CN112228222A - Distributed multi-shaft gas turbine and composite power system - Google Patents
Distributed multi-shaft gas turbine and composite power system Download PDFInfo
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- CN112228222A CN112228222A CN202011230573.5A CN202011230573A CN112228222A CN 112228222 A CN112228222 A CN 112228222A CN 202011230573 A CN202011230573 A CN 202011230573A CN 112228222 A CN112228222 A CN 112228222A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
- F02C3/103—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor the compressor being of the centrifugal type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
- H01M8/04014—Heat exchange using gaseous fluids; Heat exchange by combustion of reactants
- H01M8/04022—Heating by combustion
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/50—Fuel cells
Abstract
The invention provides a distributed multi-shaft gas turbine and a composite power system, wherein the distributed multi-shaft gas turbine comprises: the low-pressure shaft module, the first intercooler module, the high-pressure shaft module, the heat regenerator module, the combustion chamber module and the power turbine driving module are independent of each other and connected through pipelines; wherein the low spool module comprises: the low-pressure compressor and the low-pressure turbine are coaxially connected through a bearing; the high pressure shaft module includes: the high-pressure compressor and the high-pressure turbine are coaxially connected through a bearing; the power turbine drive module includes: the power turbine and the power output unit are coaxially connected through a bearing. The distributed multi-shaft gas turbine provided by the invention solves the problem that the existing single-shaft gas turbine is difficult to design.
Description
Technical Field
The invention relates to a gas turbine structure, in particular to a distributed multi-shaft gas turbine and a composite power system.
Background
The gas turbine continuously sucks air from the atmosphere through the gas compressor and compresses the air, the compressed air enters the combustion chamber and is mixed with the sprayed fuel to be combusted into high-temperature gas, and then the high-temperature gas flows into the turbine to be expanded and do work so as to push the turbine impeller to drive the gas compressor impeller to rotate together; because the work capacity of the heated high-temperature gas is obviously improved, the turbine drives the compressor and simultaneously has residual work as the output mechanical work of the gas turbine.
The existing gas turbine specially used for the ground is basically of a single-shaft structure, and is realized by adopting a low-pressure shaft (a low-pressure compressor and a low-pressure turbine), a medium-pressure shaft (a medium-pressure compressor and a medium-pressure turbine) or a high-pressure shaft (a high-pressure compressor and a high-pressure turbine) according to needs during specific application. Although the existing single-shaft structure can meet the basic functional requirements of the gas turbine, for some application scenes (such as high-pressure and high-power application scenes), the performance requirements of the gas compressor are very high, so that the design difficulty of the single-shaft gas turbine is higher.
Disclosure of Invention
In view of the above-mentioned shortcomings of the prior art, the present invention provides a distributed multi-shaft gas turbine and a hybrid power system, which are used for solving the problem of difficult design of the existing single-shaft gas turbine.
To achieve the above and other related objects, the present invention provides a distributed multi-shaft gas turbine including: a low-pressure shaft module, a first intercooler module, a high-pressure shaft module, a heat regenerator module, a combustion chamber module and a power turbine driving module which are independent from each other and connected through pipelines,
the low spool module includes: the low-pressure compressor and the low-pressure turbine are coaxially connected through a bearing;
the high pressure shaft module includes: the high-pressure compressor and the high-pressure turbine are coaxially connected through a bearing;
the power turbine drive module includes: the power turbine and the power output unit are coaxially connected through a bearing;
wherein, the air inlet of low pressure compressor is used for the inhaled air, the gas outlet of low pressure compressor with the air intlet of first intercooler module links to each other, the air outlet of first intercooler module with the air inlet of high pressure compressor links to each other, the gas outlet of high pressure compressor with the air intlet of regenerator module links to each other, the air outlet of regenerator module with the air inlet of combustion chamber module links to each other, the gas outlet of combustion chamber module with the air inlet of high pressure turbine links to each other, the gas outlet of high pressure turbine with the air inlet of low pressure turbine links to each other, the gas outlet of low pressure turbine with the air inlet of power turbine links to each other, the gas outlet of power turbine with the heat medium import of regenerator module links to each other.
Optionally, the low-pressure shaft module and the high-pressure shaft module are both implemented by axial flow structures, at this time, the low-pressure compressor and the high-pressure compressor are both axial flow compressors, and the low-pressure turbine and the high-pressure turbine are both axial flow turbines; or the low-pressure shaft module and the high-pressure shaft module are both realized by adopting a radial flow structure, at the moment, the low-pressure compressor and the high-pressure compressor are both centrifugal compressors, and the low-pressure turbine and the high-pressure turbine are both centripetal turbines; or the low-pressure shaft module and the high-pressure shaft module are realized by adopting a mixed structure, at the moment, one of the low-pressure compressor and the high-pressure compressor is an axial-flow compressor, the other is a centrifugal compressor, and the corresponding one of the low-pressure turbine and the high-pressure turbine is an axial-flow turbine and the other is a centripetal turbine.
Optionally, a turbocharger is used in place of the centrifugal compressor.
Optionally, the distributed multi-shaft gas turbine further comprises: at least one medium pressure shaft module, the medium pressure shaft module comprising: the medium-pressure compressor and the medium-pressure turbine are coaxially connected through a bearing, at the moment, the medium-pressure compressor is connected between an air outlet of the first intercooler module and an air inlet of the high-pressure compressor, and the medium-pressure turbine is connected between an air outlet of the high-pressure turbine and an air inlet of the low-pressure turbine; when the distributed multi-shaft gas turbine comprises two or more medium-pressure shaft modules, the medium-pressure compressors are connected in series between the air outlet of the first intercooler module and the air inlet of the high-pressure compressor, and the medium-pressure turbines are connected in series between the air outlet of the high-pressure turbine and the air inlet of the low-pressure turbine.
