CN116557141A - Detonation gas turbine with steam circulation system - Google Patents
Detonation gas turbine with steam circulation system Download PDFInfo
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- CN116557141A CN116557141A CN202310370375.6A CN202310370375A CN116557141A CN 116557141 A CN116557141 A CN 116557141A CN 202310370375 A CN202310370375 A CN 202310370375A CN 116557141 A CN116557141 A CN 116557141A
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- detonation
- turbine
- water
- combustion chamber
- cooling
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- 238000005474 detonation Methods 0.000 title claims abstract description 143
- 238000002485 combustion reaction Methods 0.000 claims abstract description 124
- 238000001816 cooling Methods 0.000 claims abstract description 83
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 83
- 239000000498 cooling water Substances 0.000 claims abstract description 54
- 239000007789 gas Substances 0.000 claims abstract description 47
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims abstract description 46
- 239000003546 flue gas Substances 0.000 claims abstract description 46
- 238000010438 heat treatment Methods 0.000 claims abstract description 28
- 239000002918 waste heat Substances 0.000 claims abstract description 5
- 239000000446 fuel Substances 0.000 claims description 5
- 239000007788 liquid Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 239000000779 smoke Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000009833 condensation Methods 0.000 description 2
- 230000005494 condensation Effects 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- 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
- F23R7/00—Intermittent or explosive combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K11/00—Plants characterised by the engines being structurally combined with boilers or condensers
- F01K11/02—Plants characterised by the engines being structurally combined with boilers or condensers the engines being turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
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- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F22—STEAM GENERATION
- F22B—METHODS OF STEAM GENERATION; STEAM BOILERS
- F22B37/00—Component parts or details of steam boilers
Abstract
The invention provides a detonation gas turbine with a steam circulation system, comprising: the detonation combustion chamber is internally provided with a main runner chamber and a cooling channel, wherein the main runner chamber is used for detonation combustion, and the cooling channel is used for cooling the detonation combustion chamber; the combustion device comprises a slow combustion chamber and a first turbine, wherein flue gas outlets of the slow combustion chamber and a detonation combustion chamber are connected to the first turbine; the first inlet of the heating and pressurizing device is connected with the outlet of the cooling channel of the detonation combustion chamber, the second inlet of the heating and pressurizing device is connected with the flue gas outlet of the first turbine, and the cooling water is heated and pressurized again through the waste heat of the flue gas to form supercritical water; the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water pushes the second turbine to do work; the water outlet pipe orifice of the second turbine is connected to the cooling channel inlet of the detonation combustion chamber, so that cooling water flows back to the cooling channel to form a cooling water circulation system. The invention can greatly reduce the system power loss and improve the overall cycle efficiency of the combustion engine.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a detonation gas turbine with a steam circulation system.
Background
A gas turbine is a mechanical device that uses gas energy to generate power. It is generally composed of three parts: gas engines, generators and auxiliary equipment. In a gas engine, gas is compressed, mixed with air, and burned at a high temperature. The high temperature gas generated by combustion flows through the piston to enable the piston to move up and down, thereby driving the rotor to rotate. The rotor is provided with a generator, and the generator can rotate when the rotor rotates to generate electric energy. Auxiliary equipment includes cooling systems, oil systems, exhaust systems, etc., which function to assist the gas engine in proper operation. For example, the cooling system may maintain the temperature of the gas engine within a suitable range; the oil circuit system can provide lubricating oil for the gas engine; the exhaust system may then exhaust the exhaust gas produced by the gas engine.
Detonation combustion (detonation combustion) is a combustion technique that achieves combustion by propagation of detonation waves. Detonation waves are shock waves that propagate in a detonation reaction, enabling the reactants and oxygen to react rapidly after contact. Detonation combustion techniques may be used to increase combustion efficiency, reduce pollution, and operate at higher pressures and temperatures. Detonation combustion technology is currently used in the automotive, aerospace and aerospace fields.
Detonation combustion can greatly improve the overall cycle efficiency of the gas turbine and simultaneously reduce NOx pollutant emissions. However, when using detonation combustors, a great deal of cooling is required due to the great thermal density of detonation combustors, resulting in greater energy being carried away and thus power and efficiency losses.
