Adjustable stator blade adjustment mechanism and aeroengine comprising same

Abstract

The application discloses a kind of adjustable stator blade adjusting mechanism and the aero-engine comprising it.The adjustable stator blade adjusting mechanism includes linkage ring, rocker and guiding device, one end of rocker is used to connect to the rotating shaft of adjustable stator blade, the other end is used to connect to linkage ring, and guiding device includes connected first guide component and second guide component.First guide component is arranged on linkage ring, and second guide component is used to be arranged on the outer wall surface of the casing of aero-engine, and first guide component and second guide component cooperate to make linkage ring rotate around the casing along the preset track.The adjusting mechanism improves the linkage precision of the same stage blade and improves the adjusting precision of the adjusting mechanism.At the same time, linkage ring only needs to rotate around the circumference, and this feature makes force transmission simpler, and under the same conditions, the force required by the actuator is less, i.e.the power demand of actuator is lower.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine structural design and manufacturing technology, in particular to an adjustable stator blade adjusting mechanism and an aero-engine comprising the same. BACKGROUND

[0002] With the improvement of engine performance, the working condition of the compressor is closer to the surge boundary, and the angle of the stator blades of the first few stages of the compressor is generally adjustable to achieve greater surge margin. In order to reduce the mass of the compressor and reduce the control variables, the multi-stage blade adjusting mechanism is usually designed as a linkage mechanism that is driven by a single actuator to adjust multiple rows of blades according to different angle rules. The traditional aero-engine compressor stator blade adjusting mechanism mainly includes an actuator, a connecting rod, a linkage ring, a rocker arm, etc., and can be mainly divided into two categories: torsion bar type and crank connecting rod type.

[0003] The crank connecting rod type linkage mechanism is mainly driven by the actuator to move the actuating arm, thereby driving the multiple parallel cranks connected by the connecting rod to rotate, and the rotation of the cranks drives the corresponding driving arm to actuate the corresponding linkage ring, so that the linkage ring swings around the rotation axis of the blade, and finally drives the blade. The torsion bar type linkage mechanism is mainly driven by the actuator to move the actuating arm, thereby driving the torsion bar to rotate. Each linkage ring is connected to the torsion bar through a connecting rod, and the rotation of the right torsion bar drives each linkage ring to complete the linkage process. The main feature of the torsion bar type adjusting mechanism is that the structure is relatively simple, but the required space is larger than that of the crank connecting rod type.

[0004] Due to the characteristics of the swing of the rocker arm around the rotation axis of the stator blade, the linkage ring of the existing two types of adjusting mechanisms needs to have a displacement along the axial direction in addition to the circumferential rotation around the casing. Therefore, multiple limit screws are arranged around the casing, and a boss is arranged on the casing to ensure the accuracy of the circumferential rotation of the linkage ring. In an ideal environment, the limit screws do not contact the casing and have a certain gap, and the linkage ring only depends on the connecting rod and the rocker arm hanging on the periphery of the casing. However, in actual working conditions, due to the unevenness of the force, the linkage ring will deform unevenly and will not be concentric with the casing during movement, and the limit screws will often contact and limit the casing on one side. This brings certain linkage error of the stator blade, and also brings friction and generates resistance. The multiple dimensional degrees of freedom in space also bring certain inaccuracy to the linkage of each linkage ring. These factors will affect the accuracy of the adjusting mechanism, cause errors in the angle adjustment of each stage, cause inconsistency in the angle adjustment of the blades of the same stage, and thus affect the performance of the engine.

[0005] The traditional linkage ring is in a suspended state, and its position in space is ensured by a rocker arm and a connecting rod, but neither of them can provide sufficient support, and a limiting screw needs to be additionally added to ensure the maximum deformation. Such a way cannot well ensure the concentricity of the linkage ring during movement, affects the joint adjustment accuracy of the same stage blades, and further affects the performance of the engine; and a plurality of limiting screws in the circumferential direction are needed to limit the eccentricity, and a corresponding boss needs to be designed on the casing to provide support. In actual working conditions, the contact between the screw and the boss will bring additional friction resistance, increasing the power demand of the actuator cylinder.

