CN118979818A - Intermediate bearing outer ring mounting structure - Google Patents
Intermediate bearing outer ring mounting structure Download PDFInfo
- Publication number
- CN118979818A CN118979818A CN202411091555.1A CN202411091555A CN118979818A CN 118979818 A CN118979818 A CN 118979818A CN 202411091555 A CN202411091555 A CN 202411091555A CN 118979818 A CN118979818 A CN 118979818A
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- China
- Prior art keywords
- outer ring
- edge
- mounting
- intermediate bearing
- bearing outer
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000009434 installation Methods 0.000 claims abstract description 28
- 238000002955 isolation Methods 0.000 claims abstract description 24
- 125000006850 spacer group Chemical group 0.000 claims description 14
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Abstract
The application belongs to the field of aero-engines, and particularly relates to an intermediate bearing outer ring mounting structure. The structure comprises: the cross section of the intermediate bearing outer ring is T-shaped, the intermediate bearing outer ring comprises an outer ring main body and an outer ring mounting edge arranged in the middle of the outer ring main body, and mounting holes are formed in the outer ring mounting edge; the isolation ring comprises a first isolation ring installation edge, a second isolation ring installation edge and a connecting beam for connecting the first isolation ring installation edge and the second isolation ring installation edge, and the first isolation ring installation edge and the second isolation ring installation edge are provided with installation holes; the low-pressure turbine shaft is provided with a mounting hole; the first isolating ring mounting edge is lapped on the intermediate bearing outer ring, and sequentially penetrates through the mounting hole of the outer ring mounting edge, the mounting hole of the first isolating ring mounting edge, the mounting hole of the second isolating ring mounting edge and the mounting hole of the low-pressure turbine shaft through bolts, and is fixedly connected with a matched nut.
Description
Technical Field
The application belongs to the field of aero-engines, and particularly relates to an intermediate bearing outer ring mounting structure.
Background
In the rotor fulcrum layout of a dual-rotor small bypass ratio turbofan engine, an intermediate bearing (also called an inter-shaft bearing) is often adopted to simplify the supporting structure, and the intermediate bearing is usually arranged between a high-pressure turbine and a low-pressure turbine, so that the temperature environment is poor. The bearing cavity where the intermediate bearing is located is surrounded and heated by the secondary air flow of the turbine disk cavity, and the heat of the turbine disk is also conducted to the inner ring track and the outer ring track of the intermediate bearing through the connecting structure.
With the requirements of increasing the temperature load and compactification of the structure of the engine, the temperature and the thermal deformation of the inner ring and the outer ring of the intermediate bearing are particularly influenced by the airflow of the disc cavity and the heat conduction and deformation of the turbine rotor (disc and shaft), and the uneven deformation of the runways of the inner ring and the outer ring of the bearing can deteriorate the contact load between the bearing rollers and the runways, reduce the service life of the bearing, even endanger the working safety of the engine, and the influence of the turbine rotor on the heat transfer and deformation of the inner ring and the outer ring of the intermediate bearing is urgently needed to be reduced, so that the deformation of the runways of the bearing is controlled.
Typical intermediate bearing mounting is shown in FIG. 1, wherein the intermediate bearing outer ring flange is mounted on the low pressure turbine shaft with a tight fit and the inner ring is mounted on the high pressure turbine shaft. The disadvantages include:
1. When the engine works, the temperature of the main body of the turbine disc is obviously higher than the temperature of the bearing cavity, heat is conducted from the turbine disc to the bearing outer ring through disc-shaft connection and shaft-bearing outer ring flange connection, the temperature of one side of the bearing outer ring close to the flange edge is obviously higher than the temperature of one side of the bearing outer ring far away from the flange edge, namely obvious axial temperature gradient exists, and the thermal deformation of the bearing outer ring is bell-mouth-shaped conical deformation;
2. When the engine works, the temperature load of the disk-shaft connection part of the turbine shaft is higher, and the temperature load is influenced by the partial centrifugal load of the turbine shaft and the turbine disk, so that the deformation of the connection part of the turbine shaft and the flange edge of the outer ring of the bearing is higher than the deformation of one side of the outer ring of the bearing, which is far away from the flange edge, and the conical deformation degree of the outer ring of the bearing is further increased.
