Gas turbine aircraft engine guide vane length adjustment device and test method

Abstract

The application discloses a length adjusting device and a test method of a gas turbine aero-engine guide vane, and belongs to the technical field of variable cycle engines. The adjusting device comprises a driving wheel disc, an inner ring frame, an outer ring sealing frame, a guide vane, a transmission connecting rod and a sliding sealing sheet and the like. The driving wheel disc pulls the transmission connecting rod and the guide vane by rotating, so that the guide vane slides in the inner ring hollow hole and the outer ring hollow hole. The guide vane can realize length adjustment along the inner and outer ring radial directions, other degrees of freedom are self-locked by the structure itself, the minimum stroke and the maximum stroke of the guide vane are limited by the guide vane edge plate base and the inner and outer rings, and there is no interference and jamming in the working process of each part of the adjusting mechanism. The application adjusts the length of the guide vane, changes the turbine flow passage cross-sectional area, changes the gas flow velocity in the flow passage, further controls the rotating speed of the turbine rotor, and achieves the variable condition adjusting purpose.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of variable cycle engines, and particularly relates to a length adjusting device for a turbine guide vane of a gas turbine aero-engine and a test method. BACKGROUND

[0002] The working environment of an aero-engine is complex and changeable in actual work, and such working conditions require the aero-engine to have certain variable working condition adaptability. The variable working condition of an aero-engine mainly refers to the ability to adjust the working state with the change of working conditions when working at a non-design working point, so as to obtain higher working efficiency, and a variable cycle engine emerges as the times require.

[0003] A variable cycle engine is an engine that changes the thermodynamic cycle characteristics of the engine by changing the geometry, size or position of some components of the engine. A variable geometry turbine is one of the main components of a variable cycle engine. At present, most variable geometry turbines adjust the angle of turbine guide vanes to control the flow rate of the engine, so as to improve the acceleration and deceleration characteristics of the aero-engine group and improve the operating efficiency at a lower power state. Although the turbine with adjustable guide vane angle improves the adaptability of the aero-engine under variable working conditions, due to its special structure and working process, in order to rotate the guide vane, a certain gap must be left between the end and the bottom of the guide vane to prevent the guide vane end wall and the casing wall from being scraped or stuck. This structure produces some additional efficiency loss compared to the fixed geometry turbine. The size of the gap between the end and the bottom of the guide vane directly affects the degree of leakage loss, and the guide vane has a twist angle at each cross section, and the upper and lower end walls have an inclination angle. The expansion of the gap during the angle adjustment process will inevitably increase the loss.

[0004] In the turbine guide vane angle adjusting mechanism, the guide vane rotation will inevitably produce a gap, which will inevitably cause efficiency loss. If the guide vane is no longer rotating and can still adjust the turbine rotor speed, the efficiency loss caused by the gap leakage can be solved. Therefore, it is necessary to provide a new and effective turbine guide vane height adjusting mechanism to reduce the gap leakage loss and achieve the change of the gas flow rate in the flow passage, thereby controlling the speed of the turbine rotor, so as to optimize the working efficiency of the aero-engine under partial load. SUMMARY

[0005] The technical problem to be solved by the present application is to provide a guide vane length adjusting device and test method for a gas turbine aero-engine to solve the above problems of the prior art.

[0006] To achieve the above technical purposes, the technical scheme adopted by the present application is:

[0007] The guide vane length adjusting device for the gas turbine aero-engine comprises a driving wheel disc, an inner ring frame, an outer ring sealing frame, guide vanes, a transmission connecting rod and sliding sealing sheets, the driving wheel disc is installed on the inner side of the inner ring frame, the driving wheel disc can rotate around its own axis, a plurality of wheel disc positioning points are arranged in a ring shape around the center of the driving wheel disc, the inner ring frame is a ring frame, a plurality of inner ring hollow holes are arranged in an array on the outer circumferential surface of the inner ring frame, the guide vane comprises a guide blade, a rim plate and a base connected in sequence, one end of the transmission connecting rod is hingedly connected with the wheel disc positioning point, and the other end is hingedly connected with the base, the outer ring sealing frame is a ring frame, the inner ring frame and the outer ring sealing frame are coaxial with the driving wheel disc, a plurality of outer ring hollow holes are arranged in an array on the outer circumferential surface of the outer ring sealing frame, each guide vane corresponds to an inner ring hollow hole and an outer ring hollow hole, the base passes through the inner ring hollow hole and is in sliding fit with the inner ring hollow hole, the guide blade passes through the outer ring hollow hole and is in sliding fit with the outer ring hollow hole, the sliding sealing sheet is connected on the rim plates of adjacent two guide vanes, the sliding sealing sheet is located on the outer side of the inner ring frame, the sliding sealing sheet cannot pass through the inner ring hollow hole, the driving wheel disc pulls the transmission connecting rod and the guide vane by rotating, so that the guide vane slides in the inner ring hollow hole and the outer ring hollow hole, and the length of the guide blade extending out of the outer ring sealing frame is adjusted.

