A kind of air-breathing pulse detonation combustion chamber and its detonation method
By designing a new suction pulse detonation combustion chamber, a stable detonation wave is formed using thermal insulation panels and flame transfer notches, the problem of detonation of air and aviation kerosene is solved, ignition and detonation under low energy conditions is achieved, and the engine structure is simplified. Improved thrust-to-weight ratio.
Patent Information
- Application Number
- CN202211322262.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-10-27
- Publication Date
- 2024-12-10
- Estimated Expiration
- 2042-10-27
AI Technical Summary
In aspirated pulse-detonation engine, it is difficult for air and aviation kerosene to detonate efficiently and stably, and the existing heating systems are complex and difficult to achieve.
Design a new suction type pulse detonation combustion chamber, including a semicircular main pre-detonation tube, a secondary pre-detonation tube, a valve-free flame tube, an ignition device and an annular main detonation tube, using thermal insulation The partition plate and flame transfer notch form stable knock waves, simplifying the structure to achieve knock combustion of air and aviation kerosene.
The ignition and detonation of air and aviation kerosene under low ignition energy conditions simplifies the engine structure, reduces weight and increases the thrust-to-weight ratio.
Smart Images
Figure CN115682034B_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of pulse detonation engines, and in particular relates to an air-breathing pulse detonation combustion chamber and a detonation method thereof. Background Art
[0002] The pulse detonation engine is a new type of power device that uses intermittent detonation waves to generate thrust. It has the potential theoretical advantages of simple structure and high thermal efficiency, and has attracted widespread attention from countries around the world. Among them, the pulse detonation engine that is applied within the atmosphere and uses air flow to organize detonation combustion is also called an air-breathing pulse detonation engine.
[0003] In the research field of air-breathing pulse detonation engines, how to efficiently ignite and detonate air and aviation kerosene has always been a difficult problem that researchers want to overcome. At present, the main way to make air and aviation kerosene detonate is to preheat the air and aviation kerosene so that both are in a high-energy state, and then use a high-energy igniter to ignite and detonate. The biggest disadvantage of this method is that it requires a large and complex heating system installed between the engine intake and the combustion chamber. However, this detonation method is difficult to achieve for air-breathing pulse detonation engines. Summary of the invention
[0004] The present invention is based on the problem that air and aviation kerosene cannot be detonated efficiently and stably in an air-breathing pulse detonation combustion chamber, and a new type of pulse detonation combustion chamber is designed to realize the detonation combustion of air and aviation kerosene in a simple structure. It mainly includes: a circulation structure of the new detonation combustion chamber, and an ignition and detonation method thereof.
[0005] The technical solution of the present invention is:
[0006] An air-breathing pulse detonation combustion chamber mainly comprises a main pre-detonation tube (3), a secondary pre-detonation tube (1), a valved flame-linking tube (2), a valveless flame-linking tube (5), an ignition device (4) and an annular main detonation tube (6), characterized in that: the main pre-detonation tube (3) and the secondary pre-detonation tube (1) are located inside the combustion chamber, are semicircular cylinders, and are connected through the valved flame-linking tube (2) at the head; the annular main detonation tube (6) is located outside the combustion chamber, and is respectively connected to the tails of the main pre-detonation tube (3) and the secondary pre-detonation tube (1) through the valveless flame-linking tube (5); the interior of the annular main detonation tube (6) is divided into a plurality of detonation combustion areas by an insulating baffle (7), each insulating baffle (7) has a flame transmission gap (8), and the flame transmission gaps (8) are periodically alternately arranged to ensure that a stable detonation wave has been formed at the position of each flame transmission gap (8).
[0007] The semicircular main pre-detonation tube (3), the auxiliary pre-detonation tube (1) and the annular main detonation tube (6) are of the same length and form a compact cylindrical structure as a whole, thereby greatly improving the space utilization rate of the combustion chamber.
[0008] The annular main detonation tube (6) is an integrated structure with a simple structure. The heat insulating partition (7) divides the inner area of the annular main detonation tube (6) into equal parts, ensuring that the detonation combustion characteristics of each area are basically the same.
[0009] The ignition device (4) ignites only once when the combustion chamber is started, and the subsequent cycle controls the detonation of the main pre-explosion tube (3) by opening and closing the valve-connected flame tube (2).
[0010] The main pre-explosion tube (3) is only filled with a mixture of oxygen and aviation kerosene at startup, and is always filled with a mixture of air and aviation kerosene during the following cycle. The other combustion chambers are always filled with a mixture of air and aviation kerosene.
