CN116398906B - Combustion chamber and combustion control method - Google Patents
Combustion chamber and combustion control method Download PDFInfo
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- CN116398906B CN116398906B CN202310391625.4A CN202310391625A CN116398906B CN 116398906 B CN116398906 B CN 116398906B CN 202310391625 A CN202310391625 A CN 202310391625A CN 116398906 B CN116398906 B CN 116398906B
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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
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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
- 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
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The application relates to the technical field of gas turbines, in particular to a combustion chamber and a combustion control method, wherein the combustion chamber comprises a detonation combustion chamber positioned at the central axis of the combustion chamber; the combustion control method comprises the steps of gradually expanding and decoupling after detonation waves are transmitted from an outlet of the detonation combustion cavity to form leading shock waves, and igniting fuel sprayed by the main combustion nozzle by utilizing the leading shock waves and blocking backfire of the main combustion nozzle. According to the application, after the detonation wave is transmitted from the outlet of the detonation combustion chamber, the detonation wave is gradually expanded and decoupled to form the leading shock wave, the leading shock wave is rapidly transmitted along the downstream of the flame tube, when the fuel used by the main combustion nozzle is tempered, the flame reversely propagates and contacts and collides with the leading shock wave, under the barrier effect of the leading shock wave, the flame stops propagating near the contact surface with the leading shock wave, the tempering is prevented, the burning loss of the combustion chamber is avoided, and the safe, stable and efficient combustion of the combustion chamber is facilitated.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustion chamber and a combustion control method.
Background
With the continuous development of industrial technology, gas turbines have been widely used in various industries such as energy, electricity, ships and aviation. In the aeronautical and marine industries, gas turbines typically use liquid fuels. Heavy duty gas turbines for power generation typically use gaseous fuels such as natural gas and, to meet emission standards, typically employ dry premixed combustion to control flame face temperature and reduce pollutant emissions, but premixed combustion presents a flashback risk. At present, the domestic gas turbine is used for completing the adaptive transformation of natural gas hydrogen-doped combustion, and gas turbine suppliers at home and abroad are also focusing on developing a gas turbine which takes hydrogen as fuel completely. However, the hydrogen is easy to temper during premixed combustion, and the combustion chamber is burnt and even the gas turbine is damaged when serious.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects that when a gas turbine adopts a natural gas hydrogen-doped premixed combustion mode, the gas turbine is easy to temper, the combustion chamber is easy to burn and damage, and even the gas turbine is damaged.
In order to achieve the above object, the present invention provides a combustion chamber comprising:
The device comprises an air inlet head, a detonation combustion chamber and a flame tube which are connected in sequence, wherein the detonation combustion chamber is positioned at the central axis of a combustion chamber and is suitable for pulse detonation combustion;
the main combustion nozzles are arranged around the detonation combustion chamber, one ends of the main combustion nozzles are connected with the air inlet head part, and the other ends of the main combustion nozzles are connected with the flame tube;
the intake header is adapted to provide fuel to a detonation combustion chamber and a plurality of primary combustion nozzles.
Optionally, the outlets of the plurality of main combustion nozzles are arranged at an angle to the central axis of the detonation combustion chamber, the outlets of the plurality of main combustion nozzles incline to the central axis of the detonation combustion chamber, the angle range is 30-60 degrees, and the outlets of the main combustion nozzles are arranged beyond the outlet of the detonation combustion chamber.
Optionally, the air intake head comprises:
The first fuel cavity is communicated with an inlet arranged at the closed end on the detonation combustion cavity through a first pipeline, and the first fuel cavity is respectively communicated with a plurality of main combustion nozzles through a plurality of third pipelines;
The second fuel cavity is connected with the first fuel cavity, and is communicated with an inlet arranged at the upper closed end of the detonation combustion cavity through a second pipeline, and the second fuel cavity is respectively communicated with a plurality of main combustion nozzles through a plurality of fourth pipelines.
Optionally, the first fuel cavity is of a cylindrical hollow structure, and the second fuel cavity is of a hollow circular ring structure.
Optionally, the fuel in the first fuel cavity is natural gas, and the fuel in the second fuel cavity is hydrogen.
Optionally, flow valves are respectively arranged on the first pipeline, the second pipeline, the third pipeline and the fourth pipeline.
