CN115059546A - Solid fuel gas turbine with single-cylinder combustion chamber - Google Patents
Solid fuel gas turbine with single-cylinder combustion chamber Download PDFInfo
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- CN115059546A CN115059546A CN202210775764.2A CN202210775764A CN115059546A CN 115059546 A CN115059546 A CN 115059546A CN 202210775764 A CN202210775764 A CN 202210775764A CN 115059546 A CN115059546 A CN 115059546A
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- combustion chamber
- gas turbine
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 224
- 239000007789 gas Substances 0.000 title claims abstract description 147
- 239000004449 solid propellant Substances 0.000 title claims abstract description 48
- 239000007788 liquid Substances 0.000 claims description 58
- 238000001816 cooling Methods 0.000 claims description 35
- 238000002347 injection Methods 0.000 claims description 30
- 239000007924 injection Substances 0.000 claims description 30
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 25
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 24
- 239000003546 flue gas Substances 0.000 claims description 21
- 239000002828 fuel tank Substances 0.000 claims description 7
- 239000000779 smoke Substances 0.000 claims description 7
- 239000002826 coolant Substances 0.000 claims description 6
- 229920006395 saturated elastomer Polymers 0.000 claims description 4
- 238000009736 wetting Methods 0.000 claims description 2
- 238000003860 storage Methods 0.000 abstract description 4
- 239000000446 fuel Substances 0.000 description 24
- 238000010438 heat treatment Methods 0.000 description 17
- 238000004891 communication Methods 0.000 description 10
- 239000007787 solid Substances 0.000 description 10
- 239000000463 material Substances 0.000 description 8
- 239000000567 combustion gas Substances 0.000 description 7
- 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
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- 229910052739 hydrogen Inorganic materials 0.000 description 4
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- 229910002091 carbon monoxide Inorganic materials 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- 239000000843 powder Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
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- 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
- 239000003517 fume Substances 0.000 description 2
- 150000002431 hydrogen Chemical class 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000012495 reaction gas Substances 0.000 description 2
- 238000002407 reforming Methods 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
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- 229910000831 Steel Inorganic materials 0.000 description 1
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- 239000003250 coal slurry Substances 0.000 description 1
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- 229910052751 metal Inorganic materials 0.000 description 1
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- 239000007800 oxidant agent Substances 0.000 description 1
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- 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
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- 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 and is arranged on one side of the rotating shaft, the combustion chamber 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 storage bin. The gas turbine disclosed by the invention can directly utilize solid fuel to operate so as to reduce the operation cost or increase the regional 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-cylinder combustion chamber.
Background
The gas turbine uses continuously flowing gas as working medium to drive the impeller to rotate at high speed, and converts the energy of fuel into useful work, and is 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 pressurize the air, and simultaneously, the air temperature is correspondingly increased; compressed air is pumped into a combustion chamber and is mixed with injected fuel to be combusted to generate high-temperature and high-pressure gas; then the gas or liquid fuel enters a turbine to do work through expansion, the turbine is pushed to drive the gas compressor and the external load rotor to rotate at a high speed, and the purpose that the chemical energy of the gas or liquid fuel is partially converted into mechanical work is achieved.
At present, the fuel of the gas turbine is generally liquid or gaseous fuel, however, the cost of the liquid or gaseous fuel is high, and the cost of the solid fuel is relatively low, but the general gas turbine is often difficult to directly utilize the solid fuel.
Disclosure of Invention
The embodiment of the invention provides a solid fuel gas turbine with a single-cylinder combustor, which can directly utilize solid fuel to operate so as to reduce the operation cost or increase the regional 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 and is arranged on one side of the rotating shaft, the combustion chamber 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 bin which is used for containing solid fuel.
According to an aspect of an embodiment of the present invention, at least a part of the plenum is located between the first combustion portion and the second combustion portion, and the second combustion portion includes a smoke panel and communicates with the plenum through the smoke panel.