[0006] Therefore, the adjustment mechanism for adjusting the angle of the adjustable stator blade in the prior art has the defects of low joint adjustment accuracy of the same stage blades and high power demand of the actuator cylinder. SUMMARY

[0007] The technical problem to be solved by the present application is to overcome the above-mentioned defects in the prior art, and to provide an adjustable stator blade adjustment mechanism and an aero-engine comprising the same.

[0008] The present application solves the above technical problems by the following technical solutions:

[0009] An adjustable stator blade adjustment mechanism, comprising a linkage ring and a rocker arm, one end of the rocker arm being used for being connected to a rotating shaft of an adjustable stator blade, the other end of the rocker arm being used for being connected to the linkage ring, the adjustable stator blade adjustment mechanism further comprising a guide device, the guide device comprising a first guide component and a second guide component connected to each other;

[0010] The first guide component is arranged on the linkage ring, and the second guide component is arranged on the outer wall surface of the casing of the aero-engine, and the first guide component and the second guide component cooperate to make the linkage ring rotate around the casing along a preset track.

[0011] In the present application, under the action of the first guide component and the second guide component, the linkage ring can reliably rotate around the casing along the preset track. The linkage ring is no longer suspended at the periphery of the casing, and the linkage ring has contact with the casing through the cooperation of the first guide component and the second guide component, thereby increasing the stress points and eliminating the deformation and other adverse factors caused by the insufficient rigidity of the linkage ring. The uneven deformation of the linkage ring can be avoided, thereby ensuring the accuracy of the circumferential rotation of the linkage ring, improving the joint adjustment accuracy of the same stage blades, and improving the adjustment accuracy of the adjustment mechanism. At the same time, by using the above structure, the linkage ring only needs to rotate in the circumferential direction. This feature makes the force transmission simpler, and under the same conditions, the force provided by the actuator cylinder is less, i.e. the power demand of the actuator cylinder is lower.

[0012] Preferably, one of the first guide component and the second guide component slides or rolls relative to the other.

[0013] In this scheme, the first guide component and the second guide component are connected or matched by sliding or rolling, which is relatively simple in connection or matching mode, is conducive to simplifying the overall structure of the adjusting mechanism, and is also conducive to reducing the overall weight of the aero-engine containing the adjusting mechanism.

[0014] Preferably, one of the first guide component and the second guide component is a sliding rail, and the other is a roller.

[0015] Alternatively, one of the first guide component and the second guide component is a sliding rail, and the other is a sliding block.

[0016] Preferably, the inner wall surface of the linkage ring is provided with a plurality of rollers, and the plurality of rollers are uniformly distributed along the circumferential direction of the linkage ring.

[0017] In this scheme, the plurality of stress points of the linkage ring are uniformly distributed, which is conducive to further avoiding uneven deformation of the linkage ring and further improving the precision of linkage adjustment of the same-stage blade.

[0018] Preferably, the inner wall surface of the linkage ring is provided with a plurality of rollers, and the plurality of rollers are uniformly distributed along the circumferential direction of the linkage ring.

[0019] In this scheme, the first accommodating groove can protect and limit the roller, which is conducive to improving the reliability of the adjusting mechanism.

[0020] Preferably, the adjustable stator blade adjusting mechanism further comprises a connecting assembly, the other end of the rocker arm is provided with a second accommodating groove extending along the extension direction of the rocker arm, one end of the connecting assembly is connected to the linkage ring, and at least a part of the other end of the connecting assembly is arranged in the second accommodating groove and can rotate and slide in the second accommodating groove.

[0021] In this scheme, the above structure can improve the flexibility and reliability of the adjusting process, and prevent the structure from being stuck during adjustment to affect the adjusting effect.

[0022] Preferably, the connecting assembly comprises a pin and a ball bearing, the ball bearing is arranged in the second accommodating groove, one end of the pin is connected to the linkage ring, and the other end of the pin extends out of the second accommodating groove through the ball bearing.

[0023] In this scheme, the ball bearing can conveniently and reliably realize the transmission between the linkage ring and the rocker arm.

[0024] Preferably, the ball bearing is slidable relative to the pin.

[0025] Preferably, one end of the pin is vertically connected to the outer wall surface of the linkage ring.

[0026] In this scheme, the above-mentioned structural design is beneficial to improving transmission efficiency and also to improving the compactness of the structure.

