CN209445404U - A kind of aeroengine combustor liner - Google Patents
A kind of aeroengine combustor liner Download PDFInfo
- Publication number
- CN209445404U CN209445404U CN201920155253.4U CN201920155253U CN209445404U CN 209445404 U CN209445404 U CN 209445404U CN 201920155253 U CN201920155253 U CN 201920155253U CN 209445404 U CN209445404 U CN 209445404U
- Authority
- CN
- China
- Prior art keywords
- positioning
- bolt
- nut
- inner liner
- burner inner
- 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 - Fee Related
Links
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 26
- 239000000446 fuel Substances 0.000 claims abstract description 8
- 125000004122 cyclic group Chemical group 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims description 9
- 238000002485 combustion reaction Methods 0.000 claims description 2
- 230000008450 motivation Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 description 4
- 230000036316 preload Effects 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Landscapes
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The utility model discloses a kind of aeroengine combustor liners, belong to aero-engine technology field, including burner inner liner front end and engine chamber casing, the burner inner liner front end is set in engine chamber casing, fuel nozzle is installed on the burner inner liner front end, the fuel nozzle passes through the side wall setting of burner inner liner front end and engine chamber casing, multiple positioning bolts are circumferentially installed on the engine chamber casing, reinforcing positioning ring is fixedly installed on the engine chamber casing, the reinforcing positioning ring is cyclic structure, the side for reinforcing positioning ring and multiple positioning bolts being set, the first nut is fixedly installed on each positioning bolt, the reinforcing positioning ring is recessed fluted close to the side of positioning bolt.The utility model solves the problems, such as that the positioning of existing burner inner liner head end is unstable, has the characteristics that structure is simply and easy for installation.
Description
Technical field
The utility model relates to aero-engine technology field more particularly to a kind of aeroengine combustor liners.
Background technique
In aero-engine field, it is desirable that burner inner liner works on certain spatial position in the combustion chamber, in order to ensure this
One requires, and need to use a kind of positioning method, and positioning method will can ensure that burner inner liner good can assemble in the cold state, hot lower nothing
Interference.
The positioning method of the head end of existing burner inner liner is fixed by the locating pin being circumferentially arranged, however more
The isolated setting of a locating pin, is easy to appear the problem of individual locating pins loosen, causes locating effect bad, therefore need to design
A kind of aeroengine combustor liner.
Utility model content
Purpose of the utility model is to solve disadvantages existing in the prior art, such as: the head end of existing burner inner liner
Positioning method be mostly to be fixed by the locating pin being circumferentially arranged, however the isolated setting of multiple locating pins is easy
The problem of now individual locating pins loosen causes locating effect bad, and a kind of aeroengine combustor liner proposed.
To achieve the goals above, the utility model adopts the technical scheme that
A kind of aeroengine combustor liner, including burner inner liner front end and engine chamber casing, before the burner inner liner
End is set in engine chamber casing, and fuel nozzle is equipped on the burner inner liner front end, and the fuel nozzle is worn
The side wall setting of burner inner liner front end and engine chamber casing is crossed, is circumferentially equipped on the engine chamber casing more
A positioning bolt, reinforcing positioning ring is fixedly installed on the engine chamber casing, and the reinforcing positioning ring is cyclic annular knot
Structure, the reinforcing positioning ring are arranged in the side of multiple positioning bolts, are fixedly installed first on each positioning bolt
Nut, the reinforcing positioning ring is recessed fluted close to the side of positioning bolt, the groove annular be fixed with it is multiple with it is more
A first nut matched second nut one by one, by reinforcing bolt between each first nut and second nut
It is fastenedly connected.
Preferably, multiple fixing seats are circumferentially fixed on the engine chamber casing, multiple fixing seats and more
A positioning bolt corresponds, vertical in each fixing seat to run through first offered for connecting positioning bolt
Tapped through hole is fixedly installed connection ring on the burner inner liner front end, and the connection ring is cyclic structure, and the connection ring is remote
Side from burner inner liner front end is circumferentially recessed with the tapped blind hole of multiple matching positioning bolts.
Preferably, it is mounted on positioning pin in each fixing seat, offers and is used on each positioning bolt
Match the pin hole of positioning pin.
Preferably, the positioning bolt and reinforcing bolt pass through Hydraulic Pretension Method processing.
Preferably, run through on the reinforcing positioning ring and offer multiple the second tapped through holes being connected to groove, Mei Gesuo
It states reinforcing bolt to be threaded in corresponding second tapped through hole, each first nut and each second nut
On be provided with matching reinforce bolt third tapped through hole.
Preferably, the connection ring is fixed on burner inner liner front end by multiple positioning screws.
