CN115539160B - Turbine system under supercritical carbon dioxide environment - Google Patents
Turbine system under supercritical carbon dioxide environment Download PDFInfo
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- CN115539160B CN115539160B CN202211525946.0A CN202211525946A CN115539160B CN 115539160 B CN115539160 B CN 115539160B CN 202211525946 A CN202211525946 A CN 202211525946A CN 115539160 B CN115539160 B CN 115539160B
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- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 title claims abstract description 72
- 229910002092 carbon dioxide Inorganic materials 0.000 title claims abstract description 36
- 239000001569 carbon dioxide Substances 0.000 title claims abstract description 36
- 230000001105 regulatory effect Effects 0.000 claims abstract description 27
- 230000001276 controlling effect Effects 0.000 claims abstract description 5
- 238000002347 injection Methods 0.000 claims description 36
- 239000007924 injection Substances 0.000 claims description 36
- 238000004891 communication Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 227
- 238000007789 sealing Methods 0.000 description 40
- 238000000034 method Methods 0.000 description 14
- 230000008569 process Effects 0.000 description 10
- 238000006243 chemical reaction Methods 0.000 description 9
- 230000009471 action Effects 0.000 description 7
- 238000001514 detection method Methods 0.000 description 7
- 230000008646 thermal stress Effects 0.000 description 7
- 230000003068 static effect Effects 0.000 description 5
- 230000003750 conditioning effect Effects 0.000 description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
- F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
- F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
- F01K25/103—Carbon dioxide
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—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
- F01D11/06—Control thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
- F01K7/32—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or overcritical pressure
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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
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application provides a turbine system in a supercritical carbon dioxide environment, wherein a shell of the turbine system is provided with an accommodating space; the turbine comprises a turbine body and an impeller, a medium cavity is formed in the turbine body, and the impeller is mounted in the medium cavity and divides the medium cavity into a medium inlet area and a medium outlet area; the first dry gas seal is positioned on one side of the turbine, which is provided with a medium inlet area, a first low-temperature chamber is formed in the first dry gas seal, a regulating chamber, a first working medium flow channel, a second working medium flow channel and a third working medium flow channel are formed between the first dry gas seal and the turbine, the first working medium flow channel is communicated with the medium inlet area, the second working medium flow channel is communicated with the medium outlet area, and the third working medium flow channel is communicated with the first low-temperature chamber; the flow regulating valve is arranged in the second working medium flow channel, so that the pressure in the regulating chamber can be regulated by controlling the flow regulating valve, and the axial thrust received by the turbine system is balanced through the pressure.
Description
Technical Field
The application belongs to the technical field of turbine equipment, and particularly relates to a turbine system in a supercritical carbon dioxide environment.
Background
The supercritical carbon dioxide power conversion technology adopts carbon dioxide in a supercritical state as a working medium, realizes energy transmission and energy conversion through closed Brayton cycle, has the technical advantages of simple system, high efficiency, compactness, small volume, light weight, quick response and the like, and has wide application prospect. Under a plurality of special application scenes, the turbine system for power conversion is compactly arranged, working media do not leak, and the requirement on wide operation range is extremely high. In the supercritical carbon dioxide system, a turbine and a compressor belong to turbine equipment, and the functions of providing circulating power and realizing energy conversion are achieved.
For the current turbine application, on one hand, a compressor and turbine equipment belong to rotating machinery, and a working medium leakage point exists outwards generally; on the other hand, the compressor and the turbine in the supercritical carbon dioxide environment work in the operating environment with high rotating speed, high back pressure and high thrust, especially under variable working conditions, the axial thrust borne by the equipment is complex in change, and the axial thrust is difficult to balance only by a thrust bearing, so that the compressor and the turbine are one of the main reasons that the conventional turbine system cannot operate in a wide range.
Disclosure of Invention
The embodiment of the application provides a turbine system under supercritical carbon dioxide environment, has axial thrust self-adjusting ability, can realize wide operating range.
On one hand, the embodiment of the application provides a turbine system in a supercritical carbon dioxide environment, which comprises a shell, a turbine, a first dry gas seal and a flow regulating valve, wherein the shell is provided with an accommodating space; the turbine is arranged in the accommodating space and comprises a turbine body and an impeller, a medium cavity is formed in the turbine body, and the impeller is arranged in the medium cavity and divides the medium cavity into a medium inlet area and a medium outlet area; the first dry gas seal is arranged in the accommodating space and is positioned on one side of the turbine, which is provided with a medium inlet area, a first low-temperature chamber is formed in the first dry gas seal, a regulating chamber, a first working medium flow channel, a second working medium flow channel and a third working medium flow channel are formed between the first dry gas seal and the turbine, the first working medium flow channel is communicated with the medium inlet area, the second working medium flow channel is communicated with the medium outlet area, and the third working medium flow channel is communicated with the first low-temperature chamber; the flow regulating valve is arranged in the second working medium flow passage.
According to one aspect of the application, the turbine system further comprises a motor, a compressor, a second dry gas seal and control module, wherein the motor is accommodated in the accommodating space, the motor comprises a motor main body and a rotor which is connected with the motor main body and extends towards two ends of the motor main body, the turbine is arranged on one side of the motor main body and is installed on the rotor, and the first dry gas seal is connected with the rotor and is positioned between the turbine and the motor main body; the compressor is accommodated in the accommodating space, is arranged on the other side of the motor main body and is arranged on the rotor; the second dry gas is hermetically accommodated in the accommodating space, and the second dry gas is hermetically arranged on the rotor and positioned between the compressor and the motor main body; the control module is connected with the first dry gas seal and the second dry gas seal respectively, and the control module is used for controlling gas injection flow in the first dry gas seal and the second dry gas seal.
According to one aspect of the application, the turbine system further comprises an auxiliary pressurizing part, and the first dry gas seal and the second dry gas seal divide the accommodating space into a first high pressure area, a low pressure area and a second high pressure area in sequence, wherein the turbine is located at the first high pressure area, the motor is located at the low pressure area, the compressor is located at the second high pressure area, one end of the auxiliary pressurizing part is communicated with the low pressure area, and the other end of the auxiliary pressurizing part is communicated with a closed circulation loop between the turbine and the compressor.
According to an aspect of the application, the first dry gas seal is further formed with a first gas inlet communicated with the first low-temperature chamber, the second dry gas seal is formed with a second low-temperature chamber and a second gas inlet communicated with the second low-temperature chamber, the control module comprises a control body and two gas injection devices electrically connected with the control body, and the two gas injection devices are respectively arranged at the first gas inlet and the second gas inlet.
According to one aspect of the present application, in an operating condition, a gas injection flow rate of one gas injection apparatus at a first gas inlet is different from a gas injection flow rate of another gas injection apparatus at a second gas inlet.
According to an aspect of the application, first dry gas is sealed all including sealed shell and hold sealed rotating ring and the sealed quiet ring in sealed shell with the second dry gas is sealed, be formed with first low temperature cavity or second low temperature cavity in the sealed shell, still be formed with first air inlet or second air inlet in the sealed shell, the fixed cover of sealed rotating ring is located on the rotor, sealed quiet ring encircles and sets up on the periphery of rotor and be fixed in sealed shell, form balanced membrane between sealed rotating ring and the sealed quiet ring, first air inlet or second air inlet are located one side that sealed shell is close to sealed rotating ring.
According to an aspect of the application, the control module further comprises two pressure detection pieces and two flow detection pieces which are electrically connected with the control body, the two pressure detection pieces are respectively arranged at the first air inlet and the second air inlet, and the two flow detection pieces are respectively arranged at the first air inlet and the second air inlet.
According to one aspect of the application, the turbine system further includes a thrust bearing mounted on the rotor, the thrust bearing being located between the compressor and the motor body, or alternatively, the thrust bearing being located between the turbine and the motor body.
According to one aspect of the application, the thrust bearing comprises a rotating part and a stationary part, wherein the rotating part and the stationary part are sleeved on the rotor, the rotating part is fixedly connected with the rotor, and the stationary part is fixedly connected with the shell.
According to an aspect of the application, the turbine system further comprises a thrust parameter detection piece, the thrust parameter detection piece is fixedly mounted on the stationary portion, and the thrust parameter detection piece is connected with the control module to detect axial thrust data of the rotor and send the axial thrust data to the control module.
The turbine system under the supercritical carbon dioxide environment provided by the embodiment of the application comprises a shell, a turbine, a first dry gas sealing element and a flow regulating valve, wherein the shell is provided with an accommodating cavity; the turbine is arranged in the accommodating cavity and comprises a body and an impeller, a medium cavity is formed in the body, and the impeller is arranged in the medium cavity and divides the medium cavity into a medium inlet area and a medium outlet area; the first dry gas sealing element is arranged in the accommodating cavity, a low-temperature cavity is formed in the first dry gas sealing element, an adjusting cavity, a first working medium flow passage, a second working medium flow passage and a third working medium flow passage are formed between the first dry gas sealing element and the turbine, the first working medium flow passage is communicated with the medium inlet area, the second working medium flow passage is communicated with the medium outlet area, and the third working medium flow passage is communicated with the low-temperature cavity, so that low-temperature sealing gas in the low-temperature cavity of the first dry gas sealing element can flow into the adjusting cavity through the third working medium flow passage, high-temperature medium in the medium inlet area of the turbine can flow into the adjusting cavity through the first working medium flow passage, the low-temperature sealing gas and the high-temperature medium are mixed in the adjusting cavity to reduce the temperature and flow into the medium outlet area of the turbine through the second working medium flow passage, thereby effectively preventing the low-temperature sealing gas from leaking into the medium inlet area of the turbine, avoiding the thermal stress of the impeller due to the existence of temperature difference, and ensuring the structural strength of the impeller.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a partial sectional view of a turbine system provided in accordance with certain embodiments of the present application;
FIG. 2 is yet another partial sectional view of a turbine family provided by some embodiments of the present application;
FIG. 3 is a schematic structural view of a first dry gas seal and a second dry gas seal provided in accordance with certain embodiments of the present application;
FIG. 4 is a further schematic illustration of a turbine system provided in accordance with certain embodiments of the present application;
FIG. 5 is a schematic illustration of a thrust bearing of a turbine system provided in accordance with certain embodiments of the present application;
FIG. 6 is a schematic illustration of an installation of a thrust parameter sensing piece of a turbine system according to some embodiments of the present disclosure.
Reference numerals:
a housing 100; a turbine 200; a turbine body 201; an impeller 202; a media inlet region 203; a first dry gas seal 300; a first cryogenic chamber 301; a first air inlet 302; a first leakage port 303; a sealed housing 304; a sealing moving ring 305; a seal stationary ring 306; a conditioning chamber 400; a first working medium channel 401; a third working fluid channel 402; a motor 500; a motor main body 501; a rotor 502; a compressor 600; a second dry gas seal 700; a second low temperature chamber 701; a second air inlet 702; a second leak port 703; a thrust bearing 800; a rotating portion 801; a stationary portion 802; the thrust parameter detecting member 900.
Detailed Description
Features and exemplary embodiments of various aspects of the present application will be described in detail below, and in order to make objects, technical solutions and advantages of the present application more apparent, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are intended to be illustrative only and are not intended to be limiting. It will be apparent to one skilled in the art that the present application may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present application by illustrating examples thereof.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising 8230; \8230;" comprises 8230; "does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The supercritical carbon dioxide power conversion technology adopts carbon dioxide in a supercritical state as a working medium, realizes energy transmission and energy conversion through closed Brayton cycle, has the technical advantages of simple system, high efficiency, compactness, small volume, light weight, quick response and the like, and has wide application prospect. Under a plurality of special application scenes, the turbine system for power conversion is compactly arranged, working media do not leak, and the requirement on wide operation range is extremely high. In the supercritical carbon dioxide system, a turbine and a compressor belong to turbine equipment, and the functions of providing circulating power and realizing energy conversion are achieved.
For the current supercritical carbon dioxide system, on one hand, a compressor and turbine equipment belong to rotating machinery, working medium leakage points to the outside generally exist, so dry gas seals are generally needed to be arranged to realize shaft end sealing of the turbine and the compressor, but the dry gas seals need to be filled with sealing gas in the sealing process, and the temperature of the sealing gas is much lower than that of the supercritical carbon dioxide, so when part of low-temperature sealing gas leaks into the turbine, the temperature difference between the part of low-temperature sealing gas and the supercritical carbon dioxide in the turbine can cause the impeller in the turbine to generate larger thermal stress, the structural strength of the impeller is influenced, and the service life of the turbine and even the normal operation of the whole system are influenced.
On the other hand, because the compressor and the turbine in the supercritical carbon dioxide environment work in the operating environment with high rotating speed, high back pressure and high thrust, especially under the condition of variable working conditions, the axial thrust borne by the equipment is complex in change, and it is difficult to balance the axial thrust only by a thrust bearing, which is one of the main reasons that the current turbine system cannot realize wide-range operation.
In view of this, the inventor of the present application proposes a turbine system in a supercritical carbon dioxide environment, which aims to balance the axial thrust to which the system is subjected while solving the problem of thermal stress in the turbine. The turbine system specifically comprises a shell, a turbine, a first dry gas sealing element and a flow regulating valve, wherein the shell is provided with a containing cavity; the turbine is arranged in the accommodating cavity and comprises a body and an impeller, a medium cavity is formed in the body, and the impeller is arranged in the medium cavity and divides the medium cavity into an inlet area and an outlet area; the first dry gas sealing element is arranged in the accommodating cavity, a low-temperature cavity is formed in the first dry gas sealing element, an adjusting cavity and a first working medium flow channel communicated with the adjusting cavity, a second working medium flow channel and a third working medium flow channel are formed between the first dry gas sealing element and the turbine, the first working medium flow channel is communicated with the inlet area, the second working medium flow channel is communicated with the outlet area, and the third working medium flow channel is communicated with the low-temperature cavity, so that low-temperature sealing gas in the low-temperature cavity of the first dry gas sealing element can flow into the adjusting cavity through the third working medium flow channel, high-temperature media in the inlet area of the turbine can flow into the adjusting cavity through the first working medium flow channel, the low-temperature sealing gas and the high-temperature media are mixed in the adjusting cavity to reduce the temperature and flow into the outlet area of the turbine through the second working medium flow channel, thereby effectively preventing the low-temperature sealing gas from leaking into the medium inlet area of the turbine, avoiding the thermal stress generated by the existence of temperature difference, and ensuring the structural strength of the impeller.
In order to solve the problem of the prior art, the embodiment of the application provides a turbine system in a supercritical carbon dioxide environment.
FIG. 1 is a partial cutaway view of a turbine system provided in accordance with certain embodiments of the present application.
Referring to fig. 1, the present application provides a turbine system in a supercritical carbon dioxide environment, including a casing 100, a turbine 200, a first dry gas seal 300 and a flow regulating valve, wherein the casing 100 has a receiving space; the turbine 200 is arranged in the accommodating space, the turbine 200 comprises a turbine body 201 and an impeller 202, a medium cavity is formed in the turbine body 201, and the impeller 202 is arranged in the medium cavity and divides the medium cavity into a medium inlet area 203 and a medium outlet area; the first dry gas seal 300 is arranged in the accommodating space and is positioned on one side of the turbine 200 where the medium inlet area 203 is formed, a first low-temperature chamber 301 is formed in the first dry gas seal 300, a regulating chamber 400, a first working medium flow channel 401, a second working medium flow channel and a third working medium flow channel 402 are formed between the first dry gas seal 300 and the turbine 200, the first working medium flow channel 401 is communicated with the medium inlet area 203, the second working medium flow channel is communicated with the medium outlet area, and the third working medium flow channel 402 is communicated with the first low-temperature chamber 301; the flow regulating valve is arranged in the second working medium flow passage.
The casing 100 may be a pressure casing 100, and the turbine 200, the first dry gas seal 300 and the flow control valve are all disposed in the casing 100, so that the turbine system is integrated, the structure of the turbine system is more compact, and the casing 100 may ensure complete sealing of the turbine system with the outside, so that the supercritical carbon dioxide working medium in the casing 100 may be recycled, and no external leakage of the turbine system is realized.
The conditioning chamber 400 may be formed on the first dry gas seal 300, or may be formed on the turbine 200, or the conditioning chamber 400 may be formed by enclosing the first dry gas seal 300, the turbine 200, and the casing 100, and is not particularly limited thereto.
The turbine system under the supercritical carbon dioxide environment provided by the embodiment of the application comprises a shell, a turbine 200, a first dry gas seal 300 and a flow regulating valve, wherein the shell is provided with an accommodating cavity; the turbine 200 is disposed in the containment chamber, the turbine 200 including a body having a media chamber formed therein and an impeller 202 mounted in the media chamber and dividing the media chamber into a media inlet region 203 and a media outlet region; the first dry gas seal 300 is arranged in the accommodating cavity, a low-temperature cavity is formed in the first dry gas seal 300, an adjusting cavity 400, a first working medium flow channel 401, a second working medium flow channel and a third working medium flow channel 402 are formed between the first dry gas seal 300 and the turbine 200, the first working medium flow channel 401 is communicated with the medium inlet region 203, the second working medium flow channel is communicated with the medium outlet region, and the third working medium flow channel 402 is communicated with the first low-temperature cavity 301, so that low-temperature sealing gas in the first low-temperature cavity 301 of the first dry gas seal 300 can flow into the adjusting cavity 400 through the third working medium flow channel 402, high-temperature medium in the medium inlet region 203 of the turbine 200 can flow into the adjusting cavity 400 through the first working medium flow channel 401, the low-temperature sealing gas and the high-temperature medium are mixed in the adjusting cavity 400 to reduce the temperature, and flow into the medium outlet region of the turbine 200 through the second working medium flow channel, in the process, the flow regulating valve in the second working medium flow channel is regulated, the pressure in the adjusting cavity 400 can be regulated, and further the turbine is subjected to thrust balance of the system through the thrust pressure.
Moreover, since the medium flowing into the medium inlet region 203 of the turbine 200 is in a high temperature state, and the temperature of the seal gas in the first low-temperature chamber 301 of the first dry gas seal 300 is lower than that of the high-temperature medium in the turbine 200, when the low-temperature seal gas leaks and flows into the medium inlet region 203 of the turbine 200, the impeller 202 of the turbine 200 will generate a certain thermal stress due to the temperature difference between the high-temperature medium and the low-temperature seal gas, and further affect the structural strength of the impeller 202, in this application, the regulating chamber 400 is provided between the first dry gas seal 300 and the turbine 200, and the low-temperature seal gas and the high-temperature medium are mixed in the regulating chamber 400, so that the low-temperature seal gas can be effectively prevented from leaking to the medium inlet region 203 of the turbine 200, the thermal stress of the impeller 202 due to the temperature difference can be avoided, and the structural strength of the impeller 202 can be ensured.
It can be understood that, in the working process of the turbine system, the low-temperature seal gas needs to be continuously injected into the first low-temperature chamber 301 and the high-temperature medium needs to be continuously injected into the medium inlet region 203, so the low-temperature seal gas and the high-temperature medium also continuously flow into the regulation chamber 400 and flow to the medium outlet region through the second working medium flow channel to be discharged, at this time, a certain pressure is generated in the regulation chamber 400 due to the mixing of the gases, and by controlling the size of the valve port of the flow regulating valve, the speed of discharging the gases in the regulation chamber 400 can be controlled, so that the pressure in the regulation chamber 400 is regulated, and finally the pressure is regulated to balance the axial thrust received by the system by regulating the pressure.
FIG. 2 is yet another partial cutaway view of a turbine family provided by some embodiments of the present application.
Referring to fig. 2, according to an aspect of the present application, the turbine system further includes a motor 500, a compressor 600, a second dry gas seal 700, and a control module, the motor 500 is accommodated in the accommodating space, the motor 500 includes a motor body 501 and a rotor 502 connected to the motor body 501 and extending to two ends of the motor body 501, the turbine 200 is disposed at one side of the motor body 501 and mounted on the rotor 502, and the first dry gas seal 300 is connected to the rotor 502 and located between the turbine 200 and the motor body 501; the compressor 600 is accommodated in the accommodating space, and the compressor 600 is disposed at the other side of the motor body 501 and mounted on the rotor 502; the second dry gas seal 700 is accommodated in the accommodating space, and the second dry gas seal 700 is mounted on the rotor 502 and located between the compressor 600 and the motor main body 501; the control module is connected with the first dry gas seal 300 and the second dry gas seal 700 respectively, and the control module is used for controlling the gas injection flow in the first dry gas seal 300 and the second dry gas seal 700.
It is understood that the conditioning chamber 400400 may be defined by the housing 100, the turbine 200, and the first dry gas seal 300, and the rotor 502.
It is understood that the control module may include one or more of a microprocessor, an integrated circuit having functions of receiving and transmitting signals, a mobile terminal having a wireless communication function, and the like; the electric machine 500 may be a starter-integral generator that includes a starter motor.
In the turbine system in the supercritical carbon dioxide environment provided by the embodiment of the present application, the compressor 600 and the turbine 200 are disposed on two sides of the motor 500, so that energy conversion in the system is realized; a first dry gas seal 300 is arranged between the turbine 200 and the motor 500, and a second dry gas seal 700400 is arranged between the compressor 600 and the motor 500, so that shaft end sealing of the turbine system is realized through the first dry gas seal 300 and the second dry gas seal 700; and, be connected respectively with first dry gas seal 300 and second dry gas seal 700 through the control module group to adjust the gas injection pressure in first dry gas seal 300 and the second dry gas seal 700 through control module, in order to form certain axial resultant force in the axial of rotor 502 and balance the axial thrust that the turbine system received under the supercritical carbon dioxide environment received, and then avoid each equipment in the turbine system to take place the axial float and cause physical damage, the operation safety of guarantee system, simultaneously, can increase the operating range of turbine system, realize the wide range operation of turbine system.
As a specific embodiment, the turbine system further includes an auxiliary pressurizing member, and the first dry gas seal 300 and the second dry gas seal 700 divide the accommodating space into a first high pressure region, a low pressure region, and a second high pressure region in this order, wherein the turbine 200 is located in the first high pressure region, the motor 500 is located in the low pressure region, the compressor 600 is located in the second high pressure region, one end of the auxiliary pressurizing member is communicated with the low pressure region, and the other end of the auxiliary pressurizing member is communicated with the closed cycle loop between the turbine 200 and the compressor 600.
It can be understood that the turbine 200, as a working device in the system, can convert the heat energy in the high-temperature and high-pressure supercritical carbon dioxide working medium into mechanical energy and transmit the mechanical energy to the motor 500 through the rotor 502 to generate electricity, and the compressor 600, as a power consumption device in the system, can pressurize the supercritical carbon dioxide after working, so that, in the action state of the turbine system, the supercritical carbon dioxide working media at the turbine 200 and the compressor 600 are both in a high-pressure state, that is, the compressor 600 and the turbine 200 are respectively in the first high-pressure region and the second high-pressure region; in a turbine system, to reduce losses of the electric machine 500 in an operating state, the electric machine 500 is typically placed in a low pressure environment.
The auxiliary supercharging component can be various superchargers, booster pumps or other supercharging devices.
In this embodiment, an auxiliary pressurizing member is connected to the low-pressure region, and the auxiliary pressurizing member is further connected to the circulation loop between the turbine 200 and the compressor 600, so that the supercritical carbon dioxide working medium leaked to the low-pressure region is further recycled, and the circulation system does not need to supplement air.
Fig. 3 is a schematic structural view of a first dry gas seal and a second dry gas seal provided in some embodiments of the present application.
As shown in fig. 3, as a specific embodiment, the first dry gas seal 300 is further formed with a first gas inlet 302 communicated with the first low-temperature chamber 301, the second dry gas seal 700 is formed with a second low-temperature chamber 701 and a second gas inlet 702 communicated with the second low-temperature chamber 701, and the control module includes a control body and two gas injection devices electrically connected with the control body, and the two gas injection devices are respectively disposed at the first gas inlet 302 and the second gas inlet 702.
It is understood that the first dry gas seal 300 may further define a first leakage port 303 corresponding to the low pressure region, and the second dry gas seal 700 may further define a second leakage port 703 corresponding to the low pressure region.
It can be understood that the first dry gas seal 300 and the second dry gas seal 700 preferably use supercritical carbon dioxide working medium as the seal gas, and zero leakage of the turbine system is realized while the working medium circulation of the whole turbine system is ensured. Of course, it is within the scope of the present application that the first dry gas seal 300 and the second dry gas seal 700 use other gases such as nitrogen, air, etc. as the seal gas.
The gas injection device can be an air pump, a gas tank or other various gas injection structures; the two gas injection devices can inject a sealing gas into the first dry gas seal 300 and the second dry gas seal 700 under the control of the control body.
In the first dry gas seal 300, the sealing gas is continuously injected into the first dry gas seal 300 from the first gas inlet 302 and generates a certain first axial force, and at the moment, the acted sealing gas leaks to the outside of the first dry gas seal 300 through the first leakage port; in the second dry gas seal 700, the sealing gas is continuously injected into the second dry gas seal 700 from the second gas inlet 702 and generates a certain second axial force, and at this time, the acted sealing gas leaks to the outside of the second dry gas seal 700 from the second leakage port 703; in the whole turbine system, the first axial force generated by the first dry gas seal 300 and the second axial force generated by the second dry gas seal 700 act together to form an axial resultant force so as to balance the axial thrust force applied to the system.
As a specific embodiment, in operation, the gas injection rate of one gas injection apparatus at the first gas inlet 302 is different from the gas injection rate of another gas injection apparatus at the second gas inlet 702.
Because the turbine system receives an axial thrust, by injecting seal gas into the first gas inlet 302 of the first dry gas seal 300 and the second gas inlet 702 of the second dry gas seal 700, a certain first axial force is generated in the first dry gas seal 300, and a certain second axial force is generated in the second dry gas seal 700, because the first dry gas seal 300 and the second dry gas seal 700 are disposed on two sides of the rotor 502 relative to the motor body 501, the first axial force and the second axial force are opposite in direction, and because the gas injection flow rate at the first gas inlet 302 of the first dry gas seal 300 is different from the gas injection flow rate at the second gas inlet 702 of the second dry gas seal 700, the gas injection pressures of the two are also different, and therefore, a certain axial resultant force is generated in the axial direction of the rotor 502, so as to balance the axial thrust received by the turbine system.
It is appreciated that the magnitude and direction of the resultant axial force generated by the combined action of the first and second axial forces may be flexibly adjusted by adjusting the flow rate of insufflation gas in the first and second dry gas seals 300, 700. For example, in the axial direction of the rotor 502, assuming that the direction of the compressor 600 toward the motor main body 501 is a positive direction, at this time, a first axial force generated by the first dry gas seal 300 is a positive direction, and a second axial force generated by the second dry gas seal 700 is a negative direction, when the axial thrust received by the turbine system is the positive direction, the gas injection pressure of the second dry gas seal 700 may be controlled to be greater than the gas injection pressure of the first dry gas seal 300, that is, the second axial force is greater than the first axial force, and therefore, the axial resultant force generated by the combined action of the two is the negative direction, so that the positive axial thrust received by the turbine system may be balanced to some extent, and in this process, in order to balance the axial thrust at the maximum, the gas injection flow rate in the specific first dry gas seal 300 and the axial flow rate of the second dry gas seal 700 may be adjusted according to the magnitude of the actual axial thrust, so that the value of the axial resultant force formed by the first axial force and the second axial force is closest to the axial thrust.
In this embodiment, by injecting seal gas into the first gas inlet 302 of the first dry gas seal 300 and the second gas inlet 702 of the second dry gas seal 700, respectively, a first axial force is formed in the first dry gas seal 300, and a second axial force is formed in the second dry gas seal 700, and the first axial force and the second axial force have opposite directions, and since the gas injection flow rate at the first gas inlet 302 of the first dry gas seal 300 is different from the gas injection flow rate at the second gas inlet 702 of the second dry gas seal 700, the first axial force and the second axial force have different magnitudes, so that a certain axial resultant force is formed by the combined action of the first axial force and the second axial force, and the axial thrust received by the turbine system is balanced.
Referring to fig. 3, as a specific embodiment, each of the first dry gas seal 300 and the second dry gas seal 700 includes a seal housing 304, and a seal moving ring 305 and a seal stationary ring 306 accommodated in the seal housing 304, a first low temperature chamber 301 or a second low temperature chamber 701 is formed in the seal housing 304, a first gas inlet 302 or a second gas inlet 702 is further formed in the seal housing 304, the seal moving ring 305 is fixedly sleeved on the rotor 502, the seal stationary ring 306 is circumferentially disposed on the outer periphery of the rotor 502 and fixed on the seal housing 304, a balance film is formed between the seal moving ring 305 and the seal stationary ring 306, and the first gas inlet 302 or the second gas inlet 702 is located on a side of the seal housing 304 close to the seal moving ring 305.
It is understood that in the first dry gas seal 300 or the second dry gas seal 700, the dynamic seal ring 305 and the static seal ring 306 are both sleeved on the rotor 502, the dynamic seal ring 305 is fixedly connected with the rotor 502, and the static seal ring 306 is fixedly connected with the seal housing 304, when the rotor 502 is in the operating state, the dynamic seal ring 305 rotates together with the rotor 502, and the static seal ring 306 is always in the static state, at this time, the seal gas entering the seal housing 304 through the first air inlet 302 or the second air inlet 702 generates a rigid balance film between the dynamic seal ring 305 and the static seal ring 306, when the control module controls the injection of the seal gas into the seal housing 304 at a constant speed, the forces in all directions at the balance film are in a relatively balanced state, that is, the first axial force of the first dry gas seal 300 is 0 or the second axial force of the second dry gas seal 700 is 0, when the control module changes the injection speed of the seal gas, the forces at the balance film will maintain a balanced state, and at this time, the first axial force of the first dry gas seal 300 will not generate the second axial force with a certain magnitude, or the second axial force will generate a certain magnitude at this time, and generate the second axial force of the second dry gas seal 700.
As a specific embodiment, the turbine system further includes two pressure detecting members and two flow detecting members electrically connected to the control body, wherein the two pressure detecting members are respectively disposed at the first air inlet 302 and the second air inlet 702, and the two flow detecting members are respectively disposed at the first air inlet 302 and the second air inlet 702.
It is understood that the flow detecting element is used for monitoring the flow of the sealing gas injected into the first dry gas seal 300 or the second dry gas seal 700 in real time, and the pressure detecting element is used for monitoring the pressure of the sealing gas injected into the first dry gas seal 300 or the second dry gas seal 700 in real time, so as to prevent excessive sealing gas from being injected into the first dry gas seal 300 or the second dry gas seal 700 and affecting the sealing effect and the balancing effect of the first dry gas seal 300 or the second dry gas seal 700.
FIG. 4 is a further schematic illustration of a turbine system provided in accordance with certain embodiments of the present application.
As shown in fig. 4, as a specific embodiment, the turbine system further includes a thrust bearing 800 mounted on the rotor 502, the thrust bearing 800 is located between the compressor 600 and the motor main body 501, or the thrust bearing 800 is located between the turbine 200 and the motor main body 501.
It is understood that the thrust bearing 800 may be an oil-free bearing, for example, an electromagnetic bearing, an air bearing, etc., and does not need to be lubricated by oil, so as to ensure the purity of the carbon dioxide working medium, and to realize the recycling of the carbon dioxide working medium leaked from the turbine 200 and the compressor 600.
In the embodiment, in order to further balance the high thrust force of the turbine system in the supercritical carbon dioxide environment, a thrust bearing 800 is provided in the turbine system, the thrust bearing 800 may be mounted on the rotor 502, and the thrust bearing 800 may be located between the compressor 600 and the motor body 501, or the thrust bearing 800 may be located between the turbine 200 and the motor body 501, so as to further balance the thrust force of the turbine system in the axial direction of the rotor 502, reduce the possibility of physical damage of each device in the turbine system due to the influence of the axial thrust force, and realize a wide range of operation of the turbine system.
FIG. 5 is a schematic illustration of a thrust bearing of a turbine system provided in accordance with certain embodiments of the present application.
As shown in fig. 5, as a specific embodiment, the thrust bearing 800 includes a rotating portion 801 and a stationary portion 802 sleeved on the rotor 502, the rotating portion 801 is fixedly connected to the rotor 502, and the stationary portion 802 is fixedly connected to the housing 100.
In this embodiment, the rotating portion 801 of the thrust bearing 800 is fixedly connected to the rotor 502, and the stationary portion 802 is connected to the casing 100, so that in the operating state of the rotor 502, the rotating portion 801 rotates together with the rotor 502, and the stationary portion 802 is always kept in a relatively stationary state, and at this time, the thrust force applied to the turbine system in the axial direction of the rotor 502 can be borne by the rotating portion 801, so as to prevent the axial thrust force from affecting other devices of the turbine system.
FIG. 6 is a schematic illustration of an installation of a thrust parameter sensing piece of a turbine system according to some embodiments of the present disclosure.
As shown in fig. 6, as a specific embodiment, the turbine system further includes a thrust parameter detecting element 900, the thrust parameter detecting element 900 is fixedly installed on the stationary portion 802, and the thrust parameter detecting element 900 is connected to the control module to detect axial thrust data of the rotor 502 and send the axial thrust data to the control module.
It is understood that the thrust parameter detecting member 900 may be a thrust sensor, and may also be other forms of thrust detectors.
In this embodiment, the thrust parameter detecting member 900 is disposed on the stationary portion 802 of the thrust bearing 800, so that in the working state of the rotor 502, the thrust parameter detecting member 900 is in a stationary state relative to the rotor 502, so that the thrust force applied to the turbine system in the axial direction of the rotor 502 can be detected, and since the thrust parameter detecting member 900 is connected to the control module, the detected thrust data of the turbine system in the axial direction of the rotor 502 can be generated to the control module, and the control module controls the gas injection pressures in the first dry gas seal 300 and the second dry gas seal 700 to form a certain resultant force in the axial direction of the rotor 502, so as to balance the thrust force in the axial direction.
In some embodiments, the turbine system further includes support bearings installed on the rotor 502 and respectively located at two sides of the motor main body 501, and when the turbine system is in the supercritical carbon dioxide environment, the turbine system is subjected to not only thrust distributed along the axial direction of the rotor 502, but also radial load generated by radial force generated by uneven system airflow, self weight of the rotor 502, and the like, so that the radial thrust received by the turbine system is balanced by respectively arranging the support bearings at two sides of the motor main body 501, and the influence of the radial thrust on equipment safety of the turbine system is avoided.
The turbine system in the supercritical carbon dioxide environment provided by the embodiment of the application comprises a shell, a turbine 200, a first dry gas seal 300 and a flow regulating valve, wherein the shell is provided with an accommodating cavity; the turbine 200 is disposed in the containment chamber, the turbine 200 including a body having a media chamber formed therein and an impeller 202 mounted in the media chamber and dividing the media chamber into a media inlet region 203 and a media outlet region; the first dry gas seal 300 is arranged in the accommodating cavity, a low-temperature cavity is formed in the first dry gas seal 300, an adjusting cavity 400, a first working medium flow channel 401 communicated with the adjusting cavity 400, a second working medium flow channel and a third working medium flow channel 402 are formed between the first dry gas seal 300 and the turbine 200, the first working medium flow channel 401 is communicated with the medium inlet area 203, the second working medium flow channel is communicated with the medium outlet area, the third working medium flow channel 402 is communicated with the low-temperature cavity, so that low-temperature sealing gas in the low-temperature cavity of the first dry gas seal 300 can flow into the adjusting cavity 400 through the third working medium flow channel 402, high-temperature medium in the medium inlet area 203 of the turbine 200 can flow into the adjusting cavity 400 through the first working medium flow channel 401, the low-temperature sealing gas and the high-temperature medium are mixed in the adjusting cavity 400 to reduce the temperature, the low-temperature sealing gas flows into the medium outlet area of the turbine 200 through the second working medium flow channel, thereby effectively preventing the low-temperature sealing gas from leaking to the medium inlet area 203 of the turbine 200, avoiding the generation of thermal stress due to the existence of the impeller 202, ensuring the structure strength of the impeller 202, further realizing the axial pressure balance of the adjusting cavity, and realizing the thrust pressure of the turbine in the adjusting cavity in the adjusting process of the turbine 400.
As described above, only the specific embodiments of the present application are provided, and it can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working processes of the system, the module and the unit described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again. It should be understood that the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present application, and these modifications or substitutions should be covered within the scope of the present application.
Claims (10)
1. A turbine system in a supercritical carbon dioxide environment, comprising:
a housing having an accommodating space;
the turbine is arranged in the accommodating space and comprises a turbine body and an impeller, a medium cavity is formed in the turbine body, and the impeller is arranged in the medium cavity and divides the medium cavity into a medium inlet area and a medium outlet area;
the first dry gas seal is arranged in the accommodating space and is positioned on one side of the turbine, which is provided with a medium inlet area, a first low-temperature chamber is formed in the first dry gas seal, a regulating chamber, a first working medium flow channel, a second working medium flow channel and a third working medium flow channel are formed between the first dry gas seal and the turbine and are communicated with the regulating chamber, the first working medium flow channel is communicated with the medium inlet area, the second working medium flow channel is communicated with the medium outlet area, and the third working medium flow channel is communicated with the first low-temperature chamber;
and the flow regulating valve is arranged in the second working medium flow passage.
2. The turbine system of claim 1, further comprising:
the motor is accommodated in the accommodating space and comprises a motor main body and rotors connected with the motor main body and extending towards two ends of the motor main body, the turbine is arranged on one side of the motor main body and is installed on the rotors, and the first dry gas seal is connected with the rotors and is positioned between the turbine and the motor main body;
the compressor is accommodated in the accommodating space, is arranged on the other side of the motor main body and is installed on the rotor;
the second dry gas seal is accommodated in the accommodating space, and the second dry gas seal is mounted on the rotor and positioned between the compressor and the motor main body;
the control module is connected with the first dry gas seal and the second dry gas seal respectively and used for controlling gas injection flow in the first dry gas seal and the second dry gas seal.
3. The turbine system of claim 2, further comprising an auxiliary plenum, the first and second dry gas seals dividing the containment space into a first high pressure zone, a low pressure zone, and a second high pressure zone in that order, wherein the turbine is located in the first high pressure zone, the motor is located in the low pressure zone, the compressor is located in the second high pressure zone, one end of the auxiliary plenum communicates with the low pressure zone, and the other end of the auxiliary plenum communicates with a closed cycle loop between the turbine and the compressor.
4. The turbine system of claim 2, wherein the first dry gas seal is further formed with a first gas inlet in communication with the first cryogenic chamber, the second dry gas seal is formed with a second cryogenic chamber and a second gas inlet in communication with the second cryogenic chamber, and the control module comprises a control body and two gas injection devices electrically connected to the control body, the two gas injection devices being disposed at the first gas inlet and the second gas inlet, respectively.
5. The turbine system of claim 4, wherein, in an operating state, the gas injection flow rate of one of the gas injection apparatuses at the first gas inlet is different from the gas injection flow rate of the other of the gas injection apparatuses at the second gas inlet.
6. The turbine system according to claim 4, wherein each of the first dry gas seal and the second dry gas seal includes a seal housing, and a seal moving ring and a seal stationary ring accommodated in the seal housing, the seal housing has the first low temperature chamber or the second low temperature chamber formed therein, the seal housing further has the first air inlet or the second air inlet formed therein, the seal moving ring is fixedly mounted on the rotor, the seal stationary ring is circumferentially mounted on the outer periphery of the rotor and fixed on the seal housing, a balance film is formed between the seal moving ring and the seal stationary ring, and the first air inlet or the second air inlet is located on a side of the seal housing close to the seal moving ring.
7. The turbine system of claim 4, wherein the control module further comprises two pressure sensing elements and two flow sensing elements electrically connected to the control body, the two pressure sensing elements being disposed at the first and second air inlets, respectively, and the two flow sensing elements being disposed at the first and second air inlets, respectively.
8. The turbine system of claim 2, further comprising a thrust bearing mounted on the rotor, the thrust bearing being located between the compressor and the motor body or the thrust bearing being located between the turbine and the motor body.
9. The turbine system of claim 8 wherein the thrust bearing includes a rotating portion and a stationary portion disposed about the rotor, the rotating portion being fixedly coupled to the rotor and the stationary portion being fixedly coupled to the housing.
10. The turbine system of claim 9, further comprising a thrust parameter sensing member fixedly mounted to the stationary portion, the thrust parameter sensing member being coupled to the control module to sense axial thrust data of the rotor and transmit the thrust data to the control module.
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