CN113202581A - Combustion engine cooling system and cooling method - Google Patents
Combustion engine cooling system and cooling method Download PDFInfo
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- CN113202581A CN113202581A CN202110514308.8A CN202110514308A CN113202581A CN 113202581 A CN113202581 A CN 113202581A CN 202110514308 A CN202110514308 A CN 202110514308A CN 113202581 A CN113202581 A CN 113202581A
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- 238000001816 cooling Methods 0.000 title claims abstract description 120
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 31
- 239000007789 gas Substances 0.000 claims abstract description 52
- 239000002918 waste heat Substances 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims description 7
- 239000003638 chemical reducing agent Substances 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 239000002699 waste material Substances 0.000 abstract description 7
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 3
- 239000000112 cooling gas Substances 0.000 description 3
- 239000003546 flue gas Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K9/00—Plants characterised by condensers arranged or modified to co-operate with the engines
- F01K9/003—Plants characterised by condensers arranged or modified to co-operate with the engines condenser cooling circuits
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K11/00—Plants characterised by the engines being structurally combined with boilers or condensers
- F01K11/02—Plants characterised by the engines being structurally combined with boilers or condensers the engines being turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K13/00—General layout or general methods of operation of complete plants
- F01K13/006—Auxiliaries or details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K13/00—General layout or general methods of operation of complete plants
- F01K13/02—Controlling, e.g. stopping or starting
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K27/00—Plants for converting heat or fluid energy into mechanical energy, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a combustion engine cooling system and a cooling method, and the cooling system comprises a gas compressor, a combustion chamber, a turbine, a waste heat boiler, a first anti-surge pipeline, a second anti-surge pipeline, a first valve, a second valve, a third valve, a fourth valve and a cooling device, wherein the gas compressor, the combustion chamber and the turbine are sequentially connected to form a combustion engine, the turbine is connected with a preheating boiler, the gas compressor is also communicated with the turbine through the first anti-surge pipeline and the second anti-surge pipeline, the first anti-surge pipeline is provided with the first valve and the second valve, the second anti-surge pipeline is provided with the third valve and the fourth valve, and the output end of the cooling device is respectively communicated with the first anti-surge pipeline and the second anti-surge pipeline. The invention has the advantages that the system avoids the direct discharge of the anti-surge air exhaust of the compressor, and reduces the waste of air resources; the working efficiency of the gas turbine is improved; and the phenomenon that the temperature of the compressed air is too low and the temperature difference between the compressed air and the turbine is too large to damage the blades of the turbine is avoided.
Description
Technical Field
The invention relates to the technical field of combustion engine cooling, in particular to a combustion engine cooling system and a cooling method.
Background
Surging is a major operating accident of a gas turbine power station, and permanent equipment damage and huge economic loss are often caused. For example, chinese patent publication No. CN104832221A discloses a turbocharger surge prevention system, which avoids the surge phenomenon of a turbocharger.
At present, the gas turbine generally adopts a mode that the intermediate stage of a gas compressor extracts air and discharges the air into an exhaust diffusion section to prevent surge. In the operation process of the combustion engine, because the turbine blades are in a high-temperature working environment (a turbine inlet 1200-.
The surge-proof air exhaust of the air compressor is directly discharged into an exhaust diffusion section and then enters a waste heat boiler, so that high-quality air subjected to the steps of filtering, dehumidifying, compressing and the like is directly discharged, and resource waste is caused. And the air is extracted from the air compressor and cooled in the running process of the gas turbine, so that the disturbance to the air circuit is increased, the faults such as air circuit blockage are easily induced, the flow of the working medium in the air compressor is reduced, the working efficiency of the air compressor is reduced, and the working efficiency of the gas turbine is further reduced.
Disclosure of Invention
The invention aims to solve the technical problems of reducing air resource waste and improving the working efficiency of a gas turbine.
In order to solve the technical problems, the invention provides the following technical scheme:
a cooling system of a gas turbine comprises a gas compressor, a combustion chamber, a turbine, a waste heat boiler, a first anti-surge pipeline, a second anti-surge pipeline, a first valve, a second valve, a third valve, a fourth valve and a cooling device, wherein the gas compressor, the combustion chamber and the turbine are sequentially connected to form the gas turbine, one end, far away from the combustion chamber, of the turbine is connected with the preheating boiler, the gas compressor is further communicated with the turbine through the first anti-surge pipeline and the second anti-surge pipeline, the first valve and the second valve are arranged on the first anti-surge pipeline, the third valve and the fourth valve are arranged on the second anti-surge pipeline, and the output end of the cooling device is respectively communicated with the first anti-surge pipeline and the second anti-surge pipeline.
