CN215949587U - High-pressure turbine rotor, aircraft engine and aircraft - Google Patents
High-pressure turbine rotor, aircraft engine and aircraft Download PDFInfo
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- CN215949587U CN215949587U CN202121320750.9U CN202121320750U CN215949587U CN 215949587 U CN215949587 U CN 215949587U CN 202121320750 U CN202121320750 U CN 202121320750U CN 215949587 U CN215949587 U CN 215949587U
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Abstract
The utility model discloses a high-pressure turbine rotor, an aircraft engine and an aircraft, wherein the high-pressure turbine rotor comprises: the rotor comprises a rotor body, wherein the rotor body comprises a first cylinder, a disc body assembly and a second cylinder which are sequentially connected along the axial direction, the disc body assembly comprises a plurality of disc bodies which are sequentially overlapped, the disc bodies comprise a first end and a second end from inside to outside along the radial direction, the first ends of the adjacent disc bodies are directly connected, and the second ends of the two adjacent disc bodies have a distance; the blades are connected to the outer peripheral surface of the second end of the disc body; first barrel, a plurality of disk body, a plurality of blade and second barrel integrated into one piece. The aircraft engine comprises a high pressure turbine rotor as described above. The aircraft comprises an aircraft engine as described above. The high-pressure turbine rotor adopts the integrated design and manufacturing technical idea, and is changed from the original part assembly into the structural form of integrated design as one part, so that the structure is simplified, the weight is reduced, the assembly difficulty is reduced, and the efficiency of the gas compressor is improved.
Description
Technical Field
The utility model relates to a high-pressure turbine rotor, an aircraft engine and an aircraft.
Background
The aircraft engine has the advantages of complex structure, various parts, high part processing and manufacturing precision and great assembly difficulty of parts and the whole engine. At present, a high-pressure turbine rotor of an aircraft engine with a conventional configuration is complex, and generally comprises a drum shaft, various stages of discs, blades, a baffle, a sealing part, a connecting bolt, a rear shaft neck and the like.
SUMMERY OF THE UTILITY MODEL
The utility model provides a high-pressure turbine rotor, an aero-engine and an aircraft, aiming at overcoming the defects that the weight of the whole aircraft is high due to the fact that parts of the high-pressure turbine rotor of the existing aero-engine are multiple, the thrust-weight ratio is greatly limited to further improvement, the reliability of the whole aircraft is poor, the assembly difficulty is high, and the efficiency is limited to further improvement.
The utility model solves the technical problems through the following technical scheme:
a high-pressure turbine rotor, characterized in that it comprises:
the rotor comprises a rotor body, wherein the rotor body comprises a first cylinder, a disc body assembly and a second cylinder which are sequentially connected along the axial direction, the disc body assembly comprises a plurality of disc bodies which are sequentially stacked along the axial direction, the disc bodies comprise a first end and a second end from inside to outside along the radial direction, the first ends of the adjacent disc bodies are directly connected, and the second ends of the two adjacent disc bodies have a distance;
a plurality of blades connected to an outer circumferential surface of the second end of the disc body;
wherein, the first cylinder, a plurality of the disk bodies, a plurality of the blades and the second cylinder are integrally formed.
In this technical scheme, adopt above-mentioned structural style for high-pressure turbine rotor adopts integrated design, manufacturing technology theory, becomes the structural style of integrated design for a part by original part equipment, thereby has cancelled little parts such as baffle, connecting bolt, nut among the prior art high-pressure turbine rotor, and high-pressure turbine rotor's structure is simplified, the part kind reduces, reduces part quantity, and part quantity reduces to one by hundreds, and the configuration management degree of difficulty reduces, realizes that the structure is simplified, weight reduction. Compared with the prior art that the requirement on the machining precision of a plurality of single pieces is high, the machining difficulty is generally reduced. The integrated design does not need to consider the concentricity problem, does not need single piece assembly, and reduces the assembly difficulty. Due to the adoption of the integrated design, the clearance between parts is eliminated, the aerodynamic loss is reduced, the efficiency is improved, the centrifugal force problem of the blades is eliminated, the rigidity of the high-pressure turbine rotor is improved, and the fuel consumption rate is also reduced. Meanwhile, the whole high-pressure turbine rotor is a part, the whole structure is properly reinforced, and the safety and stability of the high-pressure turbine rotor are improved.
Preferably, the tray body assembly further comprises an inter-tray sealing ring, the inter-tray sealing ring is connected between two adjacent tray bodies and is located between the first end and the second end of each tray body, and the inter-tray sealing ring and the tray bodies are integrally formed;
the outer peripheral surface of the inter-disc sealing ring is provided with an inter-disc sealing part; the sealing part between the discs is used for sealing the labyrinth, and the sealing part between the discs is integrally formed on the outer peripheral surface of the sealing ring between the discs.
