CN203431932U - Flame tube used for aero-engine - Google Patents
Flame tube used for aero-engine Download PDFInfo
- Publication number
- CN203431932U CN203431932U CN201320436883.1U CN201320436883U CN203431932U CN 203431932 U CN203431932 U CN 203431932U CN 201320436883 U CN201320436883 U CN 201320436883U CN 203431932 U CN203431932 U CN 203431932U
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- CN
- China
- Prior art keywords
- inner liner
- burner inner
- engine
- aero
- flame tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
The utility model discloses a flame tube used for an aero-engine. The flame tube comprises a flame tube head (1) and a flame tube rear end (2). The flame tube head (1) is arranged on an engine combustion chamber casing (8). The flame tube rear end (2) is arranged on an engine inner casing (5). The end part of the flame tube rear end (2) is provided with an arc-shaped installing ring (3). The tail part of the arc-shaped installing ring (3) is fixedly connected to the engine inner casing (5) through a connecting piece (4). The flame tube rear end, capable of compensating thermal deformation, is adopted for positioning; the flame tube rear end is directly connected to the inner casing in the process of positioning, so that too large gaps of the flame tube rear end are avoided, good assembly of the flame tube under a cold condition is ensured, and the flame tube is interference-free under a hot condition. The flame tube used for the aero-engine has the advantages of simple structure, convenient disassembly and reliable positioning.
Description
Technical field
The utility model relates to aero engine technology field, especially, relates to a kind of aero-engine burner inner liner.
Background technology
In aero-engine field, require burner inner liner on certain locus, to work in combustion chamber, in order to ensure this requirement, need to adopt a kind of locate mode, locate mode is wanted the assembling that can guarantee that burner inner liner can be good under cold conditions, hot lower to interfering.
The locate mode of burner inner liner is divided into two kinds of front-end and back-end locate mode at present, front end location to be adopted the head soldering pin nail seat of burner inner liner or directly on burner inner liner outer shroud, welds pin, by pin, connect and realize location, this locate mode structure location is reliable, but to often change pin in assembling and dissembling process, and rear end radial clearance is larger, along with the variation of duty, to use mouthful radial temperature profile influenced, and thermal compensation ability is poor; Location, rear end is to be directly connected to casing rear end in the rear end of burner inner liner, and welding support plate is connected on nozzle ring.This locate mode is simple and reliable for structure, and convenient disassembly is also little on exporting a temperature impact, but shortcoming is distortion, focuses on front end and can affect head fuel-air matching.
Therefore, developing a kind of novel aero-engine has been technical problem urgently to be resolved hurrily with burner inner liner.
Utility model content
The utility model object is to provide a kind of aero-engine burner inner liner, to solve the needs due to properity design, occurs the technical problem of the phenomenon etc. of hot lower interference in the Position Design of burner inner liner.
For achieving the above object, according to an aspect of the present utility model, a kind of aero-engine burner inner liner is provided, comprise burner inner liner head and burner inner liner rear end, burner inner liner head is arranged on engine chamber casing position, burner inner liner rear end is arranged on casing position in engine, and the end of burner inner liner rear end is provided with arch installing ring, and the afterbody of arch installing ring is fixed in engine on casing by connector.
Further, connector is connecting bolt.
Further, the cross sectional shape of arch installing ring is V-arrangement, N shape or W shape.
Further, arch installing ring is loop configuration.
Further, on burner inner liner head, be provided with the keeper of spacing between control engine combustion box and burner inner liner.
Further, keeper is locating pin.
Further, keeper radially arranges along burner inner liner.
Further, a plurality of keepers circumferentially and/or are vertically arranged along ring.
Further, a plurality of keepers equidistantly or unequal-interval arrange.
Further, on engine chamber casing and burner inner liner head, be also provided with fuel nozzle, fuel nozzle radially arranges along burner inner liner, and fuel nozzle is simultaneously through the wall body of engine chamber casing and the wall body of burner inner liner head.
