Gas turbine rotor supporting structure

Abstract

The utility model discloses a gas turbine rotor supporting structure which comprises a first cylindrical roller bearing arranged on a rotor of a gas turbine; the working surface of the first thrust bearing is matched with the working surface of the first thrust disc; the grating scale is arranged on the rotor; and the grating reading probe faces the grating scale and is used for detecting the displacement of the grating scale in the axial direction of the rotor. According to the application, the first thrust bearing is arranged to support the axial force of the rotor, compared with a ball bearing, the first thrust bearing has larger axial force bearing capacity, and the axial force of the rotor does not need to be tested and adjusted before the gas turbine leaves a factory. By arranging the grating scale and the grating reading probe, the displacement amount of the rotor is monitored in real time in the using process of the gas turbine, then the abrasion degree and the remaining life of the first thrust bearing are reflected in real time, a corresponding maintenance plan is made, and the risks of temporary shutdown and unplanned maintenance do not exist.

Description

Technical Field

[0001] The present application relates to the field of gas turbines, and in particular to a gas turbine rotor support structure. Background Art

[0002] In a gas turbine, the rotor of the gas turbine often needs to be supported by bearings. Currently, a cylindrical roller bearing and a ball bearing support structure are usually used. The cylindrical roller bearing bears most of the weight of the rotor, while the ball bearing bears a small part of the weight of the rotor and its axial force. The axial force refers to the combined force applied by the rotor to the bearing in the axial direction. When the axial force is large, it will accelerate the wear of the ball bearing; when the axial force is small, it will cause the ball bearing to slip, damage the surface of the ball bearing, increase vibration, and reduce the service life of the ball bearing.

[0003] Therefore, if ball bearings are used, the axial force of the rotor must be adjusted to an appropriate range before the gas turbine leaves the factory. However, even if the axial force of the rotor is adjusted to an appropriate range before the gas turbine leaves the factory, the wear degree and remaining life of the ball bearing cannot be evaluated during use, so there is a risk of temporary shutdown and unplanned maintenance. Utility Model Content

[0004] The present application proposes a gas turbine rotor support structure, which aims to solve the problems of the rotor support structure mentioned in the background technology, that is, the need to adjust the axial force of the rotor before the gas turbine leaves the factory, and the inability to assess the degree of wear and remaining life of the ball bearings during use after leaving the factory, resulting in the risk of temporary shutdown and unplanned maintenance.

[0005] In an embodiment of the present application, a gas turbine rotor support structure is proposed, comprising:

[0006] a first cylindrical roller bearing, wherein the first cylindrical roller bearing is disposed on the rotor of the gas turbine, and the first cylindrical roller bearing is used to bear the gravity and radial vibration load of the rotor;

[0007] A first thrust plate and a first thrust bearing, wherein the first thrust plate is disposed on the rotor, a working surface of the first thrust plate is perpendicular to the axial direction of the rotor, and a working surface of the first thrust bearing is adapted to a working surface of the first thrust plate;

[0008] A grating scale, wherein the grating scale is arranged on the rotor;

[0009] A grating reading probe is directed toward the grating scale, and is used to detect the displacement of the grating scale in the axial direction of the rotor.

[0010] In an embodiment of the present application, the gas turbine rotor support structure further includes:

[0011] A second thrust plate and a second thrust bearing, wherein the second thrust plate is arranged on the rotor, the working surface of the second thrust plate is perpendicular to the axial direction of the rotor, and the working surface of the second thrust bearing is adapted to the working surface of the second thrust plate; the thrust direction of the second thrust plate and the second thrust bearing is opposite to the thrust direction of the first thrust plate and the first thrust bearing.

[0012] In an embodiment of the present application, the first thrust bearing and the second thrust bearing both include:

[0013] A mounting plate, wherein the mounting plate is provided with a through hole, and the through hole is used for sleeve mounting the rotor;

[0014] A plurality of ribs, wherein the plurality of ribs extend from the edge of the through hole along the radial direction of the through hole toward the edge of the mounting plate, and the plurality of ribs are evenly distributed along the circumference of the mounting plate;

[0015] There are corresponding pillars and isolation plates between two adjacent rib columns. The isolation plate is located on the side of the pillar away from the mounting plate. Each isolation plate is provided with a thrust block on the side facing its corresponding pillar. The side of the thrust block facing the pillar is an arc surface, and the arc surface abuts against the corresponding pillar.

