CN114992517A - Natural gas intake and afterburning system of aeroderivative gas turbine - Google Patents
Natural gas intake and afterburning system of aeroderivative gas turbine Download PDFInfo
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- CN114992517A CN114992517A CN202210710223.1A CN202210710223A CN114992517A CN 114992517 A CN114992517 A CN 114992517A CN 202210710223 A CN202210710223 A CN 202210710223A CN 114992517 A CN114992517 A CN 114992517A
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- manifold
- natural gas
- gas turbine
- main pipeline
- pressure monitoring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/02—Pipe-line systems for gases or vapours
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
-
- 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
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- 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
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D5/00—Protection or supervision of installations
- F17D5/005—Protection or supervision of installations of gas pipelines, e.g. alarm
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention provides a natural gas intake and afterburning system of an aeroderivative gas turbine, which comprises a main pipeline, wherein a manual ball valve, a flow safety valve, a Y-shaped filter, a main pipeline pressure monitoring module, a flow safety valve group, a temperature sensor and a natural gas collecting pipe are sequentially arranged on the main pipeline from an air inlet; the air outlet of the main pipeline is respectively communicated with the air inlets of a plurality of manifolds through a natural gas collecting pipe, and a manifold rectifier and a flow control valve are arranged at the air inlet of any manifold; the natural gas collecting pipe and any manifold are provided with pressure monitoring devices; the gas turbine section manifolds are distributed on the peripheral side of the gas turbine, and are respectively communicated with a plurality of fuel nozzles of the gas turbine; a plurality of combustion regulating valves are arranged on the combustion engine turbine section manifold. The invention helps to better regulate the natural gas flow, thereby helping natural gas to be fully combusted when entering the turbine of the combustion engine, helping to provide post-combustion natural gas during the idle running period of the combustion engine and preventing the engine from stalling.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a natural gas intake and afterburning system of an aeroderivative gas turbine.
Background
The aeroderivative gas turbine is a gas turbine which is obtained by modifying an aerojet engine and matching the aerojet engine with a power turbine to ensure that the rotating speed and the power of the aerojet engine meet the requirements of land power generation or mechanical dragging. Except for the power turbine, it is specially designed
The above components can all utilize the components of the original aircraft engine.
The prior Chinese patent with publication number CN214944580U discloses a fuel mixed gas inlet and ignition system of a gas turbine, which comprises a natural gas inlet module, a hydrogen inlet module, a gas mixing module and an ignition module; the natural gas inlet module mainly comprises a second stop valve, a natural gas filtering device, a first flowmeter, a heating device and a first regulating valve, wherein the outlet of the natural gas valve station is sequentially connected with the second stop valve, the natural gas filtering device, the first flowmeter, the heating device and the first regulating valve, and the outlet of the first regulating valve is connected to the inlet of the gas mixer.
The inventor considers that the common gas turbine fuel air inlet system has unreasonable effect when being applied to an aeroderivative gas turbine, and needs to design a natural gas air inlet and afterburning system suitable for the aeroderivative gas turbine.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a natural gas intake and afterburning system of an aeroderivative gas turbine.
The natural gas intake and afterburning system of the aeroderivative gas turbine comprises a main pipeline, wherein a manual ball valve, a flow safety valve, a Y-shaped filter, a main pipeline pressure monitoring module, a flow safety valve group, a temperature sensor and a natural gas collecting pipe are sequentially arranged on the main pipeline from an air inlet; the air outlet of the main pipeline is respectively communicated with the air inlets of a plurality of manifolds through the natural gas collecting pipe, and a manifold rectifier and a flow control valve are arranged at the air inlet of any manifold; the natural gas collecting pipe and any one manifold are provided with a pressure monitoring device; the manifold extends out of a gas turbine section manifold from the manifold to the gas turbine, the gas turbine section manifold is distributed on the peripheral side of the gas turbine, and the gas turbine section manifold is respectively communicated with a plurality of fuel nozzles of the gas turbine; and a plurality of combustion regulating valves are arranged on the combustion engine turbine section manifold.
Preferably, the flow safety valve, the main pipeline pressure monitoring module and the pressure monitoring device are respectively connected with a control device, and the main pipeline pressure monitoring module and the temperature sensor are respectively connected with an alarm device.