The utlity model has following beneficial effect:
A, this burner inner liner adopt the location, burner inner liner rear end that can compensate thermal deformation; locate mode is directly connected to the rear end of burner inner liner on interior casing; there will not be burner inner liner rear end excesssive gap, can guarantee the assembling that burner inner liner can be good under cold conditions, hot lower to interfering.There is simple in structure, convenient disassembly and locate reliable feature.
B, head rest supporting have avoided some location, rear end that distortion is focused on to the head oil gas variation that front end causes.
C, head adopt locating pin supporting to reduce front end because of the deflection that is heated and causes, thereby reduce because of the next head fuel-air matching problem of head Zona transformans, and the Over-constrained that such structure may be brought is also compensated by the domes of burner inner liner rear end installing ring.
The cross sectional shape of d, arch installing ring adopts V-arrangement, N shape or W shape, forms multi-layered compensation, and hot lower interference can be directly left in the basket, and reaches without interfering.
E, use three above locating pins to stretch into burner inner liner to carry out radial support, play the effect of auxiliary positioning, play the effect of other parts of radial location (as nozzle) simultaneously.
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.
Accompanying drawing explanation
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 the structural representation of the burner inner liner rear end of burner inner liner for the aero-engine of the utility model preferred embodiment;
Fig. 2 is the structural representation of the burner inner liner head of burner inner liner for the aero-engine of the utility model preferred embodiment.
The specific embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
Fig. 1 is the structural representation of the burner inner liner rear end of burner inner liner for the aero-engine of the utility model preferred embodiment, as shown in Figure 1, aero-engine burner inner liner, comprise burner inner liner head 1 and burner inner liner rear end 2, burner inner liner head 1 is arranged on engine chamber casing 8 positions, burner inner liner rear end 2 is arranged on casing 5 positions in engine, and the end of burner inner liner rear end 2 is provided with arch installing ring 3, and the afterbody of arch installing ring 3 is fixed in engine on casing 5 by connector 4.Connector 4 is connecting bolt.The cross sectional shape of arch installing ring 3 is V-arrangement, N shape or W shape.Arch installing ring 3 is loop configuration.This burner inner liner adopts the location, burner inner liner rear end that can compensate thermal deformation, and locate mode is directly connected to the rear end of burner inner liner on casing, there will not be burner inner liner rear end excesssive gap, can guarantee the assembling that burner inner liner can be good under cold conditions, hot lower to interfering.There is simple in structure, convenient disassembly and locate reliable feature.
Fig. 2 is the structural representation of the burner inner liner head of burner inner liner for the aero-engine of the utility model preferred embodiment, as shown in Figure 2, is provided with the keeper 6 of spacing between control engine combustion box 8 and burner inner liner on burner inner liner head 1.Keeper 6 is locating pin.Keeper 6 radially arranges along burner inner liner.A plurality of keepers 6 circumferentially and/or are vertically arranged along ring.A plurality of keepers 6 equidistantly or unequal-interval arrange.On engine chamber casing 8 and burner inner liner head 1, be also provided with fuel nozzle 7, fuel nozzle 7 radially arranges along burner inner liner, and fuel nozzle 7 is simultaneously through the wall body of engine chamber casing 8 and the wall body of burner inner liner head.Head rest supporting has avoided some location, rear end that distortion is focused on to the head oil gas variation that front end causes.Head adopts locating pin supporting to reduce front end because of the deflection that is heated and causes, thereby reduces because of the next head fuel-air matching problem of head Zona transformans, and the Over-constrained that such structure may be brought is also compensated by the domes of burner inner liner rear end installing ring.The cross sectional shape of arch installing ring adopts V-arrangement, N shape or W shape, forms multi-layered compensation, and hot lower interference can be directly left in the basket, and reaches without interfering.Use three above locating pins to stretch into burner inner liner and carry out radial support, play the effect of auxiliary positioning, play the effect of other parts of radial location (as nozzle) simultaneously.
