CN111075750A - Low blast loss turbomachinery pivot structure that can balance axial thrust - Google Patents
Low blast loss turbomachinery pivot structure that can balance axial thrust Download PDFInfo
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- CN111075750A CN111075750A CN201911235819.5A CN201911235819A CN111075750A CN 111075750 A CN111075750 A CN 111075750A CN 201911235819 A CN201911235819 A CN 201911235819A CN 111075750 A CN111075750 A CN 111075750A
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- 238000007789 sealing Methods 0.000 claims abstract description 65
- 238000007664 blowing Methods 0.000 claims abstract description 49
- 238000000605 extraction Methods 0.000 claims description 13
- 238000012544 monitoring process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 239000007769 metal material Substances 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910002804 graphite Inorganic materials 0.000 description 3
- 239000010439 graphite Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000000306 component Substances 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/051—Axial thrust balancing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
- F04D29/104—Shaft sealings especially adapted for elastic fluid pumps the sealing fluid being other than the working fluid or being the working fluid treated
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a turbomachine rotating shaft structure with low blast loss and capability of balancing axial thrust, which comprises a rotating shaft, a positive and negative pressure integrated multifunctional pump and the like; wherein, the middle part of the air blowing section of the rotating shaft is provided with an annular groove; the bearing and the thrust load sensor lean against the end walls at the two sides of the blast section; sealing teeth are arranged on the end wall side and the groove side of the blast section of the rotating shaft; the unit shell is a split shell; a bearing chamber, a blast chamber and an axial balance chamber are formed between the rotating shaft and the unit shell; the end wall of the thrust balance arm is provided with a sealing tooth and divides the balance chamber into a left chamber and a right chamber; the sealing rings are arranged in grooves of the blower section of the unit shell and the rotating shaft and are fixed through pin blocks; the pressure sensor is arranged in the air blowing cavity and used for monitoring pressure in real time, the air suction port of the positive and negative pressure integrated multifunctional pump is arranged in the air blowing cavity, and the air jet port is arranged in the left and right axial balance cavities. The invention can be applied to extreme conditions, has simple structure, is economic and reliable, and has wide application prospect.
Description
Technical Field
The invention relates to a rotating shaft structure of a turbine machine, in particular to a rotating shaft structure of a turbine machine, which has low blast loss and can balance axial thrust.
Background
The rotating shaft is used as one of core components in the energy conversion process of the turbine machinery, when the rotating shaft works, torque needs to be transmitted, and the interference of axial thrust and the like caused by the pressure difference between a working area and a non-working area needs to be borne, so that the dynamic characteristics of the rotating shaft have important significance for safe, stable and efficient operation of a system. In recent years, with the increasing demand for power systems in the industrial field, turbomachinery equipment is becoming larger, more intelligent, higher in rotational speed, and higher in energy density. For the rotating shaft, the working load of the rotating shaft is continuously increased, and the high rotating speed not only brings challenges to the critical rotating speed, unbalanced response and stability of the rotating shaft, but also causes the increase of the blowing loss of the rotating system and is not beneficial to the improvement of the system performance. In addition, the axial thrust borne by the rotating shaft is increased due to the large-scale high-energy-density turbine machinery, the requirement of the increasing axial thrust is difficult to meet through the traditional rotating shaft material and the structural design for balancing the axial force, and a new test is brought to the selection of the rotating shaft material and the safety of operation.
