CN117345353A - Adjustable stator structure with variable-length rocker arm and air compressor - Google Patents
Adjustable stator structure with variable-length rocker arm and air compressor Download PDFInfo
- Publication number
- CN117345353A CN117345353A CN202311640680.9A CN202311640680A CN117345353A CN 117345353 A CN117345353 A CN 117345353A CN 202311640680 A CN202311640680 A CN 202311640680A CN 117345353 A CN117345353 A CN 117345353A
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- casing
- linkage ring
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- 239000012530 fluid Substances 0.000 claims abstract description 32
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000010276 construction Methods 0.000 claims 5
- 230000001105 regulatory effect Effects 0.000 abstract description 2
- 238000004088 simulation Methods 0.000 description 12
- 238000009826 distribution Methods 0.000 description 7
- 230000008901 benefit Effects 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an adjustable stator structure with a variable-length rocker arm and a compressor, wherein the adjustable stator structure comprises a casing, and the casing is cylindrical; a plurality of stator blades are arranged on the casing at intervals along the circumferential direction of the casing, and the stator blades are positioned on the first cross section of the casing; the outside of the casing is coaxially provided with a linkage ring, and the linkage ring is positioned on the second cross section of the casing; the vane handles of the stator vanes are positioned outside the casing, rocker arms are arranged between each vane handle and the linkage ring, and the length direction of each rocker arm is parallel to the axis of the casing; the rocker arms are fixedly connected with the leaf handles, and each rocker arm is hinged with the linkage ring; according to the invention, the length of the rocker arm in the boundary layer low-energy fluid range is regulated, so that the rotating angle of the corresponding stator blade is reduced when the linkage ring rotates and moves, the air flow direction is closer to the axis of the casing, the influence of low distortion pressure is counteracted, and the distortion index of the engine fan inlet is reduced.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines, and particularly relates to an adjustable stator structure with a variable-length rocker arm and a compressor.
Background
In recent years, aircraft and engine designs have been progressively refined in the field of aviation, with traditional aerodynamic layout and engine architecture, system performance has approached a limit. Designers are beginning to consider benefits in the integration of engines and aircraft, with the desire to further reduce drag and fuel consumption through a more compact fuselage/propulsion system integration scheme.
In this context, boundary layer suction (boundary layer ingestion, BLI) propulsion systems are gradually brought into the field of view of the designer, and BLI refers to a large amount of fuselage or wing boundary layer low energy fluid entering the inlet (thickness may reach 30% of inlet height of the inlet), becoming working medium for the engine, taking part in work to generate thrust. In aviation aircraft, BLI propulsion systems often employ embedded engines with air inlets, engines, mounted aft of the wing or fuselage to extract the boundary layer low energy fluid of the aircraft.
Although the BLI propulsion system may reduce aircraft drag and engine demand power. However, in some special states (such as a large attack angle) of the aircraft, the boundary layer airflow has thicker low-energy fluid, and flow separation easily occurs after the boundary layer airflow enters the air inlet channel of the aircraft, so that the distortion index of the inlet of the engine fan is increased, and the efficiency and margin of the fan are reduced.
Disclosure of Invention
The invention aims to provide an adjustable stator structure with a variable-length rocker arm and a compressor, so that the rotation angle of a blade in the stator structure is adjusted, and the distortion index of an inlet of a fan of an engine is reduced.
The invention adopts the following technical scheme: an adjustable stator structure with a variable-length rocker arm comprises a casing, wherein the casing is cylindrical;
a plurality of stator blades are arranged on the casing at intervals along the circumferential direction of the casing, and the stator blades are positioned on the first cross section of the casing;
the outside of the casing is coaxially provided with a linkage ring, and the linkage ring is positioned on the second cross section of the casing;
the vane handles of the stator vanes are positioned outside the casing, rocker arms are arranged between each vane handle and the linkage ring, and the length direction of each rocker arm is parallel to the axis of the casing; the rocker arms are fixedly connected with the leaf handles, and each rocker arm is hinged with the linkage ring;
wherein the length of the rocker arm in the boundary layer low energy fluid range is greater than the length of the rocker arm outside the boundary layer low energy fluid range.
