Gas turbine aero-engine guider blade length adjusting device and test method

Abstract

The invention discloses a gas turbine aero-engine guider blade length adjusting device and a test method, 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, guider blades, a transmission connecting rod, a sliding sealing piece and other structures, and the driving wheel disc rotates to pull the transmission connecting rod and the guider blades, so that the guider blades slide in the inner ring hollowed-out holes and the outer ring hollowed-out holes. Length adjustment of the guider blade in the radius direction of the inner ring and the outer ring can be achieved, self-locking of other degrees of freedom is completed through the structure, the minimum stroke and the maximum stroke of the guider blade are limited through cooperation of the guider blade margin plate base and the inner ring and the outer ring, and interference clamping stagnation does not exist in the working process of all parts of the adjusting mechanism. The section area of the turbine runner is changed by adjusting the extending length of the guider blade, so that the gas flow rate in the runner is changed, the rotating speed of the turbine rotor is controlled, and the purpose of variable working condition adjustment is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of variable cycle engines, and in particular relates to a device for adjusting the length of a guide vane of a gas turbine aircraft engine and a test method thereof. Background Art

[0002] The actual working environment of aircraft engines is complex and changeable. Such working conditions require aircraft engines to have a certain ability to adapt to variable working conditions. The variable working conditions of aircraft engines mainly refer to the ability to adjust the working state as the working conditions change when working at non-design working points, so as to obtain higher working efficiency. Variable cycle engines came into being.

[0003] A variable cycle engine is an engine that changes its thermodynamic cycle characteristics by changing the geometry, size or position of some engine components. The variable geometry turbine is one of the most important components of a variable cycle engine. Most current variable geometry turbines control the engine flow by adjusting the angle of the turbine guide vane, thereby improving the acceleration and deceleration characteristics of the aircraft engine group and improving the operating efficiency at lower power states. Although the turbine with adjustable guide vane angle improves the adaptability of the aircraft 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 end wall of the guide vane from scratching or getting stuck with the casing wall. This structure produces some additional efficiency losses 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. In addition, each section of the guide vane is provided with a torsion angle, and the upper and lower end walls are provided with an inclination angle. The expansion of the gap during the angle adjustment process is bound to increase the loss.

[0004] In the turbine guide vane angle adjustment mechanism, the rotation of the guide vane will inevitably produce a gap, which will inevitably lead to efficiency loss. If the guide vane can still adjust the turbine rotor speed without rotating, the efficiency loss caused by gap leakage can be solved. Therefore, it is necessary to provide a new and effective turbine guide vane height adjustment mechanism to reduce gap leakage loss and change the gas flow rate in the flow channel, thereby controlling the speed of the turbine rotor, thereby optimizing the working efficiency of the aircraft engine at partial load. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a gas turbine aircraft engine guide vane length adjustment device and test method in view of the deficiencies of the above-mentioned prior art. The guide vane of the present invention can realize the length adjustment along the radial direction of the inner and outer rings, and the other degrees of freedom are self-locking by the structure itself. The minimum stroke and maximum stroke of the guide vane are limited by the cooperation of the guide vane edge plate base and the inner and outer rings, and there is no interference and jamming during the operation of the various components of the adjustment mechanism. The present invention changes the cross-sectional area of ​​the turbine flow channel by adjusting the extension length of the guide vane, thereby changing the gas flow rate in the flow channel, and then controlling the rotation speed of the turbine rotor to achieve the purpose of variable working condition regulation.

[0006] In order to achieve the above technical purpose, the technical solution adopted by the present invention is:

