CN206600840 U CN 206600840U
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- inner liner
- burner inner
- tube wall
- combustion chamber
- casing
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Abstract
The utility model provides a kind of burner inner liner of combustion chamber, the combustion chamber includes outer casing and interior casing, the junction of the outer casing and the interior casing is provided with opening, the burner inner liner is located in the cavity that the outer casing of the combustion chamber and interior casing are surrounded, the head of the burner inner liner is corresponding with the opening, outer ring cavity between the outer tube wall of the outer casing and the burner inner liner, ring cavity in being formed between the inner tube wall of the interior casing and the burner inner liner, cooling gas enters the combustion chamber through the opening, and pass through the outer ring cavity and the interior ring cavity, the outer tube wall of the burner inner liner towards the outer wall and the inner tube wall of outer ring cavity side towards the outer wall of interior ring cavity side on be provided with multiple fin structures, the fin structure is set along the cooling gas direction of flow.
Description
Technical field
The utility model is related to aero-engine field, more particularly to a kind of burner inner liner of aeroengine combustor buring room.
Background technology
Gas turbine is widely used in generating electricity and aviation field, in the gas turbine, the pressure-air flowed out through compressor
After being mixed with fuel (aviation kerosine), fully burnt in combustion chamber flame drum, primary zone maximum temperature is up to 2400K, and mesh
Preceding flame tube wall metal material normal working temperature is in below 1300K.To enable burner inner liner far surpassing its normal working temperature
Lower reliably working, mainly takes the method cooled down to burner inner liner.It is modern first to pursue higher gas turbine combination property
Enter the continuous improvement of gas-turbine combustion chamber outlet temperature, flame cylinder roasting temperature is also constantly lifted.It correspond to, on the one hand fire
Burn room import pressure-air temperature constantly to be lifted, cool down air cooling reduced capability；On the other hand it is used for fuel combustion and high pressure whirlpool
The air capacity increase of wheel cooling, causes the AIR Proportional that can be used for burner inner liner to cool down constantly to reduce, cold to flame combustion chamber barrel
But design proposes requirements at the higher level, studies more efficiently burner inner liner cooling pattern particularly important.
The mode cooled down for combustion chamber flame drum has gaseous film control, convection current gaseous film control, impact gaseous film control, diverging cold
But cooled down with laminate etc., its basic cooling principle is all that cold air ring cavity inside and outside combustion chamber enters in burner inner liner, in flame tube wall
Plate hot side surface forms one layer of air film, and air film is close to the hot side flow of flame tube wall plate, and air film plays cooling wall and isolation is fired
Gas washes away the effect of burner inner liner wall, and the quality of air film quality directly affects the cooling effectiveness of cooling gas.Existing most research
All it is the form and arrangement by changing Cooling Holes, to lift flame tube wall plate hot side air film quality.Corrugated fin is strong
Change the conventional structure of heat transfer, corrugated fin can effectively facilitate air turbulence, separation and destruction thermal resistance boundary layer, can be effectively increased pair
Heat exchange area is flowed, heat transference efficiency is improved.
Authorization Notice No. discloses a kind of fire with external cooler structure for CN 105042639A Chinese invention patent
Flame cylinder, it is mainly characterized by increasing radiator in burner inner liner outer low temperature environment, and when burner inner liner works, liquid or gaseous state are cold
But circulated between cavity and radiator of the agent inside flame tube wall, the heat of flame tube wall is transferred to outer low temperature environment
In, protect burner inner liner not to be burned.The cooling to burner inner liner is realized using cooling agent and heat exchanger, it is not necessary to go out using compressor
Mouth air is cooled down and without the high new material of use cost, is the advantage of such a structure flame tube structure.But due to it
It is additionally arranged in flame tube wall internal cavities, ring cavity and sets up heat exchange pipeline, outside hangs huge heat exchanger, its is complicated, again
Measure larger, difficulty of processing big.