[0008] To optimize the technical scheme, the present application further adopts the following measures:

[0009] The driving wheel disc is provided with a wheel disc hollow cavity in the middle, and a ring-shaped boss is arranged on the upper surface of the driving wheel disc along the edge of the wheel disc hollow cavity, the wheel disc hollow cavity is used for penetrating a transmission shaft, the transmission shaft is in transmission connection with a motor, and the motor can drive the driving wheel disc to rotate.

[0010] The inner ring frame upper surface is provided with an inner ring frame cover, the driving wheel disc is located below the inner ring frame cover, the inner ring frame cover is provided with trapezoidal notches arranged in an array with the inner ring frame center as the center, each trapezoidal notch corresponds to a transmission connecting rod, and the trapezoidal notches are used to provide operation space for assembling the transmission connecting rod.

[0011] The outer ring sealing frame outer side is matched with a plurality of external sealing sheets, the shape of the outer ring hollow hole is adapted to the shape of the guide vane, the external sealing sheet is provided with a sealing sheet hole adapted to the shape of the guide vane, the guide vane sequentially passes through the outer ring hollow hole and the sealing sheet hole, and the external sealing sheet is used to seal the gap between the outer ring hollow hole and the guide vane.

[0012] The external sealing sheet is provided with a threaded hole, and the external sealing sheet is fixed to the outer side of the outer ring sealing frame by a bolt.

[0013] The base is provided with an assembly hole used to be connected with the transmission connecting rod, the flange plate is provided with bosses on the upper side and the lower side, the shapes of the upper end and the lower end of the inner ring hollow hole are adapted to the bosses, and the bosses are matched with the inner ring hollow hole to limit the left-right shaking of the flange plate.

[0014] The flange plate is provided with guide vane sealing grooves on the left side and the right side, and the sliding sealing sheet is simultaneously inserted into the guide vane sealing grooves of the adjacent two guide vanes to be positioned.

[0015] The sliding sealing sheet is provided with a plurality of transverse guide grooves, the guide vane sealing groove is provided with a sliding convexity adapted to the guide groove, the sliding convexity is matched with the guide groove to vertically position the sliding sealing sheet in the guide vane sealing groove when the sliding sealing sheet is inserted into the guide vane sealing groove, the sliding sealing sheet can slide horizontally in the guide vane sealing groove, and the width of the sliding sealing sheet is set as follows: the sliding sealing sheet does not separate from the guide vane sealing groove when the guide vane extends to the longest stroke; and the left and right ends of the sliding sealing sheet do not extrude the inner wall of the guide vane sealing groove when the guide vane retracts to the shortest stroke.

[0016] The outer side of the outer ring sealing frame is provided with a circle of engine outer cabs, cooling gas is provided for cooling between the outer ring sealing frame and the engine outer cab, the cooling gas is introduced from a compressor, and the compressor can pressurize the gas between the outer ring sealing frame and the engine outer cab.

