CN112343668A - Thrust balance system of supercritical carbon dioxide TAC unit and control method - Google Patents
Thrust balance system of supercritical carbon dioxide TAC unit and control method Download PDFInfo
- Publication number
- CN112343668A CN112343668A CN202011210913.8A CN202011210913A CN112343668A CN 112343668 A CN112343668 A CN 112343668A CN 202011210913 A CN202011210913 A CN 202011210913A CN 112343668 A CN112343668 A CN 112343668A
- Authority
- CN
- China
- Prior art keywords
- motor shaft
- compressor
- thrust
- turbine
- air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- 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
- F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
- F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- 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
- F04D29/0513—Axial thrust balancing hydrostatic; hydrodynamic thrust bearings
-
- 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
Abstract
The invention discloses a thrust balancing system of a supercritical carbon dioxide TAC unit, which comprises: a motor having a motor shaft; the turbine and the compressor are coaxially arranged at two ends of a motor shaft along the axial direction, and a turbine impeller and a compressor impeller are arranged oppositely; the thrust balancing unit is arranged between the turbine and the compressor and comprises a first balancing chamber arranged between the turbine and the motor and a second balancing chamber arranged between the compressor and the motor, working media are introduced into the balancing chambers on the two sides through the air entraining adjusting structure and the air quantity is adjusted, and the working media respectively form thrust opposite to the direction of the motor shaft in the balancing chambers on the two sides, so that the adjustment of resultant force on the motor shaft is realized. The invention adopts the coaxial design of the compressor and the turbine, the compressor is driven by the turbine, one driving motor is reduced, the structure is compact, the total resultant force on the motor shaft is reduced, the power consumption of the bearing is reduced, and the efficiency is improved; and meanwhile, the axial thrust is balanced and controlled, and the safe operation of the unit is ensured.
Description
Technical Field
The invention belongs to the technical field of power, and relates to a thrust balancing system and a control method for a supercritical carbon dioxide TAC unit.
Background
The supercritical carbon dioxide Brayton cycle power generation technology is a closed cycle turbine power generation technology adopting supercritical carbon dioxide as a working medium, is a leading-edge technology which is rapidly developed in recent years, and has the advantages of high cycle efficiency, wide power coverage range (hundreds of kilowatts to hundreds of megawatts), high power density, low vibration noise and the like.
The TAC (Turbine-Alternator-Compressor, also called Turbine-starter motor-Compressor) unit is a power generation core device in the supercritical carbon dioxide Brayton power generation system, and the sizes of the Compressor and the Turbine in the TAC unit can be greatly reduced due to the high density characteristic of the supercritical carbon dioxide, so that the impeller mechanical part structure is compact, and the improvement of the energy density of a power device is facilitated. However, the supercritical carbon dioxide compressor and the turbine have high working pressure, and the thrust on the single side of the turbine impeller and the compressor impeller is high, so that the temperature rise of the bearing is easily caused, the power consumption of the bearing is increased, and the transmission efficiency is reduced.
Disclosure of Invention
In order to solve the technical problems, the invention provides a coaxial design of the compressor and the turbine, the compressor is driven by the turbine, one driving motor is reduced, the structure is compact, the total resultant force on a motor shaft is reduced, the power consumption of a bearing is reduced, and the efficiency is improved. However, thrust changes of the compressor and the turbine in the processes of starting, running and the like are inconsistent, changes of axial clearance and even reverse play are easily caused, and if the axial clearance changes seriously, a motor shaft and a casing can be rubbed, so that the safe running of the TAC unit is influenced. Therefore, the axial thrust needs to be balanced and controlled, the safe operation of the TAC unit is ensured, and the influence on the performance of the TAC unit is reduced to the minimum. Therefore, the supercritical carbon dioxide TAC unit thrust balancing system and the control method provided by the invention have the advantages that the structure is compact, the operation cost is reduced, the axial thrust of the motor shaft is convenient to balance, the resultant force on the motor shaft is reduced so as to reduce the power consumption of the bearing, and the efficiency is improved.
One of the purposes of the invention is to provide a thrust balancing system of a supercritical carbon dioxide TAC unit, which adopts the following technical scheme:
a thrust balancing system of a supercritical carbon dioxide (TAC) unit comprises:
a motor having a motor shaft;
the turbine and the compressor are respectively coaxially arranged at two ends of the motor shaft along the axial direction, and the turbine impeller and the compressor impeller are arranged oppositely;
a thrust balancing unit provided between the turbine and the compressor; the thrust balancing unit comprises a first balancing chamber arranged between the turbine and the motor and a second balancing chamber arranged between the compressor and the motor, working media are introduced into the first balancing chamber and the second balancing chamber through the air entraining adjusting structure and the air quantity is adjusted, and the working media form thrust opposite to the direction of the motor shaft in the first balancing chamber and the second balancing chamber respectively so as to adjust resultant force on the motor shaft.
Preferably, the two ends of the motor close to the turbine and the compressor are respectively provided with a first bearing and a second bearing, and the first bearing and the second bearing are respectively arranged in the first bearing seat and the second bearing seat;
a first balance chamber is formed between the first bearing seat and the turbine, and a second balance chamber is formed between the second bearing seat and the compressor.
