Gas-driven integrated support plate pulse injector and application method

Abstract

The invention discloses a gas-driven integrated support plate pulse injector which comprises a pulse injection assembly and an integrated support plate arranged at the output end of the pulse injection assembly, and the pulse injection assembly comprises a rotor support cylinder with an inner cavity provided with an exhaust hole; the cylinder cover is fixed at the top of the rotor supporting cylinder; the rotor is arranged in the rotor supporting cylinder; the pulse flow generating shaft is in transmission connection with the rotor; an oil inlet pipeline is arranged at the lower end of the rotor supporting cylinder, a side hole is formed in the side face of the pulse flow generating shaft, and a blind hole is formed in the bottom of the pulse flow generating shaft and communicates with an oil supply channel in the integrated supporting plate. According to the gas-driven integrated support plate pulse injector provided by the invention, the gas-driven pulse injection assembly is arranged, so that pulse injection can be carried out without configuring a power supply and a motor, and the burden of a power supply system of an aircraft is reduced; and the pulse injection assembly is simple and compact in structure, and the pulse injection oil supply process is safe and reliable.

Description

Technical Field

[0001] The present invention relates to an injector used in a supersonic combustion chamber of an aircraft, and more specifically, to a gas-driven integrated support plate pulse injector and an application method thereof. Background Art

[0002] The inlet flow velocity of the supersonic combustion chamber is fast and the dynamic pressure is high. When the fuel is injected into the wall by traditional methods, the penetration depth is often low, which is not conducive to the mixing and combustion of the fuel in the combustion chamber. In order to enhance the mixing characteristics of the fuel and the supersonic flow and improve the combustion efficiency, a series of enhanced mixing technologies have been developed. These enhanced mixing technologies can generally be divided into passive enhanced mixing technologies and active enhanced mixing technologies. Among them, passive enhanced mixing technologies include adding support plates, ramps, concave cavities, etc., which enhance mixing by inducing the generation of stream vortices; active mixing enhancement technologies include pulse injection, plasma-assisted jets, etc., which enhance mixing through external excitation.

[0003] At present, common pulse injectors are often driven by electricity. These design solutions not only require the design of pulse injectors, but also often require the configuration of electric devices to drive pulse injectors. For aircraft with long flight time, it is necessary to configure a sufficiently powerful power supply to ensure the safety and reliability of the pulse injection fuel supply system throughout the entire flight. As a result, higher requirements are placed on the aircraft power supply system. This not only makes the entire pulse injection system more complicated, but also increases the weight of the aircraft. Summary of the invention

[0004] An object of the present invention is to solve at least the above problems and / or disadvantages and to provide at least the advantages which will be described hereinafter.

[0005] In order to achieve these objects and other advantages of the present invention, a gas-driven integrated support plate pulse injector is provided, comprising: a pulse injection assembly and an integrated support plate arranged at the output end of the pulse injection assembly, wherein the pulse injection assembly comprises: a rotor support cylinder having an inner cavity with an exhaust hole; A cylinder cover fixed to the top of the rotor support cylinder; A rotor disposed in a rotor support cylinder; A pulse flow generating shaft drivingly connected to the rotor; Wherein, the rotor support cylinder and / or the cylinder cover is provided with an inlet channel cooperating with the external driving gas; An oil inlet pipeline is provided at the lower end of the rotor support cylinder, and a side hole which is highly adapted to the oil inlet pipeline is opened on the side of the pulse flow generating shaft; A blind hole connected to the side hole is provided at the bottom of the pulse flow generating shaft, and one end of the pulse flow generating shaft having the blind hole extends into the interior of the integrated support plate and is connected to the oil supply passage in the integrated support plate.

[0006] Preferably, it further comprises: a driving gas rectifying shell sleeved on the outer side of the rotor and adapted thereto; The driving gas rectifying shell is provided with an arc-shaped rectifying groove connecting the inner side thereof with the driving gas inlet channel; A pressure relief groove is provided on the outer side of the driving gas rectifying shell at a position corresponding to the exhaust hole, and at least one exhaust port is provided on the pressure relief groove.

[0007] Preferably, the rotor is connected to the pulse flow generating shaft via a coupling.

[0008] Preferably, the inner cavity of the rotor support cylinder is a multi-stage structure, and the area from the bottom to the top is in a stepped shape that expands step by step.

[0009] Preferably, the integrated support plate comprises: an embedded support plate whose lower end extends into the interior of the engine combustion chamber and a mounting flange connected to the lower end of the rotor support cylinder; The end surface of the mounting flange is provided with a circular hole adapted to the pulse flow generating shaft; The bottom of the circular hole is provided with a first liquid collecting chamber vertically arranged thereto; A plurality of second liquid collecting cavities communicating with the first liquid collecting cavities are arranged in the extending direction of the embedded support plate, and a plurality of spray holes communicating with the second liquid collecting cavities are arranged on the side surface of the embedded support plate.

