Pulse detonation type engine

Abstract

The invention discloses a pulse detonation type engine which comprises a machine shell, a spraying pipe connected with a machine shell flange, a combustion chamber connected with the spraying pipe flange end, a clock valve located in the machine shell and rotationally connected with the machine shell, a thrust plate attached to the end face of the clock valve in a sliding and rotating mode, a motor driving the clock valve to rotate and an encoder detecting the angle of the motor. The control assembly is connected with and controls the motor, the clock valve, the sparking plug and the encoder, the motor drives the clock valve to form middle gas inlet and edge fuel inlet, and the clock valve and the thrust plate are rotationally attached to form pulse opening and closing of a gas path and a fuel path. Air inlet, ignition and exhaust intervals are generated through cooperation of the clock valve and the thrust plate hole site, and the control assembly only needs to control the ignition time, so that non-stop rapid rotation circulation and high-frequency work can be achieved. The device is simple in structure and control, small in size, low in cost and capable of being deployed on a small aircraft.

Description

Technical Field

[0001] The present invention relates to a pulse detonation engine, belonging to the technical field of aircrafts. Background Art

[0002] Pulse detonation engines have great thrust and speed advantages. Existing ring detonation engines have a high frequency but are limited by nozzle sizes, resulting in relatively large overall engine sizes, and are only suitable as power sources for large equipment such as large rockets or fighter jets.

[0003] For example, US09882649 pulse detonation aeroengine has at least one nozzle surface and a plurality of pulse detonation devices mounted on the nozzle surface to replace more common combustion-based burners. The orientation of each pulse detonation device is such that its combustion products are directed along the nozzle surface. This technology is used in aeroengines.

[0004] Another example is CN202411043091.7 a combined power aircraft and flight method of a turbofan engine and a pulse detonation engine, including turbofan engines mounted on both sides of the belly of the aircraft and an air-breathing pulse detonation device mounted at the belly position; wherein, the air-breathing pulse detonation device includes: an air inlet duct, a detonation tube mounted in the air inlet duct, and a tail nozzle; the detonation tube has an air valve, and behind the air valve is a detonation chamber; when the air valve is opened, air is introduced into the detonation chamber and mixed with the combustibles in the detonation chamber, when the air valve is closed, the initiator ignites the combustibles in the detonation chamber, and after the combustibles burn, they are ejected through the tail nozzle; the air inlet duct is provided with a detonation window for controlling the opening and closing of the air inlet of the air inlet duct. This technology is mainly applied to large aircrafts or fighter jets.

[0005] Currently, pulse detonation engines cannot be used in engines of small aircrafts. The main reason is that the existing rotary shutter type pulse detonation engines have a low frequency and limited efficiency, and it is difficult to miniaturize them for use in small aircrafts. Summary of the Invention

[0006] In order to solve the problems raised in the background art, the present invention provides a more compact, simple and efficient pulse detonation engine and its control method, which is applied to small aircrafts.

[0007] To achieve the above object, the technical means adopted by the present invention is: a pulse detonation engine, comprising a housing, a nozzle flange-connected to the housing, a combustion chamber connected to the flange end of the nozzle, a clock valve rotatably connected to the housing and located inside the housing, a thrust plate slidably and rotatably fitted to the end face of the clock valve, a motor for driving the clock valve to rotate, an encoder for detecting the angle of the motor, a fan blade connected to the other end of the output shaft of the motor, a spark plug installed on the combustion chamber, and a control component connected to and controlling the motor, the clock valve, the spark plug and the encoder. The clock valve is driven by the motor, with air intake in the middle and fuel intake at the edge. The flange end face of the clock valve is rotatably fitted to the thrust plate to form a pulsed opening and closing of the air path and the fuel path. By the cooperation of the clock holes provided on the clock valve and the holes evenly distributed in a circular ring on the thrust plate, intake, ignition and exhaust intervals are generated. The control component only needs to control the ignition time to achieve a fast rotation cycle without pause in the middle and high-frequency operation.

[0008] Further, the application of the pulse detonation engine in a small aircraft.

[0009] Further, the housing has an inner cavity. An air intake passage, a fuel passage and a spark plug passage are sequentially arranged on the housing body from one end to the nozzle connection end. One end of the motor shaft extends into the housing and is connected to the clock valve. The motor shaft is connected to the end face of the housing through a bearing. The other end of the motor shaft is connected to the encoder and the fan blade. A heat dissipation air hood is arranged outside the housing and the motor. The heat dissipation air hood is provided with openings corresponding to the positions of the air intake passage, the fuel passage and the spark plug passage. The spark plug is inserted into the combustion chamber through the spark plug passage.

