CN112377272B - Centripetal turbine axial force adjusting device - Google Patents
Centripetal turbine axial force adjusting device Download PDFInfo
- Publication number
- CN112377272B CN112377272B CN202011374180.1A CN202011374180A CN112377272B CN 112377272 B CN112377272 B CN 112377272B CN 202011374180 A CN202011374180 A CN 202011374180A CN 112377272 B CN112377272 B CN 112377272B
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- turbine
- pressure area
- hole
- volute
- shell
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a centripetal turbine axial force adjusting device, comprising: the device comprises a shell, a main shaft, a turbine, a volute and a diversion cone; one end of the turbine is combined with the volute and the main shaft to form a low-pressure area A; the other end of the turbine is combined with the volute to form a high-pressure area B; the turbine, the shell and the diversion cone are combined to form a secondary high pressure area C; along with the expansion work of the turbine, a first fluid medium positioned in the high-pressure area B enters the low-pressure area A; and a second fluid medium located in the high pressure zone B enters the secondary high pressure zone C; the volute through hole is formed in one end, close to the low-pressure area A, of the volute; a shell adjusting hole is formed in one end, close to the secondary high-pressure area C, of the shell; and a flow regulating assembly is arranged on the shell regulating hole and used for regulating and controlling the flow of the second fluid medium in the secondary high-pressure area C into the low-pressure area A. Through add flow control assembly on the shell regulation hole, make exhaust flow controllable, strengthened unit operating stability, reduced energy loss.
Description
Technical Field
The invention relates to the technical field of centripetal turbine structures, in particular to a centripetal turbine axial force adjusting device.
Background
In the existing centripetal turbine device, a fluid medium enters from an air inlet of the centripetal turbine, one part of the fluid medium pushes the turbine to do work, and the other part of the fluid medium flows to a secondary high-pressure area close to the air inlet along with the expansion work of the turbine, so that the gas pressure in the secondary high-pressure area acts on a cover plate on the left side of the turbine to generate a rightward axial thrust. The fluid medium in the secondary high pressure area flows into the low pressure area through the communicated pore canal, so that the pressure difference at two sides of the turbine can be reduced, and the aim of reducing the axial force is fulfilled.
However, the flow rate of the exhaust gas flowing to the low-pressure area in the secondary high-pressure area cannot be controlled, so that the axial force is unstable easily, and the normal operation of the centripetal turbine device is seriously influenced.
In addition, the excessive flow of the fluid medium in the secondary high pressure zone through the communicating channels into the low pressure zone can result in excessive energy losses. In addition, the pressure difference of two sides of the turbine seal is increased due to the fact that the gas pressure in the secondary high-pressure area is excessively reduced, so that the leakage of the turbine seal is increased, energy loss is further increased, and finally the efficiency of the unit is affected.
Disclosure of Invention
In order to solve the problems, the invention aims to provide the centripetal turbine axial force adjusting device, which is characterized in that a flow adjusting component is additionally arranged on a shell adjusting hole, so that the flow of a fluid medium in a secondary high-pressure area to a low-pressure area through the shell adjusting hole and a volute through hole is controllable, the axial force is adjustable, the running stability of a unit is enhanced, the energy loss is reduced, and the problems that the device is unstable and the energy loss is increased due to the fact that the exhaust flow is uncontrollable and the exhaust flow is overlarge in the existing centripetal turbine device are solved.
In order to achieve the above object, the technical scheme of the present invention is as follows.
A centripetal turbine axial force adjustment device comprising:
a housing in which a spindle is disposed;
a turbine provided at an end of the main shaft;
The volute is arranged between the turbine and the shell, and one end of the turbine, the volute and the main shaft are combined to form a low-pressure area A; the other end of the turbine is combined with the volute to form a high-pressure area B; a volute through hole is formed in one end, close to the low-pressure area A, of the volute;
The guide cone is arranged at one end of the shell, and the turbine, the shell and the guide cone are combined to form a secondary high-pressure area C;
Along with the expansion work of the turbine, a first fluid medium positioned in the high-pressure area B enters the low-pressure area A; and a second fluid medium located in the high pressure zone B enters the secondary high pressure zone C;
Wherein, one end of the shell close to the secondary high pressure area C is provided with a shell adjusting hole; and the shell adjusting hole is provided with a flow adjusting component for adjusting and controlling the flow of the second fluid medium in the secondary high-pressure area C into the low-pressure area A.
