CN203980349U - For burner inner liner and the aero-engine of aeroengine combustor buring chamber - Google Patents
For burner inner liner and the aero-engine of aeroengine combustor buring chamber Download PDFInfo
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- CN203980349U CN203980349U CN201420293197.8U CN201420293197U CN203980349U CN 203980349 U CN203980349 U CN 203980349U CN 201420293197 U CN201420293197 U CN 201420293197U CN 203980349 U CN203980349 U CN 203980349U
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Abstract
The utility model discloses a kind of burner inner liner for aeroengine combustor buring chamber and aero-engine.Burner inner liner comprises ring section in burner inner liner head sections, burner inner liner outer shroud leading portion, burner inner liner outer shroud back segment and burner inner liner, and burner inner liner outer shroud back segment is provided with the first admission gear with the position that burner inner liner outer shroud leading portion is connected; Burner inner liner outer shroud leading portion is connected with the first end of burner inner liner head sections, and the position that burner inner liner outer shroud leading portion is connected with burner inner liner head sections is provided with the second admission gear; In burner inner liner, ring section is connected with the second end of burner inner liner head sections, and the position that in burner inner liner, ring section is connected with burner inner liner head sections is provided with the 3rd admission gear; On the wall body of burner inner liner head sections, offer head air admission hole; The first admission gear, the second admission gear, the 3rd admission gear and head air admission hole, all by the inner chamber of the air guide burner inner liner head sections of introducing, form recirculation zone at the inner chamber of burner inner liner head sections.Can cooling wall and smooth combustion.
Description
Technical field
The utility model relates to aero engine technology field, especially, relates to a kind of burner inner liner for aeroengine combustor buring chamber.In addition, the utility model also relates to a kind of aero-engine that comprises above-mentioned burner inner liner.
Background technology
Combustion chamber flame drum is for controlling fuel oil and air burning, controls air mass flow and distributes, the cavity of tissue burning and cooling-air film.Aeroengine combustor buring chamber burner inner liner generally comprises ring, burner inner liner head and swirler in burner inner liner outer shroud, burner inner liner.Cooling-air enters burner inner liner by air film hole, forms air film at burner inner liner wall, directly contacts with burner inner liner wall in order to intercept high-temperature fuel gas.These burner inner liner wall cooling structures all only have the effect of cooling wall.Except air film hole, that conventional burner inner liner wall cooling structure impacts is in addition cold, it is cooling etc. to disperse.These cooling structures all only have the effect of cooling wall.
Existing combustion chamber flame drum wants smooth combustion need on burner inner liner, offer in addition primary holes and swirler is set, and combustion air enters burner inner liner by primary holes, forms recirculating zone with swirler air inlet, thus smooth combustion.Its complex structure, has strengthened the difficulty of processing of burner inner liner, and increase swirler, burner inner liner deadweight is increased, and has increased manufacturing cost.Swirler cannot be stablized grasp gas flow rate simultaneously, likely causes primary zone combustion gas to accelerate, and makes mist of oil and air undercompounding, causes burning insufficient.
Utility model content
The utility model object is to provide a kind of burner inner liner for aeroengine combustor buring chamber and aero-engine, all only has the effect of cooling wall to solve existing burner inner liner wall cooling structure; And want the burner inner liner burning of smooth combustion chamber need on burner inner liner, offer in addition hole and loading equipemtn, cause cost increase, deadweight increase, difficulty of processing to increase; Gas flow rate is uncontrollable, causes that combustion gas mixing is insufficient, the inadequate technical problem of burning.
For achieving the above object, the technical solution adopted in the utility model is as follows:
A kind of burner inner liner for aeroengine combustor buring chamber, comprise ring section in burner inner liner head sections, burner inner liner outer shroud leading portion, burner inner liner outer shroud back segment and burner inner liner, burner inner liner outer shroud back segment is connected with burner inner liner outer shroud leading portion, the first admission gear that the position that burner inner liner outer shroud back segment is connected with burner inner liner outer shroud leading portion is provided with to introduce air; Burner inner liner outer shroud leading portion is connected with the first end of burner inner liner head sections, and the position that burner inner liner outer shroud leading portion is connected with burner inner liner head sections is provided with to introduce the second admission gear of air; In burner inner liner, ring section is connected with the second end of burner inner liner head sections, the 3rd admission gear that the position that in burner inner liner, ring section is connected with burner inner liner head sections is provided with to introduce air; On the wall body of burner inner liner head sections, offer head air admission hole; The first admission gear, the second admission gear, the 3rd admission gear and head air admission hole, all by the inner chamber of the air guide burner inner liner head sections of introducing, form recirculation zone at the inner chamber of burner inner liner head sections.