Further, the blade handle is provided with a connecting section and a threaded section;
the peripheral surface of the connecting section is provided with a fixing surface;
the thread segments are located at the free ends of the shanks and adjacent the connecting segments.
Further, the blade body of the stator blade is located inside the casing, and the stator blade can rotate relative to the axis of the stator blade.
Further, the linkage ring is in a ring shape, and an accommodating cavity is formed in the end face of the linkage ring, facing the blade handle;
the connecting ring is provided with a pin shaft penetrating through the accommodating cavity, one end of the rocker arm is provided with a first connecting through hole, and the pin shaft penetrates through the first connecting through hole.
Further, a knuckle bearing is arranged on the pin shaft.
Further, the other end of the rocker arm is provided with a second connecting through hole, the second connecting through hole is sleeved on the connecting section, and the cross section of the second connecting through hole is identical to the cross section of the connecting section in shape.
Further, a first fixing hole and a second fixing hole for mounting the pin shaft are formed in the linkage ring;
the first fixing hole is a strip-shaped hole and is positioned in the boundary layer low-energy fluid range, and the length direction of the first fixing hole is consistent with the axial direction of the linkage ring;
the second fixing hole is a round hole and is positioned outside the low-energy fluid range of the boundary layer.
Further, adjacent rocker arms within the boundary layer low energy fluid range are different in length, and corresponding first fixing holes are different in length.
Further, the part of the linkage ring located in the boundary layer low-energy fluid range is an extension section, and the ring body of the extension section extends in the opposite direction of the stator blade in the axial direction of the linkage ring.
Another technical scheme of the invention is as follows: a compressor comprises the adjustable stator structure with the variable-length rocker arm.
The beneficial effects of the invention are as follows: according to the invention, the length of the rocker arm in the boundary layer low-energy fluid range is regulated, so that the rotating angle of the corresponding stator blade is reduced when the linkage ring rotates and moves, the airflow direction is closer to the axis of the casing, and the acting pressurizing capacity of the rotor behind the stator structure is increased, thereby counteracting the influence of abnormal low pressure and reducing the distortion index of the inlet of the engine fan.
Drawings
FIG. 1 is a schematic view of an adjustable stator structure with a variable length rocker arm according to an embodiment of the present invention;
FIG. 2 is a schematic view of a stator vane according to an embodiment of the present invention;
FIG. 3 is a schematic view of a rocker arm according to an embodiment of the present invention;
FIG. 4 is a schematic diagram showing a connection state of a rocker arm according to an embodiment of the present invention;
FIG. 5 is a schematic view of the structure of a linkage ring according to an embodiment of the present invention;
FIG. 6 is a schematic side view of a linkage ring according to an embodiment of the present invention;
FIG. 7 is a schematic view showing a state of the adjustable stator structure after the movement of the linkage ring according to the embodiment of the present invention;
FIG. 8 is a schematic illustration of a rocker arm length distribution within a boundary layer low energy fluid range in an embodiment of the present invention;
FIG. 9 is a graph illustrating vane adjustment angle profiles after adjustment for rocker arm length distribution over boundary layer low energy fluid ranges in accordance with embodiments of the present invention;
FIG. 10 is a graph showing the flow ratio characteristics of simulation test results in accordance with an embodiment of the present invention;
FIG. 11 is a graph showing flow efficiency characteristics of simulation test results in the embodiment of the present invention.
Wherein: 10. a casing;
20. a linkage ring; 21. a lengthening section; 22. a first fixing hole; 23. a receiving chamber; 24. a second fixing hole;
30. stator blades; 31. a leaf body; 32. a petiole; 33. a connection section; 34. a limiting ring; 35. a threaded section;
40. a rocker arm; 41. a first connection through hole; 42. a second connection through hole;
50. a pin shaft;
60. and a knuckle bearing.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
Compared with the traditional propulsion system, the BLI propulsion system has the characteristics of further reducing the resistance of the aircraft, reducing the power required by the engine and improving the propulsion efficiency of the engine, and according to related researches, the fuel efficiency of the aircraft after the boundary layer is sucked can be improved by about 8%.