[0016] In the embodiment of the present application, the mounting plate is provided with an oil supply nozzle, and each rib column is provided with an oil supply pipe, and each of the oil supply pipes is connected to the oil supply nozzle;

[0017] A plurality of oil injection nozzles are arranged on one side of each rib column close to the mounting plate and on one side away from the mounting plate.

[0018] In an embodiment of the present application, a plurality of fuel injectors on a side of any rib column away from the mounting plate are distributed in two rows, and the two rows of fuel injectors are respectively distributed at the edge positions of the rib column close to the isolation plates on both sides thereof, and on the rotation path of the rotor on the rib column, the number and aperture of the fuel injectors in the front row of the rotation path are smaller than the number and aperture of the fuel injectors in the rear row of the rotation path.

[0019] In an embodiment of the present application, the gas turbine rotor support structure further includes:

[0020] A second cylindrical roller bearing, the second cylindrical roller bearing is arranged on the rotor, and in the axial direction of the rotor, the second cylindrical roller bearing and the first cylindrical roller bearing are spaced apart, the second cylindrical roller bearing and the first cylindrical roller bearing are located on the same side of each thrust bearing, and the first cylindrical roller bearing and the second cylindrical roller bearing jointly bear the gravity and radial vibration load of the rotor.

[0021] In the embodiment of the present application, the first thrust plate and the first thrust bearing are eliminated, and the cylindrical roller bearing close to the first thrust plate is replaced by a ball bearing.

[0022] In an embodiment of the present application, the grating scale is located between the ball bearing and the second thrust plate.

[0023] In the embodiment of the present application, the second thrust plate and the second thrust bearing are eliminated, and the cylindrical roller bearing close to the second thrust plate is replaced by a ball bearing.

[0024] In the embodiment of the present application, the grating scale is located on a side of the first thrust plate away from the ball bearing.

[0025] In the embodiment of the present application, when the gas turbine rotor is subjected to axial force in only a single direction, a first thrust plate and a first thrust bearing are provided to support the axial force of the rotor. Compared with the use of ball bearings, the first thrust plate and the first thrust bearing can provide a larger axial force bearing capacity. Therefore, there is no need to test or adjust the axial force of the rotor before the gas turbine leaves the factory. In addition, by providing a grating scale and a grating reading probe, the displacement of the rotor can be monitored in real time during the use of the gas turbine, so that the wear degree and the remaining life of the first thrust bearing can be reflected in real time, and then a corresponding maintenance plan can be formulated without the risk of temporary shutdown and unplanned maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0027] Figure 1 This is a schematic structural diagram of a gas turbine rotor support structure in one embodiment of the present application;

[0028] Figure 2 It is a schematic structural diagram of a thrust bearing in one embodiment of the present application;

[0029] Figure 3 for Figure 2 A cross-sectional view of the thrust bearing AA in FIG.

[0030] Figure 4 This is a schematic structural diagram of a gas turbine rotor support structure in another embodiment of the present application;

[0031] Figure 5This is a schematic structural diagram of a gas turbine rotor support structure in yet another embodiment of the present application.

[0032] Description of reference numerals:

[0033] 100-first cylindrical roller bearing, 110-second cylindrical roller bearing, 200-first thrust bearing, 210-second thrust bearing, 230-mounting plate, 231-perforation, 232-rib column, 233-isolation plate, 234-thrust block, 235-arc surface, 236-pillar, 237-oil supply nozzle, 238-oil supply pipe, 239-oil injection nozzle, 240-threaded hole, 300-first thrust plate, 310-second thrust plate, 400-rotor, 500-grating scale, 510-grating reading probe, 600-ball bearing.