Although great achievement is achieved in the aspects of reducing the loss of the rotating shaft and balancing the axial thrust, the current new energy situation puts higher requirements on the turbomachinery, the operating condition of the rotating shaft is worse, and the improvement of the efficiency and the operating safety of the rotating shaft is crucial to the efficient and stable operation of turbomachinery equipment.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a turbomachine rotating shaft structure which has stable operation, small loss, low blast loss and balanced axial thrust and can balance the axial thrust, is a rotating shaft structure which can be applied to high-load extreme operation conditions and has simple structure, high safety and high economy, and has wide application prospect.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a low blast loss turbine mechanical rotating shaft structure capable of balancing axial thrust comprises a rotating shaft, a bearing, a unit shell, a sealing tooth, a thrust balancing arm, a sealing ring, a pin block, a pressure sensor, a positive and negative pressure integrated multifunctional pump and a thrust load sensor; the rotating shaft is a stepped shaft and comprises three parts, namely a bearing section on two sides and a middle air blowing section, and an annular groove is formed in the middle of the air blowing section; the bearing sections on the two sides of the rotating shaft are respectively provided with a bearing and a thrust load sensor, and the bearing and the thrust load sensor are used in a set and lean against the end walls on the two sides of the air blowing section; sealing teeth are arranged on the end wall side and the groove side of the blast section of the rotating shaft; the unit shell is a split shell and comprises an upper cover plate and a lower seat which are detachable, and the unit shell is assembled through external bolts; a bearing chamber, a blast chamber and an axial balance chamber are formed between the rotating shaft and the unit shell (3);
the thrust balance arm is fixed on the unit shell and extends into the axial balance cavity and is used for dividing the axial balance cavity into a left cavity and a right cavity, and sealing teeth are arranged on the end wall of the thrust balance arm; the sealing rings are arranged in grooves of the blower section of the unit shell and the rotating shaft and are fixed through pin blocks;
the pressure sensor is arranged in the air blowing cavity through a through hole in the unit shell and used for monitoring the pressure in the air blowing cavity in real time, the air suction port of the positive and negative pressure integrated multifunctional pump is arranged in the air blowing cavity through the through hole in the unit shell, the air jet port is arranged in the left and right axial balance cavities through the through hole in the thrust balance arm, and the positive and negative pressure integrated multifunctional pump can achieve directional air suction and air blowing.
The invention is further improved in that the sealing teeth are circular teeth, triangular teeth, parabolic teeth, high and low teeth, longitudinal treeing teeth or helical teeth.
The invention is further improved in that the number of the sealing teeth is 3-8, and the ratio of the tooth thickness to the tooth height of the sealing teeth is 0.2-1.
The invention is further improved in that the number of the sealing ring teeth corresponds to the number of the sealing teeth, and the ratio of the tooth thickness to the tooth height is 0.2-1.
The invention has the further improvement that the sealing rings and the sealing teeth are arranged in a tooth-shaped staggered manner to form a staggered tooth type labyrinth sealing unit together, and a plurality of sequentially arranged annular air chambers are formed between the sealing rings and the sealing teeth to increase the flow resistance of the working medium passing through the area.
A further improvement of the invention is that the thrust balancing arm is a circular member.
The invention has the further improvement that a pressure sensor is adopted to monitor the pressure value of the blast cavity in real time during the operation of the rotating shaft, and when the pressure value of the blast cavity is greater than a set value, the positive and negative pressure integrated multifunctional pump performs air extraction through the air extraction opening, so that the pressure value of the blast cavity is always kept in a lower state, and the rotating shaft always keeps lower blast loss.
The invention has the further improvement that in the working process of the rotating shaft, the axial thrust applied to the rotating shaft is obtained through the thrust load sensor, then the pressure of the chambers on the left side and the right side of the axial balance chamber is adjusted through the air jet by the positive-negative pressure integrated multifunctional pump, the axial thrust applied to the rotating shaft is balanced by utilizing the pressure difference on the left side and the right side of the axial balance chamber to be smaller than the allowable axial thrust, and the axial thrust satisfies the following relational expression:
wherein, F0The axial thrust is allowed to be used for the rotating shaft,
when the axial balance chamber does not work, the rotating shaft bears the axial thrust,
for balancing the chamber forces axially, pi being the circumferential ratio, r2Is the radius of the blowing section r1Is the inner radius of the groove of the blowing section, PlFor axially balancing the chamber pressure on the left side, PrTo axially balance the chamber pressure on the right side of the chamber.