Of course, the new layout also presents new challenges, for conventional pod aircraft, the fuselage is located at a distance from the engine, which is less disturbing to each other and is generally negligible in the design process. The integrated distributed propulsion system uses a plurality of small engines which are semi-embedded in the upper surface of the wing body fusion body to replace a large-size engine, and the overall benefit is improved through a boundary layer suction technology. At this time, the coupling effect of the aircraft and the internal and external flow fields of the engine is obvious, the thickness of the boundary layer sucked by the engine is thinner in a cruising state, the influence on the engine fan is smaller, and the benefit of the whole aircraft is larger.
However, in the takeoff state, the attack angle of the aircraft is larger, the boundary layer is thicker, and at the moment, after the boundary layer low-energy fluid enters the air inlet channel, flow separation is very easy to occur under S-shaped curvature, so that the distortion index of the inlet of the engine fan is increased, the fan efficiency and margin are reduced, and the benefits of partial wing body fusion and boundary layer suction are counteracted. Therefore, there is an urgent need to develop a fan structure that can operate efficiently under both strong distortion and uneven air intake.
The invention discloses an adjustable stator structure with a variable-length rocker arm, which is shown in fig. 1, and comprises a casing 10, wherein the casing 10 is cylindrical; a plurality of stator blades 30 are mounted on the casing 10 at intervals along the circumferential direction of the casing 10, and the stator blades 30 are positioned on the first cross section of the casing 10; a linkage ring 20 is coaxially arranged outside the casing 10, namely the casing 10 and the linkage ring 20 are coaxially arranged, and the linkage ring 20 is positioned on the second cross section of the casing 10; the vane handles 32 of the stator vanes 30 are positioned outside the casing 10, a rocker arm 40 is arranged between each vane handle 32 and the linkage ring 20, and the length direction of the rocker arm 40 is parallel to the axis of the casing 10; the rocker arms 40 are fixedly connected with the blade handles 32, and each rocker arm 40 is hinged with the linkage ring 20; wherein the length of the rocker arm 40 located in the boundary layer low energy fluid range is greater than the length of the rocker arm 40 located outside the boundary layer low energy fluid range.
According to the invention, by adjusting the length of the rocker arm 40 in the boundary layer low-energy fluid range, the rotating angle of the corresponding stator blade 30 is reduced when the linkage ring 20 rotates and moves, the air flow direction is closer to the axial direction of the casing 10, and the acting pressurizing capacity of the rotor behind the stator structure is increased, so that the influence of abnormal low pressure is counteracted, and the distortion index of the inlet of the engine fan is reduced.
The boundary layer low-energy fluid range refers to a corresponding boundary layer low-energy fluid range in an aircraft take-off state, and can be determined according to aerodynamic layout, airfoil thickness, airfoil loading mode, airfoil length, flight height, attack angle, speed and incoming flow density of an aircraft.
Typically, several sets of stators and rotors are disposed on the casing 10 along the axial direction thereof, and the stators and rotors are disposed at intervals. The above-mentioned plurality of stator blades 30 being located on the first cross section of the casing 10 means that the axes of the stator blades 30 in one group of stators are all on the first cross section of the casing 10. The first cross section and the second cross section refer to cross sections located at different axial positions, that is, the stator vane 30 and the linkage ring 20 are spaced from each other in the axial direction of the casing 10, so that the two sections can be prevented from being interfered during the installation process.
As shown in fig. 2, the stator vane 30 is divided into two parts, the vane body 31 is located inside the casing 10, the orientation of the vane body can be adjusted according to the need, and a certain gap is formed between the vane body 31 and the inner wall of the casing 10, so as to avoid interference with the inner wall of the casing when the vane body 31 rotates. The linkage ring 20 rotates relative to the axis thereof and moves in the axial direction under the action of external force, so that the rocker arm 40 drives the vane stem 32 to rotate, and the adjustment of the vane body 31 direction is completed.