[0034] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0036] It should be noted that if the embodiments of the present application involve directional indications (such as up, down, left, right, front, back...), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0037] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or suggesting their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0038] like Figure 1 As shown, the embodiment of the present application provides a gas turbine rotor support structure, including:

[0039] A first cylindrical roller bearing 100, wherein the first cylindrical roller bearing 100 is disposed on the rotor 400 of the gas turbine, and the first cylindrical roller bearing 100 is used to bear the gravity and radial vibration load of the rotor 400;

[0040] A first thrust plate 300 and a first thrust bearing 200, wherein the first thrust plate 300 is disposed on the rotor 400, the working surface of the first thrust plate 300 is perpendicular to the axial direction of the rotor 400, and the working surface of the first thrust bearing 200 is adapted to the working surface of the first thrust plate 300;

[0041] A grating scale 500, wherein the grating scale 500 is disposed on the rotor 400;

[0042] A grating reading probe 510 is directed toward the grating scale 500 , and is used to detect the displacement of the grating scale 500 in the axial direction of the rotor 400 .

[0043] like Figure 1 As shown, the first cylindrical roller bearing 100 is sleeved on the rotor 400. The first cylindrical roller bearing 100 mainly supports the gravity and radial vibration load of the rotor 400. In the axial direction of the rotor 400, the first cylindrical roller bearing 100 does not bear the axial force of the rotor 400, that is, within an appropriate range, the rotor 400 can move along the first cylindrical roller bearing 100 in its axial direction.

[0044] Continue to refer to Figure 1 The first thrust plate 300 may be made of wear-resistant steel and is fixedly disposed on the rotor 400 to remain relatively stationary with the rotor 400 .

[0045] like Figure 2 , Figure 3 As shown, in the embodiment of the present application, the first thrust bearing 200 includes:

[0046] A mounting plate 230, wherein the mounting plate 230 is provided with a through hole 231, wherein the through hole 231 is used to sleeve the rotor 400, and a plurality of ribs 232 are provided on one side surface of the mounting plate 230, wherein the plurality of ribs 232 extend from the edge of the through hole 231 along the radial direction of the through hole 231 toward the edge of the mounting plate 230, and the plurality of ribs 232 are evenly distributed along the circumference of the mounting plate 230;

[0047] There are corresponding pillars 236 and isolation plates 233 between two adjacent rib columns 232. The isolation plate 233 is located on the side of the pillar 236 away from the mounting plate 230. Each isolation plate 233 is provided with a thrust block 234 on the side facing its corresponding pillar 236. The side of the thrust block 234 facing the pillar 236 is an arc surface 235, and the arc surface 235 abuts against its corresponding pillar 236.

[0048] Among them, Figure 2 As shown, the outer contour of the mounting plate 230 is circular, and the through hole 231 is arranged at the center of the mounting plate 230, so the mounting plate 230 is roughly annular. In the embodiment of the present application, eight ribs 232 are arranged, and the eight ribs 232 extend along the radial direction of the mounting plate 230 and are distributed along the circumference of the mounting plate 230. The eight ribs 232 divide the annular mounting plate 230 into eight areas, and each area is provided with a corresponding pillar 236, thrust block 234 and isolation disk 233. Among them, along the axial direction of the mounting plate, the isolation disk 233 is located at the outermost side, the thrust block 234 is located in the middle, and the pillar 236 is located on the inner side. The side of the thrust block 234 close to the isolation disk 233 is fixedly connected to the isolation disk 233, and the side of the thrust block 234 close to the pillar 236 is a circular arc surface 235 and abuts against the pillar 236. In addition, a plurality of threaded holes 240 are also provided at the edge of the mounting plate 230.

[0049] When in use, the first thrust bearing 200 is sleeved on the rotor 400 by using the through hole 231, and each isolation disk 233 is abutted against the first thrust disk 300, and then the first thrust bearing 200 is fixed to the gas turbine by using the threaded hole 240 on the mounting plate 230. When the rotor 400 is subjected to an axial force, the first thrust disk 300 applies pressure to each isolation disk 233. Since the thrust block 234 corresponding to each isolation disk 233 abuts against the support 236 on a circular arc surface 235, each isolation disk 233 can be tilted in a small range on the support 236, so that the first thrust bearing 200 can bear a large axial force.

[0050] like Figure 2 , Figure 3 As shown, in the embodiment of the present application, an oil supply nozzle 237 is provided on the mounting plate 230, and an oil supply pipe 238 is provided in each rib column 232, and each of the oil supply pipes 238 is connected to the oil supply nozzle 237; each rib column 232 is provided with a plurality of oil nozzles 239 on the side close to the mounting plate 230 and the side away from the mounting plate 230.