[0010] Furthermore, a plurality of fuel inlet holes are arranged on the outer circumferential surface of the clock valve facing the valve body. A plurality of fuel outlet holes are evenly distributed in a circle on the end face of the clock valve facing the thrust plate, and the fuel inlet holes and the fuel outlet holes are in one-to-one correspondence and conduction. A plurality of air jet holes are arranged on the inner circle circumference of the fuel outlet hole circle on the end face of the clock valve facing the thrust plate. The air jet holes are evenly distributed in groups of two along the circle. In each group, one air jet hole corresponds to the position of the fuel outlet hole and is located on the radial line emitted from the same center of the circle. The corresponding fuel outlet hole and the adjacent fuel outlet hole are trisected. The other air jet hole is located on the one-third included angle radial line close to the corresponding fuel outlet hole. Two circles of through holes are evenly distributed along the circumference on the thrust plate. The inner circle is an air vent hole and the outer circle is a fuel hole. The arrangement positions of the air vent holes and the fuel holes on the circumference correspond and are located on the radial line emitted from the same center of the circle.

[0011] Furthermore, a groove is arranged on the thrust plate to engage with the boss of the combustion chamber. The thrust plate is located inside the housing and together with the air intake end of the nozzle forms the combustion chamber.

[0012] Furthermore, the control component controls the motor to drive the clock valve to rotate counterclockwise, the thrust plate remains stationary, and compressed air enters the inner cavity of the casing from the air inlet passage. When the two corresponding air injection holes and fuel outlet holes on the clock valve rotate to the communicating position with the air vent hole and fuel hole of the thrust plate, the fuel is sprayed through the fuel passage, the fuel inlet hole corresponding to the fuel passage, and the fuel outlet hole, and is blocked by the spark plug in the combustion chamber and mixed with the simultaneously sprayed air; the control component collects the motor angle according to the encoder installed on the motor shaft, judges the rotation angle of the clock valve and the angle of the thrust plate. When the air vent hole and the fuel hole do not coincide and communicate, the control component controls the spark plug to ignite, and the mixture explodes and sprays out; the clock valve continues to rotate counterclockwise by an angle. At this angle, only the air injection hole located on the one-third included angle meridian on the clock valve communicates with the air vent hole of the thrust plate. At this time, compressed air enters and sprays out the residual flame in the combustion chamber; the clock valve continues to rotate counterclockwise by an angle until the two corresponding air injection holes and fuel outlet holes on the clock valve rotate to the communicating position with the air vent hole and fuel hole of the thrust plate, forming a cyclic operation.

[0013] Further, the nozzle gradually contracts in an arc from the nozzle flange end to the other end to form an opening circle smaller than the flange end, and gradually expands in an arc from this opening circle to the other end, and the diameter of the opening circle at this end is larger than the diameter of the opening circle at the flange end face.

[0014] Compared with the prior art, the beneficial technical effects of the present invention are as follows: 1. The control component only needs to control the ignition time, and can perform a fast rotation cycle without pause in the middle and work at a high frequency. It does not need to separately control the fuel and air injection switches before each ignition, so the structure and control are simple. 2. The structure is simple, the volume is small, the cost is low, and it can be deployed on small aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention will be further described below with reference to the drawings and embodiments.

[0016] Figure 1 External structure schematic diagram of the present invention; Figure 2 Overall structure sectional schematic diagram of the present invention; Figure 3 Exploded schematic diagram of the local structure of the present invention; Figure 4 Ignition time schematic diagram of the pulse cooperation between the clock valve b and the thrust plate a of the present invention; In the figure: 1. nozzle, 2. combustion chamber, 21. boss, 3. clock valve, 31. fuel inlet hole, 32. fuel injection port, 33. air injection hole, 4. housing, 41. housing flange, 42. inner cavity, 43. spark plug channel, 44. fuel channel, 45. air intake channel, 5. motor, 51. motor shaft, 52. motor housing, 6. fan blade, 7. encoder, 8. thrust plate, 81. groove, 82. ventilation hole, 83. fuel hole, 9. heat dissipation air shroud, 10. spark plug. Detailed implementation manner Embodiment

[0017] As Figures 1-3 Shown is a pulse detonation engine used in a small aircraft, including a housing 4, a nozzle 1 connected to the housing flange 41, a combustion chamber 2 connected to the flange end of the nozzle, a clock valve 3 rotatably connected to the housing 4 inside the housing, a thrust plate 8 slidably and rotatably fitted to the end face of the clock valve 3, with a groove 81 provided on the thrust plate 8, and the groove 81 serves for installation and positioning and engages with the boss 21 of the combustion chamber 2. The thrust plate 8 is located inside the housing 4 and together with the air inlet end of the nozzle 1 forms the combustion chamber 2. The spark plug 10 is installed on the combustion chamber 2.