Further, the first bearing seat is fixedly connected with a shell of the turbine into a whole through a first seal box, the first seal box is fixedly connected with a motor shaft through a first dry gas seal element, a first partition plate is sleeved on the outer surface, close to a turbine impeller and facing the motor, of the motor shaft, the tail end, far away from the motor shaft, of the first partition plate is connected with the turbine shell in a sealing mode, and a first balance chamber is defined by the first partition plate, the first dry gas seal element, the turbine shell and the first seal box;
the second bearing seat is fixedly connected with the shell of the compressor into a whole through a second sealing box, the second sealing box is fixedly connected with the motor shaft through a second dry gas sealing element, a second partition plate is sleeved on the outer surface, close to the impeller of the compressor and facing the motor, of the motor shaft, the tail end, far away from the motor shaft, of the second partition plate is connected with the shell of the compressor in a sealing mode, and a second balance chamber is defined by the second partition plate, the second dry gas sealing element, the shell of the compressor and the second sealing box;
and the direction of the first dry gas sealing element subjected to the working medium load in the first balance chamber is opposite to the direction of the second dry gas sealing element subjected to the working medium load in the second balance chamber, and the resultant force of the first dry gas sealing element and the second dry gas sealing element along the axial direction is adjusted through the air-entraining adjusting mechanism.
Furthermore, the air-entraining adjusting structure comprises a first air-entraining channel and a second air-entraining channel which are respectively arranged on the first sealing box and the second sealing box, and the first air-entraining channel and the second air-entraining channel are respectively communicated with the working medium outlet of the compressor through a first pressure regulating valve and a second pressure regulating valve;
working medium pressures in the first balance chamber and the second balance chamber are adjusted through the first air-entraining channel and the second air-entraining channel, and the load directions of the working medium acting on the first dry air sealing element and the second dry air sealing element are opposite, so that the adjustment of resultant force on a motor shaft is realized.
The first air-entraining channel and the second air-entraining channel are respectively communicated with the air tank for storing working media through a third pressure regulating valve and a fourth pressure regulating valve.
Furthermore, the first air-entraining channel and the second air-entraining channel are respectively provided with a plurality of air-entraining channels.
Furthermore, the first air-entraining channel and the second air-entraining channel are arranged into a bending cavity or an inclined cavity forming an included angle with the motor shaft.
Furthermore, an oil seal ring is arranged on one side of the first bearing facing the turbine, and an oil seal ring is arranged on one side of the second bearing facing the compressor.
Furthermore, the first dry gas sealing element and the second dry gas sealing element comprise a first dry gas sealing movable ring and a second dry gas sealing static ring which are respectively sleeved at two end parts of the motor shaft, the second dry gas sealing movable ring and the second dry gas sealing static ring, the first dry gas sealing movable ring and the second dry gas sealing movable ring are positioned through a shaft shoulder of the motor shaft, and sealing end faces are formed between the first dry gas sealing static ring and the first dry gas sealing movable ring and between the second dry gas sealing static ring and the second dry gas sealing movable ring.
Furthermore, thrust sensors are respectively arranged on the thrust discs on the two sides of the first bearing and the second bearing along the axial direction.
The thrust sensor, the first regulating valve, the second regulating valve, the third regulating valve and the fourth regulating valve are all electrically connected with the controller.
The invention also aims to provide a thrust balance control method of the supercritical carbon dioxide TAC unit, which utilizes the thrust balance system to carry out the following steps:
one path of working medium at the outlet of the compressor enters a first balance chamber at the side of the turbine, the flow is controlled by the air entraining adjusting mechanism, and the thrust of the working medium in the first balance chamber acting on the motor shaft is adjusted; the other path of the working medium enters a second balance chamber at the side of the compressor, the flow is controlled by the air-entraining adjusting mechanism, and the thrust of the working medium in the second balance chamber acting on the motor shaft is adjusted; the compressor and the turbine are coaxially arranged at two ends of the motor shaft, and the thrust of the working medium in the first balance cavity acting on the motor shaft is opposite to the thrust of the working medium in the second balance cavity acting on the motor shaft, so that the resultant force on the motor shaft is adjusted.
The invention can bring the following beneficial effects:
1) the compressor and the turbine are respectively arranged at the shaft ends at the two sides of the motor, and the compressor and the turbine are driven by the motor when the motor is started; when the rated rotation speed is reached, the turbine drives the compressor to do work and drives the motor to generate electricity, compared with the arrangement mode that the motor is connected with the compressor and the generator is connected with the turbine in the traditional TAC set, the structure is more compact, one motor is reduced, and the operation cost is reduced; and the total resultant force on the motor shaft can be reduced, the power consumption of the bearing is reduced, and the operation efficiency of the unit is improved.
2) Two balance chambers are respectively formed at the shaft ends of two sides of the motor, the turbine impeller and the compressor impeller are oppositely arranged at two ends of the motor shaft, and the load directions of the working medium acted on the compressor impeller and the turbine impeller are opposite, so that the pressure in the two balance chambers is changed through the air-entraining adjusting structure, the acting forces of the working medium acted on the turbine impeller and the compressor impeller in opposite directions are respectively adjusted, and finally the resultant force on the motor shaft is reduced.
3) Two balance chambers are respectively formed at the shaft ends of two sides of the motor, dry gas sealing elements are respectively arranged at two ends of the motor shaft, and the load directions of working media acting on a first dry gas sealing movable ring and a second dry gas sealing movable ring are opposite; therefore, the thrust acting on the dry gas sealing dynamic rings on the two sides can be flexibly adjusted by adjusting the working medium pressure of the balance chambers on the two sides, and the thrust balance along the opposite directions of the two sides in the axial direction is realized.
4) The thrust sensors are directly arranged on the thrust discs on the two sides of the bearing, so that the thrust balance device has the advantages of high measurement accuracy, high precision and low time delay, and the function of real-time thrust balance is realized more favorably.