In the technical scheme, the space between two adjacent disc bodies is sealed by arranging the inter-disc sealing ring, and the sealing effect is further improved by arranging the inter-disc sealing part; meanwhile, the inter-disc sealing part is integrated on the inter-disc sealing ring, the inter-disc sealing ring is integrated on the disc body, namely the rotor body, the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembling difficulty is reduced.
Preferably, a first sealing ring is arranged on one side, close to the first cylinder, of the disc body assembly, and the first sealing ring is integrally formed on the disc body assembly;
a first sealing part is arranged on the peripheral surface of the first sealing ring; the first sealing portion is used for sealing the labyrinth, and the first sealing portion is integrally formed on the outer peripheral surface of the first sealing ring.
In the technical scheme, the first sealing part is mainly used for sealing, and the sealing effect can be greatly improved by arranging the first sealing part; simultaneously, with first portion of obturating integrated on first obturating ring, with first ring of obturating integrated on the disk body subassembly, integrate promptly on rotor body, realize that overall structure is compacter, reduce the processing degree of difficulty, improve the qualification rate, reduce the assembly degree of difficulty simultaneously.
Preferably, a second sealing ring is arranged on one side, close to the second cylinder, of the disc body assembly, and the second sealing ring is integrally formed on the disc body assembly;
a second sealing part is arranged on the outer peripheral surface of the second sealing ring; the second sealing portion is used for sealing the labyrinth and is integrally formed on the outer peripheral surface of the second sealing ring.
In the technical scheme, the second sealing part is mainly used for sealing, and the sealing effect can be greatly improved by arranging the second sealing part; meanwhile, the second sealing part is integrated on the second sealing ring, the second sealing ring is integrated on the disc body assembly, namely the rotor body, the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembling difficulty is reduced.
Preferably, a shaft shoulder and an internal thread are sequentially arranged on the inner wall surface of one end, far away from the disc body assembly, of the second cylinder body from the direction close to the disc body assembly to the direction far away from the disc body assembly, and the shaft shoulder and the internal thread are integrally formed on the second cylinder body.
In this technical scheme, adopt above-mentioned structural style, the rotor subject passes through internal thread and shaft shoulder installation fixing bearing, and then realizes that high-pressure turbine rotor's axial is spacing to reduce and improve the qualification rate, reduce the assembly degree of difficulty.
Preferably, a third sealing part is arranged on the inner wall surface of one end, close to the disc body assembly, of the second cylinder body;
the third sealing part is a coating.
In the technical scheme, the third sealing part is matched with the labyrinth on the outer surface of the low-pressure turbine shaft in a sealing mode by adopting the structural form, and the sealing device is mainly used for sealing between high-pressure rotors and low-pressure rotors, so that the sealing effect is greatly improved.
Preferably, the outer circumferential surface of the second cylinder body is provided with a fourth sealing part;
the fourth sealing part is used for sealing the labyrinth, and the fourth sealing part is integrally formed on the peripheral surface of the cylinder body.
In the technical scheme, the fourth sealing part is mainly used for sealing, and the sealing effect can be greatly improved by arranging the fourth sealing part; meanwhile, the fourth sealing part is integrated on the rotor main body, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembling difficulty is reduced.
Preferably, an inner wall surface of one end of the first cylinder, which is far away from the tray body assembly, is provided with a connecting spigot.
In this technical scheme, be used for with the connection tang of other parts inter-working through the setting, realize that the assembly precision is higher, reduce the assembly degree of difficulty.
Preferably, the rotor body is of a drum structure.
In this technical scheme, adopt the drum-type structure through rotor subject, promptly, along axial first barrel, disk body subassembly and second barrel intercommunication and integrated into one piece to protruding structural integrity, thereby cancel the connecting piece, reduce weight, structural integrity is higher.
An aircraft engine characterised in that it comprises a high-pressure turbine rotor as described above.
In the technical scheme, the high-pressure turbine rotor adopts the integrated design and manufacturing technical concept, the original part assembly is changed into the integrated design of the part, the structure is simplified, the weight is reduced, the processing difficulty is reduced overall, the assembly difficulty is reduced, the efficiency is improved, and the fuel consumption of the aircraft engine is reduced. Meanwhile, the whole high-pressure turbine rotor is a part, the whole structure is properly reinforced, and the safety and stability of the aircraft engine are improved.
An aircraft characterised in that it comprises an aircraft engine as described above.