Optionally, the distributed multi-shaft gas turbine further comprises: at least one second intercooler module connected between an air outlet of the medium pressure compressor and an air inlet of the high pressure compressor; when the distributed multi-shaft gas turbine comprises two or more second air cooler modules, the second air cooler modules are further connected between the two adjacent medium-pressure compressors.
Optionally, the low-pressure shaft module, the medium-pressure shaft module and the high-pressure shaft module are all implemented by adopting an axial-flow structure, at this time, the low-pressure compressor, the medium-pressure compressor and the high-pressure compressor are all axial-flow compressors, and the low-pressure turbine, the medium-pressure turbine and the high-pressure turbine are all axial-flow turbines; or the low-pressure shaft module, the medium-pressure shaft module and the high-pressure shaft module are all realized by adopting a radial flow structure, at the moment, the low-pressure compressor, the medium-pressure compressor and the high-pressure compressor are all centrifugal compressors, and the low-pressure turbine, the medium-pressure turbine and the high-pressure turbine are all centripetal turbines; or the low-pressure shaft module, the medium-pressure shaft module and the high-pressure shaft module are realized by adopting a mixed structure, at the moment, any one or two of the low-pressure compressor, the medium-pressure compressor and the high-pressure compressor is/are an axial-flow compressor, the rest is/are a centrifugal compressor, the corresponding one or two of the low-pressure turbine, the medium-pressure turbine and the high-pressure turbine is/are an axial-flow turbine, and the rest is a centripetal turbine.
Optionally, a turbocharger is used in place of the centrifugal compressor.
Optionally, the power output unit comprises a high speed motor or a gearbox.
The present invention also provides a hybrid power system, comprising: the distributed multi-shaft gas turbine and high temperature fuel cell of any one of the above claims, wherein the high temperature fuel cell is connected between an air outlet of the recuperator module and an air inlet of the combustor module.
The present invention also provides a hybrid power system, comprising: the distributed multi-shaft gas turbine and the high-temperature fuel cell as described in any one of the above, wherein the high-temperature fuel cell is connected between an air outlet of the power turbine and a heat medium inlet of the heat regenerator module.
The present invention also provides a hybrid power system, comprising: the distributed multi-shaft gas turbine and the high-temperature fuel cell as described in any one of the above, wherein the high-temperature fuel cell is connected into the distributed multi-shaft gas turbine through a high-temperature heat regenerator module; at the moment, the air outlet of the high-temperature fuel cell is connected with the heating medium inlet of the high-temperature heat regenerator module, the air inlet of the high-temperature heat regenerator module is connected with the air outlet of the heat regenerator module, and the air outlet of the high-temperature heat regenerator module is connected with the air inlet of the combustion chamber module.
The present invention also provides a hybrid power system, comprising: the distributed multi-shaft gas turbine and the high-temperature fuel cell as described in any one of the above, wherein the high-temperature fuel cell is connected into the distributed multi-shaft gas turbine through a high-temperature heat regenerator module; at the moment, the gas outlet of the high-temperature fuel cell is connected with the heat medium inlet of the high-temperature heat regenerator module, the tail gas inlet of the high-temperature heat regenerator module is connected with the gas outlet of the power turbine, and the tail gas outlet of the high-temperature heat regenerator module is connected with the heat medium inlet of the heat regenerator module.
The present invention also provides a hybrid power system, comprising: the distributed multi-shaft gas turbine, the first high-temperature fuel cell and the second high-temperature fuel cell as described in any of the above, wherein the first high-temperature fuel cell is connected to the distributed multi-shaft gas turbine through a first high-temperature regenerator module, and the second high-temperature fuel cell is connected to the distributed multi-shaft gas turbine through a second high-temperature regenerator module; at this moment, the gas outlet of first high temperature fuel cell with the heat medium import of first high temperature regenerator module links to each other, the air intlet of first high temperature regenerator module with the air outlet of regenerator module links to each other, the air outlet of first high temperature regenerator module with the air intlet of combustion chamber module links to each other, the gas outlet of second high temperature fuel cell with the heat medium import of second high temperature regenerator module links to each other, the tail gas import of second high temperature regenerator module with power turbine's gas outlet links to each other, the tail gas export of second high temperature regenerator module with the heat medium import of regenerator module links to each other.
The present invention also provides a hybrid power system, comprising: the distributed multi-shaft gas turbine and solar receiver of any of the above claims, wherein the solar receiver is connected between an air outlet of the thermal regenerator module and an air inlet of the combustor module.
As described above, the distributed multi-shaft gas turbine and the hybrid power system according to the present invention have the following advantageous effects:
1. the invention adopts the modularized structural design, so that scattered space is easier to utilize, distributed layout of all modules in a smaller space is realized, and the assembly of the multi-shaft gas turbine is completed.
2. Because the invention adopts a multi-shaft structure, the rotating speed and the pressure ratio of each shaft can be independently adjusted, the approximate equivalent rate operation under partial load is ensured, and the design flexibility and the efficiency of the gas turbine are improved.
3. The modules in the distributed multi-shaft gas turbine can be realized by adopting the existing mature technology, for example, the functions of a low-pressure compressor, a medium-pressure compressor and/or a high-pressure compressor are realized by adopting a turbocharger with mature technology and low price, so that the design difficulty and the cost of the distributed multi-shaft gas turbine are reduced.
4. The distributed multi-shaft gas turbine can be conveniently coupled with other energy systems to form a composite power system, so that the system efficiency and the layout flexibility of the composite power system are greatly improved.
Drawings
Fig. 1 shows a schematic structural diagram of a distributed multi-shaft gas turbine according to a first embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a distributed multi-shaft gas turbine according to a second embodiment of the present invention.
Fig. 3 is a schematic structural diagram of a hybrid power system according to a third embodiment of the present invention.
Fig. 4 is a schematic structural diagram of a hybrid power system according to a fourth embodiment of the invention.
Fig. 5 is a schematic structural diagram of a hybrid power system according to a fifth embodiment of the present invention.
Fig. 6 is a schematic structural diagram of a hybrid power system according to a sixth embodiment of the invention.
