Method of installing a cushioning shafting for a hovercraft

Abstract

The application belongs to the technical field of ships and discloses a mounting method of a hovercraft cushioning shaft system. The cushioning shaft system is divided into a first shaft section, a second shaft section, a third shaft section and a fourth shaft section. The first shaft section is from a stern cushioning fan reducer to an accessory box, the second shaft section is from the stern cushioning fan reducer to a bow cushioning fan reducer, the third shaft section is from the stern cushioning fan reducer to a stern cushioning fan and from the bow cushioning fan reducer to a bow cushioning fan, and the fourth shaft section is from the accessory box to a cushioning main reducer. The mounting method comprises the following steps: positioning and installing the stern cushioning fan reducer on the ship; positioning and installing the first shaft section, the second shaft section, the third shaft section and the fourth shaft section, wherein the first shaft section, the second shaft section and the third shaft section are positioned and installed with the stern cushioning fan reducer as a reference. The mounting method reduces the difficulty of centering, shortens the centering cycle, improves the installation efficiency of the cushioning shaft system and reduces the workload.

Description

Technical Field

[0001] The present invention relates to the technical field of ships, and in particular to a method for installing a cushion-lift shaft system of an air cushion vessel. Background Art

[0002] The cushioning shaft system of the hovercraft is long and contains many devices. All the devices in the cushioning shaft system need to be aligned and positioned for installation. In addition, there are horizontal and vertical axes in the cushioning shaft system, with multiple alignment dimensions and shaft segments, which makes alignment complex and difficult. At present, the installation method of the cushioning shaft system is to align all the equipment first, complete the inspection of all point data, and then proceed to the final installation. However, due to the large number of alignment points, the fact that aluminum products are greatly affected by ambient temperature and hull deformation, and the high accuracy requirements for shaft system alignment, any slight change in any point in the shaft system will cause changes in the data of all equipment in the entire shaft system. Alignment of points is time-consuming and laborious, and it is difficult to find a relatively stable state for inspection during alignment, making it impossible to proceed to the next step. Summary of the Invention

[0003] The purpose of the present invention is to provide an installation method for a cushion lifting shaft system of a hovercraft, which reduces the difficulty of centering, shortens the centering period, improves the installation efficiency of the cushion lifting shaft system, and reduces the workload.

[0004] To achieve this object, the present invention adopts the following technical solutions:

[0005] A method for installing a cushion lift shaft system of a hovercraft, the cushion lift shaft system comprising a gas turbine, a cushion lift main reducer, an accessory box, a stern cushion lift fan reducer and a bow cushion lift fan reducer arranged in sequence, the vertical output end of the stern cushion lift fan reducer is connected to the stern cushion lift fan, and the vertical output end of the bow cushion lift fan reducer is connected to the bow cushion lift fan, the cushion lift shaft system is divided into a first shaft section, a second shaft section, a third shaft section and a fourth shaft section, the first shaft section is from the stern cushion lift fan reducer to the accessory box, the second shaft section is from the stern cushion lift fan reducer to the bow cushion lift fan reducer, the third shaft section is from the stern cushion lift fan reducer to the stern cushion lift fan, and from the bow cushion lift fan reducer to the bow cushion lift fan, and the fourth shaft section is from the accessory box to the cushion lift main reducer; the installation method comprises:

[0006] The stern pad lift fan reducer is centrally positioned and installed on board;

[0007] The first shaft segment, the second shaft segment, the third shaft segment and the fourth shaft segment are respectively positioned and installed in a centering manner, wherein the first shaft segment, the second shaft segment and the third shaft segment are respectively positioned and installed with the stern pad lift fan reducer as a reference.

[0008] In some possible implementations, when the first shaft segment, the second shaft segment, the third shaft segment, and the fourth shaft segment are respectively aligned and positioned for installation, the steps include:

[0009] The first shaft segment is centrally positioned and installed;

[0010] Check whether the first shaft segment is properly aligned and positioned;

[0011] If yes, the fourth shaft segment is installed in a centering position.

[0012] In some possible implementations, the stern pad lift fan reducer is installed in a centrally positioned manner on a ship, including:

[0013] Install a flange and a blind plate at the vertical output end of the stern pad lift fan reducer, punch out the center point of the flange center on the blind plate, and place the stern pad lift fan reducer on the base below the enclosure shaft of the stern pad lift fan;

[0014] Using jacking bolts to preliminarily set the gap between the support surface of the stern pad lift fan reducer and the base;

[0015] Fix and lower a plumb bob at the theoretical data position of the hull, and move the stern pad lift fan reducer until the tip of the plumb bob coincides with the flange center of the stern pad lift fan reducer;

[0016] Remove the blind plate;

[0017] Install the quadrant on the flange and calibrate the stern lift fan reducer on a horizontal plane to ensure that the flange surface is level. At the same time, use a laser plummet to measure the flange center of the input end and the flange center of the horizontal output end of the stern lift fan reducer to ensure that the flange center of the input end and the stern base point are on the same axis, and the flange center of the horizontal output end and the bow base point are on the same axis;

[0018] Fix the stern pad lift fan reducer and the base.

