CN219865249U - Engine bearing cavity cooling structure and engine - Google Patents
Engine bearing cavity cooling structure and engine Download PDFInfo
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- CN219865249U CN219865249U CN202321758940.8U CN202321758940U CN219865249U CN 219865249 U CN219865249 U CN 219865249U CN 202321758940 U CN202321758940 U CN 202321758940U CN 219865249 U CN219865249 U CN 219865249U
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- 238000001816 cooling Methods 0.000 title claims abstract description 182
- 238000007789 sealing Methods 0.000 claims abstract description 35
- 239000012720 thermal barrier coating Substances 0.000 claims description 3
- 239000010687 lubricating oil Substances 0.000 abstract description 10
- 230000001050 lubricating effect Effects 0.000 abstract description 2
- 230000005855 radiation Effects 0.000 description 10
- 239000007789 gas Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 238000004939 coking Methods 0.000 description 3
- 238000005461 lubrication Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Abstract
The utility model relates to the technical field of heat management of gas turbines and aeroengines, in particular to an engine bearing cavity cooling structure and an engine, comprising the following components: the cooling box is hollow and arranged around the periphery of the bearing seat, and cold air is continuously reserved in the cooling box; the first cooling hole is formed in the side wall, facing the inner cavity of the bearing casing, of the cooling box, and the first cooling hole is communicated with the inner cavities of the cooling box and the bearing casing; the second cooling hole is formed in the side wall, facing the rim sealing cavity, of the cooling box, and the second cooling hole is communicated with the cooling box and the rim sealing cavity; the cooling air is output from the first cooling hole to the inner cavity of the bearing casing and is also output from the second cooling hole to the rim sealing cavity. The utility model can effectively reduce the temperature of the bearing cavity, improve the lubricating effect of the lubricating oil, reduce the consumption of the lubricating oil and improve the reliability and the safety of the engine.
Description
Technical Field
The utility model relates to the technical field of heat management of gas turbines and aeroengines, in particular to an engine bearing cavity cooling structure and an engine.
Background
When designing a gas turbine and an aeroengine, a bearing support point is often required to be designed at the rear end of the turbine so as to ensure the normal operation of the engine. Because the high-temperature gas temperature of the turbine outlet is very high, heat can be transferred to the bearing cavity in a heat conduction or heat radiation mode and the like, so that the temperature of the bearing cavity is too high. Excessive bearing cavity temperatures can cause excessive oil consumption, engine failures such as oil coking, and even premature bearing failure with catastrophic results.
In the prior design scheme, the bearing cavity is usually far away from the turbine runner as far as possible, but for a small and medium-sized engine, the structural space is limited, and the scheme cannot be adopted frequently; or cooling is directly supplied to the bearing cavity to cool, but the pressure of the bearing cavity is increased, so that on one hand, higher requirements are put forward on sealing of the bearing cavity, and on the other hand, the supply pressure of lubricating oil is increased, and the consumption of lubricating oil is also increased.
Disclosure of Invention
Therefore, the technical problem to be solved by the utility model is to overcome the defects in the prior art, and an aeroengine bearing cavity capable of effectively reducing the position of a rear bearing cavity of a turbine is designed.
When the bearing seat is arranged at the rear end of the turbine, the temperature of high-temperature fuel gas at the inlet of the turbine can reach more than 1000 ℃, and the temperature at the outlet of the turbine can reach more than 800 ℃. Under the action of high-temperature heat radiation, the temperature of the whole bearing cavity can also be increased. In order to avoid coking of the lubricating oil and ensure effective lubrication of the bearing, the oil supply amount of the lubricating oil has to be increased. In order to solve this problem, the bearing chamber temperature must be reduced, and the heat resulting in an increase in the bearing chamber temperature is mainly derived from the heat conduction of the connection of the bearing housing to the bearing housing on the one hand and the heat radiation of the entire turbine component on the other hand. For this reason, the solution provided by the utility model will result in an improved heat conduction and heat radiation.
In order to solve the technical problems, the utility model provides an engine bearing cavity cooling structure, which is arranged between a bearing seat and a bearing casing and comprises:
the cooling box is hollow and arranged around the periphery of the bearing seat, and cold air is continuously reserved in the cooling box;
the first cooling hole is formed in the side wall, facing the inner cavity of the bearing casing, of the cooling box, and the first cooling hole is communicated with the inner cavities of the cooling box and the bearing casing;
the second cooling hole is formed in the side wall, facing the rim sealing cavity, of the cooling box, and the second cooling hole is communicated with the cooling box and the rim sealing cavity;
the cooling air is output from the first cooling hole to the inner cavity of the bearing casing and is also output from the second cooling hole to the rim sealing cavity.
In one embodiment of the present utility model, the first cooling holes are provided in a plurality of cross-shaped film cooling holes.