Utility model content
The brief overview of one or more aspects given below is to provide to the basic comprehension in terms of these.This general introduction is not
The extensive overview of all aspects contemplated, and it is also non-to be both not intended to identify the key or decisive key element of all aspects
Attempt to define the scope in terms of any or all.Its unique purpose is to provide the one of one or more aspects in simplified form
A little concepts think the sequence of more detailed description given later.
The purpose of this utility model is a kind of burner inner liner for aeroengine combustor buring room of offer, and the burner inner liner is carried
Fin structure so that cooling gas thermal boundary layer is constantly separated with flow boundary layer, recombinated, and then can be more preferable than prior art
Ground cools to combustion barrel.
According to above-mentioned purpose, the present invention provides a kind of burner inner liner of combustion chamber, and the combustion chamber includes outer casing and interior machine
Casket, opening is provided with the junction of the outer casing and the interior casing, and the burner inner liner is located at the outer machine of the combustion chamber
In the cavity that casket and interior casing are surrounded, the head of the burner inner liner is corresponding with the opening, the outer casing and the burner inner liner
Outer tube wall between outer ring cavity, formed between the inner tube wall of the interior casing and the burner inner liner in ring cavity, cooling gas is through institute
State opening and enter the combustion chamber, and pass through the outer ring cavity and the interior ring cavity, the outer tube wall direction of the burner inner liner
The outer wall and the inner tube wall of outer ring cavity side are towards being provided with multiple fin structures, the fin on the outer wall of interior ring cavity side
Structure is set along the cooling gas direction of flow.
In one embodiment, perforation is offered on the outer tube wall and the inner tube wall of the burner inner liner.
In one embodiment, the perforation is uniformly distributed on the outer tube wall and the inner tube wall of the burner inner liner.
In one embodiment, the bearing of trend of the perforation on the outer tube wall and the inner tube wall and itself institute are in place
The wall tangent line put is in an angle, to be tilted towards the cooling gas direction of flow.
In one embodiment, the angle is 10 °~90 °.
In one embodiment, the perforation is circular hole, a diameter of 0.5~4mm of the circular hole.
In one embodiment, the fin structure along its length direction be in sinusoidal wave shape.
In one embodiment, spacing of the adjacent fin structure on the identical circumferential section of burner inner liner is equal.
In one embodiment, the height of the fin structure is 4~15mm.
In one embodiment, diffuser is provided with the opening, it is described for being sent into after the cooling gas is pressurizeed
Combustion chamber.
The utility model increases heat exchange area by the setting of blade construction, while making ring cavity cool down gas thermal boundary
Layer is constantly separated with flow boundary layer, recombinated, and greatly strengthen the cooling capacity of burner inner liner.
Brief description of the drawings
After the detailed description of embodiment of the disclosure is read in conjunction with the following drawings, it better understood when the present invention's
Features described above and advantage.In the accompanying drawings, each component is not necessarily drawn to scale, and with similar correlation properties or feature
Component may have same or like reference.
Fig. 1 shows the structural representation for the combustion chamber for being traditionally used for aero-engine；
Fig. 2 shows the structural representation of the barrel one side of the utility model burner inner liner；
Fig. 3 shows the structural representation of the flame tube wall with sinusoidal wave shape fin structure.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.Note, it is below in conjunction with accompanying drawing and specifically real
It is only exemplary to apply the aspects of example description, and is understood not to carry out any limitation to protection scope of the present invention.
The utility model provides a kind of burner inner liner that fin structure is carried on barrel, while being provided with band on barrel
There is a hole of deflection angle, while enhancing heat exchange, be more beneficial for forming coverage rate and preferably cool down air film.
In order to be best understood from the utility model, Fig. 1 is refer to, Fig. 1 shows the burning for being traditionally used for aero-engine
The structural representation of room.
Combustion chamber is that showing for combustion chamber is illustrate only in the circumferentially continuous distribution around engine axis 111, Fig. 1
It is intended to.Combustion chamber 10 includes outer casing 101 and interior casing 102, and so-called outer casing refers to the combustion for being relatively distant from engine axis 111
Chamber enclosure is burnt, so-called interior casing refers to the combustor outer casing of relatively close engine axis 111, outer casing 101 and interior casing
102 collectively constitute combustion chamber cavity 112.