Disclosure of Invention
In view of this, embodiments of the present application provide a detonation gas turbine with a steam circulation system to achieve the purposes of reducing system power loss and improving overall cycle efficiency of the gas turbine.
The embodiment of the application provides the following technical scheme: a detonation gas turbine with a steam circulation system, comprising:
the detonation combustion chamber is internally provided with a main runner chamber and a cooling channel, wherein the main runner chamber is used for detonation combustion, and cooling water is introduced into the cooling channel and used for cooling the detonation combustion chamber;
the combustion system comprises a slow combustion chamber and a first turbine, wherein flue gas outlets of the slow combustion chamber and the detonation combustion chamber are connected to the first turbine, so that flue gas generated by combustion pushes the first turbine to do work;
the first inlet of the heating and pressurizing device is connected with the outlet of the cooling channel of the detonation combustion chamber, so that cooling water subjected to heat exchange enters the heating and pressurizing device; the second inlet of the heating and pressurizing device is connected with the flue gas outlet of the first turbine, so that flue gas pushing the first turbine to do work enters the heating and pressurizing device, and the cooling water is heated and pressurized again through the waste heat of the flue gas, so that the cooling water reaches a supercritical state, and supercritical water is formed;
the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water pushes the second turbine to do work; the water outlet pipe orifice of the second turbine is connected to the inlet of the cooling channel of the detonation combustion chamber, so that cooling water pushing the second turbine to do work flows back to the cooling channel to form a cooling water circulation system.
According to one embodiment of the present application, the detonation combustion chamber comprises a detonation combustion chamber housing, wherein a detonation outer ring and a detonation inner ring are coaxially sleeved in sequence from outside to inside in an inner cavity of the detonation combustion chamber housing, the detonation outer ring and the detonation inner ring are both in a tubular structure, a main runner annular cavity for performing detonation combustion is formed between annular walls of the detonation outer ring and the detonation inner ring, and an air inlet of the main runner annular cavity is connected with air for enabling the air to be mixed with fuel in the main runner annular cavity for performing detonation combustion;
a first annular cavity is formed between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and cooling water is introduced into the first annular cavity as an outer cooling channel; an inner cooling channel is arranged in the inner cavity of the knocking inner ring, and cooling water is introduced into the inner cooling channel.
According to one embodiment of the present application, the detonation combustion chamber housing further comprises a cooling inner ring, the cooling inner ring is of a columnar structure, and is coaxially sleeved in the inner cavity of the detonation inner ring, so that a second annular cavity is formed between the cooling inner ring and the detonation inner ring, and the second annular cavity forms the inner cooling channel.
According to one embodiment of the present application, the cooling device further comprises a condenser, wherein the condenser is arranged between the water outlet pipe orifice of the second turbine and the cooling channel inlet of the detonation combustion chamber, and is used for condensing the cooling water of the water outlet pipe orifice of the second turbine and then introducing the cooling water into the cooling channel.
According to one embodiment of the present application, the detonation combustor further comprises a circulating pump disposed on a line between an outlet of the condenser and an inlet of a cooling channel of the detonation combustor.
According to one embodiment of the application, the heating and pressurizing device comprises a plurality of water pipes, a reserved gap is arranged between two adjacent water pipes, and the reserved gap forms a smoke cavity.
According to one embodiment of the application, the heating and pressurizing device further comprises a shell, wherein the shell comprises a water storage cavity and a steam cavity, the water storage cavity is respectively arranged on the water inlet side, the steam cavity is arranged on the water outlet side, the water pipe is arranged between the water storage cavity and the steam cavity, the water inlet ends of the water pipe are respectively communicated with the water storage cavity, and the water outlet ends of the water pipe are respectively communicated with the steam cavity;
the water storage cavity is connected with the cooling channel outlet of the detonation combustion chamber through the first inlet, the steam cavity is connected to the second turbine through the first outlet, and the flue gas inlet of the flue gas cavity is connected with the flue gas outlet of the first turbine through the second inlet.
According to one embodiment of the present application, the flue gas outlet of the flue gas chamber is vented to atmosphere.
According to one embodiment of the present application, the first inlet and the first outlet are respectively provided with a control valve.