[0019] In some possible implementations, the centering and positioning installation of the first shaft segment includes:

[0020] Using jacking bolts to preliminarily set the gap between the accessory box base and the pedestal;

[0021] A bearing is provided at the input end of the stern pad lift fan reducer, and a laser alignment instrument is set up between the input flange of the bearing and the output flange of the accessory box to align the accessory box and the bearing using the laser alignment instrument;

[0022] Adjust the distance between the output flange of the accessory box and the input flange of the bearing to meet the preset requirements.

[0023] In some possible implementations, the centering and positioning installation of the second shaft segment includes:

[0024] Install a flange and a blind plate at the vertical output end of the bow pad lift fan reducer, punch out the center point of the flange center on the blind plate, and place the bow pad lift fan reducer on the base below the bow pad lift fan enclosure;

[0025] Using jacking bolts to preliminarily set the gap between the support surface of the bow pad lift wind turbine reducer and the base;

[0026] Fix and lower a plumb bob at the theoretical data position of the hull, and move the bow pad lift fan reducer until the tip of the plumb bob coincides with the flange center of the bow pad lift fan reducer;

[0027] Remove the blind plate;

[0028] Install the quadrant on the flange and calibrate the bow pad lift fan reducer on the horizontal plane to ensure that the flange surface is level;

[0029] A bearing is provided at the input end of the stern pad lift fan reducer, and a laser plummet is set up between the output flange of the bearing and the input flange of the bow pad lift fan reducer, and the laser plummet is used to complete the alignment of the bearing and the bow pad lift fan reducer;

[0030] Fix the bow pad lift fan reducer and the base.

[0031] In some possible implementations, the stern pad lift fan reducer and the stern pad lift fan are installed in the same manner as the bow pad lift fan. When the third shaft segment is installed in a centering position, the stern pad lift fan reducer and the stern pad lift fan, and the bow pad lift fan reducer and the bow pad lift fan are installed separately. When the stern pad lift fan reducer and the stern pad lift fan are installed, the following steps are included:

[0032] A laser centering instrument is arranged between the vertical output end of the stern pad lift fan reducer and the stern pad lift fan;

[0033] Adjust the relative position of the stern pad lift fan and the stern pad lift fan reducer, and use a laser alignment tool to complete the alignment of the stern pad lift fan and the stern pad lift fan reducer;

[0034] Measure the distance between the vertical output end flange of the stern pad lift fan reducer and the input end flange of the stern pad lift fan to meet the preset requirements.

[0035] In some possible implementations, the fourth shaft segment, when being centrally positioned and installed, includes:

[0036] Using jacking bolts to preliminarily set the gap between the supporting surface of the main reducer and the base;

[0037] Hang a weight line on the output flange of the main reducer, check the end position of the weight line, and require that the end coincides with the preset rib position number and reaches the preset distance from the midship;

[0038] A bearing is provided at the input end of the accessory box, and a laser alignment instrument is set up between the input flange of the bearing and the output flange of the main reducer. The laser alignment tool is used to complete the alignment of the main reducer and the input end flange of the bearing.

[0039] In some possible implementations, the lifting shaft system further includes a gear coupling and a bearing. The installation method includes: before aligning and positioning the first shaft segment, the second shaft segment, the third shaft segment, and the fourth shaft segment, respectively, further including:

[0040] The gear coupling is stretched and the bearing is aligned.

[0041] In some possible implementations, the input end of the stern lift fan reducer, the input end and output end of the accessory box, and the output end of the lift main reducer are all provided with the gear coupling, and the stretching method of the gear coupling is the same, and the stretching method includes:

[0042] To adjust the theoretical position of the gear coupling, first push the gear coupling inward and turn the gear coupling at the same time. After reaching the axial thrust point of the gear coupling, use a depth gauge to measure the distance between the gear coupling and the shaft seal. Then pull the gear coupling out by 3mm to 4mm. During this process, use the depth gauge to measure and record the actual pull-out amount. When measuring, measure 4 points evenly distributed around the circumference and take the average value. The gear coupling is in the theoretical working position.

[0043] To center the gear coupling, clamp the first and second dial indicators on the shaft respectively, rotate the shaft system, record a data every 45°, and record the measured data. According to the calculation formula: measured runout value Lc = (first dial indicator - second dial indicator) / 2, calculate the diagonal point difference value. The deviation result of the gear coupling is not greater than 0.25mm / m. Measure the position diameter D, and the measured diagonal point difference value should be less than 0.25D.