Optionally, a plurality of first air inlet holes are circumferentially arranged on the knocking combustion chamber at a position close to the closed end, and the first air inlet holes are suitable for providing air into the knocking combustion chamber;
An explosion-increasing barrier is arranged in the detonation combustion chamber;
And the steady flow plate is suitable for blocking expansion waves and fuel gas diffused by the detonation combustion cavity from propagating in the reverse direction and limiting the expansion waves and the fuel gas diffused from propagating to the downstream of the flame tube.
Optionally, the main combustion nozzle comprises:
A fuel section consisting of a cylindrical cavity and a conical cavity in communication, the fuel section being adapted to be fed with fuel; a plurality of cyclones are arranged on the periphery of the fuel section, blades of the cyclones are hollow, and the blades are communicated with the fuel section through conveying holes;
the air section is sleeved on the peripheries of the fuel section and the cyclone, air is contained in the air section, the blades are communicated with the air section through fuel holes, the air section is communicated with the flame tube, the inlet of the air section is circular, and the outlet of the air section is fan-shaped.
Optionally, the method further comprises:
The flame tube comprises a flame tube, a casing, a plurality of second air inlets, a plurality of first air inlets, a plurality of second air inlets and a plurality of second air inlets, wherein the casing is sleeved on the periphery of the flame tube at intervals and connected with the air inlet head, and the casing is connected with the flame tube through an air inlet plate;
The flame tube is sleeved on the peripheries of the main combustion nozzles at intervals and connected with the main combustion nozzles through support plates;
The detonation combustion chamber is characterized in that an air supply chamber is sleeved on the periphery of the detonation combustion chamber, one side of the air supply chamber, which is close to the closed end of the detonation combustion chamber, is connected with an air supply pipeline, and one side of the air supply chamber, which is close to the open end of the detonation combustion chamber, is provided with a third air inlet hole;
the air supply cavity is connected with a plurality of main combustion nozzles through a support plate;
the support plate is provided with a plurality of fourth air inlets which are suitable for leading part of air in the middle cavity into the flame tube.
The invention also provides a combustion control method, which uses the combustion chamber to burn, comprising the following steps:
And the pilot shock wave is utilized to ignite the fuel sprayed by the main combustion nozzle and prevent the tempering of the main combustion nozzle.
Compared with the prior art, the technical scheme of the invention has the following advantages:
1. The application provides a combustion chamber which comprises an air inlet head, a detonation combustion chamber and a flame tube which are sequentially connected, wherein the detonation combustion chamber is positioned at the central axis of the combustion chamber and is suitable for pulse detonation combustion, a plurality of main combustion nozzles are arranged around the detonation combustion chamber, one ends of the main combustion nozzles are connected with the air inlet head, the other ends of the main combustion nozzles are connected with the flame tube, and the air inlet head is suitable for providing fuel for the detonation combustion chamber and the main combustion nozzles. Meanwhile, the fresh premixed gas of the main combustion nozzle is subjected to strong compression of the leading shock wave to raise temperature and raise pressure, is ignited by high-temperature fuel gas after the leading shock wave, and can continuously ignite fresh mixed gas transmitted from the main combustion nozzle; because the detonation wave parameters are determined to have stability by the detonation combustion characteristics, under the same air supply and ignition conditions, the pressure, speed and other parameters of the detonation wave are not greatly different, so that the detonation combustion cavity is used as an on-duty nozzle, and the detonation combustion cavity can stably ignite fresh mixed air in the flame tube and stabilize a fire source as the traditional on-duty nozzle continuously burns. After the detonation wave is transmitted from the outlet of the detonation combustion chamber, the detonation wave is gradually expanded and decoupled to form a leading shock wave, and the leading shock wave is quickly propagated along the downstream of the flame tube, when the fuel used by the main combustion nozzle is tempered, flame is reversely propagated and is contacted and collided with the leading shock wave, and the leading shock wave has high pressure and high speed and holds higher energy, and the propagation directions of the leading shock wave and the flame are opposite, so that the flame can stop propagating near the contact surface of the leading shock wave under the barrier effect of the leading shock wave, the tempering is prevented, the burning loss of the combustion chamber is avoided, and the safe, stable and efficient combustion of the combustion chamber is facilitated. In addition, because detonation combustion occurs in a semi-enclosed small space, ignition energy is low, and compared with a combustion chamber of a traditional gas turbine, the detonation combustion device has lower requirements on ignition electrodes.