[0051] Among them, Figure 2 , Figure 3As shown, in the embodiment of the present application, each rib column 232 can be hollow inside to form an oil supply pipe 238, and the oil supply pipes 238 of each rib column 232 can be interconnected at the inner ring position of the circular ring formed by the mounting plate 230, so that an oil supply nozzle 237 is set on the mounting plate 230 to supply oil to the oil supply pipes 238 inside each rib column 232.

[0052] In addition, the side of the rib column 232 away from the mounting plate 230 is Figure 3 The left side of the rib column 232 near the mounting plate 230 is Figure 3 On the right side of the orientation shown, Figure 3 In the orientation shown, multiple oil spray nozzles 239 are arranged on the left and right sides of the rib column 232. The left side of the rib column 232 faces the first thrust plate 300, so the oil spray nozzle 239 located on the left side of the rib column 232 can spray oil onto the first thrust plate 300. When the first thrust plate 300 rotates with the rotor 400, the oil sprayed by the oil spray nozzle 239 will diffuse between the first thrust plate 300 and each isolation plate 233 and form a floating oil film, thereby playing the role of lubrication, vibration reduction, and wear resistance for the first thrust plate 300 and each isolation plate 233. Figure 3 In the shown orientation, the right side of the rib column 232 is close to the position where the thrust block 234 and the support column 236 abut each other. Therefore, the oil sprayed from the oil nozzle 239 on the right side of the rib column 232 can play the role of lubrication, vibration reduction, and wear resistance for each thrust block 234 and the support column 236.

[0053] like Figure 2 As shown, in the embodiment of the present application, the multiple fuel injectors 239 on the side of any rib column 232 away from the mounting plate 230 are distributed in two rows, and the two rows of fuel injectors 239 are respectively distributed on the edge positions of the rib column 232 close to the isolation plates 233 on both sides thereof, and on the rotation path of the rotor 400 on the rib column 232, the number and aperture of the fuel injectors 239 in the front row of the rotation path are smaller than the number and aperture of the fuel injectors 239 in the rear row.

[0054] like Figure 2 As shown, Figure 2 The front side of the orientation shown is the side of the rib column 232 away from the mounting plate 230. In the embodiment of the present application, each rib column 232 is provided with eight oil spray nozzles 239 on the side away from the mounting plate 230, wherein the eight oil spray nozzles 239 are distributed in two rows, and both sides of the rib column 232 are isolation disks 233, and the two rows of oil spray nozzles 239 are respectively located at the edge of the rib column 232 near the isolation disks 233 on both sides thereof. Assuming that the first thrust bearing 200 is installed on the rotor 400 and will rotate clockwise, then if Figure 2As shown, for the oil injection nozzles 239 on the same rib column 232, the number of the oil injection nozzles 239 located in the front row of the rotation path of the first thrust bearing 200 is small and the aperture is small, while the number of the oil injection nozzles 239 located in the rear row of the rotation path of the first thrust bearing 200 is large and the aperture is large. Figure 2 As shown, in the embodiment of the present application, three oil nozzles 239 are arranged in one of the two rows of oil nozzles 239, and five oil nozzles 239 are arranged in one row. When the first thrust plate 300 rotates clockwise, the first thrust plate 300 passes through the three oil nozzles 239 arranged in a row at the same position, and then passes through the five oil nozzles 239 arranged in a row. After passing through the five oil nozzles 239 arranged in a row, it contacts the isolation plate 233. The five oil nozzles 239 arranged in a row not only have large apertures but also have a large number of them, so they can provide more oil, which is convenient for forming a floating oil film between the first thrust plate 300 and the isolation plate 233. It should be noted that Figure 2 The thrust bearing shown only shows the oil nozzle 239 on the side of one of the ribs 232 away from the mounting plate 230, while the other ribs 232 and the oil nozzles 239 on the side close to the mounting plate 230 are not shown. However, this does not mean that there are no oil nozzles 239 thereon.

