CN115059546B - Solid fuel gas turbine with single-barrel combustion chamber - Google Patents
Solid fuel gas turbine with single-barrel combustion chamber Download PDFInfo
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- CN115059546B CN115059546B CN202210775764.2A CN202210775764A CN115059546B CN 115059546 B CN115059546 B CN 115059546B CN 202210775764 A CN202210775764 A CN 202210775764A CN 115059546 B CN115059546 B CN 115059546B
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- gas turbine
- combustion chamber
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 225
- 239000007789 gas Substances 0.000 title claims abstract description 113
- 239000004449 solid propellant Substances 0.000 title claims abstract description 43
- 239000007788 liquid Substances 0.000 claims description 59
- 238000001816 cooling Methods 0.000 claims description 36
- 238000002347 injection Methods 0.000 claims description 27
- 239000007924 injection Substances 0.000 claims description 27
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 25
- 239000000779 smoke Substances 0.000 claims description 19
- 239000002828 fuel tank Substances 0.000 claims description 7
- 239000002826 coolant Substances 0.000 claims description 6
- 229920006395 saturated elastomer Polymers 0.000 claims description 4
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims 1
- 235000017491 Bambusa tulda Nutrition 0.000 claims 1
- 241001330002 Bambuseae Species 0.000 claims 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims 1
- 239000011425 bamboo Substances 0.000 claims 1
- 239000011148 porous material Substances 0.000 claims 1
- 239000000446 fuel Substances 0.000 description 26
- 238000010438 heat treatment Methods 0.000 description 17
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 15
- 239000003546 flue gas Substances 0.000 description 12
- 239000007787 solid Substances 0.000 description 11
- 238000004891 communication Methods 0.000 description 10
- 239000000463 material Substances 0.000 description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 6
- 239000003245 coal Substances 0.000 description 5
- 239000000428 dust Substances 0.000 description 5
- 229910052739 hydrogen Inorganic materials 0.000 description 4
- 239000001257 hydrogen Substances 0.000 description 4
- 229910002091 carbon monoxide Inorganic materials 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910000990 Ni alloy Inorganic materials 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000007795 chemical reaction product Substances 0.000 description 2
- -1 however Substances 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 239000003250 coal slurry Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 239000012495 reaction gas Substances 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 239000010802 sludge Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000010902 straw Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/26—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension
- F02C3/28—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension using a separate gas producer for gasifying the fuel before combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R5/00—Continuous combustion chambers using solid or pulverulent fuel
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a solid fuel gas turbine with a single-cylinder combustion chamber, which comprises a gas compressor, a turbine and a combustion chamber, wherein the gas compressor and the turbine are sequentially arranged on a rotating shaft in the axial direction, the combustion chamber is connected with the gas outlet end of the gas compressor, the combustion chamber is a single-cylinder combustion chamber, the combustion chamber is arranged at one side of the rotating shaft and comprises a first combustion part, a second combustion part and a gas chamber, the second combustion part is arranged below the first combustion part, the gas chamber surrounds the first combustion part, the gas chamber is provided with a combustion chamber gas inlet connected with the gas outlet end of the gas compressor, the first combustion part is provided with a combustion chamber gas outlet connected with the gas inlet end of the turbine, the combustion chamber gas inlet and the combustion chamber gas outlet are arranged in the same direction, and the second combustion part is connected with a stock bin. The gas turbine disclosed by the invention can directly utilize the solid fuel to operate so as to reduce the operation cost or increase the region application range of the gas turbine.
Description
Technical Field
The invention belongs to the field of heat engines, and particularly relates to a solid fuel gas turbine with a single-barrel combustion chamber.
Background
The gas turbine takes continuously flowing gas as working medium to drive the impeller to rotate at high speed, and converts the energy of fuel into useful work, thus being a rotary impeller type heat engine. The device mainly comprises three parts of a gas compressor, a combustion chamber and a turbine: the air compressor sucks air from the external atmospheric environment, compresses the air to boost the pressure, and simultaneously the temperature of the air is correspondingly increased; compressed air is sent to a combustion chamber under pressure to be mixed with injected fuel for combustion to generate high-temperature and high-pressure gas; then the gas enters the turbine to expand and do work, the turbine is pushed to drive the gas compressor and the external load rotor to rotate together at high speed, and the chemical energy of the gas or liquid fuel is partially converted into mechanical work.