[0007] The guide vane length adjustment device of a gas turbine aircraft engine 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, wherein 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 arranged in a ring shape with the driving wheel disc axis as the center point are arranged on the driving wheel disc, the inner ring frame is an annular frame, a plurality of inner ring hollow holes arranged in an array are arranged on the outer peripheral surface of the inner ring frame, the guide vane comprises a guide vane, an edge plate and a base connected in sequence, one end of the transmission connecting rod is hingedly connected to the wheel disc positioning point, and the other end is hingedly connected to the base, the outer ring sealing frame is an annular frame, the inner ring frame, the outer ring sealing frame and the guide vane are hingedly connected to the wheel disc positioning point, and the other end is hingedly connected to the base, the outer ring sealing frame is an annular frame, the inner ring frame, the outer ring sealing frame and the guide vane are hingedly connected to the wheel disc positioning point, and the outer ring sealing frame and the guide vane are hingedly connected to the base, and the inner ring frame and the outer ring sealing frame are hingedly connected to the wheel disc positioning point ... The ring sealing frames are all coaxial with the driving wheel disc, and the outer peripheral surface of the outer ring sealing frame is provided with a plurality of outer ring hollow holes arranged in an array, and 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 slides with the inner ring hollow hole, the guide vane passes through the outer ring hollow hole and slides with the outer ring hollow hole, the sliding sealing sheet is connected to the edge plate of two adjacent guide vanes, the sliding sealing sheet is located on the outside of the inner ring frame, and the sliding sealing sheet cannot pass through the inner ring hollow hole, and the driving wheel disc rotates to pull the transmission connecting rod and the guide vane, so that the guide vane slides in the inner ring hollow hole and the outer ring hollow hole, thereby adjusting the length of the guide vane extending out of the outer ring sealing frame.

[0008] To optimize the technical solution, the present invention further adopts the following measures:

[0009] The above-mentioned driving wheel disc is provided with a wheel disc hollow cavity in the middle part, and an annular boss is provided 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 to penetrate the transmission shaft, and the transmission shaft is connected to the motor transmission, and the motor can drive the driving wheel disc to rotate.

[0010] An inner ring frame cover is provided on the upper surface of the inner ring frame, and the driving wheel is located below the inner ring frame cover. The inner ring frame cover is provided with trapezoidal slots arranged in an array with the axis of the inner ring frame as the center. Each trapezoidal slot corresponds to a transmission connecting rod, and the trapezoidal slot is used to provide an operating space for assembling the transmission connecting rod.

[0011] The outer side surface of the outer ring sealing frame is equipped 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 sealing sheet holes adapted to the shape of the guide vane. The guide vane passes through the outer ring hollow hole and the sealing sheet hole in sequence. The external sealing sheet is used to seal the gap between the outer ring hollow hole and the guide vane.

[0012] The above-mentioned external sealing sheet is provided with threaded holes, and the external sealing sheet is fixed to the outer side surface of the outer ring sealing frame by bolts.

[0013] The above-mentioned base is provided with an assembly hole for connecting with the transmission connecting rod, and bosses are provided on the upper and lower sides of the edge plate. The shapes of the upper and lower ends of the inner ring hollow hole are adapted to the bosses, and the bosses cooperate with the inner ring hollow hole to limit the left and right shaking of the edge plate.

[0014] The left and right sides of the above-mentioned edge plate are both provided with guide vane sealing grooves, and the sliding sealing sheet is simultaneously inserted into the guide vane sealing grooves of two adjacent guide vanes for positioning.

[0015] The above-mentioned sliding sealing sheet is provided with a plurality of transverse guide grooves, and the guide vane sealing groove is provided with a sliding protrusion adapted to the guide groove. When the sliding sealing sheet is inserted into the guide vane sealing groove, the sliding protrusion cooperates with the guide groove to vertically limit the sliding sealing sheet in the guide vane sealing groove, and the sliding sealing sheet can slide transversely in the guide vane sealing groove. The width of the sliding sealing sheet is set as follows: when the guide vane is extended to the longest stroke, the sliding sealing sheet does not separate from the guide vane sealing groove; when the guide vane is retracted to the shortest stroke, the left and right ends of the sliding sealing sheet do not squeeze the inner wall of the guide vane sealing groove.

[0016] A circle of engine outer casing is arranged outside the above-mentioned outer ring sealing frame, and cooling air is passed between the outer ring sealing frame and the engine outer casing to provide cooling. The cooling air is drawn from the compressor, and the compressor can pressurize the gas between the outer ring sealing frame and the engine outer casing.

