CN209743239U - Novel gas turbine compressor rotor - Google Patents
Novel gas turbine compressor rotor Download PDFInfo
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- CN209743239U CN209743239U CN201920580498.1U CN201920580498U CN209743239U CN 209743239 U CN209743239 U CN 209743239U CN 201920580498 U CN201920580498 U CN 201920580498U CN 209743239 U CN209743239 U CN 209743239U
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Abstract
The utility model relates to a novel gas turbine compressor rotor, including the pivot, be equipped with the location plectane in the pivot, the upper end of location plectane is equipped with the low pressure impeller, and the excircle downside of low pressure impeller is equipped with low pressure side boss, and the upper portion of low pressure impeller is equipped with low pressure long blade and low pressure short blade respectively, and the lower extreme of location plectane is equipped with the high pressure impeller, and the excircle upside of high pressure impeller is equipped with the high pressure side boss, and the high pressure impeller still includes high pressure long blade and high pressure short blade, and the low pressure impeller is equipped with the impeller seal tooth with the outside of high pressure impeller. The utility model discloses a low pressure impeller leans on with the high pressure impeller back of the body mutually, and the length of pivot shortens, and structural strength improves, and the axial force at pivot both ends also can offset each other, has guaranteed the stability of pivot under high rotational speed, and simultaneously, impeller seal tooth and interstage seal tooth can reduce interstage gas leakage loss, make the high pressure ratio become more excellent, the circulation parameter of effectual improvement combustion engine, the operation is stable, and the reliability is splendid.
Description
Technical Field
The utility model belongs to the technical field of gas turbine's compressor, in particular to novel gas turbine compressor rotor.
Background
The gas turbine engine is also called as a combustion engine, the combustion engine has a series of advantages of small volume, light weight, quick start and the like, has been developed in various fields, is widely applied to the fields of power generation, ship power, vehicle power, natural gas, petroleum pipeline transportation and the like, and is an important embodiment of national science and technology, industry and national defense strength. Therefore, it is important to improve the overall performance and reliability of the internal combustion engine.
In a small and medium-sized gas turbine compressor rotor, the reliability of the high pressure ratio of the traditional gas turbine compressor rotor at a high rotating speed is extremely poor, the overall performance parameters of the gas turbine mainly depend on the pressure ratio of the gas turbine, the high rotating speed and multiple stages of the gas turbine rotor are needed to realize the high pressure ratio of the gas turbine, but the axial force on one side of the rotor at the high critical rotating speed is usually large when the span is increased along with the increase of the rotating speed and the increase of a rotor rotating shaft, and the stability and the reliability of the rotor are extremely poor at the moment, so that the improvement of the overall performance of the gas turbine is limited, and the overall performance of.
SUMMERY OF THE UTILITY MODEL
The invention provides a novel gas compressor rotor of a gas turbine, which aims to solve the technical problems of poor axial and radial stability and poor reliability of the proposed longer rotor at high revolution.
The utility model provides a technical scheme that above-mentioned technical problem took is: a novel gas turbine compressor rotor is structurally characterized by comprising a rotating shaft, wherein the rotating shaft is in a shape that two ends are thinner, the middle part of the rotating shaft is thicker and is in uniform transition, a concave ring is arranged in the middle of the rotating shaft, a bulge is arranged above the concave ring, a positioning circular plate is arranged below the concave ring, a low-pressure impeller is arranged at the upper end of the positioning circular plate, a low-pressure side boss is arranged on the lower side of the excircle of the low-pressure impeller, a low-pressure long blade and a low-pressure short blade are respectively arranged on the upper part of the low-pressure impeller, a bent front section is arranged at one end of the low-pressure long blade, the outer side of the low-pressure long blade is in a C-shaped arc shape, a high-pressure impeller is arranged at the lower end of the positioning circular plate, a high-pressure side boss is arranged on the upper side of the excircle of the high-pressure, the outer part of the positioning circular plate is provided with interstage sealing teeth, the lower end of the rotating shaft is provided with a positioning hole, and the plane of the lower end of the rotating shaft is provided with a threaded hole.