In this technical scheme, adopt above-mentioned structural style, adopt integrated design, manufacturing technology theory through the high-pressure turbine rotor, become the structural style of integrated design as a part by original part equipment, realize that the structure is simplified, weight reduction, the processing degree of difficulty reduces to some extent on the whole, reduces the assembly degree of difficulty, raises the efficiency, also contributes to the fuel oil consumption rate decline of aircraft. Meanwhile, the whole high-pressure turbine rotor is a part, the whole structure is properly strengthened, and the safety and stability of the aircraft are improved.
The positive progress effects of the utility model are as follows:
according to the high-pressure turbine rotor, the aircraft engine and the aircraft, the high-pressure turbine rotor adopts the integrated design and manufacturing technical concept, the original part assembly is changed into the structure form of integrally designing the high-pressure turbine rotor into one part, the structure is simplified, the weight is reduced, the assembly difficulty is reduced, the efficiency of the gas compressor is improved, and the fuel consumption is reduced.
Drawings
FIG. 1 is a schematic partial cross-sectional structural view of a high pressure turbine rotor according to an embodiment of the present invention.
Description of the reference numerals
High-pressure turbine rotor 1
Connecting spigot 31
Inter-disc sealing ring 42
Inter-disc sealing portion 421
Shaft shoulder 51
Third sealing part 53
Fourth sealing portion 54
First sealing ring 60
First sealing part 61
Second sealing part 71
Central axis O
Axial direction P
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 provides a high-pressure turbine rotor 1 including: a rotor body 10 and a plurality of blades 20. The high-pressure turbine rotor 1 is arranged symmetrically along the center axis O in fig. 1.
The rotor body 10 comprises a first cylinder 30, a disc assembly 40 and a second cylinder 50 which are sequentially connected along an axial direction P, the disc assembly 40 comprises a plurality of discs 41 which are sequentially stacked along the axial direction P, the discs 41 comprise a first end 411 and a second end 412 from inside to outside along a radial direction, the first ends 411 of the adjacent discs 41 are directly connected, and the second ends 412 of the two adjacent discs 41 have a distance; a plurality of vanes 20 are attached to the outer circumferential surface of the second end 412 of the disc 41; wherein, the first cylinder 30, the plurality of disks 41, the plurality of blades 20, and the second cylinder 50 are integrally formed.
Like this, adopt above-mentioned structural style for high-pressure turbine rotor 1 adopts integrated design, manufacturing technology theory, becomes the structural style of integrated design as a part by original part equipment, thereby has cancelled little parts such as baffle, connecting bolt, nut among the prior art high-pressure turbine rotor 1, and high-pressure turbine rotor 1's structure is simplified, part kind reduces, reduces part quantity, and part quantity reduces to one by hundreds, and the configuration management degree of difficulty reduces, realizes that the structure is simplified, weight reduction. Compared with the prior art that the requirement on the machining precision of a plurality of single pieces is high, the machining difficulty is generally reduced. The integrated design does not need to consider the concentricity problem, does not need single piece assembly, and reduces the assembly difficulty. Due to the adoption of the integrated design, the clearance between parts is eliminated, the aerodynamic loss is reduced, the efficiency is improved, the centrifugal force problem of the blades 20 is eliminated, the rigidity of the high-pressure turbine rotor 1 is improved, and the fuel consumption is reduced. Meanwhile, the whole high-pressure turbine rotor 1 is a part, the whole structure is properly reinforced, and the safety and stability of the high-pressure turbine rotor 1 are improved.
In this embodiment, the number of the disc bodies 41 is two, two disc bodies 41 are sequentially stacked in the axial direction P, the first ends 411 of the two adjacent disc bodies 41 are directly connected, and the second ends 412 have a distance. But not limited thereto, in other embodiments, the number of the disc 41 may be other values, and is not limited herein.
The disc assembly 40 further includes an inter-disc sealing ring 42, the inter-disc sealing ring 42 is connected between two adjacent discs 41 and located between the first end 411 and the second end 412 of the disc 41, and the inter-disc sealing ring 42 is integrally formed with the disc 41. An inter-disc sealing portion 421 is provided on the outer peripheral surface of the inter-disc sealing ring 42; the inter-disc sealing portion 421 is a labyrinth seal, and the inter-disc sealing portion 421 is integrally formed on the outer peripheral surface of the inter-disc sealing ring 42.
Thus, the space between two adjacent disk bodies 41 is sealed by providing the inter-disk sealing ring 42, and the sealing effect is further improved by providing the inter-disk sealing portion 421; meanwhile, the inter-disc sealing portion 421 is integrated on the inter-disc sealing ring 42, and the inter-disc sealing ring 42 is integrated on the disc body 41, that is, on the rotor main body 10, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembly difficulty is reduced.