Further, a first turbine seal is arranged between the volute and one end of the turbine close to the low-pressure area A, and the first turbine seal is used for forming a rotary seal.
Further, a second turbine seal is arranged between the housing and one end of the turbine close to the secondary high pressure area C, and is used for forming a rotary seal.
Further, the flow rate of the first fluid medium is greater than the flow rate of the second fluid medium.
Further, the shell and the volute are combined to form a volute cavity, and the volute cavity is communicated with the low-pressure area A through the volute through hole; the volute chamber is communicated with the secondary high pressure area C through the shell adjusting hole.
Further, the shell adjusting hole is an L-shaped hole, and a mounting hole is formed in the side wall, close to the bevel part of the shell adjusting hole, of the shell and is used for mounting the flow adjusting assembly, and the mounting hole is communicated with the shell adjusting hole.
Still further, the flow regulating assembly includes:
The adjusting rod is provided with an installation hole, one end of the adjusting rod penetrates through the installation hole and extends into the shell adjusting hole, and the adjusting rod is used for adjusting the flow section of the shell adjusting hole;
The compression nut is sleeved on the other end of the adjusting rod and is in threaded connection with the adjusting rod;
The sealing gasket is arranged in the mounting hole, and the lower end of the compression nut is abutted against the sealing gasket;
The lock nut is fixedly arranged on the mounting hole; the compression nut is in threaded connection with the locking nut.
Further, the number of the volute through holes is 1-4.
The invention has the beneficial effects that:
1. according to the device, as the turbine expands to do work, most of the fluid medium in the high-pressure area B enters the low-pressure area A, and the other part enters the secondary high-pressure area C, and the fluid medium in the secondary high-pressure area C sequentially passes through the shell adjusting hole and the volute through hole and enters the low-pressure area A.
Through add flow control assembly on the shell regulation hole, make the fluid medium of secondary high pressure district C flow direction low pressure district A's flow controllable through shell regulation hole and spiral case through-hole to make axial force adjustable, strengthened unit operating stability, reduced energy loss, solved the unable control of exhaust flow that exists among the current centripetal turbine device and lead to the unstable device and the too big problem that leads to energy loss to increase of exhaust flow.
2. The device can control the flow of the fluid medium through the flow cross section area in the regulating hole of the shell through the flow regulating component so as to control the flow, thereby effectively regulating and controlling the pressure in the secondary high pressure area C.
The pressure acts on the turbine, creating an axial force to the right; the axial force can be controlled to be in a reasonable interval of the thrust bearing load by controlling the pressure in the secondary high pressure area C; therefore, the pressure difference at two sides of the turbine rotary seal can be effectively regulated and controlled, and the running stability of the unit can be enhanced while the energy loss is reduced.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Fig. 2 is a schematic partial structure of the upper half of fig. 1.
Fig. 3 is a schematic structural diagram of the M portion in fig. 2.
In the figure: 1. a housing; 2. a main shaft; 3. a turbine; 4. a volute; 5. a volute through hole; 6. a diversion cone; 7. a housing adjustment aperture; 8. a flow regulating assembly; 801. an adjusting rod; 802. a compression nut; 803. a sealing gasket; 804. a lock nut; 9. a first turbine seal; 10. a second turbine seal; 11. a volute chamber; 12. a mounting hole;
A low pressure zone A; a high-voltage region B; secondary high pressure zone C.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1, a schematic structural diagram of a radial inflow turbine axial force adjusting device according to an embodiment of the present invention is provided, where the radial inflow turbine axial force adjusting device includes: a housing 1, a turbine 3, a volute 4 and a cone 6.
Referring to fig. 1, the end of the housing 1 is connected to a centripetal turbine inlet 13; the end of the housing is provided with a fixing part facing axially inwards, and the middle of the fixing part is provided with a through groove. After entering from the inlet 13 of the centripetal turbine, the fluid medium enters one side of the turbine through the through groove and pushes the turbine to do work.
A main shaft 2 is arranged in the shell 1; the turbine 3 is provided at an end of the main shaft 2. The turbine is in interference fit connection with the main shaft and is in rigid connection. One end of the turbine, which faces the air inlet of the centripetal turbine, is abutted with the fixed part of the shell and is rotatably connected.