Fig. 7 is a schematic structural diagram of a hybrid power system according to a seventh embodiment of the invention.
Fig. 8 is a schematic structural diagram of a hybrid power system according to an eighth embodiment of the present invention.
Description of the element reference numerals
1 composite power system
10 distributed multi-shaft gas turbine
100 low-pressure shaft module
101 low pressure compressor
102 low pressure turbine
200 first intercooler module
300 medium-pressure shaft module
301 medium pressure compressor
302 medium pressure turbine
400 second chiller module
500 high-pressure shaft module
501 high-pressure compressor
502 high-pressure turbine
600 heat regenerator module
700 combustion chamber module
800 power turbine drive module
801 power turbine
802 power output unit
20 high temperature fuel cell
21 first high temperature fuel cell
22 second high temperature fuel cell
30 high temperature regenerator module
31 first high temperature regenerator module
32 second high temperature regenerator module
40 solar receiver
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention.
Please refer to fig. 1 to 8. It should be noted that the drawings provided in the present embodiment are only schematic and illustrate the basic idea of the present invention, and although the drawings only show the components related to the present invention and are not drawn according to the number, shape and size of the components in actual implementation, the form, quantity and proportion of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
Example one
As shown in FIG. 1, the present embodiment provides a distributed multi-shaft gas turbine engine 10 comprising: a low pressure shaft module 100, a first intercooler module 200, a high pressure shaft module 500, a regenerator module 600, a combustor module 700, and a power turbine driving module 800 which are independent from each other and connected by a pipe,
the low pressure shaft module 100 includes: the low-pressure compressor 101 and the low-pressure turbine 102 are coaxially connected through a bearing;
the high pressure shaft module 500 includes: the high-pressure turbine comprises a high-pressure compressor 501 and a high-pressure turbine 502, wherein the high-pressure compressor 501 and the high-pressure turbine 502 are coaxially connected through a bearing;
the power turbine drive module 800 includes: a power turbine 801 and a power output unit 802, wherein the power turbine 801 and the power output unit 802 are coaxially connected through a bearing;
the air inlet of the low-pressure compressor 101 is used for sucking air, the air outlet of the low-pressure compressor 101 is connected with the air inlet of the first intercooler module 200, the air outlet of the first intercooler module 200 is connected with the air inlet of the high-pressure compressor 501, the air outlet of the high-pressure compressor 501 is connected with the air inlet of the heat regenerator module 600, the air outlet of the heat regenerator module 600 is connected with the air inlet of the combustion chamber module 700, the air outlet of the combustion chamber module 700 is connected with the air inlet of the high-pressure turbine 502, the air outlet of the high-pressure turbine 502 is connected with the air inlet of the low-pressure turbine 102, the air outlet of the low-pressure turbine 102 is connected with the air inlet of the power turbine 801, and the air outlet of the power turbine 801 is connected with the heat medium inlet of the heat regenerator module 600.
In this example, the low pressure shaft module 100, the first intercooler module 200, the high pressure shaft module 500, the regenerator module 600, the combustor module 700, and the power turbine drive module 800 all have separate housings to modularize the above parts; when the modules are connected through the pipeline, the pipeline needs to have certain pressure resistance and thermal expansion, the pressure resistance can be realized by selecting proper pipeline materials, and the thermal expansion can be realized by arranging a flexible link (such as an expansion joint) on the pipeline.
In a specific application, the low-pressure compressor 101 is used for compressing low-pressure air from the environment, and the low-pressure turbine 102 is used for receiving tail gas discharged from the high-pressure turbine 502; in this example, the rotation speed of the low-pressure compressor 101 is consistent with the rotation speed of the low-pressure turbine 102, so that the work output of the low-pressure turbine 102 is consistent with the power consumption of the low-pressure compressor 101, and the net power of the low-pressure shaft module 100 is zero. The first intercooler module 200 is used for reducing the temperature of the air from the low-pressure compressor 101 to be close to the temperature of the air before the air enters the low-pressure compressor 101 (namely, the temperature of the air in the environment), so that the power consumption of the high-pressure compressor 501 in the compression process is reduced; in this example, the first intercooler module 200 may select a suitable refrigerant to exchange heat, such as air, according to the requirement. The high-pressure compressor 501 is used for compressing air from the first intercooler module 200, and the high-pressure turbine 502 is used for receiving tail gas discharged after combustion from the combustor module 700; in this example, the rotation speed of the high-pressure compressor 501 is consistent with the rotation speed of the high-pressure turbine 502, so that the work output of the high-pressure turbine 502 is consistent with the power consumption of the high-pressure compressor 501, and the net power of the high-pressure shaft module 500 is zero. The heat regenerator module 600 is used for exchanging heat between the exhaust gas discharged from the power turbine 801 and the air from the high-pressure compressor 501, so as to increase the temperature of the air entering the combustor module 700, thereby reducing the fuel consumption and improving the combustion efficiency of the system, so that the comprehensive efficiency of the system is not lower than 40%. The power turbine 801 is used for receiving tail gas discharged from the low-pressure compressor 102, and the power output unit 802 is used for outputting high-frequency alternating current under the driving of the power turbine 801.