According to one aspect of the embodiment of the invention, the heat regenerator is further included, the exhaust end of the turbine is connected with the inlet of the first flow channel of the heat regenerator, the exhaust end of the compressor is connected with the inlet of the second flow channel of the heat regenerator, the outlet of the second flow channel is connected with the inlet of the gas 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 the embodiment of the present invention, the combustion chamber includes a first housing, a second housing, and a third housing, the second housing surrounding a first combustion portion forming a single cylinder shape and having an opening corresponding to an exhaust port of the combustion chamber at one end in an axial direction; the first housing at least partially surrounds 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 into a second combustion part; the flue gas board is close to the second casing and sets up in the third casing.
According to one aspect of the embodiment of the invention, the storage bin comprises a cabin, a feeding hole, a conveying device, a pressurizing hole and a first liquid injection hole, wherein solid fuel is contained in the cabin; the feed inlet is positioned at the upper side of the cabin and is provided with an airtight door which can be opened and closed; 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 introduces pressurized air into the cabin; the first liquid injection port is connected with the water supply device and injects the liquid containing the solid fuel into the chamber.
According to an aspect of the embodiment of the present invention, a cooling portion is provided between the second combustion portion and the first combustion portion, the cooling portion is connected to the first combustion portion and is 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 provided with the gaseous or liquid cooling medium flowing through.
According to an aspect of an embodiment of the present invention, the second combustion portion further includes: the second liquid injection port extends into the lower part of the flue gas plate, is connected with the water supply device and injects liquid into a combustion area of the second combustion part; and/or a third liquid injection port which is arranged close to the input port, is connected with the water supply device and injects liquid containing the solid fuel.
According to an aspect of the embodiment of the present invention, when the second combustion portion includes the second liquid injection port, the number of the second liquid injection port is plural, the plural second liquid injection ports are arranged around the combustion area of the second combustion portion, and the liquid injected through the second liquid injection port is saturated water.
According to an aspect of an embodiment of the present invention, the gas turbine further includes a fuel tank, and the first combustion section is provided with a nozzle, which is connected to the fuel tank.
The solid fuel gas turbine with the single-cylinder combustor according to the embodiment of the invention has the advantages that the solid fuel gas turbine can directly use the solid fuel to operate and work by arranging the combustor comprising the first combustion part, the second combustion part and the air chamber and the silo containing the solid fuel connected with the second combustion part, so that the operation cost is reduced or the regional application range of the gas turbine is increased. And the gas chamber is at least partially arranged around the first combustion part, and the second combustion part is positioned below the first combustion part, so that high-temperature flue gas generated by combustion of solid fuel in the second combustion part enters the gas chamber and more uniformly enters the first combustion part through the gas chamber to provide high-temperature combustion gas or carry out secondary combustion, and thus, stable combustion of the first combustion part can be ensured, and the working effect of the gas turbine taking the solid fuel as energy is further ensured. In addition, the gas turbine with the single-cylinder combustion chamber provided by the embodiment of the invention has a compact structure, can be arranged on mobile equipment, and can be formed by reforming a conventional gas turbine, so that the cost is further reduced.
Drawings
Other features, objects and advantages of the invention will become apparent from the following detailed description of non-limiting embodiments thereof, when read in conjunction with the accompanying drawings, in which like reference characters designate the same or similar parts throughout the figures thereof, and which are not to scale.
Fig. 1 shows a schematic illustration of the structure of a gas turbine according to the invention.
Fig. 2 shows a schematic view of the structure of the combustion chamber of fig. 1.
Figure 3 shows a schematic view of the structure of the smoke panel of figure 2.
Fig. 4 shows a schematic view of the structure of a mono-can combustor.
Fig. 5 shows a schematic structural view of the silo of fig. 1.
FIG. 6 is a schematic diagram of a gas turbine engine having second and third injection ports.