[0044] In some possible implementations, there are seven bearings, including: a first bearing provided between the stern pad lift fan reducer and the accessory box, a second bearing, a third bearing, and a fourth bearing provided sequentially between the stern pad lift fan reducer and the bow pad lift fan reducer, and a fifth bearing, a sixth bearing, and a seventh bearing provided sequentially between the accessory box and the pad lift main reducer;

[0045] When the first shaft section is aligned and positioned for installation, a laser alignment instrument is used to sequentially align the first bearing and the stern pad lift fan reducer, and the accessory box and the first bearing;

[0046] When the second shaft segment is aligned and positioned for installation, a laser alignment instrument is used to sequentially align the second bearing and the stern pad lift fan reducer, the third bearing and the second bearing, and the fourth bearing and the third bearing;

[0047] When the fourth shaft segment is centered and positioned for installation, a laser centering instrument is used to sequentially align the fifth bearing and the accessory box, the sixth bearing and the fifth bearing, and the seventh bearing and the sixth bearing.

[0048] Beneficial effects of the present invention:

[0049] The present invention provides a method for installing a cushioned shaft system for a hovercraft. The cushioned shaft system primarily uses the stern cushioned fan reducer as a reference, with the input, horizontal, and vertical output terminals of the stern cushioned fan reducer serving as references for simultaneous alignment of the cushioned shaft system in multiple dimensions, bowward, sternward, and upward. The cushioned shaft system is divided into four sections, each of which is individually aligned and installed, one section at a time. This method reduces the impact of ambient temperature on overall alignment data, lowers alignment difficulty, enables parallel work, shortens the alignment cycle, improves cushioned shaft system installation efficiency, and reduces workload. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 is a schematic diagram of a lifting shaft system provided by a specific embodiment of the present invention;

[0051] Figure 2 is a flow chart of a method for installing a cushion lift shaft system of a hovercraft provided by a specific embodiment of the present invention;

[0052] Figure 3 This is a schematic diagram of the installation of a stern pad lift fan reducer provided by a specific embodiment of the present invention;

[0053] Figure 4 This is a schematic diagram of the "M" shape of the flange surface of the stern pad lift fan reducer provided by a specific embodiment of the present invention;

[0054] Figure 5 Schematic diagram of measuring the telescopic clearance of a gear coupling provided by a specific embodiment of the present invention;

[0055] Figure 6 This is a schematic diagram of centering measurement of a gear coupling provided by a specific embodiment of the present invention;

[0056] Figure 7 This is a schematic diagram of centering a bearing seat provided by a specific embodiment of the present invention;

[0057] Figure 8 This is a schematic diagram of centering the first shaft segment provided by a specific embodiment of the present invention;

[0058] Figure 9 This is a schematic diagram of centering the second shaft segment provided by a specific embodiment of the present invention;

[0059] Figure 10 This is a schematic diagram of centering the third shaft segment provided by a specific embodiment of the present invention;

[0060] Figure 11 It is a schematic diagram of centering the fourth shaft segment provided by a specific embodiment of the present invention.

[0061] In the picture:

[0062] 1. Gas turbine; 2. Main reducer for pad lift; 3. Accessory box; 4. Stern pad lift fan reducer; 5. Bow pad lift fan reducer; 6. Stern pad lift fan; 7. Bow pad lift fan; 8. First bearing; 9. Second bearing; 10. Third bearing; 11. Fourth bearing; 12. Fifth bearing; 13. Sixth bearing; 14. Seventh bearing; 15. Gear coupling;

[0063] 100, Laser alignment instrument; 200, First dial indicator; 300, Second dial indicator; 400, Third dial indicator; 500, Fourth dial indicator; 600, Bearing seat centering tool. DETAILED DESCRIPTION

[0064] To make the technical problems solved by the present invention, the technical solutions adopted, and the technical effects achieved more clearly, the technical solutions of the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making any creative efforts shall fall within the scope of protection of the present invention.

[0065] In the description of the present invention, unless otherwise expressly specified or limited, the terms "connected," "connected," and "fixed" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integration; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific circumstances.