The invention has at least the following beneficial technical effects:
1. the invention has reasonable design, simple structure, convenient installation and better reliability, is suitable for various working environments and improves the operating efficiency and the safety of the rotating shaft;
2. labyrinth seal units are arranged on two sides of the air blowing section, the seal units increase the flow resistance of the working medium passing through the area, high-pressure leakage flow is prevented from entering the air blowing chamber, air blowing loss of the air blowing chamber is effectively reduced, and therefore the efficiency of the rotating shaft is improved;
3. the pressure sensor and the extraction opening are arranged in the blast cavity, the pressure sensor monitors the pressure in the blast cavity in real time, and when the pressure in the blast cavity is increased due to the fact that the turbine set is in an extreme operation working condition or a fault operation working condition, the positive-negative pressure integrated multifunctional pump performs air extraction through the extraction opening, so that the pressure value in the blast cavity is always kept in a low state, the rotating shaft is kept in a low blast loss state, and the stability and the robustness of the rotating shaft are improved;
4. thrust load sensors are arranged on two sides of the air blowing section, an axial balance cavity is formed in the middle of the air blowing section, and the air blowing section is divided into a left cavity and a right cavity by a thrust balance arm. In the working process of the rotating shaft, the thrust load sensor monitors the magnitude and direction of the axial thrust borne by the rotating shaft in real time, then the positive-negative pressure integrated multifunctional pump adjusts the pressure of the chambers on the left side and the right side of the axial balance chamber through the air jet, the axial thrust borne by the rotating shaft can be effectively balanced by utilizing the pressure difference on the left side and the right side of the axial balance chamber, the safety and the reliability of the operation of the rotating shaft are improved, and the difficulty of bearing type selection is also reduced;
5. the sealing ring adopts split type profile of tooth sealing ring, and the loading and unloading and change of being convenient for can resume seal structure's performance through simply changing the sealing ring when sealed inefficacy, and the economic nature is high. The sealing ring is made of graphite or a metal material with lower hardness, the hardness of the sealing ring is lower relative to that of a shafting material, and when the sealing assembly is rubbed and ground due to shafting vibration, the sealing ring with lower relative hardness is worn firstly, so that the rotating shaft is not influenced, and the safety of the rotating shaft is improved.
Drawings
FIG. 1 is an axial cross-sectional view of a low windage loss, axial thrust balancing turbomachine rotor shaft configuration of the present invention;
description of reference numerals:
1. the pump comprises a rotating shaft, 2, a bearing, 3, a unit shell, 4, a bearing chamber, 5, a blowing chamber, 6, a sealing tooth, 7, a thrust balance arm, 8, an axial balance chamber, 9, a sealing ring, 10, a pin block, 11, a pressure sensor, 12, a positive-negative pressure integrated multifunctional pump, 13, an air suction port, 14, a thrust load sensor, 15 and an air jet port, wherein the A1, the A2, the B1, the B2 and the C1 are different in cross section.
Detailed Description
The following embodiments of the present invention are described in detail with reference to the accompanying drawings, and the embodiments and specific operations of the embodiments are provided on the premise of the technical solution of the present invention, but the scope of the present invention is not limited to the following embodiments.
As shown in FIG. 1, the rotating shaft structure of the turbomachine with low blowing loss and capability of balancing axial thrust provided by the invention comprises a rotating shaft 1, a bearing 2, a unit shell 3, a bearing chamber 4, a blowing chamber 5, a sealing tooth 6, a thrust balancing arm 7, an axial balancing chamber 8, a sealing ring 9, a pin block 10, a pressure sensor 11, a positive and negative pressure integrated multifunctional pump 12, an extraction opening 13, a thrust load sensor 14 and a gas injection opening 15.
The rotating shaft 1 is a stepped shaft and comprises three parts, namely a bearing section and an air blowing section, which are arranged on two sides, wherein an annular groove is formed in the middle of the air blowing section; the bearing sections on two sides of the rotating shaft 1 are respectively provided with a bearing 2 and a thrust load sensor 14, and the bearing 2 and the thrust load sensor 14 are used in a set and lean against end walls on two sides of the air blowing section; sealing teeth 6 are respectively arranged on the end wall side and the groove side of the air blowing section of the rotating shaft 1. The unit shell 3 is a split shell, comprises a detachable upper cover plate and a lower seat, and is assembled through an external bolt. A bearing chamber 4, a blast chamber 5 and an axial balance chamber 8 are formed between the rotating shaft 1 and the unit shell 3.
The thrust balance arm 7 is fixed on the unit shell 3 and extends into the axial balance chamber 8, and is used for dividing the axial balance chamber 8 into a left chamber and a right chamber, the thrust balance arm 7 can be a round component made of steel (or other metal materials), and the size and the thickness of the round component can meet the requirement of bearing the pressure difference of the axial balance chambers on two sides; the thrust balancing arm 7 is also provided with sealing teeth 6 on the end wall. The sealing teeth 6 can be in various structural forms such as circular teeth, triangular teeth, parabolic teeth, high-low teeth, longitudinal tree teeth and helical teeth, the number of the sealing teeth 6 is 3-8, and the ratio of the tooth thickness to the tooth height of the sealing teeth 6 is 0.2-1.