[0010] Preferably, the rotor support cylinder is provided with a first high-speed oil seal and a second high-speed oil seal at the upper and lower ends of the inner cavity wall cooperating with the pulse flow generating shaft; The rotor support cylinder is provided with a sealing ring on the lower end surface matched with the integrated support plate.

[0011] An application method, which uses the gas-driven integrated support plate pulse injector as described above, comprises: Step 1: The driving gas enters the inner cavity of the rotor support cylinder from the driving gas inlet channel to drive the rotor to rotate; Step 2: The rotor synchronously drives the pulse flow generating shaft to rotate, so that the side holes on the pulse flow generating shaft are periodically connected to the oil inlet pipe. By periodically opening and closing the oil supply passage, a pulse jet is generated at the blind hole outlet of the pulse flow generating shaft, thereby completing the pulse fuel supply to the fuel inside the engine combustion chamber.

[0012] An application method further comprising: When the rotor synchronously drives the pulse flow to rotate the shaft, the process of processing the driving gas through the driving gas rectifying shell includes: Step 20: After the driving gas enters the driving gas inlet channel, it passes through the arc-shaped rectifying groove and enters the inner cavity of the rotor support cylinder. The arc-shaped surface on the arc-shaped rectifying groove guides the gas to impact the windward surface of the rotor in the arc direction, so as to drive the rotor to rotate in the arc direction of the rectifying groove; Step 21: The driving gas flows into the pressure relief groove through the exhaust port, and then flows out through the exhaust hole on the rotor support cylinder.

[0013] The present invention includes at least the following beneficial effects: by setting up a gas-driven pulse injection assembly, the required driving gas can be provided by the extruded gas carried by the aircraft or the flowing gas captured by the aircraft, and pulse injection can be performed without configuring a power supply and an electric motor, thereby reducing the burden on the aircraft's power supply system; and the pulse injection assembly has a simple structure, and by integrating the component providing the pulse drive, namely the pulse injection assembly, with the integrated support plate, the structure is simple and compact, and the pulse injection fuel supply process is safe and reliable.

[0014] Other advantages, objectives and features of the present invention will be embodied in part through the following description, and in part will be understood by those skilled in the art through study and practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 An assembly diagram of a gas-driven integrated support plate pulse injector according to an embodiment of the present invention; Figure 2 A top view of an assembly diagram of a gas-driven integrated support plate pulse injector with the cylinder cover removed in one embodiment of the present invention; Figure 3 is an axonometric view of a rotor in one embodiment of the present invention; Figure 4 is a top view of a rotor in one embodiment of the present invention; Figure 5 is a schematic diagram of an angular contact ball bearing in one embodiment of the present invention; Figure 6 An exploded view of a coupling in one embodiment of the present invention; Figure 7 It is an isometric view of the pulse flow generation axis in one embodiment of the present invention; Figure 8 It is a cross-sectional view of the pulse flow in one embodiment of the present invention; Fig. 9 It is an isometric view of a driving gas rectifying shell in one embodiment of the present invention; Fig.10 An axonometric view of a rotor support cover in one embodiment of the present invention; Fig.11 It is an axonometric view of a rotor support bottom cover in one embodiment of the present invention; Fig.12 It is an axonometric view of a cylinder head in one embodiment of the present invention; Fig.13 It is an axonometric view II of a cylinder head in one embodiment of the present invention; Fig.14 A cross-sectional view of a cylinder head in one embodiment of the present invention; Fig.15 A cross-sectional view of a rotor support cylinder in one embodiment of the present invention; Fig.16 A top view of a rotor support cylinder in one embodiment of the present invention; Fig.17 It is an axonometric view of an integrated support plate in one embodiment of the present invention; Fig.18 A cross-sectional view of an integrated support plate in one embodiment of the present invention; Fig.19 It is an isometric view of the first high-speed oil seal / the second high-speed oil seal in one embodiment of the present invention; Fig. 20 It is an axonometric view of a sealing ring in one embodiment of the present invention; Fig.21 This is an axonometric view of a positioning pin in one embodiment of the present invention.