[0055] In an embodiment of the present application, 4-8 fuel nozzles 239 can be set on the side of each rib column 232 away from the mounting plate 230, and the aperture of each fuel nozzle 239 can be between 1-1.4 mm; 2-4 fuel nozzles 239 can be set on the side of each rib column 232 close to the mounting plate 230, and the aperture of each fuel nozzle 239 can be between 0.5-0.7 mm.

[0056] In the embodiment of the present application, a babbitt alloy wear-resistant coating may be provided on the working surface of the isolation disk 233 (ie, the side away from the support 236 ) so that the wear of the isolation disk 233 during operation becomes slow.

[0057] Continue to refer to Figure 1The grating scale 500 is set on the rotor 400 and remains relatively still with the rotor 400. The grating reading probe 510 faces the grating scale 500. The detection position of the grating reading probe 510 remains unchanged. When the rotor 400 is displaced in the axial direction by the axial force, the grating scale 500 will be displaced synchronously with the rotor 400. The grating reading probe 510 can detect the displacement of the grating scale 500. The displacement of the grating scale 500 is the displacement of the rotor 400. Therefore, the displacement of the grating scale 500 can reflect the displacement of the rotor 400. The displacement of the rotor 400 can indirectly reflect the wear degree and remaining life of the first thrust bearing 200. For example, the greater the displacement of the rotor 400, the higher the wear degree of the first thrust bearing 200 and the shorter the remaining life. When the displacement of the rotor 400 reaches a certain set value, it can be determined that the service life of the first thrust bearing 200 has ended.

[0058] After introducing the specific structures of the various components of the gas turbine rotor support structure, the gas turbine rotor support structure is described as a whole based on the axial force on the gas turbine rotor 400. The axial force on the gas turbine rotor 400 is uncertain. For example, the rotor 400 of some gas turbines is only subjected to axial forces in a single direction, while the rotor 400 of some gas turbines may be subjected to axial forces in two directions. Figure 1 As shown, in Figure 1 In the orientation shown, the gas turbine rotor 400 is subjected to axial force in only one direction, which can be divided into the following situations:

[0059] Case 1: only subjected to leftward axial force;

[0060] Case 2: Only subjected to rightward axial force.

[0061] Continue to refer to Figure 1 ,exist Figure 1 In the orientation shown, the gas turbine rotor 400 is subjected to axial forces in two directions, which can be divided into the following situations:

[0062] Case 3: Subject to large axial forces to the left and right;

[0063] Case 4: The axial force to the right is larger, and the axial force to the left is smaller or negligible;

[0064] Case 5: The axial force to the left is larger, and the axial force to the right is smaller or negligible.

[0065] Next, the gas turbine rotor support structure in the present application is described in detail based on the above-mentioned case one, case two, case three, case four and case five respectively.

[0066] For case one

[0067] In the embodiment of the present application, Figure 1 In the orientation shown, the rotor 400 is only subjected to a horizontal leftward axial force, so in the axial direction of the rotor 400, the first thrust plate 300 can be arranged on the right side of the first thrust bearing 200, the working surface of the first thrust plate 300 is the surface in contact with the first thrust bearing 200, the working surface of the first thrust plate 300 faces the left side, the working surface of the first thrust bearing 200 is the surface in contact with the first thrust plate 200, the working surface of the first thrust bearing 200 faces the right side, and the working surface of the first thrust plate 300 is in contact with and adapted to the working surface of the first thrust bearing 200. When the rotor 400 is subjected to a horizontal leftward axial force, the working surface of the first thrust plate 300 abuts against the working surface of the first thrust bearing 200, and then the first thrust bearing 200 plays a role in bearing the horizontal leftward axial force of the rotor 400.

[0068] For case 2

[0069] In the embodiments of the present application, Figure 1 As shown, in Figure 1 In the orientation shown, the rotor 400 is only subjected to a horizontal axial force to the right. At this time, the first thrust plate 300 can be arranged on the left side of the first thrust bearing 200, and the working surface of the first thrust plate 300 is facing the right side, and the working surface of the first thrust bearing 200 is facing the left side and in contact with the working surface of the first thrust plate 300, so that the first thrust bearing 200 can play the role of bearing the horizontal axial force of the rotor 400 to the right.