As an example, the low-pressure shaft module 100 and the high-pressure shaft module 500 are both implemented by adopting an axial flow structure, so that the distributed multi-shaft gas turbine of the present example is suitable for a high-power application scenario; at this time, the low-pressure compressor 101 and the high-pressure compressor 501 are both axial-flow compressors, and the low-pressure turbine 102 and the high-pressure turbine 502 are both axial-flow turbines. Alternatively, the low-pressure shaft module 100 and the high-pressure shaft module 500 are both implemented by adopting a radial flow structure, so that the distributed multi-shaft gas turbine of this example is suitable for an application scenario with power less than 5MW, and the design difficulty of the distributed multi-shaft gas turbine is simplified by using a simple radial flow structure; at this time, the low-pressure compressor 101 and the high-pressure compressor 501 are both centrifugal compressors, and the low-pressure turbine 102 and the high-pressure turbine 502 are both centripetal turbines. Of course, the low-pressure shaft module 100 and the high-pressure shaft module 500 may also be implemented by a hybrid structure, in this case, one of the low-pressure compressor 101 and the high-pressure compressor 501 is an axial-flow compressor, the other is a centrifugal compressor, and the corresponding one of the low-pressure turbine 102 and the high-pressure turbine 502 is an axial-flow turbine and the other is a centripetal turbine. It should be noted that, here, "one of the low-pressure turbine 102 and the high-pressure turbine 502 is an axial-flow turbine, and the other is a centripetal turbine" means: when the low-pressure compressor 101 is an axial-flow compressor and the high-pressure compressor 501 is a centrifugal compressor, the low-pressure turbine 102 is an axial-flow turbine and the high-pressure turbine 502 is a centripetal turbine; when the low-pressure compressor 101 is a centrifugal compressor and the high-pressure compressor 501 is an axial-flow compressor, the low-pressure turbine 102 is a centripetal turbine and the high-pressure turbine 502 is an axial-flow turbine. Optionally, when the low-pressure compressor 101 and/or the high-pressure compressor 501 are centrifugal compressors, a turbocharger may be used to replace the centrifugal compressors, thereby reducing the design difficulty and cost of the distributed multi-shaft gas turbine according to this example.
As an example, in order to reduce the complexity of the distributed multi-shaft gas turbine of the present example, the low-pressure compressor 101 and the low-pressure turbine 102, the high-pressure compressor 501 and the high-pressure turbine 502, and the power turbine 801 and the power output unit 802 are coaxially connected by air bearings, thereby eliminating the need for a lubricating oil system of the distributed multi-shaft gas turbine of the present example.
By way of example, the power output unit 802 includes a high speed motor or gearbox; when the power output unit 802 is a high-speed motor, the power turbine 801 is a power turbine with a fixed nozzle, and at this time, the high-speed motor adopts a variable-speed operation mode so as to adjust an operation condition point of the power turbine 802; when the power output unit 802 is a gear box, the power turbine 801 is a power turbine with an adjustable nozzle, and the gear box can realize variable rotation speed through the adjustable nozzle of the power turbine, so as to adjust the operating point of the power turbine 802.
The operation of the distributed multi-shaft gas turbine according to the present embodiment will be described with reference to fig. 1.
The low-pressure compressor 101 sucks low-pressure air in the environment and compresses the low-pressure air, the air compressed by the low-pressure compressor 101 enters the first intercooler module 200 to be cooled, then enters the high-pressure compressor 501, the air compressed by the high-pressure compressor 501 enters the heat regenerator module 600 and exchanges heat with tail gas discharged from the power turbine 801, the air after exchanging heat enters the combustor module 700 and combusts with fuel sprayed into the combustor module 700, high-temperature and high-pressure tail gas generated after combustion sequentially passes through the high-pressure turbine 502, the low-pressure turbine 102 and finally enters the power turbine 801 to do work so as to drive the power output unit 802 to output high-frequency alternating current, and meanwhile, the tail gas discharged after the power turbine 801 does work enters the heat regenerator module 600 through a heat medium inlet. It should be noted that the tail gas after heat exchange is discharged through the heat medium outlet of the heat regenerator module 600, and may be directly discharged to the air, or may be discharged to other equipment through a pipeline for subsequent treatment, which is not limited in this example.
Example two
As shown in fig. 2, the present embodiment provides a distributed multi-shaft gas turbine, which is different from the first embodiment in that the distributed multi-shaft gas turbine 10 of the present example further includes: at least one medium pressure shaft module 300, said medium pressure shaft module 300 comprising: the intermediate pressure compressor 301 and the intermediate pressure turbine 302 are coaxially connected through a bearing, in this case, the intermediate pressure compressor 301 is connected between an air outlet of the first intercooler module 200 and an air inlet of the high pressure compressor 501, and the intermediate pressure turbine 302 is connected between an air outlet of the high pressure turbine 502 and an air inlet of the low pressure turbine 102; when the distributed multi-shaft gas turbine 10 includes two or more intermediate-pressure shaft modules 300, a plurality of the intermediate-pressure compressors 301 are connected in series between the air outlet of the first intercooler module 200 and the air inlet of the high-pressure compressor 501, and a plurality of the intermediate-pressure turbines 302 are connected in series between the air outlet of the high-pressure turbine 502 and the air inlet of the low-pressure turbine 102.
As an example, as shown in fig. 2, the distributed multi-shaft gas turbine 10 further includes: at least one second intercooler module 400, wherein the second intercooler module 400 is connected between an air outlet of the medium-pressure compressor 301 and an air inlet of the high-pressure compressor 501; when the distributed multi-shaft gas turbine 10 includes two or more second chiller modules 400, the second chiller modules 400 are further connected between two adjacent intermediate-pressure compressors 301. Optionally, when the distributed multi-shaft gas turbine 10 includes two or more second chiller modules 400, the number of the second chiller modules 400 is the same as that of the intermediate-pressure compressors 301, and the second chiller modules 400 are spaced from the intermediate-pressure compressors 301, so that the second chiller modules 400 are disposed between two adjacent intermediate-pressure compressors 301 and between the intermediate-pressure compressors 301 and the high-pressure compressors 501. In practical applications, the number of the intermediate pressure shaft modules 300 and the second intercooler modules 400 can be set as required, so as to improve the design flexibility of the distributed multi-shaft gas turbine in the present example.