[0017] Reference numerals: 10. First angular contact ball bearing; 11. First angular contact ball bearing inner ring; 12. First angular contact ball bearing outer ring; 20. Rotor; 21. First rotor shaft section; 22. Second rotor shaft section; 23. Third rotor shaft section; 24. First rotor shoulder; 25. Second rotor shoulder; 30. Blade; 31. Windward side of blade; 32. Fillet; 40. Second angular contact ball bearing; 41. Second angular contact ball bearing inner ring; 42. Second angular contact ball bearing outer ring; 50. Coupling; 51. First half coupling; 52. Intermediate plate; 53. Second half coupling; 54. Protruding teeth; 55. Grooves; 60. First High-speed oil seal; 70, pulse flow generating shaft; 71, side hole; 72, blind hole; 73, bottom of blind hole; 80, second high-speed oil seal; 90, integrated support plate; 91, first end face of integrated support plate flange; 92, support plate connecting threaded hole; 93, step hole; 94, support plate oil inlet hole; 95, second end face of integrated support plate flange; 96, first positioning groove; 97, support plate embedded body; 98, support plate; 99, fuel injection hole; 910, second positioning groove; 911, first liquid collecting cavity; 912, second liquid collecting cavity; 100, sealing ring; 110, rotor support cylinder; 111, upper end face of rotor support cylinder; 112 , spline hole; 113, spline groove; 114, exhaust hole; 115, first step hole; 116, second step hole; 117, third step hole; 118, oil inlet pipeline; 119, oil inlet hole; 1110, sealing ring groove; 1111, fourth step hole; 1112, first hole shoulder; 1113, second hole shoulder; 1114, lower end face of rotor support cylinder; 1115, third hole shoulder; 1116, cylinder head connection threaded hole; 120, rotor support bottom cover; 121, external spline; 122, inner ring of rotor support bottom cover; 130, driving gas rectifier shell; 131, rectifier shell upper end face; 132, rectifier Groove; 133, locating pin hole I; 134, outer cylinder of the rectifier shell; 135, lower end surface of the rectifier shell; 136, pressure relief groove; 137, first exhaust port; 138, second exhaust port; 139, inner cylinder of the rectifier shell; 140, rotor support top cover; 141, driving gas channel; 142, locating pin hole II; 143, outer ring of the rotor support top cover; 144, inner ring of the rotor support top cover; 150, cylinder head; 151, driving gas inlet pipeline; 152, driving gas inlet; 153, screw installation step; 154, cylinder head light hole; 155, cylinder head inner cavity; 156, locating pin hole III; 160, locating pin. DETAILED DESCRIPTION

[0019] The present invention is further described in detail below in conjunction with the accompanying drawings so that those skilled in the art can implement the invention with reference to the description.

[0020] It should be understood that terms such as “having”, “including” and “comprising” used herein do not specify the existence or addition of one or more other elements or combinations thereof.

[0021] It should be noted that in the description of the present invention, the orientation or positional relationship indicated by the term is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0022] In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installed", "provided with", "mounted / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection. It can be a mechanical connection or an electrical connection. It can be a direct connection or an indirect connection through an intermediate medium. It can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0023] Figure 1-21 The embodiment of a gas-driven integrated support plate 90 pulse injector and its components according to the present invention is shown, which includes: a rotor 20, a gas rectifier shell, a rolling bearing, a rotor 20 support end cover, a coupling 50, a pulse flow generating shaft 70, a high-speed oil seal ring, a rotor support cylinder 110, a cylinder cover 150 and a locating pin 160.

[0024] The gas-driven pulse injection device includes: a rotor 20, gas-driven blades 30, a gas rectification housing, a rolling bearing, a rotor 20 support end cover, a coupling 50, a pulse flow generating shaft 70, a high-speed oil seal ring, a rotor support cylinder 110, a cylinder cover 150 and a positioning pin 160.

[0025] The rotor 20 is a shaft with blades 30, which can be divided into three shaft sections. In the shaft section in the middle of the rotor 20, 8 blades 30 are evenly arranged along the circumference. In actual use, the number of blades 30 of the rotor 20 can be set according to the specific situation to ensure the rotation speed of the rotor 20 and the stability of the device operation; in order to ensure the strength of the blades 30, the blades 30 and the rotor 20 are integrated into a design, the number of connecting parts is reduced, and fillets 32 are designed between the blades 30 and the rotor 20 to reduce stress concentration and improve the fatigue resistance of the rotor 20. The 8 evenly distributed blades 30 generate torque under the action of the driving gas, driving the rotor 20 to rotate at high speed, providing a power source for the pulse jet. For the shaft section with thinner ends, one end is shorter and is used to install a rolling bearing; the other end is longer and is used to install a rolling bearing and connect with the cross slider coupling 50.

[0026] The driving gas rectification shell 130 is a coaxial cylinder, that is, the inner cavity cylinder and the outer cylinder are coaxially designed, and its axial length is the same as the axial length of the thicker shaft section of the rotor 20. A positioning pin 160 hole is designed at one end of the cylinder, which is used to assemble the positioning pin 160 to limit the rotation of the gas rectification shell; an arc-shaped gas rectification groove 132 is designed on one side of the positioning pin 160 hole, so that the driving gas enters the gas rectification shell in a specific direction to push the gas driving blade 30, guides the driving gas to concentrate on impacting the windward surface 31 of the blade, and enhances the driving force of the rotor 20; a first exhaust port 137 is designed near one side of the positioning pin 160 hole, and a second exhaust port 138 is also designed at the bottom end of the gas rectification shell in order to discharge the gas more smoothly, and the outer wall surface of the gas discharge groove is thinned along the axial direction to accelerate the exhaust of the exhaust gas, reduce the back pressure, and reduce energy loss.