In conclusion, the stress on the compressor impeller, the turbine impeller and the dry gas seal moving rings on the two sides in the thrust balancing system is mutually offset, and the resultant force on the motor shaft is reduced, so that the thrust acting on the bearing on the motor shaft can be effectively reduced, the power consumption of the bearing is reduced, and the transmission efficiency is improved; and the working medium gas amount is adjusted and controlled through the thrust force fed back by the thrust sensor at the bearing, and the flow of high-pressure working medium gas entering the balance chamber is changed, so that the pressure in the balance chambers at two sides is adjusted, the axial thrust of the TAC unit is kept in a reasonable range in the starting and stopping process and normal operation conditions, and the aim of low bearing power consumption on a motor shaft is fulfilled. In addition, the design provided by the invention can be applied to other rotating machines, and the applicability is wide.
Drawings
FIG. 1 is a schematic structural diagram of a thrust balancing system of a supercritical carbon dioxide TAC unit.
Fig. 2 is a partially enlarged structural view of the first balance chamber of fig. 1.
Fig. 3 is a partially enlarged structural view of the second equilibrium chamber of fig. 1.
FIG. 4 is a schematic diagram of thrust balance control of the supercritical carbon dioxide TAC unit.
The notations in the figures have the following meanings:
1-a motor; 10-motor shaft; 11-a first bearing; 110-a first bearing seat; 111-a first sealed cartridge; 112-a first dry gas seal element; 1120 a first dry gas seal moving ring; 1121-first dry gas seal stationary ring; 12-second bearing, 120-second bearing seat, 121-second seal cartridge, 122-second dry gas seal element, 1220-second dry gas seal dynamic ring, 1221-second dry gas seal static ring; 13-a thrust sensor; 2-a turbine; 20-a turbine casing; 21-a turbine wheel; 22-a first separator; 3-a compressor; 30-compressor housing; 31-a compressor wheel; 32-a second separator; 4-thrust balancing unit, 41-first balancing chamber; 42-a second equilibrium chamber; 5-a bleed air adjusting mechanism; 51-a first bleed air channel; 52-a second bleed air channel; 53-a first pressure regulating valve; 54-a second pressure regulating valve; 55-a third pressure regulating valve; 56-fourth pressure regulating valve; 6-oil seal ring; 7-gas tank.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, embodiments accompanying the present application are described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth to provide a thorough understanding of the present application, and in the accompanying drawings, preferred embodiments of the present application are set forth. This application may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete. This application is capable of embodiments in many different forms than those described herein and those skilled in the art will be able to make similar modifications without departing from the spirit of the application and it is therefore not intended to be limited to the specific embodiments disclosed below.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product.
Further, in the description of the present application, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise. In the description of the present application, "a number" means at least one, such as one, two, etc., unless specifically limited otherwise.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
According to the present embodiment, a thrust balancing system of a supercritical carbon dioxide TAC unit is provided, as shown in fig. 1, including: a motor 1, the motor 1 having a motor shaft 10;
a turbine 2 and a compressor 3 coaxially provided at both ends of the motor shaft 10 in the axial direction, respectively, and having a turbine wheel 21 and a compressor wheel 31 disposed to face each other;
a thrust balancing unit 4 provided between the turbine 2 and the compressor 3; the thrust balancing unit 4 comprises a first balancing chamber 41 arranged between the turbine 2 and the motor 1 and a second balancing chamber 42 arranged between the compressor 3 and the motor 1, working media are introduced into the first balancing chamber 41 and the second balancing chamber 42 through the air-entraining adjusting structure 5 and the air quantity is adjusted, and the working media form thrust opposite to the direction of the motor shaft 1 in the first balancing chamber 41 and the second balancing chamber 42 respectively so as to adjust resultant force on the motor shaft 10.
According to the embodiment, the compressor 2 and the turbine 3 are respectively arranged at the two side shaft ends of the motor, and the compressor and the turbine are driven by the motor during starting; under the design state, the turbine 2 drives the compressor 3 to do work and drags the motor 1 to generate electricity, and compared with the traditional arrangement mode that a motor is connected with the compressor and a generator is connected with the turbine in a TAC unit, the structure is more compact, and meanwhile, one motor is reduced, and the operation cost is reduced. And because the turbine impeller 21 and the compressor impeller 31 are coaxially arranged oppositely, loads with different sizes and opposite directions are respectively applied to the motor shaft 10, two balance chambers are respectively formed at the two side shaft ends of the motor 1, working medium is introduced through the air-entraining adjusting structure 5, so that the working medium respectively forms thrust with opposite directions to the motor shaft 1 in the balance chambers at the two sides, the acting thrust in the balance chambers at the two sides is adjusted by changing the pressure in the two balance chambers, and further the resultant force applied on the motor shaft 10 can be adjusted on the basis of the loads applied to the motor shaft by the turbine impeller and the compressor impeller, wherein the resultant force comprises the direction and the size of the resultant force. The axial direction referred to in this application represents the axial direction of the motor shaft.
As a preferred embodiment, the motor 1 is provided with a first bearing 11 and a second bearing 12 near two ends of the turbine 2 and the compressor 3, respectively, and the first bearing 11 and the second bearing 12 are respectively disposed in the first bearing seat 110 and the second bearing seat 120; a first balance chamber 41 is formed between the first bearing housing 110 and the turbine 2, and a second balance chamber 42 is formed between the second bearing housing 120 and the compressor 3. Similarly, by changing the pressure in the balance chambers on both sides, the axial thrust acting on the motor shaft 10 can be conveniently adjusted, reducing the wear on the bearings on both sides. Wherein, the first bearing 11 is provided with an oil seal ring 6 on one side facing the turbine 2, and the second bearing 12 is provided with an oil seal ring on one side facing the compressor 3, so as to prevent the lubricating oil in the bearings from leaking outwards, and further prevent the working medium in the balance chambers on both sides from entering the motor 1.