Fig. 7 shows a schematic view of the structure of the combustion chamber in fig. 6.
Fig. 8 shows a schematic illustration of a gas turbine with a cooling section.
Fig. 9 is a schematic structural view showing one embodiment of the cooling part of fig. 8.
Fig. 10 is a schematic structural view showing another embodiment of the cooling part of fig. 8.
Fig. 11 is a schematic view showing the structure of still another embodiment of the cooling part of fig. 8.
Fig. 12 shows a schematic illustration 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 view of another embodiment of the combustor of FIG. 12.
Fig. 15 shows a schematic view of the structure of one embodiment of the heating device in fig. 13.
Fig. 16 shows a schematic view of another embodiment of the heating apparatus of fig. 13.
Fig. 17 is a schematic view showing the construction of still another embodiment of the heating apparatus of fig. 13.
Fig. 18 shows a schematic view of a structure of still another embodiment of the heating apparatus of 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 objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.
At present, fuels generally have liquid state, gaseous state and solid state, the solid state is widely distributed, the existing forms are various, and the acquisition (exploitation) cost is low, so that the price is low, for example, waste materials such as coal (powder), straws, even kitchen garbage, sludge, biogas residues and the like have a certain calorific value, can be used as solid state fuels, and are subjected to harmless treatment. However, these solid fuels are not readily available for direct use and require secondary processing such as refining and conversion, which increases costs, and the widespread distribution of these solid fuels is widespread and decentralized, resulting in additional transportation and storage costs.
Therefore, there is a need for a solid fuel utilization device, which can convert solid fuel into directly usable energy such as heat energy, kinetic energy and/or electric energy, and can realize local utilization in the area where the solid fuel is distributed.
To achieve the above object, as shown in fig. 1, fig. 1 shows a schematic structural view of a gas turbine according to an embodiment of the present invention, and the present invention provides a solid fuel gas turbine having a mono-can combustor, which includes a compressor 200 and a turbine 300 axially mounted to a rotating shaft 100 in sequence, and a combustor 400 connected to an outlet end of the compressor 200. The gas turbine further comprises a heat regenerator 800, wherein the exhaust end of the turbine 300 is connected with the inlet of a first flow channel of the heat regenerator 800, the exhaust end of the compressor 200 is connected with the inlet of a second flow channel of the heat regenerator 800, the outlet of the second flow channel is connected with the inlet of the gas chamber 410, and the gas in the first flow channel and the gas in the second flow channel exchange heat in the heat regenerator 800. The regenerator 800 may include heat exchange fins to exchange heat between the first flow channel and the gas in the second flow channel, and the heat-exchanged high-temperature gas (300-600 ℃) enters the gas chamber 410 to be reused, so that the solid fuel in the second combustion part 430 can be ignited when the temperature of the high-temperature gas is at a higher level.
The rotating shaft 100 may be an integral rotating shaft, or may be a segmented rotating shaft connected by a coupling. The material of the rotating shaft can be steel, and can also be other suitable metals, alloys or composite materials. The shaft 100 is supported by bearings to the casing or bearing housing of the gas turbine. Fig. 1 schematically shows a bearing 500. The bearing may be a ball bearing, or a non-contact bearing such as a magnetic bearing, an air bearing, or a gas-magnetic hybrid bearing. Air bearings are preferred in embodiments of the present invention.
The compressor 200 may be an axial compressor or a centrifugal compressor. In some embodiments, the compressor 200 may include a compressor wheel and diffuser. An air inlet of the compressor 200 communicates with the external environment for air suction, and sucked air (e.g., air) is compressed by the compressor 200 and then enters the combustion chamber 400 through an 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 a nickel alloy. The turbine 300 is generally coupled to an exhaust end of the combustor 400 to receive the high temperature combustion gases from the combustor 400 and to utilize the high temperature combustion gases to produce work.