[0011] Beneficial Effects
[0012] The beneficial effect of the present invention is that after adopting the new detonation combustion chamber, the air-breathing pulse detonation engine can realize the ignition and detonation of air and aviation kerosene under low ignition energy conditions. This combustion chamber greatly simplifies the structure of the air-breathing pulse detonation engine, reduces the weight of the engine, and thus improves the thrust-to-weight ratio of the engine. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 : Schematic diagram of the working cycle process of the present invention
[0014] Figure 2 : Side view of the detonation combustion chamber outlet
[0015] Figure 3 : Main view of detonation combustion chamber, including: 1- auxiliary pre-detonation tube, 2- valved flame tube, 3- main pre-detonation tube, 4- ignition device, 5- valveless flame tube, 6- annular main detonation tube, 7- insulation baffle, 8- flame transfer gap, 9- oil and gas supply schematic device. DETAILED DESCRIPTION
[0016] The present invention will now be further described in conjunction with the embodiments and drawings.
[0017] like Figure 2 , 3As shown, the air-intake pulse detonation combustion chamber of the present invention is cylindrical in shape as a whole, and is divided into two parts: a semicircular main pre-detonation tube (3) in the center, a secondary pre-detonation tube (1), and an outer ring main detonation tube (6). In the pre-detonation tube related structure, the main pre-detonation tube (3) and the secondary pre-detonation tube (1) are semicircular in shape. The main pre-detonation tube (3) and the secondary pre-detonation tube (1) are both provided with oil and gas supply schematic devices (9) at the head. The main pre-detonation tube (3) and the secondary pre-detonation tube (1) are connected through a valved flame-linking tube (2) at the head, and the valved flame-linking tube (2) controls the flame transfer process between the two pre-detonation tubes. The ignition device (4) is located on the main pre-detonation tube (3), and is located above the valved flame-linking tube (2). The inside of the annular main detonation tube (6) is divided into six detonation combustion areas by an insulating baffle (7). The detonation combustion areas are diffracted by heat transfer notches (8) on the insulating baffle (7). The flame transfer notches (8) are periodically distributed at the head and tail of the detonation combustion area so as to diffract stable detonation waves. The tails of the main pre-detonation tube (3) and the auxiliary pre-detonation tube (1) are connected to the tails of two adjacent detonation combustion areas of the annular main detonation tube (6) through a straight valveless flame-crossing tube (5), and there is no flame transfer notch (8) on the insulating baffle (7) between the two detonation combustion areas. The valveless flame-crossing tube (5) not only plays a role in detonation wave diffraction, but also plays a role in supporting the entire structure of the main pre-detonation tube (3) and the auxiliary pre-detonation tube (1). The front end of the annular main detonation tube (6) is equipped with six oil and air supply schematic devices (9) to supply air and aviation kerosene to the six detonation combustion areas respectively.
[0018] Working cycle process
[0019] The detonation cycle process of a continuous detonation multi-tube pulse detonation combustion chamber cycle structure is as follows Figure 1As shown, it can be expressed as follows: when the combustion chamber is started, the valve body (5) of the valved flame tube (2) remains closed, the ignition device (4) ignites the mixture of aviation kerosene and oxygen in the main pre-detonation tube (3), and the resulting detonation wave propagates toward the tail of the main pre-detonation tube (3). Most of the detonation wave is discharged through the outlet of the main pre-detonation tube (3), and a part of the detonation wave propagates through the valveless flame tube (5) to the first detonation combustion area of the annular main detonation tube (6). At this time, the first detonation combustion area of the annular main detonation tube (6) is filled with air and aviation kerosene, and the detonation wave causes this detonation combustion area to be detonated. The detonation combustion is rapidly carried out in the annular main detonation tube (6), and a new detonation wave is generated from the head of the area and propagates toward the outlet direction of the annular detonation tube (6), wherein a small part of the detonation wave propagates to the next detonation combustion area through the tail flame transmission gap (8), and the mixture of aviation kerosene and air in the new detonation combustion area is detonated from the tail, and the generated new detonation wave first propagates to the head of the annular main detonation tube (6), and a small part of the detonation wave propagates to the next detonation combustion area through the head flame transmission gap (8), and most of the detonation wave is finally discharged through the tail of the annular main detonation tube (6) after impacting the head. According to this propagation law, other detonation combustion areas in the annular main detonation tube (6) are allowed to continuously perform detonation combustion. When the detonation wave propagates to the detonation combustion area connected to the auxiliary pre-detonation tube (1), a part of the detonation wave propagates to the tail of the auxiliary pre-detonation tube (1) through the valveless flame tube (5), detonates the mixture of air and aviation kerosene in the auxiliary pre-detonation tube (1), generates a detonation wave propagating to the head of the auxiliary pre-detonation tube (1), and opens the valve (5) of the valved flame tube (2). At this time, the main pre-detonation tube (3) has completed a detonation combustion and is refilled with air and aviation kerosene. At this point, one cycle is completed and a new cycle begins.