Currently, gas turbines are typically liquid or gaseous fuels, however, liquid or gaseous fuels are costly and solid fuels are relatively low cost, but it is often difficult for typical gas turbines to directly utilize solid fuels.
Disclosure of Invention
The embodiment of the invention provides a solid fuel gas turbine with a single-barrel combustion chamber, which can directly utilize solid fuel to operate so as to reduce the operation cost or increase the region application range of the gas turbine.
The invention provides a solid fuel gas turbine with a single-cylinder combustion chamber, which comprises a gas compressor, a turbine and a combustion chamber, wherein the gas compressor and the turbine are sequentially arranged on a rotating shaft in the axial direction, the combustion chamber is connected with the gas outlet end of the gas compressor, the combustion chamber is a single-cylinder combustion chamber, the combustion chamber is arranged at one side of the rotating shaft and comprises a first combustion part, a second combustion part and a gas chamber, the second combustion part is arranged below the first combustion part, the gas chamber surrounds the first combustion part, the gas chamber is provided with a combustion chamber gas inlet connected with the gas outlet end of the gas compressor, the first combustion part is provided with a combustion chamber gas outlet connected with the gas inlet end of the turbine, and the combustion chamber gas inlet and the combustion chamber gas outlet are arranged in the same direction; the second combustion part is connected with a storage bin which is used for containing solid fuel.
According to one aspect of an embodiment of the invention, at least part of the plenum is located between the first combustion section and the second combustion section, the second combustion section comprising a flue gas plate and being in communication with the plenum through the flue gas plate.
According to an aspect of the embodiment of the invention, the heat regenerator is further comprised, an exhaust end of the turbine is connected with an inlet of a first flow channel of the heat regenerator, an exhaust end of the compressor is connected with an inlet of a second flow channel of the heat regenerator, an outlet of the second flow channel is connected with an inlet of the air chamber, and the gas in the first flow channel and the gas in the second flow channel exchange heat in the heat regenerator.
According to an aspect of an embodiment of the present invention, a combustion chamber includes a first casing, a second casing, and a third casing, the second casing surrounding a first combustion portion forming a single cylinder and having an opening at one axial end corresponding to an exhaust port of the combustion chamber; the first housing at least partially encloses the second housing and defines a plenum therewith; the second shell is provided with a through hole for communicating the air chamber with the first combustion part; the third shell is connected with the first shell and extends to form a second combustion part; the flue gas plate is arranged on the third shell close to the second shell.
According to one aspect of an embodiment of the invention, the bin comprises a chamber, a feed port, a delivery device, a pressurization port, and a first liquid injection port, wherein the chamber contains a solid fuel; the feed inlet is positioned at the upper side of the cabin and is provided with an openable airtight door; the conveying device is positioned at the lower side of the cabin and is connected with the input port of the second combustion part through the output port; the pressurizing port is connected with the air source and is used for introducing pressurized air into the cabin; the first liquid injection port is connected with the water supply device and injects liquid containing solid fuel into the cabin.
According to an aspect of an embodiment of the invention, a cooling portion is arranged between the second combustion portion and the first combustion portion, the cooling portion being connected to the first combustion portion and being at least partially located on a side of the first combustion portion facing the second combustion portion.
According to an aspect of the embodiment of the present invention, the cooling portion completely surrounds the first combustion portion in the circumferential direction, or the cooling portion surrounds half of the first combustion portion in the circumferential direction; and the cooling part is provided with a cooling channel, a gaseous or liquid cooling medium is arranged in the cooling channel, and/or the cooling channel is arranged to flow through the gaseous or liquid cooling medium.