[0027] The present invention also provides an aero engine, which includes a casing and the aforementioned adjustable stator blade adjustment mechanism, wherein the second guide member is disposed on the outer wall surface of the casing.

[0028] Based on common knowledge in the field, the above-mentioned preferred conditions can be combined arbitrarily to obtain various preferred embodiments of the present invention.

[0029] The positive and progressive effects of this invention are as follows:

[0030] In this adjustable stator blade adjustment mechanism, under the action of the first and second guide components, the linkage ring can reliably rotate around the casing along a preset trajectory. The linkage ring is no longer suspended outside the casing; it makes contact with the casing through the cooperation of the first and second guide components, increasing the force-bearing points and eliminating adverse factors such as deformation caused by insufficient rigidity of the linkage ring itself. This avoids uneven deformation of the linkage ring, ensuring the accuracy of its circumferential rotation, improving the adjustment accuracy of the same-stage blades, and enhancing the adjustment accuracy of the adjustment mechanism. Furthermore, with this structural design, the linkage ring only needs to rotate circumferentially, simplifying force transmission. Under the same conditions, less force is required from the actuator, meaning lower power demand on the actuator. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the adjustable stator blade adjustment mechanism according to a preferred embodiment of the present invention.

[0032] Figure 2 for Figure 1 A schematic diagram of the structure along section AA in the middle.

[0033] Figure 3 This is another structural schematic diagram of the adjustable stator blade adjustment mechanism according to a preferred embodiment of the present invention.

[0034] Figure 4 This is a schematic diagram of the rocker arm in the adjustable stator blade adjustment mechanism of a preferred embodiment of the present invention.

[0035] Figure 5 for Figure 4 A schematic diagram of the structure along the EE section.

[0036] Figure 6 for Figure 4 A schematic diagram of the structure of the CC section along the middle edge.

[0037] Figure 7 Another structural schematic view of the rocker arm in the adjustable stator vane adjustment mechanism of a preferred embodiment of the present application.

[0038] Figure 8 For Figure 7 A structural schematic view along the B-B portion.

[0039] Figure 9 A structural schematic view of the connection between the rocker arm and the linkage ring in the adjustable stator vane adjustment mechanism of a preferred embodiment of the present application.

[0040] Figure 10 For Figure 9 A structural schematic view along the D-D portion.

[0041] 10 linkage ring

[0042] 101 first accommodating groove

[0043] 20 rocker arm

[0044] 201 second accommodating groove

[0045] 30 roller

[0046] 40 pin

[0047] 50 ball bearing

[0048] 60 vane

[0049] 601 body

[0050] 602 rotating shaft DETAILED DESCRIPTION

[0051] The present application will be further described by way of examples without limiting the present application to the examples.

[0052] As Figures 1-10 shown, the present embodiment discloses an adjustable stator vane adjustment mechanism, which comprises a linkage ring 10 and a rocker arm 20, one end of the rocker arm 20 is connected to a rotating shaft 602 of an adjustable stator vane 60, and the other end is connected to the linkage ring 10, and the adjustable stator vane adjustment mechanism further comprises a guiding device, which comprises a first guiding component and a second guiding component connected to each other. The first guiding component is arranged on the linkage ring 10, and the second guiding component is arranged on an outer wall surface of a casing of an aero-engine, and the first guiding component and the second guiding component cooperate to rotate the linkage ring 10 along a preset track around the casing.

[0053] In the embodiment, under the action of the first guide component and the second guide component, the linkage ring 10 can reliably rotate along the preset track around the casing, the linkage ring 10 is no longer suspended at the periphery of the casing, the linkage ring 10 has contact with the casing through cooperation of the first guide component and the second guide component, stress points are increased, and deformation and other adverse factors caused by insufficient rigidity of the linkage ring 10 are eliminated, uneven deformation of the linkage ring 10 can be avoided, the precision of circumferential rotation of the linkage ring 10 can be ensured, the linkage precision of the same-stage blade 60 is improved, and the adjustment precision of the adjustment mechanism is improved. Meanwhile, by adopting the above structure, the linkage ring 10 only needs to rotate in the circumferential direction, this characteristic makes force transmission simpler, and under the same condition, the force provided by the actuating cylinder is smaller, that is, the power demand of the actuating cylinder is lower.

[0054] In a preferred embodiment, one of the first guide component and the second guide component slides or rolls relative to the other.