The volute 4 is arranged between the turbine 3 and the shell 1, and one end of the turbine 3, the volute 4 and the main shaft 2 are combined to form a low-pressure area A; the other end of the turbine 3 is combined with the volute 4 to form a high-pressure area B; the end of the volute 4 near the low-pressure area A is provided with a volute through hole 5. In this embodiment, the number of the scroll through holes 5 is 1 to 4, and can be set as appropriate. The arrangement of the volute through hole mainly plays a role in reducing the pressure in the secondary high-pressure area, and guides the fluid medium in the secondary high-pressure area C to flow into the low-pressure area A finally after passing through the shell adjusting hole and then passing through the volute through hole.
The diversion cone 6 is arranged at one end of the shell 1 close to the centripetal turbine air inlet 13; the turbine 3, the casing 1 and the guide cone 6 combine to form a sub-high pressure region C. The guide cone is arranged in the radial inflow opening 13 of the radial inflow turbine and is connected in a sealing and detachable manner to the fastening part of the housing by means of a screw. The size of the diversion cone gradually increases along the flowing direction of the fluid medium to form a cone-shaped structure. The fluid medium in the air inlet of the centripetal turbine enters one side of the turbine after passing through the through groove in the fixing part of the shell under the diversion effect of the diversion cone, and pushes the turbine to do work.
As the turbine 3 expands to do work, the first fluid medium in the high-pressure area B enters the low-pressure area A; and a second fluid medium located in the high pressure zone B enters the secondary high pressure zone C; and the flow rate of the first fluid medium is greater than the flow rate of the second fluid medium. Of course, the fluid medium is gaseous. After the turbine does work, most of the fluid medium enters the low-pressure area A, and a small part of the fluid medium enters the secondary high-pressure area C due to leakage of the turbine sealing element, and the low-pressure area A and the secondary high-pressure area C are respectively positioned at two sides of the high-pressure area B.
The gas pressure in the secondary high pressure area C acts on the left cover plate of the turbine to generate a rightward axial force, the acting position of the axial force is on the turbine, and the turbine is in interference fit connection with the main shaft, so that the axial force finally acts on the main shaft to form a rightward acting force.
In order to conveniently adjust the gas pressure in the secondary high pressure area C so as to conveniently adjust the axial force, one end of the shell 1, which is close to the secondary high pressure area C, is provided with a shell adjusting hole 7; the flow regulating assembly 8 is arranged on the shell regulating hole 7 and is used for regulating and controlling the flow of the second fluid medium in the secondary high-pressure area C into the low-pressure area A.
In this embodiment, as the turbine expands to perform work, a large portion of the fluid medium in the high-pressure region B enters the low-pressure region a, a small portion enters the sub-high-pressure region C, and the fluid medium in the sub-high-pressure region C sequentially passes through the housing adjustment hole and the volute through hole and enters the low-pressure region a. The flow adjusting assembly is additionally arranged on the shell adjusting hole, so that the flow of the fluid medium in the secondary high-pressure area C flowing to the low-pressure area A through the shell adjusting hole and the volute through hole is controllable, the axial force is adjustable, the running stability of the unit is enhanced, and the energy loss is reduced.
Of course, the device can control the flow cross-section area of the fluid medium in the regulating hole of the shell through the flow regulating component so as to control the flow, thereby effectively regulating and controlling the pressure in the secondary high pressure area C, and the pressure acts on the turbine to generate rightward axial force; the axial force can be controlled to be in a reasonable interval of the thrust bearing load by controlling the pressure in the secondary high-pressure area C, so that the pressure difference at two sides of the turbine rotary seal can be effectively regulated and controlled, namely the pressure difference of the high-pressure area B towards the secondary high-pressure area C, and the running stability of the unit can be enhanced while the energy loss is reduced.
Referring to fig. 1 to 2, a first turbine seal 9 is provided between the end of the turbine 3 adjacent to the low pressure region a and the volute 4 for forming a rotary seal. A second turbine seal 10 is provided between the end of the turbine 3 adjacent the secondary high pressure region C and the casing 1 for forming a rotary seal. The second fluid medium in the high-pressure zone B flows into the secondary high-pressure zone C as a result of the sealing leakage of the second turbine seal.
