CN113653536A - Turbine interstage support with cage bars - Google Patents
Turbine interstage support with cage bars Download PDFInfo
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- CN113653536A CN113653536A CN202110945124.7A CN202110945124A CN113653536A CN 113653536 A CN113653536 A CN 113653536A CN 202110945124 A CN202110945124 A CN 202110945124A CN 113653536 A CN113653536 A CN 113653536A
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- bearing
- cage
- turbine
- inner ring
- support
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention discloses a turbine interstage support with cage strips, which belongs to the technical field of aero-engines and comprises a force-bearing outer ring, a force-bearing supporting plate and a force-bearing inner ring, wherein the force-bearing inner ring comprises an inner ring mounting edge, a cage strip type sleeve and an inner flange plate, one end of the cage strip type sleeve is fixedly connected with the inner ring mounting edge, the cage strip type sleeve is provided with a plurality of cage strips and supporting parts for fixing two ends of the cage strips, and the cage strips are circumferentially distributed on a turbine rotor and used for elastic support between turbine stages. The cage bar type elastic supporting structure is integrated on the bearing inner ring, so that the bearing requirements of the turbine interstage support, the control of the critical rotating speed of the rotor and the vibration reduction requirements can be met, the number of parts is reduced, the assembly is facilitated, and the cost is reduced. The cage bar type force bearing inner ring can reduce heat transfer of hot gas of a runner to the bearing seat and the bearing through the inner ring, reduce the thermal stress of the force bearing inner ring, reduce the working temperature of the bearing, and improve the service life and the safety of the turbine interstage support and the bearing.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a turbine interstage support with cage bars.
Background
The axial position of the turbine interstage support of the existing gas turbine engine is generally positioned between two stages of turbines and mainly comprises a bearing outer ring, a bearing support plate or a blade and a bearing inner ring. The bearing outer ring is provided with a mounting edge and is connected with an engine outer casing or a mounting joint; the middle part is a bearing support plate or a blade, is a component part of the fuel gas runner and is used for transmitting mechanical load of the rotor and the like; the inner ring is a bearing sleeve and a mounting edge and is connected with the bearing seat, the elastic support and the bearing. The load of the engine rotor is usually transmitted to an engine outer casing or a mounting section via a bearing, an elastic support, a bearing seat, a turbine inter-stage support, and the like. In order to meet the requirement of robustness of a high-speed rotor support system of an engine, an elastic support structure is usually arranged on a bearing seat and used for reducing the critical rotating speed of the rotor and reducing the vibration of the rotor.
The turbine interstage support is part of an engine bearing system and is generally used for supporting a low-pressure rotor or a power rotor. The load-bearing inner ring of the interstage bearing is connected with the bearing seat and the bearing, and the load of the rotor is transmitted to the load-bearing supporting plate or the blade through the load-bearing inner ring and then transmitted to the mounting edge of the load-bearing outer ring. The entire turbine interstage support generally has better strength and rigidity requirements, is located around high-temperature combustion gas, and needs to have the capabilities of resisting high temperature and thermal stress.
The bearing and the bearing are connected to a bearing seat and a turbine interstage support through an elastic support due to the requirement of reducing the critical rotating speed and the vibration reduction of the rotor system. The whole bearing seat assembly comprises complex oil supply and return, air cooling and sealing, elastic support and other structures, so that the design is difficult and the structure is complex.
Accordingly, the present invention provides a turbine interstage support with cage bars that addresses the problems set forth in the background above.
Disclosure of Invention
The invention aims to provide a turbine interstage support with cage bars, which integrates a cage bar type elastic support structure on a bearing inner ring, wherein the bearing inner ring is of a cage bar structure, so that the requirements of the engine rotor on the critical rotating speed and vibration reduction can be met under the condition of not needing independent elastic support, the thermal stress of the turbine interstage support is reduced, and the heat conduction of high-temperature gas to a bearing seat and a bearing is reduced.
According to one aspect of the invention, the turbine interstage support with the cage strips comprises a force-bearing outer ring, a force-bearing supporting plate and a force-bearing inner ring, wherein a turbine fuel gas flow channel is arranged between the force-bearing outer ring and the force-bearing inner ring, one end of the force-bearing supporting plate is fixed to the force-bearing outer ring, the other end of the force-bearing supporting plate is fixed to the force-bearing inner ring, the force-bearing inner ring comprises an inner ring mounting edge, a cage strip type sleeve and an inner edge plate, the inner ring mounting edge is fixedly connected with a bearing seat, the bearing seat is matched with a turbine rotor bearing in a centering mode, one end of the cage sleeve is fixedly connected with the inner ring mounting edge, the axial cross section of a structure formed by the cage strip type sleeve and the inner edge plate is U-shaped, the cage strip type sleeve is provided with a plurality of cage strips and strip type supporting portions used for fixing two ends of the cage strips, and the cage strips are circumferentially distributed on the turbine rotor and are used for elastically supporting the turbine interstage.