In this embodiment, a first sealing ring 60 is disposed on a side of the disc assembly 40 close to the first cylinder 30, and the first sealing ring 60 is integrally formed on the disc assembly 40. The first sealing ring 60 is provided with a first sealing portion 61 on its outer peripheral surface. In this embodiment, the first sealing portion 61 is a labyrinth seal, and the first sealing portion 61 is integrally formed on the outer peripheral surface of the first sealing ring 60. The first sealing part 61 is mainly used for sealing, and the sealing effect can be greatly improved by arranging the first sealing part 61; meanwhile, the first sealing part 61 is integrated on the first sealing ring 60, and the first sealing ring 60 is integrated on the disk body assembly 40, namely on the rotor body 10, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembly difficulty is reduced.
In this embodiment, a second sealing ring 70 is disposed on one side of the disk assembly 40 close to the second cylinder 50, and the second sealing ring 70 is integrally formed on the disk assembly 40. The outer peripheral surface of the second seal ring 70 is provided with a second seal portion 71. In the present embodiment, the second sealing portion 71 is a labyrinth seal, and the second sealing portion 71 is integrally formed on the outer peripheral surface of the second sealing ring 70. The second sealing part 71 is mainly used for sealing, and the sealing effect can be greatly improved by arranging the second sealing part 71; meanwhile, the second sealing portion 71 is integrated on the second sealing ring 70, and the second sealing ring 70 is integrated on the disk body assembly 40, namely, the rotor body 10, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembly difficulty is reduced.
In the present embodiment, the inner wall surface of the end of the second cylinder 50 away from the tray assembly 40 is provided with a shoulder 51 and an internal thread 52 in sequence from the direction close to the tray assembly 40 to the direction away from the tray assembly 40, and the shoulder 51 and the internal thread 52 are integrally formed on the second cylinder 50. In this way, the rotor body 10 is provided with the fixed bearing through the internal thread 52 and the shaft shoulder 51, so that the axial limiting of the high-pressure turbine rotor 1 is realized, the qualification rate is reduced, and the assembly difficulty is reduced.
In this embodiment, the inner wall surface of the second cylinder 50 near one end of the tray assembly 40 is provided with a third sealing portion 53. In this embodiment, the third sealing portion 53 is a coating. Therefore, by adopting the structure, the third sealing part 53 is matched with the labyrinth on the outer surface of the low-pressure turbine shaft in a sealing way and the like, and is mainly used for sealing between high-pressure rotors and low-pressure rotors, so that the sealing effect is greatly improved. Of course, in other embodiments, the third obturating portion 53 includes, but is not limited to, a coating, a labyrinth, and the like.
In the present embodiment, the second cylinder 50 has a fourth sealing portion 54 on its outer circumferential surface. In the present embodiment, the fourth sealing portion 54 is a labyrinth seal, and the fourth sealing portion 54 is integrally formed on the outer peripheral surface of the cylinder. Therefore, the four sealing parts are mainly used for sealing, and the sealing effect can be greatly improved by arranging the fourth sealing part 54; meanwhile, the fourth sealing part 54 is integrated on the rotor main body 10, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembly difficulty is reduced.
In the present embodiment, an inner wall surface of one end of the first cylinder 30 away from the tray body assembly 40 has a connection spigot 31. Therefore, the connecting spigot 31 matched with other parts is arranged, so that higher assembling precision is realized, and the assembling difficulty is reduced.
In the present embodiment, the rotor body 10 is a drum structure, that is, the first cylinder 30, the disc assembly 40, and the second cylinder 50 along the axial direction P are communicated and integrally formed. In this way, the rotor body 10 adopts a drum structure to highlight the structural integrity, thereby eliminating the connecting member, reducing the weight and having higher structural integrity. The outer diameter of the second cylinder 50 is smaller than the outer diameter of the first cylinder 30, and the inner diameter of the second cylinder 50 is smaller than the inner diameter of the first cylinder 30.
It should be noted that, in other embodiments, the first sealing portion 61, the second sealing portion 71, and the fourth sealing portion 54 may be other types of seals, such as graphite seals, brush seals, or piston ring seals, and may be adjusted according to specific design requirements. Similarly, the third sealing portion 53 may also be other types of seals, such as a labyrinth seal, a graphite seal, or a piston ring seal, which may be adjusted according to specific design requirements.