In this example, the middle pressure shaft module 300 and the second air cooler module 400 also have independent housings to achieve modularization. In a specific application, the intermediate-pressure compressor 301 is used for compressing air from the first intercooler module 200 or the intermediate-pressure compressor 301 of a previous stage, and the intermediate-pressure turbine 302 is used for receiving tail gas discharged from the high-pressure turbine 502 or the intermediate-pressure turbine 302 of a previous stage; in this example, the rotation speed of the intermediate pressure compressor 301 is consistent with the rotation speed of the intermediate pressure turbine 302, so that the work output of the intermediate pressure turbine 302 is consistent with the power consumption of the intermediate pressure compressor 301, and the net power of the intermediate pressure shaft module 300 is zero. The second intercooler module 400 is configured to reduce the temperature of the air from the intermediate-pressure compressor 301 to a temperature close to that before the air enters the intermediate-pressure compressor, so as to reduce the power consumption of the subsequent intermediate-pressure compressor 301 or the subsequent high-pressure compressor 501 in the compression process; in this example, the second intercooler module 400 may select a suitable refrigerant to exchange heat, such as air, according to the requirement.
As an example, the low-pressure shaft module 100, the medium-pressure shaft module 300, and the high-pressure shaft module 500 are all implemented by adopting an axial flow structure, so that the distributed multi-shaft gas turbine of the present example is suitable for a high-power application scenario; at this time, the low-pressure compressor 101, the intermediate-pressure compressor 301, and the high-pressure compressor 501 are all axial-flow compressors, and the low-pressure turbine 102, the intermediate-pressure turbine 302, and the high-pressure turbine 502 are all axial-flow turbines. Or, the low-pressure shaft module 100, the medium-pressure shaft module 300, and the high-pressure shaft module 500 are all implemented by adopting a radial flow structure, so that the distributed multi-shaft gas turbine of this example is suitable for an application scenario with power less than 5MW, and the design difficulty is simplified by using a simple radial flow structure; in this case, the low-pressure compressor 101, the intermediate-pressure compressor 301, and the high-pressure compressor 501 are all centrifugal compressors, and the low-pressure turbine 102, the intermediate-pressure turbine 302, and the high-pressure turbine 502 are all centripetal turbines. Of course, the low-pressure shaft module 100, the intermediate-pressure shaft module 300, and the high-pressure shaft module 500 may also be implemented by a hybrid structure, at this time, any one or two of the low-pressure compressor 101, the intermediate-pressure compressor 301, and the high-pressure compressor 501 are axial-flow compressors, the rest are centrifugal compressors, corresponding one or two of the low-pressure turbine 102, the intermediate-pressure turbine 302, and the high-pressure turbine 502 are axial-flow turbines, and the rest are centripetal turbines. It should be noted that, here, "one or two of the low-pressure turbine 102, the intermediate-pressure turbine 302, and the high-pressure turbine 502 are axial-flow turbines, and the rest are centripetal turbines" means: when the low-pressure compressor 101 is an axial-flow compressor, and the medium-pressure compressor 301 and the high-pressure compressor 501 are both centrifugal compressors, the low-pressure turbine 102 is an axial-flow turbine, and the medium-pressure turbine 302 and the high-pressure turbine 502 are both centripetal turbines; when the intermediate-pressure compressor 301 is an axial-flow compressor, and the low-pressure compressor 101 and the high-pressure compressor 501 are both centrifugal compressors, the intermediate-pressure turbine 302 is an axial-flow turbine, and the low-pressure turbine 102 and the high-pressure turbine 502 are both centripetal turbines; when the high-pressure compressor 501 is an axial-flow compressor, and the low-pressure compressor 101 and the medium-pressure compressor 301 are both centrifugal compressors, the high-pressure compressor 501 is an axial-flow turbine, and the low-pressure turbine 102 and the medium-pressure turbine 302 are both centripetal turbines; when the low-pressure compressor 101 and the medium-pressure compressor 301 are both axial-flow compressors and the high-pressure compressor 501 is a centrifugal compressor, the low-pressure turbine 102 and the medium-pressure turbine 302 are both axial-flow turbines and the high-pressure turbine 502 is a centripetal turbine; when the low-pressure compressor 101 and the high-pressure compressor 501 are both axial-flow compressors and the medium-pressure compressor 301 is a centrifugal compressor, the low-pressure turbine 102 and the high-pressure turbine 502 are both axial-flow turbines and the medium-pressure turbine 302 is a centripetal turbine; when the intermediate-pressure compressor 301 and the high-pressure compressor 501 are both axial-flow compressors and the low-pressure compressor 101 is a centrifugal compressor, the intermediate-pressure turbine 302 and the high-pressure turbine 502 are both axial-flow turbines, and the low-pressure turbine 102 is a centripetal turbine. Optionally, when the low-pressure compressor 101, the intermediate-pressure compressor 301 and/or the high-pressure compressor 501 are centrifugal compressors, a turbocharger may be used to replace the centrifugal compressors, thereby reducing the design difficulty and cost of the distributed multi-shaft gas turbine according to this example.
As an example, in order to reduce the complexity of the distributed multi-shaft gas turbine according to the present example, the intermediate-pressure compressor 301 and the intermediate-pressure turbine 302 are also coaxially connected by an air bearing, thereby eliminating the need for a lubricating oil system in the distributed multi-shaft gas turbine according to the present example.
The operation of the distributed multi-shaft gas turbine according to the present embodiment will be described with reference to fig. 2, which includes one medium-pressure shaft module 300 and one second intercooler module 400 as an example.
The low-pressure compressor 101 sucks in low-pressure air in the environment and compresses the low-pressure air, the air compressed by the low-pressure compressor 101 enters the first intercooler module 200 for cooling, then enters the medium-pressure compressor 301, the air compressed by the medium-pressure compressor 301 enters the second intercooler module 400 for cooling, then enters the high-pressure compressor 501, the air compressed by the high-pressure compressor 501 enters the heat regenerator module 600 and exchanges heat with tail gas discharged from the power turbine 801, the air after exchanging heat enters the combustor module 700 and combusts with fuel sprayed in the combustor module 700, high-temperature and high-pressure tail gas generated after combustion sequentially passes through the high-pressure turbine 502, the medium-pressure turbine 302, the low-pressure turbine 102 and finally enters the power turbine 801 to do work to drive the power output unit 802 to output high-frequency alternating current, meanwhile, the tail gas discharged after the power turbine 801 applies work enters the heat regenerator module 600 through a heat medium inlet. It should be noted that the tail gas after heat exchange is discharged through the heat medium outlet of the heat regenerator module 600, and may be directly discharged to the air, or may be discharged to other equipment through a pipeline for subsequent treatment, which is not limited in this example.