Further, the second admission gear and the dislocation of the first admission gear are arranged; And/or the dislocation of the second admission gear and the 3rd admission gear is arranged.
Further, the first end of burner inner liner head sections is with the first bend, burner inner liner head sections is overlapped on by the first bend outside the wall body of burner inner liner outer shroud leading portion, overlapping part adopts and is tightly connected, the first admission gear is located on the first bend, or the first admission gear is located at burner inner liner outer shroud leading portion simultaneously on the position of stretching to burner inner liner head sections and is located on the first bend; Burner inner liner outer shroud leading portion is with the second bend, burner inner liner outer shroud leading portion is overlapped on by the second bend outside the wall body of burner inner liner outer shroud back segment, overlapping part adopts and is tightly connected, the second admission gear is located on the second bend, or the second admission gear is located at burner inner liner outer shroud back segment simultaneously on the position of stretching to burner inner liner outer shroud leading portion and is located on the second bend; The second end of burner inner liner head sections is with the 3rd bend, burner inner liner head sections is overlapped on by the 3rd bend outside the wall body of ring section in burner inner liner, overlapping part adopts and is tightly connected, the 3rd admission gear is located on the 3rd bend, or the 3rd admission gear is located in burner inner liner ring section simultaneously on the position of stretching to burner inner liner head sections and is located on the 3rd bend.
Further, the first admission gear comprises that at least one is opened in the first air film hole on the first bend and at least one is opened in first airport of burner inner liner outer shroud leading portion on the position of stretching to burner inner liner head sections, on the wall body of burner inner liner outer shroud leading portion, offer the first crack arrest groove for air guide from the first airport to burner inner liner head sections direction, the first air film hole is corresponding with the first airport to be arranged in groups, and corresponding the first air film hole arranged of many groups and the first airport are along circumferentially equidistantly arranging.
Further, the second admission gear comprises that at least one is opened in the second air film hole on the second bend and at least one is opened in second airport of burner inner liner outer shroud back segment on the position of stretching to burner inner liner outer shroud leading portion, on the wall body of burner inner liner outer shroud back segment, offer the second crack arrest groove for air guide from the second airport to burner inner liner head sections direction, the second air film hole is corresponding with the second airport to be arranged in groups, and corresponding the second air film hole arranged of many groups and the second airport are along circumferentially equidistantly arranging.
Further, the 3rd admission gear comprises that at least one is opened in the 3rd air film hole on the 3rd bend and at least one is opened in three airport of ring section on the position of stretching to burner inner liner head sections in burner inner liner, in burner inner liner, on the wall body of ring section, offer the 3rd crack arrest groove for air guide from the 3rd airport to burner inner liner head sections direction, the 3rd air film hole is with the 3rd airport is corresponding arranges in groups, and corresponding the 3rd air film hole of arranging of many groups and the 3rd airport are along circumferentially equidistantly arranging.
Further, the 3rd bend and the dislocation of the first bend are arranged, and/or the 3rd bend and the second bend dislocation layout.
Further, on burner inner liner outer shroud back segment and/or in burner inner liner, in ring section, offer the blending hole of introducing dilution air for the dilution zone between ring section in burner inner liner outer shroud back segment and burner inner liner.
Further, blending hole is set to multiple, and multiple blending hole are equidistantly arranged.
According on the other hand of the present utility model, a kind of aero-engine is also provided, it comprises the above-mentioned burner inner liner for aeroengine combustor buring chamber.