According to an aspect of the embodiment of the present invention, the second combustion section further includes: the second liquid injection port extends below the smoke plate and is connected with the water supply device, and liquid is injected into the combustion area of the second combustion part; and/or a third liquid injection port is arranged adjacent to the input port and connected with the water supply device, and is used for injecting liquid containing solid fuel.
According to an aspect of the embodiment of the present invention, when the second combustion section includes the second liquid injection ports, the number of the second liquid injection ports is plural, the plural second liquid injection ports are arranged around the combustion area of the second combustion section, and the liquid injected through the second liquid injection ports is saturated water.
According to an aspect of an embodiment of the invention, the gas turbine further comprises a fuel tank, the first combustion section being provided with a nozzle, the nozzle being connected to the fuel tank.
According to the solid fuel gas turbine with the single-barrel combustion chamber, through the combustion chamber comprising the first combustion part, the second combustion part and the air chamber and the storage bin connected with the second combustion part and used for containing solid fuel, the gas turbine can directly operate by using the solid fuel, so that the operating cost is reduced or the region application range of the gas turbine is increased. And the air chamber is at least partially arranged around the first combustion part, the second combustion part is arranged below the first combustion part, so that high-temperature flue gas generated by the combustion of the solid fuel in the second combustion part enters the air chamber and more uniformly enters the first combustion part through the air chamber to provide high-temperature combustion gas or perform secondary combustion, the combustion stability of the first combustion part can be ensured, and the working effect of the gas turbine taking the solid fuel as an energy source is further ensured. Moreover, the gas turbine with the single-barrel combustion chamber is compact in structure, can be arranged on mobile equipment, can be reformed by using a conventional gas turbine, and further reduces cost.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading the following detailed description of non-limiting embodiments, taken in conjunction with the accompanying drawings, in which like reference characters designate the same or similar features, and in which the figures are not to scale.
Fig. 1 shows a schematic view of a gas turbine according to the invention.
Fig. 2 shows a schematic structural view of the combustion chamber in fig. 1.
Fig. 3 shows a schematic structural view of the smoke plate of fig. 2.
Fig. 4 shows a schematic structural view of a single-can combustor.
Fig. 5 shows a schematic structural view of the silo of fig. 1.
FIG. 6 shows a schematic view of a gas turbine engine having a second and third ports.
Fig. 7 shows a schematic structural view of the combustion chamber in fig. 6.
FIG. 8 shows a schematic structural view of a gas turbine with a cooling section.
FIG. 9 shows a schematic structural view of one embodiment of the cooling portion of FIG. 8.
Fig. 10 shows a schematic structural view of another embodiment of the cooling part in fig. 8.
Fig. 11 shows a schematic structural view of still another embodiment of the cooling part in fig. 8.
Fig. 12 shows a schematic view of a gas turbine with a heating device.
FIG. 13 illustrates a schematic structural view of an embodiment of the combustion chamber of FIG. 12.
FIG. 14 shows a schematic structural view of another embodiment of the combustion chamber of FIG. 12.
FIG. 15 shows a schematic structural view of an embodiment of the heating device of FIG. 13.
Fig. 16 shows a schematic structural view of another embodiment of the heating device in fig. 13.
Fig. 17 shows a schematic structural view of still another embodiment of the heating device in fig. 13.
Fig. 18 shows a schematic structural view of a further embodiment of the heating device in fig. 13.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings and the detailed embodiments.
At present, the fuel generally has liquid, gas and solid, the solid is widely distributed, the existing forms are various, and the acquisition (exploitation) cost is low, so that the price is low, for example, coal (powder), straw, even kitchen garbage, sludge, biogas residue and other waste materials have certain heat value, and the fuel can be used as the solid fuel and is subjected to harmless treatment. However, these solid fuels are not readily available for direct use and require secondary treatments such as refining and conversion, which increases costs, while these solid fuels are widely distributed but are quite distributed and transportation concentrations result in additional transportation and storage costs.
Therefore, there is a need for a solid fuel utilization device that can convert solid fuel into heat energy, kinetic energy, and/or electrical energy that can be directly utilized, and that can be utilized locally in an area where the solid fuel is distributed.