[0017] The test method for adjusting the length of the guide vane of the gas turbine aero-engine, the specific method includes the following steps:

[0018] Step 1: modeling and assembling the driving wheel disc, the inner ring frame, the outer ring sealing frame, the guide vane, the transmission connecting rod and the sliding sealing sheet, adding a moving body and a motion pair to each structure module after completion;

[0019] Step 2: the driving wheel disc is used as the driving pair, the driving wheel disc and the transmission connecting rod concentric cylinder are set as the rotary pair, and the transmission connecting rod is assembled with the driving wheel disc to realize synchronous displacement;

[0020] Step 3: the transmission connecting rod and the base assembly hole concentric cylinder are set as the rotary pair, and the base is displaced synchronously with the transmission connecting rod;

[0021] Step 4: the guide vane is slidably connected with the outer ring sealing frame, so that the guide vane and the outer ring sealing frame are set as the sliding pair, and the outer ring sealing frame is set as the fixed constraint;

[0022] Step 5: the inner ring frame is constrained in the main shaft direction freedom, and the sliding sealing piece and the guide vane sealing groove are relatively slid, so that the sliding sealing piece and the guide vane sealing groove are set as the sliding pair, and the sliding sealing piece is displaced synchronously with the two connected edge plates;

[0023] Step 6: kinematics simulation is carried out on each structure module to obtain the motion animation and motion data of each structure module;

[0024] Step 7: the virtual test piece of all structure modules is modified into an entity, and the motion simulation is stopped when entity interference occurs, whether the overall structure is in line with the ideal motion, whether interference occurs between the virtual test pieces, and whether the working stroke range of the designed gas turbine aircraft engine guide vane length adjusting device is verified;

[0025] Step 8: the virtual test piece is analyzed to obtain the length change relationship curve of the driving wheel disc rotation angle and the guide vane extending out of the outer ring sealing frame;

[0026] Step 9: the driving wheel disc rotation angle and the length of the guide vane extending out of the outer ring sealing frame are obtained by analyzing and calculating the data table;

[0027] Step 10: whether the stroke of the gas turbine aircraft engine guide vane length adjusting device meets the design expectation is verified through the test data curve, and the angle and angular velocity of the driving wheel disc are set according to the fitting curve.

[0028] Compared with the prior art, the present application has the following beneficial effects:

[0029] 1、The present application adjusts the turbine guide vane extension length, changes the turbine flow passage cross-sectional area and the gas flow velocity in the flow passage, and then controls the rotation speed of the turbine rotor, thereby optimizing the working efficiency of the aircraft engine under partial load. Combined with the aircraft engine using advanced sensors and full-authorization digital electronic control system, the present application can realize task automatic planning and situation automatic sensing capability, realize adaptive adjustment, and achieve the best comprehensive performance;

[0030] 2、The present application guarantees that the parts reach the working stiffness, under the premise of reducing the mechanical structure in the turbine airflow channel, reducing the self-weight, avoiding blocking the airflow, and improving the operation efficiency of the aero-engine;

[0031] 3、The scheme provided by the present application has strong flexibility, good fixing effect and universality, and can be adapted by slightly adjusting the size of the length adjusting mechanism of the gas turbine aero-engine guider vane. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 is the principle diagram of the length adjusting mechanism of the gas turbine aero-engine guider vane of the present application;

[0033] Figure 2 is the structural schematic diagram of the driving wheel disc of the present application;

[0034] Figure 3 is the structural schematic diagram of the inner ring frame of the present application;

[0035] Figure 4 is the structural schematic diagram of the outer ring sealing frame of the present application;

[0036] Figure 5 is the structural schematic diagram of the guider vane of the present application;

[0037] Figure 6 is the structural schematic diagram of the transmission connecting rod of the present application;

[0038] Figure 7 is the structural schematic diagram of the sliding sealing sheet of the present application;

[0039] Figure 8 is the assembly drawing of the length adjusting mechanism of the gas turbine aero-engine guider vane of the present application;

[0040] Figure 9 is the structural schematic diagram of the external sealing sheet of the present application;

[0041] Figure 10 is the sealing groove on the external sealing sheet of the present application;

[0042] Figure 11 is the assembly drawing of the external sealing sheet of the present application;

[0043] Figure 12 is the structural schematic diagram of the sealing groove in the staggered sealing structure of the present application;

[0044] Figure 13 is the installation schematic diagram of the outer casing of the present application;

[0045] Figure 14 is the stroke schematic diagram of the motion simulation part of the present application;

[0046] Figure 15 is the driving wheel disc rotation angle and guide vane length change relationship curve of the present application;

[0047] Figure 16 is the vane adjustment length and wheel disc rotation angle relationship fitting curve of the present application.

