Gas turbine rotor shaft with lubricating oil guide structure and gas turbine
By setting an annular oil guide groove on the rotor shaft of the gas turbine to collect and guide the lubricant, the problem of lubricant coking at the seal is solved, ensuring the functionality of the seal and the safe operation of the rotor shaft of the gas turbine.
Patent Information
- Application Number
- CN202323129085.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2023-11-17
- Publication Date
- 2025-01-10
- Estimated Expiration
- 2033-11-17
AI Technical Summary
The lubricating oil of the rotor shaft of the gas turbine is easily coking at the seal, resulting in damage to the functional performance of the seal and affecting the safe and stable operation of the rotor.
A gas turbine rotor shaft with a lubricating oil guide structure is designed. By providing an annular oil guide groove between the rotor bearing and the seal, lubricating oil is collected and guided, thereby avoiding its direct impact on the seal, ensuring that the lubricating oil is on the rotor shaft and the bearing. The lubrication gap between them takes away the heat generated by friction.
It effectively prevents lubricating oil from coking at the seal, protects the functionality of the seal, ensures the safe operation of the rotor shaft and rotor bearing, and extends the service life of the seal.
Smart Images
Figure CN222333909U_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of oil-immersed transformers and relates to a double-oil-chamber transformer with a semi-enclosed partition structure. Background Art
[0002] As a new generation of power devices, gas turbines are widely used in power generation, distributed energy, ship power, natural gas, oil pipeline transportation and other fields. The gas turbine includes three major components from upstream to upstream along the air intake direction: compressor, combustion chamber and gas turbine. A rotor is arranged inside the gas turbine. The rotor of the gas turbine includes multiple rotor disks, a front rotor shaft and a rear rotor shaft, and these rotor disks are clamped together by central connecting bolts.
[0003] The gas turbine also has a lubricating oil system, which is an important part of the gas turbine auxiliary system. Its function is to provide sufficient lubricating oil with appropriate temperature and pressure to various bearings, transmission devices and auxiliary equipment in the gas turbine during the startup, normal operation and shutdown of the gas turbine unit, to ensure the safe and reliable operation of the unit and prevent the rotating parts from overheating, deformation or damage.
[0004] The rotor of the gas turbine is supported by two rotor bearings at the front rotor shaft and the rear rotor shaft. The rotor bearings are mounted on the bearing housing. The bearing housing is also provided with seals to separate the lubricating oil from the hot gas. The rotor bearings supporting the front rotor shaft and the rear rotor shaft are provided with lubricating oil through lubricating oil channels. These lubricating oils can be directly sprayed on the seals during operation, which can easily cause the lubricating oil to coke at the seals. The increased coking of the lubricating oil will endanger the functionality of the seals in the long term and affect the safe and stable operation of the rotor.
[0005] To date, no dedicated solutions have been used to direct the lubricating oil away from the seals. Utility Model Content
[0006] The technical problem to be solved by the present disclosure is to provide a gas turbine rotor shaft and a gas turbine with a lubricating oil guiding structure, which can reduce or avoid the coking of lubricating oil and damage to the functionality of the seal.
[0007] To solve the above technical problems, the present disclosure provides a gas turbine rotor shaft and a gas turbine with a lubricating oil guide structure, wherein the gas turbine rotor shaft comprises: a first diameter section, which is used to be inserted into a rotor bearing to be supported on the rotor bearing; a second diameter section, which is adjacent to the first diameter section and is used to cooperate with a seal surrounding the radial outer side of the second diameter section, the diameter of the second diameter section is larger than the diameter of the first diameter section; and an annular oil guide groove, which is arranged between the first diameter section and the second diameter section to form the lubricating oil guide structure, the diameter of the lowest point of the annular oil guide groove is smaller than the diameter of the first diameter section.
[0008] In the present disclosure, the lubricating oil provided to the rotor bearing enters the lubricating gap between the rotor bearing and the rotor shaft, effectively taking away the heat generated by friction, and the lubricating oil flowing out of the lubricating gap is received and guided by the annular oil guide groove and away from the seal, and flows out of the rotor bearing, and because the diameter of the second diameter section is greater than the diameter of the first diameter section, this further ensures that the seal can be protected from direct lubricating oil impact. Therefore, the solution of the present disclosure can prevent the coking of the lubricating oil at the seal, and ensure the safe operation of the rotor shaft and the rotor bearing.
[0009] Furthermore, the annular oil guide groove is arranged at a corner where the first diameter section and the second diameter section are adjacent to each other.