The principle and the process of the invention mainly comprise the following steps:
during the operation of the rotating shaft 1, a leakage flow working medium with high temperature and high pressure possibly exists on the side A or the side B, and the leakage flow working medium leaks from the high-pressure side to the low-pressure side along a cavity formed by the rotating shaft 1 and the unit shell 3, so that higher pressure is maintained in the blast cavity 5, the high-pressure state of the blast cavity 5 can cause the rotating shaft 1 to generate larger blast loss, the efficiency and the operation reliability of the turbine machinery are reduced, and theoretically, in order to reduce the blast loss, the pressure in the blast cavity 5 needs to be reduced as much as possible. The sealing teeth 6 and the sealing rings 9 at the sections A1 and B1 jointly form a staggered tooth type labyrinth sealing unit, a plurality of annular air chambers which are sequentially arranged are formed between the sealing rings 9 and the sealing teeth 6, when working media pass through the gap between each sealing tooth 6 and the sealing ring 9, the flow area is sharply reduced, the flow speed is increased, the pressure energy of the working media is converted into kinetic energy, and jet flow is formed. And then the jet flow enters the annular air chamber to form vortex, so that the kinetic energy of the working medium is partially converted into heat energy, and the flowing speed of the working medium is reduced. The sealing units at the sections A1 and B1 increase the flow resistance of the working medium passing through the area, prevent high-pressure leakage flow from entering the blast chamber 5, reduce blast loss in the blast chamber 5 and improve the unit efficiency. When a turbine unit is started and stopped, runs under variable working conditions and fails, the rotating shaft 1 can vibrate in an increased amplitude or generate radial displacement, and the like, so that the sealing effect at the sections of A1 and B1 is reduced or fails. According to the invention, the pressure sensor 11 is adopted to monitor the pressure value of the blast cavity 5 in real time, and when the pressure value of the blast cavity 5 is greater than a set value, the positive and negative pressure integrated multifunctional pump 12 performs air extraction through the air extraction opening 13, so that the pressure value of the blast cavity 5 is always kept in a lower state, and the rotating shaft 1 always keeps lower blast loss.
In the turbomachinery working process, pivot 1 not only needs the transmission moment of torsion, still needs to bear the axial thrust that the work area leads to with the regional pressure differential of non-work, and axial thrust can not arouse pivot 1 to take place axial displacement if can not obtain good balance, causes to bump between the sound part and grinds, bumps and grinds and can lead to contact department to produce a large amount of heats, makes the rotor local overheat, probably causes serious accidents such as pivot bending, endangers the safe and stable operation of pivot 1. Thrust load sensors 14 are arranged on the end faces of the two sides of the air blowing section 5 of the rotating shaft 1, so that the axial thrust borne by the rotating shaft can be monitored at any time. The middle part of the air blowing section 5 is provided with an axial balance chamber 8 which is divided into a left chamber and a right chamber by a thrust balance arm 7. In the working process of the rotating shaft 1, the axial thrust applied to the rotating shaft is obtained through the thrust load sensor 14, then the pressure of the chambers on the left side and the right side of the axial balance chamber 8 is adjusted through the air jet 15 by the positive-negative pressure integrated multifunctional pump 12, the axial thrust applied to the rotating shaft 1 is balanced by utilizing the pressure difference on the left side and the right side of the axial balance chamber 8, so that the axial thrust is smaller than the allowable axial thrust, and the relation is satisfied as follows:
wherein, F0The axial thrust is allowed to be used for the rotating shaft,
when the axial balance chamber does not work, the rotating shaft bears the axial thrust,
for balancing the chamber forces axially, pi being the circumferential ratio, r2Is the radius of the blowing section r1Is the inner radius of the groove of the blowing section, PlFor axially balancing the chamber pressure on the left side, PrTo axially balance the chamber pressure on the right side of the chamber.
Meanwhile, labyrinth seal units are arranged at the sections A1 and B1, high-pressure gas in the axial balance chamber 8 is prevented from leaking to the air blowing chambers on two sides, and the pressure in the air blowing chamber 5 is guaranteed not to be influenced by the pressure change in the axial balance chamber 8. The labyrinth seal unit at the section of C1 prevents the high-pressure side gas in the axial balance chamber 8 from leaking to the low-pressure side, and ensures the normal and stable function of the axial balance chamber 8.