The utlity model has following beneficial effect:
This is for the burner inner liner of aeroengine combustor buring chamber, the first admission gear, the second admission gear, the 3rd admission gear and head air admission hole are by the air of introducing from different directions, make air form recirculation zone at the inner chamber of burner inner liner head sections, can be in order to cooling wall, make the combustion gas in inner chamber fully mix simultaneously; By admission gear being set at the each parts connecting portion of burner inner liner, have the function of cooling wall and tissue burning formation recirculating zone concurrently, simplify chamber structure; By admission gear and the automatic regulating gas flow velocity of head air admission hole, make primary zone combustion gas speed low, mist of oil can fully mix, burn with air, makes burning more abundant.
Except object described above, feature and advantage, the utility model also has other object, feature and advantage.Below with reference to figure, the utility model is described in further detail.
Brief description of the drawings
The accompanying drawing that forms the application's a part is used to provide further understanding of the present utility model, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is one of structural representation of the burner inner liner for aeroengine combustor buring chamber of the utility model preferred embodiment;
Fig. 2 be the burner inner liner for aeroengine combustor buring chamber of the utility model preferred embodiment structural representation two.
Marginal data:
1, burner inner liner head sections; 2, burner inner liner outer shroud leading portion; 3, burner inner liner outer shroud back segment; 4, ring section in burner inner liner; 5, the first admission gear; 501, the first air film hole; 502, the first airport; 503, the first crack arrest groove; 6, the second admission gear; 601, the second air film hole; 602, the second airport; 603, the second crack arrest groove; 7, the 3rd admission gear; 701, the 3rd air film hole; 702, the 3rd airport; 703, the 3rd crack arrest groove; 8, the first bend; 9, the second bend; 10, the 3rd bend; 11, blending hole; 12, head air admission hole.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated, but the utility model can by the multitude of different ways that limits and cover implement.
Fig. 1 is one of structural representation of the burner inner liner for aeroengine combustor buring chamber of the utility model preferred embodiment; Fig. 2 be the burner inner liner for aeroengine combustor buring chamber of the utility model preferred embodiment structural representation two.
As shown in Figure 1, the burner inner liner for aeroengine combustor buring chamber of the present embodiment, comprise ring section 4 in burner inner liner head sections 1, burner inner liner outer shroud leading portion 2, burner inner liner outer shroud back segment 3 and burner inner liner, burner inner liner outer shroud back segment 3 is connected with burner inner liner outer shroud leading portion 2, and the position that burner inner liner outer shroud back segment 3 is connected with burner inner liner outer shroud leading portion 2 is provided with to introduce the first admission gear 5 of air; Burner inner liner outer shroud leading portion 2 is connected with the first end of burner inner liner head sections 1, and the position that burner inner liner outer shroud leading portion 2 is connected with burner inner liner head sections 1 is provided with to introduce the second admission gear 6 of air; In burner inner liner, ring section 4 is connected with the second end of burner inner liner head sections 1, the 3rd admission gear 7 that in burner inner liner, ring section 4 positions that are connected with burner inner liner head sections 1 are provided with to introduce air; On the wall body of burner inner liner head sections 1, offer head air admission hole 12; The first admission gear 5, the second admission gear 6, the 3rd admission gear 7 and head air admission hole 12, all by the inner chamber of the air guide burner inner liner head sections 1 of introducing, form recirculation zone at the inner chamber of burner inner liner head sections 1.This is for the burner inner liner of aeroengine combustor buring chamber, the first admission gear 5, the second admission gear 6, the 3rd admission gear 7 and head air admission hole 12 are by the air of introducing from different directions, make air form recirculation zone at the inner chamber of burner inner liner head sections 1, can be in order to cooling wall, make the combustion gas in inner chamber fully mix simultaneously; By admission gear being set at the each parts connecting portion of burner inner liner, have the function of cooling wall and tissue burning formation recirculating zone concurrently, simplify chamber structure; By admission gear and the automatic regulating gas flow velocity of head air admission hole 12, make primary zone combustion gas speed low, mist of oil can fully mix, burn with air, makes burning more abundant.
As depicted in figs. 1 and 2, in the present embodiment, the second admission gear 6 and 5 dislocation of the first admission gear are arranged.The second admission gear 6 and 7 dislocation of the 3rd admission gear are arranged.Dislocation is arranged can prevent that charge air flow from liquidating mutually, thereby ensures that the air-flow that all directions enter can form the recirculation zone circulating at inner chamber, makes inner combustion gas mixing more abundant, burns more abundant.