To achieve the above object, as shown in fig. 1, fig. 1 shows a schematic configuration of a gas turbine according to an embodiment of the present invention, which provides a solid fuel gas turbine having a single can combustor, including a compressor 200 and a turbine 300 axially sequentially installed to a rotating shaft 100, and a combustor 400 connected to an outlet end of the compressor 200. The gas turbine further comprises a regenerator 800, the exhaust end of the turbine 300 is connected with the inlet of a first flow channel of the regenerator 800, the exhaust end of the compressor 200 is connected with the inlet of a second flow channel of the regenerator 800, the outlet of the second flow channel is connected with the inlet of the air chamber 410, and the gas in the first flow channel and the gas in the second flow channel exchange heat in the regenerator 800. Regenerator 800 may include heat exchange fins to exchange heat between the gas in the first flow path and the gas in the second flow path, and the high temperature gas (300 ℃ -600 ℃) after heat exchange enters gas chamber 410 for reuse, and when the temperature of the high temperature gas is at a higher level, the solid-containing fuel in second combustion section 430 can be ignited.
The rotating shaft 100 may be an integral rotating shaft or a segmented rotating shaft connected through a coupling. The material of the rotating shaft can be steel, or other suitable metal, alloy or composite material. The shaft 100 is supported by bearings on a housing or bearing block of the gas turbine. Fig. 1 schematically illustrates a bearing 500. The bearing may be a ball bearing, or may be a non-contact bearing such as a magnetic bearing, an air bearing, or a hybrid air-magnetic bearing. In the embodiment of the invention, the air bearing is preferable.
The compressor 200 may be an axial compressor or a centrifugal compressor. In some embodiments, the compressor 200 may include a compressor wheel and a diffuser. The air inlet of the compressor 200 communicates with the external environment for intake air, and the intake air (e.g., air) is compressed by the compressor 200 and then enters the combustion chamber 400 through the air outlet end of the compressor 200.
The turbine 300 may be an axial turbine or a centrifugal turbine. The material of the turbine 300 may be a high temperature resistant material, such as nickel or nickel alloy. Turbine 300 is typically coupled to an exhaust end of combustor 400 to receive high temperature gas from combustor 400 and to perform work using the high temperature gas.
The combustion chamber 400 includes a first combustion section 420, a second combustion section 430, and an air chamber 410. The inlet end of the plenum 410 is connected to the outlet end of the compressor 200. The plenum 410 is disposed at least partially around the first combustion section 420, i.e., the plenum 410 may circumferentially entirely surround the first combustion section 420, or the plenum 410 circumferentially surrounds a portion of the first combustion section 420, depending on the design location of the intake passages (intake holes) of the first combustion section 420 but capable of satisfying uniform and adequate intake conditions and achieving proper flame location and combustion temperature. The gas chamber 410 and the first combustion portion 420 may be in gas communication, for example, the gas chamber 410 and the first combustion portion 420 may be in communication through gas holes, and the pressurized gas from the compressor 200 may enter the first combustion portion 420 to participate in combustion (e.g., provide sufficient oxidant). The second combustion section 430 is located below the first combustion section 420, and the second combustion section 430 contains a solid fuel. The solid-state-containing fuel as used herein refers to a single-state fuel or a mixed-state fuel containing at least solid fuel, such as solid pulverized coal, coal slurry in which liquid water is mixed with solid pulverized coal, and the like. The solid-containing fuel may be completely combusted, partially combusted, and reacted gas (combustible gas such as carbon monoxide or hydrogen, etc.) in the second combustion part 430, and the reacted gas (such as carbon monoxide) enters the first combustion part 420 for secondary combustion. The air chamber 410 and the second combustion portion 430 can be in air communication, for example, the air chamber 410 and the second combustion portion 430 are communicated through air holes, and the combustion air from the second combustion portion 430 can enter the air chamber 410, then enter the first combustion portion 420 through the air chamber 410 to participate in providing high-temperature combustion air or further combustion. In some alternative embodiments, when the solid fuel is coal or other elemental carbon-containing fuel and water (particularly steam) is introduced into the second combustion section 500, the chemical reaction of the reaction gas may comprise a reaction similar to coal gasification (carbon reacts with water at high temperatures of 700-1200 ℃ to produce carbon monoxide and hydrogen, i.e., water gas).
