CN108731030A - A kind of combustion chamber with compound special-shaped groove gaseous film control structure - Google Patents
A kind of combustion chamber with compound special-shaped groove gaseous film control structure Download PDFInfo
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- CN108731030A CN108731030A CN201810911073.4A CN201810911073A CN108731030A CN 108731030 A CN108731030 A CN 108731030A CN 201810911073 A CN201810911073 A CN 201810911073A CN 108731030 A CN108731030 A CN 108731030A
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- groove body
- inner liner
- wall
- burner inner
- combustion chamber
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 65
- 150000001875 compounds Chemical class 0.000 title claims abstract description 35
- 230000007704 transition Effects 0.000 claims description 14
- 238000007667 floating Methods 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 12
- 238000009792 diffusion process Methods 0.000 claims description 9
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 2
- 238000001816 cooling Methods 0.000 abstract description 53
- 239000000112 cooling gas Substances 0.000 abstract description 36
- 239000007789 gas Substances 0.000 abstract description 31
- 230000004992 fission Effects 0.000 description 18
- 238000012545 processing Methods 0.000 description 12
- 238000005516 engineering process Methods 0.000 description 10
- 239000000446 fuel Substances 0.000 description 8
- 239000002737 fuel gas Substances 0.000 description 7
- 230000035882 stress Effects 0.000 description 6
- 230000015572 biosynthetic process Effects 0.000 description 5
- 238000007664 blowing Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 239000000295 fuel oil Substances 0.000 description 4
- 238000002156 mixing Methods 0.000 description 4
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- 238000010146 3D printing Methods 0.000 description 3
- 238000001311 chemical methods and process Methods 0.000 description 3
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- 238000005457 optimization Methods 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
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- 230000003628 erosive effect Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The present invention provides a kind of combustion chamber with compound special-shaped groove gaseous film control structure, including burner inner liner, and it is compound special-shaped groove that the inner wall of burner inner liner, which has the groove body of several indents, groove body, at least consists of two parts along depth direction, is H from groove body bottom depth1Part be first part, remainder is second part, and at least one side wall of second part is formed by the same side wall lateral magnification of first part.Cooling gas fully develops from after discrete holes A ejections in the first part of groove body, form continuous, uniform barotropic gas, then it is transmitted to open end through second part and is biased to the outflow of burner inner liner internal face side, cooling air film that is continuous, uniform, attaching is formed in burner inner liner internal face, efficient cooling may be implemented, the heat-resisting ability to improving combustion chamber is of great significance.
Description
Technical field
The present invention relates to the combustion chambers of the dynamic fields such as aero-engine, gas turbine, and in particular to one kind has compound
The combustion chamber of special-shaped groove gaseous film control structure.
Background technology
Combustion chamber is the device that the chemical energy of fuel oil is changed into thermal energy, is the core of aero-engine and gas turbine
One of part, the high-temperature fuel gas of generation can be used for pushing the work of turbo blade etc..
The combustion process of combustion chamber occurs mainly in the burner inner liner of combustion chamber, and burner inner liner wall surface is subjected to thermal-flame and draws
The thermal stress and heat erosion, harsh use environment risen is used for life and reliability and proposes huge challenge.In general, using
In addition to this allowable work temperature that heat-resisting material improves combustion chamber also takes efficient cooling technology to have burner inner liner
Effect cooling.
Currently, the type of cooling of combustion chamber includes mainly stacking annulus slit gaseous film control, slant multi-hole film cooling, laminate
Porous cooling etc..The gaseous film control of early stage is to obstruct main combustion gas by wall surface slit or the cold flow of aperture blowout, as the U.S. is special
Shown in sharp US4896510, the advantages that have that integrated model is rigidly good, cooling flow controllability is good etc., but there are cold air demand is big,
The problems such as even to burner inner liner wall surface inhomogeneous cooling.Slant multi-hole film cooling projects cold air at an angle by oblique hole structure,
Isolation air film is formed in burner inner liner wall surface, plays the role of protecting wall surface.Early stage inclined hole is mostly straight circular hole, and there are single hole protection faces
The problems such as product is less than normal, and air film stripping is serious when air blowing ratio is big, needs very intensive air film hole.More advanced diffusion hole and complexity
Three-dimensional special-shaped hole has been used for the gaseous film control of combustion chamber, and single hole cooling protection can be increased considerably relative to simple straight circular hole
Area and the air film attaching degree under various air blowing ratios, as shown in 2008/0271457 A1 of United States Patent (USP) US.But use gas
When fenestra, the surface air film uniformity of burner inner liner wall surface and the distribution in hole and shape are closely related, and the uniformity of film overcast is not
Foot is the major technology bottleneck for restricting combustion chamber maximum cooling protection.
It is the cooling in current combustion room forward position that double wall in conjunction with advanced film cooling holes technology is cooling or compound wall cools down
Technology, such as United States Patent (USP) US4109459, US 103968418 B of 2002/0174658 A1, Chinese patent CN and document：Quotient
Body pine, Zhao Ming, the development of ice-glazed happy aeroengine combustor burings room cooling structure and the key technology of floating wall construction, aviation work
Cheng Jinzhan, 2013,4 (4):407~413..Current compound wall cooling structure using " impinging cooling+densification air film hole cools down+
Lamination gap cools down " compound cooling structure that combines, there are many variations of structure in document, such as turbulence columns, micro- texture, middle layer
Etc..With bilayer or multilayer wall construction, the one side (internal layer) towards combustion gas is generally Inclined multihole wass, and the one side towards cold air is (outer
Layer) it is straight hole wall.The cooling air entered from outer wall trepanning impacts inner layer wall and carries out impinging cooling, subsequently into flow-disturbing chamber
Or in inclined hole, inner layer wall is initially subjected to cooling internal convection heat exchange protection, then forms protection air film by inclined hole as much as possible, and
The cold air air film that ladder-like stacking zonary structure gap sprays together, reduces combustion chamber wall surface temperature.This kind of technical solution exists
Deficiency be：It is big that step structure gap flow sprays air consumption；Gas film behavior on Inner Wall of Combustion Chamber needs cooling hole, and from
Scattered cooling hole it is difficult to ensure that cooling efficiency uniformity；Bilayer or multilayer wall construction is complicated, causes combustion chamber manufacturing cost high
High, further loss of weight is difficult.