The combustion chamber 400 includes a first combustion part 420, a second combustion part 430, and a gas chamber 410. The air inlet end of the air chamber 410 is connected with the air outlet end of the compressor 200. The gas chamber 410 is disposed at least partially around the first combustion portion 420, that is, the gas chamber 410 may completely surround the first combustion portion 420 in the circumferential direction, or the gas chamber 410 may surround a portion of the first combustion portion 420 in the circumferential direction, depending on the design position of the intake passage (intake hole) of the first combustion portion 420 but capable of satisfying a uniform and sufficient intake condition and achieving a proper flame position and combustion temperature. The gas chamber 410 can be in gas communication with the first combustion portion 420, for example, the gas chamber 410 can be in gas communication with the first combustion portion 420 through the gas holes, and the pressure gas from the compressor 200 can enter the first combustion portion 420 to participate in combustion (for example, to provide enough oxidant). The second combustion part 430 is located below the first combustion part 420, and the second combustion part 430 contains solid fuel therein. The solid fuel is a single-state fuel or a mixed-state fuel containing at least a solid fuel, such as solid coal powder, coal slurry obtained by mixing liquid water with solid coal powder, and the like. The solid fuel may be completely combusted, partially combusted, or reacted in the second combustion portion 430 to produce a gas (e.g., a combustible gas such as carbon monoxide or hydrogen), and the reacted gas (e.g., carbon monoxide) enters the first combustion portion 420 for secondary combustion. The gas chamber 410 and the second combustion portion 430 can be in gas communication with each other, for example, the gas chamber 410 and the second combustion portion 430 are in gas communication with each other through gas holes, so that the combustion gas from the second combustion portion 430 can enter the gas chamber 410, and then enter the first combustion portion 420 through the gas chamber 410 to be involved in supplying high-temperature combustion gas or performing further combustion. In some alternative embodiments, when the solid fuel is coal or other elemental carbon-containing fuel, and water (especially steam) is introduced into the second combustion portion 500, the chemical reaction of the reaction gas may include a reaction similar to coal gasification (where carbon reacts with water at high temperatures between 700 ℃ and 1200 ℃ to form carbon monoxide and hydrogen, i.e., water gas).
The gas turbine provided by the present invention also includes a silo 600 containing a solid fuel. The second combustion part 430 is connected to the silo 600 to receive the solid-containing fuel from the silo 600. The silo 600 may be a sealable storage silo with a certain pressure.
The solid fuel gas turbine with the mono-can combustor according to the embodiment of the invention, by providing the combustor 400 including the first combustion part 420, the second combustion part 430 and the gas chamber 410, and the silo 600 containing the solid fuel connected with the second combustion part 430, the gas turbine can directly use the solid fuel to operate, so as to reduce the operation cost or increase the geographical applicability of the gas turbine. The solid fuel gas turbine with the single-cylinder combustion chamber provided by the embodiment of the invention has a compact structure, can be arranged on mobile equipment, and can be formed by reforming a conventional gas turbine, so that the cost is further reduced.
Further, as shown in FIG. 2, FIG. 2 shows a schematic view of the structure of the combustion chamber of FIG. 1, and at least a portion of the gas chamber 410 is located between the first combustion part 420 and the second combustion part 430. This further improves the uniformity of the high-temperature combustion gas generated in the second combustion part 430 entering the first combustion part 420, and the gas chamber 410 serves as a buffer between the first combustion part 420 and the second combustion part 430, thereby preventing the flame from directly burning the first combustion part 420 as much as possible, and improving the durability of the material of the first combustion part 420. The second combustion portion 430 includes a flue gas panel 432 and communicates with the plenum 410 through the flue gas panel 432. The smoke panel 432 may control the flame height of the second combustion portion 430, making the height flame more uniform and preventing the flame from rising upward.