2. According to the technical scheme, when fuel gas downstream of the main combustion nozzles is sprayed out of the main combustion nozzles, the fuel gas moves along the direction close to the central axis of the flame tube, the velocity direction can be decomposed into a component parallel to the central axis of the flame tube and moving downstream of the flame tube and a first component perpendicular to the central axis of the flame tube and moving inwards in the radial direction, and the velocity direction of detonation wave and wave generated by the detonation combustion chambers can be decomposed into a component parallel to the central axis of the flame tube and a second component perpendicular to the central axis of the flame tube and moving outwards in the radial direction, so that the two perpendicular first components and the second component can cancel each other, the fuel gas after the main combustion nozzles is spread downstream of the flame tube in parallel to the central axis of the flame tube, and the fuel gas is uniformly distributed in the flame tube, and the uniformity of the temperature distribution of the outlet of the combustion chamber is ensured.
3. The application adopts the technical scheme that the detonation combustion characteristics and the fuel types have a great relationship, different types of fuels can be supplied to the main combustion nozzles and the detonation combustion chambers by arranging the first fuel chamber and the second fuel chamber, and the gas turbine can automatically switch and select fuel supply in different working stages within the range allowed by the change of fuel white index, so that the safety, stability and economy of the gas turbine are improved when the gas turbine operates, and the performance of the gas turbine is optimized.
4. The application adopts the technical scheme that the first fuel cavity is of a cylindrical hollow structure, the second fuel cavity is of a hollow circular ring structure, and enough installation spaces are reserved for the first pipeline, the second pipeline, the third pipeline and the fourth pipeline through the middle gap of the hollow circular ring structure.
5. According to the technical scheme, the combustion chamber can support the main combustion nozzle to burn with all natural gas or natural gas in a hydrogen-doped combustion range within the allowed range of the fuel bloom index, and can also support the detonation combustion chamber to burn with all hydrogen, all natural gas or natural gas in a hydrogen-doped combustion range.
6. By adopting the technical scheme, the application controls the on-off of the pipeline and the fuel flow through the flow valves, and can automatically switch the fuel supply of the gas turbine in different working stages and adjust the fuel flow and the proportion within the range allowed by the fuel white index change, thereby optimizing the performance of the gas turbine and improving the combustion safety, stability and economy of the gas turbine.
7. The application adopts the technical scheme that the detonation wave self-sustained downstream propagation is formed by accelerating the detonation transition to the detonation through the explosion increasing barrier, air is provided to the detonation combustion chamber through the first air inlet, when the detonation wave carries the gas to spread out from the outlet, the diffusion expansion wave and the gas can be prevented from reversely propagating by playing a physical blocking role by the flow stabilizing plate, and the gas is prevented from propagating downstream of the combustion chamber.
8. The main combustion nozzle comprises a fuel section, an air section, a flame tube and a circular air section inlet and an air outlet, wherein the fuel section consists of a communicated cylindrical cavity and a conical cavity, the fuel section is suitable for being filled with fuel, a plurality of swirlers are arranged on the periphery of the fuel section, blades of the swirlers are hollow and are communicated with the fuel section through delivery holes, the air section is sleeved on the periphery of the fuel section and the swirlers, air is contained in the air section and is communicated with the air section through the fuel holes, the air section is communicated with the flame tube, and the air section inlet is circular, and the air outlet is fan-shaped.
9. The combustion chamber provided by the application further comprises a casing, a spacer sleeve is arranged on the periphery of the flame tube, the casing is connected with the air inlet head, the casing is connected with the flame tube through an air inlet plate, the air inlet plate is arranged close to the air inlet head, a plurality of second air inlets are formed in the air inlet plate, the second air inlets are suitable for enabling air between the casing and the flame tube to be communicated into a middle cavity formed between the air inlet head and the flame tube, the flame tube spacer sleeve is arranged on the periphery of the plurality of main combustion nozzles and connected with the flame tube through a support plate, an air supply cavity is sleeved on the periphery of the flame tube and connected with an air supply pipeline, one side of the air supply cavity close to the closed end of the detonation combustion cavity is provided with a third air inlet, the third air inlet is suitable for enabling air in the air supply cavity to be communicated into the flame tube, the air supply cavity is connected with the plurality of main combustion nozzles through a support plate, the fourth air inlet is arranged on the support plate, the air supply cavity is suitable for enabling air to flow into the flame tube through the fourth air inlet hole, and the air supply cavity is suitable for cooling the flame tube through the fourth air inlet hole through the middle cavity.