EXAMPLE III
As shown in fig. 3, the present embodiment provides a hybrid system, the hybrid system 1 including: the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 according to the first embodiment or the second embodiment, wherein the high-temperature fuel cell 20 is connected between an air outlet of the heat regenerator module 600 and an air inlet of the combustor module 700; at this time, the distributed multi-shaft gas turbine 10 and the high temperature fuel cell 20 are directly top-coupled, that is, the air after heat exchange by the heat regenerator module 600 directly enters the high temperature fuel cell 20 and electrochemically reacts with the fuel 2 therein to heat the air that does not participate in the reaction, so as to further increase the temperature of the air entering the combustor module 700, thereby increasing the combustion efficiency of the system, and simultaneously reducing the fuel demand entering the combustor module 700.
As an example, the high temperature fuel cell 20 is a pressurized type fuel cell, such as a Solid Oxide Fuel Cell (SOFC). It should be noted that the fuel 1 entering the combustor module 700 and the fuel 2 entering the high temperature fuel cell 20 may be the same or different, and may be selected according to actual needs, which is not limited in this example.
Example four
As shown in fig. 4, the present embodiment provides a hybrid system, the hybrid system 1 including: the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 according to the first embodiment or the second embodiment, wherein the high-temperature fuel cell 20 is connected between the air outlet of the power turbine 801 and the heat medium inlet of the heat regenerator module 600; at this time, the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 are directly coupled as a bottom layer, and the high-temperature tail gas of the power turbine 801 is used as the air of the high-temperature fuel cell 20 to perform an electrochemical reaction with the fuel 2 therein, so as to increase the temperature of the air entering the high-temperature fuel cell 20, thereby improving the combustion efficiency of the system.
The high-temperature fuel cell 20 is, for example, an atmospheric pressure type fuel cell. It should be noted that the fuel 1 entering the combustor module 700 and the fuel 2 entering the high temperature fuel cell 20 may be the same or different, and may be selected according to actual needs, which is not limited in this example.
EXAMPLE five
As shown in fig. 5, the present embodiment provides a hybrid system, the hybrid system 1 including: the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 according to the first embodiment or the second embodiment, wherein the high-temperature fuel cell 20 is connected to the distributed multi-shaft gas turbine 10 through a high-temperature regenerator module 30; at this time, the air outlet of the high-temperature fuel cell 20 is connected to the heat medium inlet of the high-temperature regenerator module 30, the air inlet of the high-temperature regenerator module 30 is connected to the air outlet of the regenerator module 600, and the air outlet of the high-temperature regenerator module 30 is connected to the air inlet of the combustor module 700; the distributed multi-shaft gas turbine 10 is indirectly coupled to the high-temperature fuel cell 20, and the exhaust gas discharged after the electrochemical reaction of the high-temperature fuel cell 20 is used to preheat the air after heat exchange by the heat regenerator module 600, so as to further increase the temperature of the air entering the combustion chamber module 700, thereby improving the combustion efficiency of the system, and simultaneously reducing the fuel demand entering the combustion chamber module 700.
As an example, the high-temperature fuel cell 20 is a pressurized-type fuel cell. It should be noted that the fuel 1 entering the combustor module 700 and the fuel 2 entering the high temperature fuel cell 20 may be the same or different, and may be selected according to actual needs, which is not limited in this example.
As an example, the heat medium outlet of the high temperature heat regenerator module 30 is connected to the heat medium outlet of the heat regenerator module 600, so as to perform centralized treatment on the exhaust gas discharged from the system, for example, the exhaust gas is applied to subsequent equipment.
EXAMPLE six
As shown in fig. 6, the present embodiment provides a hybrid system, the hybrid system 1 including: the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 according to the first embodiment or the second embodiment, wherein the high-temperature fuel cell 20 is connected to the distributed multi-shaft gas turbine 10 through a high-temperature regenerator module 30; at this time, the gas outlet of the high-temperature fuel cell 20 is connected to the heat medium inlet of the high-temperature heat regenerator module 30, the tail gas inlet of the high-temperature heat regenerator module 30 is connected to the gas outlet of the power turbine 801, and the tail gas outlet of the high-temperature heat regenerator module 30 is connected to the heat medium inlet of the heat regenerator module 600; the distributed multi-shaft gas turbine 10 is indirectly coupled to the high-temperature fuel cell 20, and the tail gas discharged after the electrochemical reaction of the high-temperature fuel cell 20 is utilized to preheat the tail gas discharged from the power turbine 801, so as to increase the temperature of the tail gas entering the heat regenerator module 600, further increase the temperature of the air entering the combustor module 700, thereby increasing the combustion efficiency of the system, and simultaneously reducing the fuel demand entering the combustor module 700.
The high-temperature fuel cell 20 is, for example, an atmospheric pressure type fuel cell. It should be noted that the fuel 1 entering the combustor module 700 and the fuel 2 entering the high temperature fuel cell 20 may be the same or different, and may be selected according to actual needs, which is not limited in this example.
As an example, the heat medium outlet of the high temperature heat regenerator module 30 is connected to the heat medium outlet of the heat regenerator module 600, so as to perform centralized treatment on the exhaust gas discharged from the system, for example, the exhaust gas is applied to subsequent equipment.