In fig. 2, the annular portion next to the blade body 31 is a limiting portion of the stator blade 30 and the casing 10, a groove for accommodating the annular portion is formed on the inner wall of the casing 10, and a through hole through which the blade shank 32 passes is further formed, and when the stator blade 30 rotates, the annular portion rotates in the groove of the casing 10. Meanwhile, a sealing member is provided between the stator vane 30 and the casing 10, so that the leakage of the air flow inside the casing 10 from the gap can be prevented.
More specifically, the shank 32 has a connecting section 33 and a threaded section 35 thereon; the peripheral surface of the connecting section 33 is provided with a fixing surface; the fixing surface may be a flat surface or a rough surface, and the number of fixing surfaces may be one, two, three, or the like, as long as the fixing with the rocker arm 40 can be achieved. A threaded section 35 is located at the free end of the shank 32 and adjacent to the connecting section 33.
During installation, the vane stem 32 firstly penetrates out of the casing 10, then the second connecting through hole 42 of the rocker arm 40 is sleeved on the connecting section 33, and finally the thread section 35 is provided with the limiting ring 34 and the nut, so that the stator vane 30 can be prevented from falling into the casing 10 through the cooperation of the limiting ring 34 and the nut.
The blade body 31 of the stator blade 30 is positioned inside the casing 10 by the above-described method, and the stator blade 30 is rotatable with respect to its own axis.
As shown in fig. 3, a second connecting through hole 42 is formed at one end of the rocker arm 40, the second connecting through hole 42 is sleeved on the connecting section 33, and the cross section of the second connecting through hole 42 is the same as the cross section of the connecting section 33. Through the second connecting through hole 42 and the connecting section 33, when one end of the rocker arm 40 receives the rotating force of the linkage ring 20, the rocker arm 40 rotates relative to the axis of the connecting section 33, and the connecting section 33 is driven to rotate, so that the angle change of the blade body 31 is realized.
Locking of the rocker arm 40 and stator vane 30 is achieved by the above-described fixing surfaces. Further, a radially outwardly disposed support portion may be provided on the casing 10 to support the rocker arm 40 against falling off. Regarding the thread section 35, the retainer ring 34 is first installed so that one face of the retainer ring 34 blocks the rocker arm 40 to prevent the rocker arm 40 from coming out of the thread section 35, and then the nut is tightened to complete the installation of the rocker arm 40. As shown in fig. 4, the rocker arm 40 and the stator vane 30 are shown in a locked configuration.
In one embodiment, the linkage ring 20 is annular, the end surface of the linkage ring 20 facing the vane stem 32 is provided with a receiving cavity 23, and the end of the rocker arm 40 is inserted into the receiving cavity 23. The accommodating chamber 23 may be an annular whole or a plurality of chambers formed at intervals. The link ring 20 is provided with a pin 50 passing through the accommodating chamber 23, the other end of the rocker arm 40 is provided with a first connecting through hole 41, and the pin 50 passes through the first connecting through hole 41. The fixing of the rocker arm 40 can be conveniently realized by the mutual matching of the pin shaft 50 and the accommodating cavity 23. The "one end" and "the other end" mentioned above refer to both end portions of a certain object, respectively, and neither refer to a specific end portion.
In addition, since the lengths of the different rocker arms 40 are different, the initial fixing position of the pin 50 is also changed. Moreover, as shown in fig. 7, when the link ring 20 rotates and moves in the axial direction thereof under the action of an external force, the rotation angle and the axial movement distance of the partially lengthened rocker arm 40 are different, so that in order to avoid the axial locking of the link ring 20, the pivot shaft 50 is provided with the knuckle bearing 60, so that when the rocker arm 40 moves with the link ring 20, the pivot angle can be adjusted in a small range, and the axial locking of the rocker arm 40 and the link ring 20 is avoided.
As shown in fig. 5 and 6, in order to better match the movement of the lengthened rocker arm 40, the linkage ring 20 is provided with a first fixing hole 22 and a second fixing hole 24 for installing the pin 50; the first fixing hole 22 is a strip-shaped hole, is positioned in the boundary layer low-energy fluid range, and has the length direction consistent with the axial direction of the linkage ring 20; the second fixing hole 24 is a round hole, and is matched with the pin shaft 50 in size and located outside the boundary layer low-energy fluid range.
