CN117287420A - Stationary blade adjusting mechanism and aeroengine - Google Patents
Stationary blade adjusting mechanism and aeroengine Download PDFInfo
- Publication number
- CN117287420A CN117287420A CN202210688795.4A CN202210688795A CN117287420A CN 117287420 A CN117287420 A CN 117287420A CN 202210688795 A CN202210688795 A CN 202210688795A CN 117287420 A CN117287420 A CN 117287420A
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- Prior art keywords
- rocker arm
- adjustment mechanism
- hole
- side wall
- gap
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- 230000007246 mechanism Effects 0.000 title claims abstract description 46
- 239000003351 stiffener Substances 0.000 claims 1
- 238000006073 displacement reaction Methods 0.000 abstract description 9
- 238000005516 engineering process Methods 0.000 abstract description 6
- 238000005452 bending Methods 0.000 abstract description 5
- 230000008859 change Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 11
- 230000008569 process Effects 0.000 description 11
- 230000000694 effects Effects 0.000 description 6
- 230000003014 reinforcing effect Effects 0.000 description 6
- 230000003068 static effect Effects 0.000 description 4
- 208000006673 asthma Diseases 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a stationary blade adjusting mechanism and an aeroengine. The stationary blade adjusting mechanism includes: the device comprises a case, a stator blade, a rocker arm and a linkage ring, wherein the linkage ring is provided with a containing cavity with an opening facing the stator blade, and a first through hole and a second through hole are respectively formed in a first side wall and a second side wall of the containing cavity; the rocker arm is a flexible rocker arm, and the first end of the rocker arm is inserted into the accommodating cavity through the opening; the stationary blade adjusting mechanism further comprises a fixing piece, wherein the fixing piece sequentially penetrates through the first through hole, a rocker arm hole positioned at the first end of the rocker arm in the accommodating cavity and the second through hole, so that the linkage ring and the rocker arm are fixed together. According to the invention, the concrete structure of the stationary blade adjusting mechanism is arranged, so that deformation of the rocker arm caused by a riveting processing technology is avoided; meanwhile, the rocker arm is flexible, so that the change of angular displacement can be compensated through the bending deformation of the rocker arm, and the rocker arm is prevented from being clamped in rotation.
Description
Technical Field
The invention relates to a stationary blade adjusting mechanism and an aeroengine.
Background
The adjustable stationary blade (Variable Stator Vane, VSV, adjustable stator blade) adjusting mechanism is mainly used for improving the working characteristics of the compressor, expanding the stable working range of the compressor and preventing surging. The VSV adjusting mechanism is mainly used for adjusting the mounting angle of the VSV according to the working states of the engine at different moments, is in a design state that the air flow right angle of the inlet of the rotor blade is close to the design state, eliminates the air flow separation of the blade back, and ensures that the stable working range of the air compressor is wider.
The stator blade adjusting mechanism can also be called a stator blade adjusting mechanism, the partial schematic diagram of the stator blade adjusting mechanism is shown in fig. 1, in the moving process, the actuating cylinder transmits torque through the connecting rod to drive the linkage ring 3 positioned on the outer side of the casing 1 to circumferentially rotate around the axis of the engine, and meanwhile, the rocker arm 2 moves around the rotation axis of the adjustable stator blade (the stator blade 4) to drive the stator blade 4 to adjust the installation angle. The linkage ring 3 is connected with the stator blades 4 through a rocker arm 2 of a circle.
The accuracy of the angle adjustment of the stationary blade adjusting mechanism is the key for ensuring the normal and safe operation of the aircraft because of the stable operation of the engine. If the adjustment precision does not meet the design requirement, the condition that the angle of the air compressor is off or off in the actual operation process is caused, the air flow is unstable, and the phenomena of front asthma, rear blockage or front blockage and rear asthma are caused.
At present, the rocker arm and the linkage ring are connected in a riveting mode, the riveting process needs to be tested and groped, and acting force needs to be applied in the riveting process, so that the position accuracy of the rivet after riveting is low, and the rocker arm can deform due to riveting.
Disclosure of Invention
The invention aims to overcome the defects that in the prior art, rivets are low in position precision and rocker arms deform due to riveting, and provides a stationary blade adjusting mechanism and an aeroengine.