[0027] The rotor 20 support end cover is divided into a rotor support top cover 140 and a rotor support bottom cover 120. The inner cylindrical surface of the rotor support top cover 140 cooperates with the outer ring of the rolling bearing installed on the shorter and thinner shaft section of the rotor 20, and the rotor support top cover 140 is designed with an arc groove for passing gas as a driving gas channel 141 and a positioning pin 160 hole II 142 for installing the positioning pin 160; the inner cylindrical surface of the rotor 20 support bottom cover cooperates with the outer ring of the rolling bearing installed on the longer and thinner shaft section of the rotor 20, and the outer periphery of the rotor support bottom cover 120 is designed with an external spline 121 structure to limit the rotation of the rotor support bottom cover 120.

[0028] The coupling 50 is composed of two half couplings 50 with two protruding teeth 54 on the end faces and an intermediate disk 52 with a groove 55, wherein one half coupling 50 is connected to the longer thin shaft section of the rotor 20, and the other half coupling 50 is connected to the pulse flow generating shaft 70. The structure of the protruding teeth 54 and the groove 55 ensures torque transmission while allowing a certain axial / radial offset, which can compensate for installation errors and improve system stability. In addition, it is a modular design, which is easy to disassemble and maintain, and can reduce maintenance costs.

[0029] The pulse flow generating shaft 70 is a shaft with a blind hole 72 and a side hole 71, and the side hole 71 is opened near the bottom 73 of the blind hole. In one rotation cycle of the pulse flow generating shaft 70, when the side hole 71 is opposite to the fuel supply pipeline, the fuel can enter the blind hole 72 through the side hole 71, and the entire injection system flows; when the side hole 71 rotates through the fuel supply pipeline with the pulse generating shaft, the fuel cannot enter the blind hole 72 through the side hole 71, and the entire injection system does not flow, thereby forming a pulse flow; the pulse frequency can be adjusted by the rotation speed of the rotor 20 to meet the requirements of different working conditions. At the same time, the number and size of the blind holes 72 of the pulse flow generating shaft 70 can also be configured according to actual needs. Different numbers and sizes of blind holes 72 can be set according to needs to achieve the configuration of pulse speed and injection volume.

[0030] The rotor support cylinder 110 is a cylinder body, and the rotor 20, gas drive blades 30, drive gas rectifier housing 130, first angular contact ball bearing 10, second angular contact ball bearing 40, cross slider coupling 50, rotor support bottom cover 120, rotor support top cover 140 and pulse flow generating shaft 70 are placed in the inner cavity. The inner cavity of the rotor support cylinder 110 is three sections of stepped holes that expand gradually from the bottom to the top, the lowest hole section is a circular hole, which forms a clearance fit with the pulse flow generating shaft 70, and small stepped holes are provided at both ends of the circular hole for installing the first high-speed oil seal 60 and the second high-speed oil seal 80; the middle section hole section is a circular hole, the diameter of which is larger than the outer diameter of the cross slider coupling 50; the topmost hole is provided with an internal spline, which cooperates with the external spline 121 of the rotor support bottom cover 120 to limit the rotation of the rotor support bottom cover 120.

[0031] The rotor support cylinder 110 is generally a coaxial cylinder with a thin lower part and a thick upper part. A fuel inlet channel is provided at a position where the thinner cylindrical section at the lower part is in line with the height of the side hole 71 of the pulse flow generating shaft 70; each component in the inner cavity of the rotor support cylinder 110 can be loaded and unloaded for easy replacement, reducing maintenance and repair costs; three circular holes are provided at the thicker cylindrical end at the upper part for discharging driving gas. The rotor support cylinder 110 is provided with flanges at both ends, wherein the upper end flange is provided with six cylinder head connection threaded holes 1116 arranged along the circumference for installing the cylinder head 150; the lower end flange is evenly provided with six light holes along the circumference for passing bolts to connect the rotor support cylinder 110 and the integrated support plate 90.

[0032] The cylinder cover 150 is a disc-shaped structure, with six light holes evenly arranged along the circumferential direction corresponding to the threaded holes on the upper flange of the rotor support cylinder 110, and the cylinder cover 150 can be connected to the rotor support cylinder 110 by threads. A positioning pin 160 hole III 156 is set on the end surface of the cylinder cover 150 that matches the upper flange of the rotor support cylinder 110, which is used to install the positioning pin 160, so that the rotor support top cover 140 and the driving gas rectifier shell 130 can be accurately positioned and limited to rotate. A driving gas inlet 152 channel is opened on the side of the cylinder cover 150, and a driving gas flow channel communicating with the driving gas inlet 152 channel is opened on the inner surface of the vertical cylinder cover 150.

[0033] The integrated support plate 90 is composed of two parts: an embedded support plate 98 and a mounting flange.

