CN215949602U - Turbine interstage casing, aircraft engine and aircraft - Google Patents
Turbine interstage casing, aircraft engine and aircraft Download PDFInfo
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- CN215949602U CN215949602U CN202122061681.0U CN202122061681U CN215949602U CN 215949602 U CN215949602 U CN 215949602U CN 202122061681 U CN202122061681 U CN 202122061681U CN 215949602 U CN215949602 U CN 215949602U
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- casing
- outer casing
- cold air
- heat insulation
- turbine interstage
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Abstract
The utility model provides a turbine interstage casing, an aero-engine and an aircraft. The rectifying blades are fixed on the inner side of the outer casing. The bearing support plate is arranged between two adjacent rectifying blades, and one end of the bearing support plate is connected with the outer casing. One end of the bearing support plate close to the outer casing is provided with a cold air hole. The heat insulation plate is connected with the outer casing. The heat insulation plate is provided with a through hole. A first cold air cavity is formed between the heat insulation plate and the outer casing, and a second cold air cavity is formed between the heat insulation plate and the rectifying blades. The cold air hole is communicated with the first cold air cavity, the through hole and the second cold air cavity in sequence. The heat insulation plate can reduce the heat radiation of the rectifying blades to the outer casing, can guide cold air, preferentially cools the parts which are easy to exceed the temperature, such as the outer casing, and improves the cooling effect of the interstage casing.
Description
Technical Field
The utility model relates to the technical field of aviation, in particular to a turbine interstage casing, an aero-engine and an aircraft.
Background
The commercial aircraft engine body structure generally comprises a fan supercharging stage, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and other parts, wherein the interstage casing is a part which is positioned between the high-pressure turbine and the low-pressure turbine in the aircraft engine, guides and transitions high-pressure turbine outlet gas to a low-pressure turbine inlet, and fixedly installs an engine bearing. For commercial aircraft engines, high pressure turbine exit temperatures reach over 1000K, so the interstage casing components must be designed with cooling considerations.
The main parts of the interstage casing comprise an outer casing, an inner casing, a bearing support plate and a rectifying blade. The outer casing, the bearing support plate and the inner casing form a bearing frame. The rectifying blades isolate the fuel gas in the flow passage, so that the bearing part is separated from the temperature bearing part. In order to cool the bearing frame and the rectifying blades, cold air is introduced from the high-pressure compressor and enters the cavities of the bearing support plate and the inner casing from the outer casing for cooling, and the temperature of an oil pipe and an air pipe of a bearing seat in the bearing support plate is reduced. The cold air enters the outer cavities of the rectification blades and the outer casing through the holes in the support plate, and the outer casing, the rectification blades and the like are cooled. The cooling mode makes the temperature of the inner cavity of the bearing support plate lower than that of the outer cavity of the rectifying blade.
The part of the interstage casing with the highest temperature under the engine working state is a rectifying blade. Due to the direct heat transfer, the outer casing connection to the fixed fairing blades is often at risk of critical overtemperature. Meanwhile, various mounting seats, sealing rings and the like outside the outer casing need to be prevented from generating overtemperature in a working state, and the structural strength and the sealing effect are guaranteed. Because the structure of the casing needs to use cooling measures, the temperature of the casing and the surface mounting seat is reduced.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defects of the prior art and provides a turbine interstage casing, an aircraft engine and an aircraft.
The utility model solves the technical problems through the following technical scheme:
a turbine interstage casing comprises an outer casing, a rectifying blade, a bearing support plate and a heat insulation plate. The rectifying blades are fixed on the inner side of the outer casing. The bearing support plate is arranged between two adjacent rectifying blades, and one end of the bearing support plate is connected with the outer casing. And one end of the bearing support plate, which is close to the outer casing, is provided with a cold air hole. The heat insulation plate is connected with the outer casing. The heat insulation plate is provided with a through hole. A first cold air cavity is formed between the heat insulation plate and the outer casing, and a second cold air cavity is formed between the heat insulation plate and the rectifying blades. The air conditioning hole communicates in proper order first cold wind chamber with the through-hole with the second cold wind chamber to make air conditioning advance and enter first cold wind chamber, the rethread the through-hole gets into the second cold wind chamber.
In this scheme, adopt above-mentioned structural style, can reduce the thermal radiation of rectification blade to outer cartridge receiver, can guide air conditioning simultaneously, preferentially cool off easy overtemperature's positions such as outer cartridge receiver, improved interstage cartridge receiver cooling effect, reduce interstage cartridge receiver outer cartridge receiver overtemperature risk. On the basis of improving the cooling effect, less air compressors are used for introducing cold air into the interstage casing, the loss of air flow is reduced, and the efficiency of the engine is optimized.