The invention solves the technical problems by the following technical scheme:
a vane adjustment mechanism, the vane adjustment mechanism comprising: the machine case is characterized in that the machine case comprises a machine case body, stator blades, a rocker arm and a linkage ring, wherein the stator blades penetrate through the machine case body, the linkage ring is connected with the stator blades through the rocker arm and is arranged on the outer side of the machine case body,
the linkage ring is provided with a containing cavity, the containing cavity is provided with an opening facing the stator blade, the containing cavity comprises a first side wall and a second side wall which are oppositely arranged along the radial direction of the casing, the second side wall is positioned between the first side wall and the casing, and a first through hole and a second through hole are respectively formed in the first side wall and the second side wall;
the rocker arm is a flexible rocker arm, the first end of the rocker arm is inserted into the accommodating cavity through the opening, and the second end of the rocker arm is connected with the stator blade;
the stationary blade adjusting mechanism further comprises a fixing piece, wherein the fixing piece sequentially penetrates through the first through hole, a rocker arm hole located in the accommodating cavity and arranged at the first end of the rocker arm, and the second through hole, so that the linkage ring and the rocker arm are fixed together.
In this technical scheme, wear to locate in the rocking arm hole on the first end of rocking arm in holding chamber and the second through-hole through setting up the mounting in proper order to fix the linkage ring with the rocking arm together, thereby avoid using riveted processing technology to connect linkage ring and rocking arm, and can not produce the deformation to the rocking arm, and, compare in riveted processing technology, the processing technology of trompil on the rocking arm is simpler. Meanwhile, the rocker arm is set to be a flexible rocker arm, the flexible rocker arm can deform, and the change of the angular displacement is compensated through bending deformation of the flexible rocker arm, so that the rocker arm is prevented from being clamped in rotation. Compared with a rigid rocker arm (namely a rocker arm which cannot deform, the flexible rocker arm is required to compensate the angular displacement variation through components such as a spherical pair, the flexible rocker arm can realize the compensation of the angular displacement variation through deformation of the flexible rocker arm, so that the structure of the static blade adjusting mechanism is simpler, and the mass of the flexible rocker arm is lighter than that of the rigid rocker arm, so that the overall weight of the static blade adjusting mechanism is lighter and the cost is lower.
Preferably, the stationary blade adjusting mechanism further comprises a bushing, and the bushing is sleeved outside the fixing piece and located in the rocker arm hole.
In this technical scheme, through setting up the bush in order to avoid the contact friction between rocking arm and the mounting to increase life.
Preferably, a first gap is formed between the bushing and the linkage ring along the radial direction of the casing, and the first gap is greater than 0 and less than or equal to 0.1mm.
In the technical scheme, the first gap is formed between the bushing and the linkage ring, and is larger than 0 and smaller than or equal to 0.1mm, namely, the first gap is a smaller gap, so that the activity of the bushing in the radial direction of the casing is reduced as much as possible, and the error caused by the gap in the movement process is reduced.
Preferably, a second gap is formed between the bushing and the inner wall surface of the rocker arm hole, and the second gap is more than 0 and less than or equal to 0.1mm; and/or the number of the groups of groups,
a third gap is formed between the bushing and the outer wall surface of the fixing piece, and the third gap is larger than 0 and smaller than or equal to 0.03mm.
In the technical scheme, the second gap is formed between the bushing and the inner wall surface of the rocker arm hole, and is larger than 0 and smaller than or equal to 0.1mm, namely, the second gap is a smaller gap, so that the activity between the bushing and the rocker arm is reduced as much as possible, and the error caused by the gap in the movement process is reduced. The third gap is arranged between the bushing and the outer wall surface of the fixing piece and is larger than 0 and smaller than or equal to 0.03mm, namely, the third gap is a smaller gap, so that the activity between the bushing and the fixing piece is reduced as much as possible, and the error caused by the gap in the movement process is reduced.
Preferably, the height of the bushing is equal to or greater than the sum of the height of the rocker arm and the distance between the rocker arm and the second side wall.
In this technical scheme, through setting up the high more than or equal to of bush the height of rocking arm with the distance sum between the rocking arm and the second lateral wall to realize that the bush can cover the height of whole rocking arm, with the connection between assurance rocking arm and the mounting more stable.
Preferably, a reinforcing rib is arranged on one surface of the first side wall, which is far away from the casing.
In this technical scheme, keep away from through in the first lateral wall set up the strengthening rib on the one side of receiver, can strengthen the intensity of link ring self.