With the promotion of aero-engine and gas turbine performance, operating temperature needs further to be promoted, above-mentioned combustion chamber
Cooling capacity face the challenge.It is badly in need of the combustion chamber with the cooling structure that can form continuous, uniform air film in the industry.
Invention content
Present situation in view of the above technology, the present invention is intended to provide a kind of combustion chamber, burner inner liner internal face can be formed it is continuous,
Uniform cooling air film, may be implemented efficient cooling, and the heat-resisting ability to improving combustion chamber is of great significance.
In order to achieve the above technical purposes, the present inventor passes through long-term research and probe, in the cylinder of the burner inner liner of combustion chamber
Wall setting includes discrete holes and the gaseous film control structure of groove body, and the compound abnormal shape that groove body is designed as being formed by two parts
Slot, that is, along groove body depth direction, first part is intermediate expansion slot, for filling the cooling gas entered from discrete holes
Distribution exhibition forms continuous, uniform barotropic gas；Second part is lateral magnification slot, for making the barotropic gas be biased to matrix
Surface side is flowed out, and the continuous cooling air film uniformly attached is formed in the internal face of burner inner liner.
That is, the technical scheme is that：A kind of combustion chamber with compound special-shaped groove gaseous film control structure, including flame
Cylinder, combustion process occur mainly in the burner inner liner；The inner wall of the burner inner liner has the groove body of several indents, the groove body
Including groove body bottom, and along the two side of groove body length direction；Each groove body bottom setting is several to be through to the flame
The discrete holes A, the discrete holes A of drum outer wall are arranged generally along the length direction of the groove body；
The depth of the groove body is H, and the groove body at least consists of two parts along depth direction, and from groove body bottom, depth is
H1Part be first part, remaining part be second part, that is, second part depth be H2=H-H1；Second part is extremely
Few one side wall is formed by the same side wall lateral magnification of first part.
Preferably, method of the groove body along the axis and the burner inner liner internal face of the open end 102 of depth direction
Wire clamp angle is α, 10 °≤α≤90 °, preferably 30 °≤α≤80 °, further preferably 45 °≤α≤70 °.
Preferably, in the vertical cross-section along groove body width direction of the groove body, the two side of first part is to deposit
Two straightways at interval.Every straightway and slot bottom angle are preferably 10 ° -170 °, further preferably 30 ° -150 °, more excellent
It is selected as 60 ° -120 °.Two straightways can be parallel to each other, can also form a clamp.The side wall of second part can be straight
Line segment can also be arc segment, preferably, the arc segment that at least one side wall of second part is.In addition, preferably,
The junction of at least one side wall of a part and the same side wall of second part connects for chamfered transition, or connects for arc transition
It connects, is smoothly connected with realizing.
The maximum gauge of the discrete holes A is d, and the minimum widith of the groove body is D.Preferably, D >=d.As excellent
Choosing, H >=2d, further preferably H >=3d, more preferably H >=4d.
In the combustion chamber of above structure, the cooling gas of burner inner liner outside wall surface enters groove body from discrete holes A, at first
Divide fully diffusion, mixing, is transmitted in the open end deviation burner inner liner through second part after forming uniform barotropic gas
Wall surface flow out, burner inner liner internal face formed it is uniform, continuously cool down air film.
Preferably, H1>H2；Further preferably H1：H2≥2：1；More preferably H1：H2≥3：1, most preferably H1：H2≥
4：1.
The internal face of the burner inner liner can be parallel to each other with outside wall surface, and can be in a certain angle.
The discrete holes A can be straight circular hole, can also be diffusion hole, can also be the three-dimensional special-shaped hole of complexity.Make
To be preferred, the central axis of the discrete holes A and the angle of the burner inner liner outside wall surface are θ.Angle α can not with angle theta
Together.Preferably, angle theta is to reduce based on hole machined thickness, it is generally preferable to it is 0 °≤θ≤60 °, more preferably 10 °≤θ≤
45°；Angle α is based on ensureing that good air film attaches.Preferably, chamfered transition knot is arranged in the open end of the discrete holes A
Structure or arc transition structure cause stress concentration phenomenon and gas to circulate the problems such as unsmooth to avoid pointed structures.
Each groove body is unlimited in the setting of the burner inner liner inner wall, can deposit according to the true form of burner inner liner internal face
Spacing is arranged in parallel, can also be to be staggered, so that the continuous air film that each groove body is formed forms burner inner liner internal face
Based on all standing.
In the present invention, the preparation method of burner inner liner is unlimited, for example, being made using 3D printing technique, utilizes overall processing skill
Art be made etc..The present invention also provides a kind of methods preparing burner inner liner, first, the burner inner liner are divided at least two parts；
Then, the inner wall in every part prepares first groove body, and the outer wall in every part prepares the discrete holes A；Finally, Jiang Gebu
Subassembly forms the burner inner liner.Alternatively, the burner inner liner inner wall successively process formed the first groove body second part,
First part and discrete holes A obtain the burner inner liner.