In one embodiment of the utility model, the first cooling holes are uniformly distributed on the side wall of the cooling box, which faces the inner cavity of the bearing casing.
In one embodiment of the present utility model, extension lines of adjacent first cooling holes intersect.
In one embodiment of the utility model, the second cooling holes are uniformly distributed on the side wall of the cooling box facing the rim sealing cavity.
In one embodiment of the utility model, a turbine outlet is arranged at one side of the rim sealing cavity, and cold air is output from the rim sealing cavity to the turbine outlet.
In one embodiment of the utility model, the side wall of the cooling box is provided with at least two layers, and a hollow cold air flow cavity is formed inside the side wall of the cooling box.
In one embodiment of the utility model, the side walls of the cooling boxes facing the inner cavity of the bearing casing are respectively provided with a first cooling hole, and the side walls of the cooling boxes facing the rim sealing cavity are respectively provided with a second cooling hole.
In one embodiment of the utility model, the outer wall surface of the cooling box is sprayed with a thermal barrier coating.
An engine comprising an engine bearing cavity cooling structure as claimed in any one of the preceding claims.
Compared with the prior art, the technical scheme of the utility model has the following advantages:
according to the cooling structure of the engine bearing cavity and the engine, the cooling box is arranged between the bearing seat and the bearing casing, the bearing seat and the bearing casing are isolated, the inner cavity of the bearing casing is cooled through the first cooling hole of the cooling box, and the cooling cavity is sealed by the rim through the second cooling hole of the cooling box, so that the lubricating effect of lubricating oil is improved, the consumption of lubricating oil is reduced, and the reliability and safety of the engine are improved.
Drawings
In order that the utility model may be more readily understood, a more particular description of the utility model will be rendered by reference to specific embodiments thereof that are illustrated in the appended drawings.
FIG. 1 is an assembled cross-sectional schematic view of an engine bearing cavity cooling structure of the present utility model.
FIG. 2 is a schematic diagram of the flow of cold air in a cooling structure for a bearing cavity of an engine according to the present utility model.
FIG. 3 is a schematic view showing the whole first cooling hole side of a cooling box of an engine bearing cavity cooling structure according to the present utility model.
FIG. 4 is a second cooling hole side schematic view of a cooling box of an engine bearing cavity cooling structure according to the present utility model.
FIG. 5 is a schematic cross-sectional view of a cooling box of an engine bearing cavity cooling structure according to the present utility model.
FIG. 6 is a schematic cross-sectional view of a cooling box of a multi-layered sidewall of an engine bearing cavity cooling structure of the present utility model.
Description of the specification reference numerals: 1. a cooling box; 11. a first cooling hole; 12. a second cooling hole; 13. a cold air flow chamber; 2. a bearing seat; 3. a bearing; 4. a bearing casing; 41. an inner cavity of the bearing casing; 42. a hollow support plate; 5. a rim seal cavity; 51. a turbine outlet; 52. a turbine blade disc; 6. and a cold air pipe.
Detailed Description
The present utility model will be further described with reference to the accompanying drawings and specific examples, which are not intended to be limiting, so that those skilled in the art will better understand the utility model and practice it.
Example 1
Referring to fig. 1 to 6, an embodiment of a cooling structure for a cavity of an engine bearing 3 according to the present utility model is shown.
When the bearing support 2 is arranged at the rear end of the turbine, the high temperature gas temperature at the turbine inlet can reach more than 1000 ℃, and the temperature at the turbine outlet 51 can reach more than 800 ℃. Under the action of high-temperature heat radiation, the temperature of the whole cavity of the bearing 3 can also be increased. In order to avoid coking of the lubricating oil, effective lubrication of the bearing 3 is ensured, and the oil supply amount of the lubricating oil has to be increased. In order to solve this problem, it is necessary to reduce the temperature of the cavity of the bearing 3, and the heat resulting in the temperature rise of the cavity of the bearing 3 is mainly derived from heat conduction of the connection of the bearing housing 4 with the bearing housing 2 on the one hand, and heat radiation of the entire turbine component on the other hand. For this reason, the solution provided by the utility model will result in an improved heat conduction and heat radiation.
The cooling structure of the engine bearing 3 cavity is arranged between the bearing seat 2 and the bearing casing 4, and the cooling structure of the engine bearing 3 cavity comprises: cooling box 1. An annular cooling box 1 is arranged between the bearing seat 2 and the bearing box 4, the bearing seat 2 and the bearing box 4 are isolated, one side of the cooling box 1 faces the rim sealing cavity, the other side faces the inner cavity 41 of the bearing box, and high-pressure cold air is input into the cooling box 1 so that the high-pressure cold air is output to the rim sealing cavity 5 and the inner cavity 41 of the bearing box, and cooling of the bearing 3 cavity and the inner cavity 41 of the bearing box is achieved.