As depicted in figs. 1 and 2, in the present embodiment, the first end of burner inner liner head sections 1 is with the first bend 8.Burner inner liner head sections 1 is overlapped on by the first bend 8 outside the wall body of burner inner liner outer shroud leading portion 2, and overlapping part adopts and is tightly connected.The first admission gear 5 is located on the first bend 8, or the first admission gear 5 is located at burner inner liner outer shroud leading portion 2 simultaneously on the position of stretching to burner inner liner head sections 1 and is located on the first bend 8.Burner inner liner outer shroud leading portion 2 is with the second bend 9.Burner inner liner outer shroud leading portion 2 is overlapped on by the second bend 9 outside the wall body of burner inner liner outer shroud back segment 3, and overlapping part adopts and is tightly connected.The second admission gear 6 is located on the second bend 9, or the second admission gear 6 is located at burner inner liner outer shroud back segment 3 simultaneously on the position of stretching to burner inner liner outer shroud leading portion 2 and is located on the second bend 9.The second end of burner inner liner head sections 1 is with the 3rd bend 10.Burner inner liner head sections 1 is overlapped on outside the wall body of ring section 4 in burner inner liner by the 3rd bend 10, and overlapping part adopts and is tightly connected.The 3rd admission gear 7 is located on the 3rd bend 10, or the 3rd admission gear 7 is located in burner inner liner ring section 4 simultaneously on the position of stretching to burner inner liner head sections 1 and is located on the 3rd bend 10.By the position connecting, bend is set between parts, and adopts the form of overlap joint to connect, provide cushion space for air enters, improve by simple structural form the speed that air enters, improve air inlet.Overlapping part adopts and is tightly connected, thereby ensures the sealing of structure, makes the circulation of air more smooth, improves the globality of structure, reduces structure risk in use.
As depicted in figs. 1 and 2, in the present embodiment, the first admission gear 5 comprises that at least one is opened in the first air film hole 501 on the first bend 8 and at least one is opened in first airport 502 of burner inner liner outer shroud leading portion 2 on the position of stretching to burner inner liner head sections 1, on the wall body of burner inner liner outer shroud leading portion 2, offer the first crack arrest groove 503 for air guide from the first airport 502 to burner inner liner head sections 1 direction, the first air film hole 501 is with first airport 502 is corresponding arranges in groups, corresponding the first air film hole 501 arranged of many groups and the first airport 502 are along circumferentially equidistantly arranging.Enter air by the first air film hole 501, play the effect of cooling wall; By the first airport 502 and the first crack arrest groove 503 by the air entering from the first air film hole 501 burner inner liner head sections 1 that leads rapidly, by cooperatively interacting with head air admission hole 12, form air return, the combustion gas in burner inner liner is fully mixed, combustion gas is fully burned.
As depicted in figs. 1 and 2, in the present embodiment, the second admission gear 6 comprises that at least one is opened in the second air film hole 601 on the second bend 9 and at least one is opened in second airport 602 of burner inner liner outer shroud back segment 3 on the position of stretching to burner inner liner outer shroud leading portion 2, on the wall body of burner inner liner outer shroud back segment 3, offer the second crack arrest groove 603 for air guide from the second airport 602 to burner inner liner head sections 1 direction, the second air film hole 601 is with second airport 602 is corresponding arranges in groups, corresponding the second air film hole 601 arranged of many groups and the second airport 602 are along circumferentially equidistantly arranging.Enter air by the second air film hole 601, play the effect of cooling wall; By the second airport 602 and the second crack arrest groove 603 by the air entering from the second air film hole 601 burner inner liner head sections 1 that leads rapidly, by cooperatively interacting with head air admission hole 12, form air return, the combustion gas in burner inner liner is fully mixed, combustion gas is fully burned.