[0048] The marks in the drawings are: driving wheel disc 1, wheel disc positioning point 11, annular boss 12, inner ring frame 2, inner ring frame cover 22, inner ring frame cover 22, trapezoidal notch 23, outer ring sealing frame 3, outer ring hollow hole 31, guider vane 4, guide vane 41, edge plate 42, base 43, boss 44, guide vane sealing groove 45, transmission connecting rod 5, sliding sealing piece 6, guide groove 61, external sealing piece 7, sealing piece hole 71, engine outer casing 8. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical scheme and advantages of the present application more clear and understandable, the present application is described and explained below in combination with the drawings and examples. It should be understood that the specific examples described herein are only used to explain the present application and not to limit the present application. Based on the examples provided in the present application, all other examples obtained by those of ordinary skill in the art without making creative efforts fall within the scope of the present application.

[0050] Obviously, the drawings described below are only some examples or embodiments of the present application, and for those of ordinary skill in the art, the present application can also be applied to other similar scenarios without making creative efforts based on these drawings. In addition, it can be understood that although the efforts made in this development process can be complex and lengthy, for those of ordinary skill in the art related to the content disclosed in the present application, some design, manufacture or production changes based on the technical content disclosed in the present application are only routine technical means and should not be understood as insufficient disclosure of the present application.

[0051] In the present application, "example" means that the specific features, structures or characteristics described in combination with the example can be included in at least one embodiment of the present application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it independent or alternative to other embodiments. Those of ordinary skill in the art explicitly and implicitly understand that the embodiments described in the present application can be combined with other embodiments without conflict.

[0052] As shown in Figure 8 The gas turbine aircraft engine guider vane length adjustment device includes a driving wheel disc 1, an inner ring frame 2, an outer ring sealing frame 3, a guider vane 4, a transmission connecting rod 5 and a sliding sealing piece 6.

[0053] As shown in Figure 2 the outer circle radius of the driving wheel disc 1 is 150 mm, and the hollowed radius is 106 mm. The middle part is an annular boss 12 with a radius of 106 mm-116 mm, which can increase the stability of the driving wheel disc 1 during rotation. The outermost part is a wheel positioning point 11 with a radius of 4 mm.

[0054] As shown in Figure 3 the outermost radius of the inner ring frame 2 is 220 mm. The radius of 106 mm-215 mm is subjected to cutting treatment, and the cutting thickness needs to be greater than the sum of the thickness of the transmission connecting rod 5 itself and the thickness of the assembled pin end, so as to ensure that the transmission connecting rod 5 can still rotate without jamming between the inner ring frame 2 and the driving wheel disc 1 after assembly. Subsequently, the hollowing weight reduction treatment is carried out, and each trapezoidal notch 23 corresponds to an initial assembly position of the transmission connecting rod 5, and a matching space is left for the assembly required tooling. The arrayed inner ring hollow holes 21 on the outermost cylindrical surface are matched with the cuboid bosses 44 on both sides of the base 43, which allows the guide vane 4 to slide relative to the inner ring frame 2 and restricts the rotation of the guide vane 4, thereby restricting the freedom of the guide vane.

[0055] As shown in Figure 4 the outer ring sealing frame 3 is processed by a boss with a radius of 315 mm-320 mm. The installation edge is designed on the inlet side to realize fixed constraint. The hollow structure on the outer cylindrical surface, i.e. the outer ring hollow hole 31, is completely matched with the shape of the guide vane 41, and the outer ring hollow hole 31 is assisted by the outer sealing sheet 7 added outside the outer ring hollow hole 31 to realize the auxiliary sealing of the outer ring hollow hole 31. This design not only limits the relative rotation of the guide vane 41, but also transmits the constraint torque through the guide vane 41 to limit the rotation of the inner ring frame 2 around the shaft, and the guide vane 41 can adjust the length along the outer ring sealing frame 3 in the radial direction.