[0066] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0067] like Figure 1 and Figure 2 As shown, the cushion lifting shaft system includes a gas turbine 1, a cushion lifting main reducer 2, an accessory box 3, a stern cushion lifting fan reducer 4 and a bow cushion lifting fan reducer 5 which are arranged in sequence. The vertical output end of the stern cushion lifting fan reducer 4 is connected to the stern cushion lifting fan 6, and the vertical output end of the bow cushion lifting fan reducer 5 is connected to the bow cushion lifting fan 7. This embodiment provides an installation method for a cushion lifting shaft system of a hovercraft, which divides the cushion lifting shaft system into a first shaft section, a second shaft section, a third shaft section and a fourth shaft section. The first shaft section is from the stern cushion lifting fan reducer 4 to the accessory box 3, the second shaft section is from the stern cushion lifting fan reducer 4 to the bow cushion lifting fan reducer 5, the third shaft section is from the stern cushion lifting fan reducer 4 to the stern cushion lifting fan 6, and the bow cushion lifting fan reducer 5 to the bow cushion lifting fan 7, and the fourth shaft section is from the accessory box 3 to the cushion lifting main reducer 2. The installation method includes:

[0068] S100, stern pad lift fan reducer 4 is centrally positioned and installed on board;

[0069] S300, the first shaft segment, the second shaft segment, the third shaft segment and the fourth shaft segment are respectively aligned and positioned and installed, wherein the first shaft segment, the second shaft segment and the third shaft segment are respectively positioned and installed with the stern pad lift fan reducer 4 as the reference.

[0070] The stern lift fan reducer 4 serves as the primary reference point for the stern lift fan reducer. The input, horizontal, and vertical output terminals of the stern lift fan reducer 4 serve as the reference points for simultaneous alignment of the stern lift shaft system in multiple dimensions, bow, stern, and upward. The stern lift shaft system is divided into four sections, each of which is individually aligned and installed, with each section aligned and installed one at a time. This reduces the impact of ambient temperature on overall alignment data, lowers alignment difficulty, enables parallel work, shortens alignment cycles, improves stern lift shaft system installation efficiency, and reduces workload.

[0071] Optionally, the lifting shaft system of the hovercraft includes two sets of the above structures, one set on each side, which are symmetrical and parallel to the centerline on both sides, and are installed in the same way.

[0072] Optionally, in step S300, the following steps are included:

[0073] S301, centering and positioning installation of the first shaft segment;

[0074] S302, check whether the centering, positioning and installation of the first shaft segment are qualified;

[0075] S303: If yes, the fourth shaft segment is aligned and positioned for installation; if no, the first shaft segment is continuously aligned and adjusted and inspected until it passes the test, thereby improving the alignment reliability.

[0076] Optionally, step S300 further includes:

[0077] S304, centering and positioning installation of the second shaft segment;

[0078] S305, alignment and positioning of the third shaft segment;

[0079] The first shaft segment, the second shaft segment and the third shaft segment can be installed in any order, or can be installed simultaneously without limitation.

[0080] like Figure 3 and Figure 4 As shown, in step S100, it includes:

[0081] S101. Install a flange and a blind plate at the vertical output end of the stern lift fan reducer 4, punch out the center point of the flange on the blind plate with a sample punch, and place the stern lift fan reducer 4 on the base below the enclosure of the stern lift fan 6; specifically, apply molybdenum disulfide on the spline of the vertical output shaft of the stern lift fan reducer 4, and install the adjustment ring and reducer flange assembly on the vertical output shaft neck of the reducer.

[0082] S102. Preliminarily set the gap between the supporting surface of the stern pad lift fan reducer 4 and the base using the jacking bolts. The gap is 0-25 mm.

[0083] S103. Fix and lower the plumb bob at the theoretical data position of the hull, and move the stern pad lift fan reducer 4 until the tip of the plumb bob coincides with the flange center of the stern pad lift fan reducer 4, with a deviation of no more than ±3 mm; the specific theoretical data position of the hull is the theoretical data from the centerline, baseline, and rib number.

[0084] S104, remove the blind plate;

[0085] S105. Install the quadrant on the flange and calibrate the stern lift fan reducer 4 on a horizontal plane to ensure the flange surface is level. Measure the "M"-shaped horizontality of the flange surface, with a deviation of no more than 10'. Simultaneously, use a laser plummet 100 to measure the flange center at the input end and the flange center at the horizontal output end of the stern lift fan reducer 4. Ensure that the input flange center and the stern base point are aligned on the same axis, and the horizontal output flange center and the bow base point are aligned on the same axis, with a deviation of no more than ±3mm.

[0086] S106: After the data is qualified, the stern pad lift fan reducer 4 and the base are fixed to prevent movement. Specifically, the stern pad lift fan reducer 4 and the base can be fixed using the tooling in the prior art.

[0087] In one embodiment, the stern pad lift fan reducer 4 positioning measurement table is shown in Table 1, and the flange surface "M" shape levelness measurement table is shown in Table 2. The actual measured values ​​are recorded in Tables 1 and 2, and the measured values ​​are compared with the theoretical values ​​to verify compliance. The measurement values ​​in the following tables can be filled in according to the actual measurement results.

[0088] Table 1 Stern pad lift fan reducer 4 positioning measurement table

[0089]

[0090] Table 2 Flange surface "M" shape levelness measurement table

[0091]

[0092] The lifting shaft system further includes a gear coupling 15 and a bearing. The installation method includes: before step S300, further including:

[0093] S200, stretching of gear coupling 15 and centering of bearings.

