Quick adjusting device and method for bearing displacement of aero-engine

Abstract

The invention discloses a quick adjusting device and method for the bearing displacement of an aero-engine. The quick adjusting device comprises a long cross beam, a short cross beam, a ruler frame, a screw, a ruler body, a first cup head rivet, a first cylindrical pin, a second cylindrical pin, a second cup head rivet, a vernier frame and a straight screw. During adjustment, the distance between the rear mounting edge of the low-pressure turbine stator and the end face of the outer ring of the fulcrum bearing and the distance between the front mounting edge of the turbine bearing and the end face of the mounting seat of the inner ring of the fulcrum bearing are respectively measured through the quick adjusting device, and the actual thickness of the fulcrum adjusting pad can be calculated by combining the displacement of the fulcrum bearing. And the supporting point adjusting pad with the selected thickness is mounted at the supporting point bearing assembly position. According to the method, the repeated trial and error time is shortened, one-time matching success is ensured, the efficiency is improved, and the quality risk is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine complete machine assembly and test running, and in particular relates to a rapid adjustment device and method for the misalignment of an aircraft engine bearing. Background Art

[0002] like Figure 1 As shown, the aircraft engine fulcrum bearing 15 needs to ensure the displacement a of the inner and outer rings by adjusting the thickness of the fulcrum adjustment pad 17 to ensure that the fulcrum bearing 15 is in a safe working area during the operation of the aircraft engine.

[0003] The traditional measurement method is to test-install the turbine support 16, apply grease on the fulcrum bearing roller, observe the actual contact mark of the fulcrum bearing roller on the inner steel sleeve, measure the position of the mark with a vernier caliper or other tools, and then adjust the thickness of the adjustment pad as required. This method requires repeated test-installation of the turbine support 16, which is inefficient, and the contact marks are not clear, resulting in large measurement errors. Summary of the invention

[0004] The present invention aims to provide a device and method for quickly adjusting the misalignment of an aircraft engine bearing, so as to reduce the time of repeated trial and error, ensure a successful selection at one time, improve efficiency and reduce quality risks.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A rapid adjustment device for the misalignment of an aircraft engine bearing, comprising:

[0007] A long crossbeam, wherein the long crossbeam extends in a straight line;

[0008] Short crossbeams, two of which are respectively fixed at the left and right ends of the long crossbeam in the extension direction, and the short crossbeams include a support arm and a support foot, the support arm is L-shaped, one end of which is connected to the long crossbeam, and the other end is connected to the support foot, and the support feet of the two short crossbeams are located in the same plane parallel to the long crossbeam;

[0009] A ruler frame, the ruler frame is fixed on the long crossbeam and is between the two short crossbeams;

[0010] Vernier scale frames, two of which are installed in parallel and at intervals on the same side surface of the scale frame, and the surface of the vernier scale frames is engraved with length values;

[0011] The ruler body is slidably connected to the ruler frame, the length value is engraved on the surface of the ruler body, and the measuring end of the ruler body is hook-shaped.

[0012] As a solution:

[0013] The short crossbeam is rigidly connected to the long crossbeam through a first semicircular head rivet and a first cylindrical pin;

[0014] The ruler frame is rigidly connected to the long crossbeam through a second cylindrical pin and a second semicircular head rivet;

[0015] The vernier frame is mounted on the ruler frame by means of slotted screws.

[0016] Furthermore, a screw is provided on the ruler body, and the screw is located at an end of the ruler body away from the hook-shaped measuring end.

[0017] As a solution:

[0018] The surface of the vernier frame is engraved with length values ​​of 1 to 10 mm, and the minimum scale value is 1 mm;

[0019] The surface of the ruler is engraved with length values ​​ranging from -6cm to +6cm, and the smallest scale value is 1mm.

[0020] A method for quickly adjusting the misalignment of an aircraft engine bearing adopts the above-mentioned quick adjustment device and comprises the following steps:

[0021] Step 1: first place the quick adjustment device on the installation edge of the low-pressure turbine stator, and the end face of the short crossbeam's foot is in contact with the rear installation edge of the low-pressure turbine stator. The hook-shaped measuring end of the ruler body avoids the fulcrum bearing nut and contacts the end face of the outer ring of the fulcrum bearing. Read the reading of the ruler body at this time, which is recorded as b.