Preferably, a first external pipeline is communicated with the main pipeline between the flow safety valve and the Y-shaped filter, a remote exhaust valve is arranged on the first external pipeline, and an air outlet of the first external pipeline is communicated with a safe region.
Preferably, the main pipeline pressure monitoring module comprises a first main pipeline pressure monitoring module and a second main pipeline pressure monitoring module.
Preferably, a second external communication pipeline is communicated with the main pipeline between the first main pipeline pressure monitoring module and the second main pipeline pressure monitoring module, a liquid level control valve is arranged on the second external communication pipeline, and an air outlet of the second external communication pipeline is communicated with the safe region.
Preferably, the main pipeline positioned in the flow safety valve group is communicated with a third external pipeline, and an air outlet of the third external pipeline is communicated with the safety region.
Preferably, the manifolds include manifold a, manifold B, manifold C, manifold D, and manifold E; the manifold rectifiers comprise a manifold A rectifier, a manifold B rectifier, a manifold C rectifier, a manifold D rectifier and a manifold E rectifier corresponding to the manifold; the flow control valves comprise a manifold A flow control valve, a manifold B flow control valve, a manifold C flow control valve, a manifold D flow control valve and a manifold E flow control valve which correspond to the manifolds.
Preferably, a first orifice plate is arranged between the manifold B and the manifold C, and a second orifice plate is arranged between the manifold C and the manifold D.
Preferably, the natural gas header expansion flanges are arranged on two sides of the natural gas header.
Preferably, the temperature sensor comprises two temperature sensors.
Compared with the prior art, the invention has the following beneficial effects:
1. the natural gas flow control device is beneficial to better regulating the natural gas flow by arranging the plurality of flow safety valves, the rectifier, the flow control valve and the combustion regulating valve, thereby being beneficial to fully combusting the natural gas when the natural gas enters a turbine of the combustion engine, being beneficial to providing afterburning natural gas in the idle running stage of the combustion engine and preventing the engine from flameout.
2. The natural gas is distributed to the manifold through the natural gas header, and the manifold is arranged on the periphery of the turbine of the combustion engine through the manifold of the turbine section of the combustion engine, so that the flow of the natural gas is distributed, and the adjustment and control of the flow of the natural gas are facilitated.
3. According to the invention, the plurality of external pipelines, the plurality of temperature sensors and the plurality of pressure monitoring devices are arranged, so that the coping efficiency in the case of a fault is improved, the service life of the system is prolonged, and the working efficiency is improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic overall structure diagram of a main pipeline of a natural gas intake and afterburning system of a gas turbine mainly embodying the present invention;
FIG. 2 is a schematic structural diagram of the connection of the natural gas inlet and afterburning system manifold and the turbine of the aero-modified gas turbine mainly embodying the invention.
Shown in the figure:
manual ball valve 1, flow safety valve 2 and remote exhaust valve 3
Y-shaped filter 4, first main pipeline pressure monitoring module 5, liquid level control valve 6
Manifold B rectifier 13 manifold C rectifier 14 manifold D rectifier 15
Manifold E rectifier 16 manifold A flow control valve 17 manifold B flow control valve 18
Manifold C flow control valve 19 manifold D flow control valve 20 manifold E flow control valve 21
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the natural gas intake and afterburning system of the aero-derivative gas turbine provided by the invention comprises a main pipeline, wherein a manual ball valve 1, a flow safety valve 2, a Y-shaped filter 4, a main pipeline pressure monitoring module, a flow safety valve group 8, a temperature sensor 9 and a natural gas header 10 are sequentially arranged on the main pipeline from an air inlet; the air outlet of the main pipeline is respectively communicated with the air inlets of a plurality of manifolds through a natural gas header 10, and a manifold rectifier and a flow control valve are arranged at the air inlet of any manifold; the natural gas header 10 and any manifold are provided with a pressure monitoring device 24; the manifold extends out of a combustion engine turbine section manifold 38 from the manifold to the combustion engine turbine, the combustion engine turbine section manifold 38 is distributed on the peripheral side of the combustion engine turbine, and the combustion engine turbine section manifold 38 is respectively communicated with a plurality of fuel nozzles of the combustion engine turbine; a plurality of combustion trim valves are provided in the engine turbine section manifold 38. The flow safety valve 2, the main pipeline pressure monitoring module and the pressure monitoring device 24 are respectively connected with the control device, and the main pipeline pressure monitoring module and the temperature sensor 9 are respectively connected with the alarm device.