This deformation will lead to unbalanced loading of the bearing rollers, worsening the contact load between the bearing rollers and the racetrack, reducing bearing life and even compromising engine operation safety.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The object of the present application is to provide an intermediate bearing outer ring mounting structure that solves at least one of the problems of the prior art.
The technical scheme of the application is as follows:
an intermediate bearing outer ring mounting structure comprising:
The middle bearing outer ring is T-shaped in cross section, and comprises an outer ring main body and an outer ring mounting edge arranged in the middle of the outer ring main body, wherein mounting holes are formed in the outer ring mounting edge;
The isolation ring comprises a first isolation ring installation edge, a second isolation ring installation edge and a connecting beam for connecting the first isolation ring installation edge and the second isolation ring installation edge, and the first isolation ring installation edge and the second isolation ring installation edge are provided with installation holes;
the low-pressure turbine shaft is provided with a mounting hole;
the first isolating ring mounting edge is lapped on the intermediate bearing outer ring and sequentially penetrates through the mounting hole of the outer ring mounting edge, the mounting hole of the first isolating ring mounting edge, the mounting hole of the second isolating ring mounting edge and the mounting hole of the low-pressure turbine shaft through bolts, and the first isolating ring mounting edge, the mounting hole of the second isolating ring mounting edge and the mounting hole of the low-pressure turbine shaft are fixedly connected through nuts.
In at least one embodiment of the present application, a U-shaped opening is provided at the outer edge of the outer ring mounting edge.
In at least one embodiment of the present application, the mounting holes and the U-shaped openings on the mounting edge of the outer ring are uniformly distributed along the circumferential direction.
In at least one embodiment of the application, a U-shaped notch is arranged on the outer ring mounting edge at intervals of two mounting holes.
In at least one embodiment of the present application, the outer edges of the first isolating ring mounting edge and the second isolating ring mounting edge are provided with U-shaped openings.
In at least one embodiment of the present application, the mounting holes and the U-shaped openings on the first spacer ring mounting edge and the second spacer ring mounting edge are uniformly distributed along the circumferential direction.
In at least one embodiment of the present application, a U-shaped notch is disposed on each of the first spacer ring mounting edge and the second spacer ring mounting edge at two mounting holes.
In at least one embodiment of the present application, the connection beams on the isolating ring are uniformly distributed along the circumferential direction, and a forming hole is formed between two adjacent connection beams, and the axial direction of the forming hole is the local radial direction.
In at least one embodiment of the application, the radially inner and outer surfaces of the connection beam are cylindrical surfaces.
The invention has at least the following beneficial technical effects:
The intermediate bearing outer ring mounting structure can reduce heat conduction of the turbine rotor to the intermediate bearing outer ring, relieve the influence of deformation of the joint of the turbine shaft and the bearing on the traction of the intermediate bearing outer ring, and enable centrifugal force deformation and thermal deformation of the runway to be distributed more uniformly along the axial direction.
Drawings
FIG. 1 is a schematic illustration of a typical intermediate bearing mounting structure;
FIG. 2 is a schematic illustration of an intermediate bearing outer ring mounting structure according to one embodiment of the present application;
FIG. 3 is a schematic diagram of an assembly of a spacer ring with an intermediate bearing outer ring in accordance with one embodiment of the present application;
FIG. 4 is an exploded view of an isolator ring and intermediate bearing outer ring in accordance with one embodiment of the present application;
FIG. 5 is a side view of the mounting edge of the outer ring of one embodiment of the present application;
FIG. 6 is a side view of an isolator ring in accordance with one embodiment of the present application;
FIG. 7 is a view in the A direction of FIG. 6;
fig. 8 is a B-B view of fig. 6.