10. The combustion control method comprises the steps of gradually expanding and decoupling after a detonation wave is transmitted from an outlet of the detonation combustion chamber to form a leading shock wave, igniting fuel sprayed out of a main combustion nozzle by the leading shock wave and blocking backfire of the main combustion nozzle, gradually expanding and decoupling after the detonation wave is transmitted from the outlet of the detonation combustion chamber to form the leading shock wave, rapidly spreading along the downstream of the flame tube, and reversely spreading flame and contacting and colliding with the leading shock wave when the fuel used by the main combustion nozzle is backfire, wherein the pressure of the leading shock wave is high and the speed is high, the leading shock wave has higher energy, and the spreading directions of the leading shock wave and the leading shock wave are opposite, so that the flame stops spreading near the contact surface with the leading shock wave under the blocking action of the leading shock wave, backfire is prevented, the combustion chamber is prevented from being burnt, and the combustion chamber is beneficial to safety, stability and high efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic perspective view of a combustion chamber according to an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of a combustion chamber provided in an embodiment of the present invention;
fig. 3 is a schematic right-view structure of a combustion chamber provided in an embodiment of the present invention.
Reference numerals illustrate:
1. a first inlet; 2, a first fuel cavity, 3, a second inlet, 4, a second fuel cavity, 5, a first pipeline, 6, a second pipeline, 7, an inlet, 8, a third pipeline, 9, a fourth pipeline, 10, a fuel section, 11, a detonation combustion cavity, 12, an air inlet hole, 13, an explosion increasing barrier, 14, an air supply cavity, 15, an air inlet plate, 16, a support plate, 17, an air section, 18, a flow stabilizing plate, 19, an air film hole, 20, a mixing hole, 21, a flame tube, 22, a casing, 23, a cyclone, 24, a flange, 25, a second air inlet hole, 26, a middle cavity, 27, a third air inlet hole, 28 and a fourth air inlet hole.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected via an intervening medium, or in communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
One specific embodiment of the combustion chamber shown in fig. 1 to 3 comprises an air inlet head, a detonation combustion chamber 11 and a flame tube 21 which are sequentially connected, six main combustion nozzles uniformly distributed around the detonation combustion chamber 11, and a casing 22 which is sleeved on the periphery of the flame tube 21 at intervals.
As shown in fig. 1, the casing 22 is connected to the intake head by a flange 24.
As shown in fig. 1 and 2, the detonation combustion chamber 11 is located at a central axis of the combustion chamber, and pulse detonation combustion is adapted to occur in the detonation combustion chamber 11. Pulse detonation combustion is an unsteady combustion mode that utilizes intermittent detonation waves to generate thrust. Compared with the common slow combustion, the pulse detonation combustion has the advantages of strong chemical reaction, high thermal cycle efficiency and the like. In general, the pulse detonation combustion chamber has a simple structure similar to a long straight cylinder, one end of the pulse detonation combustion chamber is a closed end, the other end of the pulse detonation combustion chamber is an open end, fuel and oxidant enter from the closed end of the long straight cylinder and are ignited by an igniter to generate detonation waves, the detonation waves are self-sustained to propagate downstream to perform unstable self-boosting combustion, and expansion decoupling is performed after the detonation waves are transmitted from an outlet (namely the open end) of the detonation tube to perform an exhaust process so as to prepare for the next detonation combustion. The front ends of the six main combustion nozzles are connected to an inlet header, the rear ends of which are connected to a flame tube 21, said inlet header being adapted to supply fuel to the detonation combustion chamber 11 and to the six main combustion nozzles. The outlets of the six main combustion nozzles are arranged at an angle with the central axis of the detonation combustion chamber 11, the outlets of the six main combustion nozzles incline to the central axis of the detonation combustion chamber 11, the angle range is 30-60 degrees, and the outlets of the main combustion nozzles are arranged beyond the outlet of the detonation combustion chamber 11.
The air inlet head comprises a first fuel cavity 2 and a second fuel cavity 4 which are connected, the first fuel cavity 2 is of a cylindrical hollow structure, the second fuel cavity 4 is of a hollow circular ring structure, fuel in the first fuel cavity 2 is natural gas, fuel in the second fuel cavity 4 is hydrogen, a first inlet 1 is formed in the first fuel cavity 2 to be filled with the natural gas, two opposite second inlets 3 are formed in the second fuel cavity 4 to be filled with the hydrogen, the natural gas is used as a main fuel, and the hydrogen is used as an auxiliary fuel. The first fuel cavity 2 is communicated with an inlet 7 arranged at the closed end of the detonation combustion cavity 11 through a first pipeline 5, the first fuel cavity 2 is respectively communicated with six main combustion nozzles through six third pipelines 8, the second fuel cavity 4 is communicated with the inlet 7 arranged at the closed end of the detonation combustion cavity 11 through a second pipeline 6, and the second fuel cavity 4 is respectively communicated with six main combustion nozzles through six fourth pipelines 9. Further, flow valves are provided in the first, second, third and fourth pipes 5, 6, 8 and 9, respectively. Specifically, the flow valve is a servo flow valve.