[0017] The test method for adjusting the length of the guide vane of a gas turbine aircraft engine uses the above-mentioned gas turbine aircraft engine guide vane length adjustment device, and the specific method includes the following steps:

[0018] Step 1: After the drive wheel, inner ring frame, outer ring seal frame, guide vane, transmission connecting rod and sliding seal are modeled and assembled, add kinematic bodies and kinematic pairs to each structural module;

[0019] Step 2: With the driving wheel disc as the driving pair, the driving wheel disc and the concentric cylinder of the transmission connecting rod are set as a revolute pair, and the transmission connecting rod moves synchronously with the assembly position of the driving wheel disc;

[0020] Step 3: The transmission connecting rod and the concentric cylinder of the base assembly hole are set as a revolute pair, and the base moves synchronously with the transmission connecting rod;

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

[0022] Step 5: Constrain the freedom of the inner ring frame along the main axis direction. The sliding seal sheet and the guide vane sealing groove slide relative to each other. Therefore, the sliding seal sheet and the guide vane sealing groove are set as a sliding pair. The sliding seal sheet moves synchronously with the two connected edge plates.

[0023] Step 6: Perform kinematic simulation on each structural module to obtain motion animation and motion data of each structural module;

[0024] Step 7: Modify the virtual test pieces of all structural modules into entities, and set the motion simulation to stop when entity interference occurs, verify whether the overall structure fits the ideal motion, whether interference occurs between the virtual test pieces, and verify the working range of the designed gas turbine aircraft engine guide vane length adjustment device;

[0025] Step 8: Analyze the virtual test piece to obtain a curve showing the relationship between the driving wheel angle and the length of the guide vane extending out of the outer ring sealing frame;

[0026] Step 9: Analyze and calculate through the data table to obtain the fitting curve function of the driving wheel rotation angle and the length of the guide vane extending out of the outer ring sealing frame;

[0027] Step 10: Verify whether the stroke of the gas turbine aircraft engine guide vane length adjustment device meets the design expectations through the test data curve, and set the angle and angular velocity of the drive wheel according to the fitting curve.

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

[0029] 1. The present invention adjusts the extension length of the turbine guide vane, changes the cross-sectional area of ​​the turbine flow channel and the gas flow rate in the flow channel, and then controls the speed of the turbine rotor, thereby optimizing the working efficiency of the aircraft engine at partial load. In conjunction with aircraft engines that use advanced sensors and full-authority digital electronic control systems, it can achieve automatic task planning and situational automatic perception capabilities, realize adaptive adjustment, and achieve optimal comprehensive performance;

[0030] 2. The present invention minimizes the mechanical structure in the turbine airflow channel while ensuring that the components reach the working rigidity, reduces the dead weight while avoiding blocking the airflow, and improves the operating efficiency of the aircraft engine;

[0031] 3. The solution proposed by the present invention is highly flexible, has a good fixing effect and is universal. It can adapt to different sizes of aircraft engine main shafts and casings by fine-tuning the size of the gas turbine aircraft engine guide vane length adjustment mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the length adjustment mechanism of the guide vane of the gas turbine aircraft engine of the present invention;

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

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

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

[0036] Figure 5 It is a schematic diagram of the structure of the guide blade of the present invention;

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

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

[0039] Figure 8 It is an assembly diagram of the gas turbine aircraft engine guide vane length adjustment mechanism of the present invention;

[0040] Fig. 9 It is a structural schematic diagram of the external sealing sheet of the present invention;

[0041] Fig.10 It is a sealing groove on the external sealing sheet of the present invention;

[0042] Fig.11 This is an assembly diagram of the external sealing sheet of the present invention;

[0043] Fig.12 It is a structural schematic diagram of the sealing groove in the staggered sealing structure of the present invention;

[0044] Fig.13 It is a schematic diagram of the installation of the outer casing of the present invention;

[0045] Fig.14 It is a schematic diagram of the motion simulation part of the present invention;

[0046] Fig.15 is a curve showing the relationship between the rotation angle of the driving wheel and the length of the guide vane of the present invention;

[0047] Fig.16 It is a fitting curve of the relationship between the blade adjustment length and the wheel rotation angle of the present invention.