Preferably, the fixing piece is a pin;
the fixing piece comprises a head and a rod, the outer diameter of the head is larger than that of the rod, and the head is clamped on the outer side of the first side wall.
In this technical scheme, through setting up the mounting and be the pin, and can realize higher installation accuracy.
Preferably, a limiting piece is arranged on the outer side of the head of the fixing piece, the limiting piece is arranged along the axial direction of the casing, and the limiting piece is used for limiting the fixing piece to drop from the rocker arm.
In the technical scheme, the limiting piece is arranged on the outer side of the head of the fixing piece, so that the fixing piece is prevented from falling off the rocker arm.
Preferably, the rocker arm includes a connecting portion connected between the first end and the second end, and the height of the first end is greater than the height of the connecting portion.
In this technical scheme, through setting up the height that highly is greater than the connecting portion of first end to make the intensity of first end higher, can bear the torsion that brings because the rotation of linkage ring better.
An aeroengine characterised in that it comprises a vane adjustment mechanism as described above.
The invention has the positive progress effects that:
the invention avoids connecting the linkage ring and the rocker arm by using a riveted processing technology by arranging the specific structure of the stationary blade adjusting mechanism, does not deform the rocker arm, and has simpler processing technology. Meanwhile, the rocker arm is set to be a flexible rocker arm, the flexible rocker arm can deform, and the change of the angular displacement is compensated through bending deformation of the flexible rocker arm, so that the rocker arm is prevented from being clamped in rotation.
Drawings
Fig. 1 is a schematic perspective view of a part of a vane adjusting mechanism in the prior art.
FIG. 2 is a schematic view of a vane adjustment mechanism according to a preferred embodiment of the present invention.
Fig. 3 is a partial enlarged view of a portion a in fig. 2.
FIG. 4 is a schematic top view of a swing arm of a vane adjustment mechanism according to a preferred embodiment of the present invention.
Fig. 5 is a sectional view in the direction B-B of fig. 4.
Detailed Description
The invention is further illustrated by means of examples which follow, without thereby restricting the scope of the invention thereto.
As will be appreciated in conjunction with fig. 2 to 5, the present embodiment provides a vane adjusting mechanism 10, the vane adjusting mechanism 10 including: the device comprises a case 20, stator blades 30, a rocker arm 40 and a linkage ring 50, wherein the stator blades 30 are arranged on the case 20 in a penetrating mode, and the linkage ring 50 is connected with the stator blades 30 through the rocker arm 40 and is arranged on the outer side of the case 20.
The linkage ring 50 is provided with a containing cavity 51, the containing cavity 51 is provided with an opening 52 facing the stator blade 30, the containing cavity 51 comprises a first side wall 53 and a second side wall 54 which are oppositely arranged along the radial direction R of the casing 20, the second side wall 54 is positioned between the first side wall 53 and the casing 20, and a first through hole 55 and a second through hole 56 are respectively formed in the first side wall 53 and the second side wall 54. That is, the first sidewall 53 is provided with a first through hole 55, and the second sidewall 54 is provided with a second through hole 56.
The rocker arm 40 is a flexible rocker arm, and during the movement process, the rocker arm 40 is subjected to torsional deformation to drive the stator blade 30 to rotate. The first end 41 of the rocker arm 40 is inserted into the receiving cavity 51 through the opening 52, and the second end 42 of the rocker arm 40 is connected to the stator vane 30. The rocker arm 40 is made of metal. By providing the rocker arm 40 as a flexible rocker arm, the flexible rocker arm itself is deformable, and changes in angular displacement are compensated for by bending deformation of itself, thereby avoiding jamming of the rocker arm 40 during rotation. Compared with a rigid rocker arm (namely a rocker arm which cannot deform by itself) and the like, the angular displacement variation needs to be compensated by a component such as a spherical pair and the like, the flexible rocker arm can realize the compensation of the angular displacement variation by only deforming by itself without the assistance of the component, so that the static blade adjusting mechanism 10 has simpler structure, and the mass of the flexible rocker arm is lighter than that of the rigid rocker arm, so that the static blade adjusting mechanism 10 has lighter overall weight and lower cost.
