CN113653536B - Turbine interstage support with cage bars - Google Patents
Turbine interstage support with cage bars Download PDFInfo
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- CN113653536B CN113653536B CN202110945124.7A CN202110945124A CN113653536B CN 113653536 B CN113653536 B CN 113653536B CN 202110945124 A CN202110945124 A CN 202110945124A CN 113653536 B CN113653536 B CN 113653536B
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- bearing
- cage
- inner ring
- turbine
- 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 bars, which belongs to the technical field of aeroengines and comprises a bearing outer ring, a bearing support plate and a bearing inner ring, wherein the bearing inner ring comprises an inner ring mounting edge, a cage bar type sleeve and an inner edge plate, one end of the cage bar type sleeve is fixedly connected with the inner ring mounting edge, the cage bar type sleeve is provided with a plurality of cage bars and supporting parts for fixing two ends of the cage bars, and the cage bars are circumferentially distributed on a turbine rotor and are used for elastic supporting of the turbine interstage. The cage bar type elastic supporting structure is integrated on the bearing inner ring, so that the bearing capacity of the turbine interstage supporting, the critical rotating speed control of the rotor and the vibration reduction requirement can be simultaneously met, the number of parts is reduced, the assembly is facilitated, and the cost is reduced. The cage bar type bearing inner ring can reduce heat transfer of the runner hot gas to the bearing seat and the bearing through the inner ring, reduce thermal stress of the bearing inner ring, reduce working temperature of the bearing, and improve service life and safety of the turbine interstage support and the bearing.
Description
Technical Field
The invention belongs to the technical field of aeroengines, and particularly relates to a turbine interstage support with cage bars.
Background
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 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 flow passage 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 typically transferred to the engine outer casing or mounting section via bearings, elastomeric bearings, bearing blocks, turbine interstage bearings, and the like. Among other things, turbine inter-stage support is typically of rigid design, and to meet the robustness requirements of the engine high speed rotor support system, an elastic support structure is typically provided on the bearing housing for reducing the critical rotational speed of the rotor and reducing rotor vibration.
Turbine interstage support, which is part of the engine's bearing system, is typically used to support the low pressure or power rotors. The bearing inner ring of the interstage support is connected with the bearing seat and the bearing, and the load of the rotor is transmitted to the bearing support plate or the blade through the bearing inner ring and then transmitted to the mounting edge of the bearing outer ring. The overall turbine interstage support generally has good strength and stiffness requirements and is located around high temperature combustion gases and requires the ability to withstand high temperatures and thermal stresses.
The bearing and the bearing are connected to the bearing seat and the turbine interstage support through elastic support due to the requirement of the rotor system for reducing critical rotation speed and vibration reduction. 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 to address the problems set forth in the background above.
Disclosure of Invention
The invention aims at overcoming the defects of the prior art, and provides 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 critical rotation speed and vibration reduction requirement of an engine rotor can be met under the condition that independent elastic support is not needed, the thermal stress of the turbine interstage support is reduced, and the heat conduction from high-temperature fuel gas to a bearing seat and a bearing is reduced.
According to one aspect of the invention, a turbine interstage support with cage bars is provided, which comprises a bearing outer ring, a bearing support plate and a bearing inner ring, wherein a turbine fuel runner is arranged between the bearing outer ring and the bearing inner ring, one end of the bearing support plate is fixed on the bearing outer ring, the other end of the bearing support plate is fixed on the bearing inner ring, the bearing inner ring comprises an inner ring mounting edge, a cage bar 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 manner, one end of the cage bar sleeve is fixedly connected with the inner ring mounting edge, the axial section of a structure formed by the cage bar sleeve and the inner edge plate is U-shaped, and the cage bar sleeve is provided with a plurality of cage bars and bearing parts for fixing two ends of the cage bars, and the cage bars are circumferentially distributed on a turbine rotor for elastic support of 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, one end of the connecting sleeve is excessively connected to the outer side of the tail part of the outer edge plate in an arc shape, 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 outer engine casing or a mounting joint, 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 invention, the inner and outer rim plates are the inner and outer boundaries, respectively, of the turbine gas flow channel.
According to the preferred embodiment of the invention, the axis of the connecting sleeve is consistent with the axis direction of the turbine rotor, so that the stability of the integral structure of the bearing outer ring is facilitated.
According to the preferred embodiment of the invention, the radial section of the cage bars is circular, elliptical or rectangular, the heat conduction from the fuel gas to the bearing seat and the bearing can be directly reduced through the cage bar structure with smaller sectional area, and the thermal stress of the structure with smaller rigidity when resisting thermal deformation is also smaller, so that the overall 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 junction of the cage bars with the support site is 3-10mm.