The detonation combustion chamber 11 is provided with a plurality of first air inlets 12 in the circumferential direction at the position close to the closed end, the first air inlets 12 are suitable for providing air into the detonation combustion chamber 11, the detonation combustion chamber 11 is provided with a detonation obstacle 13, the detonation combustion chamber 11 is provided with a flow stabilizing plate 18 at the position close to the outlet of the opening end, and the flow stabilizing plate 18 is suitable for blocking expansion waves and fuel gas diffused by the detonation combustion chamber 11 from reversely spreading and limiting the expansion waves and fuel gas diffused from spreading to the downstream of the flame tube 21. Specifically, the stabilizer 18 has a thin annular shape.
The main combustion nozzle comprises a fuel section 10 and an air section 17. The fuel section 10 consists of a cylindrical cavity at the front end and a conical cavity at the rear end which are communicated, the fuel section 10 is suitable for being filled with fuel, a plurality of swirlers 23 are arranged on the periphery of the fuel section 10, blades of the swirlers 23 are hollow and are communicated with the fuel section 10 through delivery holes, the air section 17 is sleeved on the periphery of the fuel section 10 and the swirlers 23, air is contained in the air section 17, the blades are communicated with the air section 17 through two fuel holes, and the air section 17 is communicated with the flame tube 21. Specifically, the air section 17 has a circular cross section at the front and a circular cross section at the rear, and is a transition section from a circular cross section to a fan-shaped cross section, the six transition sections are uniformly distributed along the circumference, and the outlets of the six transition sections form an included angle of 30-60 degrees with the central axis of the detonation combustion chamber 11.
As shown in fig. 2 and 3, the casing 22 is connected to the flame tube 21 through the air inlet plate 15, and specifically, the air inlet plate 15 is welded to the flame tube 21. The air inlet plate 15 is arranged close to the air inlet head, a plurality of second air inlet holes 25 are formed in the air inlet plate 15, the second air inlet holes 25 are suitable for leading air between the casing 22 and the flame tube 21 into an intermediate cavity 26 formed between the air inlet head and the flame tube 21, the air inlet plate 15 is in a circular ring shape, the second air inlet holes 25 are strip-shaped air holes, a plurality of air film holes 19 are further formed in the periphery of the flame tube 21 so as to cool the wall surface of the flame tube 21, and a plurality of mixing holes 20 are formed in the periphery of the flame tube 21 close to the outlet position so as to adjust the temperature distribution of a combustion chamber outlet. The flame tube 21 is sleeved on the periphery of the six main combustion nozzles at intervals, the flame tube 21 is connected with the six main combustion nozzles through the support plate 16, the periphery of the detonation combustion chamber 11 is sleeved with an air supply chamber 14, one side of the air supply chamber 14, which is close to the closed end of the detonation combustion chamber 11, is connected with an air supply pipeline, and air from a gas compressor enters the air supply pipeline. The air supply chamber 14 is provided with a third air inlet 27 at a side close to the open end of the detonation combustion chamber 11, and the third air inlet 27 is suitable for leading air in the air supply chamber 14 into the flame tube 21, namely, part of air in the air supply chamber 14 supplies air into the detonation combustion chamber 11 through the first air inlet 12, and the other part of air supplies air into the flame tube 21 through the third air inlet 27. The air supply cavity 14 is connected with six main combustion nozzles through a support plate 16, a plurality of fourth air inlet holes 28 are arranged on the support plate 16, and the fourth air inlet holes 28 are suitable for leading part of air in the middle cavity 26 into the flame tube 21. Air between the casing 22 and the flame tube 21 is transmitted from the compressor to the air at the tail of the casing 22. Air sent out from the outlet of the air compressor reaches the tail part of the casing 22 and sequentially enters the mixing hole 20 and the air film hole 19, the rest air enters the middle cavity 26 through the strip-shaped air hole on the air inlet plate 15, then enters the flame tube 21 to be internally involved in combustion through the fourth air inlet hole 28 and the air section 17 on the support plate 16, and most of the air enters the flame tube 21 to be internally involved in combustion through the air section 17.