[0010] Furthermore, the gas turbine rotor shaft further comprises: a third diameter section, adjacent to the second diameter section and located at an end of the second diameter section away from the first diameter section, the diameter of the third diameter section being greater than the diameter of the second diameter section.
[0011] According to another aspect of the present disclosure, a gas turbine is provided, comprising a rotor having a gas turbine rotor shaft as described in any one of the above.
[0012] Furthermore, the rotor also includes: a plurality of rotor disks; a front rotor shaft, arranged on the upstream side of the plurality of rotor disks; a rear rotor shaft, arranged on the downstream side of the plurality of rotor disks, and the gas turbine also includes: two bearing housings, respectively arranged at positions corresponding to the front rotor shaft and the rear rotor shaft; two rotor bearings, respectively installed in the two bearing housings, wherein the front rotor shaft and / or the rear rotor shaft adopts the aforementioned gas turbine rotor shaft.
[0013] Furthermore, the rear rotor shaft adopts the aforementioned gas turbine rotor shaft; the bearing housing corresponding to the rear rotor shaft is provided with a bearing mounting portion for mounting the rotor bearing and a seal mounting portion for mounting the seal located on the upstream side of the bearing mounting portion.
[0014] Further, the bearing mounting portion and the seal mounting portion are both constructed as protrusions extending radially inward; the seal is arranged on the radial inner side of the seal mounting portion, and includes: a seal body; a seal axial protrusion extending axially from the seal body toward the rotor bearing and contacting the end face of the rotor bearing; and a seal radial protrusion extending radially outward from the seal body and contacting the upstream end face of the seal mounting portion.
[0015] Further, a first distance between the seal body and the rotor bearing is greater than a second distance between the second diameter section and the rotor bearing.
[0016] Furthermore, the plurality of rotor disks, the front rotor shaft and the rear rotor shaft are clamped and connected by a central connecting bolt coaxially penetrating therethrough.
[0017] Furthermore, the rotor bearing is a split journal bearing and is provided with a radial lubricating oil passage to provide lubricating oil to the lubricating gap between the rotor bearing and the first diameter section of the rotor shaft. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] The drawings described herein are used to provide a further understanding of the present disclosure and constitute a part of the present disclosure. The illustrative embodiments of the present disclosure and their descriptions are used to explain the present disclosure and do not constitute an improper limitation on the present disclosure. In the drawings:
[0019] Figure 1 is a partial cross-sectional view of a gas turbine according to the present disclosure, showing a rear rotor shaft, a rotor bearing, a bearing housing and a seal, wherein a lubricating oil guide structure is provided on the rear rotor shaft;
[0020] Figure 2 yes Figure 1 A partial enlarged view of a partial cross-sectional view of a gas turbine is shown, showing details of the seals and lubricating oil guiding structure.
[0021] Description of Figure Numbers:
[0022] 1. Rear rotor shaft; 2. Rotor bearing; 3. Annular oil guide groove; 4. Bearing housing; 41. Bearing mounting portion; 42. Sealing component installation portion; 5. Lubricating oil; 6. Seals; 61. Seal body; 62. The seal is axially protruding; 63. The seal is radially protruding; 7. Central connecting bolt; D1, first diameter section; D2, second diameter section; D3, third diameter section; g. Lubrication clearance; S, annular septum; S1, first distance; S2, second distance. DETAILED DESCRIPTION
[0023] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present disclosure and its application or use. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present disclosure.
[0024] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present disclosure. As used herein, unless the context clearly indicates otherwise, the singular form is intended to include the plural form as well.
[0025] Figure 1 It is a partial cross-sectional view of a gas turbine according to the present disclosure, showing a rear rotor shaft, a rotor bearing, a bearing housing and a seal, wherein a lubricating oil guide structure is provided on the rear rotor shaft. Figure 2 yes Figure 1 A partial enlarged view of a partial cross-sectional view of a gas turbine is shown, showing details of the seals and lubricating oil guiding structure.
[0026] See also Figure 1 and Figure 2 According to one embodiment of the present disclosure, a gas turbine rotor shaft and a gas turbine having a lubricating oil guide structure are provided. The gas turbine rotor shaft comprises: a first diameter section D1, which is used to be inserted into a rotor bearing 2 to be supported on the rotor bearing 2; a second diameter section D2, which is adjacent to the first diameter section D1 and is used to cooperate with a seal 6 surrounding the radial outer side of the second diameter section D2, wherein the diameter of the second diameter section D2 is greater than the diameter of the first diameter section D1; and an annular oil guide groove 3, which is arranged between the first diameter section D1 and the second diameter section D2 to form the lubricating oil guide structure, wherein the diameter of the lowest point of the annular oil guide groove 3 is smaller than the diameter of the first diameter section D1.