Preferably, the first bearing seat 110 is fixedly connected with the housing 20 of the turbine 2 through a first seal box 111, specifically, the first bearing seat 110 is fixed on the first seal box 111 through bolts, the first seal box 111 is fixed on the turbine housing 20 through bolts, the first seal box 111 is fixedly connected with the motor shaft 10 through a first dry gas seal element 112, a first partition plate 22 is sleeved on the outer surface of the motor shaft 10 close to the turbine impeller 21 and facing the motor, and the end of the first partition plate 22 far away from the motor shaft 10 is connected with the turbine housing 20 in a sealing manner (that is, the impeller 21 of the turbine 2 is provided with the first partition plate 22 on the outer surface facing the motor 1, the first partition plate 22 is sleeved on the motor shaft 10, and the end of the first partition plate 22 far away from the motor shaft 10 is connected with the turbine housing 20 in a sealing manner), and the first partition plate 22 is sealed with the turbine impeller 21 through comb teeth, a first balance chamber 41 is enclosed among the first partition plate 22, the first dry gas sealing element 112, the turbine housing 20 and the first seal box 111;
the second bearing seat 120 is fixedly connected with the housing 30 of the compressor 3 as a whole through a second seal box 121, specifically, the second bearing seat 120 is fixed on the second seal box 121 through bolts, the second seal box 121 is fixed on the housing 30 of the compressor 3 through bolts, the second seal box 121 is fixedly connected with the motor shaft 10 through a second dry gas seal element 122, a second partition plate 32 is sleeved on the outer surface of the motor shaft 10 close to the compressor impeller 31 and facing the motor 1, and the end of the second partition plate 32 far away from the motor shaft 10 is connected with the compressor housing 30 and the second seal box 121 in a sealing manner (that is, the impeller 31 of the compressor 3 is provided with the second partition plate 32 on the outer surface facing the motor 1, the second partition plate 32 is sleeved on the motor shaft 10, and the end of the second partition plate 32 far away from the motor shaft 10 is connected with the compressor housing 30 in a sealing manner), a second balance chamber 42 is enclosed among the second partition plate 22, the second dry gas sealing element 122, the compressor shell 30 and the second seal box 121;
and the direction of the first dry gas sealing element 112 subjected to the working medium load in the first balance chamber is opposite to the direction of the second dry gas sealing element 122 subjected to the working medium load in the second balance chamber, and the resultant force of the first dry gas sealing element 112 and the second dry gas sealing element 122 along the axial direction is adjusted through the bleed air adjusting mechanism 5.
According to the embodiment, dry gas sealing structures are arranged on both sides of the motor shaft 10, so that working media can be prevented from leaking to the motor side; working medium pressures in the first balance chamber and the second balance chamber are adjusted through the bleed air adjusting mechanism 5, and the load directions of the first dry air sealing element 112 and the second dry air sealing element 122 along the axial direction are opposite, so that the resultant force on the motor shaft 10 is reduced. As shown in fig. 2 and 3, the working medium enters the first/second balance chamber 41/42, then enters the back of the turbine/compressor impeller through the first/second partition plate 32 through the comb seal, and flows into the main flow, so as to form pressure on the turbine/compressor impeller, and the load directions of the working medium acting on the turbine impeller 21 and the compressor impeller 31 are also opposite, but considering that the pressure formed by the gas flow of the part is small, the adjustment of the load force on the motor shaft 10 is mainly the working medium pressure in the opposite direction formed by the working medium on the first/second dry gas seal element. In practical applications, the first dry gas sealing element 112 and the second dry gas sealing element 122 are disposed in axial symmetry on both sides of the motor shaft 10. It should be noted that the first balance chamber on the turbine side and the second balance chamber on the compressor side may be the same or different in shape and size, and specific shapes and design parameters may be adjusted as required, only the relative sealing in the balance chambers needs to be ensured, and only a small amount of working medium flows out from the comb teeth seal and enters the main flow, so as to form a high-pressure environment for the dry gas seal element in the balance chamber, and generate thrust in opposite directions for the first/second dry gas seal elements.
As a more preferred embodiment, the bleed air adjusting structure 5 includes a first bleed air passage 51 and a second bleed air passage 52 respectively disposed on the first sealing box 111 and the second sealing box 121, the first/second bleed air passage 51/52 is respectively communicated with the working medium outlet of the compressor 3 through a first/second pressure regulating valve 53/54, and the working medium pressures in the first balance chamber 41 and the second balance chamber 42 are adjusted through the first bleed air passage 51 and the second bleed air passage 52, so that the load directions of the working medium acting on the first dry air sealing element 112 and the second dry air sealing element 122 are opposite, and the resultant force applied to the motor shaft 10 is reduced. The number of the first bleed air channels 51 and the number of the second bleed air channels 52 are respectively set to be several, and may be set to be 1 or more according to requirements; the first bleed air channel 51 and the second bleed air channel 52 are bent or inclined cavities forming an included angle with the motor shaft. The specific shape and design parameters can be adjusted as desired.
In order to ensure safe operation, a reserve-regulated gas tank 7 is added to the thrust balancing system, and the first/second bleed air channel 51/52 is also communicated with the gas tank 7 for storing working medium via a third/fourth pressure regulating valve 55/56. The gas tank 7 of the invention stores a certain amount of high-pressure working medium, when the gas quantity led from the outlet of the compressor can not meet the regulation requirement, the gas quantity can be regulated by regulating the third pressure regulating valve 55 and the fourth pressure regulating valve 56, thereby balancing the thrust of the dry gas sealing dynamic rings at two sides along the left and right directions of the motor shaft 10 in the figure.