[0055] The first guide component and the second guide component are connected or cooperated in a sliding or rolling manner, the connection or cooperation manner is relatively simple, which is beneficial to simplify the overall structure of the adjustment mechanism and reduce the overall weight of the aero-engine including the adjustment mechanism.

[0056] In a preferred embodiment, one of the first guide component and the second guide component is a sliding rail, and the other is a roller 30, so that one of the first guide component and the second guide component can roll relative to the other.

[0057] In another preferred embodiment, one of the first guide component and the second guide component is a sliding rail, and the other is a sliding block, so that one of the first guide component and the second guide component can slide relative to the other.

[0058] Of course, it should be noted that in other alternative embodiments, any other structure applicable to the sliding or rolling can be adopted, and the structure is not limited to the above structure.

[0059] As shown in FIGS. 1, 2 and 3, the linkage ring 10 is arranged on the casing 20, and the linkage ring 10 is connected to the same-stage blade 60 through the adjustment mechanism 100. Figures 1-3 , Figures 9-10 As shown in FIGS. 1, 2 and 3, the linkage ring 10 is arranged on the casing 20, and the linkage ring 10 is connected to the same-stage blade 60 through the adjustment mechanism 100.

[0060] The plurality of stress points of the linkage ring 10 are uniformly distributed, which is beneficial to further avoid uneven deformation of the linkage ring 10 and further improve the linkage precision of the same-stage blade 60.

[0061] In another preferred embodiment, as shown in FIGS. 1, 2 and 3, the first guide component and the second guide component are arranged on the inner wall surface of the linkage ring 10. Figures 1-3 , Figures 9-10As shown, the inner wall surface of the linkage ring 10 is formed with a first accommodating groove 101 in the circumferential direction for accommodating a plurality of rollers 30.

[0062] The first accommodating groove 101 can protect and limit the rollers 30, which is conducive to improving the reliability of the adjusting mechanism.

[0063] It should be noted that the connection of the rollers 30 to the linkage ring 10 is not limited, and any suitable connection method can be used. In this embodiment, as an illustrative embodiment, at least as shown Figures 1-3 The roller 30 is sleeved on the connecting shaft, the two ends of the connecting shaft extend out of the two side walls of the second accommodating groove 201, and then are fixed by a fastener.

[0064] As shown Figures 1-10 The adjustable stator blade adjusting mechanism further includes a connecting assembly, the other end of the rocker arm 20 is provided with a second accommodating groove 201 extending in the extension direction of the rocker arm 20, one end of the connecting assembly is connected to the linkage ring 10, and at least a part of the other end of the connecting assembly is arranged in the second accommodating groove 201 and can rotate and slide in the second accommodating groove 201.

[0065] The above structure can improve the flexibility and reliability of the adjusting process, and prevent the structure from being stuck during adjustment to affect the adjusting effect.

[0066] In a preferred embodiment, the connecting assembly includes a pin 40 and a ball bearing 50, the ball bearing 50 is arranged in the second accommodating groove 201, one end of the pin 40 is connected to the linkage ring 10, and the other end of the pin 40 passes through the ball bearing 50 and extends out of the second accommodating groove 201.

[0067] The ball bearing 50 can conveniently and reliably realize the transmission between the linkage ring 10 and the rocker arm 20.

[0068] In another preferred embodiment, the ball bearing 50 is slidable relative to the pin 40.

[0069] It should be noted that the movement of the ball bearing 50 includes three types: (1) the ball bearing 50 slides along the pin 40; (2) the ball bearing 50 rotates in the second accommodating groove 201; (3) the ball bearing 50 slides in the second accommodating groove 201 along the second accommodating groove 201.

[0070] In another preferred embodiment, one end of the pin 40 is connected perpendicularly to the outer wall surface of the linkage ring 10.

[0071] In this way, the transmission efficiency is improved, and the power demand of the actuator is further reduced. In addition, the above structure is also conducive to improving the compactness of the structure.

[0072] The embodiment also provides an aero-engine, which comprises a casing and the adjustable stator blade adjusting mechanism.