According to one embodiment of the present application, the engine further comprises a compressor coaxially coupled to the first turbine, an air inlet of the compressor is connected to air, and an air outlet of the compressor is connected to an air inlet of the main runner annular cavity in the detonation combustor and an air inlet of the slow combustion combustor.
The detonation gas turbine provided by the embodiment of the invention adopts the cooling water to sufficiently cool the detonation combustion chamber, and adopts the flue gas waste heat after pushing the first turbine of the gas turbine to do work to heat the cooling water after heat exchange again, so that the cooling water reaches a supercritical state, the generated supercritical water is utilized to do work on the second turbine, and the cooling water after pushing the second work is condensed and then flows back into the cooling channel of the detonation combustion chamber to perform heat exchange again, so that the circulation of the whole system is completed.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least: on the basis of ensuring the cooling effect of the detonation combustion chamber, the embodiment of the invention further heats and pressurizes the cooling water after heat exchange to form supercritical water so as to drive the turbine to do work, and finally returns to the detonation combustion chamber after condensation to recover the energy of cooling loss, thereby greatly reducing the power loss of the system, improving the power utilization rate and further improving the integral circulation efficiency of the combustion engine.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of a detonation gas turbine of an embodiment of the present invention;
FIG. 2 is a schematic diagram of a detonation combustor configuration of an embodiment of the present invention;
FIG. 3 is a schematic diagram of a heating and pressurizing device according to an embodiment of the present invention;
in the figure, the air conditioner comprises a 1-detonation outer ring, a 2-detonation inner ring, a 3-main flow passage chamber, a 4-outer cooling passage, a 5-inner cooling passage, a 6-cooling inner ring, a 7-water pipe, an 8-smoke air chamber, a 9-water storage chamber and a 10-steam chamber.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
As shown in FIG. 1, an embodiment of the present invention provides a detonation gas turbine with a steam circulation system, comprising: the detonation combustion chamber is internally provided with a main runner chamber and a cooling channel, wherein the main runner chamber is used for detonation combustion, and cooling water is introduced into the cooling channel and used for cooling the detonation combustion chamber; the combustion system comprises a slow combustion chamber and a first turbine, wherein flue gas outlets of the slow combustion chamber and the detonation combustion chamber are connected to the first turbine, so that flue gas generated by combustion pushes the first turbine to do work; the first inlet of the heating and pressurizing device is connected with the outlet of the cooling channel of the detonation combustion chamber, so that cooling water subjected to heat exchange enters the heating and pressurizing device; the second inlet of the heating and pressurizing device is connected with the flue gas outlet of the first turbine, so that flue gas pushing the first turbine to do work enters the heating and pressurizing device, and the cooling water is heated and pressurized again through the waste heat of the flue gas, so that the cooling water reaches a supercritical state, and supercritical water is formed; the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water pushes the second turbine to do work; the water outlet pipe orifice of the second turbine is connected to the inlet of the cooling channel of the detonation combustion chamber, so that cooling water pushing the second turbine to do work flows back to the cooling channel to form a cooling water circulation system.
In this embodiment, the gas turbine includes a compressor, an air inlet of the compressor is connected to air, and an air outlet of the compressor is connected to inlets of a conventional slow combustion chamber and a detonation combustion chamber, and is used for compressing the air and then respectively introducing the air into the slow combustion chamber and the detonation combustion chamber. The air and fuel in the slow combustion chamber are mixed and combusted in the combustion chamber to generate high-temperature smoke, the air and fuel in the knocking combustion chamber are subjected to knocking combustion, the high-temperature smoke generated by the slow combustion and the knocking combustion acts on the first turbine, and the first turbine drives the generator to output electric energy to serve as main energy output of the combustion turbine. Because of the relatively high pressure and temperature operating environment within detonation combustors, a cooling system is required to maintain the temperature of the gas engine within a suitable range. Therefore, in the embodiment of the invention, the detonation combustion chamber is provided with the cooling channel for cooling the detonation combustion chamber, and a large amount of cooling can take away more energy, so that power and efficiency are lost.