The processing technology is unlimited, including mechanical processing, laser processing, electrical-chemistry method etc..
Compared with prior art, discrete holes and groove body is arranged in flame tube wall of the present invention in combustion chamber, forms gaseous film control
Structure, and groove body is the compound special-shaped groove formed by two parts, and along groove body depth direction, first part's depth is H1, shape
At intermediate expansion slot, second part depth is H2, lateral magnification slot is formed, such structure has the advantages that：
(1) cooling gas, due to the compound special-shaped groove that groove body is two sections of formation, has larger from after discrete holes enter groove body
Depth is in narrow structure along the vertical cross-section of groove body width direction, and the diffusion gas from each discrete holes not only can be along groove body
Length direction extension, mixing, and can be spread along groove body depth direction, mix, be overlapped mutually, that is, it can be in groove body
First part fully develops, and to form continuous, uniform barotropic gas, is then transmitted to opening via the second part of groove body
End pneumatically needs to optimize the shape of open end, gas is made to be biased to one effluent of matrix surface according to what air film attached
Go out, the continuous cooling air film uniformly attached is formed in burner inner liner inner wall, and since groove body depth is larger, by groove body open end
The cooling gas of outflow has powerful air pressure, therefore the cooling air film strength attaching of the continuous uniform formed in burner inner liner inner wall
In burner inner liner internal face.That is, in the present invention, the cooling air film for being set as continuous, uniform strength attaching of compound abnormal shape slot structure
Provide necessary condition.Cooling gas enters groove body from discrete holes A, fully spreads in first part, mixes, formed it is uniform just
It calms the anger and is transmitted to open end through second part after body and is biased to the outflow of burner inner liner internal face, formed in burner inner liner internal face and uniformly connected
Continuous air film.
(2) cooling gas passes through the aerodynamics simu1ation figure of the flame tube wall in the combustion chamber of the present invention as indicated with 1, it was confirmed that this
Cooling gas can be sprayed through discrete holes to groove body in invention, is extended, is mixed in groove body, forms continuous, uniform positive pressure gas
Then body forms full film overcast in burner inner liner inner wall surface.
(3) in order to further increase cooling gas it is continuous, uniformly and adhesion, the present invention also proposes below three kinds it is excellent
The chamber structure of change.
The first is that hollow cavity is combined on above-mentioned flame tube wall architecture basics.That is, the burner inner liner inner wall with
Hollow cavity is set between outer wall；Several discrete holes B for being through to the hollow cavity are arranged in the outer wall of the burner inner liner；It is described
The inner wall of burner inner liner has the groove body of several indents, and the groove body includes groove body bottom, and along the two of groove body length direction
Side wall；Several discrete holes for being through to the hollow cavity are arranged in each groove body bottom, and the discrete holes are generally along the groove body
Length direction arrangement；The depth of the groove body is H, and the groove body at least consists of two parts along depth direction, from groove body bottom
Portion's depth is H1Part be first part, remaining part be second part, that is, second part depth be H2=H-H1；Second
Partial at least one side wall is formed by the same side wall lateral magnification of first part.
Cooling gas enters hollow cavity through discrete holes B first and carries out convection current cooling, forms positive pressure, then discrete through second
Hole enters the groove body.
Efficiently to sputter cooling gas, it is optimization aim to form positive pressure for the selection of the height W of the hollow cavity.
Preferably, the discrete holes B and discrete holes A is dislocatedly distributed.
The discrete holes B can be straight circular hole, can also be diffusion hole, can also be the three-dimensional special-shaped hole of complexity.
Preferably, the open end setting chamfered transition structure or arc transition structure of the discrete holes B, to avoid
Pointed structures cause stress concentration phenomenon and gas to circulate the problems such as unsmooth.
The preparation method of the burner inner liner of above structure is unlimited, for example, being made using 3D printing technique, utilizes overall processing skill
Art be made etc..The present invention also provides a kind of methods for the burner inner liner preparing the structure to be first divided into the burner inner liner at least
Two parts；Then, the inner wall in every part prepares the groove body and discrete holes A, and the outer wall in every part prepares the discrete holes
B；Finally, each section is combined, forms the burner inner liner.
The processing technology is unlimited, including mechanical processing, laser processing, electrical-chemistry method etc..
Second is that floating wall is arranged in above-mentioned flame tube wall periphery, is formed between the floating wall and the outer wall of burner inner liner
Cavity；Several discrete holes B for being through to the hollow cavity are arranged in the side of the floating wall；Cooling gas is first through discrete holes
B enters hollow cavity and carries out convection current cooling, forms positive pressure, then enters the groove body through discrete holes A.
The third is that the groove bodies of several indents is arranged in the outer wall of above-mentioned burner inner liner, in order to distinguish and burner inner liner inner wall is arranged
Groove body, the groove body for being arranged in burner inner liner inner wall is known as the first groove body, the groove body for being arranged in flame drum outer wall is known as second
Groove body；First groove body includes groove body bottom, and the two side along groove body length direction；Second groove body includes slot
Body bottom, and the two side along groove body length direction；The setting of each first groove body bottom is several to be through to the second groove body bottom
The discrete holes A, the discrete holes A in portion are arranged generally along the length direction of first groove body.The depth of first groove body is
H, first groove body at least consist of two parts along depth direction, are H from the first groove body bottom depth1Part be first
Point, remaining part is second part, that is, second part depth is H2=H-H1；At least one side wall of second part is by first
Partial same side wall lateral magnification is formed.