According to the preferred embodiment of the invention, the bearing outer ring comprises an outer ring mounting edge, a connecting sleeve and an outer edge plate, wherein one end of the connecting sleeve is in arc-shaped transition connection with the outer side of the tail part of the outer edge plate, the other end of the connecting sleeve is fixedly connected with the outer ring mounting edge, the outer ring mounting edge is fixedly connected with an engine outer casing or a mounting section, and the connecting sleeve is used for indirectly connecting the outer ring mounting edge and the outer edge plate, so that the overall thermal stress of the bearing outer ring can be effectively reduced.
According to a preferred embodiment of the present invention, the inner and outer edge plates are respectively inner and outer boundaries of the turbine gas flow path.
According to the preferred embodiment of the invention, the axial direction of the connecting sleeve is consistent with the axial direction of the turbine rotor, which is beneficial to the stability of the whole structure of the bearing outer ring.
According to the preferred embodiment of the invention, the cage bars are circular, elliptical or rectangular in radial section, the heat conduction of gas to the bearing seat and the bearing can be directly reduced through the cage bar structure with smaller section area, and the structure with smaller rigidity has smaller thermal stress when resisting thermal deformation, so that the service life and the safety of the turbine interstage support, the bearing seat and the bearing are obviously prolonged.
According to a preferred embodiment of the invention, the chamfer radius R at the connection of the cage bars with the bearing points is 3-10 mm.
According to a preferred embodiment of the invention, the cage bars have a length L of 60 to 100mm, a number N of 16 to 20, a cross-sectional width b and a height h of 3 to 10mm and 2 to 4mm, respectively.
According to the preferred embodiment of the invention, the bearing support plate is in a cylinder, an elliptic cylinder or a blade type, and the bearing support plate directly penetrates through the turbine gas flow channel along the radial direction, can only provide the function of transmitting the mechanical force of the rotor, and also can simultaneously have a blade profile to bear the functions of accelerating and deflecting gas of a guider in the flow channel, so that the turbine gas flow channel has good rigidity and high strength.
According to the preferred embodiment of the invention, the bearing support plate can be solid or hollow, and the hollow support plate can be directly ventilated or filled with oil for cooling or lubricating the bearing, or an inner pipe can be continuously sleeved in the hollow support plate for ventilation or oil filling.
According to the preferred embodiment of the invention, the number of the bearing support plates is 4-24, the bearing support plates are divided into large support plates and small support plates, and the number of the small support plates is more than that of the large support plates.
Compared with the prior art, the invention has the beneficial effects that:
1. and integrating the cage bar type elastic supporting structure on the force bearing inner ring. The structure can simultaneously meet the requirements of bearing force of the turbine interstage support, controlling the critical rotating speed of the rotor and reducing vibration, reduces the number of parts, is beneficial to assembly and reduces the cost.
2. The cage bar type sleeve is matched with the flexibility required by the engine rotor to reduce the independent elastic support assembled in the bearing seat assembly, the structure is simplified, the cage bar type force bearing inner ring can reduce the heat transfer of hot gas in a runner to the bearing seat and the bearing through the inner ring, the heat stress of the force bearing inner ring is reduced, the working temperature of the bearing is reduced, and the service life and the safety of the turbine interstage support and the bearing are improved.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is an axial cross-sectional structural schematic view of a turbine interstage support of the invention;
FIG. 2 is a schematic view of a partial structure of the cage bar sleeve of the present invention;
FIG. 3 is a cross-sectional structural diagram of the squirrel cage bar sleeve of the present invention;
fig. 4 is a schematic cross-sectional structure view of the tie-rod type cage bar sleeve of the present invention.
In the figure: 1. a force bearing outer ring; 11. an outer ring mounting edge; 12. a connecting sleeve; 13. an outer edge plate; 2. a bearing support plate; 3. a force bearing inner ring; 31. an inner ring mounting edge; 32. a cage bar type sleeve; 33. an inner edge panel; 321. cage bars; 322. a support portion; 4. a turbine gas flowpath.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention and should not be construed as limiting the invention.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in schematic form in order to simplify the drawing.