[0094] like Figure 5 and Figure 6 As shown, the input end of the stern lift fan reducer 4, the input end and output end of the accessory box 3, and the output end of the lift main reducer 2 are all provided with a gear coupling 15. The stretching method of the gear coupling 15 is the same, and the stretching method includes:

[0095] S201. Adjust the theoretical position of gear coupling 15. First, push gear coupling 15 inward while turning the gear coupling 15 to its axial thrust point. Use a depth gauge to measure the distance between gear coupling 15 and the shaft seal. Then, pull gear coupling 15 out 3 to 4 mm. During this process, measure and record the actual withdrawal amount using the depth gauge. Four points should be evenly spaced around the circumference and the average value should be taken. Gear coupling 15 is in its theoretical working position. The telescopic clearance measurement table for gear coupling 15 is shown in Table 3.

[0096] Table 3 Schematic diagram of measurement of telescopic clearance of gear coupling 15

[0097]

[0098] S202. Center the gear coupling 15. Place the first and second dial indicators 200 and 300 on the shaft, rotate the shaft, and record a reading every 45°. The measured data is then recorded. The diagonal point difference is calculated using the formula: measured runout value Lc = (first dial indicator 200 - second dial indicator 300) / 2. The deviation of the gear coupling 15 is no greater than 0.25 mm / m. The measured position diameter D should have a measured diagonal point difference of less than 0.25D. The centering measurement table for the gear coupling 15 is shown in Table 4.

[0099] Table 4 Gear coupling 15 centering measurement table

[0100]

[0101] There are seven bearings, including: the first bearing 8 located between the stern pad lift fan reducer 4 and the accessory box 3, the second bearing 9, the third bearing 10 and the fourth bearing 11 located between the stern pad lift fan reducer 4 and the bow pad lift fan reducer 5, and the fifth bearing 12, the sixth bearing 13 and the seventh bearing 14 located between the accessory box 3 and the pad lift main reducer 2. Since the bearing input and output are not completely stacked, each bearing seat must be aligned with the bearing seat housing and its internal shaft during installation to ensure that the deviation is no more than 0.6mm / m. The centering method for all bearings is the same, such as Figure 7 As shown, the centering methods include:

[0102] S203. The third and fourth dial indicators 400 and 500 are respectively fixed on the transmission shaft inside the bearing seat. Rotate the shaft system and record a data every 45°. Record the measured data and fill it into the table. According to the calculation formula: measured runout value Lc = (third dial indicator 400-fourth dial indicator 500) / 2, calculate the diagonal point difference value and measure the position diameter D. The measured diagonal point difference value is not greater than 0.6D. Figure 7 As shown in Table 5, a bearing seat centering tool 600 is set on the internal transmission shaft of the bearing seat, and the dial indicator tool is clamped on the shaft. The bearing seat centering tool 600 is an existing technology and will not be described in detail.

[0103] Table 5 Bearing seat centering measurement table

[0104]

[0105] Note: The bearing seat number includes port and starboard information and position information. The position information is 1-7 according to the power transmission direction. For example, the third bearing seat on the port side is recorded as: Left 3.

[0106] When aligning and positioning the first shaft section, the laser alignment instrument 100 is used to sequentially align the first bearing 8 and the stern pad lift fan reducer 4, and the accessory box 3 and the first bearing 8;

[0107] When aligning and positioning the second shaft section, use the laser alignment instrument 100 to align the second bearing 9 and the stern pad lift fan reducer 4, the third bearing 10 and the second bearing 9, and the fourth bearing 11 and the third bearing 10 in sequence.

[0108] When the fourth shaft section is aligned and positioned for installation, the laser alignment instrument 100 is used to sequentially align the fifth bearing 12 and the accessory box 3 , the sixth bearing 13 and the fifth bearing 12 , and the seventh bearing 14 and the sixth bearing 13 .

[0109] Specifically, when installing the bearing, the bending amount φ between the shaft of the device to be aligned and the shaft of the aligned device is required to be ≤ 0.25 mm / m, and the offset δ is required to be ≤ 0.20 mm, so that the bearing can be installed at the preset position of the shaft section.

[0110] like Figure 8 As shown, in step S301, it includes:

[0111] S3011. Preliminarily set the gap between the base of the accessory box 3 and the foundation using the jacking bolts. Specifically, weld a jacking fixture onto the foundation of the accessory box 3, and preliminarily set the distance between the base of the accessory box 3 and the hull foundation panel to 0-30 mm by adjusting the four M16 jacking bolts on the machine feet.