In the structure of the optimization, the outer wall of the burner inner liner is arranged the second groove body, and the introducing of the second groove body is conducive to cold
But high efficiency air flow is transmitted to discrete holes A, and forms positive pressure, reduces the working depth of discrete holes A.
Efficiently to sputter cooling gas, it is optimization aim to form positive pressure for the selection of the height of second groove body.
The preparation method of the burner inner liner of above structure is unlimited, for example, being made using 3D printing technique, utilizes overall processing skill
Art be made etc..The present invention also provides a kind of methods for the burner inner liner preparing the structure to be first divided into the burner inner liner at least
Two parts；Then, the inner wall in every part prepares first groove body, the outer wall in every part prepare second groove body with from
Dissipate hole A；Finally, each section is combined, forms the turbo blade with compound special-shaped groove gaseous film control structure.
The processing technology is unlimited, including mechanical processing, laser processing, electrical-chemistry method etc..
(4) it is experimentally confirmed that when the combustion chamber Flame cylinder of the present invention is in high temperature hot gas environment, cooling gas can
In the full film overcast that burner inner liner internal face is formed, there is good cooling effect, equivalent cooling efficiency=(fuel gas temperature-fire
The temperature measured at a certain distance from burner inner liner internal face in flame cylinder)/(fuel gas temperature-cooling gas temperature) when, in cooling
In the case of blowing ratio M=1.5 of gas, in combustion chamber of the invention, at the distance apart from ten millimeters of burner inner liner internal face or more
Equivalent cooling efficiency is 0.5 or more, and when cooling gas air blowing ratio increases, equivalent cooling efficiency can be improved to 0.7 or more.
(5) combustion chamber of the invention is widely used, including be used for aero-engine and gas turbine aircraft, hovercar and
Electricity generation system etc..
Description of the drawings
Fig. 1 is the aerodynamics simu1ation figure of the flame tube wall in combustion chamber of the cooling gas by the present invention；
Fig. 2 is the aeroengine combustor buring cell structure schematic diagram in the embodiment of the present invention 1,2；
Fig. 3 is the partial structurtes enlarged drawing of 1 Flame barrel of the embodiment of the present invention；
Fig. 4 is the partial structurtes enlarged drawing of 2 Flame barrel of the embodiment of the present invention；
Fig. 5 is the partial enlarged view of Fig. 4；
Fig. 6 is the partial structural diagram of the aeroengine combustor buring room in the embodiment of the present invention 3；
Fig. 7 is the partial structural diagram of the aeroengine combustor buring room in the embodiment of the present invention 4.
Specific implementation mode
With reference to embodiment, present invention is further described in detail, it should be pointed out that embodiment described below purport
Convenient for the understanding of the present invention, and any restriction effect is not played to it.
Reference numeral in Fig. 1-5 is：1- cooling gas, 2- cold air inlets end, the fuel galleries 3-, 4- fuel nozzles, 5-
Burner inner liner, 6- high-temperature fuel gas, 7- continuous coo1ings air film, 8- gaseous film controls structure, 10- high pressure gas；14- discrete holes B；15- is empty
Chambers of the heart body；The part of 16- flame tube walls；17- floating walls；18- discrete holes C；30- groove bodies；40- discrete holes A；50- groove bodies bottom；
The two side of 60,70- groove bodies；The second part of 80- groove bodies；The first part of 90- groove bodies；The inner wall of 100- burner inner liners；101-
The outer wall of burner inner liner；102- open ends 102；The first groove bodies of 105-；The second groove bodies of 107-；Second of the first groove bodies of 301-
Point；The first part of the first groove bodies of 302-；The first groove bodies of 500- bottom；The second groove bodies of 501- bottom；600, the first groove bodies of 700-
Two side；601, the two side of the second groove bodies of 701-.
Embodiment 1：
In this implementation, the structure of aeroengine combustor buring room is as shown in Figure 2,3, including burner inner liner 5, and combustion process is mainly sent out
Life is in burner inner liner 5.Compound film cooling structure 8 is arranged in flame tube wall.
Schematic enlarged-scale view at the local A of Fig. 2 Flame barrels as shown in figure 3, the inner wall 100 of burner inner liner 5 have it is several
The groove body 30 of indent, groove body 30 include groove body bottom 50, and the two side 60 and 70 along groove body length direction.Each groove body
Several discrete holes A 40 for being through to flame drum outer wall 101, length of the discrete holes A40 generally along the groove body 30 is arranged in bottom 50
Direction arranges.
The maximum gauge of these discrete holes A is d, and the minimum widith of groove body is D, D >=d, and H >=2d.
In the present embodiment, the depth of groove body 30 is H, and groove body 30 at least consists of two parts along depth direction, such as Fig. 3 institutes
Show, is H from groove body bottom depth1Part be first part 90, remaining part is second part 80, that is, second part is deep
Degree is H2=H-H1。
In the present embodiment, the inclined column structure of first part 90, in vertical cross-section as shown in Figure 3, first
The two side for being divided to 90 is in two straightways for depositing interval, and two straightways are parallel to each other, and every straightway is with slot bottom angle
70°.One side wall of second part 80 is also straightway, is to be extended to form by the same side wall of first part, another side wall is in
Arc segment is formed by the same side wall lateral magnification of first part.In the present embodiment, opening of the second part 90 along depth direction
Angle α between the axis and the normal of burner inner liner inner wall 100 of end 102 is 30 °.