Compared with prior art, the utility model has the beneficial effects that
1, the utility model matching by positioning bolt, reinforcing positioning ring, reinforcing bolt, the first nut and the second nut
It closes, while realizing to the positioning of burner inner liner front end, also achieves the connection to multiple positioning bolts, to be set isolated
The multiple positioning bolts set connect, and are conducive to avoid the problem that individual positioning bolts loosen, can promote connection
Firm effect；
2, the utility model positions positioning bolt by positioning pin, can circumferentially rotating to avoid positioning bolt,
To promote the stability of positioning bolt installation, the installation of the first nut not only can satisfy by the way that fixing seat is arranged, but also can be real
Existing positioning bolt is fastenedly connected with burner inner liner front end.
Detailed description of the invention
Fig. 1 be the utility model proposes a kind of aeroengine combustor liner front end structural schematic diagram；
Fig. 2 is schematic enlarged-scale view at the A of Fig. 1.
In figure: 1 burner inner liner front end, 2 engine chamber casings, 3 fuel nozzles, 4 reinforce positioning rings, 5 reinforce bolts,
6 positioning bolts, 7 first nuts, 8 second nuts, 9 fixing seats, 10 positioning pins, 11 connection rings.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.
Referring to Fig.1-2, a kind of aeroengine combustor liner, including burner inner liner front end 1 and engine chamber casing 2,
Burner inner liner front end 1 is set in engine chamber casing 2, and fuel nozzle 3, fuel oil spray are equipped on burner inner liner front end 1
Mouth 3 passes through the side wall setting of burner inner liner front end 1 and engine chamber casing 2, circumferentially installs on engine chamber casing 2
There are multiple positioning bolts 6, be fixedly installed on engine chamber casing 2 and reinforce positioning ring 4, reinforcing positioning ring 4 is cyclic annular knot
Structure reinforces the side that multiple positioning bolts 6 are arranged in positioning ring 4, is fixedly installed the first nut 7 on each positioning bolt 6,
It is recessed fluted close to the side of positioning bolt 6 to reinforce positioning ring 4, groove annular is fixed with multiple and multiple first nuts 7
Matched second nut 8 one by one is fastenedly connected by reinforcing bolt 5 between each first nut 7 and the second nut 8.
It should be noted that by positioning bolt 6, reinforcing positioning ring 4, reinforcing bolt 5, the first nut 7 and the second nut 8
Cooperation, realize to burner inner liner front end 1 position while, also achieve the connection to multiple positioning bolts 6, thus will
Multiple positioning bolts 6 of isolated setting connect, and are conducive to avoid the problem that individual positioning bolts 6 loosen, Ke Yiti
Rise whole firm effect；
Wherein, multiple fixing seats 9, multiple fixing seats 9 and multiple positioning spiral shells are circumferentially fixed on engine chamber casing 2
Bolt 6 corresponds, vertical through the first tapped through hole offered for connecting positioning bolt 6, flame in each fixing seat 9
Connection ring 11 is fixedly installed on cylinder front end 1, connection ring 11 is cyclic structure, and connection ring 11 is far from burner inner liner front end 1
Side is circumferentially recessed with the tapped blind hole of multiple matching positioning bolts 6；
It should be noted that not only having met the installation of the first nut 7 by the way that fixing seat 9 is arranged, but also it is able to achieve positioning bolt 6
It is recessed with circular track with the upside of being fastenedly connected for burner inner liner front end 1, fixing seat 9, in the process for screwing positioning bolt 6
In, 7 one side of the first nut is rotated along circular track with the turn of positioning bolt 6, on one side screwing with positioning bolt 6
And glide, when positioning bolt 6 screws, the first nut 7 is just skidded off out of circular track at this time, and the position with the second nut 8
It sets and matches；
Wherein, positioning pin 10 is mounted in each fixing seat 9, it is fixed for matching to offer on each positioning bolt 6
The pin hole of position pin 10；
It should be noted that positioning bolt 6 is positioned by positioning pin 10, it can be to avoid the circumferential direction of positioning bolt 6
Rotation, to promote the stability of the installation of positioning bolt 6；
Wherein, positioning bolt 6 and reinforcing bolt 5 are handled by Hydraulic Pretension Method；
It should be noted that carrying out preload processing, Ke Yizeng to positioning bolt 6 and reinforcing bolt 5 by hydraulic elongator
The rigidity of strong ties, compactness, anti-loose ability and bolted sliding by transverse load is prevented, to alleviate temperature change
Influence to positioning bolt 6；
Wherein, it reinforces to run through on positioning ring 4 and offers multiple the second tapped through holes being connected to groove, each reinforcing bolt
5 are threaded in corresponding second tapped through hole, are provided with matching on each first nut 7 and each second nut 8
Reinforce the third tapped through hole of bolt 5；
It should be noted that when multiple positioning bolts 6 are tightened in fixing seat 9, at this time just multiple first nuts 7 with
Multiple second nuts 8 correspond, and realize multiple positioning bolts 6 by reinforcing bolt 5, the first nut 7 and the second nut 8
Connection, to advantageously ensure that the stabilization that positioning bolt 6 is installed；
Wherein, connection ring 11 is fixed on burner inner liner front end 1 by multiple positioning screws；
It should be noted that connection ring 11 is fixed on burner inner liner front end 1 by the multiple positioning screws being circumferentially arranged
On, and positioning screw is handled by preload, and influence of the temperature change to positioning screw can be effectively relieved.
The preferable specific embodiment of the above, only the utility model, but the protection scope of the utility model is not
It is confined to this, anyone skilled in the art is within the technical scope disclosed by the utility model, practical according to this
Novel technical solution and its utility model design are subject to equivalent substitution or change, should all cover the protection model in the utility model
Within enclosing.
Claims (6)
1. a kind of aeroengine combustor liner, including burner inner liner front end (1) and engine chamber casing (2), the flame
Cylinder front end (1) is set in engine chamber casing (2), is equipped with fuel nozzle on the burner inner liner front end (1)
(3), the fuel nozzle (3) passes through the side wall setting of burner inner liner front end (1) and engine chamber casing (2), the hair
Multiple positioning bolts (6) are circumferentially installed, which is characterized in that the engine chamber casing on motivation combustion box (2)
(2) it is fixedly installed on and reinforces positioning ring (4), the reinforcing positioning ring (4) is cyclic structure, and the reinforcing positioning ring (4) sets
The side in multiple positioning bolts (6) is set, is fixedly installed the first nut (7) on each positioning bolt (6), it is described to add
Fixed bit ring (4) is recessed fluted close to the side of positioning bolt (6), and the groove annular is fixed with multiple with multiple first
Nut (7) matched second nut (8) one by one, between each first nut (7) and second nut (8) by plus
Fixing bolt (5) is fastenedly connected.
2. a kind of aeroengine combustor liner according to claim 1, which is characterized in that the engine chamber casing
(2) it being circumferentially fixed on multiple fixing seats (9), multiple fixing seats (9) and multiple positioning bolts (6) correspond,
It is vertical through the first tapped through hole offered for connecting positioning bolt (6), the flame on each fixing seat (9)
It is fixedly installed connection ring (11) on cylinder front end (1), the connection ring (11) is cyclic structure, and the connection ring (11) is separate
The side of burner inner liner front end (1) is circumferentially recessed with the tapped blind hole of multiple matchings positioning bolt (6).
3. a kind of aeroengine combustor liner according to claim 2, which is characterized in that on each fixing seat (9)
It is mounted on positioning pin (10), the pin hole for matching positioning pin (10) is offered on each positioning bolt (6).
4. a kind of aeroengine combustor liner according to claim 1, which is characterized in that the positioning bolt (6) and add
Fixing bolt (5) is handled by Hydraulic Pretension Method.
5. a kind of aeroengine combustor liner according to claim 1, which is characterized in that on the reinforcing positioning ring (4)
Through multiple the second tapped through holes being connected to groove are offered, each reinforcing bolt (5) is threaded in corresponding
In second tapped through hole, it is provided with matching on each first nut (7) and each second nut (8) and reinforces bolt
(5) third tapped through hole.
6. a kind of aeroengine combustor liner according to claim 2, which is characterized in that the connection ring (11) passes through more
A positioning screw is fixed on burner inner liner front end (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920155253.4U CN209445404U (en) | 2019-01-29 | 2019-01-29 | A kind of aeroengine combustor liner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920155253.4U CN209445404U (en) | 2019-01-29 | 2019-01-29 | A kind of aeroengine combustor liner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209445404U true CN209445404U (en) | 2019-09-27 |
Family
ID=68018282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920155253.4U Expired - Fee Related CN209445404U (en) | 2019-01-29 | 2019-01-29 | A kind of aeroengine combustor liner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209445404U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520754A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Novel miniature aeroengine combustion chamber |
| CN117366628A (en) * | 2023-10-10 | 2024-01-09 | 中国航发燃气轮机有限公司 | Tube-separating type combustion chamber |
-
2019
- 2019-01-29 CN CN201920155253.4U patent/CN209445404U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520754A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Novel miniature aeroengine combustion chamber |
| CN117366628A (en) * | 2023-10-10 | 2024-01-09 | 中国航发燃气轮机有限公司 | Tube-separating type combustion chamber |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190927 |