Specifically, referring to fig. 1 to 2, the cooling box 1 is an annular cavity, the interior of the cooling box 1 is hollow, and the cooling box 1 is disposed around the outer periphery of the bearing seat 2. Cold air is continuously introduced into the cooling box 1 from the hollow support plate 42 of the bearing box 4 through the cold air pipe 6, and the cold air pipe 6 is connected with the cooling box 1 and is communicated with the inner cavity of the cooling box 1. The cold air is high-pressure cold air, after entering the cooling box 1, the cold air is outwards diffused through the first cooling holes 11 and the second cooling holes 12 arranged on the side wall of the cooling box 1, and the air film formed by the cold air can wrap the outer wall of the cooling box 1, so that heat radiation is effectively blocked, and the wall temperature of a metal wall is reduced.
The first cooling hole 11 cools the inner cavity 41 of the bearing casing. The first cooling holes 11 are cross type air film holes. The first cooling holes 11 are used for introducing high-pressure cold air from the first cooling holes 11 on the wall surface of the cooling box 1 in a high-temperature environment by utilizing an air film cooling technology, the cold air is bent downwards under the pressure and friction force of the high-temperature air and is attached to a certain area on the wall surface of the cooling box 1, a cold air film with low temperature is formed to isolate the wall surface of the cooling box 1 from the high-temperature air, and part of radiant heat of the high-temperature air to the wall surface of a part is taken away, so that a good cooling protection effect is achieved on the outer wall surface of the cooling box 1.
Referring to fig. 3 to 5, the first cooling hole 11 is formed on a side wall of the cooling box 1 facing the inner cavity 41 of the bearing casing, and the first cooling hole 11 communicates the cooling box 1 with the inner cavity 41 of the bearing casing. The first cooling holes 11 are formed in a plurality of ways, and are uniformly distributed on the side wall of the cooling box 1, which faces the inner cavity 41 of the bearing casing, when the high-pressure cold air in the cooling box 1 passes through the first cooling holes 11, the high-pressure cold air forms an air film on the side wall of the cooling box 1, which faces the inner cavity 41 of the bearing casing, the air film cools the side wall of the cooling box 1, which faces the inner cavity 41 of the bearing casing, and meanwhile, the high-pressure cold air coming out of the first cooling holes 11 enters the inner cavity 41 of the bearing casing and is discharged outside the cavity from the hollow support plate 42 of the bearing casing 4, and the cold air flow can further reduce the temperature of the inner cavity 41 of the bearing casing and reduce heat radiation.
Wherein, referring to fig. 4, the extension lines of the adjacent first cooling holes 11 intersect. The air film hole has multiple forms, and different effects can be realized by different forms. In this design, the first cooling hole 11 adopts the cross air film hole in the inner wall of the cooling box 1, the first cooling hole 11 has two different orientations, which can realize better air film cooling efficiency and achieve the required cooling effect with relatively less cold air flow.
The second cooling hole 12 is used for cooling and sealing the rim sealing cavity. Referring to fig. 4, the second cooling hole 12 is a through hole, the second cooling hole 12 is disposed on a side wall of the cooling tank 1 facing the rim sealing cavity 5, and the second cooling hole 12 communicates the cooling tank 1 with the rim sealing cavity 5. The second cooling holes 12 are formed in a plurality of ways and are uniformly distributed on the side wall of the cooling box 1, facing the rim sealing cavity 5, the second cooling holes 12 are used for sealing the rim, and when high-pressure cold air in the cooling box 1 passes through the second cooling holes 12, the high-pressure cold air enters the rim sealing cavity to cool and seal the rim sealing cavity.
In addition, a turbine outlet 51 is provided at one side of the rim sealing cavity 5, and the turbine outlet 51 is formed by a gap between an inner wall of the rim sealing cavity 5 and a turbine impeller 52. The turbine outlet 51 can introduce the cold air in the rim sealing cavity 5 into the high-temperature fuel gas, so that the cold air is mixed with the high-temperature fuel gas to reduce the temperature. The cold air is output from the rim sealing cavity 5 to the turbine outlet 51, the pressure of the rim sealing cavity is ensured to be larger than the pressure of the turbine outlet 51, the cold air is discharged from the turbine outlet 51 to enter a high-temperature gas flow channel, the cold air is mixed with the gas at the turbine outlet 51, the temperature in the flow channel after the turbine outlet 51 can be reduced, and the temperature of the whole bearing 3 cavity is further reduced. Meanwhile, the second cooling hole 12 can also be used for sealing the rim, and when the inner pressure of the sealing cavity of the rim is larger than the pressure at the turbine outlet 51, the fuel gas can be prevented from flowing backwards, and no additional bleed air is needed. The pressure of the rim sealing cavity is regulated by the cold air inlet pressure, the inlet cross-sectional area, the size and the number of the air film cooling holes and the cold air outlet cross-sectional area parameters.