In the present embodiment, H1Slightly larger than H2。
In the present embodiment, the angle theta between the central axis and the normal direction of flame drum outer wall 101 of discrete holes A 40 is 15 °,
And arc transition structure is arranged in the open end in hole, to avoid pointed structures stress concentration phenomenon.
In the present embodiment, cooling gas 1 enters combustion chamber by cold air inlet end 2 and shunts, and a part is used to form cooling
Air film 7, a part enter combustion chamber center and participate in burning.Fuel oil is spouting by fuel gallery 3 and fuel nozzle 4, in fire
Burning in flame cylinder 5.Cooling gas passes through flame tube wall by gaseous film control structure 8, and forms continuous air film 7 and cover in burner inner liner
High-temperature fuel gas 6 is isolated in burner inner liner center, forms high pressure gas 10 and go out combustion chamber, act on turbine part by wall 100.
Wherein, transmission of the cooling gas in gaseous film control structure 8 as shown in Figure 1,101 side of outer wall of burner inner liner 5 it is cold
But gas, due to the compound special-shaped groove that groove body is two sections of formation, has larger depth, along slot from after discrete holes A enters groove body
The vertical cross-section of body width direction is in narrow structure, and the diffusion gas from each discrete holes can not only expand along groove body length direction
Exhibition, mixing, and can be spread along groove body depth direction, mix, be overlapped mutually, that is, it can be filled in the first part of groove body
Then distribution exhibition is transmitted to open end, due to opening to form continuous, uniform barotropic gas via the second part of groove body
The shape design at mouth end, cooling gas are biased to the outflow of burner inner liner internal face side, and continuous uniform patch is formed in burner inner liner inner wall
Attached cooling air film, and since groove body depth is larger, there is powerful air pressure by the cooling gas that groove body open end is flowed out, because
This is attached to burner inner liner internal face in the cooling air film strength for the continuous uniform that burner inner liner inner wall is formed.
In the present embodiment, the method for preparing above-mentioned burner inner liner is：First, which is divided into two parts, by seperated I He
Fission II is composed, wherein fission I and II connection of fission are a complete burner inner liner；Then, it is prepared in the inner wall of fission I
The groove body, discrete holes A is prepared in outer wall, and the groove body is prepared in the inner wall of fission II, and discrete holes A is prepared in outer wall；Finally,
Fission I and fission II are combined, linked for a complete burner inner liner.
Embodiment 2：
In this implementation, the structure of aeroengine combustor buring room is as shown in Fig. 2, include burner inner liner 5, combustion process mainly occurs
In burner inner liner 5.
The schematic enlarged-scale view of flame tube wall between the inner wall 100 and outer wall 101 of burner inner liner as shown in figure 4, be arranged hollow cavity
Body 15.Several discrete holes B 14 for being through to hollow cavity 15 are arranged in the outer wall 101 of burner inner liner.
The enlarged drawing of the part 16 of flame tube wall is as shown in figure 5, the inner wall 100 of burner inner liner 5 has the groove body of several indents
30, groove body 30 includes groove body bottom 50, and the two side 60 and 70 along groove body length direction.Each groove body bottom 50 is arranged
Several discrete holes A 40 for being through to hollow cavity 15, discrete holes A 40 are arranged generally along the length direction of the groove body 30.
In the present embodiment, it is 0.5 millimeter that the maximum gauge of discrete holes A, which is D, and the minimum widith of groove body is D, D >=d, and H
≥2d。
In the present embodiment, the maximum gauge of discrete holes B is suitable with the maximum gauge of discrete holes A.
In the present embodiment, the height W of hollow cavity 15 is about 0.5~5 millimeter.
In the present embodiment, discrete holes B is dislocatedly distributed with discrete holes A.
In the present embodiment, the depth of groove body 30 is H, and groove body 30 at least consists of two parts along depth direction, such as Fig. 5 institutes
Show, is H from groove body bottom depth1Part be first part, remaining part be second part, that is, second part depth be H2
=H-H1。
In the present embodiment, the inclined column structure of first part, in vertical cross-section as shown in Figure 3, first part
90 two side is in two straightways for depositing interval, and two straightways are parallel to each other, and every straightway and slot bottom angle are 70 °.
One side wall of second part 80 is also straightway, is extended to form by the same side wall of first part, another side wall is in camber line
Section, is formed by the same side wall lateral magnification of first part.In the present embodiment, open end of the second part 90 along depth direction
Angle α between 102 axis and the normal of burner inner liner inner wall 100 is 30 °.
In the present embodiment, H1Slightly larger than H2。
In the present embodiment, the angle theta between the central axis and the normal direction of hollow cavity 15 of discrete holes A 40 is 15 °, and
And arc transition structure is arranged in the open end in hole, to avoid pointed structures stress concentration phenomenon.
In the present embodiment, cooling gas 1 enters combustion chamber by cold air inlet end 2 and shunts, and a part is used to form cooling
Air film 7, a part enter combustion chamber center and participate in burning.Fuel oil is spouting by fuel gallery 3 and fuel nozzle 4, in fire
Burning in flame cylinder 5.Cooling gas passes through flame tube wall by gaseous film control structure 8, and forms continuous air film 7 and cover in burner inner liner
High-temperature fuel gas is formed high pressure gas 10, goes out combustion chamber, act on turbine part by wall 100 every 6 from burner inner liner center.