Preferably, the heat insulation plate comprises a plurality of heat insulation plate bodies, and the plurality of heat insulation plate bodies are sequentially connected along the circumferential direction of the turbine interstage casing.
In this scheme, adopt above-mentioned structural style, the installation of heat insulating board can be convenient for.
Preferably, the heat insulation board body comprises a recessed portion and a wall surface portion, the recessed portion is communicated with the cold air hole, the wall surface portion is arranged around the recessed portion, and the wall surface portion protrudes out of the recessed portion.
In this scheme, adopt above-mentioned structural style, can guide air conditioning better, improve the cooling effect.
Preferably, the wall surface portion is provided with a through hole.
In this scheme, adopt above-mentioned structural style, can guide cold air to pass through to can balance the pressure of heat insulating board both sides, reduce the vibration.
Preferably, the heat insulation board is provided with ribs, and the ribs can prevent the heat insulation board from being attached to the outer casing.
In this scheme, adopt above-mentioned structural style, can prevent that the thermal deformation back laminating from appearing in the heat insulating board is on outer quick-witted casket to avoid reducing the cooling effect.
Preferably, one end of the heat insulation plate in the radial direction of the turbine interstage casing is provided with a first lug, the other end of the heat insulation plate is provided with a second lug, the first lug is connected with the rectifying blade, and the second lug is connected with the outer casing.
In this scheme, adopt above-mentioned structural style, can strengthen the stability of heat insulating board.
Preferably, the second lug is oval in shape.
In this scheme, adopt above-mentioned structural style, can be convenient for the connection installation of second lug to reduce thermal stress when the thermal expansion.
Preferably, the turbine interstage casing further comprises a hook and a fastener, the fastener fixing the hook and the second lug on the outer casing.
In the scheme, the structure of the turbine interstage casing can be simplified and the cost is reduced by adopting the structural form.
Preferably, the turbine interstage casing further comprises an anti-loosening member, and the anti-loosening member fixes the heat insulation plate to the outer casing.
Preferably, the anti-loosening member includes a nut, a support cylinder, a bolt, an anti-rotation pin, and a washer. The nut is disposed outside the outer case. The support cylinder is arranged on the inner side of the outer casing. The bolt can penetrate through the heat insulation plate, the supporting cylinder and the outer casing in sequence and is connected with the nut. The anti-rotation pin is arranged at the joint of the outer casing and the bolt, and can prevent the anti-loosening piece from rotating. The gasket is arranged at the joint of the nut and the outer casing.
In this scheme, adopt any one above-mentioned structural style, all can reduce the vibration of thermal-insulated board, improve the stability of structure.
An aircraft engine comprises the turbine interstage casing.
An aircraft comprises the aircraft engine.
The positive progress effects of the utility model are as follows: the utility model can reduce the heat radiation of the rectifying blades to the outer casing, can guide cold air at the same time, preferentially cools the parts which are easy to overtemperature such as the outer casing, improves the cooling effect of the interstage casing, reduces the overtemperature risk of the outer casing of the interstage casing, reduces the vibration of the heat insulation plate by using the anti-loosening piece, and improves the stability of the structure. On the basis of improving the cooling effect, less air compressors are used for introducing cold air into the interstage casing, the loss of air flow is reduced, and the efficiency of the engine is optimized.
Drawings
Fig. 1 is a schematic structural view of a turbine interstage casing according to an embodiment of the utility model.
Fig. 2 is a partial perspective view of a turbine interstage casing according to an embodiment of the utility model.
Fig. 3 is a schematic structural view of a heat insulation board body according to an embodiment of the present invention.
FIG. 4 is a schematic view illustrating the connection between the heat-insulating plate and the anti-loose member according to an embodiment of the present invention.
Fig. 5 is a schematic structural view of a locking member according to an embodiment of the present invention.
FIG. 6 is a schematic view illustrating a flow direction of cold air according to an embodiment of the present invention.
Description of reference numerals:
Force bearing support plate 3
Bearing seat 5
First lug 7.1
Second lug 7.2
Recess 7.3
Wall surface part 7.4
Through-hole 7.5
Detailed Description
The present invention will be more clearly and completely described in the following description of preferred embodiments, taken in conjunction with the accompanying drawings.