In one embodiment, because the air flow angle and air pressure are different at different locations within the boundary layer low energy fluid range, adjacent rocker arms 40 within the boundary layer low energy fluid range are different in length and the corresponding first securing apertures 22 are different in length. Taking the sector distribution of general distortion and the characteristics of strong middle and weak middle into consideration, the length change of the rocker arm adopts Gaussian function distribution. As shown in FIG. 8, which is a schematic diagram illustrating the analysis of the lengths of a group of rocker arms of different lengths in this embodiment, it can be seen from the figure that the lengths of five rocker arms 40 in total are adjusted, and the numbers are respectively I-V, wherein the longest rocker arm is numbered III, the length reaches 40mm, and the lengths of the rest of the non-lengthened rocker arms are 32mm. The stator vanes 30 with different angular distributions can be constructed by adjusting the values of the parameters. As shown in fig. 9, the distribution of the adjusted angle of the stator vane 30 under the rocker arm length distribution is given, and the angles of the vane bodies 31 of the stator vane 30 after the adjustment in the remaining regions are all 30 °, in this embodiment, the angles of the vane bodies 31 are calculated according to the length of the rocker arm 40, the circumferential displacement of the link ring 20, that is, the angle=arcsin (circumferential displacement of the link ring 20/length of the rocker arm 40), which is the rotation angle with respect to the initial state of the vane bodies 31, which is the installation state of the conventional stator vane in the art, and the circumferential displacement refers to the arc length corresponding to the rotation angle of the link ring 20.
As one possible implementation, the portion of the linkage ring 20 located in the boundary layer low-energy fluid range is an extension 21, and the ring body of the extension 21 extends in the opposite direction of the stator vane 30 in the axial direction of the linkage ring 20. This provides open space for the strip-shaped holes described above on the one hand and also increases the strength of the extension 21 in the boundary layer low energy fluid range on the other hand.
According to the invention, the length of the rocker arm 40 is changed, so that the stator blade 30 on the casing 10 is in two states of symmetry and partial asymmetry, and the stator blade is used for adapting to the characteristics of strong distortion, uneven air intake and different states of even air intake. That is, the angle of the compressor stator blade 30 can be switched between symmetry and asymmetry by the scheme, so that the compressor is simultaneously adapted to distorted and uniform undistorted inlet flow fields, and the performance of the boundary layer sucked into different states of the aircraft in the future is improved.
The present invention also simulates and tests the stator structure of fixed length rocker arms and variable length rocker arms to verify the performance of the stator structure, and the results are shown in fig. 10 and 11.
Firstly, the simulation of the full-channel fan under the uniform air inlet condition is completed, and the characteristic result obtained by the simulation is compared with the test result under the uniform condition. In fig. 10 and 11, "exp" represents the test result under the condition of uniform air intake, and "full channel" represents the simulation result under the condition of uniform air intake, the flow rate of the plugging point obtained by simulation under the condition is different from that of the test by 0.78%, the peak efficiency is different by 0.1%, and the simulation and test results are very close to each other, thus illustrating the effectiveness of the simulation. In fig. 10, the fan inlet-outlet total pressure ratio is obtained by dividing the fan outlet total pressure by the fan inlet total pressure, and the fan inlet-outlet isentropic efficiency in fig. 11 can be obtained by converting the fan inlet-outlet total pressure.
Then, two kinds of stator structure performances under the distorted air intake condition are further completed by using a simulation test, wherein in the figure, "full channel distortion" refers to simulation results corresponding to stator structures of the fixed-length rocker arm, and "asymmetrical stator" refers to simulation results corresponding to stator structures of the variable-length rocker arm, and the simulation results show that: when distorted air intake is carried out, under the same inlet stagnation parameter and outlet static pressure conditions, the peak efficiency of a stator structure corresponding to the variable-length rocker arm is improved by 0.5%, the flow of a blocking point is increased by 1.8%, the margin is increased by 5%, and the performance of the fan under the distorted air intake condition is greatly improved.