The fuel enters the detonation combustion chamber 11 through the first pipeline 5 and the second pipeline 6, meanwhile, air from the air compressor enters the detonation combustion chamber 11 through the first air inlet hole 12, after being uniformly mixed with the air, the fuel is ignited to burn by an igniter, the common slow combustion rapidly develops into detonation combustion in a narrow combustion space, then the detonation wave rapidly evolves into detonation combustion through the explosion increasing barrier 13, the detonation wave is formed to be self-sustained and spread along the downstream of the detonation combustion chamber 11, finally, the detonation wave is transmitted from the outlet of the detonation combustion chamber 11, and is expanded and decoupled to form a leading shock wave, the leading shock wave is spread around in the flame tube 21, and the leading shock wave immediately follows high-temperature fuel gas and is spread together with the leading shock wave. The detonation combustion chamber 11 is used as a duty nozzle, and when the detonation combustion chamber is in a reasonable fuel proportioning range and can excite stable detonation waves in an ignition frequency range of an igniter, namely a stable ignition source is formed, the gas supply process of the main combustion nozzle is started. The fuel enters the fuel section 10 of the main combustion nozzle through the third pipeline 8 and the fourth pipeline 9, enters the blades of the cyclone 23 through the conveying holes, finally enters the air section 17 of the main combustion nozzle through the two fuel holes at the blades of the cyclone 23, meanwhile, air enters the air section 17 of the main combustion nozzle through the middle cavity 26, the two air sections are mixed at the cyclone 23, after the effect of the cyclone 23, the two air sections are mixed more uniformly, a stable backflow area is formed, fresh premixed gas propagates to the central axis of the flame tube 21 at an angle of 30-60 degrees through the outlet of the air section 17 of the main combustion nozzle, and in the propagation process, the fresh premixed gas is heated up and is ignited by high-temperature fuel gas after the front shock wave, so that the main combustion nozzle is combusted stably. Fresh premixed gas continuously passes out of the outlet of the air section 17 of the main combustion nozzle, detonation waves are continuously transmitted out of the outlet of the detonation combustion cavity 11 and decoupled to form a leading shock wave, and the leading shock wave carries high-temperature fuel gas and can timely ignite the fresh premixed gas, so that the combustion chamber continuously and stably works.
The invention also provides a combustion control method, which utilizes the combustion chamber to burn, and comprises the steps of gradually expanding and decoupling after detonation wave is transmitted from an outlet of the detonation combustion chamber 11 to form leading shock waves, and utilizing the leading shock waves to ignite fuel sprayed by the main combustion nozzle and obstruct tempering of the main combustion nozzle. Furthermore, by changing the ignition frequency of the detonation combustion chamber 11, a specific number of detonation waves and leading shock waves can be excited in a specific time period, and when the number is enough, the leading shock waves which are continuously propagated collide with the backfire flame continuously, so that backfire can be effectively prevented, and the safe, stable and efficient combustion of the combustion chamber is facilitated. When backfire occurs and the ignition frequency reaches a limit value and more detonation waves cannot be excited, the proportion of hydrogen in the main combustion nozzle can be reduced, the proportion of natural gas is increased, the backfire probability is reduced, and meanwhile, the proportion of hydrogen in the detonation combustion cavity 11 is increased, because detonation waves generated by detonation combustion of the hydrogen are faster in speed and higher in pressure, the temperature, pressure and speed of fuel gas after detonation are higher, the formed leading shock wave parameters are also increased, and the blocking effect on backfire flame is better. The type, flow and proportion of the fuel are changed by adjusting the servo flow valve, so that the combustion chamber optimizes the combustion organization process in different working phases, and the combustion safety, stability and economy of the gas turbine are improved.
The combustion control process of the combustion chamber is briefly described as follows:
In the initial stage of combustion, to ensure safe and stable detonation combustion, natural gas is only supplied to the detonation combustion chamber 11, and when the natural gas combustion can stably excite a detonation wave, a servo flow valve on the second pipeline 6 is opened and hydrogen is gradually supplied to the detonation combustion chamber 11, and the natural gas flow is reduced until the detonation combustion chamber 11 can completely combust the hydrogen to generate a detonation wave.