The first/second dry gas sealing element 112/122 includes a first/second dry gas sealing dynamic ring 1120/1220 and a first/second dry gas sealing static ring 1121/1221, which are sleeved on two end portions of the motor shaft 10, the first/second dry gas sealing dynamic ring 1120/1220 is positioned by a shaft shoulder of the motor shaft 10, and the first/second dry gas sealing static ring 1121/1221 and the first/second dry gas sealing dynamic ring 1120/1220 form a sealing end face. Specifically, the dry gas sealing element belongs to a commonly used structural member in the prior art, as shown in fig. 2 and 3, a sealing end face generally adopts an annular wedge groove, a sealing air port P is arranged on the outer surface of the annular wedge groove, a working medium is introduced from the outside through the sealing air port P, a stable air film, namely the sealing end face, is formed at the groove root of the annular wedge groove under the high-speed rotation of the dry gas sealing dynamic ring, the working medium forms two paths, and for the first dry gas sealing element 112 at one side of the turbine, the working medium directly flows into a main flow through comb tooth sealing in the leftward direction as shown in fig. 2, so that the working medium is prevented from flowing back; the other path is downward as shown in the figure, passes through the annular wedge groove, is depressurized, then enters the normal pressure cavity through the comb tooth seal rightwards and is discharged. The compressor side is symmetrical to the turbine side. Since dry gas sealing is prior art, further details are not given here. Therefore, the working fluid entering the first balance chamber 41 and the second balance chamber 42 from the first/second bleed air duct 51/52 forms a high pressure in the balance chambers on both sides, and loads in opposite directions are formed on the turbine wheel 21 and the first dry air seal dynamic ring 1120, and the compressor wheel 31 and the second dry air seal dynamic ring 1220, respectively.
In order to facilitate accurate regulation and control of each regulating valve and realize thrust balance of turbines and compressors acting on two sides of the regulating valve on a motor shaft, thrust sensors 13 are respectively arranged on thrust discs on two sides of the first bearing 11 and the second bearing 12 along the axial direction, namely on a main bearing surface and a secondary bearing surface. The first bearing/second bearing 11/12 may be in different bearing forms, such as a combined radial thrust bearing, a radial bearing, a thrust bearing or a rolling bearing, and the power loss during the operation of the motor shaft may be effectively reduced by selecting a bearing with a smaller friction coefficient.
In addition, the thrust balance system of the invention further comprises a controller, and the thrust sensor 13, the first regulating valve 53, the second regulating valve 54, the third regulating valve 55 and the fourth regulating valve 56 are all electrically connected with the controller. In practical application, a PLC controller can be selected. In addition, it should be noted that the working medium referred to in this application is carbon dioxide in a supercritical state.
With reference to the control schematic diagram shown in fig. 4, a method for controlling thrust balance of a supercritical carbon dioxide TAC unit according to the above embodiment may also be implemented, including the following steps:
one path of working medium at the outlet of the compressor enters a first balance chamber 41 at the side of the turbine 2, the flow is controlled through the air-entraining adjusting mechanism 5, and the thrust of the working medium in the first balance chamber 41 acting on the motor shaft 10 is adjusted; the other path of the flow enters a second balance chamber 42 at the side of the compressor 3, the flow is controlled through the bleed air adjusting mechanism 5, and the thrust of the working medium in the second balance chamber 42 acting on the motor shaft 10 is adjusted; wherein, the compressor 3 and the turbine 2 are coaxially arranged at both ends of the motor shaft 10, and the turbine wheel 21 is arranged opposite to the compressor wheel 31; the thrust of the working medium in the first balance chamber 41 acting on the motor shaft 10 is opposite to the thrust of the working medium in the second balance chamber 42 acting on the motor shaft 10, so that the resultant force on the motor shaft is adjusted. Specifically, the turbine impeller 21 and the compressor impeller 31 are coaxially arranged oppositely, loads with different sizes and opposite directions are applied to the motor shaft 10 respectively, and because the load changes at two sides of the turbine and the compressor are inconsistent in the starting and running processes of the unit and the like, the change of an axial gap is easily caused, at the moment, two balance chambers are formed at two side shaft ends of the motor 1 respectively, and working media are introduced through the air entraining adjusting structure 5, so that the working media form thrust with opposite directions to the motor shaft 1 in the balance chambers at two sides respectively; the acting thrust in the balance chambers on the two sides is adjusted by changing the pressure in the balance chambers on the two sides, and then the resultant force on the motor shaft 10 can be adjusted on the basis of the load applied to the motor shaft by the turbine impeller and the compressor impeller, so that the balance and control of the axial thrust in the TAC unit are finally realized.
Working medium at the outlet of the compressor 3 enters the first balance chamber 41 at the turbine 2 side through the first bleed air channel 51 as a regulating air path, and the flow is controlled through a first regulating valve 53 in the bleed air regulating mechanism 5, so as to regulate the thrust acting on the first dry air sealing movable ring 1120 in the first balance chamber 41; the other path is led into a second balance chamber 51 at the side of the compressor 3 through a second bleed air channel 52, the flow is controlled through a second regulating valve 54 in the bleed air regulating mechanism 5, and the thrust acting on a second dry air sealing movable ring 1220 in the second balance chamber 42 is regulated; thereby adjusting the resultant force acting on the motor shaft 10.
The thrust sensors 13 mounted on the thrust disks on the two sides of the first bearing 11 and/or the second bearing 12 on the motor shaft 10 transmit thrust signals to the controller, and the controller adjusts the pressures of the first regulating valve 53 and the second regulating valve 54, so as to flexibly adjust resultant force acting on the motor shaft 10 in real time.
When the working medium gas amount at the outlet of the compressor does not meet the regulation requirement, the gas amount entering the first balance chamber 41 and the second balance chamber 42 is controlled by the third regulating valve 55 and the fourth regulating valve 56 which are connected with the gas tank 7, and then the resultant force acting on the motor shaft 10 is regulated.