This application is through adjusting boat modification gas turbine natural gas air intake system, realizes that the natural gas can fully burn when getting into the combustion engine turbine, and then improves and exert oneself. Meanwhile, after-burning natural gas is provided in the idle running stage of the combustion engine, so that the engine is prevented from being flamed out.
The main pipeline is sequentially provided with a manual ball valve 1, a flow safety valve 2, a Y-shaped filter 4, a main pipeline pressure monitoring module, a flow safety valve group 8, a temperature sensor 9 and a natural gas collecting pipe 10 from an air inlet. The manual ball valve 1 is used for manually controlling the opening and closing of the main pipeline. The flow safety valve 2 remotely controls the opening and closing of the main pipeline through transmission signals. The Y-shaped filter 4 is used for filtering impurities in the natural gas.
A main pipeline between the flow safety valve 2 and the Y-shaped filter 4 is communicated with a first external pipeline, a remote exhaust valve 3 is arranged on the first external pipeline, and an air outlet of the first external pipeline is communicated with a safe area. The remote vent valve 3 drops natural gas to a safe area in a state of failure and the main pipeline is still 'on'.
The main pipeline pressure monitoring module is used for monitoring the gas pressure of the main pipeline and transmitting an alarm and a unit shutdown signal through remote control. The main pipeline pressure monitoring module comprises a first main pipeline pressure monitoring module 5 and a second main pipeline pressure monitoring module 7 which are mutually standby.
The main pipeline between the first main pipeline pressure monitoring module 5 and the second main pipeline pressure monitoring module 7 is communicated with a second external communicating pipeline, a liquid level control valve 6 is arranged on the second external communicating pipeline, and an air outlet of the second external communicating pipeline is communicated with a safe area. Under the condition that the first main pipeline pressure monitoring module 5 fails, the liquid level control valve 6 discharges natural gas to a safe area through liquid level control.
The main pipeline positioned in the flow safety valve group 8 is communicated with a third external pipeline, and an air outlet of the third external pipeline is communicated with a safety region. The flow safety valve group 8 is used for regulating the gas pressure in the main pipeline and discharging partial natural gas to a safety area under the condition of pipeline purging and other abnormal conditions.
The temperature sensor 9 is used for monitoring the temperature of natural gas in the pipeline and sending alarm and stop signals when the temperature is abnormal, and the temperature sensor 9 comprises two temperature sensors which are mutually standby.
The air outlet of the main pipeline is respectively communicated with the air inlets of a plurality of manifolds through a natural gas header 10, and a manifold rectifier and a flow control valve are arranged at the air inlet of any manifold. The natural gas header 10 distributes natural gas in the main pipeline conduit into the manifold conduits. And natural gas manifold extension flanges 11 are arranged on two sides of the natural gas manifold 10, and the natural gas manifold extension flanges 11 are extension interfaces of the natural gas manifold 10.
In the present application, the manifold includes 5 manifolds, namely, a manifold a, a manifold B, a manifold C, a manifold D, and a manifold E. The manifold rectifier includes a manifold a rectifier 12, a manifold B rectifier 13, a manifold C rectifier 14, a manifold D rectifier 15, and a manifold E rectifier 16 corresponding to the manifolds, the manifold rectifiers being used for gas rectification. The flow control valves include a manifold a flow control valve 17, a manifold B flow control valve 18, a manifold C flow control valve 19, a manifold D flow control valve 20, and a manifold E flow control valve 21 corresponding to the manifolds, which are used to regulate and meter the natural gas flow rate of the manifolds.
A first orifice plate 22 is disposed between manifold B and manifold C, and a second orifice plate 23 is disposed between manifold C and manifold D. The first orifice 22 and the second orifice 23 are used for pressure equalization.
The natural gas manifold 10 and any manifold are provided with pressure monitoring devices 24. The pressure monitoring device 24 has the functions of remote transmission of pressure signals and local marking and displaying and is used for monitoring the pressure of the natural gas in the natural gas collecting pipes 10 and the natural gas in the natural gas collecting pipes 5, and two monitoring points of each pipeline are mutually standby.
The manifold extends out of a combustion engine turbine section manifold 38 from the manifold to the combustion engine turbine, the combustion engine turbine section manifold 38 is distributed on the peripheral side of the combustion engine turbine, and the combustion engine turbine section manifold 38 is respectively communicated with a plurality of fuel nozzles of the combustion engine turbine; a plurality of combustion adjustment valves 25 are provided in the engine turbo stage manifold 38.