Wherein, cooling gas is transmitted as in gaseous film control structure 8：The cooling gas of 101 side of outer wall of burner inner liner 5 is first
First enter hollow cavity 15 through discrete holes B and carry out convection current cooling, forms positive pressure, then enter groove body through discrete holes A, due to groove body
The compound special-shaped groove formed for two sections has larger depth, is in narrow structure along the vertical cross-section of groove body width direction, comes from
The diffusion gas of each discrete holes can not only be extended along groove body length direction, be mixed, but also can be spread along groove body depth direction,
It mixes, be overlapped mutually, that is, can fully develop in the first part of groove body, to form continuous, uniform barotropic gas, so
It is transmitted to open end by by the second part of groove body, since the shape of open end designs, cooling gas is biased to burner inner liner inner wall
Face side is flowed out, and the continuous cooling air film uniformly attached is formed in burner inner liner inner wall, and since groove body depth is larger, by slot
The cooling gas of body open end outflow has powerful air pressure, therefore the cooling air film of the continuous uniform formed in burner inner liner inner wall
Strength is attached to burner inner liner internal face.
In the present embodiment, the method for preparing above-mentioned burner inner liner is：First, which is divided into two parts, by seperated I He
Fission II is composed, wherein fission I and II connection of fission are a complete burner inner liner；Then, it is prepared in the inner wall of fission I
The groove body and discrete holes A prepare discrete holes B in outer wall, the groove body and discrete holes A are prepared in II inner wall of fission, in outer wall
Prepare discrete holes B；Finally, fission I and fission II are combined, is linked for a complete burner inner liner.
Embodiment 3：
In this implementation, the partial structural diagram of aeroengine combustor buring room is as shown in Figure 6.Combustion chamber includes burner inner liner 5,
Combustion process occurs mainly in burner inner liner 5.Floating wall 17, the outer wall of floating wall 17 and burner inner liner 5 is arranged in flame tube wall periphery
Between formed hollow cavity 15；Several discrete holes C 18 for being through to the hollow cavity 15 are arranged in the side of floating wall 17.
The enlarged drawing of the part 20 of flame tube wall is as shown in figure 3, the inner wall 100 of burner inner liner 5 has the groove body of several indents
30, groove body 30 includes groove body bottom 50, and the two side 60 and 70 along groove body length direction.Each groove body bottom 50 is arranged
Several discrete holes A 40 for being through to flame drum outer wall 101, discrete holes A 40 are arranged generally along the length direction of the groove body 30.
The maximum gauge of these discrete holes A is d, and the minimum widith of groove body is D, D >=d, and H >=2d.
In the present embodiment, the depth of groove body 30 is H, and groove body 30 at least consists of two parts along depth direction, such as Fig. 3 institutes
Show, is H from groove body bottom depth1Part be first part, remaining part be second part, that is, second part depth be H2
=H-H1。
In the present embodiment, the inclined column structure of first part, in vertical cross-section as shown in Figure 3, first part
Two side be in deposit two straightways at interval, two straightways are parallel to each other, and every straightway and slot bottom angle are 70 °.The
One side wall of two parts is also straightway, is extended to form by the same side wall of first part, another side wall is in arc segment, is
It is formed by the same side wall lateral magnification of first part.In the present embodiment, axis of the second part along the open end 102 of depth direction
Angle α between line and the normal of burner inner liner inner wall 100 is 30 °.
In the present embodiment, H1Slightly larger than H2。
In the present embodiment, the angle theta between the central axis and the normal direction of flame drum outer wall 101 of discrete holes A 40 is 15 °,
And arc transition structure is arranged in the open end in hole, to avoid pointed structures stress concentration phenomenon.
In the present embodiment, cooling gas enters combustion chamber by cold air inlet end and shunts, and a part is used to form cooling air
Film, a part enter combustion chamber center and participate in burning.Fuel oil is spouting by fuel gallery and fuel nozzle, in burner inner liner 5
Interior burning.Cooling gas passes through flame tube wall, forms continuous air film 7 and covers burner inner liner inner wall, high-temperature fuel gas 6 is isolated in flame
Cylinder center forms high pressure gas and goes out combustion chamber, acts on turbine part.
Wherein, the cooling gas discrete holes C through floating wall first for being used to form cooling air film enters hollow cavity progress
Convection current cools down, and forms positive pressure, then enters groove body through discrete holes A.Due to groove body be two sections formation compound special-shaped grooves, have compared with
Big depth is in narrow structure along the vertical cross-section of groove body width direction, and the diffusion gas from each discrete holes not only can be along slot
Body length Directional Extension, mixing, and can be spread along groove body depth direction, mix, be overlapped mutually, that is, it can be in groove body
First part fully develop, to form continuous, uniform barotropic gas, be then transmitted to out via the second part of groove body
Mouth end, since the shape of open end designs, cooling gas is biased to the outflow of burner inner liner internal face side, and company is formed in burner inner liner inner wall
The continuous cooling air film uniformly attached, and since groove body depth is larger, had by the cooling gas that groove body open end is flowed out strong
Big air pressure, therefore it is attached to burner inner liner internal face in the cooling air film strength of the continuous uniform of burner inner liner inner wall formation.
Embodiment 4：
In this implementation, the structure of aeroengine combustor buring room is as shown in Fig. 2, include burner inner liner 5, combustion process mainly occurs
In burner inner liner 5.