The cooling device comprises a compressed air system, an air storage tank, a cooling pipeline, a first cooling branch pipe, a second cooling branch pipe, a fifth valve, a sixth valve and a differential pressure gauge, the compressed air system is communicated with the air storage tank, one end of the cooling pipeline is communicated with the air storage tank, the other end of the cooling pipeline penetrates through the waste heat boiler and is divided into two parts which are divided into a first cooling branch pipe and a second cooling branch pipe, the first cooling branch pipe is communicated with a first surge-proof pipeline between the first valve and the second valve, the second cooling branch pipe is communicated with a second surge-proof pipeline between the third valve and the fourth valve, and the first cooling branch pipe and the second cooling branch pipe are respectively provided with a fifth valve and a sixth valve, and differential pressure gauges are respectively arranged between the first surge-proof pipeline close to the input end of the first valve and the first cooling branch pipe close to the input end of the fifth valve and between the second surge-proof pipeline close to the input end of the second valve and the second cooling branch pipe close to the input end of the sixth valve.
When the gas turbine is started, the system opens the first valve, the third valve, the fifth valve and the sixth valve and closes the second valve and the fourth valve, and recovers air discharged by the gas compressor through the gas storage tank, so that the direct discharge of the anti-surge air suction of the gas compressor is avoided, and the waste of air resources is reduced; when the gas turbine normally operates, the first valve and the third valve are closed, the fifth valve, the sixth valve, the second valve and the fourth valve are opened, compressed air is provided by the compressed air system to cool the turbine, original cooling gas extracted from the gas compressor is replaced, the working efficiency of the gas compressor is improved, and further the working efficiency of the gas turbine is improved. In addition, the high-temperature flue gas in the waste heat boiler is used for heating the compressed air in the cooling pipeline, so that the phenomenon that the temperature of the compressed air is too low and the temperature difference between the compressed air and the turbine is too large to cause damage to blades of the turbine is avoided.
Preferably, the compressed air system is in communication with the air reservoir via an air conduit.
Preferably, a seventh valve is arranged on the air pipeline.
Preferably, a diffuser is arranged on the cooling pipeline.
Preferably, the first cooling branch pipe and the second cooling branch pipe are provided with pressure reducers.
Preferably, the compressed air system is an air compression station.
Preferably, the present invention also provides a cooling method of a cooling system of a combustion engine, comprising the steps of:
the method comprises the following steps: starting the gas turbine, closing a compressed air system, opening a first valve, a third valve, a fifth valve and a sixth valve, and closing a second valve and a fourth valve, wherein air generated by the gas compressor enters a gas storage tank through a first anti-surge pipeline, a second anti-surge pipeline, a first cooling branch pipe, a second cooling branch pipe and a cooling pipeline for storage;
step two: after the gas turbine is started, opening a second valve and a fourth valve, closing a fifth valve and a sixth valve, and simultaneously opening a compressed air system to output compressed air into an air storage tank;
step three: observing the two differential pressure meters, closing the first valve and the third valve, opening the fifth valve and the sixth valve when signals of the two differential pressure meters are in equal timing, namely the pressure in the first anti-surge pipeline is smaller than the pressure in the first cooling branch pipe and the pressure in the second anti-surge pipeline is smaller than the pressure in the second cooling branch pipe, and cooling the turbine by compressed air generated by a compressed air system through the air storage tank, the cooling pipeline, the first cooling branch pipe, the second cooling branch pipe, the first anti-surge pipeline and the second anti-surge pipeline; meanwhile, the waste heat boiler heats the compressed air passing through the cooling pipeline;
step four: and stopping the gas turbine, closing the compressed air system, observing the two differential pressure meters, opening the first valve and the third valve and closing the fifth valve and the sixth valve when the signals of the two differential pressure meters are both negative, and cooling the turbine by air generated by the air compressor.