Specifically, a volute chamber 11 is formed by combining the housing 1 and the volute 4, and the volute chamber 11 is communicated with the low-pressure area A through the volute through hole 5; the volute chamber 11 communicates with the secondary high pressure region C through the housing adjustment aperture 7. That is, one end of the housing adjustment aperture communicates with the volute chamber and the other end communicates with the secondary high pressure region C. One end of the volute through hole is communicated with the volute cavity, and the other end of the volute through hole is communicated with the low-pressure area A. Thereby, the secondary high pressure zone C and the low pressure zone a can be communicated, and the fluid medium in the secondary high pressure zone C is led into the low pressure zone a.
Referring to fig. 2 to 3, the housing adjusting hole 7 is an L-shaped hole, and a mounting hole 12 is provided on a sidewall of the housing 1 near a corner of the housing adjusting hole 7 for mounting the flow adjusting assembly 8, and the mounting hole 12 is communicated with the housing adjusting hole 7. For example, one end of the housing adjusting hole facing the secondary high pressure area C is a vertical hole, one end of the housing adjusting hole facing the volute chamber is a transverse hole, and the mounting hole is located on the upper side of the vertical hole and on the same axis as the vertical hole. The lower end of the flow regulating assembly is inserted into the upper end of the vertical hole, so that the flow section can be regulated between the vertical hole and the transverse hole.
When the displacement of the flow regulating assembly and the upper end of the vertical hole is regulated, the blocking area of the transverse hole can be regulated, and then the flow of the fluid medium flowing into the low-pressure area A from the secondary high-pressure area C can be controlled, so that the pressure in the secondary high-pressure area C is in a reasonable range where the second turbine sealing element can bear the load, and the axial force can be regulated and controlled, so that the running stability of the unit can be improved.
Referring to fig. 3, the flow rate adjusting assembly 8 includes: an adjustment rod 801, a compression nut 802, a gasket 803, and a lock nut 804.
One end of the adjusting rod 801 passes through the mounting hole 12 and extends into the housing adjusting hole 7 for adjusting the flow section of the housing adjusting hole 7; the adjusting lever here mainly serves as a flow restrictor, by means of which the flow rate of the fluid medium flowing in the secondary high-pressure region C towards the low-pressure region a in the housing adjusting bore can be adjusted.
The compression nut 802 is sleeved on the other end of the adjusting rod 801 and is in threaded connection with the adjusting rod 801; the gasket 803 is provided in the mounting hole 12, and the lower end of the compression nut 802 abuts against the gasket 803. For example, the mounting hole has a stepped cross-sectional shape, the compression nut 802 and the gasket are pressed tightly against the upper end of the stepped mounting hole, and the adjustment rod extends to the lower end of the mounting hole and is positioned in the housing adjustment hole. The number of the sealing gaskets can be 1-4, and the sealing gaskets can be arranged according to actual needs. The sealing gasket is mainly used for improving the tightness of the flow regulating assembly in the mounting hole and avoiding leakage of fluid media.
Of course, in other embodiments, the compression nut and the adjusting screw may be fixedly connected, for example, welded or integrally formed, and the matched compression nut and the adjusting screw are compressed in the mounting hole together after accurate calculation, so that the flow cross-sectional area of the housing adjusting hole is effectively adjusted.
The lock nut 804 is fixedly arranged on the mounting hole 12; compression nut 802 is threadably coupled to lock nut 804.
During the use, through setting up the regulation pole of corresponding height to adjust the cross-sectional area that overflows in the regulation hole of shell through adjusting the pole and effectively adjust, be used for regulating and controlling the flow rate of the fluid medium of inferior high pressure district C flow direction low pressure district A in the regulation hole of shell, and improve the leakproofness through the quantity of corresponding gasket, and through gland nut and lock nut's thread tightening, be used for locking, thereby improve the leakproofness of mounting hole when realizing that the flow rate is adjustable.