As depicted in figs. 1 and 2, in the present embodiment, the 3rd admission gear 7 comprises that at least one is opened in the 3rd air film hole 701 on the 3rd bend 10 and at least one is opened in three airport 702 of ring section 4 on the position of stretching to burner inner liner head sections 1 in burner inner liner, in burner inner liner, on the wall body of ring section 4, offer the 3rd crack arrest groove 703 for air guide from the 3rd airport 702 to burner inner liner head sections 1 direction, the 3rd air film hole 701 is with the 3rd airport 702 is corresponding arranges in groups, corresponding the 3rd air film hole 701 of arranging of many groups and the 3rd airport 702 are along circumferentially equidistantly arranging.Enter air by the 3rd air film hole 701, play the effect of cooling wall; By the 3rd airport 702 and the 3rd crack arrest groove 703 by the air entering from the 3rd air film hole 701 burner inner liner head sections 1 that leads rapidly, by cooperatively interacting with head air admission hole 12, form air return, the combustion gas in burner inner liner is fully mixed, combustion gas is fully burned.
As depicted in figs. 1 and 2, in the present embodiment, the 3rd bend 10 and the first bend 8 dislocation are arranged, and/or the 3rd bend 10 and the second bend 9 dislocation layouts.Dislocation is arranged can prevent that charge air flow from liquidating mutually, thereby ensures that the air-flow that all directions enter can form the recirculation zone circulating at inner chamber, makes inner combustion gas mixing more abundant, burns more abundant.
As depicted in figs. 1 and 2, in the present embodiment, on burner inner liner outer shroud back segment 3 and/or in burner inner liner, in ring section 4, offer the blending hole 11 of introducing dilution air for the dilution zone between ring section 4 in burner inner liner outer shroud back segment 3 and burner inner liner.Make dilution air abundance, outlet temperature field is easy to regulation and control.
As depicted in figs. 1 and 2, in the present embodiment, blending hole 11 is set to multiple, and multiple blending hole 11 are equidistantly arranged.Make dilution air abundance, outlet temperature field is easy to regulation and control.
The aero-engine of the present embodiment, comprises the above-mentioned burner inner liner for aeroengine combustor buring chamber.
When enforcement, the structural design of primary holes, afterburning hole, swirler has been cancelled in burner inner liner combustion zone.At burner inner liner head design two exhaust fenestras, row's air admission hole.Burner inner liner outer shroud leading portion 2 is an exhaust fenestra (the first air film hole 501).The interior ring section 4 of burner inner liner outer shroud leading portion 2, burner inner liner outer shroud back segment 3 and burner inner liner is provided with the airport with the corresponding layout of air film hole, the ring section 4 some airports of each design and crack arrest grooves in burner inner liner outer shroud leading portion 2, burner inner liner outer shroud back segment 3, burner inner liner, as shown in Figure 1 and Figure 2.Simplified flame combustion chamber barrel structure, air film hole air inlet both can cooling wall, again can be in formation recirculating zone, primary zone, smooth combustion.
Enter the attached wall cooling wall of part air of burner inner liner by air film hole, and most of air enters burner inner liner participation burning by airport.Different according to the relative position of the quantity of airport, airport and air film hole and head air admission hole 12, can meet the burning gas requirement of different parameters.On burner inner liner inner and outer ring, under the reverse air-spray of air film hole and the acting in conjunction of head air admission hole 12, burner inner liner primary zone will form the recirculating zone (as shown in Figure 2) of single maelstrom structure.Fuel oil can fully mix, evaporates and burn in recirculating zone, and remaining unburnt fuel oil Bu Ran district burns away.Due to air film hole, to account for total open area ratio little, and air inflow is less, so air velocity is lower in recirculating zone, fresh oil gas mixture has sufficient time preheating, is conducive to igniting and tissue burning.
Burner inner liner inner and outer rings air film hole has cooling wall concurrently and burns and form the function of recirculating zone with tissue, has simplified chamber structure; Primary zone combustion gas speed is low, and mist of oil can fully mix with air, burning; Dilution air abundance, outlet temperature field is easy to regulation and control.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (10)
1. for a burner inner liner for aeroengine combustor buring chamber, comprise ring section (4) in burner inner liner head sections (1), burner inner liner outer shroud leading portion (2), burner inner liner outer shroud back segment (3) and burner inner liner,
It is characterized in that,
Described burner inner liner outer shroud back segment (3) is connected with described burner inner liner outer shroud leading portion (2), and the position that described burner inner liner outer shroud back segment (3) is connected with described burner inner liner outer shroud leading portion (2) is provided with to introduce first admission gear (5) of air;
Described burner inner liner outer shroud leading portion (2) is connected with the first end of described burner inner liner head sections (1), and the position that described burner inner liner outer shroud leading portion (2) is connected with described burner inner liner head sections (1) is provided with to introduce second admission gear (6) of air;
In described burner inner liner, ring section (4) is connected with the second end of described burner inner liner head sections (1), the 3rd admission gear (7) that the position that in described burner inner liner, ring section (4) is connected with described burner inner liner head sections (1) is provided with to introduce air;
On the wall body of described burner inner liner head sections (1), offer head air admission hole (12);
Described the first admission gear (5), described the second admission gear (6), described the 3rd admission gear (7) and described head air admission hole (12), all by the inner chamber of burner inner liner head sections (1) described in the air guide of introducing, form recirculation zone at the inner chamber of described burner inner liner head sections (1).