After the detonation combustion chamber 11 has stabilized the combustion of hydrogen, the supply of natural gas into the main combustion nozzle is started, with the detonation combustion chamber 11 igniting the fresh premix gas coming out through the main combustion nozzle. After the main combustion nozzle continuously and stably burns, the gas turbine can increase the output force, at the moment, the hydrogen flow of the detonation combustion chamber 11 is kept unchanged, the natural gas inlet amount of the main combustion nozzle is increased, and the output force is increased by burning more fuel through the main combustion nozzle. When the gas turbine reaches the set hydrogen-adding rotation speed or the set outlet temperature of the combustion chamber and can burn stably, the servo flow valve on the fourth pipeline 9 is opened and automatically adjusts the hydrogen flow, and meanwhile, the servo flow valve on the third pipeline 8 automatically adjusts the natural gas flow, and the hydrogen is mixed into the natural gas for burning until the gas turbine reaches the rated rotation speed. In the process of proportioning hydrogen, the white index of the mixed fuel is required to be always kept within an allowable fluctuation range.
In the process of adding hydrogen to the main combustion nozzle, the servo flow valve on the second pipeline 6 is controlled to reduce the flow of hydrogen entering the detonation combustion chamber 11 and improve the natural gas flow, and because the proportion of the hydrogen in the premixed gas sprayed out of the main combustion nozzle is increased, the chemical property of fresh mixed gas becomes more active and is easier to ignite, so that less hydrogen is required to generate high-energy detonation waves, and the detonation waves excited during the combustion of the natural gas and hydrogen mixed fuel can quickly and effectively ignite the mixed gas of the main combustion nozzle. In view of the fact that the price of hydrogen is higher than that of natural gas, the combustion control method can optimize the flow and the proportion of the natural gas and the hydrogen in different combustion stages, so that the combustion economy of the gas turbine is improved, pollutant emission is optimized, and the environment is protected.
Before the main combustion nozzle supplies the gas, the detonation combustion chamber 11 needs to be capable of stably combusting hydrogen to generate detonation wave, because the detonation wave speed of the hydrogen detonation combustion is faster than that of the detonation wave excited by the natural gas detonation combustion, the pressure is higher, and the temperature, the pressure and the speed of the post-combustion gas are all at higher level, so that the pre-mixing gas of the natural gas and the air sent out by the main combustion nozzle can be more conveniently ignited.
When the main combustion nozzle is charged with hydrogen, tempering occurs and the ignition frequency reaches a limit value, and more detonation waves cannot be excited, the proportion of hydrogen in the detonation combustion chamber 11 needs to be increased, and leading shock waves with stronger energy are excited so as to prevent tempering. In the process of adding hydrogen to the main combustion nozzle, the hydrogen in the detonation combustion chamber 11 is reduced proportionally along with the increase of the adding hydrogen, and the combustion control methods in the two cases conflict, so that the hydrogen proportion in the detonation combustion chamber 11 should be preferentially increased, tempering is prevented, the safety of the gas turbine is protected, and the hydrogen proportion is not reduced for the reasons of economy of combustion and the like.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present invention.
Claims (9)
1. A combustion chamber, comprising:
The combustion device comprises an air inlet head, a detonation combustion chamber (11) and a flame tube (21) which are sequentially connected, wherein the detonation combustion chamber (11) is positioned at the central axis of the combustion chamber, and pulse detonation combustion is suitable for being carried out in the detonation combustion chamber (11);
a plurality of main combustion nozzles are arranged around the detonation combustion chamber (11), one ends of the main combustion nozzles are connected with the air inlet head part, and the other ends of the main combustion nozzles are connected with the flame tube (21);
the intake header is adapted to provide fuel to a detonation combustion chamber (11) and a plurality of primary combustion nozzles;
The intake head includes:
The first fuel cavity (2) is communicated with an inlet (7) arranged at the closed end on the detonation combustion cavity (11) through a first pipeline (5), and the first fuel cavity (2) is respectively communicated with a plurality of main combustion nozzles through a plurality of third pipelines (8);
The second fuel cavity (4) is connected with the first fuel cavity (2), the second fuel cavity (4) is communicated with an inlet (7) arranged at the upper closed end of the detonation combustion cavity (11) through a second pipeline (6), and the second fuel cavity (4) is respectively communicated with a plurality of main combustion nozzles through a plurality of fourth pipelines (9).
2. The combustor according to claim 1, wherein outlets of the plurality of main combustion nozzles are arranged at an angle to a central axis of the detonation combustion chamber (11), the outlets of the plurality of main combustion nozzles are inclined to the central axis of the detonation combustion chamber (11) in the range of 30-60 degrees, and the outlets of the main combustion nozzles are arranged beyond the outlets of the detonation combustion chamber (11).
3. The combustion chamber according to claim 1, characterized in that the first fuel chamber (2) is of cylindrical hollow structure and the second fuel chamber (4) is of hollow annular structure.
