A high efficiency initiator suitable for liquid fuels

Abstract

The purpose of this invention is to provide a high-efficiency detonator suitable for liquid fuel, comprising an outer wall surface, a middle wall surface, an inner wall surface, a liquid fuel atomizing nozzle, and a flexible barrier. The outer wall surface is located outside the middle wall surface, forming a liquid fuel inlet. The middle wall surface is located outside the inner wall surface, forming an air inlet. The liquid fuel atomizing nozzle is located inside the outer wall surface and installed at the end of the inner wall surface. The inner wall surface forms the combustion chamber. The flexible barrier is installed between the middle and inner wall surfaces. This invention enhances the mixing of liquid fuel and air, prevents liquid fuel from adhering to the inner wall surface and affecting combustion, and solves the problem of large amounts of liquid fuel remaining after collision with the windward side of the barrier. Ultimately, it promotes liquid fuel combustion and strengthens the transition process from slow combustion to detonation, thus having significant application value.

Description

Technical Field

[0001] The present invention relates to an initiator, specifically a gas turbine initiator. Background Technology

[0002] Traditional gas turbines are based on the Brayton cycle, and their combustion chambers employ isobaric combustion. The large entropy change during combustion significantly limits further improvements in the thermal efficiency of the gas turbine cycle. Currently, the thermal efficiency of traditional gas turbine cycles is approaching its limit, necessitating research into novel thermodynamic cycle technologies. Detonation combustion possesses advantages such as self-pressurization, low entropy change, and rapid heat release. Applying detonation combustion technology to gas turbines would enable them to achieve the high thermal efficiency of isochoric heating cycles, potentially increasing the overall thermal efficiency by approximately 20%.

[0003] Current research on detonation combustion technology mainly focuses on gaseous fuels. Compared to gaseous fuels, liquid fuels have advantages such as easy storage and high energy density. Therefore, detonation combustion technology based on liquid fuels has a wider range of application prospects. However, how to achieve reliable and efficient initiation of liquid fuels is the most important challenge for the engineering application of liquid fuel detonation combustion technology. Therefore, there is an urgent need for an initiation device suitable for liquid fuels. An initiator is a commonly used device for realizing detonation waves. The initiator's working process is as follows: fuel and air enter the initiator, forming a combustible mixture. The air and fuel supply is then shut off, and ignition occurs within the initiator, forming a laminar flame. Continuous perturbation of the flame accelerates the flame propagation process, ultimately promoting the formation of a detonation wave. During the transition from slow combustion to detonation, flame perturbation is extremely important for the detonation wave transition. Currently, most initiators use solid obstacles to perturb the flame. However, current detonators are not suitable for liquid fuels, especially since solid obstacles can block most of the liquid fuel from spreading within the detonator, forcing the fuel to adhere to the windward side of the obstacle. This results in a reduction of fuel downstream of the detonator, making it impossible to form a detonation wave or even causing the detonator to shut down. Summary of the Invention

[0004] The purpose of this invention is to provide a high-efficiency detonator suitable for liquid fuel that can enhance the mixing between liquid fuel and air, prevent liquid fuel from adhering to the inner wall of the detonator and affecting combustion, and solve the problem of a large amount of liquid fuel remaining due to collision between liquid fuel and the windward side of obstacles.

[0005] The objective of this invention is achieved as follows:

[0006] This invention discloses a high-efficiency detonator suitable for liquid fuel, characterized by comprising an outer wall surface, a middle wall surface, an inner wall surface, a liquid fuel atomizing nozzle, and a flexible barrier. The outer wall surface is located outside the middle wall surface, forming a liquid fuel inlet. The middle wall surface is located outside the inner wall surface, forming an air inlet. The liquid fuel atomizing nozzle is located inside the outer wall surface and installed at the end of the inner wall surface. The inner wall surface forms the combustion chamber. The flexible barrier is installed between the middle wall surface and the inner wall surface.