Wherein:
1-a bolt; 2-an intermediate bearing outer ring; 3-isolating rings; 4-a low pressure turbine shaft; 5-nut.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1 to 8.
The present application provides an intermediate bearing outer ring mounting structure, as shown in fig. 2, comprising: bolt 1, intermediate bearing outer ring 2, spacer ring 3, low pressure turbine shaft 4 and nut 5. Bolts 1 sequentially pass through structural members such as an intermediate bearing outer ring 2, a spacer ring 3, a low-pressure turbine shaft 4 and the like, and are fastened into a whole by nuts 5.
Specifically, the cross section of the intermediate bearing outer ring 2 is T-shaped, the intermediate bearing outer ring 2 comprises an outer ring main body and an outer ring mounting edge arranged in the middle of the outer ring main body, and mounting holes are formed in the outer ring mounting edge. By arranging the outer ring mounting edge in the middle of the outer ring body, the radial deformation of the intermediate bearing outer ring 2 can be prevented from being excessively large in the axial distribution. The isolating ring 3 comprises a first isolating ring installation edge, a second isolating ring installation edge and a connecting beam for connecting the first isolating ring installation edge and the second isolating ring installation edge, and the first isolating ring installation edge and the second isolating ring installation edge are provided with installation holes. The low-pressure turbine shaft 4 is provided with a mounting hole; the first isolating ring mounting edge is lapped on the intermediate bearing outer ring 2, sequentially penetrates through the mounting hole of the outer ring mounting edge, the mounting hole of the first isolating ring mounting edge, the mounting hole of the second isolating ring mounting edge and the mounting hole of the low-pressure turbine shaft 4 through bolts 1, and is fixedly connected with a matching nut 5.
According to the intermediate bearing outer ring mounting structure, the outer edge of the outer ring mounting edge of the intermediate bearing outer ring 2 is provided with the U-shaped notch for providing a lubricating oil flow channel. The mounting holes and the U-shaped notches on the outer ring mounting edge of the intermediate bearing outer ring 2 are preferably evenly distributed in the circumferential direction. In this embodiment, a U-shaped notch is disposed on each of the two mounting holes on the mounting edge of the outer ring, as shown in fig. 5.
According to the intermediate bearing outer ring mounting structure, U-shaped openings are formed in the outer edges of the first isolation ring mounting edge and the second isolation ring mounting edge of the isolation ring 3, and are used for providing a lubricating oil flow channel. Preferably, the mounting holes and the U-shaped openings on the two mounting edges of the isolating ring 3 are uniformly distributed along the circumferential direction. In this embodiment, a U-shaped notch is disposed on each of the two mounting holes on the two mounting sides of the spacer ring 3 at two intervals, as shown in fig. 6.
In the preferred embodiment of the application, the connecting beams on the isolating ring 3 are uniformly distributed along the circumferential direction, and a forming hole is formed between two adjacent connecting beams, so that the isolating ring 3 is hollow, and the axial direction of the forming hole is the local radial direction. Wherein, the shaping hole can be rectangle, circular or oval, and when the shaping hole is rectangle, four contained angles do the rounding processing. The cross section of the connecting beam is in a curved trapezoid shape, the radial inner surface and the radial outer surface are cylindrical surfaces, and the side surface is a hole machining surface.
In the intermediate bearing outer ring mounting structure, the connecting beam is the key of the isolating ring 3 for realizing heat transfer and deformation blocking functions. Compared with the intermediate bearing outer ring mounting structure of fig. 1, the connecting beam reduces the heat conduction area of the turbine axial intermediate bearing outer ring 2, reduces the connection rigidity between the intermediate bearing outer ring 2 and the turbine shaft, and further relieves and isolates the deformation influence of heat and deformation of the turbine shaft on the intermediate bearing outer ring 2. By adjusting the structural parameters of the number, the length, the section size and the like of the connecting beams of the isolating ring 3, the heat conducting area and the connecting rigidity can be adjusted, and the radial deformation distribution of the intermediate bearing outer ring 2 is optimized to meet the working condition requirement of the bearing. In addition, the bolt 1 after tightening also contributes to the partial joint rigidity.