In order to reduce energy loss, the embodiment is provided with the heating and pressurizing device, the flue gas after the first turbine does work and the cooling water in the cooling channel are introduced, the temperature of the cooling water rises to be lower than the critical water temperature after the cooling water exchanges heat in the detonation combustion chamber, so that the flue gas temperature discharged by the first turbine is 370-540 ℃, the flue gas discharged by the first turbine of the gas turbine is utilized to reheat the cooling water, the flue gas heat energy is fully utilized, the cooling water forms supercritical water, the supercritical water, namely, the water vapor, is utilized to push the second turbine of the gas turbine to do work, and the second turbine is utilized to drive the generator to output power again, so that the power loss is reduced, the circulation efficiency of the whole gas turbine is improved, and the pollutant emission is reduced.
Supercritical water is understood to mean that water is liquid under standard conditions and forms water vapor upon heating. If the temperature and pressure are raised, the property of the liquid is between that of the liquid and gas when the temperature and pressure are raised to the critical point of water from the standard condition, the liquid and the gas can fill the whole space like the gas, but the density of the liquid is similar to that of the liquid, namely the supercritical fluid.
In one implementation of this embodiment, the gas turbine system further includes a condenser, where the condenser is disposed between the water outlet pipe of the second turbine and the cooling channel inlet of the detonation combustor, and is configured to condense cooling water at the water outlet pipe of the second turbine and then pass through the cooling channel. After the supercritical water pushes the second turbine to do work, the water at the outlet of the second turbine is recovered to be in a normal state, is cooled by the condenser and is condensed into cooling water, and then flows into a cooling channel of the detonation combustion chamber to be cooled again
Further, the scheme also comprises a circulating pump, wherein the circulating pump is arranged on a pipeline between the outlet of the condenser and the inlet of the cooling channel of the detonation combustion chamber. Cooling water enters the detonation combustion chamber through the circulating pump to cool, and system circulation is completed.
In another embodiment of the present invention, as shown in fig. 2, the detonation combustion chamber includes a detonation combustion chamber housing, an inner cavity of the detonation combustion chamber housing is coaxially sleeved with a detonation outer ring and a detonation inner ring in sequence from outside to inside, the detonation outer ring and the detonation inner ring are both in tubular structures, the main runner annular cavity for performing detonation combustion is formed between annular walls of the detonation outer ring and the detonation inner ring, and an air inlet of the main runner annular cavity is connected with air for mixing the air with fuel in the main runner annular cavity for performing detonation combustion; a first annular cavity is formed between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and cooling water is introduced into the first annular cavity as an outer cooling channel; an inner cooling channel is arranged in the inner cavity of the knocking inner ring, and cooling water is introduced into the inner cooling channel.
In this embodiment, adopt the coaxial structure setting of knocking combustion chamber casing, knocking outer loop 1 and knocking inner loop 2, the annular chamber that forms between knocking outer loop 1 and the knocking inner loop 2 is as carrying out the main runner annular chamber 3 of knocking combustion, set up first annular chamber as outer cooling channel 4 at the knocking outer loop 1 outer lane simultaneously, set up interior cooling channel 5 at the inner circle of knocking inner loop 2, both layers all set up circulating flow's cooling water in the inside and outside of main runner annular chamber 3, can be quick carries out the cooling to the knocking combustion chamber, cooling effect has been improved by a wide margin, can guarantee the steady operation of knocking combustion chamber for a long time, and the thermal deformation that the combustion chamber temperature risees and leads to has been reduced to a great extent, the axiality and the precision of combustion chamber annular chamber structure have been guaranteed.
In this scheme, still set up cooling inner ring 6 in the detonation combustion chamber casing, cooling inner ring 6 is columnar structure, and coaxial cup joint in the inner chamber of detonation inner ring 2, make cooling inner ring 6 with form the second ring chamber between the detonation inner ring 2, the second ring chamber constitutes interior cooling channel 5.
In another embodiment of the present invention, as shown in fig. 3, the heating and pressurizing device includes a plurality of water pipes 7, and a reserved gap is disposed between two adjacent water pipes 7, and the reserved gap forms a smoke chamber 8. The flue gas discharged by the first turbine is introduced into the flue gas cavity 8, the flue gas surrounds the outer walls of the plurality of water pipes 7, and fully exchanges heat with cooling water in the water pipes 7, so that the cooling water is further heated and pressurized to reach a critical water state.