Referring to fig. 6, as one embodiment of the present utility model, the side wall of the cooling box 1 has at least two layers, and the multi-layer side wall is designed to form a hollow cold air flow chamber 13 inside the side wall of the cooling box 1, which is designed to provide a circulation path for cold air as much as possible. The cold air flow cavity 13 provides a flow channel for high-pressure cold air, and can achieve better cooling effect by matching the first cooling hole 11 and the second cooling hole 12.
When the cooling box 1 has more than two layers of side walls, the cooling box 1 has more than two layers of cold air flowing cavities 13 in the side walls. The multi-layered cold air flow chamber 13 can provide more circulation channels for cold air, and high-pressure cold air sequentially passes through the multi-layered cold air flow chamber 13 from inside to outside.
The side walls of the cooling boxes 1 facing the inner cavity 41 of the bearing casing are respectively provided with a first cooling hole 11, and the side walls of the cooling boxes 1 facing the rim sealing cavity 5 are respectively provided with a second cooling hole 12. The first cooling holes 11 on the multi-layer side wall of the cooling box 1 are in one-to-one correspondence, and the central axes of the corresponding first cooling holes 11 on the multi-layer side wall are coaxial.
As one embodiment of the present utility model, the outer wall surface of the cooling tank 1 is sprayed with a thermal barrier coating to further reduce radiation heat exchange.
Example two
Referring to fig. 1 to 6, the present embodiment is an engine, particularly an aeroengine, and the present engine includes the cooling structure of the engine bearing 3 cavity described in the first embodiment, so that details are not repeated, and the engine of the present embodiment has all the advantages of the first embodiment.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations and modifications of the present utility model will be apparent to those of ordinary skill in the art in light of the foregoing description. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present utility model.
Claims (10)
1. The utility model provides an engine bearing chamber cooling structure which characterized in that locates between bearing frame and the bearing housing, includes:
the cooling box is hollow and arranged around the periphery of the bearing seat, and cold air is continuously reserved in the cooling box;
the first cooling hole is formed in the side wall, facing the inner cavity of the bearing casing, of the cooling box, and the first cooling hole is communicated with the inner cavities of the cooling box and the bearing casing;
the second cooling hole is formed in the side wall, facing the rim sealing cavity, of the cooling box, and the second cooling hole is communicated with the cooling box and the rim sealing cavity;
the cooling air is output from the first cooling hole to the inner cavity of the bearing casing and is also output from the second cooling hole to the rim sealing cavity.
2. The engine bearing cavity cooling structure of claim 1, wherein the first cooling holes are provided in a plurality of cross-shaped film cooling holes.
3. The engine bearing cavity cooling structure according to claim 2, wherein the first cooling holes are uniformly distributed on the side wall of the cooling box, which faces the inner cavity of the bearing casing.
4. The engine bearing cavity cooling structure of claim 2, wherein extension lines of adjacent ones of said first cooling holes intersect.
5. The cooling structure of an engine bearing cavity according to claim 1, wherein a plurality of second cooling holes are uniformly distributed on the side wall of the cooling box facing the rim sealing cavity.
6. The engine bearing cavity cooling structure according to claim 1, wherein a turbine outlet is formed in one side of the rim seal cavity, and cool air is output from the rim seal cavity to the turbine outlet.
7. The engine bearing cavity cooling structure according to claim 1, wherein the cooling box has at least two layers on a side wall thereof, and a hollow cold air flow cavity is formed inside the cooling box side wall.
8. The engine bearing cavity cooling structure according to claim 7, wherein the side walls of the cooling boxes facing the inner cavity of the bearing casing are respectively provided with a first cooling hole, and the side walls of the cooling boxes facing the rim sealing cavity are respectively provided with a second cooling hole.
9. The engine bearing cavity cooling structure of claim 1, wherein the outer wall surface of the cooling box is sprayed with a thermal barrier coating.
10. An engine comprising an engine bearing cavity cooling structure according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321758940.8U CN219865249U (en) | 2023-07-06 | 2023-07-06 | Engine bearing cavity cooling structure and engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321758940.8U CN219865249U (en) | 2023-07-06 | 2023-07-06 | Engine bearing cavity cooling structure and engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219865249U true CN219865249U (en) | 2023-10-20 |
Family
ID=88347423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321758940.8U Active CN219865249U (en) | 2023-07-06 | 2023-07-06 | Engine bearing cavity cooling structure and engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219865249U (en) |
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2023
- 2023-07-06 CN CN202321758940.8U patent/CN219865249U/en active Active
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