A device and method for rapid adjustment of bearing misalignment in aero-engines.

Abstract

This invention discloses a rapid adjustment device and method for the misalignment of aero-engine bearings. The rapid adjustment device includes a long crossbeam, a short crossbeam, a ruler frame, screws, a ruler body, a first semi-circular head rivet, a first cylindrical pin, a second cylindrical pin, a second semi-circular head rivet, a vernier ruler frame, and a slotted screw. During adjustment, the distance between the rear mounting edge of the low-pressure turbine stator and the outer ring end face of the pivot bearing, and the distance between the front mounting edge of the turbine support and the inner ring mounting seat end face of the pivot bearing are measured using the rapid adjustment device. Combined with the misalignment of the pivot bearing, the actual thickness of the pivot adjustment shim can be calculated. Then, a pivot adjustment shim of the selected thickness is installed at the pivot bearing assembly. This invention reduces the time spent on repeated trial and error, ensures successful selection on the first attempt, improves efficiency, and reduces quality risks.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine assembly and testing technology, specifically a device and method for rapidly adjusting the misalignment of aero-engine bearings. Background Technology

[0002] like Figure 1 As shown, the pivot bearing 15 of the aero-engine needs to have its inner and outer ring misalignment 'a' ensured by adjusting the thickness of the pivot adjustment shim 17, so as to ensure that the pivot bearing 15 is within the safe working range during the operation of the aero-engine.

[0003] The traditional measurement method involves trial assembly of the turbine support 16, application of grease to the bearing rollers, observation of the actual contact marks of the bearing rollers on the inner steel sleeve, measurement of the mark positions using tools such as vernier calipers, and adjustment of the shim thickness as required. This method requires repeated trial assembly of the turbine support 16, is inefficient, and results in unclear contact marks and large measurement errors. Summary of the Invention

[0004] The present invention aims to provide a device and method for rapid adjustment of bearing misalignment in aero-engines, reducing trial and error time, ensuring successful selection on the first attempt, improving efficiency, and reducing quality risks.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A rapid adjustment device for the misalignment of aero-engine bearings, comprising:

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

[0008] Two short crossbeams are fixed to the left and right ends of the long crossbeam respectively in the extension direction of the long crossbeam. The short crossbeam includes a support arm and a support leg. The support arm is L-shaped, with one end connected to the long crossbeam and the other end connected to the support leg. The support legs of the two short crossbeams are located in the same plane parallel to the long crossbeam.

[0009] A ruler frame, which is fixed to a long crossbeam and located between two short crossbeams;

[0010] The vernier frame consists of two vernier frames that are installed parallel to each other and spaced apart on the same side surface of the frame, and the vernier frame surface is engraved with length values.

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

[0012] As one solution:

[0013] The short crossbeam is rigidly connected to the long crossbeam by a first semi-circular head rivet and a first cylindrical pin.

[0014] The ruler frame is rigidly connected to the long crossbeam by a second cylindrical pin and a second semi-circular head rivet.

[0015] The vernier frame is mounted on the ruler frame using flathead screws.

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

[0017] As one solution:

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

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

[0020] A method for rapidly adjusting the misalignment of an aero-engine bearing, employing the aforementioned rapid adjustment device, includes the following steps:

[0021] Step 1: Place the quick adjustment device on the mounting side of the low-pressure turbine stator, with the support end face of the short crossbeam in contact with the rear mounting side of the low-pressure turbine stator. The hook-shaped measuring end of the scale body should avoid the fulcrum bearing nut and then contact the outer ring end face of the fulcrum bearing. Read the scale body reading at this time and record it as b.

[0022] Step 2: Place the quick adjustment device on the turbine support mounting side, with the support end face of the short crossbeam in contact with the front mounting side of the turbine support, and the hook-shaped measuring end of the scale body in contact with the end face of the inner ring mounting seat of the fulcrum bearing. Read the scale body reading at this time and record it as c.

[0023] Step 3: Based on the dimensional chain calculation formula b = caT, where T is the thickness of the fulcrum adjusting shim and a is the misalignment between the inner and outer rings of the fulcrum bearing, it can be seen that the thickness T of the fulcrum adjusting shim satisfies the calculation formula T = cab. Repeat steps 1 and 2 to obtain multiple sets of measurement values ​​b and c. For each set of measurement values ​​b and c, calculate a thickness T value of the fulcrum adjusting shim. Use the average value calculation method to process multiple obtained T values, and finally calculate the actual thickness of the fulcrum adjusting shim.