Furthermore, the low-pressure long blades and the low-pressure short blades are uniformly distributed on the circumference and are spaced from each other.
Furthermore, the low-pressure long blades and the low-pressure short blades, the high-pressure long blades and the high-pressure short blades are in an S-shaped back bending shape, and the number of the low-pressure long blades is 13.
Furthermore, the high-pressure long blades and the high-pressure short blades have the same distribution form and the same number as the low-pressure long blades and the low-pressure short blades.
Further, the outer diameter of the low-pressure impeller is larger than that of the high-pressure impeller, and the outer diameter of the maximum circle where the high-pressure side boss is located is smaller than that of the minimum circle where the low-pressure side boss is located.
Further, the low-pressure impeller and the high-pressure impeller are arranged back to back.
furthermore, the threaded holes are uniformly distributed according to the axis of the rotating shaft.
the utility model has the advantages that: the utility model adopts the arrangement that the low pressure impeller and the high pressure impeller are arranged in a leaning way, so that the length of the rotating shaft is shortened, the structural strength of the rotating shaft is improved, meanwhile, gas enters from the axial direction through the low pressure long blade and is discharged from the high pressure long blade, the bending directions of the low pressure long blade and the high pressure long blade are opposite, so that the axial forces at two ends of the rotating shaft can be mutually offset, the stability of the rotating shaft at high rotating speed is effectively ensured, and the service life is prolonged; in addition, the impeller seal teeth and the interstage seal teeth can reduce interstage gas leakage loss, so that the high pressure ratio becomes better, the cycle parameters of the combustion engine are effectively improved, the operation is stable, and the reliability is excellent.
Drawings
Fig. 1 is a schematic front view of the present invention;
Fig. 2 is a schematic structural diagram of the present invention;
Fig. 3 is a schematic structural view of the low pressure impeller of the present invention;
Fig. 4 is a schematic structural view of the high-pressure impeller of the present invention;
In the figure: the rotary shaft, the concave ring 11, the convex ring 12, the positioning circular plate 2, the low-pressure impeller 3, the boss on the low-pressure side 31, the long low-pressure blade 32, the short low-pressure blade 33, the bent front section 34, the high-pressure impeller 4, the boss on the high-pressure side 41, the long high-pressure blade 42, the short high-pressure blade 43, the tail arc plate 44, the impeller sealing teeth 5, the sealing teeth between 6 stages, the positioning hole 7 and the threaded hole 8.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The components of the embodiments of the present invention, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiment of the present invention, all other embodiments obtained by the person skilled in the art without creative work belong to the protection scope of the present invention.
as an example, as shown in fig. 1, fig. 2, fig. 3 and fig. 4, a novel gas turbine compressor rotor is structurally characterized in that, a rotating shaft 1 is included, the rotating shaft 1 can be in a shape with two thinner ends and thicker middle part and uniform transition, a concave ring 11 can be arranged in the middle of the rotating shaft 1, a protrusion 12 can be arranged above the concave ring 11, a positioning circular plate 2 can be arranged below the concave ring 11, a low pressure impeller 3 can be arranged at the upper end of the positioning circular plate 2, a low pressure side boss 31 can be arranged at the lower side of the outer circle of the low pressure impeller 3, a low pressure long blade 32 and a low pressure short blade 33 can be respectively arranged at the upper part of the low pressure impeller 3, a curved front section 34 can be arranged at one end of the low pressure long blade 32, a C-shaped arc can be arranged at the outer side of the low pressure long blade 32, a high pressure impeller 4 can be arranged at the lower end of the positioning circular plate 2, a high pressure side boss, the tail end of the high-pressure long blade 42 can be provided with a tail arc plate 44, the bending direction of the high-pressure long blade 42 can be opposite to that of the low-pressure long blade 32, the outer sides of the low-pressure impeller 3 and the high-pressure impeller 4 can be provided with impeller sealing teeth 5, the outer part of the positioning circular plate 2 can be provided with interstage sealing teeth 6, the lower end of the rotating shaft 1 can be provided with a positioning hole 7, and the plane of the lower end of the rotating shaft 1 can be provided with a threaded.