The stationary blade adjusting mechanism 10 further includes a fixing member 60, where the fixing member 60 sequentially penetrates through the first through hole 55 on the first side wall 53, the rocker arm hole 43 on the first end 41 of the rocker arm 40 in the accommodating cavity 51, and the second through hole 56 on the second side wall 54, so as to fix the linkage ring 50 and the rocker arm 40 together, thereby avoiding the use of a riveting process to connect the linkage ring 50 and the rocker arm 40 without deforming the rocker arm 40, and making a hole in the rocker arm 40 simpler than the riveting process.
In the present embodiment, the fixing member 60 is perforated to fix the rocker arm 40 and the link ring 50 by punching the rocker arm 40, and the rocker arm 40 is a flexible rocker arm, so that the overall vane adjusting mechanism 10 can be more compact and lighter.
In the present embodiment, the vane adjusting mechanism 10 further includes a bushing 70, and the bushing 70 is sleeved outside the fixing member 60 and is located in the rocker arm hole 43. The bushing 70 is provided to avoid contact friction between the rocker arm 40 and the mount 60, thereby increasing the service life.
In the radial direction R of the casing 20, a first gap 81 is formed between the bushing 70 and the link ring 50, and the first gap 81 is greater than 0 and less than or equal to 0.1mm. The first gap 81 is arranged between the bushing 70 and the linkage ring 50, and the first gap 81 is larger than 0 and smaller than or equal to 0.1mm, namely the first gap 81 is a smaller gap, so that the activity of the bushing 70 in the radial direction R of the casing 20 is reduced as much as possible, and the error caused by the gap in the movement process is reduced.
The second gap 82 is formed between the bushing 70 and the inner wall surface of the rocker arm hole 43, and the second gap 82 is greater than 0 and less than or equal to 0.1mm, i.e., the second gap 82 is a smaller gap, so that the activity between the bushing 70 and the rocker arm 40 is reduced as much as possible, and errors caused by the gap during movement are reduced.
The third gap 83 is formed between the bushing 70 and the outer wall surface of the fixing member 60, and the third gap 83 is greater than 0 and less than or equal to 0.03mm, i.e. the third gap 83 is a smaller gap, so that the movement amount between the bushing 70 and the fixing member 60 is reduced as much as possible, and errors caused by the gaps during movement are reduced.
Preferably, the height h1 of the bushing 70 is greater than or equal to the sum of the height h2 of the rocker arm and the distance D between the rocker arm 40 and the second side wall 54, so as to achieve that the bushing 70 can cover the entire height h2 of the rocker arm, so as to ensure that the connection between the rocker arm 40 and the fixing member 60 is more stable. The height h2 of the rocker arm refers to the height of the first end 41 of the rocker arm 40.
Preferably, a reinforcing rib 57 is provided on a side of the first side wall 53 away from the casing 20 to reinforce the strength of the coupling ring 50 itself. One end of the rib 57 is connected to the link ring 50, and the other end extends in the radial direction R of the casing 20 in a direction away from the link ring 50. In the present embodiment, the number of the reinforcing ribs 57 is two. The two reinforcing ribs 57 are provided at intervals along the axial direction P of the casing 20.
In the present embodiment, the fixing member 60 is a pin to achieve higher mounting accuracy. Specifically, the fixing member 60 includes a head portion 61 and a rod portion 62, the outer diameter of the head portion 61 is larger than the outer diameter of the rod portion 62, and the head portion 61 is engaged with the outer side of the first side wall 53. However, the fixing member 60 is not limited thereto, and may be a fixing member such as a bolt.
In the present embodiment, since the fixing member 60 is a pin, in order to prevent the fixing member 60 from falling off the rocker arm 40, a stopper is provided on the outer side of the head 61 of the fixing member 60, and the stopper is provided along the axial direction P of the casing 20. The stopper is fixed to the reinforcing rib 57. Specifically, the reinforcing rib 57 is provided with a mounting hole 58 along the axial direction P of the casing 20, and the stopper is mounted in the mounting hole 58.
The rocker arm 40 includes a connecting portion 44 connected between the first end 41 and the second end 42, and the height h3 of the first end 41 is greater than the height h4 of the connecting portion 44, so that the strength of the first end 41 is higher and the torsion force caused by the rotation of the linkage ring 50 can be better borne.
A space is provided between the first end 41 of the rocker arm 40 and the link ring 50 to ensure that they do not interfere with each other during movement. Specifically, the first end 41 of the rocker arm 40 has a first spacing W1 from the first side wall 53 and the first end 41 of the rocker arm 40 has a second spacing W2 from the second side wall 54; the first spacing W1 is greater than the second spacing W2 to better ensure positional change of the snap ring 50 during rotation. Preferably, the second pitch W2 is 0.3mm to 0.5mm.