2. the burner inner liner for aeroengine combustor buring chamber according to claim 1, is characterized in that,
Described the second admission gear (6) and described the first admission gear (5) dislocation layout;
And/or described the second admission gear (6) and described the 3rd admission gear (7) dislocation layout.
3. the burner inner liner for aeroengine combustor buring chamber according to claim 1, is characterized in that,
The first end of described burner inner liner head sections (1) is with the first bend (8),
Described burner inner liner head sections (1) is overlapped on by described the first bend (8) outside the wall body of described burner inner liner outer shroud leading portion (2), and overlapping part adopts and is tightly connected,
It is upper that described the first admission gear (5) is located at described the first bend (8), or described the first admission gear (5) is located at described burner inner liner outer shroud leading portion (2) simultaneously on the position of stretching to described burner inner liner head sections (1) and is located on described the first bend (8);
Described burner inner liner outer shroud leading portion (2) is with the second bend (9),
Described burner inner liner outer shroud leading portion (2) is overlapped on by described the second bend (9) outside the wall body of described burner inner liner outer shroud back segment (3), and overlapping part adopts and is tightly connected,
It is upper that described the second admission gear (6) is located at described the second bend (9), or described the second admission gear (6) is located at described burner inner liner outer shroud back segment (3) simultaneously on the position of stretching to described burner inner liner outer shroud leading portion (2) and is located on described the second bend (9);
The second end of described burner inner liner head sections (1) is with the 3rd bend (10),
Described burner inner liner head sections (1) is overlapped on by described the 3rd bend (10) outside the wall body of ring section (4) in described burner inner liner, and overlapping part adopts and is tightly connected,
It is upper that described the 3rd admission gear (7) is located at described the 3rd bend (10), or described the 3rd admission gear (7) is located in described burner inner liner ring section (4) simultaneously on the position of stretching to described burner inner liner head sections (1) and is located on described the 3rd bend (10).
4. the burner inner liner for aeroengine combustor buring chamber according to claim 3, is characterized in that,
Described the first admission gear (5) comprises that at least one is opened in the first air film hole (501) on described the first bend (8) and at least one is opened in first airport (502) of described burner inner liner outer shroud leading portion (2) on the position of stretching to described burner inner liner head sections (1)
On the wall body of described burner inner liner outer shroud leading portion (2), offer the first crack arrest groove (503) for air guide from described the first airport (502) to described burner inner liner head sections (1) direction,
Described the first air film hole (501) is corresponding with described the first airport (502) to be arranged in groups,
Corresponding described the first air film hole (501) arranged of many groups and described the first airport (502) are along circumferentially equidistantly arranging.
5. the burner inner liner for aeroengine combustor buring chamber according to claim 3, is characterized in that,
Described the second admission gear (6) comprises that at least one is opened in the second air film hole (601) on described the second bend (9) and at least one is opened in second airport (602) of described burner inner liner outer shroud back segment (3) on the position of stretching to described burner inner liner outer shroud leading portion (2)
On the wall body of described burner inner liner outer shroud back segment (3), offer the second crack arrest groove (603) for air guide from described the second airport (602) to described burner inner liner head sections (1) direction,
Described the second air film hole (601) is corresponding with described the second airport (602) to be arranged in groups,
Corresponding described the second air film hole (601) arranged of many groups and described the second airport (602) are along circumferentially equidistantly arranging.