Burner inner liner 103 is located in combustion chamber cavity 112, burner inner liner similar with the structure of outer combustion case and interior casing
103 have outer tube wall 1031 and inner tube wall 1032, and so-called outer tube wall refers to be relatively distant from outside the burner inner liner of engine axis 111
Shell, so-called inner tube wall refers to the burner inner liner shell of relatively close engine axis 111, and outer tube wall 1031 and inner tube wall 1032 are common
Constitute burner inner liner cavity 1033.
So, outer ring cavity 113 is formed between the outer casing 101 of combustion chamber and the outer tube wall 1031 of burner inner liner, combustion chamber
Ring cavity 114 in being formed between the inner tube wall of the inner tube wall 1032 of interior casing 102 and burner inner liner.
The shell of combustion chamber 10 is provided with opening 104, and opening 104 goes out in the connection of outer casing 101 and interior casing 102,
It is also to be understood that the shell of combustion chamber 10 is divided into outer casing 101 and interior casing 102 by opening 104.
The head 1034 of burner inner liner is corresponding with opening 104, so, and cooling gas enters inside combustion chamber 10 from opening 104,
And go deep into along outer ring cavity 113 and interior ring cavity 114 inside combustion chamber 10.
Air film is cooled down in the formation that outer ring cavity 113 and interior ring cavity 114 flow in cooling gas, cooling air film is close to burner inner liner
Outer tube wall 1031 and inner tube wall 1032 flow, absorbed by the outer tube wall 1031 and inner tube wall 1032 of burner inner liner in burner inner liner
Heat, reaches the purpose cooled to burner inner liner.
Core content of the present utility model is to carry out the outer tube wall and inner tube wall of burner inner liner the improvement in structure so that
Flame tube structure after improvement can better profit from cooling gas and burner inner liner is cooled.
Fig. 2 is refer to, Fig. 2 shows the structural representation of the barrel one side of the utility model burner inner liner.Burner inner liner
20 outer tube wall towards the outer wall and inner tube wall of outer ring cavity side towards the outer wall of interior ring cavity side on be provided with multiple fin knots
Structure 201, fin structure 201 is set along cooling gas direction of flow.That is, the setting of fin structure 201 is along cold
But the motion of gas, rather than to obstruct the motion of cooling gas.
The design of fin structure can increase the contact area of flame drum outer wall and cooling gas, and then can strengthen cooling
The heat exchange of gas and burner inner liner, so as to preferably cool to burner inner liner.
On the other hand, fin structure can be split cooling gas, make thermal boundary in ring cavity on cooling gas flow direction
Layer and flow boundary fault rupture, restructuring, improve flame drum outer wall cold side heat convection effect, the cold side cooling of reinforcing flame drum outer wall
Effect, so that the temperature of whole burner inner liner be reduced.
In one embodiment, perforation 202 is offered on the outer tube wall and inner tube wall of burner inner liner 20.The setting of perforation 202,
Cooling gas is entered inside burner inner liner by perforation 202, all standing air film or impact are formed on the inside of flame tube wall
Air-flow, so as to preferably cool to burner inner liner 20.
In one embodiment, perforation 202 is uniformly distributed on the barrel 203 of burner inner liner 20.Equally distributed purpose be for
Allow cooling air film is more uniform, cooling air film is more uniform, and heat exchange is more abundant, better to the cooling-down effect of burner inner liner.
More preferably, the bearing of trend of perforation 202 and the wall tangent line of position are in an angle, to be flowed towards cooling gas
Direction is tilted.In such manner, it is possible to so that cooling gas preferably enters in combustion chamber, and formation is more preferable on the barrel of combustion chamber
Cool down air film.