[0022] Step 2: Place the quick adjustment device on the mounting edge of the turbine support, the end face of the short crossbeam's support leg contacts the front mounting edge of the turbine support, the hook-shaped measuring end of the ruler contacts the end face of the fulcrum bearing inner ring mounting seat, and read the ruler's reading at this time, recorded as c;

[0023] Step 3: Based on the calculation formula b=caT of the dimension chain, where T is the thickness of the pivot adjustment pad and a is the displacement of the inner and outer rings of the pivot bearing, it can be seen that the thickness T of the pivot adjustment pad satisfies the calculation formula T=cab. Repeat steps 1 and 2 to obtain multiple groups of measurement values ​​b and c. For each group of measurement values ​​b and c, calculate a thickness T value of the pivot adjustment pad. Use the average value calculation method to process multiple obtained T values, and finally calculate the actual thickness of the pivot adjustment pad.

[0024] Step 4: Select a pivot adjustment pad with a thickness of T and install it on the assembly point between the inner ring of the pivot bearing and the turbine support.

[0025] The present invention uses the same measuring device (quick adjustment device) under the same reference plane to measure two quantities, namely the distance b between the rear mounting edge of the low-pressure turbine stator and the end face of the outer ring of the fulcrum bearing and the distance c between the front mounting edge of the turbine support and the end face of the inner ring mounting seat of the fulcrum bearing, and calculates the thickness of the fulcrum adjustment pad through these two quantities. After multi-point measurement, the average value of the calculated values ​​of the fulcrum adjustment pad is taken as the actual value of the fulcrum adjustment pad. Since the quick adjustment method of the present invention uses the same measuring device and is based on the same reference plane, it can eliminate measurement errors (even if the quick measuring device itself has a reference error, it can be offset), improve the accuracy of measurement, and does not need to calibrate the quick adjustment device before measurement, and does not need to replace the measuring device during the measurement, thereby improving the efficiency of measurement.

[0026] Compared with the prior art, the present invention can reduce the time of repeated trial and error, ensure that the fulcrum adjustment pad is successfully matched at one time, and improve efficiency. At the same time, combined with the structural characteristics of the engine, a set of special measuring tools is designed as a quick adjustment device. This solution enables a set of measuring tools to measure the dimensions of two positions, which can eliminate the errors of the measuring tools themselves and improve the accuracy of the measurement. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the installation of the pivot bearing;

[0028] Figure 2 This is the general diagram of the quick adjustment device for the pivot bearing;

[0029] Figure 3 Schematic diagram for measuring dimension b;

[0030] Figure 4 Schematic diagram for measuring dimension c;

[0031] In the figure: 1. long crossbeam, 2. short crossbeam, 3. ruler frame, 4. screw, 5. ruler body, 6. first semicircular head rivet, 7. first cylindrical pin, 8. second cylindrical pin, 9. second semicircular head rivet, 10. vernier frame, 11. slotted screw, 12. low-pressure turbine rotor, 13. stop screw, 14. low-pressure turbine stator, 15. fulcrum bearing, 16 turbine support, 17. fulcrum adjustment pad, 18. fulcrum bearing nut. DETAILED DESCRIPTION

[0032] The present invention is further described below in conjunction with specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0033] The rapid adjustment of the displacement of the aircraft engine pivot bearing 15 is achieved by using a special depth gauge for measuring the pivot bearing. Figure 2 As shown, the special depth gauge includes a long crossbeam 1, a short crossbeam 2, a ruler frame 3, screws 4, a ruler body 5, a first semicircular head rivet 6, a first cylindrical pin 7, a second cylindrical pin 8, a second semicircular head rivet 9, a vernier frame 10 and a slotted screw 11. The assembly relationship and function of each component are as follows:

[0034] (1) The short crossbeam 2 is in contact with the mounting edge of the turbine support 16 and the low-pressure turbine stator 14 casing, respectively, to ensure that the special depth gauge can be placed stably. The short crossbeam 2 is L-shaped, one end of which is fixed to the long crossbeam 1, and the other end is connected to the support foot, such as Figure 2 , the end surface of the support leg is a plane and extends in a direction perpendicular to the long beam 1, and the support legs of the two short beams 2 have different lengths;

[0035] (2) The long crossbeam 1 is the main structure of the special depth gauge, and is rigidly connected to the short crossbeam 2 through a first semicircular head rivet 6 and a first cylindrical pin 7, and is rigidly connected to the ruler frame 3 through a second cylindrical pin 8 and a second semicircular head rivet 9;

[0036] (3) A groove is provided in the middle of the ruler frame 3 (the groove is used for the ruler body 5 to slide freely in it). The vernier ruler frames 10 are two rulers with scales on the surface, which are installed on the same side surface of the ruler frame 3 in parallel and at intervals by slotted screws 11. There are scale numbers of 1 to 10 mm on the vernier ruler frames 10, and each scale is 1 mm. The ruler body 5 also slides between the two vernier ruler frames 10;

[0037] (4) The ruler body 5 is provided with a length scale covering a range of ±6 cm. Each length scale is divided into 10 small scales, each small scale is 1 mm, and it cooperates with the vernier frame 10 to achieve dimension measurement. The rear end of the ruler body 5 is provided with a screw 4 to prevent the ruler body 5 from escaping from the ruler frame 3. The front end of the ruler body 5 is designed to be hook-shaped to avoid interference with the fulcrum bearing nut 18. A stop screw 13 is also provided on the ruler frame 3 to fix the position of the ruler body 5.

[0038] like Figure 1 As shown, Figure 1 The assembly relationship of the low-pressure turbine stator 14, the pivot bearing 15, the turbine support 16 and the pivot adjustment pad 17 is shown in FIG. 1 , wherein the low-pressure turbine stator 14 and the turbine support 16 are connected by their respective mounting edges. Figure 1 The front and rear are distinguished by the direction indicated by the middle arrow, and the rear mounting edge of the low-pressure turbine stator 14 is in contact with the front mounting edge of the turbine support 16.

[0039] The method for quickly adjusting the misalignment of the aeroengine pivot bearing comprises the following steps:

[0040] Step 1, such as Figure 2, assemble the long crossbeam 1, the short crossbeam 2, the ruler frame 3, the screw 4, the ruler body 5, the first semicircular head rivet 6, the first cylindrical pin 7, the first cylindrical pin 8, the second semicircular head rivet 9, the vernier frame 10, the slotted screw 11 and the stop screw 13 into a whole, and realize the size measurement by adjusting the extension and contraction of the ruler body 5.

[0041] Step 2, such as Figure 3 First, place the special depth gauge on the installation edge of the low-pressure turbine stator 14, the end face of the foot of the short crossbeam 2 contacts the rear installation edge of the low-pressure turbine stator 14, and the hook-shaped front end face of the ruler body 5 avoids the fulcrum bearing nut 18 and contacts the outer ring end face of the fulcrum bearing 15, and read the reading b of the ruler body 5;

[0042] Step three, such as Figure 4 , then place the special depth gauge on the installation edge of the turbine support 16, the end face of the foot of the short crossbeam 2 contacts the front installation edge of the turbine support 16, the hook-shaped front end face of the ruler body 5 contacts the end face of the inner ring installation seat of the fulcrum bearing 15, and read the reading c of the ruler body 5;

[0043] ③ Based on the calculation formula b=caT of the dimension chain, where T is the thickness of the fulcrum adjustment pad 17, and a is the displacement of the inner and outer rings of the fulcrum bearing 15, it can be seen that the thickness T of the fulcrum adjustment pad 17 satisfies the calculation formula T=cab. Repeat steps 1 and 2 to obtain multiple groups of measurement values ​​b and c. For each group of measurement values ​​b and c, a thickness T value of the fulcrum adjustment pad 17 is calculated. The average value calculation method is used to process multiple obtained T values, and finally the actual thickness of the fulcrum adjustment pad 17 is calculated.