Compared with the prior art, the invention has the beneficial effects that:
when the gas turbine is started, the system opens the first valve, the third valve, the fifth valve and the sixth valve and closes the second valve and the fourth valve, and recovers air discharged by the gas compressor through the gas storage tank, so that the direct discharge of the anti-surge air suction of the gas compressor is avoided, and the waste of air resources is reduced; when the gas turbine normally operates, the first valve and the third valve are closed, the fifth valve, the sixth valve, the second valve and the fourth valve are opened, compressed air is provided by the compressed air system to cool the turbine, original cooling gas extracted from the gas compressor is replaced, the working efficiency of the gas compressor is improved, and further the working efficiency of the gas turbine is improved. In addition, the high-temperature flue gas in the waste heat boiler is used for heating the compressed air in the cooling pipeline, so that the phenomenon that the temperature of the compressed air is too low and the temperature difference between the compressed air and the turbine is too large to cause damage to blades of the turbine is avoided.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Detailed Description
In order to facilitate the understanding of the technical solutions of the present invention for those skilled in the art, the technical solutions of the present invention will be further described with reference to the drawings attached to the specification.
In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In this application, unless explicitly stated or limited otherwise, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
Referring to fig. 1, the embodiment discloses a cooling system of a combustion engine, which includes a compressor 1, a combustion chamber 2, a turbine 3, a waste heat boiler 4, a first anti-surge pipeline 5, a second anti-surge pipeline 6, a first valve 7, a second valve 8, a third valve 9, a fourth valve 10 and a cooling device 11, wherein the compressor 1, the combustion chamber 2 and the turbine 3 are sequentially connected to form the combustion engine, one end of the turbine 3, which is far away from the combustion chamber 2, is connected to the preheating boiler 4, the compressor 1 is further communicated with the turbine 3 through the first anti-surge pipeline 5 and the second anti-surge pipeline 6, the first anti-surge pipeline 5 is provided with the first valve 7 and the second valve 8, the second anti-surge pipeline 6 is provided with the third valve 9 and the fourth valve 10, and an output end of the cooling device 11 is respectively communicated with the first anti-surge pipeline 5 and the second anti-surge pipeline 6.
The cooling device 11 includes a compressed air system 1101, an air tank 1102, a cooling pipeline 1103, a first cooling branch 1104, a second cooling branch 1105, a fifth valve 1106, a sixth valve 1107 and a differential pressure gauge 1108, wherein the compressed air system 1101 is communicated with the air tank 1102, and in this embodiment, the compressed air system 1101 is an air pressure station. One end of the cooling pipeline 1103 is communicated with the air storage tank 1102, the other end of the cooling pipeline penetrates through the waste heat boiler 4 and is divided into two parts, the two parts are divided into a first cooling branch pipe 1104 and a second cooling branch pipe 1105, the first cooling branch pipe 1104 is communicated with a first anti-surge pipeline 5 between a first valve 7 and a second valve 8, the second cooling branch pipe 1105 is communicated with a second anti-surge pipeline 6 between a third valve 9 and a fourth valve 10, the first cooling branch pipe 1104 and the second cooling branch pipe 1105 are respectively provided with a fifth valve 1106 and a sixth valve 1107, and differential pressure gauges 1108 are respectively arranged between the first anti-surge pipeline 5 close to the input end of the first valve 7 and the first cooling branch pipe 1104 close to the input end of the fifth valve 1106 and between the second anti-surge pipeline 6 close to the input end of the second valve 8 and the second cooling branch pipe 1105 close to the input end of the sixth valve 1107.
When the gas turbine is started, the system opens the first valve 7, the third valve 9, the fifth valve 1106 and the sixth valve 1107 and closes the second valve 8 and the fourth valve 10, and recovers air exhausted by the gas compressor 1 through the gas storage tank 1102, so that the direct exhaust of the anti-surge air exhaust of the gas compressor 1 is avoided, and the waste of air resources is reduced; when the combustion engine normally operates, the first valve 7 and the third valve 9 are closed, the fifth valve 1106, the sixth valve 1107, the second valve 8 and the fourth valve 10 are opened, and compressed air is provided by the compressed air system 1101 to cool the turbine 3, so that the original cooling gas extracted from the compressor 1 is replaced, the working efficiency of the compressor is improved, and further the working efficiency of the combustion engine is improved. In addition, the high-temperature flue gas in the exhaust-heat boiler 4 is used for heating the compressed air in the cooling pipeline 1103, so that the phenomenon that the temperature of the compressed air is too low and the temperature difference between the compressed air and the turbine 3 is too large to damage the blades of the turbine 3 is avoided.