Further, as shown in fig. 3, fig. 3 shows a schematic structural view of the flue gas panel of fig. 2, and the flue gas panel 432 includes a plurality of flue gas panel communication holes communicating the second combustion portion 430 with the gas chamber 410. Figure 3 shows a rectangular flue gas panel 432, however the flue gas panel 432 may also be circular, triangular, oval, etc. in other shapes. Figure 3 shows circular fume plate communication holes, however the fume plate communication holes may also be rectangular, triangular, oval, etc. in other shapes. The material of the flue gas panel 432 may be nickel or a nickel alloy, for example the flue gas panel 432 may be a nickel mesh. The flue gas panel 432 is a high-mesh plate to prevent combustion dust from entering the gas chamber 410 as much as possible and to allow combustion high-temperature gas and/or reaction gas to enter the gas chamber 410. For example, the aperture of the smoke plate communication hole is 0.1mm to 100 mm.
In some alternative embodiments, as shown in FIG. 1, the gas turbine further includes a fuel tank 700. The fuel tank 700 may store gaseous fuel and/or liquid fuel. The first combustion part 420 is provided with a nozzle 490, and the nozzle 490 is connected to a 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 stage and the stop stage of the gas turbine, or the combustion mode through the nozzle 490 may also be used for the auxiliary combustion, so that the combustion chamber 400 can provide a sufficient stable temperature, and the combustion gas or the unburnt fuel generated from the second combustion portion 430 is secondarily combusted, so that the combustion chamber 400 is more fully combusted as a whole.
In some alternative embodiments, the exhaust end of the turbine 300 may be provided with a dust removal device and/or a three-way catalyst to increase the emission standards of the gas turbine. Wherein, 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 structural view of a mono-tube combustion chamber according to the present invention, the combustion chamber 400 is a mono-tube combustion chamber, the combustion chamber 400 is disposed at one side of the rotary shaft 100, the gas chamber 410 surrounds the first combustion portion 420, the gas chamber 410 has a combustion chamber inlet 413 connected to an outlet end of the compressor 200, the first combustion portion 420 has a combustion chamber outlet 422 connected to an inlet end of the turbine 300, and the combustion chamber inlet 413 and the combustion chamber outlet 422 are disposed in the same direction.
Specifically, the combustion chamber 400 includes a first housing 411, a second housing 421, and a third housing 433. The second housing 421 surrounds the first combustion part 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 together therewith defines the air chamber 410. The second housing 421 has a through hole communicating the air chamber 410 and the first combustion part 420. The third housing 433 is connected to the first housing 411 and extends to form the second combustion part 430. The smoke panel 432 is provided adjacent to the second case 421 to the third case 433.
Fig. 5 shows a schematic structural view of the cartridge of fig. 1, the cartridge 600 including a chamber 610, a feed port 620, and a conveyor 630. The chamber 610 contains a solid fuel. The inlet 620 is located on the upper side of the chamber 610 and is provided with an openable and closable air-tight door, which can feed the chamber 610 through the inlet 620 when opened, and which can be in air-tight connection with the inlet 620 when closed to maintain the pressure in the silo 600. The transport device 630 is located at the lower side of the chamber 610 and is connected to the inlet 439 of the second combustion part 430 through the outlet 601. The conveying means 630 may be a screw conveyor, a conveyor track, or the like.
Further, the cartridge 600 further includes a pressurization port 640 and a first injection port 650. The pressurization port 640 is connected to a gas source and supplies pressurized gas to the chamber 610 to maintain the pressure in the chamber 610 to prevent backflow of the pressurized gas from the combustion chamber 400. The first injection port 650 is connected to a water supply device and injects a liquid for wetting the solid fuel into the chamber 610. The injected liquid is mixed with the solid fuel, so that the combustion characteristics of the solid fuel can be improved, the combustion is more stable, and the reaction products can be controlled (for example, when the liquid is water, the mixed fuel is combusted and controlled 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 the combustion or assisting the reaction.