Thrust borne on the motor shaft mainly comes from resultant force generated by thrust generated by the turbine impeller 21 and the compressor impeller 31 in the rotating process and towards the motor direction and pressure acting on the first dry gas sealing dynamic ring 1120 and the second dry gas sealing dynamic ring 1220, and after the working medium enters the balance chambers on the two sides, reverse thrust is provided for the first dry gas sealing dynamic ring 1120 and the second dry gas sealing dynamic ring 1220, so that load on the motor shaft 10 can be reduced. Specifically, the turbine wheel 21 generates a thrust force in a direction (i.e., a right direction in fig. 4) toward the motor 1 to the motor shaft 10 during the rotation, i.e., F in fig. 41(ii) a The working medium will also generate a right thrust to the first dry gas seal dynamic ring 1120, i.e. F in FIG. 42(ii) a The compressor impeller 31 generates a thrust force in a motor direction (i.e., a leftward direction in fig. 4) on the motor shaft 10 during the rotation, i.e., F in fig. 43(ii) a The working medium will also generate a leftward thrust on the second dry gas seal dynamic ring 1220, i.e. F in FIG. 44. It is evident from this that by adjusting F2And F4The axial force F of the TAC coaxial unit along two sides of the motor shaft can be adjusted1+F2And F3+F4The resultant force of the two components further reduces the thrust acting on the motor shaft, and reduces the abrasion and power consumption of the bearing on the motor shaft.
It should be noted that the above embodiments can be freely combined as necessary. The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A thrust balancing system of a supercritical carbon dioxide TAC unit is characterized by comprising:
a motor having a motor shaft;
the turbine and the compressor are respectively coaxially arranged at two ends of the motor shaft along the axial direction, and the turbine impeller and the compressor impeller are arranged oppositely;
a thrust balancing unit provided between the turbine and the compressor; the thrust balancing unit comprises a first balancing chamber arranged between the turbine and the motor and a second balancing chamber arranged between the compressor and the motor, working media are introduced into the first balancing chamber and the second balancing chamber through the air entraining adjusting structure and the air quantity is adjusted, and the working media form thrust opposite to the direction of the motor shaft in the first balancing chamber and the second balancing chamber respectively so as to adjust resultant force on the motor shaft.
2. The supercritical carbon dioxide TAC unit thrust balancing system of claim 1, wherein:
the two ends of the motor close to the turbine and the compressor are respectively provided with a first bearing and a second bearing, and the first bearing and the second bearing are respectively arranged in a first bearing seat and a second bearing seat;
a first balance chamber is formed between the first bearing seat and the turbine, and a second balance chamber is formed between the second bearing seat and the compressor.
3. The supercritical carbon dioxide TAC unit thrust balancing system of claim 2, wherein:
the first bearing seat is fixedly connected with a shell of the turbine into a whole through a first seal box, the first seal box is fixedly connected with a motor shaft through a first dry gas seal element, a first partition plate is sleeved on the outer surface, close to a turbine impeller and facing the motor, of the motor shaft, the tail end, far away from the motor shaft, of the first partition plate is connected with the shell of the turbine in a seal mode, and a first balance chamber is defined by the first partition plate, the first dry gas seal element, the shell of the turbine and the first seal box;
the second bearing seat is fixedly connected with the shell of the compressor into a whole through a second sealing box, the second sealing box is fixedly connected with the motor shaft through a second dry gas sealing element, a second partition plate is sleeved on the outer surface, close to the impeller of the compressor and facing the motor, of the motor shaft, the tail end, far away from the motor shaft, of the second partition plate is connected with the shell of the compressor in a sealing mode, and a second balance chamber is defined by the second partition plate, the second dry gas sealing element, the shell of the compressor and the second sealing box;
and the direction of the first dry gas sealing element subjected to the working medium load in the first balance chamber is opposite to the direction of the second dry gas sealing element subjected to the working medium load in the second balance chamber, and the resultant force of the first dry gas sealing element and the second dry gas sealing element along the axial direction is adjusted through the air-entraining adjusting mechanism.
4. The supercritical carbon dioxide TAC unit thrust balancing system of claim 3, wherein:
the air-entraining adjusting structure comprises a first air-entraining channel and a second air-entraining channel which are respectively arranged on a first sealing box and a second sealing box, and the first air-entraining channel and the second air-entraining channel are respectively communicated with a working medium outlet of the compressor through a first pressure regulating valve and a second pressure regulating valve;
working medium pressures in the first balance chamber and the second balance chamber are adjusted through the first air-entraining channel and the second air-entraining channel, and the load directions of the working medium acting on the first dry air sealing element and the second dry air sealing element are opposite, so that the adjustment of resultant force on a motor shaft is realized.
5. The supercritical carbon dioxide TAC unit thrust balancing system of claim 4, wherein:
the first air-entraining channel and the second air-entraining channel are respectively communicated with the air tank for storing working media through a third pressure regulating valve and a fourth pressure regulating valve.
6. The supercritical carbon dioxide TAC unit thrust balancing system of claim 3, wherein:
the first air-entraining channels and the second air-entraining channels are respectively provided with a plurality of air-entraining channels;
and/or;
the first air-entraining channel and the second air-entraining channel are arranged into a bending cavity or an inclined cavity forming an included angle with the motor shaft.
7. The supercritical carbon dioxide TAC unit thrust balancing system of claim 3, wherein:
an oil seal ring is arranged on one side of the first bearing, which faces the turbine, and an oil seal ring is arranged on one side of the second bearing, which faces the compressor;
and/or;
the first dry gas sealing element and the second dry gas sealing element comprise a first dry gas sealing movable ring and a second dry gas sealing static ring which are respectively sleeved at two end parts of the motor shaft, and the second dry gas sealing movable ring and the second dry gas sealing static ring are positioned through a shaft shoulder of the motor shaft, and sealing end faces are formed between the first dry gas sealing static ring and the first dry gas sealing movable ring and between the second dry gas sealing static ring and the second dry gas sealing movable ring.