The partial structurtes enlarged drawing of flame tube wall is as shown in fig. 7, the inner wall 100 of burner inner liner 5 has the first of several indents
Groove body 105, the outer wall 101 of burner inner liner 5 have the second groove body 107 of several indents.First groove body 105 includes the first groove body bottom
500, and along the two side 600 and 700 of the first groove body length direction.Second groove body 107 includes the second groove body bottom 501,
And the two side 601 and 701 along the second groove body length direction.Each first groove body bottom 500, which is arranged, several is through to
The discrete holes A40 of two groove body bottoms 501, discrete holes A40 are arranged generally along the length direction of first groove body 105.
The maximum gauge of these discrete holes A is d, and the minimum widith of groove body is D, D >=d, and H >=2d.
In the present embodiment, the depth of the first groove body 105 is H, and the first groove body 105 is along depth direction at least by two parts group
At, as shown in fig. 7, from groove body bottom depth be H1Part be first part 302, remaining part be second part 301,
That is, second part depth is H2=H-H1。
In the present embodiment, the inclined column structure of first part 302, in vertical cross-section as shown in Figure 7, first
The two side for being divided to 302 is in two straightways for depositing interval, and two straightways are parallel to each other, and every straightway is with slot bottom angle
70°；One side wall of second part 301 is also straightway, is to be extended to form by the same side wall of first part, another side wall is in
Arc segment is formed by the same side wall lateral magnification of first part.In the present embodiment, second part is along the open end of depth direction
Angle α between the axis and the normal of matrix surface 101 in portion is 30 °.
In the present embodiment, H1Slightly larger than H2。
In the present embodiment, the angle theta between the central axis and the normal direction of flame drum outer wall 101 of discrete holes A is 15 °, and
And arc transition structure is arranged in the open end in hole, to avoid pointed structures stress concentration phenomenon.
Cooling gas being transmitted as in the present embodiment：The cooling gas of 101 side of flame drum outer wall is first transmitted to second
Groove body enters the first groove body, the cooling from each discrete holes A in the second groove body high efficiency of transmission and after forming positive pressure through discrete holes A
Gas can not only be extended along the first groove body length direction, be mixed, but also can spread, mix along the first groove body depth direction,
It is overlapped mutually, that is, can fully develop in the first part of the first groove body, to form continuous, uniform barotropic gas, so
It is transmitted to open end by the second part by the first groove body and is biased to the outflow of turbo blade outer wall side, in turbo blade outer wall shape
At the air film continuously uniformly attached, and since groove body depth is larger, had by the gas that groove body open end is flowed out powerful
Air pressure, therefore it is attached to burner inner liner inner wall in the air film strength of the continuous uniform of burner inner liner inner wall formation.
In the present embodiment, the method for preparing above-mentioned burner inner liner is：First, burner inner liner is divided into two parts, by fission I and divided
Body II is combined into a complete burner inner liner；Then, the first groove body is prepared in the inner wall of fission I, the second slot is prepared in outer wall
Body and discrete holes A prepare the first groove body in the inner wall of fission II, the second groove body and discrete holes A are prepared in outer wall；Finally, will divide
Body I and fission II combine, and link for a complete burner inner liner.
Technical scheme of the present invention is described in detail in embodiment described above, it should be understood that the above is only
For specific embodiments of the present invention, it is not intended to restrict the invention, all any modifications made in the spirit of the present invention,
Supplement or similar fashion replacement etc., should all be included in the protection scope of the present invention.
Claims (16)
1. a kind of combustion chamber with compound special-shaped groove gaseous film control structure, including burner inner liner, combustion process occur mainly in institute
It states in burner inner liner；It is characterized in that：
The inner wall of the burner inner liner has the groove body of several indents, and the groove body includes groove body bottom, and along groove body length
The two side in direction；It is big that several discrete holes A, the discrete holes A for being through to the flame drum outer wall are arranged in each groove body bottom
Body is arranged along the length direction of the groove body；
The depth of the groove body is H, and the groove body at least consists of two parts along depth direction, is H from groove body bottom depth1's
Part is first part, and remaining part is second part, that is, second part depth is H2=H-H1；At least the one of second part
Side wall is formed by the same side wall lateral magnification of first part.
2. the combustion chamber with compound special-shaped groove gaseous film control structure as described in claim 1, it is characterized in that：The burner inner liner
Floating wall is arranged in wall periphery, and cavity is formed between the floating wall and the outer wall of burner inner liner；If the side of the floating wall is arranged
The dry discrete holes B for being through to the hollow cavity.
3. the combustion chamber with compound special-shaped groove gaseous film control structure as described in claim 1, it is characterized in that：The burner inner liner
Prepare it is as follows：
First, the burner inner liner is divided at least two parts；Then, the inner wall in every part prepares first groove body, every
Partial outer wall prepares the discrete holes A；Finally, each section is combined, forms the burner inner liner；Alternatively, in the burner inner liner
Inner wall process second part, first part and the discrete holes A for forming the first groove body successively, obtain the burner inner liner.
4. a kind of combustion chamber with compound special-shaped groove gaseous film control structure, including burner inner liner, combustion process occur mainly in institute
It states in burner inner liner；It is characterized in that：Hollow cavity is set between the inner wall and outer wall of the burner inner liner；
Several discrete holes B for being through to the hollow cavity are arranged in the outer wall of the burner inner liner；
The inner wall of the burner inner liner has the groove body of several indents, and the groove body includes groove body bottom, and along groove body length
The two side in direction；Each groove body bottom is arranged several discrete holes for being through to the hollow cavity, the discrete holes substantially along
The length direction arrangement of the groove body；
The depth of the groove body is H, and the groove body at least consists of two parts along depth direction, is H from groove body bottom depth1's
Part is first part, and remaining part is second part, that is, second part depth is H2=H-H1；At least the one of second part
Side wall is formed by the same side wall lateral magnification of first part.