[0034] The embedded support plate 98 is composed of an embedded body that cooperates with the engine wall and a support plate 98 extending into the engine combustion chamber. The long side of the cross section of the embedded body is parallel to the engine flow direction, and the two short sides are designed in semicircles. The height of the embedded body is the same as the engine wall. The long side of the cross section of the support plate 98 is also parallel to the engine flow direction, and the two short sides of the cross section are designed in semicircles. The height of the support plate 98 is the same as the height of the engine combustion chamber.

[0035] The mounting flange is designed to match the flange at the lower end of the rotor support cylinder 110, and six support plate connection threaded holes 92 are evenly arranged along the circumference for connecting with the rotor support cylinder 110 through bolts. Four step holes 93 are opened diagonally inside the circumferentially evenly distributed threaded holes for connecting the support plate 98 to the engine body through bolts. Two positioning grooves are opened on the end surface where the mounting flange is connected to the engine, preferably, the two positioning grooves are at an angle of 90° to ensure that they are installed and aligned.

[0036] A circular hole is provided at the geometric center of the end face of the mounting flange as the fuel inlet of the support plate 98. The circular hole is clearance-matched with the pulse flow generating shaft 70, and the depth of the circular hole is consistent with the length of the pulse generating shaft extending out of the flange end face of the lower end of the rotor supporting cylinder 110. A first liquid collecting cavity 911 perpendicular to the circular hole is provided at the bottom of the circular hole. A second liquid collecting cavity 912 perpendicular to the liquid collecting cavity and the end face of the support plate 98 is provided inside the support plate 98, and a spray hole perpendicular to the side face and the second liquid collecting cavity 912 is provided on the side face of the support plate 98.

[0037] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, the rotor 20 includes three shaft sections: a first rotor shaft section 21, a second rotor shaft section 22, and a third rotor shaft section 23. Eight blades 30 are evenly designed along the circumference of the second rotor shaft section 22. When the driving gas acts on the windward surface 31 of the blades, the blades 30 will drive the rotor 20 to rotate. In order to ensure the strength of the blades 30 when the rotor 20 is light, the blades 30 and the rotor 20 are designed as an integrated whole, and fillets 32 are designed on the blades 30 and the rotor 20 to reduce stress concentration. The first rotor shaft section 21 is connected to the first angular contact ball bearing 10 ( Figure 5 ) is connected to the first angular contact ball bearing inner ring 11 for fixing the rotor 20. The rotor third shaft section 23 is longer than the rotor first shaft section 21. In addition to being connected to the second angular contact ball bearing inner ring 41 for fixing the rotor 20, it is also connected to the first half coupling 51 with two protruding teeth 54, and the rotor first shaft shoulder 24 and the rotor second shaft shoulder 25 at both ends of the rotor second shaft section 22 are respectively against the first angular contact ball bearing 10 and the second angular contact ball bearing 40 for fixing.

[0038] The first half coupling 51, the second half coupling 53 with two protruding teeth 54, and the intermediate disk 52 together constitute the coupling 50. The intermediate disk 52 is designed with two symmetrically arranged grooves 55 on the upper and lower end surfaces, respectively. The two symmetrically arranged grooves 55 on the upper end surface of the intermediate disk 52 are respectively matched with the two symmetrically arranged protruding teeth 54 of the first half coupling; the two symmetrically arranged grooves 55 on the lower end surface of the intermediate disk 52 are respectively matched with the two symmetrically arranged protruding teeth 54 of the first half coupling. Through the extrusion of the protruding teeth 54 and the grooves 55, the rotation of the first half coupling 51 can be transmitted to the second half coupling.

[0039] Furthermore, the second half coupling 53 and the pulse flow generating shaft 70 ( Figure 7 , Figure 8) is connected to transmit the rotation to the pulse flow generating shaft 70. The pulse flow generating shaft 70 is designed with a blind hole 72, and a side hole 71 is opened near the bottom 73 of the blind hole for fuel to enter. Therefore, the integrated rotor 20 with blades 30, the coupling 50 and the pulse flow generating shaft 70 together constitute the rotatable part of the present invention.

[0040] like Figure 1 , Figure 2 and Fig.10 , the first angular contact ball bearing 10 is positioned by the first angular contact ball bearing outer ring 12 cooperating with the rotor support cover inner ring 144. The rotor support cover 140 is also provided with a rotor support cover outer ring 143 and a driving gas channel 141. The driving gas rectifying shell 130, the rotor support cover 140 and the cylinder head 150 are respectively provided with a positioning pin 160 hole I 133, a positioning pin 160 hole II 142 and a positioning pin 160 hole III 156, and the positioning pin 160 hole II 142 is penetrated with a positioning pin 160 ( Fig.21 ), limiting the rotation of the rotor support cover 140 and the driving gas fairing shell 130; the driving gas channel 141 is used to pass the driving gas; the rotor support cover outer ring 143 is connected to the cylinder head 150 ( Fig.12 , Fig.13 , Fig.14 ) cooperates to further limit the position of the rotor support top cover 140.