In one embodiment, the bearing of trend of perforation 202 and the wall tangent line angle that is in of position be 10 °~
90°。
According to the size of traditional combustion room, in one embodiment, perforation 202 is circular hole, circular hole a diameter of 0.5~
4mm.The arrangement of circular hole is avoided situation that is overstocked or crossing comb occur.
In a preferred embodiment, fin structure is in sinusoidal wave shape along its length direction, specifically refer to Fig. 3, Fig. 3
The structural representation of the flame tube wall with sinusoidal wave shape fin structure is shown, fin structure 301 is on the outside of flame tube wall
Sinusoidal wave shape extends.
In the design of sinuous fin structure, flame tube wall cylinder and the contact surface of cooling gas are further increased
Product, the same cooling-down effect of enhancing flame.Such a design can also strengthen the flow-disturbing of cooling gas, so as to preferably enter to burner inner liner
Row cooling.
In one embodiment, spacing of the adjacent fin structure on the identical circumferential section of burner inner liner is equal.Due to
The circle diameter of flame tube head is different with the circle diameter of afterbody, and fin structure is not necessarily what is be parallel to each other, may be in fire
Flame cylinder head is closeer, and is relatively dredged in flame drum tail.But as long as the adjacent fin structure of holding is in the identical circumference of burner inner liner
Spacing on section is equal, it becomes possible to when cooling gas be uniformly distributed on flame tube wall, it is to avoid burner inner liner local temperature is too high
Situation.
Fin structure it is unsuitable too high, it is too high to expend more materials, increase manufacturing cost, fin structure also should not mistake
It is low, it is too low to reduce cooling gas and the contact area of burner inner liner, and then it is unfavorable for the cooling to burner inner liner.According to actual warp
Test, the general height for choosing fin structure is advisable for 4~15mm.
In one embodiment, diffuser is equipped with the opening of combustion chamber, for sending into combustion chamber after cooling gas is pressurizeed.
Cooling gas is pressurizeed, the flow velocity of cooling gas can make it that faster, and then cooling gas is quickly entered with burner inner liner
Row heat exchange, and then improve the cooling capacity of burner inner liner.
In order to verify heat transfer effect of the present utility model, operating condition parameter is selected, respectively to conventional chilling structure and reality
Three-dimensional CFD fluid and structural simulations are carried out with new cooling structure, result of calculation is shown in Table 1.
The result of calculation of table 1
| Wall surface temperature/K | Operating mode one |
| Conventional flame tube structure | 1195.46 |
| Band fin structure burner inner liner | 1128.73 |
As it can be seen from table 1 being compared using the burner inner liner of cooling structure of the present utility model with conventional burner inner liner, flame
Tube wall surface temperature reduces 66.73K, and heat-transfer effect improves obvious.
The processing method of flame tube wall of the utility model with fin structure, including：
On the flame tube wall flat board of fixed thickness, by laser cutting method, cut on flame tube wall flat board certain
The circular through hole of angle；
Flame tube wall flat board is pressed into by columnar flame tube wall plate by circle hub；
By fin structure soldering in the outside of flame tube wall, the flame tube wall with fin structure and perforation is formed.
It is for so that any person skilled in the art all can make or use this public affairs to provide of this disclosure be previously described
Open.Various modifications of this disclosure all will be apparent for a person skilled in the art, and as defined herein general
Suitable principle can be applied to spirit or scope of other variants without departing from the disclosure.Thus, the disclosure is not intended to be limited
Due to example described herein and design, but it should be awarded and principle disclosed herein and novel features phase one
The widest scope of cause.
Claims (10)
1. a kind of burner inner liner of combustion chamber, it is characterised in that the combustion chamber includes outer casing and interior casing, in the outer casing
The junction of the interior casing is provided with opening, what the outer casing and interior casing that the burner inner liner is located at the combustion chamber were surrounded
In cavity, the head of the burner inner liner is corresponding with the opening, outer shroud between the outer tube wall of the outer casing and the burner inner liner
Ring cavity in being formed between chamber, the inner tube wall of the interior casing and the burner inner liner, cooling gas enters the combustion through the opening
Room is burnt, and through the outer ring cavity and the interior ring cavity,
The outer tube wall of the burner inner liner is towards the outer wall and the inner tube wall of outer ring cavity side towards the outer of interior ring cavity side
Multiple fin structures are provided with wall, the fin structure is set along the cooling gas direction of flow.