The invention also discloses a compressor, which comprises the adjustable stator structure with the variable-length rocker arm.
Claims (10)
1. An adjustable stator structure with a variable-length rocker arm is characterized by comprising a casing (10), wherein the casing (10) is cylindrical;
a plurality of stator blades (30) are mounted on the casing (10) at intervals along the circumferential direction of the casing, and the stator blades (30) are positioned on a first cross section of the casing (10);
a linkage ring (20) is coaxially arranged outside the casing (10), and the linkage ring (20) is positioned on a second cross section of the casing (10);
a vane handle (32) of the stator vane (30) is positioned outside the casing (10), a rocker arm (40) is arranged between each vane handle (32) and the linkage ring (20), and the length direction of the rocker arm (40) is parallel to the axis of the casing (10); the rocker arms (40) are fixedly connected with the leaf stems (32), and each rocker arm (40) is hinged with the linkage ring (20);
wherein the length of the rocker arm (40) located in the boundary layer low energy fluid range is greater than the length of the rocker arm (40) located outside the boundary layer low energy fluid range, and the adjacent rocker arms (40) located in the boundary layer low energy fluid range are different in length.
2. An adjustable stator construction with a variable length rocker arm according to claim 1, characterized in that the shank (32) has a connecting section (33) and a threaded section (35);
the peripheral surface of the connecting section (33) is provided with a fixing surface;
the threaded section (35) is located at the free end of the shank (32) and adjacent to the connecting section (33).
3. An adjustable stator arrangement with a variable length rocker arm according to claim 2, characterized in that the blade body (31) of the stator blade (30) is located inside the casing (10) and that the stator blade (30) is rotatable with respect to its axis.
4. An adjustable stator structure with a variable length rocker arm according to claim 3, characterized in that the linkage ring (20) is circular, and the end surface of the linkage ring (20) facing the vane stem (32) is provided with a containing cavity (23);
the connecting device is characterized in that a pin shaft (50) penetrating through the accommodating cavity (23) is arranged on the linkage ring (20), a first connecting through hole (41) is formed in one end of the rocker arm (40), and the pin shaft (50) penetrates through the first connecting through hole (41).
5. An adjustable stator construction with a variable length rocker arm according to claim 4, characterized in that the pin (50) is provided with a knuckle bearing (60).
6. An adjustable stator arrangement with a variable length rocker arm according to claim 4, characterized in that a second connecting through hole (42) is provided at the other end of the rocker arm (40), the second connecting through hole (42) is sleeved on the connecting section (33), and the cross section of the second connecting through hole (42) is identical to the cross section of the connecting section (33).
7. An adjustable stator construction with a variable length rocker arm according to claim 6, characterized in that the linkage ring (20) is provided with a first fixing hole (22) and a second fixing hole (24) for the pin shaft (50) to be mounted;
the first fixing hole (22) is a strip-shaped hole and is positioned in the boundary layer low-energy fluid range, and the length direction of the first fixing hole is consistent with the axis direction of the linkage ring (20);
the second fixing hole (24) is a round hole and is positioned outside the boundary layer low-energy fluid range.
8. An adjustable stator construction with a variable length rocker arm according to claim 7, characterized in that the rocker arm (40) located in the boundary layer low energy fluid range has a different length of the corresponding first fixation hole (22).
9. An adjustable stator construction with a variable length rocker arm according to claim 8, characterized in that the portion of the linkage ring (20) located in the boundary layer low energy fluid range is an extension (21), the ring body of the extension (21) extending in the axial direction of the linkage ring (20) in the opposite direction of the stator vanes (30).
10. A compressor comprising an adjustable stator arrangement having a variable length rocker arm according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311640680.9A CN117345353B (en) | 2023-12-04 | 2023-12-04 | Adjustable stator structure with variable-length rocker arm and air compressor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311640680.9A CN117345353B (en) | 2023-12-04 | 2023-12-04 | Adjustable stator structure with variable-length rocker arm and air compressor |
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| CN117345353A true CN117345353A (en) | 2024-01-05 |
| CN117345353B CN117345353B (en) | 2024-01-26 |
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