[0027] In the present disclosure, the lubricating oil 5 provided to the rotor bearing 2 (the lubricating oil is referred to as the position on the rear rotor shaft 1 where the lubricating oil is collected and guided, i.e., the position where the annular oil guide groove 3 is located) enters the lubrication gap g between the rotor bearing and the gas turbine rotor shaft (the rear rotor shaft 1).
[0028] Lubricating oil 5 is provided to reduce the coefficient of friction between the rear rotor shaft 1 and the rotor bearing 2. It also helps to remove the heat generated during operation. Seals 6 are designed to separate the lubricating oil 5 from the hot gases.
[0029] The temperature of the lubricating oil 5 increases during operation, and it needs to be collected and removed to prevent heat accumulation at the rear rotor shaft 1 and the rotor bearing 2 .
[0030] The annular oil guide groove 3 provided on the rear rotor shaft 1 is a recess for collecting and guiding oil. The outer diameter of the recess is smaller than the outer diameter of the first diameter portion of the rear rotor shaft 1, so the lubricating oil 5 can accumulate in the recess, and during the rotation of the rotor, the accumulated lubricating oil 5 is guided in the recess, which prevents the lubricating oil 5 from being directly sprayed on the seal 6. The lubricating oil 5 effectively takes away the heat generated by friction and ensures the safe operation of the rear rotor shaft 1 and the rotor bearing 2, while ensuring that the seal 6 is protected from direct impact of the lubricating oil. This prevents the coking of the lubricating oil 5 at the seal 6 and potential subsequent technical problems, ensuring the safe operation of the rear rotor shaft 1 and the rotor bearing 2.
[0031] from Figure 1 and Figure 2 It can also be seen that the annular oil guide groove 3 is arranged at the corner where the first diameter section D1 and the second diameter section D2 are adjacent.
[0032] from Figure 1 It can also be seen that the gas turbine rotor shaft further includes: a third diameter section D3, which is adjacent to the second diameter section D2 and is located at an end of the second diameter section D2 away from the first diameter section D1, and the diameter of the third diameter section D3 is greater than the diameter of the second diameter section D2. The third diameter section D3 is located on the upstream side of the seal and extends upward to a predetermined distance above the lower end of the seal 6, for example, to a position corresponding to the approximate middle of the seal 6.
[0033] According to another aspect of the present disclosure, a gas turbine is provided, comprising a rotor having a gas turbine rotor shaft according to any one of the above-mentioned items.
[0034] More specifically, see Figure 1 and Figure 2 , the rotor further includes: a plurality of rotor disks (not shown); a front rotor shaft (not shown), which is arranged on the upstream side of the plurality of rotor disks; a rear rotor shaft 1, which is arranged on the downstream side of the plurality of rotor disks, and the gas turbine further includes: two bearing housings 4, which are respectively arranged at positions corresponding to the front rotor shaft and the rear rotor shaft 1; the two rotor bearings 2 are respectively installed in the two bearing housings 4, wherein the front rotor shaft and / or the rear rotor shaft 1 adopts the aforementioned gas turbine rotor shaft.
[0035] Continue to see Figure 1 and Figure 2 The rear rotor shaft 1 adopts the aforementioned gas turbine rotor shaft; the bearing housing 4 corresponding to the rear rotor shaft 1 is provided with a bearing mounting portion 41 for mounting the rotor bearing 2 and a seal mounting portion 42 located on the upstream side of the bearing mounting portion 41 for mounting the seal 6.
[0036] Continue to see Figure 1 and Figure 2 The bearing mounting portion 41 and the seal mounting portion 42 are both constructed as protrusions extending radially inward; the seal 6 is arranged on the radial inner side of the seal mounting portion 42, and includes: a seal body 61; a seal axial protrusion 62 (which may be an annular protrusion), which extends axially from the seal body 61 toward the rotor bearing 2 and contacts the end surface of the rotor bearing 2; and a seal radial protrusion 63 (which may be an annular protrusion), which extends radially outward from the seal body 61 and contacts the upstream side end surface of the seal mounting portion 42.
[0037] Continue to see Figure 1 and Figure 2 , a first distance S1 between the seal body 61 and the rotor bearing 2 is greater than a second distance S2 between the second diameter section and the rotor bearing 2. Since the diameter of the second diameter section D2 is greater than the diameter of the first diameter section D1, the lubricating oil 5 from the lubrication gap g can be stopped by the second diameter section D2, thereby preventing the seal 6 from being directly impacted by the lubricating oil 5.