2. burner inner liner as claimed in claim 1, it is characterised in that on the outer tube wall and the inner tube wall of the burner inner liner
Offer perforation.
3. burner inner liner as claimed in claim 2, it is characterised in that the outer tube wall and institute of the perforation in the burner inner liner
State and be uniformly distributed on inner tube wall.
4. burner inner liner as claimed in claim 2, it is characterised in that the perforation on the outer tube wall and the inner tube wall
Bearing of trend and the wall tangent line of itself position are in an angle, to be tilted towards the cooling gas direction of flow.
5. burner inner liner as claimed in claim 4, it is characterised in that the angle is 10 °~90 °.
6. burner inner liner as claimed in claim 2, it is characterised in that the perforation is circular hole, the circular hole a diameter of 0.5~
4mm。
7. burner inner liner as claimed in claim 1, it is characterised in that the fin structure is along its length direction in sine wave
Shape.
8. burner inner liner as claimed in claim 1, it is characterised in that adjacent fin structure is cut in the identical circumference of burner inner liner
Spacing on face is equal.
9. burner inner liner as claimed in claim 1, it is characterised in that the height of the fin structure is 4~15mm.
10. burner inner liner as claimed in claim 1, it is characterised in that be provided with diffuser at the opening, for will be described cold
But the combustion chamber is sent into after gas pressurized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621471088.6U CN206600840U (en) | 2016-12-29 | 2016-12-29 | A kind of burner inner liner of combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621471088.6U CN206600840U (en) | 2016-12-29 | 2016-12-29 | A kind of burner inner liner of combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206600840U true CN206600840U (en) | 2017-10-31 |
Family
ID=60149276
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621471088.6U Active CN206600840U (en) | 2016-12-29 | 2016-12-29 | A kind of burner inner liner of combustion chamber |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110044626A (en) * | 2018-01-15 | 2019-07-23 | 中国航发商用航空发动机有限责任公司 | A kind of single sector combustor test device |
| CN110094758A (en) * | 2018-01-30 | 2019-08-06 | 通用电气公司 | Burner and operation method for improved discharge and durability |
| CN111207415A (en) * | 2020-01-17 | 2020-05-29 | 西北工业大学 | Flame tube of combustion chamber of aircraft engine |
| CN112178692A (en) * | 2020-10-27 | 2021-01-05 | 西北工业大学 | Longitudinal corrugated cooling structure with L-shaped impact orifice plate |
| CN113483362A (en) * | 2021-08-18 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Flame tube and gas turbine |
-
2016
- 2016-12-29 CN CN201621471088.6U patent/CN206600840U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110044626A (en) * | 2018-01-15 | 2019-07-23 | 中国航发商用航空发动机有限责任公司 | A kind of single sector combustor test device |
| CN110044626B (en) * | 2018-01-15 | 2021-04-16 | 中国航发商用航空发动机有限责任公司 | Single-sector combustion chamber test device |
| CN110094758A (en) * | 2018-01-30 | 2019-08-06 | 通用电气公司 | Burner and operation method for improved discharge and durability |
| CN110094758B (en) * | 2018-01-30 | 2021-02-12 | 通用电气公司 | Burner for improved emissions and durability and method of operation |
| CN111207415A (en) * | 2020-01-17 | 2020-05-29 | 西北工业大学 | Flame tube of combustion chamber of aircraft engine |
| CN112178692A (en) * | 2020-10-27 | 2021-01-05 | 西北工业大学 | Longitudinal corrugated cooling structure with L-shaped impact orifice plate |
| CN113483362A (en) * | 2021-08-18 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Flame tube and gas turbine |
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