CN112282937B - Gas turbine system and coupling power system based on gas turbine system and new energy power generation system - Google Patents
Gas turbine system and coupling power system based on gas turbine system and new energy power generation system Download PDFInfo
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- CN112282937B CN112282937B CN202011306586.6A CN202011306586A CN112282937B CN 112282937 B CN112282937 B CN 112282937B CN 202011306586 A CN202011306586 A CN 202011306586A CN 112282937 B CN112282937 B CN 112282937B
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- 238000010248 power generation Methods 0.000 title claims abstract description 24
- 230000008878 coupling Effects 0.000 title description 11
- 238000010168 coupling process Methods 0.000 title description 11
- 238000005859 coupling reaction Methods 0.000 title description 11
- 238000010438 heat treatment Methods 0.000 claims abstract description 46
- 238000002485 combustion reaction Methods 0.000 claims abstract description 29
- 238000000034 method Methods 0.000 claims description 10
- 238000005485 electric heating Methods 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 230000017525 heat dissipation Effects 0.000 claims description 3
- 230000006698 induction Effects 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 229910001338 liquidmetal Inorganic materials 0.000 claims description 3
- 230000005855 radiation Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 238000002076 thermal analysis method Methods 0.000 claims description 2
- 239000012530 fluid Substances 0.000 claims 1
- 230000004044 response Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 4
- 238000005265 energy consumption Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 239000002699 waste material Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
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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
- F02C6/003—Gas-turbine plants with heaters between turbine stages
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The present disclosure provides a gas turbine system comprising: the compressor comprises a compressor cylinder and a compressor rotor, and is used for enabling working medium to flow between the compressor cylinder and the compressor rotor and be compressed; the combustion chamber is connected with the working medium output end of the air compressor; the turbine comprises a turbine cylinder and a turbine rotor, and is connected with the working medium output end of the combustion chamber; and the heating device is arranged on the outer surfaces of the air compressor cylinder and the turbine cylinder and is used for keeping the average temperature of the air compressor cylinder and the turbine cylinder not lower than 50% of the average temperature of the air compressor cylinder and the turbine cylinder in a stable working state so as to improve the starting speed of the gas turbine system. The present disclosure also provides a coupled power system utilizing the gas turbine system and the new energy power generation system as described in any of the above; the new energy power generation system is provided with a new energy unit, a control system, a load and a power grid.
Description
Technical Field
The disclosure relates to the technical field of coupled power systems in the technical field of new energy, and in particular relates to a coupled power system for improving the stability of a new energy system by using a method for improving the response speed of a gas turbine.
Background
With the continuous improvement of the specific gravity of clean energy in an electric power system, including wind power, photovoltaic, hydropower and the like, the large-scale access of the new energy into a power grid brings hidden trouble to the safe operation and stable operation of the electric power system due to the intermittent and fluctuation characteristics of the new energy. Because the cost of the energy storage technology is too high, the economy of a new energy system adopting the energy storage system is often poor, and the gas turbine has high response speed due to mature technology, and has better competitiveness with a coupling power system formed by the new energy system, thereby being an important technical approach for improving the stability of the new energy system and improving the safety consumption of the new energy.
The traditional heavy gas turbine usually needs about 30 minutes from starting to full load, and cannot meet the requirement of quick response of a new energy system. Thus, as power systems develop demands, the demand for gas turbines for rapid response capability increases further. However, due to the influence of the heat capacities of the compressor and the turbine cylinders, a process is needed for heating; the rotor and the cylinder system are not matched in heat capacity, so that the deformation coordination of the rotor and the cylinder system is inconsistent, the centrifugal force caused by the increase of the rotation speed of the rotor system is instantly loaded, the influence of environmental factors is added, and the like, so that the starting speed of the gas turbine cannot exceed a certain limit value, otherwise, the gas turbine can be prevented from running safely due to static friction.
Therefore, the deformation coordination capacity of the cylinder and the rotor is improved, and the rotating and static clearance in the starting stage can be improved, so that the speed of the rotor system for improving the rotating speed is improved, and the quick response capacity of the gas turbine is improved. Thereby further improving the stability of the fuel gas-new energy power coupling system.
Disclosure of Invention
First, the technical problem to be solved
Based on the above problems, the present disclosure provides a gas turbine system and a power system based on the gas turbine system and a new energy power generation system, so as to alleviate at least one of the above technical problems in the prior art.