The application provides an intermediate bearing outer ring mounting structure for reducing the heat conduction and centrifugal deformation influence of a turbine rotor, which has the following beneficial effects:
(1) A hollowed isolating ring is arranged between the outer ring mounting edge of the intermediate bearing outer ring and the low-pressure turbine shaft, so that the heat conduction of the turbine rotor to the intermediate bearing outer ring is reduced, and the axial temperature gradient of the intermediate bearing outer ring is reduced;
(2) The hollow heat insulation ring has the characteristic of a flexible structure, and the influence of deformation at the joint of the turbine shaft and the bearing on the influence of the deformation on the outer ring of the bearing is relieved;
(3) The mounting edge on the intermediate bearing outer ring is arranged at the middle part of the bearing runway instead of one end, so that the centrifugal force deformation and the thermal deformation of the runway are more uniformly distributed along the axial direction, namely, the cone degree of a bell mouth shape is reduced.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An intermediate bearing outer ring mounting structure, comprising:
the cross section of the intermediate bearing outer ring (2) is T-shaped, the intermediate bearing outer ring (2) comprises an outer ring main body and an outer ring mounting edge arranged in the middle of the outer ring main body, and mounting holes are formed in the outer ring mounting edge;
the isolation ring (3) comprises a first isolation ring installation edge, a second isolation ring installation edge and a connecting beam for connecting the first isolation ring installation edge and the second isolation ring installation edge, wherein the first isolation ring installation edge and the second isolation ring installation edge are provided with installation holes;
a low-pressure turbine shaft (4), wherein a mounting hole is formed in the low-pressure turbine shaft (4);
The first isolating ring mounting edge is lapped on the intermediate bearing outer ring (2), sequentially penetrates through the mounting hole of the outer ring mounting edge, the mounting hole of the first isolating ring mounting edge, the mounting hole of the second isolating ring mounting edge and the mounting hole of the low-pressure turbine shaft (4) through bolts (1), and is fixedly connected with a matching nut (5).
2. The intermediate bearing outer ring mounting structure of claim 1, wherein the outer edge of the outer ring mounting edge is provided with a U-shaped notch.
3. The intermediate bearing outer ring mounting structure of claim 2, wherein the mounting holes and U-shaped cutouts on the outer ring mounting edge are evenly distributed circumferentially.
4. A mediating bearing outer ring mounting structure according to claim 3, wherein a U-shaped notch is provided on the outer ring mounting edge at two mounting holes each.
5. The intermediate bearing outer ring mounting structure of claim 4, wherein the outer edges of the first spacer ring mounting edge and the second spacer ring mounting edge are each provided with a U-shaped notch.
6. The intermediate bearing outer ring mounting structure of claim 5, wherein the mounting holes and U-shaped cutouts in the first and second spacer ring mounting edges are evenly distributed circumferentially.
7. The intermediate bearing outer ring mounting structure of claim 6, wherein a U-shaped gap is disposed on each of the first spacer ring mounting edge and the second spacer ring mounting edge with two mounting holes spaced apart.
8. Intermediate bearing outer ring mounting structure according to claim 1, characterized in that the connection beams on the spacer ring (3) are evenly distributed along the circumferential direction, and a shaped hole is formed between two adjacent connection beams, and the axial direction of the shaped hole is the local radial direction.
9. The intermediate bearing outer ring mounting structure of claim 8, wherein the shaped aperture is rectangular, circular or oval.
10. The intermediate bearing outer ring mounting structure of claim 8, wherein the radially inner and outer surfaces of the connecting beams are cylindrical surfaces.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118979818A true CN118979818A (en) | 2024-11-19 |
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