In addition, the sealing ring 9 is made of graphite or a metal material with low hardness, the hardness is low relative to a shafting material, when the sealing assembly is rubbed and ground due to shafting vibration, the sealing ring 9 with low relative hardness is firstly worn, the rotating shaft 1 is not affected, and the safety of the rotating shaft 1 is improved; the sealing ring 9 adopts a split type design, is convenient to assemble, disassemble and replace, and can recover the performance of the sealing structure by simply replacing the sealing ring 9 when the sealing fails. The turbomachine rotating shaft structure with low blast loss and capability of balancing the axial thrust can automatically balance the axial thrust according to the operation working condition, simultaneously reduce the blast loss of the rotating shaft, and ensure that the rotating shaft can still run efficiently and stably under extreme conditions.
Claims (8)
1. A turbomachine rotating shaft structure with low blast loss and capability of balancing axial thrust is characterized by comprising a rotating shaft (1), a bearing (2), a unit shell (3), a sealing tooth (6), a thrust balancing arm (7), a sealing ring (9), a pin block (10), a pressure sensor (11), a positive and negative pressure integrated multifunctional pump (12) and a thrust load sensor (14); wherein,
the rotating shaft (1) is a step-shaped shaft and comprises three parts, namely a bearing section on two sides and a middle air blowing section, wherein the middle part of the air blowing section is provided with an annular groove; the bearing sections on two sides of the rotating shaft (1) are respectively provided with a bearing (2) and a thrust load sensor (14), and the bearing (2) and the thrust load sensor (14) are used in a set and lean against the end walls on two sides of the air blowing section; sealing teeth (6) are respectively arranged on the end wall side and the groove side of the air blowing section of the rotating shaft (1); the unit shell (3) is a split shell, comprises an upper cover plate and a lower seat which are detachable, and is assembled through an external bolt; a bearing chamber (4), a blast chamber (5) and an axial balance chamber (8) are formed between the rotating shaft (1) and the unit shell (3);
the thrust balance arm (7) is fixed on the unit shell (3) and extends into the axial balance chamber (8) to divide the axial balance chamber (8) into a left chamber and a right chamber, and the end wall of the thrust balance arm (7) is provided with a sealing tooth (6); the sealing ring (9) is arranged in grooves of the blower section of the unit shell (3) and the rotating shaft (1) and is fixed through a pin block (10);
pressure sensor (11) are arranged in blast air cavity (5) through the through-hole on unit casing (3) for real-time supervision blast air cavity (5) internal pressure, the extraction opening (13) of positive negative pressure integral type multifunctional pump (12) are arranged in blast air cavity (5) through the through-hole on unit casing (3), jet orifice (15) are arranged in left and right axial balance cavity (8) through the through-hole on thrust balance arm (7), directional air extraction and blast air can be realized to positive negative pressure integral type multifunctional pump (12).
2. The rotating shaft structure of a turbomachine with low blowing loss and balanced axial thrust according to claim 1, wherein the seal teeth (6) are circular teeth, triangular teeth, parabolic teeth, high-low teeth, longitudinal tree teeth or helical teeth.
3. The rotating shaft structure of the turbomachine with low blowing loss and balanced axial thrust according to claim 1, wherein the number of the seal teeth (6) is 3-8, and the ratio of the tooth thickness to the tooth height of the seal teeth (6) is 0.2-1.
4. The rotating shaft structure of the turbomachinery with low blowing loss and balanced axial thrust as claimed in claim 1, wherein the number of teeth of the seal ring (9) corresponds to the number of teeth of the seal teeth (6), and the ratio of the tooth thickness to the tooth height is between 0.2 and 1.
5. The rotating shaft structure of the turbomachine with low blowing loss and balanced axial thrust as claimed in claim 4, characterized in that the seal rings (9) and the seal teeth (6) are arranged in a tooth-like staggered manner to form a staggered tooth labyrinth seal unit, and a plurality of annular air chambers are formed between the seal rings (9) and the seal teeth (6) and arranged in sequence to increase the flow resistance of the working medium passing through the area.