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

[0025] This invention measures two quantities using the same measuring device (rapid adjustment device) under the same reference plane: the distance *b* between the rear mounting edge of the low-pressure turbine stator and the outer ring end face of the pivot bearing, and the distance *c* between the front mounting edge of the turbine support and the inner ring mounting seat end face of the pivot bearing. The thickness of the pivot adjustment shim is calculated using these two quantities. After multiple measurements, the average of the calculated values ​​is taken as the actual value of the pivot adjustment shim. Because this rapid adjustment method uses the same measuring device and is based on the same reference plane, it can eliminate measurement errors (even if the rapid measuring device itself has reference errors, these can be offset), improving measurement accuracy. Furthermore, it eliminates the need to calibrate the rapid adjustment device before measurement and does not require changing the measuring device during the measurement process, thus improving measurement efficiency.

[0026] Compared with existing technologies, this invention can reduce the time spent on repeated trial and error, ensure successful selection of the fulcrum adjustment pad on the first attempt, and improve efficiency. At the same time, in combination 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 error of the measuring tools themselves and improve the accuracy of the measurement. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the fulcrum bearing installation.

[0028] Figure 2 General drawing of the quick adjustment device for the fulcrum bearing;

[0029] Figure 3 This is a schematic diagram for measuring dimension b;

[0030] Figure 4 This is a schematic diagram for measuring dimension c;

[0031] In the diagram: 1. Long crossbeam, 2. Short crossbeam, 3. Ruler frame, 4. Screw, 5. Ruler body, 6. First semi-circular head rivet, 7. First cylindrical pin, 8. Second cylindrical pin, 9. Second semi-circular head rivet, 10. Vernier frame, 11. Slotted screw, 12. Low-pressure turbine rotor, 13. Locking screw, 14. Low-pressure turbine stator, 15. Pivot bearing, 16. Turbine support, 17. Pivot adjusting shim, 18. Pivot bearing nut. Detailed Implementation

[0032] The present invention will be further described below with reference to specific embodiments, but it should not be construed as limiting the scope of the subject matter of the present invention to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0033] The misalignment of the aircraft engine pivot bearing 15 is quickly adjusted using a special depth gauge for measuring the pivot bearing. For example... Figure 2 As shown, this special depth gauge includes a long crossbeam 1, a short crossbeam 2, a frame 3, screws 4, a body 5, a first semi-circular head rivet 6, a first cylindrical pin 7, a second cylindrical pin 8, a second semi-circular 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 contacts the turbine support 16 and the mounting edge of the low-pressure turbine stator 14 casing respectively, ensuring that the special depth gauge can be placed stably. The short crossbeam 2 is L-shaped, with one end fixed to the long crossbeam 1 and the other end connected to the support leg. Figure 2 The end face of the support is flat and extends in a direction perpendicular to the long crossbeam 1. The support lengths of the two short crossbeams 2 are different.

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

[0036] (3) A groove is opened in the middle of the surface of the frame 3 (the groove is used for the body 5 to slide freely in it). The vernier frame 10 consists of two scales with graduations on their surfaces. They are installed on the same side surface of the frame 3 in parallel by slotted screws 11. The vernier frame 10 has graduations from 1 to 10 mm, with each graduation being 1 mm. The body 5 also slides between the two vernier frames 10.

[0037] (4) The ruler body 5 has a length scale covering a range of ±6cm. Each length scale is divided into 10 small scales, each small scale being 1mm. It works in conjunction with the vernier frame 10 to achieve size measurement. The rear end of the ruler body 5 is equipped with a screw 4 to prevent the ruler body 5 from coming out of the ruler frame 3. The front end of the ruler body 5 is designed as a hook to avoid interference with the fulcrum bearing nut 18. The ruler frame 3 is also equipped with a stop screw 13 to fix the position of the ruler body 5.

[0038] like Figure 1 As shown, Figure 1 The image shows the assembly relationship of the low-pressure turbine stator 14, the pivot bearing 15, the turbine support 16, and the pivot adjusting shim 17. The low-pressure turbine stator 14 and the turbine support 16 are connected via their respective mounting edges. Figure 1 The direction indicated by the middle arrow distinguishes the front and rear, with the rear mounting edge of the low-pressure turbine stator 14 fitting against the front mounting edge of the turbine support 16.

[0039] The rapid adjustment method for the misalignment of the pivot bearing in an aero-engine includes the following steps:

[0040] Step 1, as follows Figure 2The long crossbeam 1, short crossbeam 2, ruler frame 3, screw 4, ruler body 5, first semi-circular head rivet 6, first cylindrical pin 7, first cylindrical pin 8, second semi-circular head rivet 9, vernier frame 10, flathead screw 11 and stop screw 13 are assembled into a whole, and the size measurement is achieved by adjusting the extension and retraction of the ruler body 5.