[0112] S3012. A bearing is provided at the input end of the stern pad lift fan reducer 4. A laser alignment instrument 100 is set up between the input flange of the bearing and the output flange of the accessory box 3. The laser alignment instrument 100 is used to align the accessory box 3 and the bearing. The curvature of the input flange of the intermediate bearing between the ship's accessory box 3 and No. 4 is required to be φ≤0.25mm / m, and the offset δ≤0.20mm.

[0113] S3013. Adjust the distance between the output flange of accessory box 3 and the input flange of the bearing to meet the preset requirements.

[0114] Specifically, before step S3011 , the process also includes the bearing installation and adjustment of the gear couplings 15 at both ends of the accessory box 3 .

[0115] like Figure 9 As shown, optionally, in step S304, the following steps are included:

[0116] S3041. Install a flange and a blind plate at the vertical output end of the bow pad lift fan reducer 5, punch out the center point of the flange center on the blind plate, and use a lifting tool to place the bow pad lift fan reducer 5 on the base below the bow pad lift fan 7 enclosure; specifically, apply molybdenum disulfide on the splines of the vertical output shaft of the bow pad lift fan reducer 5, and install the adjusting ring and reducer flange assembly on the vertical output shaft neck of the reducer.

[0117] S3042. Use the jacking bolts to preliminarily set the gap between the supporting surface of the bow pad lift wind turbine reducer 5 and the base. The gap is 0-25 mm.

[0118] S3043. Fix and lower a plumb bob at the theoretical hull position. Move the bow pad lift fan reducer 5 until the plumb bob's tip aligns with the flange center of the bow pad lift fan reducer 5. The deviation must not exceed ±3 mm. The theoretical hull position is the theoretical data from the centerline, baseline, and rib number. All theoretical data in this embodiment are based on existing technology and will not be repeated here.

[0119] S3044, remove the blind plate;

[0120] S3045. Install the quadrant on the flange and calibrate the bow pad lift fan reducer 5 on the horizontal plane to ensure that the flange surface is level with a deviation of no more than 10';

[0121] S3046. A bearing is provided at the input end of the stern pad lift fan reducer 4. A laser alignment instrument 100 is set up between the output flange of the bearing and the input flange of the bow pad lift fan reducer 5. The laser alignment instrument 100 is used to align the bearing and the bow pad lift fan reducer 5. Requirements: the bending amount φ ≤ 0.25 mm / m, the offset amount δ ≤ 0.20 mm.

[0122] S3047. Fix the bow pad lift fan reducer 5 and the base.

[0123] Before step S3041, the installation of three bearings is also completed.

[0124] like Figure 10 As shown, the installation method of the stern pad lift fan reducer 4 and the stern pad lift fan 6, and the installation method of the bow pad lift fan reducer 5 and the bow pad lift fan 7 are the same. In step S305, the stern pad lift fan reducer 4 and the stern pad lift fan 6, and the bow pad lift fan reducer 5 and the bow pad lift fan 7 are installed separately. They can be installed at the same time or in any order without limitation. Taking the installation of the stern pad lift fan reducer 4 and the stern pad lift fan 6 as an example, the installation steps include:

[0125] S3051. Arrange a laser centering device 100 between the vertical output end of the stern pad lift fan reducer 4 and the stern pad lift fan 6.

[0126] S3052. Adjust the relative position of the stern pad lift fan 6 and the stern pad lift fan reducer 4 by using a jacking tool such as in the prior art, and use a laser alignment tool to complete the alignment of the stern pad lift fan 6 and the stern pad lift fan reducer 4; requirements: bending amount φ ≤ 0.20 mm / m, offset amount δ ≤ 0.15 mm.

[0127] S3053. Measure the distance between the vertical output end flange of the stern pad lift fan reducer 4 and the input end flange of the stern pad lift fan 6 to meet the preset requirements.

[0128] like Figure 11 As shown, in step S303, it includes:

[0129] S3031. Use the jacking bolts to preliminarily set the gap between the supporting surface of the main reducer 2 and the base, the gap is 0-30mm; specifically, weld the jacking tooling on the base of the main reducer 2, and adjust the jacking bolts on the machine feet.

[0130] S3032. Hang a weight line on the output flange of the raised main reducer 2 and check the end position of the weight line. The end is required to coincide with the preset rib position and reach a preset distance from the midship. For example, the end is required to coincide with rib position #42, with an axial deviation of no more than ±3mm and a distance of 6000 from the midship, with a deviation of no more than ±3mm.

[0131] S3033. The input end of accessory box 3 is equipped with a bearing. Install a laser alignment tool 100 between the bearing's input flange and the output flange of the shim-lift final reducer 2. Use the laser alignment tool to align the shim-lift final reducer 2 with the bearing's input flange. Requirements: flexure φ ≤ 0.25 mm / m, offset δ ≤ 0.20 mm.

[0132] Specifically, before step S3031, the installation of three bearings is also included.