When the scheme is implemented, the heating and pressurizing device further comprises a shell, wherein the shell comprises a water storage cavity 9 and a steam cavity 10, the water storage cavity 9 is arranged on the water inlet side, the steam cavity 10 is arranged on the water outlet side, the water pipe 7 is arranged in the water storage cavity 9 and the steam cavity 10, the water inlet end of the water pipe 7 is respectively communicated with the water storage cavity 9, and the water outlet end of the water pipe 7 is respectively communicated with the steam cavity 10; the water storage cavity 9 is connected with the cooling channel outlet of the detonation combustion chamber through the first inlet, the steam cavity 10 is connected with the second turbine through the first outlet, and the flue gas inlet of the flue gas cavity 8 is connected with the flue gas outlet of the first turbine through the second inlet.
In the scheme, the water storage cavity 9 and the steam cavity 10 are respectively arranged at the two sides in the shell, the introduced cooling water firstly enters the water storage cavity 9, the cooling water can be ensured to uniformly enter each water pipe 7, and the flue gas can be ensured to uniformly and fully contact and exchange heat with the cooling water in the structural arrangement; the heated water vapor is collected by the vapor chamber 10 and then discharged. The temperature of the flue gas after heat exchange is reduced, so that the flue gas outlet of the flue gas cavity 8 is filled with the atmosphere.
In this scheme, still further, the first entry with set up control valve respectively on the first export. In order to ensure that the cooling water and the flue gas in the heating and pressurizing device are fully subjected to heat exchange, the control valves of the first inlet and the first outlet can be closed for a preset time, so that the cooling water and the flue gas are fully contacted and subjected to heat exchange within a period of time, and the cooling water reaches a critical water state.
In other embodiments of the present invention, a plurality of detonation combustors may be disposed in the gas turbine, and the detonation combustors are circumferentially distributed inside a casing of the gas turbine. In order to realize detonation combustion, the height of a combustion chamber channel can only be adjusted in a small range in the prior detonation combustion chamber structure, so that a single narrow channel is required to be formed when the detonation combustion chamber structure is applied to an engine with slightly higher power, the large-diameter circular ring structure is very difficult to process and manufacture, the precision is difficult to guarantee, and the temperature of the combustion chamber is increased to cause thermal deformation in a working state, so that the coaxiality and the precision of the full-channel large-diameter circular ring are further greatly deteriorated. In addition, because the working range of the detonation combustion chamber is narrower, for example, the setting point power is 100, the detonation combustion chamber can only realize detonation combustion in the range of 90-100, and the gas turbine needs to stably work in the larger range of 0-100, so compared with the traditional detonation combustion engine with a single large-diameter combustion chamber, the structure of a plurality of combustion chambers is convenient for cooling, and meanwhile, the start and stop of any detonation combustion chamber can be controlled, so that the power regulation of the gas turbine in a larger range is realized, the combustion efficiency is effectively improved, the processing difficulty is reduced, and the structural design precision is ensured.
The gas turbine system provided by the embodiment of the invention can rapidly cool the detonation combustion chamber through the outer cooling channel and the inner cooling channel arranged in the detonation combustion chamber, so that the cooling effect is greatly improved, the long-time stable operation of the detonation combustion chamber is ensured, the thermal deformation caused by the temperature rise of the combustion chamber is greatly reduced, and the coaxiality and the precision of the annular cavity structure of the combustion chamber are ensured. Meanwhile, on the basis of guaranteeing the cooling effect of the detonation combustion chamber, the cooling water after heat exchange is further heated and pressurized to form supercritical water so as to push the turbine to do work, finally, the cooling water flows back to the detonation combustion chamber after condensation, the energy of cooling loss is recovered, the power loss of the system is reduced to a great extent, the power utilization rate is improved, and the overall cycle efficiency of the combustion engine is further improved.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A detonation gas turbine with a steam circulation system, comprising:
the detonation combustion chamber is internally provided with a main runner chamber and a cooling channel, wherein the main runner chamber is used for detonation combustion, and cooling water is introduced into the cooling channel and used for cooling the detonation combustion chamber;
the combustion system comprises a slow combustion chamber and a first turbine, wherein flue gas outlets of the slow combustion chamber and the detonation combustion chamber are connected to the first turbine, so that flue gas generated by combustion pushes the first turbine to do work;
the first inlet of the heating and pressurizing device is connected with the outlet of the cooling channel of the detonation combustion chamber, so that cooling water subjected to heat exchange enters the heating and pressurizing device; the second inlet of the heating and pressurizing device is connected with the flue gas outlet of the first turbine, so that flue gas pushing the first turbine to do work enters the heating and pressurizing device, and the cooling water is heated and pressurized again through the waste heat of the flue gas, so that the cooling water reaches a supercritical state, and supercritical water is formed;
the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water pushes the second turbine to do work; the water outlet pipe orifice of the second turbine is connected to the inlet of the cooling channel of the detonation combustion chamber, so that cooling water pushing the second turbine to do work flows back to the cooling channel to form a cooling water circulation system.