[0018] The housing 4 has an inner cavity 42. An air intake channel 45, a fuel channel 44, and a spark plug channel 43 are sequentially provided on the housing body from one end to the nozzle connection end. One end of the motor shaft 51 extends deep into the housing and is connected to the clock valve 3. The motor shaft 51 is connected to the housing end face through a bearing. The other end of the motor shaft 51 is connected to an encoder 7 and a fan blade 6. A heat dissipation air shroud 9 is provided outside the housing 4 and the motor 5. The heat dissipation air shroud 9 is provided with openings corresponding to the positions of the air intake channel 45, the fuel channel 44, and the spark plug channel 43. The spark plug 10 is inserted into the combustion chamber 2 through the spark plug channel 43. The motor 5 drives the clock valve 3 to rotate. The encoder 7 detects the motor angle. The fan blade 6 is connected to the other end of the motor output shaft 51 and is used for heat dissipation. The motor 5 not only drives the clock valve to supply air and fuel intermittently at high frequency, but also drives the fan blade 6 to generate a backward air flow to take away the high temperature of the engine along the outer walls of the housing and the nozzle through the heat dissipation air shroud 9.

[0019] As Figure 4As shown in the figure, two circles of through holes are evenly distributed along the circumference on the thrust plate 8. The inner circle is the air vent hole 82, and the outer circle is the fuel hole 83. The arrangement positions of the air vent hole 82 and the fuel hole 83 on the circumference correspond to each other and are located on the radial line emitted from the same center; several fuel inlet holes 31 are arranged on the outer circumference of the clock valve 3 facing the valve body, and several fuel outlet holes 32 are evenly distributed on the circumference of the end face of the clock valve 3 facing the thrust plate 8. The fuel inlet holes 31 and the fuel outlet holes 32 are in one-to-one correspondence and conduction. Several air jet holes 33 are arranged on the inner circle of the circumference of the fuel outlet holes 32 on the end face of the clock valve 3 facing the thrust plate 8. The air jet holes 33 are evenly distributed in groups of two along the circumference. One air jet hole in each group corresponds to the position of the fuel outlet hole and is located on the radial line emitted from the same center. The corresponding fuel outlet hole and the adjacent fuel outlet hole are trisected, and the other air jet hole is located on the one-third included angle radial line close to the corresponding fuel outlet hole.

[0020] Working process: The motor drives the clock valve 3 to rotate counterclockwise. Compressed air enters the inner cavity of the housing from the air inlet passage 45. When the b0 angle of the clock valve 3 is aligned with the a0 angle of the thrust plate 8, the air path and fuel path of the clock valve 3 and the thrust plate 8 are connected before and after. Air and fuel are simultaneously sprayed into the combustion chamber and are blocked by the spark plug in the combustion chamber for mixing. When the control component judges that the clock valve 3 rotates to the b1 angle and coincides with the a0 angle of the thrust plate 8 according to the encoder 7 installed on the motor shaft 31, the control component controls the spark plug to ignite. At this time, the air path and fuel path are closed, and the mixed gas explodes and sprays out; when the clock valve 3 continues to rotate counterclockwise to the b2 angle and is aligned with the a0 angle of the thrust plate 8, only the air path of the clock valve 3 and the thrust plate 8 is connected, and the compressed air will spray out the residual flame in the combustion chamber; when the clock valve 3 continues to rotate counterclockwise to the b3 angle and is aligned with the a0 angle of the thrust plate 8, the above state of alignment of the b0 angle and the a0 angle is repeated, and so on in a cycle.

[0021] The control component is connected to and controls the motor, clock valve, spark plug and encoder. The motor drives the clock valve. Air enters from the middle and fuel enters from the edge. The flange end face of the clock valve rotates and fits with the thrust plate to form a pulsed opening and closing of the air path and fuel path. Through the cooperation of the clock hole positions set on the clock valve and the hole positions evenly distributed according to the ring on the thrust plate, intake, ignition and exhaust intervals are generated. The control component only needs to control the ignition time to achieve a fast rotation cycle without pause in the middle. The combined clock valve driven by the motor replaces the shutter-type pulse. Air enters from the middle and fuel enters from the edge. Through the cooperation of the clock hole positions with non-all-equal specific arrangements on the clock valve and the hole positions evenly distributed in a ring on the thrust plate, intake, ignition and exhaust intervals are automatically generated without pause in the middle, and it can quickly rotate and cycle for ignition and exhaust, working at a high frequency. It does not require separate control of the fuel and air injection switches before each ignition, and only needs to control the ignition time. Therefore, both the structure and the control are simple.