As shown in fig. 1, the present embodiment discloses a turbine interstage casing, which includes an outer casing 1, a straightening vane 2, a bearing support plate 3 and a heat insulation plate 7. The straightening vanes 2 are fixed to the inside of the outer casing 1. The bearing support plate 3 is arranged between two adjacent rectifying blades 2, and one end of the bearing support plate 3 is connected with the outer casing 1. One end of the bearing support plate 3 close to the outer casing 1 is provided with a cold air hole. The heat shield 7 is connected to the outer case 1. The heat insulation plate 7 is provided with a through hole. A first cold air cavity is formed between the heat insulation plate 7 and the outer casing 1, and a second cold air cavity is formed between the heat insulation plate 7 and the rectifying blades 2. The cold air holes are sequentially communicated with the first cold air cavity, the through holes and the second cold air cavity, so that cold air enters the first cold air cavity firstly and then enters the second cold air cavity through the through holes.
In the present embodiment, the heat insulating plate 7 is located between the flow straightening vanes 2 and the outer casing 1, and insulates the outer casing 1 by forming an air layer with the outer casing 1. The existence of the heat insulation plate 7 can reduce the heat radiation of the rectifying blades 2 to the outer casing 1, can guide the cold air discharged from the cold air holes of the bearing support plate 3, preferentially cools the parts which are easy to overtemperature, such as the outer casing 1, improves the cooling effect of the interstage casing, and reduces the overtemperature risk of the outer casing 1 of the interstage casing. On the basis of improving the cooling effect, less air compressors are used for introducing cold air into the interstage casing, the loss of air flow is reduced, and the efficiency of the engine is optimized.
As shown in fig. 2 and 3, in the present embodiment, the heat shield 7 includes a plurality of heat shield bodies, two symmetrical heat shield bodies are correspondingly disposed on each of the plurality of blades 2, each of the heat shield bodies has two first lugs and three second lugs, and the plurality of heat shield bodies are sequentially connected along a circumferential direction of the turbine interstage casing.
In the embodiment, the plurality of heat insulation plate bodies are sequentially spliced to form the heat insulation plate 7, so that the heat insulation plate 7 can be conveniently installed, and as shown in fig. 3, when sixteen rectifying blades 2 are used for the turbine interstage casing, thirty-two heat insulation plate bodies are correspondingly installed.
As shown in fig. 2, 3 and 6, in the present embodiment, the heat insulation board body includes a concave portion and a wall portion, the concave portion is equal to the height of the cooling air hole at the upper end of the bearing support plate 3 so as to communicate the concave portion with the cooling air hole, the wall portion is disposed around the concave portion, and the distance between the wall portion and the outer casing 1 is 2-5 mm. The distance between the position of the concave part and the inner wall of the outer casing 1 is 7-10 mm.
In the embodiment, when the mounting seat of the outer casing 1 introduces cold air into the inner cavity of the bearing support plate 3, the cold air enters the cavities of the rectifier blades 2 and the outer casing 1 through the cold air holes on the bearing support plate 3. Under the guidance of the sunken part of the heat insulation plate 7, cold air firstly enters the first cold air cavity to take away heat. And the cold air is blown to the joint of the outer casing 1 and the flow straightening blades 2 under the guidance of the heat insulation plate 7, so that the temperature of the joint is reduced.
As shown in fig. 2 and 3, in the present embodiment, the wall surface portion is provided with a through hole.
In the present embodiment, the through holes can not only guide the cold air to pass through, but also balance the pressure on both sides of the heat insulation plate 7, reducing vibration.
In the embodiment shown in fig. 3, the heat insulation board 7 is provided with ribs, which can prevent the heat insulation board 7 from adhering to the outer casing 1.
In this embodiment, the ribs can prevent the heat insulation plate 7 from being thermally deformed and then attached to the outer casing 1, so that the temperature of the outer casing 1 is too high through heat conduction, thereby reducing the cooling effect.
As shown in fig. 3, in the present embodiment, the heat shield plate 7 is provided with a first lug at one end in the radial direction of the turbine interstage casing and a second lug at the other end, the first lug is connected with the flow straightening vane 2, and the second lug is connected with the outer casing 1.
In the present embodiment, two first lugs are fixed by the fixing bolts 11 and the pressing nuts 14 of the straightening vanes 2, and the other three second lugs are connected to the outer damper, and a double connection structure is adopted, so that the stability of the heat insulation plate 7 can be enhanced.
As shown in fig. 3, in the present embodiment, the second lug has an elliptical shape.
In the embodiment, the shape of the second lug is an ellipse, which can facilitate the connection and installation of the second lug and reduce the thermal stress when the second lug expands under heat.
As shown in fig. 1 and 4, in the present embodiment, the turbine interstage casing further includes a hook and a fastener, and the fastener fixes the hook and the second lug to the outer casing 1.