EXAMPLE seven
As shown in fig. seven, the present embodiment provides a hybrid system, and the hybrid system 1 includes: the distributed multi-shaft gas turbine 10 according to the first embodiment or the second embodiment, the first high-temperature fuel cell 21, and the second high-temperature fuel cell 22, wherein the first high-temperature fuel cell 21 is connected to the distributed multi-shaft gas turbine 10 through the first high-temperature regenerator module 31, and the second high-temperature fuel cell 22 is connected to the distributed multi-shaft gas turbine 10 through the second high-temperature regenerator module 32; at this time, the air outlet of the first high-temperature fuel cell 21 is connected to the heat medium inlet of the first high-temperature regenerator module 31, the air inlet of the first high-temperature regenerator module 21 is connected to the air outlet of the regenerator module 600, the air outlet of the first high-temperature regenerator module 31 is connected to the air inlet of the combustor module 700, the air outlet of the second high-temperature fuel cell 22 is connected to the heat medium inlet of the second high-temperature regenerator module 32, the tail gas inlet of the second high-temperature regenerator module 32 is connected to the air outlet of the power turbine 801, and the tail gas outlet of the second high-temperature regenerator module 32 is connected to the heat medium inlet of the regenerator module 600; the distributed multi-shaft gas turbine 10 is indirectly coupled to the first high temperature fuel cell 21 and the second high temperature fuel cell 22, the air heat-exchanged by the regenerator module 600 is preheated by using the tail gas discharged after the electrochemical reaction of the first high temperature fuel cell 21 to increase the temperature of the air entering the combustor module 700, and the tail gas discharged after the electrochemical reaction of the second high temperature fuel cell 22 is used to preheat the tail gas discharged by the power turbine 801 to increase the temperature of the tail gas entering the regenerator module 600, so that the temperature of the air entering the combustor module 700 is further increased, the combustion efficiency of the system is increased (by more than 70%), and the fuel demand entering the combustor module 700 is reduced.
As an example, the first high-temperature fuel cell 21 is a pressurized-type fuel cell, and the second high-temperature fuel cell 22 is an atmospheric-pressure-type fuel cell. It should be noted that the fuel 1 entering the combustor module 700 and the fuel 2 entering the first high temperature fuel cell 21 and the second high temperature fuel cell 22 may be the same or different, and may be selected according to actual needs, which is not limited in this example.
As an example, the heat medium outlet of the first high temperature regenerator module 31 and the heat medium outlet of the second high temperature regenerator module 32 are both connected to the heat medium outlet of the regenerator module 600, so as to perform centralized treatment on the exhaust gas discharged from the system, for example, the exhaust gas is applied to subsequent equipment.
Example eight
As shown in fig. 8, the present embodiment provides a hybrid system, the hybrid system 1 including: the distributed multi-shaft gas turbine 10 and the solar receiver 40 according to the first embodiment or the second embodiment, wherein the solar receiver 40 is connected between the air outlet of the heat regenerator module 600 and the air inlet of the combustor module 700, so that the air after heat exchange of the heat regenerator module 600 is heated by solar energy, thereby further increasing the temperature of the air entering the combustor module 700, so as to improve the combustion efficiency of the system, and simultaneously, the fuel requirement entering the combustor module 700 can be reduced.
Of course, the invention can also independently couple the thermal energy generating device with the distributed multi-shaft gas turbine in the first embodiment or the second embodiment to form a new compound power system according to other existing thermal energy types, thereby achieving the aim of improving the efficiency of the system.
In summary, the distributed multi-shaft gas turbine and the hybrid power system of the invention have the following beneficial effects: 1. the invention adopts the modularized structural design, so that scattered space is easier to utilize, distributed layout of all modules in a smaller space is realized, and the assembly of the multi-shaft gas turbine is completed. 2. Because the invention adopts a multi-shaft structure, the rotating speed and the pressure ratio of each shaft can be independently adjusted, the approximate equivalent rate operation under partial load is ensured, and the design flexibility and the efficiency of the gas turbine are improved. 3. The modules in the distributed multi-shaft gas turbine can be realized by adopting the existing mature technology, for example, the functions of a low-pressure compressor, a medium-pressure compressor and/or a high-pressure compressor are realized by adopting a turbocharger with mature technology and low price, so that the design difficulty and the cost of the distributed multi-shaft gas turbine are reduced. 4. The distributed multi-shaft gas turbine can be conveniently coupled with other energy systems to form a composite power system, so that the system efficiency and the layout flexibility of the composite power system are greatly improved. Therefore, the invention effectively overcomes various defects in the prior art and has high industrial utilization value.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (14)
1. A distributed multi-shaft gas turbine engine, comprising: a low-pressure shaft module, a first intercooler module, a high-pressure shaft module, a heat regenerator module, a combustion chamber module and a power turbine driving module which are independent from each other and connected through pipelines,
the low spool module includes: the low-pressure compressor and the low-pressure turbine are coaxially connected through a bearing;
the high pressure shaft module includes: the high-pressure compressor and the high-pressure turbine are coaxially connected through a bearing;
the power turbine drive module includes: the power turbine and the power output unit are coaxially connected through a bearing;
wherein, the air inlet of low pressure compressor is used for the inhaled air, the gas outlet of low pressure compressor with the air intlet of first intercooler module links to each other, the air outlet of first intercooler module with the air inlet of high pressure compressor links to each other, the gas outlet of high pressure compressor with the air intlet of regenerator module links to each other, the air outlet of regenerator module with the air inlet of combustion chamber module links to each other, the gas outlet of combustion chamber module with the air inlet of high pressure turbine links to each other, the gas outlet of high pressure turbine with the air inlet of low pressure turbine links to each other, the gas outlet of low pressure turbine with the air inlet of power turbine links to each other, the gas outlet of power turbine with the heat medium import of regenerator module links to each other.