[0070] In the embodiment of the present application, when the gas turbine rotor is subjected to axial force in only one direction, the first thrust plate 300 and the first thrust bearing 200 are provided to support the axial force of the rotor 400. Compared with the use of ball bearings, the first thrust plate 300 and the first thrust bearing 200 thrust bearing can provide a larger axial force bearing capacity. Therefore, there is no need to test and adjust the axial force of the rotor 400 before the gas turbine leaves the factory. In addition, by providing a grating scale 500 and a grating reading probe 510, the displacement of the rotor 400 can be monitored in real time during the use of the gas turbine, so that the wear degree and remaining life of the first thrust bearing 200 can be reflected in real time, and then a corresponding maintenance plan can be formulated, without the risk of temporary shutdown and unplanned maintenance.

[0071] For case three

[0072] like Figure 1 As shown, in Figure 1In the orientation shown, assuming that the rotor 400 is subjected to both horizontal axial forces to the left and horizontal axial forces to the right, if only the first thrust plate 300 and the first thrust bearing 200 are provided, it is not possible to stop the axial forces in both the left and right directions. In this case, a second thrust plate 310 and a second thrust bearing 210 may be additionally provided on the basis of the first thrust plate 300 and the first thrust bearing 200.

[0073] like Figure 1 As shown, in the embodiment of the present application, the gas turbine rotor support structure also includes: a second thrust plate 310 and a second thrust bearing 210, the second thrust plate 310 is arranged on the rotor 400, the working surface of the second thrust plate 310 is perpendicular to the axial direction of the rotor 400, and the working surface of the second thrust bearing 210 is adapted to the working surface of the second thrust plate 310; the thrust direction of the second thrust plate 310 and the second thrust bearing 210 is opposite to the thrust direction of the first thrust plate 300 and the first thrust bearing 200.

[0074] The structures of the second thrust plate 310 and the second thrust bearing 210 are the same as those of the first thrust plate 300 and the first thrust bearing 200, and are not described in detail here. The difference is that the thrust direction of the second thrust plate 310 and the second thrust bearing 210 is opposite to that of the first thrust plate 300 and the first thrust bearing 200. Figure 1 As shown, in Figure 1 In the illustrated position, the first thrust plate 300 is located on the right side of the first thrust bearing 200, and the thrust direction formed by the two is from left to right to form a thrust on the rotor 400, while the second thrust plate 310 is located on the left side of the second thrust bearing 210, and the thrust direction formed by the two is from right to left to form a thrust on the rotor 400. In addition, it should be noted that in other embodiments, the first thrust plate 300 can also be arranged on the left side of the first thrust bearing 200, and the thrust direction formed by the two is from right to left to form a thrust on the rotor 400, while the second thrust plate 310 is arranged on the right side of the second thrust bearing 210, and the thrust direction formed by the two is from left to right to form a thrust on the rotor 400.

[0075] In the embodiment of the present application, when the rotor 400 is subjected to axial forces in two directions, its radial load may be large, and when repeatedly subjected to axial forces in two directions, the rotor 400 has a higher risk of deformation. Therefore, a cylindrical roller bearing may be further provided to increase the radial load capacity and prevent the rotor 400 from deforming.

[0076] like Figure 1As shown, in the embodiment of the present application, the gas turbine rotor support structure also includes a second cylindrical roller bearing 110, which is arranged on the rotor 400. In the axial direction of the rotor 400, the second cylindrical roller bearing 110 and the first cylindrical roller bearing 100 are spaced apart, and the second cylindrical roller bearing 110 and the first cylindrical roller bearing 100 are located on the same side of each thrust bearing, and the first cylindrical roller bearing 100 and the second cylindrical roller bearing 110 jointly bear the gravity and radial vibration load of the rotor 400.

