CN209892509U - Fan blade convex shoulder working surface meshing structure and aeroengine - Google Patents
Fan blade convex shoulder working surface meshing structure and aeroengine Download PDFInfo
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- CN209892509U CN209892509U CN201920685687.5U CN201920685687U CN209892509U CN 209892509 U CN209892509 U CN 209892509U CN 201920685687 U CN201920685687 U CN 201920685687U CN 209892509 U CN209892509 U CN 209892509U
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Abstract
The utility model relates to a fan blade convex shoulder working face meshing structure belongs to aeroengine blade design field, fan blade convex shoulder working face meshing structure includes: a first fan blade having a first shoulder extending circumferentially; a second fan blade having a second shoulder extending opposite the first shoulder, wherein a line of engagement of the first shoulder with the second shoulder has a predetermined angle θ in a cold state such that the first shoulder and the second shoulder are fully engaged in a hot state. The fan blade convex shoulder working face meshing structure and the aircraft engine can effectively reduce the maximum extrusion stress of the convex shoulder working faces of the fan blades, meanwhile, the convex shoulder working faces are more uniform in contact, the working load of the engine does not need to be reduced, design space and process limitation does not exist, and applicability is strong.
Description
Technical Field
The application belongs to the technical field of aero-engine blade design, and particularly relates to a fan blade convex shoulder working surface meshing structure and an aero-engine.
Background
In the structure of the fan blade of the aircraft engine, the fan blade is provided with a convex shoulder structure, and the convex shoulder structure is generally applied to a primary rotor blade of the engine, so that on one hand, the rigidity of the blade can be improved, and on the other hand, the vibration is reduced through the dry friction between contact surfaces of the convex shoulders.
As shown in the fan blade with the shoulder structure in FIG. 1, the first fan blade 11 and the second fan blade 12 have a first shoulder 13 and a second shoulder 14 which are oppositely arranged, the working surfaces of the first shoulder 13 and the second shoulder 14 are in a complete meshing structure, when an engine runs, the shoulder contact and abutment can cause certain extrusion stress on the working surfaces, but due to the action of initial tightness and working load, the contact is not uniform, local extrusion stress concentration and excessive stress cause cracks or even blocks on the working surfaces of the shoulders, and the safety of the engine is affected.
Disclosure of Invention
It is an object of the present application to provide a fan blade shoulder working surface engagement structure to address or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: a fan blade shoulder working surface engagement structure, comprising:
a first fan blade having a first shoulder extending circumferentially;
a second fan blade having a second shoulder extending opposite the first shoulder, wherein a line of engagement of the first shoulder with the second shoulder has a predetermined angle θ in a cold state such that the first shoulder and the second shoulder are fully engaged in a hot state.
In one embodiment of the present application, the engagement line of the first shoulder and the second shoulder bisects each other and is centered on the engagement line.
In an embodiment of the present application, the predetermined angle is between-3 degrees and +3 degrees.
In an embodiment of the present application, an engagement area of the first shoulder and the second shoulder in a cold state is not less than 3/4 of an engagement area of the first shoulder and the second shoulder in a hot state.
The present application further provides an aircraft engine comprising a fan blade shoulder working surface engagement structure as described in any above.
The fan blade convex shoulder working face meshing structure and the aircraft engine can effectively reduce the maximum extrusion stress of the convex shoulder working faces of the fan blades, meanwhile, the convex shoulder working faces are more uniform in contact, the working load of the engine does not need to be reduced, design space and process limitation does not exist, and applicability is strong.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic representation of a prior art fan blade shoulder configuration.
FIG. 2 is a schematic illustration of a fan blade shoulder configuration of the present application.
Fig. 3 is a schematic diagram of a preset angle θ according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to solve prior art, convex shoulder working face extrusion stress can make convex shoulder working face produce the crackle partially, and the further extension of crackle can lead to the blade to take place destructive vibration, for effectively reducing convex shoulder working face extrusion stress, this application provides a convex shoulder working face meshing form for adjacent blade convex shoulder still rationally matches under long-term operating condition or maximum condition, improves convex shoulder contact condition.