[0038] Continue to see Figure 1 and Figure 2 The multiple rotor disks, the front rotor shaft and the rear rotor shaft 1 are clamped and connected by a central connecting bolt 7 that runs coaxially through the center.
[0039] Preferably, the rotor bearing 2 is a split journal bearing, and is provided with a radial lubricating oil passage to provide lubricating oil to the lubricating gap between the rotor bearing and the first diameter section D1 of the rotor shaft.
[0040] Preferably, if Figure 1 and Figure 2 As shown, the seal 6 is a brush seal, which can achieve a better isolation and sealing effect.
[0041] The technical effect of the solution disclosed in the present invention is that the gas turbine rotor shaft with the lubricating oil collection and guiding design improves the functionality and durability of the seal and ensures the smooth operation of the gas turbine rotor shaft and the rotor bearing.
[0042] The above are only preferred embodiments of the present disclosure. It should be pointed out that, for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present disclosure. These improvements and modifications should also be regarded as the protection scope of the present disclosure.
Claims
1. A gas turbine rotor shaft having a lubricating oil guiding structure, characterized in that: include: A first diameter section (D1) is used to be inserted into the rotor bearing (2) to be supported on the rotor bearing (2); a second diameter section (D2) adjacent to the first diameter section (D1) and adapted to cooperate with a seal (6) surrounding the radially outer side of the second diameter section (D2), wherein the diameter of the second diameter section (D2) is greater than the diameter of the first diameter section (D1); and An annular oil guide groove (3) is arranged between the first diameter section (D1) and the second diameter section (D2) to form the lubricating oil guide structure, and the diameter of the lowest point of the annular oil guide groove (3) is smaller than the diameter of the first diameter section (D1).
2. The gas turbine rotor shaft according to claim 1, characterized in that: The annular oil guide groove (3) is arranged at a corner where the first diameter section (D1) and the second diameter section (D2) are adjacent to each other.
3. The gas turbine rotor shaft according to claim 2, characterized in that: Also includes: The third diameter section (D3) is adjacent to the second diameter section (D2) and is located at an end of the second diameter section (D2) away from the first diameter section (D1), and the diameter of the third diameter section (D3) is greater than the diameter of the second diameter section (D2).
4. A gas turbine, comprising a rotor, characterized in that The rotor has a gas turbine rotor shaft according to any one of claims 1 to 3.
5. The gas turbine according to claim 4, characterized in that The rotor further comprises: a plurality of rotor disks; a front rotor shaft disposed on an upstream side of the plurality of rotor disks; A rear rotor shaft (1) is arranged on the downstream side of the plurality of rotor disks, The gas turbine further comprises: Two bearing housings (4), respectively arranged at positions corresponding to the front rotor shaft and the rear rotor shaft; The two rotor bearings (2) are respectively mounted in the two bearing housings (4). The front rotor shaft and / or the rear rotor shaft (1) is / are the gas turbine rotor shaft according to any one of claims 1 to 3.
6. The gas turbine according to claim 5, characterized in that: The rear rotor shaft (1) is a gas turbine rotor shaft according to any one of claims 1 to 3; The bearing housing (4) corresponding to the rear rotor shaft (1) is provided with a bearing mounting portion (41) for mounting the rotor bearing (2) and a seal mounting portion (42) located on the upstream side of the bearing mounting portion (41) for mounting the seal (6).
7. The gas turbine according to claim 6, characterized in that: The bearing mounting portion (41) and the seal mounting portion (42) are both configured as protrusions extending radially inwards; The sealing member (6) is arranged on the radial inner side of the sealing member mounting portion (42), and comprises: a seal body (61); A seal axial protrusion (62) extends axially from the seal body (61) toward the rotor bearing (2) and contacts an end surface of the rotor bearing (2); and A seal radial protrusion (63) extends radially outward from the seal body (61) and contacts an upstream end surface of the seal mounting portion (42).
8. The gas turbine according to claim 7, characterized in that: A first distance (S1) between the seal body (61) and the rotor bearing (2) is greater than a second distance (S2) between the second diameter section and the rotor bearing (2).
9. The gas turbine according to any one of claims 5 to 8, characterized in that: The plurality of rotor disks, the front rotor shaft and the rear rotor shaft (1) are clamped and connected via a coaxially penetrating central connecting bolt (7).
10. The gas turbine according to any one of claims 5 to 8, characterized in that The rotor bearing (2) is a split-type journal bearing and is provided with a radial lubricating oil passage to supply lubricating oil to a lubricating gap (g) between the rotor bearing and a first diameter section (D1) of the gas turbine rotor shaft.