Claims

1. A pulse detonation engine, characterized in that: It includes a casing, a nozzle connected to the casing flange, a combustion chamber connected to the flange end of the nozzle, a clock valve located in the casing and rotatably connected to the casing, a thrust plate sliding and rotatably fitted with the end face of the clock valve, a motor driving the clock valve to rotate, an encoder detecting the angle of the motor, a fan blade connected to the other end of the motor output shaft, a spark plug installed on the combustion chamber, a control component connecting and controlling the motor, the clock valve, the spark plug and the encoder, the clock valve is driven by the motor, air is taken in from the middle and fuel is taken in from the edge, the flange end face of the clock valve is rotatably fitted with the thrust plate, forming a pulse opening and closing of the air path and the fuel path, and the intake, ignition and exhaust intervals are generated by the coordination of the clock hole positions set on the clock valve and the hole positions evenly distributed in a circular ring set on the thrust plate, and the control component only needs to control the ignition time to achieve a rapid rotation cycle without pause in the middle and high frequency operation.

2. Application of the pulse detonation engine according to claim 1 in small aircraft.

3. The pulse detonation engine according to claim 1, characterized in that: The casing has an inner cavity, and an air intake channel, a fuel channel and a spark plug channel are arranged in sequence on the casing from one end to the nozzle connection end. One end of the motor shaft extends into the casing and is connected to the clock valve. The motor shaft is connected to the end face of the casing through a bearing. The other end of the motor shaft is connected to an encoder and a fan blade. A heat dissipation hood is arranged outside the casing and the motor. Openings are arranged on the heat dissipation hood corresponding to the positions of the air intake channel, the fuel channel and the spark plug channel. The spark plug is inserted into the combustion chamber through the spark plug channel.

4. The pulse detonation engine according to claim 3, characterized in that: A plurality of fuel inlet holes are arranged in the valve body on the outer circumference of the clock valve, a plurality of fuel outlet holes are evenly distributed on the circumference of the end face of the clock valve facing the thrust plate, and the fuel inlet holes are connected to the fuel outlet holes in a one-to-one correspondence, and a plurality of jet holes are arranged on the inner circumference of the circumference of the fuel outlet holes on the end face of the clock valve facing the thrust plate, and the jet holes are evenly distributed along the circumference in groups of two, and one jet hole in each group corresponds to the position of the fuel outlet hole and is located on a radial line emitted from the same center of the circle, and the corresponding fuel outlet hole is divided into three equal parts with the adjacent fuel outlet hole, and the other jet hole is located on a meridian line of one-third of the included angle close to the corresponding fuel outlet hole; two circles of through holes are evenly distributed on the thrust plate along the circumference, wherein the inner circle is a vent hole and the outer circle is a fuel hole, and the arrangement positions of the vent hole and the fuel hole on the circumference correspond to each other and are located on a radial line emitted from the same center of the circle.

5. The pulse detonation engine according to claim 4, characterized in that: The thrust plate is provided with a groove which engages with the boss of the combustion chamber. The thrust plate is located in the casing and together with the air inlet end of the nozzle forms a combustion chamber.

6. The pulse detonation engine according to claim 4, characterized in that: The control component controls the motor to drive the clock valve to rotate counterclockwise, the thrust plate is fixed, and the compressed air enters the inner cavity of the casing from the air intake channel. When the two corresponding injection holes and fuel outlet holes on the clock valve rotate to a connected position with the air vent and fuel hole of the thrust plate, the fuel is sprayed in through the fuel channel, the fuel inlet hole and the fuel outlet hole corresponding to the fuel channel, and is blocked by the spark plug in the combustion chamber to mix with the air sprayed in at the same time; the control component collects the motor angle according to the encoder installed on the motor shaft, judges the rotation angle of the clock valve and the angle of the thrust plate, and controls the spark plug to ignite when the air vent and the fuel hole are not overlapped and connected, and controls the spark plug to ignite, and the mixed gas is sprayed out by explosion; the clock valve continues to rotate counterclockwise by an angle, at which angle, only the injection holes of the clock valve located on the meridian of one-third of the angle are connected with the air vent of the thrust plate, at which time, compressed air enters and sprays out the remaining flame in the combustion chamber; the clock valve continues to rotate counterclockwise by an angle until the two corresponding injection holes and fuel outlet holes on the clock valve rotate to connect with the air vent and fuel hole of the thrust plate, forming a cycle.

7. The pulse detonation engine according to claim 1, characterized in that: The nozzle gradually shrinks in an arc from the nozzle flange end to the other end to form an opening circle smaller than the flange end, and gradually expands in an arc from this opening circle to the other end, and the opening circle diameter of this end is larger than the opening circle diameter of the flange end face.

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