During enforcement, adopt a kind of 2 location, burner inner liner rear end that can compensate thermal deformation, 1 supporting of burner inner liner head, the burner inner liner location structure of installation arch installing ring 3.Locate mode is that burner inner liner rear end 2 is directly connected in engine on casing 5, can not produce rear splaying, and burner inner liner head 1 adopts locating pin supporting to reduce burner inner liner head 1 because the deflection that is heated and causes, thereby reduce the head fuel-air matching problem of bringing because of 1 distortion of burner inner liner head, the Over-constrained that such structure may be brought is also compensated by the domes of the arch installing ring 3 of burner inner liner rear end 2.That this location has is simple in structure, convenient disassembly and locate reliable feature.
Concrete mode during assembling is first to use connecting bolt that burner inner liner rear end 2 is fixed in engine on casing 5 (as Fig. 1), refill and allot motivation combustion box 8, use the above locating pins of 3 or 3 to stretch into burner inner liner simultaneously and carry out radial support (as Fig. 2), play the effect of auxiliary positioning, radial location simultaneously can be also other parts, as nozzle.At work, because burner inner liner can be heated, be out of shape, by the domes of arch installing ring 3, realize thermal compensation.These domes can be " V " types, can be also " W " " N " type.
In use, can not there is the inaccurate phenomenon in clamping stagnation, location of burner inner liner.
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 modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (10)
1. an aero-engine burner inner liner, comprises burner inner liner head (1) and burner inner liner rear end (2), it is characterized in that,
Described burner inner liner head (1) is arranged on engine chamber casing (8) position, and described burner inner liner rear end (2) is arranged on casing (5) position in engine,
The end of described burner inner liner rear end (2) is provided with arch installing ring (3),
The afterbody of described arch installing ring (3) is fixed on the interior casing (5) of engine by connector (4).
2. aero-engine burner inner liner according to claim 1, is characterized in that, described connector (4) is connecting bolt.
3. aero-engine burner inner liner according to claim 1, is characterized in that, the cross sectional shape of described arch installing ring (3) is V-arrangement, N shape or W shape.
4. aero-engine burner inner liner according to claim 1, is characterized in that, described arch installing ring (3) is loop configuration.
5. according to the aero-engine burner inner liner described in any one in claim 1 to 4, it is characterized in that, on described burner inner liner head (1), be provided with the keeper (6) of controlling spacing between described engine chamber casing (8) and described burner inner liner.
6. aero-engine burner inner liner according to claim 5, is characterized in that, described keeper (6) is locating pin.
7. aero-engine burner inner liner according to claim 5, is characterized in that, described keeper (6) radially arranges along burner inner liner.
8. aero-engine burner inner liner according to claim 5, is characterized in that, a plurality of described keepers (6) circumferentially and/or are vertically arranged along ring.
9. aero-engine burner inner liner according to claim 8, is characterized in that, a plurality of described keepers (6) equidistantly or unequal-interval arrange.
10. according to the aero-engine burner inner liner described in any one in claim 1 to 4, it is characterized in that,
On described engine chamber casing (8) and described burner inner liner head (1), be also provided with fuel nozzle (7),
Described fuel nozzle (7) radially arranges along described burner inner liner,
Described fuel nozzle (7) is simultaneously through the wall body of described engine chamber casing (8) and the wall body of described burner inner liner head.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320436883.1U CN203431932U (en) | 2013-07-22 | 2013-07-22 | Flame tube used for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320436883.1U CN203431932U (en) | 2013-07-22 | 2013-07-22 | Flame tube used for aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203431932U true CN203431932U (en) | 2014-02-12 |
Family
ID=50060967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320436883.1U Expired - Lifetime CN203431932U (en) | 2013-07-22 | 2013-07-22 | Flame tube used for aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203431932U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106574778A (en) * | 2014-08-18 | 2017-04-19 | 川崎重工业株式会社 | Fuel injection device |
| CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
-
2013
- 2013-07-22 CN CN201320436883.1U patent/CN203431932U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106574778A (en) * | 2014-08-18 | 2017-04-19 | 川崎重工业株式会社 | Fuel injection device |
| CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140212 |