(II) technical scheme
In one aspect of the present disclosure, a gas turbine system is provided, comprising:
the compressor comprises a compressor cylinder and a compressor rotor, and is used for enabling working medium to flow between the compressor cylinder and the compressor rotor and be compressed;
the combustion chamber is connected with the working medium output end of the gas compressor and is used for receiving the working medium from the gas compressor and burning the working medium in the gas compressor to form a high-temperature high-pressure working medium;
The turbine comprises a turbine cylinder and a turbine rotor, is connected with the working medium output end of the combustion chamber and is used for receiving the high-temperature high-pressure working medium from the combustion chamber, and the high-temperature high-pressure working medium flows between the turbine cylinder and the turbine rotor, so that the temperature and the pressure of the high-temperature high-pressure working medium are reduced and then discharged through a turbine outlet;
And the heating device is arranged on the outer surfaces of the air compressor cylinder and the turbine cylinder and is used for keeping the average temperature of the air compressor cylinder and the turbine cylinder not lower than 50% of the average temperature of the air compressor cylinder and the turbine cylinder in a stable working state so as to improve the starting speed of the gas turbine system.
In an embodiment of the present disclosure, the compressor includes any one of an axial compressor, a centrifugal compressor, a mixed flow compressor, or a combination thereof.
In an embodiment of the disclosure, the combustion chamber comprises any one of a single tube combustion chamber, a circular tube combustion chamber and an annular combustion chamber, or the working medium is heated by a heat exchanger.
In the embodiment of the disclosure, the distributed controllable heating device arranged on the outer surface of the cylinder comprises any one of an electric heating device, a high-temperature gas heating device, a high-temperature liquid heating device and a liquid metal heating device.
In the embodiment of the disclosure, each heating mode includes any one of heat conduction, convection, radiation and induction heating.
In another aspect of the present disclosure, there is provided a coupled power system utilizing the gas turbine system as described in any one of the above and a new energy power generation system;
the new energy power generation system is provided with a new energy unit, a control system, a load and a power grid;
In the embodiment of the disclosure, the control system can receive the scheduling instruction and control the operation of the new energy unit by combining the load condition in the system.
In the embodiment of the disclosure, the new energy power generation system comprises any one of a wind power system, a hydropower system and a photovoltaic system.
In an embodiment of the disclosure, the new energy power generation system provides electrical energy to the heating device of the gas turbine system.
In the embodiment of the disclosure, the electric energy required by the heating device comprises any one of wind, light and water discarding of the new energy power generation system.
(III) beneficial effects
According to the technical scheme, the gas turbine system and the coupling power system based on the gas turbine system and the new energy power generation system have at least one or a part of the following beneficial effects:
(1) The response speed of the gas turbine is improved, and the starting time is shortened;
(2) The stability of the frequency and the phase of the new energy system is improved, and the impact of the new energy system on a power grid is reduced; and
(3) The stability of the new energy power generation system is improved, the wind abandoning, the light abandoning and the like are reduced, and the new energy consumption ratio is improved.
Drawings
FIG. 1 is a schematic view of a gas turbine system in an embodiment of the present disclosure;
FIG. 2 is a schematic view of section B-B of FIG. 1;
fig. 3 is a schematic structural diagram of a heating device according to an embodiment of the present disclosure.
FIG. 4 is a comparison of changes in the clearance between the gas turbine system and the turbine system before and after operation of the heating apparatus and a comparison of start-up times in an embodiment of the present disclosure.
FIG. 5 is a schematic diagram of a conventional new energy system; and
FIG. 6 is a schematic diagram of a coupling system of a gas turbine system and a new energy power generation system in an embodiment of the present disclosure;
[ in the drawings, the main reference numerals of the embodiments of the present disclosure ]
1. Air compressor
2. Combustion chamber
3. Turbine
4. Air cylinder of air compressor
5. Compressor rotor
6. Turbine cylinder
7. Turbine rotor
8. Heating device
9. Power supply
10. Power regulating device
11. Electric heating wire
12. Conducting wire
13. New energy unit
14. Gas turbine system with heating device
15. Control system
16. Load of
17. Electric network
Detailed Description
The utility model provides a gas turbine system and based on its and new forms of energy power generation system's coupling electric power system, the system improves gas turbine response speed, shortens the start-up time, improves new forms of energy system frequency and phase stability, reduces new forms of energy system's impact to the electric wire netting to further improve the stability of gas-new forms of energy electric power coupling system.
For the purposes of promoting an understanding of the principles and advantages of the disclosure, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same.