[0007] The present invention may also include:

[0008] 1. The liquid fuel atomizing nozzle includes a liquid fuel cyclone separator, an air cyclone separator, and an auxiliary atomizer. The air cyclone separator is installed outside the liquid fuel cyclone separator. The rear of the liquid fuel cyclone separator is connected to the liquid fuel inlet. The air cyclone separator and the inner wall surface of the detonator outside it form an outer air loop. An air ring cavity is formed between the air cyclone separator and the inner wall surface of the detonator behind it. The air ring cavity is connected to the air inlet through a hole on the inner wall surface of the detonator. The air cyclone separator includes a first air channel and a second air channel. The second air channel is located outside the first air channel. The air ring cavity is connected to the outer air loop, the first air channel, and the second air channel respectively.

[0009] 2. Auxiliary atomizing air holes are provided on the wall surface of the liquid fuel cyclone separator.

[0010] 3. The flexible barrier includes an air obstruction hole and a liquid fuel obstruction hole. The air obstruction hole is matched with the channel where the air inlet is located, and a flexible barrier inlet baffle is provided behind it. The liquid fuel obstruction hole is matched with the channel where the liquid fuel inlet is located, and a liquid fuel atomizing nozzle inlet baffle is provided in the channel where the liquid fuel inlet is located.

[0011] 4. During the liquid obstacle flow stage, the nozzle inlet baffle is closed and the flexible obstacle inlet baffle is opened, controlling air or liquid fuel to enter the detonator combustion chamber through the flexible obstacle, forming a flexible obstacle and thus accelerating the flame.

[0012] 5. When using liquid fuel barriers, the liquid fuel inlet is opened, and the liquid fuel enters through the flow channel between the middle wall and the outer wall of the detonator, and enters the combustion chamber of the detonator through the liquid fuel barrier hole, forming a liquid fuel barrier.

[0013] 6. When using an air obstruction, the air inlet is opened, and air enters through the flow channel between the middle wall of the detonator and the inner wall of the detonator, and enters the combustion chamber of the detonator through the air obstruction hole, forming an air obstruction.

[0014] 7. When using a gas-liquid mixture obstruction, the liquid fuel inlet switch and the air inlet are opened simultaneously. Liquid fuel and air enter the detonator combustion chamber through the fuel obstruction hole and the air obstruction hole, respectively, forming a gas-liquid mixture obstruction.

[0015] 8. The flexible obstacle consists of at least two sections, and the detonator of different lengths is formed by combining different numbers of flexible obstacles.

[0016] The advantages of this invention are as follows: By using a liquid fuel cyclone separator and a two-stage reverse air cyclone separator, and by using air and fuel to enter in opposite directions, this invention improves the atomization, mixing, and uniformity of liquid fuel distribution; by designing an outer air ring, the liquid fuel is purged and propagated downstream, preventing it from adhering to the inner wall of the initiator combustion chamber head; and by designing flexible barriers, the problem of liquid fuel being obstructed by barriers is solved while ensuring accelerated flame propagation, ultimately achieving the goal of efficient initiation of liquid fuel. Attached Figure Description

[0017] Figure 1 This is a cross-sectional view of the present invention;

[0018] Figure 2 This is a cross-sectional view of a liquid fuel atomizing nozzle.

[0019] Figure 3 This is a schematic diagram of an air cyclone separator;

[0020] Figure 4 This is a cross-sectional view of the air cyclone separator AA.

[0021] Figure 5 This is a schematic diagram of a flexible obstacle.

[0022] Figure 6 This is a cross-sectional view of the flexible obstacle BB. Detailed Implementation

[0023] The invention will now be described in more detail with reference to the accompanying drawings:

[0024] Combination Figure 1-6The present invention comprises a liquid fuel atomizing nozzle 1, an initiator combustion chamber 8, a flexible barrier 4, an inner wall surface of the initiator 5, a middle wall surface of the initiator 6, and an outer wall surface of the initiator 7; the flexible barrier 4 comprises an air channel 4-1, a liquid fuel channel 4-4, an air obstruction hole 4-2, a liquid fuel obstruction hole 4-3, and a flexible barrier air inlet baffle 4-5; the liquid fuel atomizing nozzle 1 comprises a liquid fuel cyclone separator 1-1, an air cyclone separator 1-2, and a liquid fuel atomizing nozzle inlet baffle 3. The igniter can ignite the combustible mixture of liquid fuel and air inside the detonator; the liquid fuel cyclone separator 1-1 can promote the atomization of liquid fuel; the two-stage counter-cyclone separator can enhance the atomization and mixing of fuel droplets and ensure a more uniform distribution of liquid fuel; the outer air channel 1-3 can effectively prevent fuel droplets from propagating to the head wall of the detonator combustion chamber 8, prevent droplets from adhering to the inner wall 5 of the detonator, and purge the liquid fuel downstream, which can also promote the mixing between fuel and air; the flexible barrier 4 can ensure sufficient disturbance to the flame and accelerate flame propagation. Under the premise of propagation, it also solves the problem of obstacles hindering the propagation of liquid fuel, ensuring sufficient combustible mixture downstream of the initiator combustion chamber 8; the flexible obstacle 4 can realize various obstacle modes such as air obstacle, liquid fuel obstacle, and gas-liquid mixture obstacle, and by adjusting the flow rate of fuel and air, it can obtain obstacles of different sizes to meet the needs of different working conditions; the design of reverse propagation of air and liquid fuel enables air and fuel to obtain the heat released by combustion, heating the fuel and air, and ultimately achieving the purpose of stable and efficient initiation of liquid fuel.

[0025] Air obstruction orifices 4-2 and liquid fuel obstruction orifices 4-3 are arranged alternately to control the air and liquid fuel inlet switches, enabling three modes: air obstruction, liquid fuel obstruction, and gas-liquid mixture obstruction. The flexible obstruction 4 adopts a segmented design, and different lengths of initiators can be obtained by combining different numbers of flexible obstructions 4. The air in the flexible obstruction 4 is divided into two paths: one part of the air enters the initiator combustion chamber 8 through the air obstruction orifice 4-2, and the other part enters the adjacent flexible obstruction 4 through the air channel 4-1. The liquid fuel is also divided into two paths: one part of the liquid fuel enters the initiator combustion chamber 8 through the liquid fuel obstruction orifice 4-3, and the other part enters the adjacent flexible obstruction 4 through the liquid fuel channel 4-4. By controlling the flow rate of air and liquid fuel and adjusting the jet depth, obstructions of different sizes can be obtained to meet the requirements of various fuels and various working conditions. Therefore, there is no need to replace the obstructions, simplifying the process and saving time.

[0026] Air swirlers 1-2 enter the detonator combustion chamber 8 in four directions. The first and second directions are introduced through a two-stage reverse swirler, the third direction is introduced through an auxiliary atomizing air hole, and the fourth direction is introduced through an outer air ring channel, forming an annular air film to prevent liquid fuel from adhering to the wall of the combustion chamber head.

[0027] Air and liquid fuel flow in opposite directions, absorbing the heat conducted in the combustion chamber and promoting the atomization and combustion of the liquid fuel.

[0028] The main working process of this invention is as follows: the initiator inflation stage, the flexible obstacle 4 flow stage, ignition, slow combustion to detonation wave formation stage.

[0029] During the initiator charging stage, to ensure that both liquid fuel and air enter the initiator combustion chamber 88 only through the nozzles, the inlet baffle 4-5 of the flexible barrier 4 is closed, and the inlet baffle 3 of the liquid fuel atomizing nozzle 1 is opened. Liquid fuel enters through the flow channel between the intermediate wall 6 and the outer wall 7 of the initiator. It flows through the liquid fuel channel 4-4, past adjacent barriers, to the liquid fuel atomizing nozzle 1, and finally enters the initiator combustion chamber 8 through the liquid fuel swirl generator 1-1. Air enters through the flow channel between the intermediate wall 6 and the inner wall 5 of the initiator. It propagates through the air channel 4-1, past adjacent barriers, to the atomizing nozzle 1, and finally enters the initiator combustion chamber 8 through the air swirl generator 1-2. The air channel 4-1 consists of several circumferentially evenly distributed through-holes, while the liquid fuel channel 4-4 is an annular channel.