Preferably, the low pressure long blades 32 and the low pressure short blades 33 may be spaced apart from each other and uniformly distributed on the low pressure impeller 3.
Preferably, the low pressure long blades 32 and the low pressure short blades 33, and the high pressure long blades 42 and the high pressure short blades 43 may be S-shaped and bent back, and the number of the low pressure long blades 32 may be 13.
preferably, the distribution pattern of the high-pressure long blades 42 and the high-pressure short blades 43 and the distribution pattern of the low-pressure long blades 32 and the low-pressure short blades 33 can be the same and the number of the high-pressure long blades and the low-pressure short blades can be equal.
Preferably, the outer diameter of the low pressure impeller 3 may be larger than that of the high pressure impeller 4, and the outer diameter of the maximum circle where the high pressure side boss 41 is located may be smaller than the minimum diameter of the circle where the low pressure side boss 31 is located.
Preferably, the low pressure impeller 3 and the high pressure impeller 4 may be arranged back to back.
Preferably, the threaded holes 8 may be uniformly distributed according to the axial center of the rotating shaft.
The utility model discloses an in the embodiment, the apparatus comprises a rotating shaft 1, location plectane 2, low pressure impeller 3 and high pressure impeller 4 an organic whole are made, the blank adopts the forging, then carry out whole machining shaping, low pressure long blade 32 and low pressure short blade 33 quantity are 13 pieces respectively, looks interval evenly distributed each other, crooked anterior segment 34 meets with concave ring 11's the most depressed point, the protruding 12 in upper portion of concave ring 11 can block the low pressure air current in concave ring 11, can be provided with impeller seal tooth 5 on the arch 12, impeller seal tooth 5 can prevent the leakage of low pressure gas, reduce the gas leakage loss of low pressure compressor, concave ring 11 can make the gaseous volume increase of low pressure end, the stability that the low pressure axial was admitted air has been guaranteed, location plectane 2 simultaneously is connected with low pressure impeller 3 and high pressure impeller 4 respectively, can increase low pressure impeller 3 and high pressure impeller 4's structural strength, the interstage seal tooth 6 that low pressure impeller 3 and high pressure impeller 4 and location plectane 2 set up can prevent low The leakage of a low-pressure impeller 3 of the gas compressor reduces the leakage loss between stages; in addition, the high pressure long vane 42 can be opposite to the bending direction of the low pressure long vane 32, and the gas is discharged from the low pressure impeller 3 through the high pressure impeller 4, at this time, an axial force is generated between the low pressure impeller 3 and the high pressure impeller 4 to the positioning circular plate 2, because of the action of bending the front section 34 and the tail arc plate 44, the axial forces borne by the two ends of the positioning circular plate 2 can be mutually offset, thereby ensuring the service life of the radial bearings at the two ends of the rotating shaft 1, guaranteed simultaneously that the whole thing that the drunkenness beat can not appear takes place, pivot 1 length is sweet potato axle form for a short time, is difficult for appearing the beat vibration that intensity arouses inadequately during the gyration, makes 1 gyration of pivot more stable, has guaranteed the friction loss of pivot 1 under the high rotational speed, makes the rotatory revolution of rotor improve to some extent, axial and radial stability reinforcing, and the leakproofness is good, long service life, and the reliability is extremely strong.
The utility model has the advantages that: the utility model discloses a low pressure impeller 3 leans on the setting with 4 backs of high pressure impeller, makes the length of pivot 1 shorten, has guaranteed the stability of pivot 1 under the high rotational speed, the structural strength of pivot 1 improves, simultaneously, gaseous entering and discharging by high pressure long blade 42 through low pressure long blade 32 by the axial, the bending direction of low pressure long blade 32 and high pressure long blade 42 is opposite, the axial force that the air current that the low pressure end got into the high pressure end produced the axial force and can make the axial force at pivot 1 both ends offset each other, the effectual stationarity of guaranteeing the pivot 1 under high-speed operation, life reinforcing; in addition, the impeller seal teeth 5 and the interstage seal teeth 6 can reduce interstage gas leakage loss, so that the high pressure ratio is better, the circulation parameters of the combustion engine are effectively improved, the operation is stable, and the reliability is excellent.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be dominated by the protection scope of the claims.