8. The supercritical carbon dioxide TAC unit thrust balancing system of claim 5, wherein:
thrust sensors are respectively arranged on the thrust discs on the two sides of the first bearing and the second bearing along the axial direction.
9. The supercritical carbon dioxide TAC unit thrust balancing system of claim 8, wherein:
the thrust sensor, the first regulating valve, the second regulating valve, the third regulating valve and the fourth regulating valve are all electrically connected with the controller.
10. A thrust balance control method of a supercritical carbon dioxide TAC unit is characterized in that the thrust balance system of any one of claims 1 to 9 is used for carrying out the following steps:
one path of working medium at the outlet of the compressor enters a first balance chamber at the side of the turbine, the flow is controlled by the air entraining adjusting mechanism, and the thrust of the working medium in the first balance chamber acting on the motor shaft is adjusted; the other path of the working medium enters a second balance chamber at the side of the compressor, the flow is controlled by the air-entraining adjusting mechanism, and the thrust of the working medium in the second balance chamber acting on the motor shaft is adjusted; the compressor and the turbine are coaxially arranged at two ends of a motor shaft, and the turbine impeller and the compressor impeller are arranged oppositely; the thrust of the working medium in the first balance cavity acting on the motor shaft is opposite to the thrust of the working medium in the second balance cavity acting on the motor shaft, so that the resultant force on the motor shaft is adjusted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011210913.8A CN112343668B (en) | 2020-11-03 | 2020-11-03 | Supercritical carbon dioxide TAC unit thrust balance system and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011210913.8A CN112343668B (en) | 2020-11-03 | 2020-11-03 | Supercritical carbon dioxide TAC unit thrust balance system and control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112343668A true CN112343668A (en) | 2021-02-09 |
| CN112343668B CN112343668B (en) | 2023-07-21 |
Family
ID=74355898
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011210913.8A Active CN112343668B (en) | 2020-11-03 | 2020-11-03 | Supercritical carbon dioxide TAC unit thrust balance system and control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112343668B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113137477A (en) * | 2021-03-12 | 2021-07-20 | 浙江态能动力技术有限公司 | Low-leakage high-temperature-resistant supercritical carbon dioxide sealed gas heat exchanger |
| CN113982698A (en) * | 2021-11-05 | 2022-01-28 | 重庆江增船舶重工有限公司 | Balance gas and bearing seat heat insulation system of low-temperature organic working medium expander |
| CN115419471A (en) * | 2022-11-08 | 2022-12-02 | 中国核动力研究设计院 | Turbine system and thrust balancing method |
| CN115539160A (en) * | 2022-12-01 | 2022-12-30 | 中国核动力研究设计院 | Turbine system under supercritical carbon dioxide environment |
| CN115596684A (en) * | 2022-12-01 | 2023-01-13 | 中国核动力研究设计院（Cn） | Compressor, supercritical carbon dioxide circulation system and compressor pressure control method |
| WO2024040667A1 (en) * | 2022-08-26 | 2024-02-29 | 哈电发电设备国家工程研究中心有限公司 | 15mw supercritical co2 axial flow back-pressure type turbine having volute casing air inlet |
| WO2024045240A1 (en) * | 2022-09-01 | 2024-03-07 | 哈电发电设备国家工程研究中心有限公司 | Supercritical carbon dioxide radial-inflow turbine structure suitable for gas inlet at 600 ℃ |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002077417A2 (en) * | 2001-03-26 | 2002-10-03 | Pebble Bed Modular Reactor (Proprietary) Limited | A method of operating a turbine and a gas turbine |
| JP2010190088A (en) * | 2009-02-17 | 2010-09-02 | Mitsubishi Heavy Ind Ltd | Thrust balance adjusting device and rotating machine |
| CN101970882A (en) * | 2008-03-10 | 2011-02-09 | 曼柴油机和涡轮机欧洲股份公司 | Turbo engine with improved compensating piston gasket |
| WO2011078680A1 (en) * | 2009-12-23 | 2011-06-30 | William Paul Hancock | Turbo-machine thrust balancer |
| CN102762871A (en) * | 2009-12-22 | 2012-10-31 | 诺沃皮尼奥内有限公司 | Dynamic thrust balancing for centrifugal compressors |
| US8397506B1 (en) * | 2009-06-03 | 2013-03-19 | Steven A. Wright | Turbo-alternator-compressor design for supercritical high density working fluids |
| US20130091869A1 (en) * | 2010-01-15 | 2013-04-18 | Samsung Techwin Co., Ltd. | Integral compressor-expander |
| CN105308330A (en) * | 2012-11-07 | 2016-02-03 | 热力学公司 | Compressor with thrust balancing and method thereof |
| US9562471B1 (en) * | 2013-05-01 | 2017-02-07 | Sandia Corporation | Method for controlling start-up and steady state performance of a closed split flow recompression brayton cycle |
| KR20200025523A (en) * | 2018-08-30 | 2020-03-10 | 두산중공업 주식회사 | Thrust bearing and turbine generator system and method for controlling the same |
| CN110925033A (en) * | 2019-12-25 | 2020-03-27 | 重庆江增船舶重工有限公司 | Thrust balancing system and control method for supercritical carbon dioxide turbine |
| CN111075750A (en) * | 2019-12-05 | 2020-04-28 | 西安交通大学 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
-
2020