[0133] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A method for installing a cushion lift shaft system of a hovercraft, wherein the cushion lift shaft system comprises a combustion engine (1), a cushion lift main reducer (2), an accessory box (3), a stern cushion lift fan reducer (4), and a bow cushion lift fan reducer (5) arranged in sequence, wherein the vertical output end of the stern cushion lift fan reducer (4) is connected to the stern cushion lift fan (6), and the vertical output end of the bow cushion lift fan reducer (5) is connected to the bow cushion lift fan (7), characterized in that: The pad lift shaft system is divided into a first shaft section, a second shaft section, a third shaft section and a fourth shaft section, wherein the first shaft section is from the stern pad lift fan reducer (4) to the accessory box (3), the second shaft section is from the stern pad lift fan reducer (4) to the bow pad lift fan reducer (5), the third shaft section is from the stern pad lift fan reducer (4) to the stern pad lift fan (6), and the bow pad lift fan reducer (5) to the bow pad lift fan (7), and the fourth shaft section is from the accessory box (3) to the pad lift main reducer (2); the installation method comprises: The stern pad lift fan reducer (4) is centrally positioned and installed on the ship; The first shaft section, the second shaft section, the third shaft section and the fourth shaft section are respectively aligned and positioned and installed, wherein the first shaft section, the second shaft section and the third shaft section are respectively positioned and installed with the stern pad lift fan reducer (4) as a reference.

2. The method for installing the cushion lifting shaft system of the hovercraft according to claim 1, characterized in that: When the first shaft segment, the second shaft segment, the third shaft segment and the fourth shaft segment are respectively aligned and positioned for installation, the method includes: The first shaft segment is centrally positioned and installed; Check whether the first shaft segment is properly aligned and positioned; If yes, the fourth shaft segment is installed in a centering position.

3. The method for installing the cushion shaft system of the hovercraft according to claim 1, characterized in that: The stern pad lift fan reducer (4) is installed in a centrally positioned manner on a ship, comprising: Installing a flange and a blind plate at the vertical output end of the stern pad lift fan reducer (4), punching out the center point of the flange center on the blind plate, and placing the stern pad lift fan reducer (4) on the base below the enclosure of the stern pad lift fan (6); Using jacking bolts to preliminarily set the gap between the supporting surface of the stern pad lift fan reducer (4) and the base; A plumb bob is fixed and lowered at the theoretical data position of the hull, and the stern pad lift fan reducer (4) is moved until the tip of the plumb bob coincides with the flange center of the stern pad lift fan reducer (4); Remove the blind plate; The quadrant is mounted on the flange, and the stern pad lift fan reducer (4) is calibrated on a horizontal plane to ensure that the flange surface is horizontal. At the same time, a laser centering instrument (100) is used to measure the flange center of the input end and the flange center of the horizontal output end of the stern pad lift fan reducer (4) to ensure that the flange center of the input end and the stern base point are on the same axis, and the flange center of the horizontal output end and the bow base point are on the same axis; The stern pad lift fan reducer (4) is fixed to the base.

4. The method for installing a cushion shaft system of a hovercraft according to claim 1, characterized in that: The centering and positioning installation of the first shaft segment includes: Using jacking bolts to preliminarily set the gap between the base of the accessory box (3) and the foundation; The input end of the stern pad lift fan reducer (4) is provided with a bearing, and a laser alignment instrument (100) is set between the input flange of the bearing and the output flange of the accessory box (3), and the laser alignment instrument (100) is used to complete the alignment of the accessory box (3) and the bearing; The distance between the output flange of the accessory box (3) and the input flange of the bearing is adjusted to meet the preset requirements.

5. The method for installing the cushion shaft system of a hovercraft according to claim 1, characterized in that: The centering and positioning installation of the second shaft section includes: Install a flange and a blind plate at the vertical output end of the bow pad lift fan reducer (5), punch out the center point of the flange center on the blind plate, and place the bow pad lift fan reducer (5) on the base below the bow pad lift fan (7) enclosure; Using jacking bolts to preliminarily set the gap between the support surface of the bow pad lifting wind turbine reducer (5) and the base; A plumb bob is fixed at the theoretical data position of the hull and lowered, and the bow pad lift fan reducer (5) is moved until the tip of the plumb bob coincides with the flange center of the bow pad lift fan reducer (5); Remove the blind plate; Install the quadrant on the flange and calibrate the bow pad lift fan reducer (5) on the horizontal plane to ensure that the flange surface is horizontal; The input end of the stern pad lift fan reducer (4) is provided with a bearing, and a laser alignment instrument (100) is set up between the output flange of the bearing and the input flange of the bow pad lift fan reducer (5), and the laser alignment instrument (100) is used to complete the alignment of the bearing and the bow pad lift fan reducer (5); The bow pad lift fan reducer (5) is fixed to the base.