2. The distributed multi-shaft gas turbine according to claim 1, wherein the low-pressure shaft module and the high-pressure shaft module are both implemented by an axial flow structure, in which case, the low-pressure compressor and the high-pressure compressor are both axial flow compressors, and the low-pressure turbine and the high-pressure turbine are both axial flow turbines; or the low-pressure shaft module and the high-pressure shaft module are both realized by adopting a radial flow structure, at the moment, the low-pressure compressor and the high-pressure compressor are both centrifugal compressors, and the low-pressure turbine and the high-pressure turbine are both centripetal turbines; or the low-pressure shaft module and the high-pressure shaft module are realized by adopting a mixed structure, at the moment, one of the low-pressure compressor and the high-pressure compressor is an axial-flow compressor, the other is a centrifugal compressor, and the corresponding one of the low-pressure turbine and the high-pressure turbine is an axial-flow turbine and the other is a centripetal turbine.
3. The distributed multi-shaft gas turbine as defined in claim 2, wherein a turbocharger is used in place of the centrifugal compressor.
4. The distributed multi-shaft gas turbine as set forth in claim 1, further comprising: at least one medium pressure shaft module, the medium pressure shaft module comprising: the medium-pressure compressor and the medium-pressure turbine are coaxially connected through a bearing, at the moment, the medium-pressure compressor is connected between an air outlet of the first intercooler module and an air inlet of the high-pressure compressor, and the medium-pressure turbine is connected between an air outlet of the high-pressure turbine and an air inlet of the low-pressure turbine; when the distributed multi-shaft gas turbine comprises two or more medium-pressure shaft modules, the medium-pressure compressors are connected in series between the air outlet of the first intercooler module and the air inlet of the high-pressure compressor, and the medium-pressure turbines are connected in series between the air outlet of the high-pressure turbine and the air inlet of the low-pressure turbine.
5. The distributed multi-shaft gas turbine as set forth in claim 4, further comprising: at least one second intercooler module connected between an air outlet of the medium pressure compressor and an air inlet of the high pressure compressor; when the distributed multi-shaft gas turbine comprises two or more second air cooler modules, the second air cooler modules are further connected between the two adjacent medium-pressure compressors.
6. The distributed multi-shaft gas turbine according to claim 4 or 5, wherein the low-pressure shaft module, the intermediate-pressure shaft module and the high-pressure shaft module are all implemented by an axial flow structure, in this case, the low-pressure compressor, the intermediate-pressure compressor and the high-pressure compressor are all axial flow compressors, and the low-pressure turbine, the intermediate-pressure turbine and the high-pressure turbine are all axial flow turbines; or the low-pressure shaft module, the medium-pressure shaft module and the high-pressure shaft module are all realized by adopting a radial flow structure, at the moment, the low-pressure compressor, the medium-pressure compressor and the high-pressure compressor are all centrifugal compressors, and the low-pressure turbine, the medium-pressure turbine and the high-pressure turbine are all centripetal turbines; or the low-pressure shaft module, the medium-pressure shaft module and the high-pressure shaft module are realized by adopting a mixed structure, at the moment, any one or two of the low-pressure compressor, the medium-pressure compressor and the high-pressure compressor is/are an axial-flow compressor, the rest is/are a centrifugal compressor, the corresponding one or two of the low-pressure turbine, the medium-pressure turbine and the high-pressure turbine is/are an axial-flow turbine, and the rest is a centripetal turbine.
7. The distributed multi-shaft gas turbine as defined in claim 6, wherein a turbocharger is used in place of the centrifugal compressor.
8. The distributed multi-shaft gas turbine engine as set forth in claim 1, wherein said power output unit comprises a high speed electric motor or a gearbox.
9. A hybrid powertrain system, comprising: the distributed multi-shaft gas turbine and high temperature fuel cell according to any one of claims 1-8, wherein the high temperature fuel cell is connected between an air outlet of the recuperator module and an air inlet of the combustor module.
10. A hybrid powertrain system, comprising: the distributed multi-shaft gas turbine and high temperature fuel cell according to any one of claims 1 to 8, wherein the high temperature fuel cell is connected between an outlet of the power turbine and a heating medium inlet of the recuperator module.
11. A hybrid powertrain system, comprising: the distributed multi-shaft gas turbine and high temperature fuel cell of any one of claims 1-8, the high temperature fuel cell being coupled into the distributed multi-shaft gas turbine through a high temperature recuperator module; at the moment, the air outlet of the high-temperature fuel cell is connected with the heating medium inlet of the high-temperature heat regenerator module, the air inlet of the high-temperature heat regenerator module is connected with the air outlet of the heat regenerator module, and the air outlet of the high-temperature heat regenerator module is connected with the air inlet of the combustion chamber module.
12. A hybrid powertrain system, comprising: the distributed multi-shaft gas turbine and high temperature fuel cell of any one of claims 1-8, the high temperature fuel cell being coupled into the distributed multi-shaft gas turbine through a high temperature recuperator module; at the moment, the gas outlet of the high-temperature fuel cell is connected with the heat medium inlet of the high-temperature heat regenerator module, the tail gas inlet of the high-temperature heat regenerator module is connected with the gas outlet of the power turbine, and the tail gas outlet of the high-temperature heat regenerator module is connected with the heat medium inlet of the heat regenerator module.
13. A hybrid powertrain system, comprising: the distributed multi-shaft gas turbine according to any one of claims 1 to 8, a first high temperature fuel cell coupled into the distributed multi-shaft gas turbine through a first high temperature recuperator module, and a second high temperature fuel cell coupled into the distributed multi-shaft gas turbine through a second high temperature recuperator module; at this moment, the gas outlet of first high temperature fuel cell with the heat medium import of first high temperature regenerator module links to each other, the air intlet of first high temperature regenerator module with the air outlet of regenerator module links to each other, the air outlet of first high temperature regenerator module with the air intlet of combustion chamber module links to each other, the gas outlet of second high temperature fuel cell with the heat medium import of second high temperature regenerator module links to each other, the tail gas import of second high temperature regenerator module with power turbine's gas outlet links to each other, the tail gas export of second high temperature regenerator module with the heat medium import of regenerator module links to each other.
14. A hybrid powertrain system, comprising: the distributed multi-shaft gas turbine and solar receiver of any one of claims 1-8 wherein the solar receiver is connected between an air outlet of the regenerator module and an air intake of the combustor module.
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