- 2020-11-03 CN CN202011210913.8A patent/CN112343668B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002077417A2 (en) * | 2001-03-26 | 2002-10-03 | Pebble Bed Modular Reactor (Proprietary) Limited | A method of operating a turbine and a gas turbine |
| CN101970882A (en) * | 2008-03-10 | 2011-02-09 | 曼柴油机和涡轮机欧洲股份公司 | Turbo engine with improved compensating piston gasket |
| JP2010190088A (en) * | 2009-02-17 | 2010-09-02 | Mitsubishi Heavy Ind Ltd | Thrust balance adjusting device and rotating machine |
| US8397506B1 (en) * | 2009-06-03 | 2013-03-19 | Steven A. Wright | Turbo-alternator-compressor design for supercritical high density working fluids |
| CN102762871A (en) * | 2009-12-22 | 2012-10-31 | 诺沃皮尼奥内有限公司 | Dynamic thrust balancing for centrifugal compressors |
| WO2011078680A1 (en) * | 2009-12-23 | 2011-06-30 | William Paul Hancock | Turbo-machine thrust balancer |
| US20130091869A1 (en) * | 2010-01-15 | 2013-04-18 | Samsung Techwin Co., Ltd. | Integral compressor-expander |
| CN105308330A (en) * | 2012-11-07 | 2016-02-03 | 热力学公司 | Compressor with thrust balancing and method thereof |
| US9562471B1 (en) * | 2013-05-01 | 2017-02-07 | Sandia Corporation | Method for controlling start-up and steady state performance of a closed split flow recompression brayton cycle |
| KR20200025523A (en) * | 2018-08-30 | 2020-03-10 | 두산중공업 주식회사 | Thrust bearing and turbine generator system and method for controlling the same |
| CN111075750A (en) * | 2019-12-05 | 2020-04-28 | 西安交通大学 | Low blast loss turbomachinery pivot structure that can balance axial thrust |
| CN110925033A (en) * | 2019-12-25 | 2020-03-27 | 重庆江增船舶重工有限公司 | Thrust balancing system and control method for supercritical carbon dioxide turbine |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113137477A (en) * | 2021-03-12 | 2021-07-20 | 浙江态能动力技术有限公司 | Low-leakage high-temperature-resistant supercritical carbon dioxide sealed gas heat exchanger |
| CN113982698A (en) * | 2021-11-05 | 2022-01-28 | 重庆江增船舶重工有限公司 | Balance gas and bearing seat heat insulation system of low-temperature organic working medium expander |
| CN113982698B (en) * | 2021-11-05 | 2023-10-24 | 重庆江增船舶重工有限公司 | Balanced gas of low-temperature organic working medium expansion machine and bearing pedestal heat preservation system |
| WO2024040667A1 (en) * | 2022-08-26 | 2024-02-29 | 哈电发电设备国家工程研究中心有限公司 | 15mw supercritical co2 axial flow back-pressure type turbine having volute casing air inlet |
| WO2024045240A1 (en) * | 2022-09-01 | 2024-03-07 | 哈电发电设备国家工程研究中心有限公司 | Supercritical carbon dioxide radial-inflow turbine structure suitable for gas inlet at 600 ℃ |
| CN115419471A (en) * | 2022-11-08 | 2022-12-02 | 中国核动力研究设计院 | Turbine system and thrust balancing method |
| CN115539160A (en) * | 2022-12-01 | 2022-12-30 | 中国核动力研究设计院 | Turbine system under supercritical carbon dioxide environment |
| CN115596684A (en) * | 2022-12-01 | 2023-01-13 | 中国核动力研究设计院（Cn） | Compressor, supercritical carbon dioxide circulation system and compressor pressure control method |
| CN115539160B (en) * | 2022-12-01 | 2023-03-10 | 中国核动力研究设计院 | Turbine system under supercritical carbon dioxide environment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112343668B (en) | 2023-07-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112343668B (en) | Supercritical carbon dioxide TAC unit thrust balance system and control method | |
| US5102295A (en) | Thrust force-compensating apparatus with improved hydraulic pressure-responsive balance mechanism | |
| RU2681824C2 (en) | Transmission assembly including transmission member and oil distribution system | |
| CN103953445B (en) | Many rotors gas generator with counter-rotating compressor | |
| CA2280533A1 (en) | Two-stage rotary vane motor | |
| WO2014038080A1 (en) | Thrust bearing device and rotating machine using same | |
| EP1206626A1 (en) | Pressure-assisted electromagnetic thrust bearing | |
| CA2901257A1 (en) | Rotary actuator for variable geometry vanes | |
| Tong et al. | Two-dimensional piston pump: Principle, design, and testing for aviation fuel pumps | |
| CN112502832A (en) | Micro gas turbine with axial force balancing structure | |
| JP2017520708A (en) | Eccentric blade pump | |
| CN110925033A (en) | Thrust balancing system and control method for supercritical carbon dioxide turbine | |
| CN110242366A (en) | The control of bearing rotor thrust | |
| CN101372894B (en) | Turbine pneumatic motor | |
| CN104763475B (en) | Three spool turbine | |
| CN110863910A (en) | Long-span rotor system and gas turbine generator set | |
| CN203822466U (en) | Multi-rotor fuel gas generator provided with counter-rotating compressors | |
| CN100398785C (en) | Miniature steam turbine combined with high-speed pump | |
| RU2357122C2 (en) | Gas-static thrust-axial bearing with pneumatic controller of shaft position | |
| CN204492897U (en) | Novel triple-spool counter rotating turbine | |
| Okur et al. | Experimental study of a novel hinged vane rotary turbine–part I: The effect of different vane thickness and vane weight on turbine performance | |
| CN115199348B (en) | Magnetic-gas composite thrust control system and method for organic Rankine cycle generator set | |
| CN214366394U (en) | Micro gas turbine with axial force balancing structure | |
| CN114857044B (en) | Multi-stage convection shaft air compressor with full air-floating support | |
| Beater | Air Motors and Air Turbines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |