CN208635145U - A kind of aeroengine combustor liner cover structure - Google Patents
A kind of aeroengine combustor liner cover structure Download PDFInfo
- Publication number
- CN208635145U CN208635145U CN201820875464.0U CN201820875464U CN208635145U CN 208635145 U CN208635145 U CN 208635145U CN 201820875464 U CN201820875464 U CN 201820875464U CN 208635145 U CN208635145 U CN 208635145U
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- China
- Prior art keywords
- outer cover
- cover structure
- combustor liner
- metal ring
- utility
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- 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.)
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Abstract
The utility model relates to aero-engine main chamber structure, in particular to a kind of aeroengine combustor liner cover structure.It is characterized in that, aeroengine combustor liner outer cover front end inward curl forms circular cavity, outer cover front end leading edge and outer cover inner surface are welded to connect, and circular cavity is internally provided with metal ring compatible with circular cavity, and metal ring is there are opening and surface is printed on reticulate pattern.The utility model improves existing cover structure, and cover structure is integrally in integral structure, reduces residual stress, improves reliability and vibration resistance.
Description
Technical field
The utility model relates to aero-engine main chamber structure, in particular to a kind of aeroengine combustor liner outer cover
Structure.
Background technique
Aeroengine combustor liner outer cover is the important component of engine main chamber component, aviation as shown in Figure 1
The tip 2 of engine flame tube outer cover and airflow design is integrally welded, plays guide function to air-flow, can be with lower pressure
The distribution to burner inner liner and inner and outer rings cavity space throughput is realized in power loss, forms toroidal cavity inside burner inner liner outer cover, for fire
Flame cylinder head cyclone 4 and 3 air inlet of cooling hole provide stable hydrostatic pressure condition, improve flame tube head pressure difference, to guarantee not
With the stabilization of state lower combustion chamber air mass flow distribution.
Currently, since outer cover 1 and tip 2 are using being welded to connect, it is easy to produce unbalanced stress, there are residual stress, antivibratioves
Performance is poor, is easy crackle even chip off-falling.
Summary of the invention
The purpose of the utility model is to provide a kind of aeroengine combustor liner cover structures, at least to solve above-mentioned one
A problem.
The technical solution of the utility model is: a kind of aeroengine combustor liner cover structure, outer cover front end inward curl
Circular cavity is formed, circular cavity is internally provided with metal ring compatible with circular cavity.
Preferably, outer cover front end leading edge and outer cover inner surface are welded to connect.
Preferably, metal ring is there are opening and surface is printed on reticulate pattern.
Utility model has the advantages that improved cover structure is integrally in integral structure, residual stress is reduced, is improved
Reliability and vibration resistance.
Detailed description of the invention
Fig. 1 is the operation schematic diagram of existing aeroengine combustor liner cover structure.
Fig. 2 is the structural schematic diagram of this practical aeroengine combustor liner cover structure.
Fig. 3 is that Fig. 2 Flame cylinder outer cover front end leading edge and outer cover are welded to connect by surface and install the structure of metal ring
Schematic diagram.
Fig. 4 is the structural schematic diagram of the metal ring in Fig. 3.
Specific embodiment
To keep the purposes, technical schemes and advantages of the utility model implementation clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Described reality
Applying example is the utility model a part of the embodiment, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and should not be understood as limiting the present invention.It is practical new based on this
Embodiment in type, every other implementation obtained by those of ordinary skill in the art without making creative efforts
Example, fall within the protection scope of the utility model.The embodiments of the present invention are described in detail with reference to the accompanying drawing.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of describing the present invention and simplifying the description, rather than indication or suggestion is signified
Device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to this is practical
The limitation of novel protected range.
2- Fig. 4 is described in further details the utility model with reference to the accompanying drawing.
The utility model provides a kind of aeroengine combustor liner cover structure, and 1 front end inward curl of outer cover forms circle
Shape cavity, type face are not only guaranteed to shunt but also the pressure loss are reduced to minimum according to Pneumatic Calculation.1 front end leading edge of outer cover with
1 inner surface of outer cover is welded to connect, and is prevented 1 front end leading edge of outer cover rebound in use process or is loosened.Circular cavity is internally provided with
Metal ring 5 compatible with circular cavity, there are openings in the case where retaining certain rigidity for metal ring 5, increases amount of deflection,
It is assembled in circular cavity, improves whole vibration resistance, between 5 surface printed network line of metal ring increase frictional force, reduction structure
Opposite sliding, reduce abrasion.
Above description is only a specific implementation of the present invention, but the protection scope of the utility model is not limited to
In this, anyone skilled in the art within the technical scope disclosed by the utility model, the change that can be readily occurred in
Change or replace, should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with described
Subject to scope of protection of the claims.
Claims (4)
1. a kind of aeroengine combustor liner cover structure, which is characterized in that outer cover (1) front end inward curl forms round sky
Chamber, the circular cavity are internally provided with metal ring (5) compatible with the circular cavity.
2. burner inner liner cover structure according to claim 1, which is characterized in that outer cover (1) the front end leading edge with it is described
Outer cover (1) inner surface is welded to connect.
3. burner inner liner cover structure according to claim 2, which is characterized in that there are openings for the metal ring (5).
4. burner inner liner cover structure according to claim 3, which is characterized in that metal ring (5) surface is printed on net
Line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820875464.0U CN208635145U (en) | 2018-06-05 | 2018-06-05 | A kind of aeroengine combustor liner cover structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820875464.0U CN208635145U (en) | 2018-06-05 | 2018-06-05 | A kind of aeroengine combustor liner cover structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208635145U true CN208635145U (en) | 2019-03-22 |
Family
ID=65735113
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820875464.0U Active CN208635145U (en) | 2018-06-05 | 2018-06-05 | A kind of aeroengine combustor liner cover structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208635145U (en) |
-
2018
- 2018-06-05 CN CN201820875464.0U patent/CN208635145U/en active Active
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