Referring to fig. 1 to 4, according to one general technical concept of the present invention, a preferred embodiment of the present invention discloses a specific technical solution of a turbine interstage support with cage bars as follows:
fig. 1 shows a turbine interstage support with cage bars, which comprises a bearing outer ring 1, a bearing support plate 2 and a bearing inner ring 3, wherein the bearing outer ring 1 is composed of an outer ring mounting edge 11, a connecting sleeve 12 and an outer edge plate 13, the rigidity is good, the strength is high, the axis of the connecting sleeve 12 is consistent with that of a turbine rotor, the left end is connected with the outer ring mounting edge 11, the right end is connected with the outer edge plate 13 at the interstage support tail part, the outer ring mounting edge 11 and the outer edge plate 13 are indirectly connected through the connecting sleeve 12, the overall thermal stress of the bearing outer ring 1 can be effectively reduced, the outer edge plate 13 is a component part of a turbine gas flow channel 4, the axial section of the structure composed of the cage bar type sleeve 32 and the inner edge plate 33 is U-shaped, the cage bar type sleeve 32 is provided with a plurality of cage bars 321 and supporting parts 322 for fixing two ends of the cage bars, and the cage bars 321 are circumferentially distributed on the turbine rotor for elastic support between stages of the turbine.
The bearing support plate 2 directly penetrates through the turbine gas flow channel 4 along the radial direction, can only provide the function of transmitting the mechanical force of the rotor, and can also have a blade profile to bear the functions of accelerating and deflecting gas of a guider in the flow channel, so that the rigidity is good, and the strength is high. The shape of the bearing support plate 2 can be round, oval, can also be superposed along the radial blade profile, can be a straight blade, can also be a twisted blade, and can also be slightly deflected along the radial direction to be superposed as the blade profile, namely an inclined blade. The number of the bearing support plates 2 can be 4-24, and support plates with different shapes can exist at the same time, such as 4 large support plates and 20 small support plates; or 4 straight plates and 12 oblique plates, to name a few.
The bearing support plate 2 can be solid or hollow. The hollow support plate can be directly ventilated or filled with oil for cooling or lubricating a bearing, and an inner pipe can be continuously sleeved in the hollow support plate for ventilation or oil filling; two layers of pipes, three layers of pipes or two parallel pipes can be sleeved, which is not an example.
According to one embodiment of the patent, the bearing support plate 2 is provided with a blade profile which comprises 4 large straight blades and 12 small straight blades, wherein the 4 large straight blades are of a hollow sleeve structure, and the 12 small straight blades are of a solid structure.
In this embodiment, the force-bearing inner ring 3 is a component of the turbine fuel gas flow channel 4, and a part of the force-bearing inner ring is located below the turbine fuel gas flow channel 4, and the part below the turbine fuel gas flow channel 4 is generally surrounded by cooling air, so that the force-bearing inner ring 3 has large temperature difference between the inside and the outside and large thermal stress. The force-bearing inner ring 3 is composed of an inner ring mounting edge 31, a cage bar type sleeve 32 and an inner edge plate 33, the inner ring mounting edge 31 is used for connecting a bearing seat and a bearing and transferring corresponding rotor mechanical load and generally has bolt holes, the cage bar type sleeve 32 is a direct part for reducing the rigidity of the turbine interstage support and realizing the elastic design of the turbine interstage support, and can be a squirrel cage type or a pull rod type. The chamfers R of the cage bars 321 and the supporting part 322 are 3-10mm, when the cage bars 321 are in a squirrel cage type, the cross sections of the cage bars 321 are rectangular, four corners of the rectangle are provided with chamfers, and the rigidity of the force-bearing inner ring 3 is determined by the length L, the section width b, the section height h and the number N of the cage bars 321; when the cage bars 321 are pull rod type, the cross section is circular, and the rigidity of the force-bearing inner ring 3 is determined by the length L of the cage bars 321, the diameter D of the cross section and the number N of the cage bars 321. The specific structural parameters are selected according to the rigidity value required by the engine rotor. According to one embodiment of the patent, the length L of the cage bars 321 is 60-100mm, the number N of the cage bars 321 is 16-20, the cage bars are circumferentially non-uniformly distributed or uniformly distributed, and the section width b and the height h are respectively 3-10mm and 2-4 mm. The cage bar type structure with a small sectional area can directly reduce the heat conduction of gas to the bearing seat and the bearing, and the structure with small rigidity has small thermal stress when resisting thermal deformation, so that the service life and the safety of the turbine interstage support, the bearing seat and the bearing are obviously prolonged. The inner edge plate 33 is an integral part of the turbine gas flow channel 4.