According to a preferred embodiment of the invention, the cage bars have a length L of 60-100mm, a number N of 16-20, a cross-sectional width b and a height h of 3-10mm and 2-4mm, respectively.
According to the preferred embodiment of the invention, the bearing support plate is a cylinder, an elliptic cylinder or a blade, and directly passes through the turbine fuel gas flow passage along the radial direction, so that the bearing support plate can only provide the function of transmitting the mechanical force of the rotor, can also have the blade profile at the same time, has the functions of accelerating and deflecting fuel gas of a guider in the flow passage, and 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 oiled for cooling or lubricating the bearing, and the inner tube can be continuously sleeved in the hollow support plate for ventilation or oiled.
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. cage bar type elastic supporting structure is integrated on the bearing inner ring. The structure can simultaneously meet the requirements of bearing force, controlling the critical rotation speed of the rotor and damping of the inter-stage support of the turbine, reduces the number of parts, is beneficial to assembly and reduces cost.
2. The cage bar type sleeve is matched with the flexibility required by the engine rotor so as to reduce the independent elastic support assembled in the bearing seat assembly, simplify the structure, reduce the heat transfer of the hot fuel gas in the flow passage to the bearing seat and the bearing through the inner ring, reduce the thermal stress of the bearing inner ring, reduce the working temperature of the bearing and improve the service life and the safety of the inter-stage support and the bearing of the turbine.
Drawings
The present invention is further described below with reference to the accompanying drawings for the convenience of understanding by those skilled in the art.
FIG. 1 is a schematic view of an axial cross-section of a turbine interstage support of the present invention;
FIG. 2 is a schematic view of a partial structure of a cage bar sleeve according to the present invention;
FIG. 3 is a schematic cross-sectional view of a squirrel-cage bar sleeve of the present invention;
fig. 4 is a schematic cross-sectional view of a pull rod 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 bearing inner ring; 31. an inner ring mounting edge; 32. cage bar type sleeve; 33. an inner edge plate; 321. cage bars; 322. a support section; 4. turbine fuel gas flow path.
Detailed Description
The technical solution of the present invention will be further specifically described below by way of examples with reference to the accompanying drawings in order to make the objects, technical solutions and advantages of the present invention more apparent. In the specification, the same or similar reference numerals denote the same or similar components. The following description of embodiments of the present invention with reference to the accompanying drawings is intended to illustrate the general inventive concept and should not be taken 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 present 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 the drawings in order to simplify the drawings.
Referring to fig. 1-4, according to a general technical concept of the present invention, a preferred embodiment of the present invention discloses a specific technical scheme of a turbine inter-stage support with cage bars, which is as follows:
the turbine interstage support with the cage bars comprises a bearing outer ring 1, a bearing support plate 2 and a bearing inner ring 3, wherein the bearing outer ring 1 consists 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 the axis of a turbine rotor, the left end of the connecting sleeve is connected with the outer ring mounting edge 11, the right end of the connecting sleeve is connected with the outer edge plate 13 at the tail part of the interstage support, the connecting sleeve 12 is used for indirectly connecting the outer ring mounting edge 11 and the outer edge plate 13, the whole thermal stress of the bearing outer ring 1 can be effectively reduced, the outer edge plate 13 is a component part of a turbine fuel gas runner 4, the axial cross section of a structure formed by a 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 used for fixing two ends of the cage bars, and the cage bars 321 are circumferentially distributed on the turbine rotor for the elastic support of the turbine interstage.
The bearing support plate 2 directly passes through the turbine fuel gas flow passage 4 along the radial direction, can only provide the function of transmitting the mechanical force of the rotor, can also have the blade profile at the same time, has the functions of accelerating and deflecting fuel gas of a guider in the flow passage, and has good rigidity and high strength. The bearing support plate 2 can be round, elliptical, overlapped along the radial blade profile, straight blade, torsion blade, and slightly deflected along the radial direction to overlap the blade profile, namely, oblique blade. The number of the bearing support plates 2 can be 4-24, and support plates with different shapes can exist simultaneously, such as 4 large support plates and 20 small support plates; or 4 straight braces, 12 diagonal braces, to name but a few.
The bearing support plate 2 can be solid or hollow. The hollow support plate can be directly ventilated or oiled for cooling or lubricating the bearing, and the inner tube can be continuously sleeved in the hollow support plate for ventilation or oiled; two layers of tubes, three layers of tubes, or two tubes in parallel may be sleeved, which are not examples here.
According to one embodiment of the present patent, the force bearing support plate 2 has a blade profile, which is 4 large straight blades and 12 small straight blades, the 4 large straight blades are hollow sleeve structures, and the 12 small straight blades are solid structures.