[0073] It should be noted that the adjustable stator blade adjusting mechanism further comprises an actuating cylinder, a torsion bar and a pull rod, the torsion bar is driven by the actuating cylinder, the torsion bar can synchronously drive a plurality of pull rods, and the pull rods are connected to the linkage ring 10 to drive the linkage ring 10 to rotate. The rotating shaft of the blade 60 is rotatably connected to a hole in the casing, the body 601 of the blade 60 is located on the inner side of the casing, and the linkage ring 10, the pull rods and the rocker arm 20 are located on the outer side of the casing. The working process of this part can refer to the disclosure in the Chinese patent with the application publication number CN106545524A, and will not be described here.

[0074] In the present application, in view of the adverse effects caused by the axial displacement of the linkage ring 10, a brand-new adjustable stator blade adjusting mechanism is proposed, which comprises only a linkage ring 10 that rotates in the circumferential direction. The linkage ring 10 is matched with a rocker arm 20 with a sliding groove on the inner side, which can replace the combination of the traditional linkage ring 10 and the rocker arm 20 and eliminate the adverse effects of the traditional linkage ring 10. The linkage ring 10 with a roller 30 is matched with a sliding groove on the casing, which can make the linkage ring 10 rotate in the circumferential direction around the casing at a specific position by the sliding rail-roller 30 mode. The sliding rail-roller 30 mode can also be replaced by a sliding groove-sliding block or other similar modes that can realize circumferential rotation. The linkage ring 10 of this configuration is no longer suspended on the periphery of the casing, and is in contact with the linkage ring 10, which increases the stress points and eliminates the deformation and other adverse factors caused by the insufficient rigidity of the linkage ring 10 itself. Further, the presence of the guide rail on the casing can also ensure the accuracy of the circumferential rotation and improve the adjustment accuracy of the adjusting mechanism. At the same time, the characteristic of the linkage ring 10 only rotating in the circumferential direction brought by the new configuration makes the force transmission simpler, and under the same conditions, the force provided by the actuating cylinder is less.

[0075] Although the specific embodiments of the present application are described above, those skilled in the art should understand that this is only an example, and the protection scope of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present application, and such changes and modifications all fall within the protection scope of the present application.

Claims

1. An adjustable stator blade adjustment mechanism, comprising a linkage ring and a rocker arm, wherein one end of the rocker arm is connected to the rotation shaft of the adjustable stator blade, and the other end is connected to the linkage ring, characterized in that, The adjustable stator blade adjustment mechanism further includes a guide device, which includes a first guide component and a second guide component connected together. The first guide component is disposed on the linkage ring, and the second guide component is disposed on the outer wall surface of the aircraft engine casing. The first guide component and the second guide component cooperate to make the linkage ring rotate around the casing along a preset trajectory. The adjustable stator blade adjustment mechanism further includes a connecting component. The other end of the rocker arm is provided with a second receiving groove extending along the extension direction of the rocker arm. One end of the connecting component is connected to the linkage ring, and at least a portion of the other end of the connecting component is disposed in the second receiving groove and can rotate and slide within the second receiving groove. The connecting assembly includes a pin and a ball bearing. The ball bearing is disposed in the second receiving groove. One end of the pin is connected to the linkage ring, and the other end of the pin passes through the ball bearing and extends out of the second receiving groove. The pin is slidable relative to the ball bearing.

2. The adjustable stator blade adjustment mechanism as described in claim 1, characterized in that, One of the first guide component and the second guide component slides or rotates relative to the other.

3. The adjustable stator blade adjustment mechanism as described in claim 2, characterized in that, One of the first guide component and the second guide component is a slide rail, and the other is a roller; Alternatively, one of the first guide component and the second guide component may be a slide rail and the other may be a slider.

4. The adjustable stator blade adjustment mechanism as described in claim 3, characterized in that, The inner wall of the linkage ring is provided with a plurality of rollers, which are evenly distributed along the circumferential direction of the linkage ring.

5. The adjustable stator blade adjustment mechanism as described in claim 4, characterized in that, The inner wall of the linkage ring has a first receiving groove formed along the circumferential direction for accommodating multiple rollers.

6. The adjustable stator blade adjustment mechanism as described in claim 1, characterized in that, One end of the pin is vertically connected to the outer wall of the linkage ring.

7. An aircraft engine, characterized in that, It includes a casing and an adjustable stator blade adjustment mechanism as described in any one of claims 1-6, wherein the second guide member is disposed on the outer wall surface of the casing.

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