The present disclosure provides a gas turbine system, as shown in FIG. 1, comprising: a compressor 1 including a compressor cylinder 4 and a compressor rotor 5, for compressing a working medium flowing between the compressor cylinder 4 and the compressor rotor 5; the combustion chamber 2 is connected with the working medium output end of the gas compressor 1 and is used for receiving the working medium from the gas compressor 1 and combusting the working medium in the combustion chamber to form a high-temperature high-pressure working medium; the turbine 3 provided with a turbine cylinder 6 and a turbine rotor 7 is connected with the working medium output end of the combustion chamber 2 and is used for receiving the high-temperature and high-pressure working medium from the combustion chamber 2, and the high-temperature and high-pressure working medium flows between the turbine cylinder 6 and the turbine rotor 7, so that the temperature and the pressure of the high-temperature and high-pressure working medium are reduced and then discharged through an outlet of the turbine 3; and heating means 8 disposed on the outer surfaces of the compressor cylinder 4 and the turbine cylinder 6 for maintaining the average temperature of the compressor cylinder 4 and the turbine cylinder 6 not lower than 50% of the average temperature of the cylinders in a stable operation state thereof to increase the starting speed of the gas turbine system.
In the embodiment of the disclosure, as shown in fig. 1 and 2, the gas turbine system comprises a compressor 1, a combustion chamber 2, a turbine 3 and other main components, and when the gas turbine system works, working medium enters the gas turbine system from the compressor 1, flows between a compressor cylinder 4 and a compressor rotor 5 and is compressed; the high-pressure working medium enters the combustion chamber 2 after leaving the compressor 1, and is heated by the combustion of fuel or a heat exchanger, so that the temperature is further increased; the high-temperature high-pressure working medium enters the turbine 3, flows between the turbine cylinder 6 and the turbine rotor 7, and is discharged out of the gas turbine system through an outlet of the turbine 3 after the temperature and the pressure are reduced. After the gas engine stops working, in order to prevent the temperature of each component from being reduced too much, the heating device 8 is arranged on the surface of the cylinder to heat and preserve heat of the cylinder, so that the temperatures of different positions of the cylinder are ensured to be maintained at the appointed temperature level; thus, during start-up of the gas turbine system, the temperature of the cylinder is very close to the temperature of the steady state operation. The rotor can reach heat balance faster due to the small mass and the centrifugal force effect, and the rotor deforms faster. Although the deformation of the rotor is faster than that of the cylinder, the cylinder is preheated in advance, so that the friction between the rotor and the cylinder of the gas turbine system caused by the rapid start of the rotor can be avoided, the gas turbine system can be started in a small time, and the aim of rapid start is fulfilled.
In the embodiment of the present disclosure, as shown in fig. 3, the heating device 8 of the cylinder is composed of a power supply 9, a power adjusting device 10, an electric heating wire 11, a wire 12, and the like. After the gas turbine system stops working, the temperature of the cylinder is reduced, and the expansion deformation of the cylinder is reduced. By arranging the heating device 8 on the outer surface of the cylinder, arranging the heating device 8 according to the heat dissipation capacity of the cylinder at different positions of the gas turbine system, and adjusting the power adjusting device 10 according to the result of thermal analysis, the temperature of the cylinder is kept at a predetermined level, so that the temperature of the cylinder is very close to the temperature in a stable working state during the starting process of the gas turbine system. The rotor can reach heat balance faster due to the small mass and the centrifugal force effect.
In the embodiment of the present disclosure, as shown in fig. 4, when the heating device 8 is not operated, the gas turbine system is started for a time t1, and only the heat generated by the combustion chamber 2 is needed to make the gap between the cylinder and the rotor reach a stable state, so that the gas turbine system reaches a stable operation state because the rotor deforms faster than the cylinder, which is a slow process. When the heating device 8 works, the starting time of the gas turbine system is t2, and at the moment, although the deformation of the rotor is faster than the deformation of the cylinder, the cylinder is preheated in advance, so that the friction between the rotor and the cylinder caused by the rapid starting of the rotor can be avoided, the gas turbine system can reach the full load level in a small time, the starting time of the gas turbine system is shortened (from t1 to t 2), and the operation flexibility of the gas turbine system is improved.
In the embodiment of the disclosure, the compressor may be an axial compressor, a centrifugal compressor, a mixed flow compressor, or a combination compressor of the above types of compressors.
In the embodiment of the disclosure, the combustion chamber may be a single-tube combustion chamber, a circular tube combustion chamber, an annular combustion chamber, or a heat exchanger for heating the working medium.
In the embodiment of the disclosure, the distributed controllable heating device arranged on the outer surface of the cylinder can be an electric heating device, can be used for heating high-temperature gas, can be used for heating high-temperature liquid or liquid metal;
In the embodiment of the disclosure, each heating mode may be heat conduction, convection, radiation or induction heating.