[0056] As shown in Figure 5As shown, the length of the guide vane 4 is 90 mm, which is determined by considering the matching stroke range of the guide vane sealing groove 45 and the sliding sealing piece 6, the height adjustment stroke range of the guide vane 4 itself, and the gas sealing factor. The edge of the base 43 is designed as a circular arc transition structure. The radius of the opening at the bottom of the base 43 is 4 mm, which is the assembly hole of the base 43 and the transmission connecting rod 5. The opening position is close to the center of the driving wheel disc 1 to optimize the driving torque of the connecting rod, and it is easier to drive the guide vane 4. The bosses 44 on both sides of the base 43 form a structural self-locking with the inner ring frame 2, which limits the excessive degrees of freedom of the guide vane 4 and reduces the disturbance caused by high-speed airflow. The axial hole provided on the rim plate 42 is a threaded hole with a radius of 2 mm, which is used for adding a fairing. The sliding sealing piece 6 with a positioning guide groove is installed in the guide vane sealing groove 45. When the length of the guide vane 4 is adjusted, the gap between the adjacent rim plates 42 increases, and the gap is filled by the sliding of the sliding sealing piece 6 in the guide vane sealing groove 45 on both sides of the adjacent guide vane 4, thereby continuing to maintain the sealing of the main flow passage. The staggered sealing structure is integrated in the compact guide vane 4, and the included angle between the adjacent guide vanes 4 is 10°. Therefore, the included angle between the guide vane sealing groove 45 and the central axis of the guide vane 4 is 95°, which ensures that the guide vane sealing groove 45 at the adjacent rim plate 42 remains parallel when the length of the guide vane 4 is adjusted.

[0057] As shown in Figure 6 , the total length of the transmission connecting rod 5 is 75 mm, which is the optimal setting considering the stiffness of the part, the adjustment range, and the interference. The assembly hole with a radius of 4 mm at both ends of the connecting rod is connected with the outer circular wheel disc positioning point 11 of the driving wheel disc 1 by using a pin, and the distance from the center of the connecting rod opening to the boundary circle of the connecting rod is 7.5 mm. This design can leave a gap of 2.5 mm after the transmission connecting rod 5 and the guide vane 4 are assembled, so as to prevent friction between the transmission connecting rod 5 and the lower end surface of the boss 44. The overall thickness of the transmission connecting rod 5 is 9 mm, and after assembly, the transmission connecting rod 5 and the inner ring frame 2 leave a gap of 6 mm, so that the transmission connecting rod 5 does not interfere with the inner ring frame 2 after the pin is installed.

[0058] As shown in Figure 7 , the width of the sliding sealing piece 6 is 20 mm, the length is 40 mm, the guide groove 61 fits the guide vane sealing groove 45, and the thickness is 4.9 mm, which is slightly smaller than the gap height of 5 mm of the guide vane sealing groove 45, so as to reduce the friction resistance and reserve the tolerance. The length of the guide groove 61 cut by the sliding sealing piece 6 is 17 mm, and the center distance is 13 mm. The cutting part is not penetrated, so as to play a sealing role.

[0059] As shown in Figure 9As shown, the seal piece hole 71 on the external seal piece 7 is the same as the guide vane 41 profile, which allows the guide vane 41 to pass through and slide. The external seal piece 7 has two mounting and positioning holes, which can be assembled with the hole positions on the outer ring of the outer ring seal frame 3 through a pin, and cooperates with the guide vane surface of the outer ring seal frame 3 to form a seal. One guide vane corresponds to one external seal piece 7, which is convenient for replacement during maintenance. According to the actual sealing condition, the thickness of the seal piece can be increased to enhance the sealing effect.

[0060] As shown in Figure 10 , four layers of sealing groove structures are machined in the slot on the external seal piece 7, which realizes sealing by forming a slit-cavity with the guide vane surface, and can further rely on the cooling airflow between the outer ring seal frame 3 and the casing to assist in sealing.

[0061] As shown in Figure 11 , the external seal piece 7 is installed as a secondary sealing measure on the outer ring of the outer ring seal frame 3.

[0062] As shown in Figure 12 , a labyrinth seal structure is designed between the sliding seal piece 6 and the guide vane sealing groove 45 to improve the sealing effect. In the actual working process, the sliding seal piece 6 and the sealing groove will also be affected by the pressure difference between the inner and outer cavities, and will be pressed tightly with each other to form a seal.

[0063] As shown in Figure 13 , the engine outer casing 8 is directly assembled with the outer ring seal frame 3 of the adjusting mechanism, and the secondary seal piece, i.e. the external seal piece 7, is located in the interlayer of the two.

[0064] The assembly of the improved guide vane length adjusting device of the gas turbine aero-engine includes the following steps:

[0065] Step 1: The 36 disc positioning points 11 on the circumference of the drive wheel disc 1 are connected with one end of the transmission connecting rod 5 through a standard M8 pin.