[0048] The markings in the accompanying drawings are: driving wheel 1, wheel positioning point 11, annular boss 12, inner ring frame 2, inner ring hollow hole 21, inner ring frame cover 22, trapezoidal notch 23, outer ring sealing frame 3, outer ring hollow hole 31, guide vane 4, guide vane 41, edge plate 42, base 43, boss 44, guide vane sealing groove 45, transmission connecting rod 5, sliding sealing plate 6, guide groove 61, external sealing plate 7, sealing plate hole 71, engine outer casing 8. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solutions and advantages of the present application clearer, the present application is described and illustrated below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application. Based on the embodiments provided in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present application.

[0050] Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. In addition, it can also be understood that although the efforts made in this development process may be complicated and lengthy, for ordinary technicians in this field related to the content disclosed in this application, some changes in design, manufacturing or production based on the technical content disclosed in this application are just conventional technical means, and should not be understood as insufficient content disclosed in this application.

[0051] Reference to "embodiments" in this application means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those of ordinary skill in the art that the embodiments described in this application may be combined with other embodiments without conflict.

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

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

[0054] like Figure 3 As shown, the outermost radius of the inner ring frame 2 is 220mm. Cutting is performed at the radius of 106mm-215mm, and the cutting thickness here needs to be greater than the sum of the thickness of the transmission connecting rod 5 itself and the thickness of the end of the assembly pin, so as to ensure that after the inner ring frame 2 and the driving wheel 1 are assembled, the transmission connecting rod 5 can still rotate between the two without jamming. Subsequently, hollowing and weight reduction treatment is performed, and each trapezoidal notch 23 corresponds to an initial assembly position of a transmission connecting rod 5, and a matching space is reserved for the tooling required for assembly. The inner ring hollow holes 21 arranged in an array on the outermost cylindrical surface cooperate with the rectangular bosses 44 on both sides of the base 43. This structural design allows the guide vane 4 to slide relative to the inner ring frame 2 and limit the rotation of the guide vane 4, thereby constraining the freedom of the guide vane.

[0055] like Figure 4 As shown, the outer ring sealing frame 3 is processed by a boss with a radius of 315mm-320mm. A mounting edge is designed on the air intake side to achieve fixed constraint. The hollow structure designed on the outer cylindrical surface, that is, the outer ring hollow hole 31 and the guide vane 41 are completely in shape. After adding an external sealing sheet 7 to the outside of the outer ring hollow hole 31, the auxiliary sealing of the outer ring hollow hole 31 is achieved. 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 axis, and the guide vane 41 can adjust the length radially along the outer ring sealing frame 3.

[0056] like Figure 5As shown, the length of the guide vane 4 is 90 mm. This data comprehensively considers the travel range of the guide vane sealing groove 45 and the sliding sealing sheet 6, the travel range of the height adjustment of the guide vane 4 itself and the gas sealing factor. The edge of the base 43 is designed as an arc transition structure. The bottommost opening of the base 43 with a radius of 4 mm 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 1 to optimize the driving torque of the connecting rod, making it easier to drive the guide vane 4. The bosses 44 on both sides of the base 43 form a self-locking structure with the inner ring frame 2, which limits the redundant freedom of the guide vane 4 and reduces the disturbance caused by the high-speed airflow. The axial hole set on the edge plate 42 is a threaded hole with a radius of 2 mm, which is used to install a fairing. The sliding sealing sheet 6 with a positioning guide groove is installed in the guide vane sealing groove 45. When the guide vane 4 is adjusted in length, the gap between the adjacent edge plates 42 increases. The sliding sealing sheet 6 slides in the guide vane sealing grooves 45 on both sides of the adjacent guide vanes 4 to fill the gap and continue to maintain the sealing of the main flow channel. The staggered sealing structure is integrated into the compact guide vane 4, and the angle between adjacent guide vanes 4 is 10°, so the angle between the guide vane sealing groove 45 and the central axis of the guide vane 4 is 95°, ensuring that the guide vane sealing grooves 45 at adjacent edge plates 42 remain parallel when the length of the guide vane 4 is adjusted.