The compressed air system 1101 is communicated with the air storage tank 1102 through an air pipeline 12, and a seventh valve 13 is arranged on the air pipeline 12.
The cooling pipeline 1103 is provided with a diffuser 14, and when the maximum capacity of the gas storage tank 1102 is reached, the gas is discharged through the diffuser 14.
The embodiment also discloses a cooling method of the combustion engine cooling system, which comprises the following steps:
the method comprises the following steps: starting the gas turbine, closing the compressed air system 1101, opening the first valve 7, the third valve 9, the fifth valve 1106 and the sixth valve 1107, and closing the second valve 8 and the fourth valve 10, wherein air generated by the compressor 1 enters the air storage tank 1102 through the first anti-surge pipeline 5, the second anti-surge pipeline 6, the first cooling branch pipe 1104, the second cooling branch pipe 1105 and the cooling pipeline 1103 for storage, and the air discharged by the compressor 1 is recovered, so that the direct discharge of anti-surge bleed air of the compressor 1 is avoided, and the waste of air resources is reduced.
Step two: after the engine is started, the second valve 8 and the fourth valve 10 are opened, the fifth valve 1106 and the sixth valve 1107 are closed, and the compressed air system 1101 is opened to output compressed air to the air storage tank 1102.
Step three: observing the two differential pressure meters 1108, when the signals of the two differential pressure meters 1108 are in equal timing, that is, the pressure in the first surge-preventing pipeline 5 is smaller than the pressure in the first cooling branch pipe 1104, and the pressure in the second surge-preventing pipeline 6 is smaller than the pressure in the second cooling branch pipe 1105, closing the first valve 7 and the third valve 9, opening the fifth valve 1106 and the sixth valve 1107, and cooling the turbine 3 by the compressed air generated by the compressed air system 1101 through the air storage tank 1102, the cooling pipeline 1103, the first cooling branch pipe 1104, the second cooling branch pipe 1105, the first surge-preventing pipeline 5 and the second surge-preventing pipeline 6.
Meanwhile, in the process of outputting compressed air, the exhaust-heat boiler 4 heats the compressed air passing through the cooling pipeline 1103, so that the phenomenon that the temperature of the compressed air is too low and the temperature difference between the compressed air and the turbine 3 is too large to cause damage to blades of the turbine 3 is avoided.
Step four: the engine is shut down, the compressed air system 1101 is closed, the two differential pressure gauges 1108 are observed, when both signals of the two differential pressure gauges 1108 are negative, the first valve 7 and the third valve 9 are opened, the fifth valve 1106 and the sixth valve 1107 are closed, and the turbine 3 is cooled by air generated by the compressor 1.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.
The above-mentioned embodiments only represent embodiments of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the concept of the present invention, and these embodiments are all within the protection scope of the present invention.
Claims (7)
1. A combustion engine cooling system characterized by: the system comprises a gas compressor, a combustion chamber, a turbine, a waste heat boiler, a first anti-surge pipeline, a second anti-surge pipeline, a first valve, a second valve, a third valve, a fourth valve and a cooling device, wherein the gas compressor, the combustion chamber and the turbine are sequentially connected to form a gas turbine, one end, far away from the combustion chamber, of the turbine is connected with a preheating boiler, the gas compressor is also communicated with the turbine through the first anti-surge pipeline and the second anti-surge pipeline, the first valve and the second valve are arranged on the first anti-surge pipeline, the third valve and the fourth valve are arranged on the second anti-surge pipeline, and the output end of the cooling device is respectively communicated with the first anti-surge pipeline and the second anti-surge pipeline;
the cooling device comprises a compressed air system, an air storage tank, a cooling pipeline, a first cooling branch pipe, a second cooling branch pipe, a fifth valve, a sixth valve and a differential pressure gauge, the compressed air system is communicated with the air storage tank, one end of the cooling pipeline is communicated with the air storage tank, the other end of the cooling pipeline penetrates through the waste heat boiler and is divided into two parts which are divided into a first cooling branch pipe and a second cooling branch pipe, the first cooling branch pipe is communicated with a first surge-proof pipeline between the first valve and the second valve, the second cooling branch pipe is communicated with a second surge-proof pipeline between the third valve and the fourth valve, and the first cooling branch pipe and the second cooling branch pipe are respectively provided with a fifth valve and a sixth valve, and differential pressure gauges are respectively arranged between the first surge-proof pipeline close to the input end of the first valve and the first cooling branch pipe close to the input end of the fifth valve and between the second surge-proof pipeline close to the input end of the second valve and the second cooling branch pipe close to the input end of the sixth valve.