Claims (7)
1. A novel gas turbine compressor rotor is characterized in that: the high-pressure impeller comprises a rotating shaft, wherein the rotating shaft is in a shape that two ends are thinner, the middle part is thicker and is in uniform transition, a concave ring is arranged in the middle of the rotating shaft, a bulge is arranged above the concave ring, a positioning circular plate is arranged below the concave ring, a low-pressure impeller is arranged at the upper end of the positioning circular plate, a low-pressure side boss is arranged on the lower side of the excircle of the low-pressure impeller, a low-pressure long blade and a low-pressure short blade are respectively arranged on the upper part of the low-pressure impeller, one end of the low-pressure long blade is provided with a bending front section, the outer side of the low-pressure long blade is in a C-shaped arc shape, a high-pressure impeller is arranged at the lower end of the positioning circular plate, a high-pressure side boss is arranged on the upper side of the excircle of the high-pressure impeller, the high-pressure, the lower end of the rotating shaft is provided with a positioning hole, and a threaded hole is formed in the plane of the lower end of the rotating shaft.
2. A new gas turbine compressor rotor according to claim 1, characterized in that: the low-pressure long blades and the low-pressure short blades are uniformly distributed on the circumference and are spaced from each other.
3. A new gas turbine compressor rotor according to claim 1, characterized in that: the low-pressure long blades and the low-pressure short blades and the high-pressure long blades and the high-pressure short blades are both in an S-shaped back bending shape, and the number of the low-pressure long blades is 13.
4. A new gas turbine compressor rotor according to claim 1, characterized in that: the high-pressure long blades and the high-pressure short blades have the same distribution form and the same number as the low-pressure long blades and the low-pressure short blades.
5. A new gas turbine compressor rotor according to claim 1, characterized in that: the outer diameter of the low-pressure impeller is larger than that of the high-pressure impeller, and the outer diameter of the maximum circle where the high-pressure side boss is located is smaller than that of the minimum circle where the low-pressure side boss is located.
6. A new gas turbine compressor rotor according to claim 1, characterized in that: the low-pressure impeller and the high-pressure impeller are arranged back to back.
7. A new gas turbine compressor rotor according to claim 1, characterized in that: the threaded holes are uniformly distributed according to the axis of the rotating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920580498.1U CN209743239U (en) | 2019-04-26 | 2019-04-26 | Novel gas turbine compressor rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920580498.1U CN209743239U (en) | 2019-04-26 | 2019-04-26 | Novel gas turbine compressor rotor |
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| Publication Number | Publication Date |
|---|---|
| CN209743239U true CN209743239U (en) | 2019-12-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920580498.1U Active CN209743239U (en) | 2019-04-26 | 2019-04-26 | Novel gas turbine compressor rotor |
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| CN (1) | CN209743239U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113757134A (en) * | 2021-07-28 | 2021-12-07 | 浙江镕达永能压缩机有限公司 | Centrifugal steam compressor with back-to-back arrangement of double impellers |
| CN113833675A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Impeller and air compressor with same |
-
2019
- 2019-04-26 CN CN201920580498.1U patent/CN209743239U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113757134A (en) * | 2021-07-28 | 2021-12-07 | 浙江镕达永能压缩机有限公司 | Centrifugal steam compressor with back-to-back arrangement of double impellers |
| CN113757134B (en) * | 2021-07-28 | 2023-07-14 | 浙江镕达永能压缩机有限公司 | Centrifugal vapor compressor with double impellers arranged in back-to-back manner |
| CN113833675A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Impeller and air compressor with same |
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