2. The detonation gas turbine according to claim 1, wherein the detonation combustion chamber comprises a detonation combustion chamber shell, a detonation outer ring and a detonation inner ring are coaxially sleeved in sequence from outside to inside in an inner cavity of the detonation combustion chamber shell, the detonation outer ring and the detonation inner ring are of tubular structures, the main runner annular cavity for detonation combustion is formed between annular walls of the detonation outer ring and the detonation inner ring, and an air inlet of the main runner annular cavity is connected with air for enabling the air to be mixed with fuel in the main runner annular cavity for detonation combustion;
a first annular cavity is formed between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and cooling water is introduced into the first annular cavity as an outer cooling channel; an inner cooling channel is arranged in the inner cavity of the knocking inner ring, and cooling water is introduced into the inner cooling channel.
3. The detonation gas turbine of claim 2, wherein the detonation combustor casing further includes a cooling inner ring therein, the cooling inner ring having a cylindrical configuration and being coaxially sleeved within an inner cavity of the detonation inner ring such that a second annular cavity is formed between the cooling inner ring and the detonation inner ring, the second annular cavity forming the inner cooling channel.
4. The detonation gas turbine of claim 1, further comprising a condenser disposed between the water outlet orifice of the second turbine and the cooling channel inlet of the detonation combustor for condensing the cooling water from the water outlet orifice of the second turbine before passing into the cooling channel.
5. The detonation gas turbine of claim 4, further comprising a circulation pump disposed on a conduit between an outlet of the condenser and a cooling channel inlet of the detonation combustor.
6. The detonation gas turbine of claim 1, wherein the heating and pressurizing device comprises a plurality of water pipes, a reserved gap is arranged between two adjacent water pipes, and the reserved gap forms a flue gas cavity.
7. The detonation gas turbine of claim 6, wherein the heating and pressurizing device further comprises a shell, wherein the shell comprises a water storage cavity and a steam cavity, the water storage cavity is arranged on a water inlet side and the steam cavity is arranged on a water outlet side, the water pipe is arranged between the water storage cavity and the steam cavity, the water inlet end of the water pipe is respectively communicated with the water storage cavity, and the water outlet end of the water pipe is respectively communicated with the steam cavity;
the water storage cavity is connected with the cooling channel outlet of the detonation combustion chamber through the first inlet, the steam cavity is connected to the second turbine through the first outlet, and the flue gas inlet of the flue gas cavity is connected with the flue gas outlet of the first turbine through the second inlet.
8. The detonation gas turbine of claim 7, wherein a flue gas outlet of the flue gas chamber is vented to atmosphere.
9. The detonation gas turbine of claim 7, wherein a control valve is disposed on each of the first inlet and the first outlet.
10. The detonation gas turbine of claim 1, further comprising a compressor coaxially coupled to the first turbine, an air inlet of the compressor accessing air, an air outlet of the compressor connecting an air inlet of the primary flowpath annular chamber in the detonation combustor and an air inlet of the slow combustion chamber.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310370375.6A CN116557141A (en) | 2023-04-07 | 2023-04-07 | Detonation gas turbine with steam circulation system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310370375.6A CN116557141A (en) | 2023-04-07 | 2023-04-07 | Detonation gas turbine with steam circulation system |
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| CN116557141A true CN116557141A (en) | 2023-08-08 |
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| CN202310370375.6A Pending CN116557141A (en) | 2023-04-07 | 2023-04-07 | Detonation gas turbine with steam circulation system |
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| Country | Link |
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| CN (1) | CN116557141A (en) |
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