The embodiment also discloses an aircraft engine which comprises the high-pressure turbine rotor 1. By adopting the integrated design and manufacturing technical concept of the high-pressure turbine rotor 1, the original structural form that the parts are integrally assembled into one part is changed, the structure is simplified, the weight is reduced, the processing difficulty is generally reduced, the assembly difficulty is reduced, the efficiency is improved, and the fuel consumption of the aircraft engine is reduced. Meanwhile, the whole high-pressure turbine rotor 1 is a part, the whole structure is properly reinforced, and the safety and stability of the aircraft engine are improved.
The embodiment also discloses an aircraft, and the aircraft comprises the aero-engine. By adopting the integrated design and manufacturing technical concept of the high-pressure turbine rotor 1 and changing the original part assembly into the structural form of integrally designing one part, the structure is simplified, the weight is reduced, the processing difficulty is reduced overall, the assembly difficulty is reduced, the efficiency is improved, and the fuel consumption of the aircraft is reduced. Meanwhile, the whole high-pressure turbine rotor 1 is a part, the whole structure is properly strengthened, and the safety and stability of the aircraft are improved.
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 (11)
1. A high pressure turbine rotor, comprising:
the rotor comprises a rotor body, wherein the rotor body comprises a first cylinder, a disc body assembly and a second cylinder which are sequentially connected along the axial direction, the disc body assembly comprises a plurality of disc bodies which are sequentially stacked along the axial direction, the disc bodies comprise a first end and a second end from inside to outside along the radial direction, the first ends of the adjacent disc bodies are directly connected, and the second ends of the two adjacent disc bodies have a distance;
a plurality of blades connected to an outer circumferential surface of the second end of the disc body;
wherein, the first cylinder, a plurality of the disk bodies, a plurality of the blades and the second cylinder are integrally formed.
2. The high-pressure turbine rotor of claim 1, wherein the disk body assembly further includes an inter-disk seal ring connected between two adjacent disk bodies and between the first and second ends of the disk bodies, the inter-disk seal ring being integrally formed with the disk bodies;
the outer peripheral surface of the inter-disc sealing ring is provided with an inter-disc sealing part; the sealing part between the discs is used for sealing the labyrinth, and the sealing part between the discs is integrally formed on the outer peripheral surface of the sealing ring between the discs.
3. The high pressure turbine rotor of claim 1, wherein a side of the disk assembly adjacent the first cylinder is provided with a first seal ring, the first seal ring being integrally formed on the disk assembly;
a first sealing part is arranged on the peripheral surface of the first sealing ring; the first sealing portion is used for sealing the labyrinth, and the first sealing portion is integrally formed on the outer peripheral surface of the first sealing ring.
4. The high pressure turbine rotor of claim 1, wherein a side of the disk assembly adjacent the second cylinder is provided with a second seal ring, the second seal ring being integrally formed on the disk assembly;
a second sealing part is arranged on the outer peripheral surface of the second sealing ring; the second sealing portion is used for sealing the labyrinth and is integrally formed on the outer peripheral surface of the second sealing ring.
5. The high-pressure turbine rotor as claimed in claim 1, wherein an inner wall surface of an end of the second cylinder remote from the disk assembly is provided with a shoulder and an internal thread in order from the end close to the disk assembly to the end remote from the disk assembly, and the shoulder and the internal thread are integrally formed on the second cylinder.
6. The high-pressure turbine rotor as claimed in claim 1, wherein an inner wall surface of an end of the second cylinder close to the disc assembly is provided with a third seal portion;
the third sealing part is a coating.
7. The high pressure turbine rotor as in claim 1, wherein said second cylinder has a fourth seal on its outer circumferential surface;
the fourth sealing part is used for sealing the labyrinth, and the fourth sealing part is integrally formed on the peripheral surface of the cylinder body.
8. The high pressure turbine rotor of claim 1, wherein an inner wall surface of an end of the first cylinder remote from the disc assembly has a connection spigot.
9. The high pressure turbine rotor as in claim 1, wherein said rotor body is of a drum construction.
10. An aircraft engine, characterized in that it comprises a high-pressure turbine rotor according to any one of claims 1 to 9.
11. An aircraft, characterized in that it comprises an aircraft engine according to claim 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121320750.9U CN215949587U (en) | 2021-06-11 | 2021-06-11 | High-pressure turbine rotor, aircraft engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121320750.9U CN215949587U (en) | 2021-06-11 | 2021-06-11 | High-pressure turbine rotor, aircraft engine and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215949587U true CN215949587U (en) | 2022-03-04 |
Family
ID=80565494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121320750.9U Active CN215949587U (en) | 2021-06-11 | 2021-06-11 | High-pressure turbine rotor, aircraft engine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215949587U (en) |
-
2021
- 2021-06-11 CN CN202121320750.9U patent/CN215949587U/en active Active
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