In addition, the fluid flow in the outer shell adjusting hole can be accurately measured through the flow rate meter. The end of the adjusting rod is adjusted to form the size of the cross section area of the through flow to the adjusting hole of the shell, and the pressure difference at two sides of the turbine is effectively regulated and controlled by matching with the detected flow velocity, so that the purpose of stably regulating and controlling the axial force is achieved.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (8)
1. A centripetal turbine axial force adjustment apparatus, comprising:
A housing (1) in which a spindle (2) is arranged;
a turbine (3) provided at an end of the main shaft (2);
a volute (4) arranged between the turbine (3) and the housing (1), wherein one end of the turbine (3) is combined with the volute (4) and the main shaft (2) to form a low-pressure area A; the other end of the turbine (3) is combined with the volute (4) to form a high-pressure area B; a volute through hole (5) is formed in one end, close to the low-pressure area A, of the volute (4);
The diversion cone (6) is arranged at one end of the shell (1); the turbine (3), the shell (1) and the diversion cone (6) are combined to form a secondary high pressure area C;
Along with expansion work of the turbine (3), a first fluid medium positioned in the high-pressure area B enters the low-pressure area A; and a second fluid medium located in the high pressure zone B enters the secondary high pressure zone C;
wherein, one end of the shell (1) close to the secondary high pressure area C is provided with a shell adjusting hole (7); the secondary high-pressure area C is communicated with the low-pressure area A through a shell adjusting hole (7) and a volute through hole (5); and the shell adjusting hole (7) is provided with a flow adjusting component (8) for adjusting and controlling the flow of the second fluid medium in the secondary high-pressure area C into the low-pressure area A, so as to adjust and control the pressure in the secondary high-pressure area C.
2. A centripetal turbine axial force adjustment device according to claim 1, characterized in that a first turbine seal (9) is provided between the end of the turbine (3) near the low-pressure region a and the volute (4) for forming a rotary seal.
3. A centripetal turbine axial force adjustment device according to claim 1, characterized in that a second turbine seal (10) is provided between the housing (1) and an end of the turbine (3) near the secondary high-pressure region C for forming a rotary seal.
4. The radial inflow turbine axial force adjustment device of claim 1, wherein the flow rate of the first fluid medium is greater than the flow rate of the second fluid medium.
5. The centripetal turbine axial force adjustment device according to claim 1, characterized in that a volute chamber (11) is formed between said casing (1) and said volute (4), said volute chamber (11) being in communication with said low-pressure area a through said volute through hole (5); the volute chamber (11) communicates with the secondary high pressure region C through the housing adjustment aperture (7).
6. The centripetal turbine axial force adjustment device according to claim 1, wherein the housing adjustment hole (7) is an L-shaped hole, and a mounting hole (12) is provided on a side wall of the housing (1) near a corner portion of the housing adjustment hole (7) for mounting the flow adjustment assembly (8), and the mounting hole (12) is in communication with the housing adjustment hole (7).
7. The centripetal turbine axial force adjustment device according to claim 6, wherein said flow adjustment assembly (8) comprises:
the adjusting rod (801), one end of the adjusting rod (801) passes through the mounting hole (12) and extends into the shell adjusting hole (7) for adjusting the flow cross section of the shell adjusting hole (7);
The compression nut (802) is sleeved on the other end of the adjusting rod (801) and is in threaded connection with the adjusting rod (801);
A gasket (803) provided in the mounting hole (12), the lower end of the compression nut (802) being in contact with the gasket (803);
the lock nut (804) is fixedly arranged on the mounting hole (12); the compression nut (802) is in threaded connection with the lock nut (804).
8. Centripetal turbine axial force adjustment device according to claim 1, characterized in that the number of volute through holes (5) is 1-4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011374180.1A CN112377272B (en) | 2020-11-30 | 2020-11-30 | Centripetal turbine axial force adjusting device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011374180.1A CN112377272B (en) | 2020-11-30 | 2020-11-30 | Centripetal turbine axial force adjusting device |
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| Publication Number | Publication Date |
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| CN112377272A CN112377272A (en) | 2021-02-19 |
| CN112377272B true CN112377272B (en) | 2024-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011374180.1A Active CN112377272B (en) | 2020-11-30 | 2020-11-30 | Centripetal turbine axial force adjusting device |
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| CN (1) | CN112377272B (en) |
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| FR2915535B1 (en) * | 2007-04-30 | 2009-07-24 | Snecma Sa | ROTATING MACHINE COMPRISING A PASSIVE AXIAL BALANCING SYSTEM |
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| CN1497148A (en) * | 2002-10-17 | 2004-05-19 | ͨ�õ�����˾ | Method and apparatus for controlling fluid flow in a gas turbine engine |
| CN101663466A (en) * | 2007-06-26 | 2010-03-03 | 博格华纳公司 | Variable geometry turbocharger |
| CN102661174A (en) * | 2012-02-24 | 2012-09-12 | 苏州制氧机有限责任公司 | Supercharged turbo expander |
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|---|---|
| CN112377272A (en) | 2021-02-19 |
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