2. A combustion engine cooling system as set forth in claim 1, wherein: the compressed air system is communicated with the air storage tank through an air pipeline.
3. A combustion engine cooling system as set forth in claim 2, wherein: and a seventh valve is arranged on the air pipeline.
4. A combustion engine cooling system as set forth in claim 1, wherein: the cooling pipeline is provided with a diffuser.
5. A combustion engine cooling system as set forth in claim 1, wherein: and the first cooling branch pipe and the second cooling branch pipe are both provided with a pressure reducer.
6. A combustion engine cooling system as set forth in claim 1, wherein: the compressed air system is an air compression station.
7. A cooling method using a cooling system for a combustion engine according to any one of claims 1 to 6, characterized in that: the method comprises the following steps:
the method comprises the following steps: starting the gas turbine, closing a compressed air system, opening a first valve, a third valve, a fifth valve and a sixth valve, and closing a second valve and a fourth valve, wherein air generated by the gas compressor enters a gas storage tank through a first anti-surge pipeline, a second anti-surge pipeline, a first cooling branch pipe, a second cooling branch pipe and a cooling pipeline for storage;
step two: after the gas turbine is started, opening a second valve and a fourth valve, closing a fifth valve and a sixth valve, and simultaneously opening a compressed air system to output compressed air into an air storage tank;
step three: observing the two differential pressure meters, closing the first valve and the third valve, opening the fifth valve and the sixth valve when signals of the two differential pressure meters are in equal timing, namely the pressure in the first anti-surge pipeline is smaller than the pressure in the first cooling branch pipe and the pressure in the second anti-surge pipeline is smaller than the pressure in the second cooling branch pipe, and cooling the turbine by compressed air generated by a compressed air system through the air storage tank, the cooling pipeline, the first cooling branch pipe, the second cooling branch pipe, the first anti-surge pipeline and the second anti-surge pipeline; meanwhile, the waste heat boiler heats the compressed air passing through the cooling pipeline;
step four: and stopping the gas turbine, closing the compressed air system, observing the two differential pressure meters, opening the first valve and the third valve and closing the fifth valve and the sixth valve when the signals of the two differential pressure meters are both negative, and cooling the turbine by air generated by the air compressor.
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| CN202110514308.8A CN113202581A (en) | 2021-05-07 | 2021-05-07 | Combustion engine cooling system and cooling method |
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| CN202110514308.8A CN113202581A (en) | 2021-05-07 | 2021-05-07 | Combustion engine cooling system and cooling method |
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| JP2015094344A (en) * | 2013-11-14 | 2015-05-18 | 三菱日立パワーシステムズ株式会社 | Gas turbine cooling system, gas turbine plant with gas turbine cooling system, and method of cooling gas turbine high-temperature part |
| CN104088703A (en) * | 2014-06-24 | 2014-10-08 | 华北电力大学 | Compressed air energy storage-combined cycle integration system of intercooled preheating steam turbine |
| CN108216642A (en) * | 2017-12-06 | 2018-06-29 | 中国科学院工程热物理研究所 | A kind of Reheat-type cooling turbine unit system applied to aircraft pod |
| CN108257701A (en) * | 2017-12-11 | 2018-07-06 | 清华大学 | The power regulating method and device of high temperature gas cooled reactor coupling enclosed Bradenton cycle |
| CN110273759A (en) * | 2019-07-11 | 2019-09-24 | 中国华能集团清洁能源技术研究院有限公司 | Realize the IGCC heat and power system and method for fume afterheat deep exploitation and inlet gas cooling |
| CN215672379U (en) * | 2021-05-07 | 2022-01-28 | 中国大唐集团科学技术研究院有限公司华东电力试验研究院 | Combustion engine cooling system |
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