In the embodiment, the second lug is fastened by the hook 8, and the hook 8 is connected to the outer casing 1, and the second lug of the heat insulation plate 7 is pressed at the same time, so that the structure of the turbine interstage casing can be simplified, and the cost can be reduced.
As shown in fig. 4, 5 and 6, in the embodiment, the turbine interstage casing further comprises anti-loosening elements, and each heat insulation plate body is fixed on the outer gate through two sets of anti-loosening elements. The locking piece comprises a nut 14, a support cylinder 12, a bolt 11, an anti-rotation pin 13 and a gasket 15. The nut 14 is arranged on the outside of the outer casing 1. The support cylinder 12 is disposed inside the outer casing 1. The bolt 11 can penetrate through the heat insulation plate 7, the support barrel 12 and the outer casing 1 in sequence and is connected with the nut 14. An anti-rotation pin 13 is provided at the junction of the outer case 1 and the bolt 11, the anti-rotation pin 13 being capable of preventing the anti-loosening member from rotating. A washer 15 is provided at the junction of the nut 14 and the outer case 1.
In the present embodiment, the anti-loosening member can prevent the heat insulation plate 7 from vibrating under the action of cold air, and the structural stability is improved.
The utility model also provides an aircraft engine which comprises the turbine interstage casing.
The utility model also provides an aircraft comprising the aircraft engine.
While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.
Claims (12)
1. A turbine interstage casing, comprising:
an outer case;
the rectifying blades are fixed on the inner side of the outer casing;
the bearing support plate is arranged between two adjacent rectifying blades, one end of the bearing support plate is connected with the outer casing, and one end of the bearing support plate, which is close to the outer casing, is provided with a cold air hole;
the heat insulation plate is connected with the outer casing, the heat insulation plate is provided with a through hole, a first cold air cavity is formed between the heat insulation plate and the outer casing, a second cold air cavity is formed between the heat insulation plate and the rectifying blades, and the cold air holes are sequentially communicated with the first cold air cavity, the through hole and the second cold air cavity, so that cold air enters the first cold air cavity firstly and then enters the second cold air cavity through the through hole.
2. The turbine interstage casing of claim 1, wherein the heat shield comprises a plurality of heat shield bodies, and the plurality of heat shield bodies are connected in sequence along a circumferential direction of the turbine interstage casing.
3. The turbine interstage casing of claim 2, wherein the heat shield body comprises a recess portion communicating with the cold air hole and a wall surface portion provided around the recess portion, the wall surface portion protruding from the recess portion.
4. The turbine interstage casing of claim 3, wherein a through hole is formed in the wall surface portion.
5. The turbine interstage casing of claim 1, wherein the heat shield is provided with ribs which prevent the heat shield from adhering to the outer casing.
6. The turbine interstage casing according to claim 1, wherein one end of the heat insulating plate in a radial direction of the turbine interstage casing is provided with a first lug, and the other end of the heat insulating plate is provided with a second lug, the first lug is connected with the rectifying blade, and the second lug is connected with the outer casing.
7. The turbine interstage casing of claim 6, wherein the shape of the second lug is an ellipse.
8. The turbine interstage casing of claim 7, further comprising a hook and a fastener, wherein the fastener secures the hook and the second lug to the outer casing.
9. The turbine interstage casing of claim 1, further comprising a release prevention member, wherein the release prevention member secures the heat shield to an outer casing.
10. The turbine interstage casing of claim 9, wherein the anti-loosening element comprises:
a nut disposed outside of the outer case;
a support barrel disposed inside the outer case;
the bolt can sequentially penetrate through the heat insulation plate, the supporting cylinder and the outer casing and is connected with the nut;
the anti-rotation pin is arranged at the joint of the outer casing and the bolt and can prevent the anti-loosening piece from rotating;
and the gasket is arranged at the joint of the nut and the outer casing.
11. An aircraft engine, characterized in that it comprises a turbine interstage casing as claimed in any one of claims 1 to 10.
12. An aircraft comprising an aircraft engine according to claim 11.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122061681.0U CN215949602U (en) | 2021-08-30 | 2021-08-30 | Turbine interstage casing, aircraft engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122061681.0U CN215949602U (en) | 2021-08-30 | 2021-08-30 | Turbine interstage casing, aircraft engine and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215949602U true CN215949602U (en) | 2022-03-04 |
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ID=80430659
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122061681.0U Active CN215949602U (en) | 2021-08-30 | 2021-08-30 | Turbine interstage casing, aircraft engine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215949602U (en) |
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2021
- 2021-08-30 CN CN202122061681.0U patent/CN215949602U/en active Active
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