The gas turbine provided by the present invention further includes a silo 600 containing solid fuel. The second combustion section 430 is coupled to the silo 600 to receive solid-containing fuel from the silo 600. The cartridge 600 may be a sealable storage cartridge having a pressure.
The solid fuel gas turbine with the single-can combustor according to the embodiment of the invention can directly operate by using the solid fuel by providing the combustor 400 comprising the first combustion part 420, the second combustion part 430 and the air chamber 410 and the storage bin 600 connected with the second combustion part 430 and containing the solid fuel, so as to reduce the operation cost or increase the region application range of the gas turbine. The solid fuel gas turbine with the single-barrel combustion chamber, which is disclosed by the embodiment of the invention, is compact in structure, can be arranged on mobile equipment, can be reformed by using a conventional gas turbine, and further reduces the cost.
Further, as shown in fig. 2, fig. 2 shows a schematic structural view of the combustion chamber in fig. 1, at least a portion of the plenum 410 is located between the first combustion portion 420 and the second combustion portion 430. In this way, the uniformity of the high-temperature combustion gas generated in the second combustion section 430 entering the first combustion section 420 can be further improved, and the air chamber 410 serves as a buffer between the first combustion section 420 and the second combustion section 430, so that the first combustion section 420 is prevented from being directly baked by flame as much as possible, and the durability of the material of the first combustion section 420 is improved. The second combustion section 430 includes a flue gas plate 432 and communicates with the plenum 410 through the flue gas plate 432. The flue gas panel 432 may control the flame height of the second combustion section 430, making the high flame more uniform and preventing the flame from channeling upward.
Further, as shown in fig. 3, fig. 3 shows a schematic structure of the smoke plate in fig. 2, and the smoke plate 432 includes a plurality of smoke plate communication holes communicating the second combustion part 430 and the air chamber 410. Fig. 3 shows a rectangular flue gas plate 432, however the flue gas plate 432 may also be circular, triangular, oval, etc. other shapes. Fig. 3 shows a circular smoke plate communication hole, however, the smoke plate communication hole may also be rectangular, triangular, oval, etc. other shapes. The material of the flue gas plate 432 may be nickel or a nickel alloy, for example the flue gas plate 432 may be a nickel mesh. The flue gas plate 432 is a high-mesh orifice plate to block combustion dust from entering the plenum 410 as much as possible and to allow combustion hot gases and/or reactant gases to enter the plenum 410. For example, the aperture of the smoke plate communication hole is 0.1mm to 100mm.
In some alternative embodiments, as shown in FIG. 1, the gas turbine also includes a fuel tank 700. The fuel tank 700 may store fuel in gaseous and/or liquid form. The first combustion section 420 is provided with a nozzle 490, and the nozzle 490 is connected to the fuel tank 700. The combustion mode of injecting the gaseous fuel and/or the liquid fuel through the nozzle 490 is used for the start-up and stop phases of the gas turbine, or the combustion mode of injecting the nozzle 490 is also used for auxiliary combustion, so that the combustion chamber 400 can provide enough stable temperature, and the combustion gas or the unburnt fuel generated by the second combustion part 430 is subjected to secondary combustion, so that the combustion chamber 400 is fully combusted as a whole.
In some alternative embodiments, the exhaust end of turbine 300 may be provided with a dust extraction device and/or a three-way catalyst to improve the emissions standards of the gas turbine. The dust removing device can be a cloth bag dust removing device, an electrostatic dust removing device and the like.
Fig. 4 shows a schematic structure of a single-tube combustor according to the present invention, the combustor 400 is a single-tube combustor, the combustor 400 is disposed at one side of the rotating shaft 100, the air chamber 410 surrounds the first combustion part 420, the air chamber 410 has a combustor inlet 413 connected to an outlet end of the compressor 200, the first combustion part 420 has a combustor outlet 422 connected to an inlet end of the turbine 300, and the combustor inlet 413 is disposed in the same direction as the combustor outlet 422.