The gas turbine section manifold 38 is distributed around the gas turbine and is connected with 15 two-cup fuel nozzles and 15 three-cup fuel nozzles in the gas turbine. This application can provide suitable amount of natural gas for 75 fuel nozzle when engine combustion adjustment, can reduce the emission after the abundant burning, increases output. The total number of the combustion regulating valves 25 is 13, and the combustion regulating valves have a flow regulating function, further accurately control the flow of natural gas in the manifold, and realize the accurate control of the flow of the natural gas before the natural gas enters a turbine nozzle of the combustion engine.
Natural gas enters a main pipeline from an air inlet, the manual ball valve 1 is opened manually to allow the natural gas to flow, and the flow safety valve 2 is opened through remote control of transmission signals to allow the natural gas to flow to the Y-shaped filter 4. If the fault occurs, the natural gas is discharged to a safe area through the first external pipeline and the remote exhaust valve 3. The natural gas flows to the first main pipeline pressure monitoring module 5 and the second main pipeline pressure monitoring module 7 through the Y-shaped filter 4, and under the condition that the first main pipeline pressure monitoring module 5 fails, the natural gas is discharged to a safe area through the liquid level control valve 6 through liquid level control. The natural gas flows to the flow safety valve group 8 through the main pipeline, and the flow safety valve group 8 is used for adjusting the gas pressure in the main pipeline and discharging part of the natural gas to a safety region under the conditions of pipeline purging and other abnormal conditions. The natural gas flows to the temperature sensor 9 through the main pipeline, and the temperature sensor 9 is used for monitoring the temperature of the natural gas in the pipeline and sending alarm and stop signals when the temperature is abnormal. The natural gas in the main pipeline is then distributed into the manifold pipes by means of the natural gas headers 10. The natural gas is passed through a manifold rectifier and flow control valve to a turbine section manifold 38 of the engine, regulated by a combustion trim valve 25 and passed to a plurality of fuel nozzles of the engine turbine.
This application is through adopting the flow of adjusting the natural gas when getting into the combustion engine when thorough, guarantees the abundant burning of fuel, reduces and discharges, improves and exert oneself. Simultaneously, after-burning natural gas is provided for the gas turbine during maintenance and idling, and the engine is prevented from being flamed out.
Principle of operation
Natural gas enters a main pipeline from an air inlet, the manual ball valve 1 is opened manually to allow the natural gas to flow, and the flow safety valve 2 is opened through remote control of transmission signals to allow the natural gas to flow to the Y-shaped filter 4. If the fault occurs, the natural gas is discharged to a safe area through the first external pipeline and the remote exhaust valve 3. The natural gas flows to the first main pipeline pressure monitoring module 5 and the second main pipeline pressure monitoring module 7 through the Y-shaped filter 4, and under the condition that the first main pipeline pressure monitoring module 5 is invalid, the liquid level control valve 6 discharges the natural gas to a safe area through liquid level control. The natural gas flows to the flow safety valve group 8 through the main pipeline, and the flow safety valve group 8 is used for adjusting the gas pressure in the main pipeline and discharging part of the natural gas to a safety region under the conditions of pipeline purging and other abnormal conditions. The natural gas flows to the temperature sensor 9 through the main pipeline, and the temperature sensor 9 is used for monitoring the temperature of the natural gas in the pipeline and sending alarm and stop signals when the temperature is abnormal. The natural gas in the main pipeline is then distributed into the manifold pipes by means of the natural gas headers 10. The natural gas is passed through a manifold rectifier and flow control valve to a turbine section manifold 38 of the engine, regulated by a combustion trim valve 25 and passed to a plurality of fuel nozzles of the engine turbine.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description has described specific embodiments of the present invention. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. The natural gas intake and afterburning system of the aeroderivative gas turbine is characterized by comprising a main pipeline, wherein a manual ball valve (1), a flow safety valve (2), a Y-shaped filter (4), a main pipeline pressure monitoring module, a flow safety valve group (8), a temperature sensor (9) and a natural gas collecting pipe (10) are sequentially arranged on the main pipeline from an air inlet;
the air outlet of the main pipeline is respectively communicated with the air inlets of a plurality of manifolds through the natural gas collecting pipe (10), and a manifold rectifier and a flow control valve are arranged at the air inlet of any manifold;
a pressure monitoring device (24) is arranged on each of the natural gas header (10) and any manifold;
the manifold extends out of a gas turbine section manifold (38) from the manifold to a gas turbine, the gas turbine section manifold (38) is distributed on the peripheral side of the gas turbine, and the gas turbine section manifold (38) is respectively communicated with a plurality of fuel nozzles of the gas turbine;
a plurality of combustion regulating valves (25) are arranged on the combustion engine turbine section manifold (38).