[0041] like Figure 1 and Fig.11 As shown, the second angular contact ball bearing 40 is positioned by the outer ring 42 of the second angular contact ball bearing cooperating with the inner ring 122 of the rotor support bottom cover. The outer ring of the rotor support bottom cover 120 is also designed with an external spline 121 with 6 protruding teeth 54, which is cooperating with the inner spline of the rotor support cylinder 110 ( Fig.15 ) limits the rotation of the rotor supporting the bottom cover 120.

[0042] like Figure 1 and Fig. 9As shown, the blades 30 of the rotor 20 are placed in the driving gas rectifying shell 130. The upper end surface of the driving gas rectifying shell 130 is placed below the rotor support top cover 140, and the lower end surface 135 of the rectifying shell is placed above the rotor support bottom cover 120. The driving gas rectifying shell 130 is cylindrical as a whole, including an outer cylinder 134 of the rectifying shell and an inner cylinder 139 of the rectifying shell. The inner cylinder 139 of the rectifying shell is adapted to the blades 30. A positioning pin 160 hole Ⅰ133 is provided on the upper end surface 131 of the rectifying shell; a rectifying groove 132 is provided on the left side of the positioning pin 160 hole Ⅰ133 for rectifying, so that the driving gas is biased toward the above-mentioned windward surface 31 of the blade, and the positioning pin 160 hole Ⅰ133, the rectifying groove 132 and the pressure relief groove 136 are staggered in space; a second exhaust port 138 is provided on the right side of the pin hole. In order to discharge the gas after acting on the blade 30 as quickly as possible, a first exhaust port 137 is opened on the lower end surface, and a pressure relief groove 136 is opened on the outer cylinder.

[0043] like Fig.15 and Fig.16 As shown, the rotor support cylinder 110 is a cavity structure, and its upper end surface is connected to the cylinder cover 150 ( Fig.12 , Fig.13 , Fig.14) is connected, and the upper end surface 111 of the rotor support cylinder is connected to the integrated support plate 90. The inner cavity of the rotor support cylinder 110 is provided with a spline hole 112, a first step hole 115, a second step hole 116, a third step hole 117 and a fourth step hole 1111 from top to bottom. An oil inlet pipe 118 is provided in the third step hole 117, and fuel can be injected through the oil inlet hole 119. The spline hole 112 is used to accommodate the rotor 20, and is designed with 6 evenly arranged spline grooves 113, which cooperate with the spline teeth of the above-mentioned rotor support bottom cover 120 to limit the rotation of the rotor support bottom cover 120, and the first hole shoulder 1112 further limits the position of the rotor support bottom cover 120; three exhaust ports are provided in the spline groove 113 located at 90° of the oil injection pipeline to discharge the gas after work. The first stepped hole 115 is used to accommodate the coupling 50; the second stepped hole 116 is used to install the first high-speed oil seal 60, and the first high-speed oil seal 60 is limited in upper and lower positions by the second hole shoulder 1113; the third stepped hole 117 is used to accommodate the pulse flow generating shaft 70, and the side hole 71 of the pulse flow generating shaft 70 is made to be flush with the rear end of the oil inlet hole 119 through the adaption installation, so that the fuel flowing in from the oil inlet hole 119 can enter the blind hole 72 through the side hole 71; the fourth stepped hole 1111 is used to install the second high-speed oil seal 80, and the second high-speed oil seal 80 is limited in upper and lower positions by the third hole shoulder 1115. The first high-speed oil seal 60 and the second high-speed oil seal 80 can prevent the fuel from leaking from the gap between the pulse flow generating shaft 70 and the third stepped hole 117, forming a double sealing barrier. In order to ensure the sealing requirements at the connection between the rotor support cylinder 110 and the integrated support plate 90, a sealing ring groove 1110 is opened on the lower end surface 1114 of the rotor support cylinder for installing the sealing ring 100 ( Fig. 20 ), to avoid leakage between the rotor support cylinder 110 and the integrated support plate 90, thereby ensuring the safety of the device.

[0044] like Fig.12 , Fig.13 and Fig.14 As shown, the cylinder head 150 is a disc-shaped structure, which is connected to the upper end surface 111 of the rotor support cylinder by screws passing through the cylinder head light hole 154, and the cylinder head inner cavity 155 can cooperate with the outer ring 143 of the above-mentioned rotor support top cover to fix and press the sub-support top cover. In order to facilitate installation, a screw installation step 153 is designed on the upper end surface of the light hole. The positioning pin 160 hole III 156 is set on the end surface of the cylinder head 150 that cooperates with the upper end flange of the above-mentioned rotor support cylinder 110, which is used to install the positioning pin 160, so that the rotor support top cover 140 and the driving gas rectifier shell 130 are accurately positioned and limited to rotate. In addition, the rotor support cylinder 110 is also designed with a driving gas inlet pipeline 151, and the driving gas can enter the inner cavity from the inlet.