FIG. 6 shows a schematic view of a gas turbine according to another embodiment of the present invention, FIG. 7 shows a schematic view of the structure of the combustor in FIG. 6, and the second combustion portion 430 further includes a second injection port 451 and/or a third injection port 452. The second liquid injection port 451 extends below the flue gas panel 432, is connected to a water supply device, and injects liquid into the combustion area of the second combustion part 430. The third liquid injection port 452 is provided adjacent to the input port 439 and connected to the water supply means, and injects a liquid that wets the solid fuel. The liquid may be water or other liquid capable of stabilizing the combustion or assisting the reaction. The injected liquid mixes with the solid-containing fuel and improves the combustion characteristics of the solid fuel, making combustion more stable and allowing for targeted control of the reaction products. In some alternative embodiments, the second injection port 451 may inject a large amount of liquid (e.g., water) to extinguish a flame in the second combustion portion 430 when the gas turbine is shut down (especially during an emergency shutdown) for shutdown purposes.
Specifically, when the second combustion portion 430 includes the second liquid injection port 451, the number of the second liquid injection ports 451 is plural, and the plural second liquid injection ports 451 are arranged around the combustion area of the second combustion portion 430, so that the liquid and the solid-containing fuel are more uniformly mixed.
Further, when the second combustion portion 430 includes the second liquid injection port 451, the liquid injected through the second liquid injection port 451 is saturated water. Saturated water reaches the water that closes on the boiling for the temperature, avoids cold water intensification like this to the consumption of fuel, can improve energy utilization to can avoid cold water to lead to the uneven and overcooling of temperature in combustion area, with the influence of avoiding as far as possible to combustion stability and reaction temperature.
Further, the water supply device connected to the second liquid injection port 451 includes a heat exchange line provided at the exhaust end of the turbine 300 to utilize the high-temperature exhaust gas discharged from the gas turbine, thereby achieving partial heat recovery.
In some alternative embodiments, as shown in fig. 8 to 11, fig. 8 shows a schematic structural view of a gas turbine according to still another embodiment of the present invention, fig. 9 to 11 show a schematic structural view of a different embodiment of the combustor in fig. 8, and the combustor 400 further includes a cooling part 460. The cooling part 460 is connected to the first combustion part 420 and is at least partially located at a side of the first combustion part 420 facing the second combustion part 430. In this way, the cooling part 460 can further block the direct baking of the flame of the second combustion part 430 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. Alternatively, as shown in fig. 9 and 10, the cooling portion 460 circumferentially surrounds half of the first combustion portion 420. The semi-surrounding form can reduce material costs and facilitate the arrangement of the intake ports of the first combustion part 420.
Further, the cooling part 460 has a cooling passage therein, and in some embodiments, a gaseous or liquid cooling medium is provided in the cooling passage, so that the cooling part 460 can absorb and soak heat without an external cooling substance, which may be used when the flame height of the second combustion part 430 is not high. In other embodiments, the cooling passage is configured to have a gaseous or liquid cooling medium flowing therethrough, so that the cooling portion 460 functions as a forced cooling, particularly for the cooling in the case of the flame height direct firing of the second combustion portion 430. The two methods can be used in combination.
Further, in the embodiment in which the second combustion portion 430 includes the flue gas plate 432 and the flue gas plate 432 includes the plurality of flue gas plate communication holes, the size of all the flue gas plate communication holes in the axial direction is within the axial size range of the cooling portion 460, so that the range of the flame of the second combustion portion 430 in the axial direction can be controlled to avoid the flame from scorching the end side of the first combustion portion 420 as much as possible.
In some alternative embodiments, as shown in fig. 12, fig. 12 shows a schematic structural view of a gas turbine according to still another embodiment of the present invention, the gas turbine further includes a heating device 480, and the heating device 480 is located in the second combustion part 430. The heating device 480 is used to ignite the solid-containing fuel in the second combustion portion 430 or to assist in igniting the solid-containing fuel.