[0077] In the embodiment of the present application, Figure 1 In the orientation shown, the first thrust bearing 200 is located on the right side of the second thrust bearing 210, and the second cylindrical roller bearing 110 and the first cylindrical roller bearing 100 are located on the same side of each thrust bearing, for example, the first cylindrical roller bearing 100 and the second cylindrical roller bearing 110 are both located on the left side of the second thrust bearing 210, or the first cylindrical roller bearing 100 and the second cylindrical roller bearing 110 are both located on the right side of the first thrust bearing 210. The provision of two cylindrical roller bearings can improve the ability to bear the gravity of the rotor 400, and can also improve the ability to bear the radial load of the rotor 400, and the two cylindrical roller bearings are arranged at intervals, which can also prevent the rotor 400 from tilting or bending in the radial direction to a certain extent, and prevent its deformation. It is mentioned above that for a gas turbine, the axial force on its rotor 400 is uncertain. When subjected to axial forces in two directions at the same time, one direction may be subjected to a larger axial force, while the other direction may be subjected to a smaller axial force or almost no axial force. At this time, a ball bearing 600 can be provided to stop thrust in the direction where the axial force is small or almost non-existent. In addition, since the ball bearing 600 also has the function of bearing a certain gravity, a cylindrical roller bearing can be eliminated when the ball bearing 600 is provided. Then, not only can the thrust be stopped in the direction where the axial force is small, but also the rotor 400 can be prevented from tilting or bending in the radial direction.

[0078] For case four

[0079] like Figure 4 As shown, in the embodiment of the present application, Figure 4 In the orientation shown, the axial force of the rotor 400 from left to right is larger, and the axial force from right to left is smaller. Figure 1On the basis of the gas turbine rotor support structure shown in the figure, the first thrust plate 300 and the first thrust bearing 200 are eliminated, and the cylindrical roller bearing (i.e., the second cylindrical roller bearing 110) close to the first thrust plate 300 is replaced by a ball bearing 600. The ball bearing 600 has a relatively small ability to bear axial force, so it can be used to bear the axial force of the rotor 400 from right to left, and at the same time bear part of the gravity and radial load of the rotor 400, while the second thrust bearing 210 has a relatively large ability to bear axial force, so it is used to bear a relatively large axial force from left to right.

[0080] In addition, if Figure 4 As shown, in the embodiment of the present application, the grating scale 500 can also be arranged between the ball bearing 600 and the second thrust plate 310 .

[0081] For case five

[0082] like Figure 5 As shown, in the embodiment of the present application, Figure 5 In the orientation shown, the axial force of the rotor 400 from left to right is small, and the axial force from right to left is large. Figure 1 On the basis of the gas turbine rotor support structure shown in the figure, the second thrust plate 310 and the second thrust bearing 210 are eliminated, and the cylindrical roller bearing near the second thrust plate 310 is replaced by a ball bearing 600. The ball bearing 600 has a relatively small ability to bear axial force, so it can be used to bear the axial force of the rotor 400 from left to right, and at the same time bear part of the gravity and radial load of the rotor 400, while the first thrust bearing 200 has a relatively large ability to bear axial force, so it is used to bear a relatively large axial force from right to left.

[0083] In addition, if Figure 5 As shown, the grating scale 500 can also be arranged on the side of the first thrust plate 300 away from the ball bearing 600, that is, Figure 5 The right side of the first thrust plate 300 in the orientation shown.

[0084] In the embodiment of the present application, when the gas turbine rotor 400 is subjected to a single-direction axial force, a first thrust bearing 200 is provided to support the axial force of the rotor 400. Compared with the ball bearing 600, the first thrust bearing 200 has a larger axial force bearing capacity. Therefore, it is not necessary to test and adjust the axial force of the rotor 400 before the gas turbine leaves the factory. In addition, by providing a grating scale 500 and a grating reading probe 510, the displacement of the rotor 400 can be monitored in real time during the use of the gas turbine, so that the wear degree and the remaining life of the first thrust bearing 200 can be reflected in real time, and a corresponding maintenance plan can be formulated. There is no risk of temporary shutdown and unplanned maintenance; when subjected to large axial forces in two directions, two sets of corresponding thrust plates and thrust bearings can be used to bear the high axial forces in two directions respectively; when the axial force in one direction is small and the axial force in the other direction is large, a thrust plate and a thrust bearing can be used to bear the larger axial force, and a ball bearing 600 can be used to bear the smaller axial force. In addition, since the ball bearing 600 has the ability to bear gravity and radial loads, the ball bearing 600 can cooperate with a cylindrical roller bearing to prevent the rotor 400 from deforming.