[0066] Step 2: The drive wheel disc 1 is attached to the concentric cylindrical surface on the side close to the central axis of the inner ring frame 2.

[0067] Step 3: The 36 guide vanes 4 are radially embedded along the outer ring seal frame 3. In order to facilitate assembly, the base 43 of the guide vane 4 can be attached to the inner cylindrical surface of the outer ring seal frame 3.

[0068] Step 4: After inserting the guide vane 4, the outer ring seal frame 3 is moved along its own axial direction to align the guide vane 4 with the inner ring hollow hole 21 of the inner ring frame 2.

[0069] Step 5: The length of the guide vane 4 is shortened, and the base 43 of the guide vane 4 is connected with the transmission connecting rod 5 through a standard M8 pin.

[0070] Step 6: Adjust the rotation angle of the drive wheel 1, link the guide vane 4 to the target length, and install the sliding seal 6 for auxiliary constraint and sealing. The sliding seal 6 is connected to the guide vane 4 using a semi-threaded M4 bolt.

[0071] A virtual test method for a gas turbine aero-engine guide vane length adjustment device includes the following steps:

[0072] Step 1: After modeling and assembling the drive wheel 1, inner ring frame 2, outer ring sealing frame 3, guide vane 4, transmission connecting rod 5, and sliding sealing plate 6, add moving bodies and kinematic pairs to each structural module.

[0073] Step 2: Using the drive wheel 1 as the drive pair, the drive wheel 1 and the transmission link 5 are set as a rotating pair, and the transmission link 5 moves synchronously with the assembly point of the drive wheel 1.

[0074] Step 3: The transmission link 5 and the base 43 are assembled with concentric cylinders to form a rotating pair, and the base 43 moves synchronously with the transmission link 5;

[0075] Step 4: The guide vane 41 and the outer ring sealing frame 3 are in sliding fit. Therefore, the guide vane 41 and the outer ring sealing frame 3 are set as a sliding pair, and the outer ring sealing frame 3 is set as a fixed constraint.

[0076] Step 5: Constrain the inner ring frame 2 along the main axis direction. The sliding sealing plate 6 and the guide vane sealing groove 45 are relatively sliding. Therefore, the sliding sealing plate 6 and the guide vane sealing groove 45 are set as a sliding pair. The sliding sealing plate 6 moves synchronously with the two connected flanges 42.

[0077] Step 6: After the initial simulation, import the adjustment mechanism model and the set kinematic pair files into professional kinematic simulation software for more detailed motion simulation and obtain demonstration animations, such as... Figure 14 As shown and key data for each moving body, as follows Figure 15 As shown;

[0078] Step 7: Modify all virtual test pieces to solids, and set the motion simulation to stop when solid interference occurs. Verify whether the overall structure conforms to ideal motion and whether interference occurs between the virtual test pieces. Verify the working stroke range of the designed gas turbine aero-engine guide vane length adjustment device;

[0079] Step 8: The feasibility of the design is verified by using professional kinematics simulation software. According to the data exported by the simulation, it can be seen that the speed and acceleration change between the control mechanism and the controlled guide vane is smooth, and there is no mutation, and there is no interference between the structural entities in the movement process, which indicates that the length adjusting mechanism design is reliable and stable. According to the calculation, the maximum area adjustment of the blade length adjustment can be achieved 20%, which can meet the complex actuation of the new generation of aero-engine.

[0080] Step 9: After the simulation data is exported from the software, it is processed several times to obtain the control relationship and fitting equation between the wheel disc rotation angle and the guide vane adjustment length, wherein the fitting equation is:

[0081]

[0082] Wherein y is the guide vane adjustment length, unit: mm; x is the wheel disc rotation angle, unit: deg. Under this control relationship, the adjustment length of the blade can be determined by the rotation angle of the wheel disc as shown in Figure 16

[0083] Step 10: Whether the stroke of the gas turbine aero-engine guide vane blade length adjustment device meets the design expectation is verified by the test data curve, and the angle and angular velocity of the driving wheel disc 1 are set according to the fitting curve.