Specifically, the combustion chamber 400 includes a first housing 411, a second housing 421, and a third housing 433. The second case 421 surrounds the first combustion section 420 formed in a single cylinder shape and has an opening at one axial end corresponding to the combustion chamber exhaust port 422. The first housing 411 at least partially encloses the second housing 421 and defines the air chamber 410 in combination therewith. The second case 421 has a through hole communicating the air chamber 410 with the first combustion part 420. The third housing 433 is connected to the first housing 411 and extends into the second combustion portion 430. The smoke plate 432 is disposed adjacent to the second housing 421 at the third housing 433.
Fig. 5 shows a schematic structural view of the silo of fig. 1, the silo 600 comprising a chamber 610, a feed inlet 620 and a conveying means 630. The chamber 610 contains a solid fuel. The inlet 620 is located above the chamber 610 and is provided with an openable and closable air-tight door, which when opened can feed the chamber 610 through the inlet 620, and which when closed forms an air-tight connection with the inlet 620 to facilitate maintaining the pressure in the bin 600. The delivery device 630 is located at the underside of the chamber 610 and is connected to the input port 439 of the second combustion section 430 via the output port 601. The conveyor 630 may be a screw conveyor, conveyor track, or the like.
Further, the cartridge 600 also includes a pressurization port 640 and a first priming port 650. The pressurized port 640 is connected to a source of gas and supplies pressurized gas to the chamber 610 to maintain the pressure within the chamber 610 and to minimize backflow of pressurized gas from the combustion chamber 400. The first liquid injection port 650 is connected to a water supply device and injects a liquid that wets the solid fuel-containing liquid into the chamber 610. The injected liquid is mixed with the solid-containing fuel, so that the combustion characteristics of the solid-containing fuel can be improved, the combustion can be more stable, and the reaction products can be controlled in a targeted manner (for example, when the liquid is water, the mixed fuel is combusted and controlled to react in the second combustion part 430 to generate hydrogen, and the hydrogen enters the first combustion part 420 for secondary combustion). The liquid may be water or other liquid capable of stabilizing combustion or assisting in the reaction.
Fig. 6 illustrates a schematic structure of a gas turbine according to another embodiment of the present invention, and fig. 7 illustrates a schematic structure of the combustion chamber of fig. 6, and the second combustion part 430 further includes a second injection port 451 and/or a third injection port 452. The second liquid injection port 451 extends below the smoke plate 432 and is connected to a water supply device, and injects liquid into the combustion area of the second combustion portion 430. A third fill port 452 is positioned adjacent to the input port 439 and is connected to the water supply and is filled with a liquid that wets the solid fuel-containing fluid. The liquid may be water or other liquid capable of stabilizing combustion or assisting in the reaction. The injected liquid is mixed with the solid-state-containing fuel, so that the combustion characteristic of the solid-state fuel can be improved, the combustion is more stable, and the reaction products can be controlled in a targeted manner. In some alternative embodiments, the second liquid injection port 451 may inject a large amount of liquid (e.g., water) to extinguish the flame in the second combustion portion 430 during a gas turbine shutdown (particularly during an emergency shutdown) for shutdown purposes.
Specifically, when the second combustion part 430 includes the second liquid injection ports 451, the number of the second liquid injection ports 451 is plural, and the plurality of second liquid injection ports 451 are arranged around the combustion region of the second combustion part 430 to more uniformly mix the liquid with the solid fuel.
Further, when the second combustion part 430 includes the second liquid injection port 451, the liquid injected through the second liquid injection port 451 is saturated water. The saturated water is water with the temperature close to boiling, so that the consumption of fuel caused by the temperature rise of cold water is avoided, the energy utilization rate can be improved, and the uneven temperature and excessive cooling of a combustion area caused by the cold water can be avoided, so that the influence on the combustion stability and the reaction temperature is avoided as much as possible.