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

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

[0059] like Fig. 9As shown, the sealing sheet hole 71 on the external sealing sheet 7 has the same blade shape as the guide vane 41, and the guide vane 41 can pass through and slide therethrough. The external sealing sheet 7 has two installation positioning holes, which can be assembled with the holes on the outer ring of the outer ring sealing frame 3 through pins, and cooperate with the surface of the guide vane extending out of the outer ring sealing frame 3 to form a seal. One guide vane corresponds to one external sealing sheet 7, which is convenient for replacement during maintenance. According to the actual sealing situation, the thickness of the sealing sheet can be increased to enhance the sealing effect.

[0060] like Fig.10 As shown, a four-layer sealing groove structure is machined in the groove on the external sealing sheet 7, and sealing is achieved by forming a slit-cavity with the guide vane surface. Similarly, the cooling airflow between the outer ring sealing frame 3 and the casing can further assist sealing.

[0061] like Fig.11 As shown, the external sealing sheet 7 is installed on the outer ring of the outer ring sealing frame 3 as a secondary sealing measure;

[0062] like Fig.12 As shown, a labyrinth seal structure is designed between the sliding seal sheet 6 and the guide vane seal groove 45 to improve the sealing effect. In actual operation, the sliding seal sheet 6 and the seal groove will also be affected by the pressure difference between the inner and outer cavities, and will be pressed against each other to form a seal.

[0063] like Fig.13 As shown, the engine outer casing 8 is directly assembled with the outer ring sealing frame 3 of the regulating mechanism, and the secondary sealing sheet, namely the external sealing sheet 7, is located in the sandwich layer between the two.

[0064] The assembly of the improved gas turbine aircraft engine guide vane length adjustment device comprises the following steps:

[0065] Step 1: The 36 wheel positioning points 11 on the circumference of the driving wheel 1 are connected to one end of the transmission connecting rod 5 through standard M8 pins.

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

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

[0068] Step 4: After the guide vanes 4 are inserted, the outer ring sealing frame 3 is moved along its own axial direction until the guide vanes 4 are aligned with the inner ring hollow holes 21 of the inner ring frame 2 .

[0069] Step 5: Shorten the length of the guide blade 4 and connect the drive link 5 to the base 43 of the guide blade 4 using a standard M8 pin.

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

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

[0072] Step 1: After the driving wheel 1, the inner ring frame 2, the outer ring sealing frame 3, the guide blade 4, the transmission connecting rod 5 and the sliding sealing sheet 6 are modeled and assembled, a moving body and a moving pair are added to each structural module;

[0073] Step 2: With the driving wheel disc 1 as the driving pair, the driving wheel disc 1 and the transmission connecting rod 5 are set as a revolute pair, and the transmission connecting rod 5 moves synchronously with the assembly position of the driving wheel disc 1;

[0074] Step 3: The transmission connecting rod 5 and the base 43 are assembled with concentric cylinders to set as a revolute pair, and the base 43 moves synchronously with the transmission connecting rod 5;

[0075] Step 4: The guide vane 41 and the outer ring sealing frame 3 are slidably matched, 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;

[0076] Step 5: constrain the freedom of the inner ring frame 2 along the main axis direction, 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 moves synchronously with the two connected edge plates 42;

[0077] Step 6: After the preliminary simulation, import the adjustment mechanism model and the set motion pair files into the professional kinematics simulation software to perform more detailed motion simulation and obtain the demonstration animation. Fig.14 As shown in the figure, the key data of each moving body are as follows Fig.15 As shown;

[0078] Step 7: Modify all virtual test pieces to entities, and set the motion simulation to stop when entity interference occurs, to verify whether the overall structure fits the ideal motion and whether interference occurs between the virtual test pieces. Verify the working range of the designed gas turbine aircraft engine guide vane length adjustment device;

[0079] Step 8: The feasibility of the design was verified by simulation using professional kinematics simulation software. From the data derived from the simulation run, it can be seen that the speed acceleration between the control mechanism and the controlled guide vane changes smoothly without mutations, and there is no interference between structural entities during the movement, indicating that the length adjustment mechanism is reliable and stable. It is calculated that the blade length adjustment can achieve a maximum area adjustment of 20%, which can meet the complex actuation conditions of the new generation of aircraft engines.