6. The method for installing a cushioning shaft system of a hovercraft according to claim 1, characterized in that: The stern pad lift fan reducer (4) and the stern pad lift fan (6) are installed in the same manner as the bow pad lift fan reducer (5) and the bow pad lift fan (7). When the third shaft section is centrally positioned and installed, the stern pad lift fan reducer (4) and the stern pad lift fan (6), as well as the bow pad lift fan reducer (5) and the bow pad lift fan (7) are installed separately. When the stern pad lift fan reducer (4) and the stern pad lift fan (6) are installed, the following steps are included: A laser centering instrument (100) is arranged between the vertical output end of the stern pad lift fan reducer (4) and the stern pad lift fan (6); Adjusting the relative position of the stern pad lift fan (6) and the stern pad lift fan reducer (4), and completing the centering work of the stern pad lift fan (6) and the stern pad lift fan reducer (4) using a laser centering tool; The distance between the vertical output end flange of the stern pad lift fan reducer (4) and the input end flange of the stern pad lift fan (6) is measured to meet the preset requirements.

7. The method for installing a cushioning shaft system of a hovercraft according to claim 1, characterized in that: The fourth shaft segment is aligned and positioned for installation, including: Using jacking bolts to preliminarily set the gap between the supporting surface of the main reducer (2) and the base; Hang a weight line on the output flange of the main reducer (2) and check the end position of the weight line, requiring the end to coincide with the preset rib position number and to reach a preset distance from the midship; The input end of the accessory box (3) is provided with a bearing, and a laser alignment instrument (100) is set up between the input flange of the bearing and the output flange of the pad-lift main reducer (2), and the laser alignment tool is used to complete the alignment work of the pad-lift main reducer (2) and the input end flange of the bearing.

8. The method for installing a cushion shaft system of a hovercraft according to any one of claims 1 to 7, characterized in that: The lifting shaft system further comprises a gear coupling (15) and a bearing. The installation method comprises: before the first shaft segment, the second shaft segment, the third shaft segment and the fourth shaft segment are respectively aligned and positioned for installation, the method further comprises: The gear coupling (15) is stretched and the bearing is aligned.

9. The method for installing a cushioning shaft system of a hovercraft according to claim 8, characterized in that: The input end of the stern lift fan reducer (4), the input end and output end of the accessory box (3), and the output end of the lift main reducer (2) are all provided with the gear coupling (15). The stretching method of the gear coupling (15) is the same, and the stretching method includes: The theoretical position adjustment of the gear coupling (15) is as follows: first, push the gear coupling (15) inward and rotate it at the same time until the axial thrust point of the gear coupling (15) is reached. Then, use a depth gauge to measure the distance between the gear coupling (15) and the shaft seal. Then, pull out the gear coupling (15) by 3 mm to 4 mm. During this process, measure and record the actual pull-out amount using the depth gauge. When measuring, measure 4 points evenly distributed around the circumference and take the average value. The gear coupling (15) is in the theoretical working position. To find the center of the gear coupling (15), the first dial indicator (200) and the second dial indicator (300) are respectively clamped on the shaft, the shaft system is rotated, and a data is recorded every 45°. The measured data is recorded, and the diagonal point difference value is calculated according to the calculation formula: measured runout value Lc = (first dial indicator (200) - second dial indicator (300)) / 2. The deviation result of the gear coupling (15) is not greater than 0.25mm / m. The measuring position diameter D, the measured diagonal point difference value should be less than 0.25D.

10. The method for installing a cushioning shaft system of a hovercraft according to claim 8, characterized in that: The bearings are provided with seven, including: a first bearing (8) provided between the stern pad lift fan reducer (4) and the accessory box (3), a second bearing (9), a third bearing (10) and a fourth bearing (11) provided in sequence between the stern pad lift fan reducer (4) and the bow pad lift fan reducer (5), and a fifth bearing (12), a sixth bearing (13) and a seventh bearing (14) provided in sequence between the accessory box (3) and the pad lift main reducer (2); When the first shaft section is centered and positioned for installation, a laser centering instrument (100) is used to sequentially complete the centering work of the first bearing (8) and the stern pad lift fan reducer (4), and the centering work of the accessory box (3) and the first bearing (8); When the second shaft section is aligned and positioned for installation, a laser alignment instrument (100) is used to sequentially align the second bearing (9) and the stern pad lift fan reducer (4), the third bearing (10) and the second bearing (9), and the fourth bearing (11) and the third bearing (10); When the fourth shaft segment is centered and positioned for installation, a laser centering instrument (100) is used to sequentially complete the centering work of the fifth bearing (12) and the accessory box (3), the sixth bearing (13) and the fifth bearing (12), and the seventh bearing (14) and the sixth bearing (13).

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