[0045] At this point, the driving principle of the pulse injector of the present invention can be described as follows: the driving gas enters from the inlet on the cylinder head 150, passes through the driving gas channel 141 on the rotor support top cover 140, and enters the rectifying groove 132 on the driving gas rectifying shell 130. Under the rectifying effect of the rectifying groove 132, the driving gas acts on the windward surface 31 of the rotor 20 blade, pushing the blade 30 to rotate with the rotor 20; the worked gas is discharged from the rectifier shell through the first exhaust port 137 and the second exhaust port 138 on the rectifying shell, and is discharged through the exhaust port on the rotor support cylinder 110 after passing through the pressure relief groove 136. In actual application, the size of the driving gas inlet 152 of the driving gas inlet pipe 151 and the number and size of the exhaust holes 114 can be set as needed to control the number of revolutions of the rotor 20. Different types of cylinder heads 150 and rotor support cylinders 110 can be set and replaced to configure the speed of the rotor 20. It is also possible to use a blocking component to block part of the exhaust holes 114 to control the exhaust speed and control the speed of the rotor 20.

[0046] The pulse jet principle of the pulse injector of the present invention can be described as follows: the rotor 20 drives the pulse flow generating shaft 70 to rotate through the coupling 50. During the rotation, the side hole 71 periodically passes through the tail end of the oil inlet hole 119 on the rotor support cylinder 110, thereby causing the oil supply pipeline to be periodically turned on and off, and a pulse jet is generated at the outlet of the blind hole 72 of the pulse flow generating shaft 70.

[0047] The gas-driven pulse injector of the present invention is connected to the integrated support plate 90 to form the gas-driven integrated support plate 90 pulse injector of the present invention. Fig.17 and Fig.18 As shown, the integrated support plate 90 is composed of an embedded support plate 98 and a flange. Further, the embedded support plate 98 is composed of a support plate embedded body 97 matched with the engine wall and a support plate 98 extending into the engine combustion chamber. The long side of the embedded body cross section is parallel to the engine flow direction, and the two short sides are designed as semicircles. The height of the embedded body is the same as the engine wall; the long side of the support plate 98 cross section is also parallel to the engine flow direction, and the two short sides of the cross section are designed as semicircles. The height of the support plate 98 is the same as the height of the engine combustion chamber.

[0048] The first end face 91 of the integrated support plate flange is designed to match the lower end face 1114 of the rotor support cylinder. Six support plate connection threaded holes 92 are evenly arranged along the circumference for connecting with the rotor support cylinder 110 through bolts. Four stepped holes 93 are diagonally provided inside the circumferentially evenly distributed support plate connection threaded holes 92 for connecting the support plate 98 with the engine body through bolts. A first positioning groove 96 and a second positioning groove 910 are provided on the second end face 95 of the integrated support plate flange connected to the engine. Preferably, the first positioning groove 96 and the second positioning groove 910 form an angle of 90°.

[0049] A circular support plate oil inlet hole 94 is provided at the geometric center of the first end face 91 of the integrated support plate flange. The support plate oil inlet hole 94 is clearance-matched with the pulse flow generating shaft 70, and the depth of the support plate oil inlet hole 94 is consistent with the length of the pulse generating shaft extending out of the lower end face 1114 of the rotor support cylinder. A horizontal first liquid collecting chamber 911 is provided at the bottom of the support plate oil inlet hole 94. A second liquid collecting chamber 912 is provided perpendicular to the axis of the first liquid collecting chamber 911 and the end face of the support plate 98. Preferably, three second liquid collecting chambers 912 are provided. A plurality of fuel spray holes 99 are provided on the side of the support plate 98 perpendicular to the side and the axis of the second liquid collecting chamber 912; the plurality of second liquid collecting chambers 912 in the support plate 98 cooperate with the fuel spray holes 99 to achieve uniform distribution of fuel in the combustion chamber and improve combustion efficiency.

[0050] Existing aircraft usually need to design corresponding air intakes to capture the incoming gas, so as to introduce the airflow into the engine combustion chamber for mixing and combustion with the fuel, thereby generating propulsion; for example, the invention patent with publication number: CN 105667812 A, the integrated design method of the forebody, air intake and wing waveriding of a hypersonic aircraft, the air intake design provides airflow to the combustion chamber for use by the engine. In this solution, the incoming gas can use a branch on the flow supply channel required by the original combustion chamber of the aircraft, which is connected to the inlet channel of the pulse injection assembly to provide gas driving power for it, so as to realize the gas drive of the pulse injection assembly.