[0041] Step two, as Figure 3 First, place the special depth gauge on the mounting side of the low-pressure turbine stator 14. The end face of the support leg of the short crossbeam 2 contacts the rear mounting side of the low-pressure turbine stator 14. The hook-shaped front end face of the gauge body 5 avoids the fulcrum bearing nut 18 and then contacts the outer ring end face of the fulcrum bearing 15. Read the reading b of the gauge body 5.

[0042] Step 3, as Figure 4 Then place the special depth gauge on the mounting side of the turbine support 16, with the support end face of the short crossbeam 2 in contact with the front mounting side of the turbine support 16, and the hook-shaped front end face of the gauge body 5 in contact with the end face of the inner ring mounting seat of the fulcrum bearing 15. Read the reading c of the gauge body 5.

[0043] ③ Based on the dimensional chain calculation formula b=caT, where T is the thickness of the fulcrum adjusting pad 17 and a is the misalignment between the inner and outer rings of the fulcrum bearing 15, it can be seen that the thickness T of the fulcrum adjusting pad 17 satisfies the calculation formula T=cab. Repeat steps one and two to obtain multiple sets of measurement values ​​b and c. Each set of measurement values ​​b and c is used to calculate a thickness T value of the fulcrum adjusting pad 17. The average value calculation method is used to process multiple obtained T values, and finally the actual thickness of the fulcrum adjusting pad 17 is calculated.

[0044] Contents not described in detail in this specification are prior art known to those skilled in the art. Although illustrative specific embodiments of the invention have been described above to facilitate understanding by those skilled in the art, it should be understood that the invention is not limited to the scope of the specific embodiments. Various modifications are readily apparent to those skilled in the art as long as they fall within the spirit and scope of the invention as defined and determined by the appended claims, and all inventions utilizing the concept of this invention are protected.

Claims

1. A method for rapidly adjusting the misalignment of aero-engine bearings, characterized in that, The quick adjustment device used includes: A 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 extension direction of the long crossbeam (1), and the short crossbeams (2) include support arms and support legs. The support arms are L-shaped, with one end connected to the long crossbeam (1) and the other end connected to the support legs. The support legs of the two short crossbeams (2) are located in the same plane parallel to the long crossbeam (1). The ruler frame (3) is fixed on the long crossbeam (1) and is located between two short crossbeams (2); The two vernier frames (10) are installed parallel and spaced apart on the same side surface of the ruler frame (3), and the vernier frames (10) have length values ​​engraved on their surfaces. The ruler body (5) is slidably connected to the ruler frame (3). The ruler body (5) has length values ​​engraved on its surface. The measuring end of the ruler body (5) is hook-shaped. The quick adjustment method includes the following steps: Step 1: First, place the quick adjustment device on the mounting side of the low-pressure turbine stator (14), and make the support end face of the short crossbeam (2) contact the rear mounting side of the low-pressure turbine stator (14). The hook-shaped measuring end of the scale body (5) avoids the fulcrum bearing nut (18) and then contacts the outer ring end face of the fulcrum bearing (15). Read the reading of the scale body (5) at this time and record it as b. Step 2: Place the quick adjustment device on the mounting side of the turbine support (16), with the foot end face of the short crossbeam (2) in contact with the front mounting side of the turbine support (16), and the hook-shaped measuring end of the scale body (5) in contact with the end face of the inner ring mounting seat of the fulcrum bearing (15). Read the reading of the scale body (5) at this time and record it as c. Step 3: Based on the dimensional chain calculation formula b=caT, where T is the thickness of the fulcrum adjusting pad (17) and a is the misalignment of the inner and outer rings of the fulcrum bearing (15), it can be seen that the thickness T of the fulcrum adjusting pad (17) satisfies the calculation formula T=cab. Repeat steps 1 and 2 to obtain multiple sets of measurement values ​​b and c. Each set of measurement values ​​b and c is used to calculate a thickness T value of the fulcrum adjusting pad (17). The average value calculation method is used to process multiple obtained T values, and finally the actual thickness of the fulcrum adjusting pad (17) is calculated. Step 4: Select a pivot adjustment pad (17) with a thickness of T and install it at the assembly point between the inner ring of the pivot bearing (15) and the turbine support (16).

2. The method for rapid adjustment of bearing misalignment in an aero-engine according to claim 1, characterized in that: The short crossbeam (2) is rigidly connected to the long crossbeam (1) by the first semi-circular head rivet (6) and the first cylindrical pin (7); The ruler frame (3) is rigidly connected to the long crossbeam (1) by the second cylindrical pin (8) and the second semi-circular head rivet (9); The vernier frame (10) is mounted on the frame (3) by a flathead screw (11).

3. The method for rapidly adjusting the misalignment of an aero-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 on the end of the ruler body (5) away from the hook-shaped measuring end.

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

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