The disclosure also provides a coupled power system comprising the gas turbine system and the new energy power generation system; the new energy power generation system is provided with a new energy unit 13, a control system 15, a load 16 and a power grid 17; the gas turbine system and the new energy power generation system work cooperatively.
In the embodiment of the present disclosure, as shown in fig. 5, the control system 15 receives a scheduling instruction and controls the new energy unit 13 to operate in combination with the load condition in the system. Generally, the traditional new energy system has poor internet surfing power quality due to higher volatility, limits the internet surfing hours, causes certain electric quantity waste, and threatens the safe and stable operation of the power grid 17.
In an embodiment of the present disclosure, as shown in fig. 6, a schematic diagram of a gas turbine and new energy coupling system using a heating device is shown. By adopting the gas turbine system 14 with the heating device, the characteristic of quick response of the gas turbine is fully utilized, so that the stability of a coupled power system can be greatly improved, the power quality of system output can be improved, and the level of the power generated by the new energy unit 13 can be improved.
In the embodiment of the disclosure, the new energy power generation system may be a wind power system, a hydropower system or a photovoltaic system.
In embodiments of the present disclosure, the new energy power generation system may provide electrical power to the heating device of the gas turbine system.
In the embodiment of the disclosure, the electric energy required by the heating device is the electric energy of wind abandoning, light abandoning or water abandoning of the new energy power generation system.
Thus, embodiments of the present disclosure have been described in detail with reference to the accompanying drawings. It should be noted that, in the drawings or the text of the specification, implementations not shown or described are all forms known to those of ordinary skill in the art, and not described in detail. Furthermore, the above definitions of the elements and methods are not limited to the specific structures, shapes or modes mentioned in the embodiments, and may be simply modified or replaced by those of ordinary skill in the art.
From the above description, one skilled in the art should clearly recognize that the present disclosure is directed to an electrical power system based on a gas turbine coupled with a new energy source.
In summary, the present disclosure provides an electric power system based on coupling of a gas turbine and new energy, where the system heats a compressor cylinder and a turbine cylinder through a heating device, so that the response speed of the gas turbine can be improved, and the starting time can be shortened; the new energy consumption ratio is improved; the rapid load tracking capability of the gas turbine is utilized, so that the stability of the frequency and the phase of the new energy system is improved, and the impact of the new energy system on a power grid is reduced; the stability of the new energy power generation system is greatly improved, the waste wind and the waste light are reduced, and the new energy consumption ratio is improved; thereby further improving the stability of the fuel gas-new energy power coupling system.
It should be further noted that, the directional terms mentioned in the embodiments, such as "upper", "lower", "front", "rear", "left", "right", etc., are only referring to the directions of the drawings, and are not intended to limit the scope of the present disclosure. Like elements are denoted by like or similar reference numerals throughout the drawings. Conventional structures or constructions will be omitted when they may cause confusion in understanding the present disclosure.
And the shapes and dimensions of the various elements in the drawings do not reflect actual sizes and proportions, but merely illustrate the contents of the embodiments of the present disclosure. In addition, in the claims, any reference signs placed between parentheses shall not be construed as limiting the claim.
Unless otherwise known, numerical parameters in this specification and the appended claims are approximations that may vary depending upon the desired properties sought to be obtained by the present disclosure. In particular, all numbers expressing quantities of ingredients, reaction conditions, and so forth used in the specification and claims are to be understood as being modified in all instances by the term "about". In general, the meaning of expression is meant to include a variation of + -10% in some embodiments, a variation of + -5% in some embodiments, a variation of + -1% in some embodiments, and a variation of + -0.5% in some embodiments by a particular amount.
Furthermore, the word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.
The use of ordinal numbers such as "first," "second," "third," etc., in the description and the claims to modify a corresponding element does not by itself connote any ordinal number of elements or the order of manufacturing or use of the ordinal numbers in a particular claim, merely for enabling an element having a particular name to be clearly distinguished from another element having the same name.
Furthermore, unless specifically described or steps must occur in sequence, the order of the above steps is not limited to the list above and may be changed or rearranged according to the desired design. In addition, the above embodiments may be mixed with each other or other embodiments based on design and reliability, i.e. the technical features of the different embodiments may be freely combined to form more embodiments.