[0080] Step 9: After the simulation data is exported from the software, it is iterated multiple times to finally obtain the control relationship and fitting equation between the wheel rotation angle and the guide vane adjustment length. The fitting equation is:

[0081]

[0082] Where y is the guide vane adjustment length, in mm; x is the wheel rotation angle, in deg. Under this control relationship, the blade adjustment length can be determined by the wheel rotation angle. Fig.16 shown.

[0083] Step 10: Verify whether the stroke of the gas turbine aircraft engine guide vane length adjustment device meets the design expectations through the test data curve, and set the angle and angular velocity of the driving wheel 1 according to the fitting curve.

[0084] The above are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should be regarded as the protection scope of the present invention.

Claims

1. A gas turbine aircraft engine guide vane length adjustment device, characterized in that: The invention comprises a driving wheel disc (1), an inner ring frame (2), an outer ring sealing frame (3), a guide blade (4), a transmission connecting rod (5) and a sliding sealing sheet (6); the driving wheel disc (1) is installed on the inner side of the inner ring frame (2); the driving wheel disc (1) can rotate around its own axis; the driving wheel disc (1) is provided with a plurality of wheel disc positioning points (11) arranged in a ring shape with the axis of the driving wheel disc (1) as the center point; the inner ring frame (2) is an annular frame; the inner ring frame (2) The outer peripheral surface is provided with a plurality of inner ring hollow holes (21) arranged in an array, the guide vane (4) comprises a guide vane (41), an edge plate (42) and a base (43) connected in sequence, one end of the transmission connecting rod (5) is hingedly connected to the wheel disc positioning point (11), and the other end is hingedly connected to the base (43), the outer ring sealing frame (3) is an annular frame, the inner ring frame (2) and the outer ring sealing frame (3) are coaxial with the driving wheel disc (1), and the The outer peripheral surface of the outer ring sealing frame (3) is provided with a plurality of outer ring hollow holes (31) arranged in an array, each guide vane (4) corresponds to an inner ring hollow hole (21) and an outer ring hollow hole (31), the base (43) passes through the inner ring hollow hole (21) and is slidably matched with the inner ring hollow hole (21), the guide vane (41) passes through the outer ring hollow hole (31) and is slidably matched with the outer ring hollow hole (31), and the sliding sealing sheet (6) is connected On the edge plates (42) of two adjacent guide vanes (4), a sliding sealing sheet (6) is located outside the inner ring frame (2), and the sliding sealing sheet (6) cannot pass through the inner ring hollow hole (21). The driving wheel (1) causes the guide vanes (4) to slide in the inner ring hollow hole (21) and the outer ring hollow hole (31) by rotating and pulling the transmission connecting rod (5) and the guide vanes (4), thereby adjusting the length of the guide vanes (41) extending out of the outer ring sealing frame (3).

2. The gas turbine aircraft engine guide vane length adjustment device according to claim 1, characterized in that: A wheel disc hollow cavity is arranged in the middle of the driving wheel disc (1), and an annular boss (12) is arranged on the upper surface of the driving wheel disc (1) along the edge of the wheel disc hollow cavity. The wheel disc hollow cavity is used to insert a transmission shaft, and the transmission shaft is connected to a motor, and the motor can drive the driving wheel disc (1) to rotate.

3. The gas turbine aircraft engine guide vane length adjustment device according to claim 2, characterized in that: An inner ring frame cover (22) is provided on the upper surface of the inner ring frame (2), the driving wheel disc (1) is located below the inner ring frame cover (22), and the inner ring frame cover (22) is provided with trapezoidal notches (23) arranged in an array with the axis of the inner ring frame (2) as the center, each trapezoidal notch (23) corresponds to a transmission connecting rod (5), and the trapezoidal notches (23) are used to provide an operating space for assembling the transmission connecting rod (5).

4. The gas turbine aircraft engine guide vane length adjustment device according to claim 3, characterized in that: The outer side surface of the outer ring sealing frame (3) is matched with a plurality of external sealing sheets (7); the shape of the outer ring hollow hole (31) is adapted to the shape of the guide vane (41); a sealing sheet hole (71) adapted to the shape of the guide vane (41) is provided on the external sealing sheet (7); the guide vane (41) passes through the outer ring hollow hole (31) and the sealing sheet hole (71) in sequence; the external sealing sheet (7) is used to seal 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, characterized in that: The external sealing sheet (7) is provided with a threaded hole, and the external sealing sheet (7) is fixed to the outer side surface of the outer ring sealing frame (3) by means of bolts.