The present embodiment also provides an aeroengine comprising a vane adjustment mechanism 10 as described above.
The invention avoids the use of a riveted machining process to connect the linkage ring 50 and the rocker arm 40 without deforming the rocker arm 40 and has simpler machining process by arranging the specific structure of the stationary blade adjusting mechanism 10. Meanwhile, by setting the rocker arm 40 to be a flexible rocker arm, the flexible rocker arm is deformable by itself, and changes in angular displacement are compensated by bending deformation of the flexible rocker arm itself, so that the rocker arm 40 is prevented from being stuck in rotation.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (10)
1. A vane adjustment mechanism, the vane adjustment mechanism comprising: the stator blade penetrates through the casing, the linkage ring is connected with the stator blade through the rocker arm and is arranged on the outer side of the casing,
the linkage ring is provided with a containing cavity, the containing cavity is provided with an opening facing the stator blade, the containing cavity comprises a first side wall and a second side wall which are oppositely arranged along the radial direction of the casing, the second side wall is positioned between the first side wall and the casing, and a first through hole and a second through hole are respectively formed in the first side wall and the second side wall;
the rocker arm is a flexible rocker arm, the first end of the rocker arm is inserted into the accommodating cavity through the opening, and the second end of the rocker arm is connected with the stator blade;
the stationary blade adjusting mechanism further comprises a fixing piece, wherein the fixing piece sequentially penetrates through the first through hole, a rocker arm hole located in the accommodating cavity and arranged at the first end of the rocker arm, and the second through hole, so that the linkage ring and the rocker arm are fixed together.
2. The vane adjustment mechanism of claim 1, further comprising a bushing, the bushing being nested outside the stationary member and positioned within the rocker arm bore.
3. The vane adjustment mechanism of claim 2, wherein a first gap is provided between the bushing and the link ring in a radial direction of the casing, and the first gap is greater than 0 and equal to or less than 0.1mm.
4. The vane adjustment mechanism of claim 2, wherein a second gap is provided between the bushing and an inner wall surface of the rocker arm hole, and the second gap is greater than 0 and less than or equal to 0.1mm; and/or the number of the groups of groups,
a third gap is formed between the bushing and the outer wall surface of the fixing piece, and the third gap is larger than 0 and smaller than or equal to 0.03mm.
5. The vane adjustment mechanism of claim 2, wherein a height of the bushing is equal to or greater than a sum of a height of the rocker arm and a distance between the rocker arm and the second sidewall.
6. The vane adjustment mechanism of claim 1, wherein a stiffener is provided on a face of the first sidewall remote from the casing.
7. The vane adjustment mechanism of claim 1,
the fixing piece is a pin;
the fixing piece comprises a head and a rod, the outer diameter of the head is larger than that of the rod, and the head is clamped on the outer side of the first side wall.
8. The vane adjustment mechanism of claim 7,
the outside of the head of mounting is equipped with the locating part, the locating part is followed the axial setting of receiver, the locating part is used for restricting the mounting is followed drop on the rocking arm.
9. The vane adjustment mechanism of any one of claims 1-8, wherein the rocker arm includes a connection between the first end and the second end, the first end having a height that is greater than a height of the connection.
10. Aeroengine, comprising a vane adjustment mechanism according to any of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210688795.4A CN117287420A (en) | 2022-06-16 | 2022-06-16 | Stationary blade adjusting mechanism and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210688795.4A CN117287420A (en) | 2022-06-16 | 2022-06-16 | Stationary blade adjusting mechanism and aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117287420A true CN117287420A (en) | 2023-12-26 |
Family
ID=89255867
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210688795.4A Pending CN117287420A (en) | 2022-06-16 | 2022-06-16 | Stationary blade adjusting mechanism and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117287420A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117948191A (en) * | 2024-03-26 | 2024-04-30 | 中国航发燃气轮机有限公司 | Gas turbine and stator blade adjusting structure thereof |
-
2022
- 2022-06-16 CN CN202210688795.4A patent/CN117287420A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117948191A (en) * | 2024-03-26 | 2024-04-30 | 中国航发燃气轮机有限公司 | Gas turbine and stator blade adjusting structure thereof |
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