Claims
1. An ignition and detonation method for an air-breathing pulse detonation combustion chamber, the air-breathing pulse detonation combustion chamber mainly comprising a main pre-detonation tube (3), a secondary pre-detonation tube (1), a valved cross-flame tube (2), a valveless cross-flame tube (5), an ignition device (4) and an annular main detonation tube (6), characterized in that: The air-breathing pulse detonation combustion chamber is cylindrical in shape as a whole, and is divided into a main pre-detonation tube (3) and a secondary pre-detonation tube (1) in the center, and an annular main detonation tube (6) in the outer ring; the main pre-detonation tube (3) and the secondary pre-detonation tube (1) are semicircular cylinders, and are connected through a valved flame-crossing tube (2) at the head; the annular main detonation tube (6) is connected to the tail of the main pre-detonation tube (3) and the secondary pre-detonation tube (1) respectively through a valveless flame-crossing tube (5); the interior of the annular main detonation tube (6) is divided into a plurality of detonation chambers by an insulating partition (7). The detonation combustion area is divided equally by the heat-insulating baffle (7) into the inner area of the annular main detonation tube (6), so as to ensure that the detonation combustion characteristics of each area are basically the same; except that the heat-insulating baffle (7) between the two detonation combustion areas connected to the main pre-detonation tube (3) and the auxiliary pre-detonation tube (1) has no flame transmission notch (8), each of the other heat-insulating baffles (7) has a flame transmission notch (8), and the flame transmission notches (8) are arranged alternately in a periodic manner, so as to ensure that a stable detonation wave is formed at the position of each flame transmission notch (8); The ignition and detonation method mainly comprises the following steps: when the combustion chamber is started, the valve body of the valved flame tube (2) is kept closed, the ignition device (4) ignites the mixture of aviation kerosene and oxygen in the main pre-detonation tube (3), and the resulting detonation wave propagates toward the tail of the main pre-detonation tube (3), most of the detonation wave is discharged through the outlet of the main pre-detonation tube (3), and part of the detonation wave propagates to the first detonation combustion area of the annular main detonation tube (6) through the valveless flame tube (5), at which time the first detonation combustion area of the annular main detonation tube (6) is filled with air and aviation kerosene, the detonation wave causes this detonation combustion area to rapidly perform detonation combustion, a new detonation wave is generated from the head of the area and propagates toward the outlet direction of the annular main detonation tube (6), a small part of which propagates to the next detonation combustion area through the flame transmission gap (8) at the head, and detonates the aviation kerosene in the new detonation combustion area from the head The mixture of air, kerosene and air generates a new detonation wave which will first propagate to the tail of the annular main detonation tube (6). A small part of the detonation wave is transmitted to the next detonation combustion area through the flame transmission gap (8) at the tail. Most of the detonation wave is finally discharged through the tail of the annular main detonation tube (6). According to this propagation law, other areas in the annular main detonation tube (6) are continuously subjected to detonation combustion. When the detonation wave propagates to the detonation combustion area connected to the auxiliary pre-detonation tube (1), a part of the detonation wave propagates to the tail of the auxiliary pre-detonation tube (1) through the valveless flame tube (5), detonates the mixture of air and aviation kerosene in the auxiliary pre-detonation tube (1), generates a detonation wave which propagates to the head of the auxiliary pre-detonation tube (1), and opens the valve of the valved flame tube (2). At this time, the main pre-detonation tube (3) has completed a detonation combustion and is refilled with air and aviation kerosene. At this point, one cycle is completed and the next new cycle begins.
2. The ignition and detonation method of an air-breathing pulse detonation combustion chamber according to claim 1, characterized in that: The main pre-detonation tube (3), the auxiliary pre-detonation tube (1) and the annular main detonation tube (6) are of the same length and form a compact cylindrical structure as a whole.
3. The ignition and detonation method of an air-breathing pulse detonation combustion chamber according to claim 1, characterized in that: The ignition device (4) ignites only once when the combustion chamber is started, and the subsequent cycle controls the detonation of the main pre-explosion tube (3) by opening and closing the valve-connected flame tube (2).
4. The ignition and detonation method of an air-breathing pulse detonation combustion chamber according to claim 1, characterized in that: The main pre-explosion pipe (3) is only filled with a mixture of oxygen and aviation kerosene at startup, and is always filled with a mixture of air and aviation kerosene during the following circulation process.