[0085] The above description is only an optional embodiment of the present application, and does not limit the patent scope of the present application. All equivalent structural transformations made by using the contents of the present application specification and drawings under the inventive concept of the present application, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present application.

Claims

1. A gas turbine rotor support structure, characterized in that: include: a first cylindrical roller bearing, wherein the first cylindrical roller bearing is disposed on the rotor of the gas turbine, and the first cylindrical roller bearing is used to bear the gravity and radial vibration load of the rotor; A first thrust plate and a first thrust bearing, wherein the first thrust plate is disposed on the rotor, a working surface of the first thrust plate is perpendicular to the axial direction of the rotor, and a working surface of the first thrust bearing is adapted to a working surface of the first thrust plate; A grating scale, wherein the grating scale is arranged on the rotor; A grating reading probe is directed toward the grating scale, and is used to detect the displacement of the grating scale in the axial direction of the rotor.

2. The gas turbine rotor support structure according to claim 1, characterized in that: The gas turbine rotor support structure further comprises: A second thrust plate and a second thrust bearing, wherein the second thrust plate is arranged on the rotor, the working surface of the second thrust plate is perpendicular to the axial direction of the rotor, and the working surface of the second thrust bearing is adapted to the working surface of the second thrust plate; the thrust direction of the second thrust plate and the second thrust bearing is opposite to the thrust direction of the first thrust plate and the first thrust bearing.

3. The gas turbine rotor support structure according to claim 2, characterized in that: The first thrust bearing and the second thrust bearing each include: A mounting plate, wherein the mounting plate is provided with a through hole, and the through hole is used for sleeve mounting the rotor; A plurality of ribs, wherein the plurality of ribs extend from the edge of the through hole along the radial direction of the through hole toward the edge of the mounting plate, and the plurality of ribs are evenly distributed along the circumference of the mounting plate; There are corresponding pillars and isolation plates between two adjacent rib columns. The isolation plate is located on the side of the pillar away from the mounting plate. Each isolation plate is provided with a thrust block on the side facing its corresponding pillar. The side of the thrust block facing the pillar is an arc surface, and the arc surface abuts against the corresponding pillar.

4. The gas turbine rotor support structure according to claim 3, characterized in that: The mounting plate is provided with an oil supply nozzle, and each rib column is provided with an oil supply pipe, and each of the oil supply pipes is connected to the oil supply nozzle; A plurality of oil injection nozzles are arranged on one side of each rib column close to the mounting plate and on one side away from the mounting plate.

5. The gas turbine rotor support structure according to claim 4, characterized in that: The multiple fuel injectors on one side of any rib column away from the mounting plate are distributed in two rows, and the two rows of fuel injectors are respectively distributed on the edge positions of the rib column close to the isolation plates on both sides thereof, and on the rotation path of the rotor on the rib column, the number and aperture of the fuel injectors in the front row of the rotation path are smaller than the number and aperture of the fuel injectors in the rear row.

6. The gas turbine rotor support structure according to claim 2, characterized in that: The gas turbine rotor support structure further comprises: A second cylindrical roller bearing, the second cylindrical roller bearing is arranged on the rotor, and in the axial direction of the rotor, the second cylindrical roller bearing and the first cylindrical roller bearing are spaced apart, the second cylindrical roller bearing and the first cylindrical roller bearing are located on the same side of each thrust bearing, and the first cylindrical roller bearing and the second cylindrical roller bearing jointly bear the gravity and radial vibration load of the rotor.

7. The gas turbine rotor support structure according to claim 6, characterized in that: The first thrust plate and the first thrust bearing are eliminated, and the cylindrical roller bearing close to the first thrust plate is replaced with a ball bearing.

8. The gas turbine rotor support structure according to claim 7, characterized in that: The grating scale is located between the ball bearing and the second thrust plate.

9. The gas turbine rotor support structure according to claim 6, characterized in that: The second thrust plate and the second thrust bearing are eliminated, and the cylindrical roller bearing close to the second thrust plate is replaced with a ball bearing.

10. The gas turbine rotor support structure according to claim 9, characterized in that: The grating scale is located on a side of the first thrust plate away from the ball bearing.

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