[0030] like Figure 2 As shown in the cross-sectional view of the liquid fuel atomizing nozzle 1, air enters the detonator combustion chamber 8 through four parts. Air path 1 and air path 2 enter from the first and second swirler channels of the air swirlers 1-2, respectively. The first and second swirlers are dual-stage counter-swirlers, a design that not only enhances the atomization effect of the liquid fuel but also makes the mixing of liquid fuel and air more uniform. Furthermore, this invention employs a design of reverse flow of both liquid fuel and air channels. Since the detonator is used repeatedly, even in pulse detonation, the fuel combustion within the detonator releases a large amount of energy. The counter-flow design allows the liquid fuel and air to gain heat through thermal conduction and radiation, thereby enhancing combustion and promoting detonation wave formation.

[0031] The air cyclone 1-2 of this invention also includes an auxiliary atomizing air channel 4-1. Air enters the nozzle through the auxiliary atomizing air hole 1-4 and is mixed with the liquid fuel entering through the liquid fuel cyclone 1-1 in advance in the nozzle, thereby playing a role in assisting the atomization of the liquid fuel.

[0032] The air cyclone device 1-2 of this invention also includes an outer air channel 1-3. Air enters the detonator combustion chamber 8 through the outer air channel 1-3, forming an annular gas film to block the propagation of liquid fuel to the inner wall of the detonator. This can effectively prevent liquid fuel from adhering to the inner wall of the detonator head and promote the propagation of the combustible mixture downstream of the detonator combustion chamber 88.

[0033] Solid obstacles can hinder the propagation of liquid fuel within the combustion chamber, causing a large amount of liquid fuel to accumulate on the windward side of the solid obstacle. The liquid obstacle designed in this invention can effectively solve this problem. The flexible obstacle 4 designed in this invention includes three modes: air obstacle, liquid fuel obstacle, and gas-liquid mixture obstacle.

[0034] During the flow around a liquid obstacle, such as Figure 5 As shown in the schematic diagram of the flexible barrier 4, the nozzle inlet baffle 3 is closed, and the flexible barrier 4 inlet baffle 4-5 is opened. This allows air or liquid fuel to enter the combustion chamber 8 of the detonator through the flexible barrier 4, forming the flexible barrier 4 and thus accelerating the flame. Furthermore, the flexible barrier 4 designed in this invention is a segmented design, and several flexible barriers 4 can be combined to obtain detonators of different lengths, meeting more application requirements.

[0035] When using liquid fuel barriers, the liquid fuel inlet switch is opened, and liquid fuel enters through the flow channel between the middle wall 6 and the outer wall 7 of the detonator, and enters the combustion chamber 8 of the detonator through the liquid fuel barrier hole 4-3, forming a liquid fuel barrier.

[0036] When an air obstruction is used, the air inlet switch is opened, and air enters through the flow channel between the intermediate wall 6 and the inner wall 5 of the detonator, and enters the combustion chamber 8 of the detonator through the air obstruction hole 4-2, thus forming an air obstruction.

[0037] When a gas-liquid mixture barrier is used, the liquid fuel inlet switch and the air inlet switch are opened simultaneously. As mentioned above, liquid fuel and air enter the detonator combustion chamber 8 through the fuel barrier hole 4-3 and the air barrier hole 4-2, respectively, forming a gas-liquid mixture barrier.

[0038] Because solid obstacles have fixed dimensions, and each size is typically only suitable for one type of fuel or operating condition, traditional detonators often require replacement of the solid obstacle when changing fuels or operating conditions, a cumbersome process. However, the flexible obstacle 4 designed in this invention can adjust the obstacle jet depth by regulating the flow rate of liquid fuel and air, obtaining obstacles of different sizes to meet the needs of different fuels and operating conditions. This eliminates the need to replace the obstacle, simplifying the workflow and saving working time.