[0084] The above is only the preferred embodiment of the present application, and the protection scope of the present application is not limited to the above-mentioned embodiments. Any technical solutions falling within the concept of the present application shall fall within the protection scope of the present application. It should be noted that for ordinary skilled persons in the art, some improvements and decorations without departing from the principles of the present application shall be considered as the protection scope of the present application.​

Claims

1. A gas turbine aircraft engine guide vane length adjustment device characterized by, The utility model provides a kind of drive wheel disc (1), inner ring frame (2), outer ring sealing frame (3), guider vane (4), transmission connecting rod (5) and sliding seal sheet (6), the drive wheel disc (1) is installed in the inside of inner ring frame (2), drive wheel disc (1) can rotate around its own axis, drive wheel disc (1) is provided with a plurality of disc positioning points (11) in the form of annular arrangement with drive wheel disc (1) axis as center point, the inner ring frame (2) is annular frame, and the outer circumferential surface of inner ring frame (2) is provided with a plurality of arrayed inner ring hollow holes (21), the guider vane (4) includes guide vane (41), rim plate (42) and base (43) connected in sequence, one end of the transmission connecting rod (5) is hingedly connected with disc positioning point (11), and the other end is hingedly connected with base (43), the outer ring sealing frame (3) is annular frame, and inner ring frame (2), outer ring sealing frame (3) are coaxial with drive wheel disc (1), the outer circumferential surface of outer ring sealing frame (3) is provided with a plurality of arrayed outer ring hollow holes (31), each guider vane (4) corresponds an inner ring hollow hole (21) and an outer ring hollow hole (31), the base (43) passes through inner ring hollow hole (21) and is slidably fitted with inner ring hollow hole (21), the guide vane (41) passes through outer ring hollow hole (31) and is slidably fitted with outer ring hollow hole (31), the sliding seal sheet (6) is connected on the rim plate (42) of adjacent two guider vanes (4), and sliding seal sheet (6) is located on the outside of inner ring frame (2), the sliding seal sheet (6) cannot pass through inner ring hollow hole (21), the drive wheel disc (1) pulls transmission connecting rod (5) and guider vane (4) by rotating, so that guider vane (4) slides in inner ring hollow hole (21) and outer ring hollow hole (31), to further adjust the length that guide vane (41) extends out of outer ring sealing frame (3).

2. The gas turbine aircraft engine guide vane length adjustment device according to Claim 1, wherein, The middle part of the drive wheel disc (1) is provided with a wheel disc hollow cavity, and the upper surface of the drive wheel disc (1) is provided with an annular boss (12) along the edge of the wheel disc hollow cavity, the wheel disc hollow cavity is used for penetrating a transmission shaft, the transmission shaft is in transmission connection with a motor, and the motor can drive the drive wheel disc (1) to rotate.

3. The gas turbine aircraft engine guide vane length adjustment device according to Claim 2, wherein, The upper surface of the inner ring frame (2) is provided with an inner ring frame cover (22), the drive wheel disc (1) is located below the inner ring frame cover (22), the inner ring frame cover (22) is provided with a plurality of arrayed trapezoidal notches (23) with the axis of the inner ring frame (2) as the center, each trapezoidal notch (23) corresponds a transmission connecting rod (5), and the trapezoidal notch (23) is used for providing operating space for assembling the transmission connecting rod (5).

4. The gas turbine aircraft engine guide vane length adjustment device according to Claim 3, wherein, The outer ring sealing frame (3) is matched with a plurality of external sealing sheets (7) on the outer side, the shape of the outer ring hollow hole (31) is adapted to the shape of the guide vane (41), the external sealing sheet (7) is provided with a sealing sheet hole (71) adapted to the shape of the guide vane (41), the guide vane (41) sequentially passes through the outer ring hollow hole (31) and the sealing sheet hole (71), and the external sealing sheet (7) is used for sealing the gap between the outer ring hollow hole (31) and the guide vane (41).

5. The gas turbine aircraft engine guide vane length adjustment device according to Claim 4, wherein, The external sealing sheet (7) is provided with a threaded hole, and the external sealing sheet (7) is fixed on the outer side of the outer ring sealing frame (3) through a bolt.