Further, the water supply device connected to the second liquid injection port 451 includes a heat exchange line provided at an exhaust end of the turbine 300 to utilize high-temperature exhaust gas discharged from the gas turbine, thereby realizing partial heat recovery.
In some alternative embodiments, as shown in fig. 8-11, fig. 8 shows a schematic structural view of a gas turbine according to yet another embodiment of the present invention, and fig. 9-11 show a schematic structural view of a different embodiment of the combustor in fig. 8, the combustor 400 further including a cooling portion 460. The cooling portion 460 is connected to the first combustion portion 420 and is at least partially located on a side of the first combustion portion 420 facing the second combustion portion 430. In this way, the cooling part 460 can further block the flame of the second combustion part 430 from being directly baked to protect the first combustion part 420.
Further, as shown in fig. 11, the cooling portion 460 completely surrounds the first combustion portion 420 in the circumferential direction. The full-surrounding form is simpler to manufacture. Or as shown in fig. 9 and 10, the cooling portion 460 circumferentially surrounds half of the first combustion portion 420. The semi-enclosed form can reduce material costs and further facilitate the arrangement of the inlet holes of the first combustion section 420.
Further, the cooling portion 460 has a cooling channel, and in some embodiments, a gaseous or liquid cooling medium is disposed in the cooling channel, so that the cooling portion 460 can absorb heat and soak heat, no external cooling substance is needed, and such a configuration can be adopted when the flame height of the second combustion portion 430 is not high. In other embodiments, the cooling channels are configured to have a gaseous or liquid cooling medium flowing therethrough such that the cooling portion 460 acts as a forced cooling, particularly for cooling when the flame of the second combustion portion 430 is highly direct baked. The two modes can be mixed for use.
Further, in the embodiment in which the second combustion section 430 includes the smoke plate 432 and the smoke plate 432 includes the plurality of smoke plate communication holes, the sizes of all the smoke plate communication holes in the axial direction are within the axial size range of the cooling section 460, so that the flames of the second combustion section 430 can be controlled to be in the axial direction range, and the flames are prevented from baking the end sides of the first combustion section 420 as much as possible.
In some alternative implementations, as shown in FIG. 12, FIG. 12 illustrates a schematic structural view of a gas turbine engine according to yet another embodiment of the present invention, the gas turbine engine further including a heating device 480, the heating device 480 being located within the second combustion section 430. Heating device 480 is used to ignite the solid-containing fuel in second combustion section 430 or to assist in igniting the solid-containing fuel.
Further, as shown in fig. 13, fig. 13 shows a schematic structural view of an embodiment of the combustion chamber in fig. 12, and a heating device 480 is disposed adjacent to an input port 439 of the second combustion section 430.
Further, the number of the heating devices 480 is plural, and the plurality of the heating devices 480 are arranged around the combustion area of the second combustion part 430.
Further, as shown in fig. 14 to 18, fig. 14 shows a schematic structural view of another embodiment of the combustion chamber in fig. 12, and fig. 15 to 18 show a schematic structural view of a different embodiment of the heating device in fig. 13, wherein the heating device 480 is a single heating pipe, a plurality of heating pipes, a heating ring or a heating plate.
In the description of the present invention, a description of the terms "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (10)
1. The utility model provides a solid fuel gas turbine with single section of thick bamboo combustor, includes that the axial is installed in compressor and the turbine of pivot in proper order to and with the combustor that the end of giving vent to anger of compressor is connected, its characterized in that:
The combustion chamber is a single-cylinder combustion chamber, the combustion chamber is arranged at one side of the rotating shaft, the combustion chamber comprises a first combustion part, a second combustion part and an air chamber, the second combustion part is arranged below the first combustion part, the air chamber surrounds the first combustion part, the air chamber is provided with a combustion chamber air inlet connected with an air outlet end of the air compressor, the first combustion part is provided with a combustion chamber air outlet connected with an air inlet end of the turbine, and the combustion chamber air inlet and the combustion chamber air outlet are arranged in the same direction; the second combustion part is connected with a bin, and the bin is used for containing solid fuel; the second combustion part comprises a smoke plate and is communicated with the air chamber through the smoke plate, and the smoke plate is a high-mesh pore plate.