[0039] Ignition 2 is turned on, igniting the combustible mixture in the combustion chamber 8 of the detonator, forming a laminar flame. Under the continuous disturbance of the flexible barrier 4, the flame accelerates continuously, promoting the formation of the detonation wave, and finally completing the detonation of the liquid fuel.

Claims

1. A high-efficiency detonator suitable for liquid fuels, characterized in that: It includes an outer wall surface of the detonator, a middle wall surface of the detonator, an inner wall surface of the detonator, a liquid fuel atomizing nozzle, and a flexible barrier. The outer wall surface of the detonator is located outside the middle wall surface of the detonator, and the two form a liquid fuel inlet. The middle wall surface of the detonator is located outside the inner wall surface of the detonator, and the two form an air inlet. The liquid fuel atomizing nozzle is located inside the outer wall surface of the detonator and installed at the end of the inner wall surface of the detonator. The inner wall surface of the detonator is the combustion chamber of the detonator. The flexible barrier is installed between the middle wall surface and the inner wall surface of the detonator. The liquid fuel atomizing nozzle includes a liquid fuel cyclone separator, an air cyclone separator, and an auxiliary atomizer. The air cyclone separator is installed outside the liquid fuel cyclone separator, and the rear of the liquid fuel cyclone separator is connected to the liquid fuel inlet. The air cyclone separator and the inner wall surface of the detonator outside it form an outer air loop. An air ring cavity is formed between the air cyclone separator and the inner wall surface of the detonator behind it. The air ring cavity is connected to the air inlet through a hole on the inner wall surface of the detonator. The air cyclone separator includes a first air channel and a second air channel. The second air channel is located outside the first air channel. The air ring cavity is connected to the outer air loop, the first air channel, and the second air channel respectively. The flexible obstruction includes an air obstruction orifice and a liquid fuel obstruction orifice. The air obstruction orifice cooperates with the channel where the air inlet is located. A flexible obstruction inlet baffle is provided behind the air obstruction orifice and the liquid fuel obstruction orifice. The liquid fuel obstruction orifice cooperates with the channel where the liquid fuel inlet is located. A liquid fuel atomizing nozzle inlet baffle is provided in the channel where the liquid fuel inlet is located.

2. The high-efficiency detonator suitable for liquid fuel according to claim 1, characterized in that: Auxiliary atomizing air holes are provided on the wall surface of the liquid fuel cyclone separator.

3. A high-efficiency detonator suitable for liquid fuel according to claim 1, characterized in that: in During the flexible barrier formation stage, the inlet baffle of the liquid fuel atomizing nozzle is closed, and the inlet baffle of the flexible barrier is opened, controlling air or liquid fuel to enter the combustion chamber of the detonator through the flexible barrier, forming a flexible barrier and thus accelerating the flame.

4. The high-efficiency detonator suitable for liquid fuel according to claim 1, characterized in that: When liquid fuel obstruction is used, the liquid fuel inlet is opened, and the liquid fuel enters through the flow channel between the middle wall and the outer wall of the detonator, and enters the combustion chamber of the detonator through the liquid fuel obstruction hole, forming a liquid fuel obstruction.

5. A high-efficiency detonator suitable for liquid fuel according to claim 1, characterized in that: When an air obstruction is used, the air inlet is opened, and air enters through the flow channel between the middle wall of the detonator and the inner wall of the detonator, and enters the combustion chamber of the detonator through the air obstruction hole, thus forming an air obstruction.

6. A high-efficiency detonator suitable for liquid fuel according to claim 1, characterized in that: When a gas-liquid mixture barrier is used, the liquid fuel inlet switch and the air inlet are opened simultaneously. Liquid fuel and air enter the detonator combustion chamber through the liquid fuel barrier hole and the air barrier hole, respectively, forming a gas-liquid mixture barrier.

7. A high-efficiency detonator suitable for liquid fuel according to claim 1, characterized in that: The flexible barrier consists of at least two sections, and by combining different numbers of flexible barriers, detonators of different lengths can be formed.

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