The engagement structure of the working faces of the shoulders of the fan blades ensures that the working faces of the adjacent shoulders are not in a complete engagement state but have certain angle and position difference when in an assembly state (namely a cold state), so that the fan blades can be changed from incomplete engagement to complete engagement when in work (a hot state). As shown in fig. 2, the fan blade shoulder working surface engagement structure of the present application includes a first fan blade 21 and a second fan blade 22, the first fan blade 21 having a first shoulder 23 extending in the circumferential direction, the second fan blade 22 having a second shoulder 24 extending opposite to the first shoulder 23, wherein the engagement line of the first shoulder 23 and the second shoulder 24 has a predetermined angle in the cold state, so that the first shoulder 23 and the second shoulder 24 are completely engaged in the hot state.
After the aircraft engine runs, the convex shoulder can produce the deformation under the effect of working load, because the influence of rigidity and frictional state, the deformation of convex shoulder working face is inconsistent, and the meshing working face structure just can make adjacent convex shoulder working face complete meshing in this application to make the contact relatively even, reach the purpose that reduces the biggest extrusion stress of convex shoulder working face.
As shown in FIG. 3, since the conventional bowl-side and back-side shoulder (the bowl-side in the front and back in the direction of flow Q in FIG. 2) faces are perfectly flush and equal, the adjustment of the back-side shoulder face is described herein as an example to keep the bowl-side shoulder face constant:
1) when the cold-state shoulder working surfaces are completely meshed, the motion deformation of the two adjacent working surfaces can be decomposed into an X axis and a Y axis, and a certain extrusion stress can exist on the meshed working surfaces due to the initial tightness, so that the two shoulder working surfaces cannot be staggered in the working process, namely, the working surfaces are inevitably provided with contact parts, and the central points O and the Y axes of the central lines of the two adjacent shoulder working surfaces are always kept unchanged;
2) the method is characterized in that a preset included angle theta between two long shafts of working faces of adjacent convex shoulders is the core of the method, and the optimal solution of the preset angle theta is continuously sought by establishing a parameterized model and finite element simulation, so that the adjacent blade convex shoulders can be completely meshed in a long-term working state or a maximum state, and a reasonable cold working face meshing structure is obtained; through continuous exploration, the range of the preset angle theta obtained by the method is set to be the most reasonable range from-3 degrees to 3 degrees, and the angle is determined to be adjusted towards the positive direction or the negative direction according to the displacement of the working face obtained through calculation.
3) During the exploration of the predetermined angle θ, the shoulder land engagement area should be no less than 3/4 of the full engagement area to prevent the shoulder from failing to reach the intended engagement position during operation.
Finally, the present application provides an aircraft engine comprising a fan blade shoulder working surface engagement structure as described in any of the above.
The fan blade convex shoulder working face meshing structure and the aircraft engine can effectively reduce the maximum extrusion stress of the convex shoulder working faces of the fan blades, meanwhile, the convex shoulder working faces are more uniform in contact, the working load of the engine does not need to be reduced, design space and process limitation does not exist, and applicability is strong.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A fan blade convex shoulder working surface meshing structure is characterized by comprising
A first fan blade (21), the first fan blade (21) having a first shoulder (23) extending in a circumferential direction;
a second fan blade (22), wherein the second fan blade (22) has a second shoulder (24) extending opposite to the first shoulder (23), and wherein the line of engagement of the first shoulder (23) with the second shoulder (24) has a predetermined angle in the cold state, such that the first shoulder (23) and the second shoulder (24) are completely engaged in the hot state.
2. The fan blade shoulder land engagement structure of claim 1, wherein the first shoulder (23) and the second shoulder (24) have a line of engagement that is mutually flat and centered with respect to the line of engagement.
3. The fan blade shoulder engaging structure of claim 2, wherein the predetermined angle is between-3 degrees and +3 degrees.
4. A fan blade shoulder engagement structure according to any one of claims 1-3, wherein the area of engagement of the first shoulder (23) with the second shoulder (24) in the cold state is no less than 3/4 of the area of engagement of the first shoulder (23) with the second shoulder (24) in the hot state.
5. An aircraft engine, comprising a fan blade shoulder land engaging structure according to any one of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920685687.5U CN209892509U (en) | 2019-05-14 | 2019-05-14 | Fan blade convex shoulder working surface meshing structure and aeroengine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920685687.5U CN209892509U (en) | 2019-05-14 | 2019-05-14 | Fan blade convex shoulder working surface meshing structure and aeroengine |
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| CN209892509U true CN209892509U (en) | 2020-01-03 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115270567A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Method for analyzing vibration characteristics of fan rotor blade with shoulder |
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2019
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115270567A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Method for analyzing vibration characteristics of fan rotor blade with shoulder |
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