5. the combustion chamber with compound special-shaped groove gaseous film control structure as claimed in claim 4, it is characterized in that：The burner inner liner
Prepare it is as follows：
First, the burner inner liner is divided at least two parts；Then, the inner wall in every part prepares the groove body and discrete holes A,
Outer wall in every part prepares the discrete holes B；Finally, each section is combined, forms the burner inner liner.
6. a kind of combustion chamber with compound special-shaped groove gaseous film control structure, including burner inner liner, combustion process occur mainly in institute
It states in burner inner liner；It is characterized in that：The inner wall of the burner inner liner has the first groove body of several indents, the outer wall tool of the burner inner liner
There is the second groove body with several indents of several indents；First groove body includes groove body bottom, and along groove body length
The two side in direction；Second groove body includes groove body bottom, and the two side along groove body length direction；Each first slot
Several length of discrete holes A, the discrete holes A generally along first groove body for being through to the second groove body bottom are arranged in body bottom
Direction arranges；
The depth of first groove body is H, and first groove body at least consists of two parts along depth direction, from the first groove body bottom
Portion's depth is H1Part be first part, remaining part be second part, that is, second part depth be H2=H-H1；Second
Partial at least one side wall is formed by the same side wall lateral magnification of first part.
7. the combustion chamber with compound special-shaped groove gaseous film control structure as claimed in claim 6, it is characterized in that：The burner inner liner
Prepare it is as follows：
First, the burner inner liner is divided at least two parts；Then, the inner wall in every part prepares first groove body, every
Partial outer wall prepares second groove body and discrete holes A；Finally, each section is combined, is formed described with compound special-shaped groove
The turbo blade of gaseous film control structure.
8. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 7,
It is characterized in：The groove body is α along the normal angle of axis and the burner inner liner internal face of the open end of depth direction, 10 °≤α≤
90 °, preferably 30 °≤α≤80 °, further preferably 45 °≤α≤70 °.
9. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 7,
It is characterized in：In the vertical cross-section along groove body width direction of the groove body, the two side of first part is deposit interval two
Straightway；
Preferably, at least one side wall of second part is arc segment；
Preferably, the junction of the same side wall of at least one side wall and second part of first part connects for chamfered transition, or
Person connects for arc transition；
Preferably, the burner inner liner internal face and burner inner liner outside wall surface are parallel to each other or shape forms an angle.
10. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 7,
It is characterized in that：The maximum gauge of the discrete holes A is d, and the depth of the groove body is H, and the minimum widith of the groove body is D, D >=
D, and H >=2d, preferably H >=3d, further preferably H >=4d.
11. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 7,
It is characterized in that：The discrete holes A is straight circular hole or is diffusion hole or complicated abnormal shape hole；
Preferably, the angle of the central axis of the discrete holes A and flame drum outer wall is θ, 0 °≤θ≤60 °, preferably
10°≤θ≤45°；
Preferably, the open end setting chamfered transition structure or arc transition structure of the discrete holes A.
12. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 7,
It is characterized in that：The continuous air film that each groove body is formed forms all standing to burner inner liner internal face；Alternatively, each first groove body is formed
Continuous air film to burner inner liner internal face formed all standing.
13. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 7,
It is characterized in that：H1>H2；
Preferably, H1：H2≥2：1, further preferably H1：H2≥3：1, most preferably H1：H2≥4：1.
14. the combustion chamber with compound special-shaped groove gaseous film control structure as described in any claim in claim 1 to 5,
It is characterized in that：Every straightway of first part and slot bottom angle are 10 ° -170 °, preferably 30 ° -150 °, further preferably
60°-120°。
15. the combustion chamber with compound special-shaped groove gaseous film control structure as claimed in claims 6 or 7, it is characterized in that：First
The every straightway and the first slot bottom angle divided is 10 ° -170 °, preferably 30 ° -150 °, further preferably 60 ° -120 °.
16. the combustion chamber with compound special-shaped groove gaseous film control structure as described in claim 2 or 4, it is characterized in that：It is described from
Hole B and discrete holes A is dissipated to be dislocatedly distributed.
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| CN112146127A (en) * | 2020-08-13 | 2020-12-29 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN113251441A (en) * | 2021-06-28 | 2021-08-13 | 南京航空航天大学 | Novel many inclined hole board ellipsoid pendulum cooling structure for aeroengine |
| CN113483354A (en) * | 2021-07-16 | 2021-10-08 | 西北工业大学 | Bent truss structure heat shield for afterburner and method for forming gas film |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
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| CN112146127A (en) * | 2020-08-13 | 2020-12-29 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN112146127B (en) * | 2020-08-13 | 2022-04-08 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN113251441A (en) * | 2021-06-28 | 2021-08-13 | 南京航空航天大学 | Novel many inclined hole board ellipsoid pendulum cooling structure for aeroengine |
| CN113251441B (en) * | 2021-06-28 | 2022-03-25 | 南京航空航天大学 | Novel many inclined hole board ellipsoid pendulum cooling structure for aeroengine |
| CN113483354A (en) * | 2021-07-16 | 2021-10-08 | 西北工业大学 | Bent truss structure heat shield for afterburner and method for forming gas film |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
| CN115493163B (en) * | 2022-09-06 | 2024-02-20 | 清华大学 | Combustion chamber flame tube and high-efficiency cooling method thereof |
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