6. The gas turbine aircraft engine guide vane length adjustment device according to claim 3, characterized in that: The base (43) is provided with an assembly hole for connecting with the transmission connecting rod (5), and bosses (44) are provided on the upper and lower sides of the edge plate (42). The shapes of the upper and lower ends of the inner ring hollow hole (21) are adapted to the bosses (44), and the bosses (44) cooperate with the inner ring hollow hole (21) to limit the left and right shaking of the edge plate (42).

7. The gas turbine aircraft engine guide vane length adjustment device according to claim 6, characterized in that: The left and right sides of the edge plate (42) are both provided with guide vane sealing grooves (45), and the sliding sealing sheet (6) is simultaneously inserted into the guide vane sealing grooves (45) of two adjacent guide vanes (4) for positioning.

8. The gas turbine aircraft engine guide vane length adjustment device according to claim 7, characterized in that: The sliding sealing sheet (6) is provided with a plurality of transverse guide grooves (61), and the guide vane sealing groove (45) is provided with a sliding protrusion adapted to the guide groove (61). When the sliding sealing sheet (6) is inserted into the guide vane sealing groove (45), the sliding protrusion cooperates 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 transversely in the guide vane sealing groove (45). The width of the sliding sealing sheet (6) is set such that: when the guide vane (4) is extended to the longest stroke, the sliding sealing sheet (6) does not separate from the guide vane sealing groove (45); when the guide vane (4) is retracted to the shortest stroke, the left and right ends of the sliding sealing sheet (6) do not squeeze against 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, characterized in that: A circle of engine outer casing (8) is arranged outside the outer ring sealing frame (3), and cooling air is passed between the outer ring sealing frame (3) and the engine outer casing (8) to provide cooling. The cooling air is drawn from the compressor, and the compressor can pressurize the gas between the outer ring sealing frame (3) and the engine outer casing (8).

10. A test method for adjusting the length of a gas turbine aircraft engine guide vane, characterized in that: The gas turbine aircraft engine guide vane length adjustment device according to claim 8 is used, and the specific method comprises the following steps: Step 1: After the driving wheel (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) are modeled and assembled, a kinematic body and a kinematic pair are added to each structural module; Step 2: The driving wheel disc (1) is used as a driving pair, and the driving wheel disc (1) and the transmission connecting rod (5) are set as a revolute pair with the concentric cylinder, and the transmission connecting rod (5) moves synchronously with the assembly position of the driving wheel disc (1); Step 3: The transmission connecting rod (5) and the concentric cylinder of the assembly hole of the base (43) are set as a revolute pair, and the base (43) moves synchronously with the transmission connecting rod (5); Step 4: The guide vane (41) and the outer ring sealing frame (3) are slidably matched, 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 to have a degree of freedom along the main axis direction, and the sliding seal sheet (6) and the guide vane sealing groove (45) are in relative sliding motion, so the sliding seal sheet (6) and the guide vane sealing groove (45) are set as a sliding pair, and the sliding seal sheet (6) moves synchronously with the two connected edge plates (42); Step 6: Perform kinematic simulation on each structural module to obtain motion animation and motion data of each structural module; Step 7: Modify the virtual test pieces of all structural modules into entities, and set the motion simulation to stop when entity interference occurs, verify whether the overall structure fits the ideal motion, whether interference occurs between the virtual test pieces, and verify the working range of the designed gas turbine aircraft engine guide vane length adjustment device; Step 8: Analyze the virtual test piece to obtain a curve showing the relationship between the rotation angle of the driving wheel disc (1) and the length of the guide vane (41) extending out of the outer ring sealing frame (3); Step 9: Analyze and calculate through the data table to obtain a fitting curve function of the rotation angle of the driving wheel disc (1) and the length of the guide vane (41) extending out of the outer ring sealing frame (3); Step 10: Verify whether the stroke of the gas turbine aircraft engine guide vane length adjustment device meets the design expectations through the test data curve, and set the angle and angular velocity of the driving wheel (1) according to the fitting curve.

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