Those skilled in the art will appreciate that the modules in the apparatus of the embodiments may be adaptively changed and disposed in one or more apparatuses different from the embodiments. The modules or units or components of the embodiments may be combined into one module or unit or component and, furthermore, they may be divided into a plurality of sub-modules or sub-units or sub-components. Any combination of all features disclosed in this specification (including any accompanying claims, abstract and drawings), and all of the processes or units of any method or apparatus so disclosed, may be used in combination, except insofar as at least some of such features and/or processes or units are mutually exclusive. Each feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Also, in the unit claims enumerating several means, several of these means may be embodied by one and the same item of hardware.
Similarly, it should be appreciated that in the above description of exemplary embodiments of the disclosure, various features of the disclosure are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various disclosed aspects. However, the disclosed method should not be construed as reflecting the intention that: i.e., the claimed disclosure requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this disclosure.
While the foregoing embodiments have been described in some detail for purposes of clarity of understanding, it will be understood that the foregoing embodiments are merely illustrative of the invention and are not intended to limit the invention, and that any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the present disclosure are intended to be included within the scope of the present disclosure.
Claims (10)
1. A gas turbine system, comprising:
the compressor comprises a compressor cylinder and a compressor rotor, and is used for enabling working medium to flow between the compressor cylinder and the compressor rotor and be compressed;
the combustion chamber is connected with the working medium output end of the gas compressor and is used for receiving the working medium from the gas compressor and burning the working medium in the gas compressor to form a high-temperature high-pressure working medium;
The turbine comprises a turbine cylinder and a turbine rotor, is connected with the working medium output end of the combustion chamber and is used for receiving the high-temperature high-pressure working medium from the combustion chamber, and the high-temperature high-pressure working medium flows between the turbine cylinder and the turbine rotor, so that the temperature and the pressure of the high-temperature high-pressure working medium are reduced and then discharged through a turbine outlet;
The heating device is arranged on the outer surfaces of the air compressor cylinder and the turbine cylinder and is used for keeping the average temperature of the air compressor cylinder and the turbine cylinder not lower than 50% of the average temperature of the air compressor cylinder and the turbine cylinder in a stable working state so as to improve the starting speed of a gas turbine system;
The heating device comprises a power supply, a power adjusting device, an electric heating wire and a wire, wherein the electric heating wire is arranged on the outer surfaces of the compressor cylinder and the turbine cylinder;
according to the different positions of the gas turbine system, the heating device is arranged according to the heat dissipation capacity of the gas compressor cylinder and the heat dissipation capacity of the turbine cylinder, and the power adjusting device is adjusted according to the result of thermal analysis, so that the temperature of the gas compressor cylinder and the temperature of the turbine cylinder are kept at a preset level, and the temperature of the gas compressor cylinder and the temperature of the turbine cylinder are close to the temperature in a stable working state in the starting process of the gas turbine system.
2. The gas turbine system of claim 1, wherein the compressor comprises any one of an axial compressor, a centrifugal compressor, a mixed flow compressor, or a combination thereof.
3. The gas turbine system of claim 1, wherein the combustion chamber comprises any one of a single tube combustion chamber, a can-annular combustion chamber, an annular combustion chamber, or a heat exchanger to heat a working fluid.
4. The gas turbine system of claim 1, wherein the distributed controllable heating means disposed on the cylinder outer surface comprises any one of an electrical heating means, a high temperature gas heating, a high temperature liquid heating, a liquid metal heating.
5. The gas turbine system of claim 4, wherein each heating mode of the heating device comprises any one of heat conduction, convection, radiation, and induction heating.
6. A coupled power system comprising the gas turbine system of any one of claims 1 to 5 and a new energy power generation system;
The new energy power generation system is provided with a new energy unit, a control system, a load and a power grid.
7. The coupled power system of claim 6, wherein the control system is operable to receive scheduling instructions and control operation of the new energy unit in combination with load conditions within the system.
8. The coupled power system of claim 6, wherein the new energy generation system comprises any one of a wind power system, a hydro-power system, a photovoltaic system.
9. The coupled power system of claim 6, wherein the new energy generation system provides electrical energy to the heating device of the gas turbine system.
10. The coupled power system of claim 9, wherein the electrical energy required by the heating device comprises electrical energy from any of a wind, a light, and a water reject of a new energy power generation system.
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| CN202011306586.6A CN112282937B (en) | 2020-11-19 | 2020-11-19 | Gas turbine system and coupling power system based on gas turbine system and new energy power generation system |
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| CN202011306586.6A CN112282937B (en) | 2020-11-19 | 2020-11-19 | Gas turbine system and coupling power system based on gas turbine system and new energy power generation system |
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| 欧阳安.电厂汽轮机故障诊断分析处理与技术改造手册 第4卷.银声音像出版社,2005,第1290-1294页. * |
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