6. The gas turbine aircraft engine guide vane length adjustment device according to Claim 3, wherein, The base (43) is provided with an assembly hole for being connected with the transmission connecting rod (5), the flange plate (42) is provided with a boss (44) on the upper side and the lower side, the upper end and the lower end of the inner ring hollow hole (21) are adapted to the boss (44), and the boss (44) is matched with the inner ring hollow hole (21) to limit the left-right shaking of the flange plate (42).

7. The gas turbine aircraft engine guide vane length adjustment device according to Claim 6, wherein, The flange plate (42) is provided with a guide vane sealing groove (45) on the left side and the right side, and the sliding sealing sheet (6) is simultaneously inserted into the guide vane sealing groove (45) of the adjacent two guide vanes (4) for positioning.

8. The gas turbine aircraft engine guide vane length adjustment device according to Claim 7, wherein, The sliding sealing sheet (6) is provided with a plurality of transverse guide grooves (61), the guide vane sealing groove (45) is provided with a sliding convexity adapted to the guide groove (61), when the sliding sealing sheet (6) is inserted into the guide vane sealing groove (45), the sliding convexity is matched with the guide groove (61) to vertically limit the sliding sealing sheet (6) in the guide vane sealing groove (45), the sliding sealing sheet (6) can slide horizontally in the guide vane sealing groove (45), and the width of the sliding sealing sheet (6) is set as follows: when the guide vane (4) extends to the longest stroke, the sliding sealing sheet (6) does not separate from the guide vane sealing groove (45); when the guide vane (4) retracts to the shortest stroke, the left and right ends of the sliding sealing sheet (6) do not extrude the inner wall of the guide vane sealing groove (45).

9. The gas turbine aircraft engine guide vane length adjustment device according to Claim 1, wherein, The outer ring sealing frame (3) is provided with an engine outer casing (8) on the outer side, cooling gas is provided for cooling between the outer ring sealing frame (3) and the engine outer casing (8), and the cooling gas is introduced from a compressor, and the compressor can pressurize the gas between the outer ring sealing frame (3) and the engine outer casing (8).

10. A method of testing the length adjustment of a gas turbine aeroengine guide vane, characterised in that, The specific method comprises the following steps: Step 1: modeling and assembling the driving wheel disc (1), the inner ring frame (2), the outer ring sealing frame (3), the guide vane (4), the transmission connecting rod (5) and the sliding sealing sheet (6), and adding a moving body and a moving pair to each structure module; Step 2: taking the driving wheel disc (1) as a driving pair, and setting the driving wheel disc (1) and the transmission connecting rod (5) as concentric cylinders as a rotating pair, and the transmission connecting rod (5) is displaced synchronously with the driving wheel disc (1) at the assembly position; Step 3: The transmission connecting rod (5) and the base (43) are assembled into a concentric cylinder, which is set as a rotary pair, and the base (43) synchronously displaces with the transmission connecting rod (5); Step 4: The guide vane (41) and the outer ring sealing frame (3) are in sliding fit, so the guide vane (41) and the outer ring sealing frame (3) are set as a sliding pair, and the outer ring sealing frame (3) is set as a fixed constraint; Step 5: The inner ring frame (2) is constrained in the direction of the main shaft, and the sliding sealing piece (6) and the guide vane sealing groove (45) are in relative sliding, so the sliding sealing piece (6) and the guide vane sealing groove (45) are set as a sliding pair, and the sliding sealing piece (6) synchronously displaces with the two connected edge plates (42); Step 6: Kinematics simulation is performed on each structure module to obtain the motion animation and data of each structure module; Step 7: The virtual test pieces of all structure modules are modified into entities, and the motion simulation is stopped when entity interference occurs, to verify whether the overall structure fits the ideal motion, whether interference occurs between each virtual test piece, and whether the designed gas turbine aircraft engine guide vane length adjustment device working stroke range is reasonable; Step 8: The virtual test pieces are analyzed to obtain the relationship curve between the driving wheel disc (1) rotation angle and the guide vane (41) length extending out of the outer ring sealing frame (3); Step 9: The data table is analyzed and calculated to obtain the fitting curve function of the driving wheel disc (1) rotation angle and the guide vane (41) length extending out of the outer ring sealing frame (3); Step 10: The test data curve is used to verify whether the stroke of the gas turbine aircraft engine guide vane length adjustment device meets the design expectation, and the angle and angular velocity of the driving wheel disc (1) are set according to the fitting curve.

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