6. the burner inner liner for aeroengine combustor buring chamber according to claim 3, is characterized in that,
Described the 3rd admission gear (7) comprises that at least one is opened in the 3rd air film hole (701) on described the 3rd bend (10) and at least one is opened in ring section (4) the 3rd airport (702) on the position of stretching to described burner inner liner head sections (1) in described burner inner liner
In described burner inner liner, on the wall body of ring section (4), offer the 3rd crack arrest groove (703) for air guide from described the 3rd airport (702) to described burner inner liner head sections (1) direction,
Described the 3rd air film hole (701) is with the described the 3rd airport (702) is corresponding arranges in groups,
Corresponding described the 3rd air film hole (701) of arranging of many groups and described the 3rd airport (702) are along circumferentially equidistantly arranging.
7. the burner inner liner for aeroengine combustor buring chamber according to claim 3, is characterized in that,
Described the 3rd bend (10) and described the first bend (8) dislocation layout,
And/or described the 3rd bend (10) is arranged with described the second bend (9) dislocation.
8. according to the burner inner liner for aeroengine combustor buring chamber described in any one in claim 1 to 7, it is characterized in that, in the upper and/or described burner inner liner of described burner inner liner outer shroud back segment (3), in ring section (4), offer the blending hole (11) for the dilution zone introducing dilution air between ring section (4) in described burner inner liner outer shroud back segment (3) and described burner inner liner.
9. the burner inner liner for aeroengine combustor buring chamber according to claim 8, is characterized in that, described blending hole (11) is set to multiple, and multiple described blending hole (11) are equidistantly arranged.
10. an aero-engine, is characterized in that, comprises the burner inner liner for aeroengine combustor buring chamber described in any one in claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420293197.8U CN203980349U (en) | 2014-06-04 | 2014-06-04 | For burner inner liner and the aero-engine of aeroengine combustor buring chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420293197.8U CN203980349U (en) | 2014-06-04 | 2014-06-04 | For burner inner liner and the aero-engine of aeroengine combustor buring chamber |
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| CN203980349U true CN203980349U (en) | 2014-12-03 |
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| CN109060152A (en) * | 2018-07-19 | 2018-12-21 | 中国航发沈阳发动机研究所 | A kind of thermocouple sensor for the test of combustor exit thermal field |
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| CN111878851A (en) * | 2020-07-31 | 2020-11-03 | 中国航发湖南动力机械研究所 | Flame tube and engine |
| CN113137627A (en) * | 2021-03-29 | 2021-07-20 | 华东师范大学 | Machining and positioning method for aero-engine flame tube cooling air film hole |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109060152A (en) * | 2018-07-19 | 2018-12-21 | 中国航发沈阳发动机研究所 | A kind of thermocouple sensor for the test of combustor exit thermal field |
| CN109060152B (en) * | 2018-07-19 | 2020-10-09 | 中国航发沈阳发动机研究所 | Thermocouple sensor for testing outlet temperature field of combustion chamber |
| CN111829012A (en) * | 2019-04-17 | 2020-10-27 | 中国航发湖南动力机械研究所 | Flame tube |
| CN111829012B (en) * | 2019-04-17 | 2022-04-08 | 中国航发湖南动力机械研究所 | Flame tube |
| US11591267B2 (en) | 2019-08-15 | 2023-02-28 | Central South University | Automated preparation method of a SiCf/SiC composite flame tube |
| CN111503659A (en) * | 2020-04-28 | 2020-08-07 | 中国航发湖南动力机械研究所 | Flame tube, micro turbojet engine and preparation process of flame tube |
| CN111503659B (en) * | 2020-04-28 | 2021-11-09 | 中国航发湖南动力机械研究所 | Flame tube, micro turbojet engine and preparation process of flame tube |
| CN111878851A (en) * | 2020-07-31 | 2020-11-03 | 中国航发湖南动力机械研究所 | Flame tube and engine |
| CN113137627A (en) * | 2021-03-29 | 2021-07-20 | 华东师范大学 | Machining and positioning method for aero-engine flame tube cooling air film hole |
| CN113137627B (en) * | 2021-03-29 | 2022-07-08 | 星控激光科技(上海)有限公司 | Machining and positioning method for cooling air film hole of flame tube of aircraft engine |
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