In this embodiment, the bearing inner ring 3 is a component part of the turbine fuel gas flow channel 4, and a part of the bearing inner ring is located below the turbine fuel gas flow channel 4, and a part below the turbine fuel gas flow channel 4 is generally surrounded by cooling air, so that the temperature difference between the inside and the outside of the bearing inner ring 3 is large, and the thermal stress is large. The bearing inner ring 3 consists of an inner ring mounting edge 31, a cage bar type sleeve 32 and an inner edge plate 33, wherein the inner ring mounting edge 31 is used for connecting a bearing seat and a bearing and transmitting corresponding mechanical loads of a rotor, and generally is provided with bolt holes, the cage bar type sleeve 32 is a direct part for reducing the rigidity of the turbine inter-stage support and realizing the elastic design of the turbine inter-stage support, and can be a squirrel cage type or a pull rod type. The chamfer R of the cage bar 321 and the supporting part 322 is 3-10mm, when the cage bar 321 is a squirrel cage, the cross section of the cage bar is rectangular, the four corners of the rectangle are chamfered, and the rigidity of the bearing inner ring 3 is determined by the length L of the cage bar 321, the width b of the cross section, the height h of the cross section and the number N of the cage bars 321; when the cage bars 321 are pull-rod type, the cross section of the cage bars 321 is circular, and the rigidity of the bearing inner ring 3 is determined by the length L of the cage bars 321, the cross section diameter D and the number N of the cage bars 321. The specific structural parameters are selected according to the required rigidity value of 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 not uniformly distributed or uniformly distributed in the circumferential direction, and the section width b and the section height h are 3-10mm and 2-4mm respectively. Through the cage bar type structure with smaller sectional area, the heat conduction from the fuel gas to the bearing pedestal and the bearing can be directly reduced, and the thermal stress of the structure with smaller rigidity when resisting thermal deformation is also smaller, so that the overall service life and the safety of the turbine interstage support, the bearing pedestal and the bearing are obviously prolonged. The inner edge plate 33 is an integral part of the turbine fuel flow passage 4.
The invention is practical and feasible through the use of related actual machines. After finite element calculation and cage bar type structural transformation, the rigidity value of the original inner annular sleeve is reduced from 2.2 multiplied by 107N/m to about 0.8 multiplied by 107N/m, and the corresponding first-order critical rotation speed is reduced by about 3-4%. The corresponding requirements of the engine rotor can be met. Additionally, the cage bar type load bearing inner ring 3 reduces the heat transfer to the bearing housing by about 53% through the inner ring mounting edge 31 when the sleeve left and right ends are kept constant at the thermal boundary.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (3)
1. The utility model provides a take turbine interstage support of cage strip, includes load-bearing outer ring (1), load-bearing support plate (2) and load-bearing inner ring (3), be turbine fuel runner (4) between load-bearing outer ring (1) and load-bearing inner ring (3), load-bearing support plate (2) one end is fixed in load-bearing outer ring (1), load-bearing support plate (2) other end is fixed in load-bearing inner ring (3), characterized in that, load-bearing inner ring (3) include inner ring installation limit (31), cage strip sleeve (32) and inner flange plate (33) are constituteed, cage strip sleeve (32) one end and inner ring installation limit (31) fixed connection, the axial cross-section of the structure that cage strip sleeve (32) and inner flange plate (33) constitute is the U-shaped, cage strip sleeve (32) are equipped with a plurality of cage strips (321) and are used for fixing support portion (322) at cage strip both ends, cage strip (321) circumference distributes in turbine rotor for turbine interstage elastic support;
the 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 part 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 outer casing or a mounting joint of the engine;
the inner edge plate (33) and the outer edge plate (13) are respectively an inner boundary and an outer boundary of the turbine fuel gas flow channel (4);
the axis of the connecting sleeve (12) is consistent with the axis direction of the turbine rotor;
the radial section of the cage bar (321) is round, elliptical or rectangular;
the chamfer radius R of the joint of the cage bar (321) and the supporting part (322) is 3-10mm;
the length L of the cage bars (321) is 60-100mm, the number N is 16-20, and the cross section width b and the height h are 3-10mm and 2-4mm respectively.
2. A turbine inter-stage support with cage bars according to claim 1, characterized in that the bearing support plate (2) is of cylindrical, elliptic cylindrical or vane type.
3. The turbine interstage support with cage bars according to claim 2, wherein the number of the bearing support plates (2) is 4-24, and the bearing support plates (2) 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.
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 CN113653536A (en) | 2021-11-16 |
| CN113653536B true CN113653536B (en) | 2023-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110945124.7A Active CN113653536B (en) | 2021-08-17 | 2021-08-17 | Turbine interstage support with cage bars |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115013161A (en) * | 2022-06-29 | 2022-09-06 | 中国航发湖南动力机械研究所 | Turbine interstage supporting structure and gas turbine engine |
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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| CN113653536A (en) | 2021-11-16 |
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