4. The combustion chamber according to claim 1, characterized in that the fuel in the first fuel chamber (2) is natural gas and the fuel in the second fuel chamber (4) is hydrogen.
5. A combustion chamber according to claim 1, characterized in that flow valves are provided in the first (5), second (6), third (8) and fourth (9) lines, respectively.
6. A combustion chamber according to any one of claims 1-5, characterized in that a plurality of first air inlet holes (12) are circumferentially provided in said detonation combustion chamber (11) at a position near the closed end, said first air inlet holes (12) being adapted to provide air into said detonation combustion chamber (11);
an explosion-increasing barrier (13) is arranged in the detonation combustion chamber (11);
A flow stabilizing plate (18) is arranged at an outlet, close to the opening end, of the detonation combustion cavity (11), and the flow stabilizing plate (18) is suitable for blocking expansion waves and fuel gas diffused by the detonation combustion cavity (11) from propagating in the reverse direction and limiting the expansion waves and the fuel gas diffused from propagating to the downstream of the flame tube (21).
7. The combustor of any one of claims 1-5, wherein the main combustion nozzle comprises:
The fuel section (10) consists of a communicated cylindrical cavity and a conical cavity, wherein the fuel section (10) is suitable for being filled with fuel, a plurality of cyclones (23) are arranged on the periphery of the fuel section (10), blades of the cyclones (23) are hollow, and the blades are communicated with the fuel section (10) through delivery holes;
The air section (17) is sleeved on the peripheries of the fuel section (10) and the cyclone (23), air is contained in the air section (17), the blades are communicated with the air section (17) through fuel holes, the air section (17) is communicated with the flame tube (21), and the inlet of the air section (17) is circular, and the outlet of the air section is fan-shaped.
8. The combustor according to any one of claims 1 to 5, further comprising:
The flame tube comprises a flame tube (21), a casing (22), a plurality of second air inlets (25), a plurality of air inlets (25) and a plurality of air inlets (26), wherein the casing (22) is sleeved on the periphery of the flame tube (21) at intervals, the casing (22) is connected with the air inlet head, the casing (22) is connected with the flame tube (21) through an air inlet plate (15), the air inlet plate (15) is arranged close to the air inlet head, and the second air inlets (25) are suitable for introducing air between the casing (22) and the flame tube (21) into an intermediate cavity (26) formed between the air inlet head and the flame tube (21);
The flame tube (21) is sleeved on the peripheries of the main combustion nozzles at intervals, and the flame tube (21) is connected with the main combustion nozzles through the support plate (16);
An air supply cavity (14) is sleeved on the periphery of the detonation combustion cavity (11), one side, close to the closed end of the detonation combustion cavity (11), of the air supply cavity (14) is connected with an air supply pipeline, and one side, close to the open end of the detonation combustion cavity (11), of the air supply cavity (14) is provided with a third air inlet hole (27), and the third air inlet hole (27) is suitable for leading air in the air supply cavity (14) into the flame tube (21);
the air supply cavity (14) is connected with a plurality of main combustion nozzles through a support plate (16);
A plurality of fourth air inlet holes (28) are arranged on the support plate (16), and the fourth air inlet holes (28) are suitable for leading part of air in the middle cavity (26) into the flame tube (21).
9. A combustion control method for combustion using the combustion chamber according to any one of claims 1 to 8, comprising:
After the detonation wave is transmitted from the outlet of the detonation combustion chamber (11), the detonation wave is gradually expanded and decoupled to form a leading shock wave, and the leading shock wave is utilized to ignite the fuel sprayed by the main combustion nozzle and obstruct the tempering of the main combustion nozzle.
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| US20110126510A1 (en) * | 2009-11-30 | 2011-06-02 | General Electric Company | Pulse detonation combustor |
| CN104153884B (en) * | 2014-08-06 | 2015-10-28 | 西安热工研究院有限公司 | A kind of rotation pinking gas turbine |
| JP2017146062A (en) * | 2016-02-19 | 2017-08-24 | 国立大学法人名古屋大学 | Rotation detonation engine |
| CN105972638B (en) * | 2016-05-26 | 2018-06-19 | 西北工业大学 | A kind of reverse-flow type pulse detonation combustor |
| US11674476B2 (en) * | 2017-06-09 | 2023-06-13 | General Electric Company | Multiple chamber rotating detonation combustor |
| CN111664022B (en) * | 2020-06-16 | 2021-06-18 | 中国人民解放军国防科技大学 | Combustion chamber of rotary detonation ramjet engine with fuel injection |
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