[0044] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For ordinary technicians in the field of this technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. A rapid adjustment device for the misalignment of an aircraft engine bearing, characterized in that: include: A long crossbeam (1), wherein the long crossbeam (1) extends in a straight line; Short crossbeams (2), two short crossbeams (2) are respectively fixed at the left and right ends of the long crossbeam (1) in the extension direction, and the short crossbeam (2) comprises a support arm and a support foot, the support arm is L-shaped, one end of which is connected to the long crossbeam (1), and the other end is connected to the support foot, and the support feet of the two short crossbeams (2) are located in the same plane parallel to the long crossbeam (1); A ruler frame (3), wherein the ruler frame (3) is fixed on the long crossbeam (1) and is located between the two short crossbeams (2); Vernier frames (10), two of the vernier frames (10) are installed in parallel and at intervals on the same side surface of the scale frame (3), and the surfaces of the vernier frames (10) are engraved with length values; A ruler body (5) is slidably connected to the ruler frame (3), a length value is engraved on the surface of the ruler body (5), and a measuring end of the ruler body (5) is hook-shaped.

2. A rapid adjustment device for the misalignment of an aircraft engine bearing according to claim 1, characterized in that: The short crossbeam (2) is rigidly connected to the long crossbeam (1) via a first semicircular head rivet (6) and a first cylindrical pin (7); The ruler frame (3) is rigidly connected to the long crossbeam (1) via a second cylindrical pin (8) and a second semicircular head rivet (9); The vernier frame (10) is mounted on the ruler frame (3) via a slotted screw (11).

3. The device for quickly adjusting the misalignment of an aircraft engine bearing according to claim 1, characterized in that: The ruler body (5) is also provided with a screw (4), and the screw (4) is located at an end of the ruler body (5) away from the hook-shaped measuring end.

4. A rapid adjustment device for the misalignment of an aircraft engine bearing according to claim 1, characterized in that: The surface of the vernier ruler frame (10) is engraved with length values ​​of 1 to 10 mm, and the smallest scale value is 1 mm; the surface of the ruler body (5) is engraved with length values ​​of -6 cm to +6 cm, and the smallest scale value is 1 mm.

5. A method for quickly adjusting the misalignment of an aircraft engine bearing, characterized in that: The quick adjustment device according to claim 1 is used, and comprises the following steps: Step 1: first place the quick adjustment device on the mounting edge of the low-pressure turbine stator (14), and the end face of the foot of the short crossbeam (2) contacts the rear mounting edge of the low-pressure turbine stator (14), and the hook-shaped measuring end of the ruler body (5) avoids the fulcrum bearing nut (18) and contacts the outer ring end face of the fulcrum bearing (15), and read the reading of the ruler body (5) at this time, which is recorded as b; Step 2: Place the quick adjustment device on the mounting edge of the turbine support (16), the end face of the support leg of the short crossbeam (2) contacts the front mounting edge of the turbine support (16), the hook-shaped measuring end of the ruler body (5) contacts the end face of the inner ring mounting seat of the fulcrum bearing (15), and read the reading of the ruler body (5) at this time, which is recorded as c; Step 3: Based on the calculation formula b=caT of the dimension chain, where T is the thickness of the fulcrum adjustment pad (17), and a is the displacement between the inner and outer rings of the fulcrum bearing (15), it can be seen that the thickness T of the fulcrum adjustment pad (17) satisfies the calculation formula T=cab. Steps 1 and 2 are repeated to obtain multiple groups of measurement values ​​b and c. For each group of measurement values ​​b and c, a thickness T value of the fulcrum adjustment pad (17) is calculated. The average value calculation method is used to process the multiple obtained T values, and finally the actual thickness of the fulcrum adjustment pad (17) is calculated. Step 4: Select a fulcrum adjustment pad (17) with a thickness of T and install it on the assembly point between the inner ring of the fulcrum bearing (15) and the turbine support (16).

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