2. The gas turbine of claim 1, wherein at least a portion of the plenum is located between the first combustion section and the second combustion section.
3. The gas turbine of claim 1, further comprising a regenerator, wherein an exhaust end of the turbine is coupled to an inlet of a first flow passage of the regenerator, an exhaust end of the compressor is coupled to an inlet of a second flow passage of the regenerator, an outlet of the second flow passage is coupled to an inlet of the plenum, and the gas in the first flow passage and the second flow passage exchange heat within the regenerator.
4. The gas turbine of claim 2, wherein the combustion chamber comprises a first housing, a second housing, and a third housing,
The second shell surrounds the first combustion part which forms a single cylinder shape and is provided with an opening corresponding to the exhaust port of the combustion chamber at one axial end;
the first housing at least partially encloses the second housing and defines the plenum therewith;
the second shell is provided with a through hole for communicating the air chamber with the first combustion part;
The third shell is connected with the first shell and extends to form the second combustion part;
The smoke plate is arranged adjacent to the second shell and is arranged on the third shell.
5. The gas turbine of claim 1, wherein the silo includes a chamber, a feed port, a delivery device, a pressurization port, and a first injection port, the chamber containing a solid fuel; the feed inlet is positioned at the upper side of the cabin and is provided with an openable airtight door; the conveying device is positioned at the lower side of the cabin and is connected with the input port of the second combustion part through the output port; the pressurizing port is connected with an air source and is used for introducing pressurized air into the cabin; the first liquid injection port is connected with a water supply device and injects the liquid containing the solid fuel into the cabin.
6. The gas turbine of claim 1, wherein a cooling portion is disposed between the second combustion portion and the first combustion portion, the cooling portion being coupled to the first combustion portion and at least partially located on a side of the first combustion portion facing the second combustion portion.
7. The gas turbine of claim 6, wherein the cooling portion completely circumferentially surrounds the first combustion portion or the cooling portion circumferentially surrounds half of the first combustion portion; and the cooling part is provided with a cooling channel, a gaseous or liquid cooling medium is arranged in the cooling channel, and/or the cooling channel is arranged to flow through the gaseous or liquid cooling medium.
8. The gas turbine of claim 2, wherein the second combustion section further comprises:
the second liquid injection port extends below the smoke plate and is connected with a water supply device, and liquid is injected into a combustion area of the second combustion part; and/or the number of the groups of groups,
And the third liquid injection port is arranged close to the input port and connected with the water supply device, and is used for injecting the liquid containing the solid fuel.
9. The gas turbine of claim 8, wherein when the second combustion section includes the second liquid injection ports, the number of the second liquid injection ports is plural, the plural second liquid injection ports are arranged around the combustion region of the second combustion section, and the liquid injected through the second liquid injection ports is saturated water.
10. The gas turbine of claim 1, further comprising a fuel tank, wherein the first combustion section is provided with a nozzle, and wherein the nozzle is connected to the fuel tank.
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| AU685766B2 (en) * | 1993-03-03 | 1998-01-29 | Ebara Corporation | Pressurized internal circulating fluidized-bed boiler |
| US7189270B2 (en) * | 2001-12-10 | 2007-03-13 | Gas Technology Institute | Method and apparatus for gasification-based power generation |
| DE102011113623A1 (en) * | 2011-09-16 | 2013-03-21 | H S Reformer Gmbh | gas turbine |
| CN103644003A (en) * | 2013-12-17 | 2014-03-19 | 汪禹 | Combined-cycle thermal power generation device with general fuel |
| CN213513983U (en) * | 2020-07-27 | 2021-06-22 | 西安联创分布式可再生能源研究院有限公司 | Double-combustion external combustion type gas turbine system |
| CN113623033A (en) * | 2021-09-15 | 2021-11-09 | 中国华能集团清洁能源技术研究院有限公司 | IGCC system adopting air gasification and working method thereof |
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