2. Aeroderivative gas turbine natural gas admission and afterburning system according to claim 1, wherein the flow safety valve (2), the main line pressure monitoring module and the pressure monitoring device (24) are each connected to a control device, and the main line pressure monitoring module and the temperature sensor (9) are each connected to an alarm device.
3. Aeroderivative gas turbine natural gas inlet and post-combustion system according to claim 1, wherein the main pipeline between the flow safety valve (2) and the Y-type filter (4) is communicated with a first external pipeline, a remote exhaust valve (3) is arranged on the first external pipeline, and an air outlet of the first external pipeline is communicated with a safe area.
4. Aeroderivative gas turbine natural gas intake and post-combustion system according to claim 1, wherein said main line pressure monitoring module comprises a first main line pressure monitoring module (5) and a second main line pressure monitoring module (7).
5. The aeroderivative natural gas intake and afterburning system of claim 4, wherein a second external pipeline is communicated with the main pipeline between the first main pipeline pressure monitoring module (5) and the second main pipeline pressure monitoring module (7), a liquid level control valve (6) is arranged on the second external pipeline, and an air outlet of the second external pipeline is communicated with a safe area.
6. Aeroderivative gas turbine natural gas intake and post-combustion system according to claim 1, wherein the main pipeline in the flow safety valve set (8) is communicated with a third external pipeline, and the outlet of the third external pipeline is communicated with a safety zone.
7. The aero-retrofit gas turbine natural gas intake and post-combustion system of claim 1 wherein said manifold comprises manifold a, manifold B, manifold C, manifold D, and manifold E;
the manifold rectifier comprises a manifold A rectifier (12), a manifold B rectifier (13), a manifold C rectifier (14), a manifold D rectifier (15) and a manifold E rectifier (16) corresponding to the manifold;
the flow control valves comprise a manifold A flow control valve (17), a manifold B flow control valve (18), a manifold C flow control valve (19), a manifold D flow control valve (20) and a manifold E flow control valve (21) which correspond to the manifolds.
8. Aeroderivative gas turbine natural gas inlet and post-combustion system according to claim 7, wherein a first orifice plate (22) is arranged between said manifold B and said manifold C, and a second orifice plate (23) is arranged between said manifold C and said manifold D.
9. Aeroderivative gas turbine natural gas inlet and post-combustion system according to claim 1, wherein said natural gas manifold (10) is provided with natural gas manifold extension flanges (11) on both sides.
10. Aeroderivative gas turbine natural gas inlet and post combustion system according to claim 1, wherein said temperature sensor (9) comprises two temperature sensors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210710223.1A CN114992517A (en) | 2022-06-22 | 2022-06-22 | Natural gas intake and afterburning system of aeroderivative gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210710223.1A CN114992517A (en) | 2022-06-22 | 2022-06-22 | Natural gas intake and afterburning system of aeroderivative gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN114992517A true CN114992517A (en) | 2022-09-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210710223.1A Pending CN114992517A (en) | 2022-06-22 | 2022-06-22 | Natural gas intake and afterburning system of aeroderivative gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117091125A (en) * | 2023-08-22 | 2023-11-21 | 青岛凯能环保科技股份有限公司 | Integrated device for afterburning of tail exhaust-heat boiler of gas turbine |
-
2022
- 2022-06-22 CN CN202210710223.1A patent/CN114992517A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117091125A (en) * | 2023-08-22 | 2023-11-21 | 青岛凯能环保科技股份有限公司 | Integrated device for afterburning of tail exhaust-heat boiler of gas turbine |
| CN117091125B (en) * | 2023-08-22 | 2024-03-22 | 青岛凯能环保科技股份有限公司 | Integrated device for afterburning of tail exhaust-heat boiler of gas turbine |
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