Further, as shown in FIG. 13, FIG. 13 shows a schematic view of the structure of one embodiment of the combustion chamber of FIG. 12, with a heating device 480 disposed adjacent the charging port 439 of the second combustion portion 430.
Further, the number of the heating devices 480 is plural, and the plural heating devices 480 are arranged around the combustion zone 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, fig. 15 to 18 show a schematic structural view of a different embodiment of the heating device in fig. 13, and 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, reference to the description of the terms "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like 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, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. 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 using specific embodiments, which are presented only to help understand the method and its core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (10)
1. The utility model provides a solid fuel gas turbine with single-cylinder combustion chamber, includes to install in proper order in the axial in compressor and the turbine of pivot, and with the combustion chamber that the end is connected of giving vent to anger of compressor, its characterized in that:
the combustion chamber is a single-cylinder combustion chamber, the combustion chamber is arranged on 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 silo which is used for containing solid fuel.
2. The gas turbine of claim 1, wherein at least a portion of said plenum is located between said first combustion section and said second combustion section, said second combustion section comprising a flue gas panel and communicating with said plenum through said flue gas panel.
3. The gas turbine of claim 1, further comprising a regenerator, wherein the exhaust end of the turbine is connected to the inlet of a first flow channel of the regenerator, the exhaust end of the compressor is connected to the inlet of a second flow channel of the regenerator, the outlet of the second flow channel is connected to the inlet of the plenum, and the first flow channel exchanges heat with the gas in the second flow channel in the regenerator.
4. The gas turbine of claim 2, wherein the combustor comprises a first casing, a second casing, and a third casing,
the second housing surrounds the first combustion part forming a single cylinder shape and has an opening corresponding to the combustion chamber exhaust port at one axial end;
the first housing at least partially encloses the second housing and together therewith defines the plenum;
the second shell is provided with a through hole for communicating the air chamber with the first combustion part;
the third casing is connected to the first casing and extends into the second combustion section;
the flue gas panel is close to the second casing set up in the third casing.
5. The gas turbine according to claim 1, wherein the bunker includes a chamber, a feed inlet, a conveying device, a pressurizing port, and a first injection port, the chamber containing a solid fuel; the feed inlet is positioned on the upper side of the cabin and is provided with an airtight door capable of being opened and closed; the conveying device is positioned at the lower side of the chamber and is connected with the input port of the second combustion part through an output port; the pressurizing port is connected with an air source and introduces pressurized gas into the chamber; the first liquid injection port is connected with a water supply device and injects the liquid containing the solid fuel into the cabin in a wetting mode.
6. The gas turbine according to claim 1, wherein a cooling portion is provided between the second combustion portion and the first combustion portion, the cooling portion being connected to the first combustion portion and being located at least partially on a side of the first combustion portion facing the second combustion portion.
7. The gas turbine according to claim 6, wherein the cooling portion circumferentially completely 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 provided with the gaseous or liquid cooling medium flowing through.
8. The gas turbine according to claim 2, wherein the second combustion section further comprises:
the second liquid injection port extends into the lower part of the smoke plate, is connected with the water supply device and injects liquid into a combustion area of the second combustion part; and/or the presence of a gas in the gas,
and the third liquid injection port is arranged close to the input port, is connected with the water supply device and injects the liquid containing the solid fuel.
9. The gas turbine according to claim 8, wherein when said second combustion portion includes said second liquid injection port, the number of said second liquid injection ports is plural, the plural second liquid injection ports are arranged around a combustion area of said second combustion portion, and the liquid injected through said second liquid injection port is saturated water.
10. A gas turbine according to claim 1, further comprising a fuel tank, the first combustion section being provided with a nozzle, the nozzle being connected to the fuel tank.
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| CN1095810A (en) * | 1993-03-03 | 1994-11-30 | 株式会社荏原制作所 | Pressurized internal circulating fluidized-bed boiler |
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