6. A low windage balanced axial thrust turbomachine rotor shaft arrangement as claimed in claim 1, characterised in that the thrust balancing arms (7) are circular members.
7. The rotating shaft structure of the turbomachine with low blowing loss and balanced axial thrust as claimed in claim 1, characterized in that during the operation of the rotating shaft (1), the pressure sensor (11) is used to monitor the pressure value of the blowing chamber (5) in real time, when the pressure value of the blowing chamber (5) is greater than a set value, the positive and negative pressure integrated multifunctional pump (12) performs air extraction through the air extraction opening (13), so as to ensure that the pressure value of the blowing chamber (5) is always kept in a low state, and the rotating shaft (1) always keeps low blowing loss.
8. The rotating shaft structure of the turbomachine with low blowing loss and balanced axial thrust as claimed in claim 1, wherein during the operation of the rotating shaft (1), the magnitude and direction of the axial thrust applied to the rotating shaft are obtained through the thrust load sensor (14), then the positive-negative pressure integrated multifunctional pump (12) adjusts the pressure of the chambers on the left and right sides of the axial balance chamber (8) through the air jet (15), and the axial thrust applied to the rotating shaft (1) is balanced by utilizing the differential pressure on the left and right sides of the axial balance chamber (8) to be smaller than the allowable axial thrust, which satisfies the following relational expression:
wherein, F0The axial thrust is allowed to be used for the rotating shaft,
when the axial balance chamber does not work, the rotating shaft bears the axial thrust,
for balancing the chamber forces axially, pi being the circumferential ratio, r2Is the radius of the blowing section r1Is the inner radius of the groove of the blowing section, PlFor axially balancing the chamber pressure on the left side, PrTo axially balance the chamber pressure on the right side of the chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911235819.5A CN111075750A (en) | 2019-12-05 | 2019-12-05 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911235819.5A CN111075750A (en) | 2019-12-05 | 2019-12-05 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111075750A true CN111075750A (en) | 2020-04-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911235819.5A Pending CN111075750A (en) | 2019-12-05 | 2019-12-05 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
Country Status (1)
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| CN (1) | CN111075750A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112343668A (en) * | 2020-11-03 | 2021-02-09 | 上海齐耀动力技术有限公司 | Thrust balance system of supercritical carbon dioxide TAC unit and control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014081901A1 (en) * | 2012-11-20 | 2014-05-30 | New Way Machine Components, Inc. | Air bearing for use as seal |
| CN107939699A (en) * | 2017-12-04 | 2018-04-20 | 南京磁谷科技有限公司 | A kind of magnetic suspension compressor structure |
| US20180209425A1 (en) * | 2017-01-24 | 2018-07-26 | Onesubsea Ip Uk Limited | Mechanical barrier fluid pressure regulation for subsea systems |
| CN109882425A (en) * | 2019-03-15 | 2019-06-14 | 湖南泛航智能装备有限公司 | Axial force balance and sealing structure and high power density centrifugal blower |
| CN211288202U (en) * | 2019-12-05 | 2020-08-18 | 西安交通大学 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
-
2019
- 2019-12-05 CN CN201911235819.5A patent/CN111075750A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014081901A1 (en) * | 2012-11-20 | 2014-05-30 | New Way Machine Components, Inc. | Air bearing for use as seal |
| US20180209425A1 (en) * | 2017-01-24 | 2018-07-26 | Onesubsea Ip Uk Limited | Mechanical barrier fluid pressure regulation for subsea systems |
| CN107939699A (en) * | 2017-12-04 | 2018-04-20 | 南京磁谷科技有限公司 | A kind of magnetic suspension compressor structure |
| CN109882425A (en) * | 2019-03-15 | 2019-06-14 | 湖南泛航智能装备有限公司 | Axial force balance and sealing structure and high power density centrifugal blower |
| CN211288202U (en) * | 2019-12-05 | 2020-08-18 | 西安交通大学 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112343668A (en) * | 2020-11-03 | 2021-02-09 | 上海齐耀动力技术有限公司 | Thrust balance system of supercritical carbon dioxide TAC unit and control method |
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Inventor after: Shi Dongbo Inventor after: Li Jinxing Inventor after: Xie Yonghui Inventor after: Zhang Di Inventor before: Xie Yonghui Inventor before: Li Jinxing Inventor before: Shi Dongbo Inventor before: Zhang Di |