The invention is practical and feasible through relevant practical mechanical use. Through finite element calculation, after the original inner ring sleeve is transformed by a cage bar type structure, the rigidity value is reduced to about 0.8 multiplied by 107N/m from 2.2 multiplied by 107N/m, and the corresponding first-order critical rotating speed is reduced by about 3-4%. The corresponding requirements of the engine rotor can be met. Additionally, when the left end and the right end of the sleeve are kept unchanged as thermal boundaries, the heat transfer quantity of the cage-bar type force-bearing inner ring 3 to the bearing seat through the inner ring mounting edge 31 is reduced by about 53 percent.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The turbine interstage support with the cage strips comprises a bearing outer ring (1), a bearing supporting plate (2) and a bearing inner ring (3), wherein a turbine fuel gas flow channel (4) is arranged between the bearing outer ring (1) and the bearing inner ring (3), one end of the bearing supporting plate (2) is fixed to the bearing outer ring (1), the other end of the bearing supporting plate (2) is fixed to the bearing inner ring (3), the turbine interstage support is characterized in that the bearing inner ring (3) comprises an inner ring mounting edge (31), a cage strip type sleeve (32) and an inner edge plate (33), one end of the cage strip type sleeve (32) is fixedly connected with the inner ring mounting edge (31), the axial section of a structure formed by the cage strip type sleeve (32) and the inner edge plate (33) is U-shaped, the cage strip type sleeve (32) is provided with a plurality of cage strips (321) and supporting portions (322) used for fixing two ends of the cage strips, and the cage strips (321) are distributed on a turbine rotor in the circumferential direction, for elastic support between turbine stages.
2. The turbine interstage support with the cage bars as claimed in claim 1, characterized in that the force bearing outer ring (1) comprises an outer ring mounting edge (11), a connecting sleeve (12) and an outer edge plate (13), one end of the connecting sleeve (12) is in arc transition connection with the outer side of the tail portion of the outer edge plate (13), the other end of the connecting sleeve (12) is fixedly connected with the outer ring mounting edge (11), and the outer ring mounting edge (11) is fixedly connected with an engine casing or a mounting joint.
3. The turbine interstage support with cage strips as claimed in claim 2, characterized in that the inner and outer edge plates (33, 13) are respectively an inner and an outer boundary of the turbine gas flow channel (4).
4. The turbine interstage support with cage bars as claimed in claim 2, characterized in that the axis of the connecting sleeve (12) coincides with the direction of the turbine rotor axis.
5. The turbine interstage support with cage bars as claimed in claim 1, characterized in that the cage bars (321) are circular, elliptical or rectangular in radial cross section.
6. The turbine interstage support with cage bars as claimed in claim 4, characterized in that the chamfer radius R at the junction of the cage bars (321) and the support part (322) is 3-10 mm.
7. The turbine interstage support with cage bars as claimed in claim 5, characterized in that the length L of the cage bars (321) is 60-100mm, the number N is 16-20, the cross-sectional width b and the height h are 3-10mm and 2-4mm, respectively.
8. The turbine interstage support with cage bars as claimed in claim 1, characterized in that the force bearing plate (2) is of cylindrical, elliptic cylindrical or blade type.
9. The turbine interstage support with the cage strips as claimed in claim 8, wherein the number of the bearing plates (2) is 4-24, the bearing plates (2) are divided into large plates and small plates, and the number of the small plates is larger than that of the large plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110945124.7A CN113653536B (en) | 2021-08-17 | 2021-08-17 | Turbine interstage support with cage bars |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110945124.7A CN113653536B (en) | 2021-08-17 | 2021-08-17 | Turbine interstage support with cage bars |
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| Publication Number | Publication Date |
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| CN113653536A true CN113653536A (en) | 2021-11-16 |
| CN113653536B CN113653536B (en) | 2023-10-20 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008031871A (en) * | 2006-07-26 | 2008-02-14 | Mitsubishi Heavy Ind Ltd | Strut structure and gas turbine |
| RU2375596C1 (en) * | 2008-04-28 | 2009-12-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Gas turbine engine support |
| CN112483199A (en) * | 2020-12-11 | 2021-03-12 | 中国科学院工程热物理研究所 | Engine rotor transition section elastic support structure |
-
2021
- 2021-08-17 CN CN202110945124.7A patent/CN113653536B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008031871A (en) * | 2006-07-26 | 2008-02-14 | Mitsubishi Heavy Ind Ltd | Strut structure and gas turbine |
| RU2375596C1 (en) * | 2008-04-28 | 2009-12-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Gas turbine engine support |
| CN112483199A (en) * | 2020-12-11 | 2021-03-12 | 中国科学院工程热物理研究所 | Engine rotor transition section elastic support structure |
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| CN113653536B (en) | 2023-10-20 |
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