[0051] Through the above-mentioned embodiment, the advantages of pulse injection and support plate 98 injection can be combined to provide a more abundant oil injection scheme for the supersonic combustion chamber. The gas-driven integrated support plate 90 pulse injector is gas-driven, and the required driving gas can be provided by the squeezed gas carried by the aircraft or by the incoming gas captured by the aircraft, wherein the incoming gas can be captured outside the aircraft when the aircraft is flying at high speed, such as: using the carried squeezed gas to drive when the aircraft is flying at a low speed, and using the captured incoming gas to drive when the flight speed reaches the standard, so there is no need to configure the electric device composed of power supply and motor like the previous pulse injector, and compared with the traditional split injector, the weight is significantly reduced, which can adapt to the weight reduction requirements of the aircraft; the integrated structure reduces the failure points, and the double sealing system and redundant positioning design extend the service life; in addition, the gas-driven integrated support plate 90 pulse injector adopts the support plate 98 and pulse injection technology at the same time, that is, it combines the passive enhancement mixing technology and the active enhancement mixing technology, which is more conducive to the mixing of fuel and supersonic incoming flow to enhance the mixing effect of the fuel. The modular design of the pulse jet assembly supports quick disassembly and replacement of core components, shortening the maintenance cycle and reducing maintenance costs.

[0052] The above solution is only an illustration of a preferred embodiment, but is not limited thereto. When implementing the present invention, appropriate replacement and / or modification can be performed according to user needs.

[0053] The number of devices and processing scales described here are used to simplify the description of the present invention. Applications, modifications and variations of the present invention will be obvious to those skilled in the art.

[0054] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily realized. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. A gas-driven integrated support plate pulse injector, comprising: A pulse jet assembly and an integrated support plate arranged at the output end of the pulse jet assembly, characterized in that the pulse jet assembly comprises: a rotor support cylinder with an exhaust hole in the inner cavity; A cylinder cover fixed to the top of the rotor support cylinder; A rotor disposed in a rotor support cylinder; A pulse flow generating shaft drivingly connected to the rotor; Wherein, the rotor support cylinder and / or the cylinder cover is provided with an inlet channel cooperating with the external driving gas; An oil inlet pipeline is provided at the lower end of the rotor support cylinder, and a side hole which is highly adapted to the oil inlet pipeline is opened on the side of the pulse flow generating shaft; A blind hole connected to the side hole is provided at the bottom of the pulse flow generating shaft, and one end of the pulse flow generating shaft having the blind hole extends into the interior of the integrated support plate and is connected to the oil supply passage in the integrated support plate.

2. The gas-driven integrated support plate pulse injector according to claim 1, characterized in that: Also includes: A driving gas rectifying shell sleeved on the outer side of the rotor and adapted thereto; The driving gas rectifying shell is provided with an arc-shaped rectifying groove connecting the inner side thereof with the driving gas inlet channel; A pressure relief groove is provided on the outer side of the driving gas rectifying shell at a position corresponding to the exhaust hole, and at least one exhaust port is provided on the pressure relief groove.

3. The gas-driven integrated support plate pulse injector according to claim 1, characterized in that: The rotor is connected to the pulse flow generating shaft through a coupling.

4. The gas-driven integrated support plate pulse injector according to claim 3, characterized in that: The inner cavity of the rotor support cylinder is a multi-stage structure, and the area from the bottom to the top is in a step-like shape that expands step by step.

5. The gas-driven integrated support plate pulse injector according to claim 1, characterized in that: The integrated support plate comprises: an embedded support plate with a lower end extending into the interior of the engine combustion chamber and a mounting flange connected to the lower end of the rotor support cylinder; The end surface of the mounting flange is provided with a circular hole adapted to the pulse flow generating shaft; The bottom of the circular hole is provided with a first liquid collecting chamber vertically arranged thereto; A plurality of second liquid collecting cavities communicating with the first liquid collecting cavities are arranged in the extending direction of the embedded support plate, and a plurality of spray holes communicating with the second liquid collecting cavities are arranged on the side surface of the embedded support plate.

6. The gas-driven integrated support plate pulse injector according to claim 1, characterized in that: The rotor support cylinder is provided with a first high-speed oil seal and a second high-speed oil seal at the upper and lower ends of the inner cavity wall matched with the pulse flow generating shaft; The rotor support cylinder is provided with a sealing ring on the lower end surface matched with the integrated support plate.

7. An application method, which uses the gas-driven integrated support plate pulse injector according to any one of claims 1 to 6, characterized in that: include: Step 1: The driving gas enters the inner cavity of the rotor support cylinder from the driving gas inlet channel to drive the rotor to rotate; Step 2: The rotor synchronously drives the pulse flow generating shaft to rotate, so that the side holes on the pulse flow generating shaft are periodically connected to the oil inlet pipe. By periodically opening and closing the oil supply passage, a pulse jet is generated at the blind hole outlet of the pulse flow generating shaft, thereby completing the pulse fuel supply to the fuel inside the engine combustion chamber.

8. The application method according to claim 7, characterized in that: Also includes: When the rotor synchronously drives the pulse flow to rotate the shaft, the process of processing the driving gas through the driving gas rectifying shell includes: Step 20: After the driving gas enters the driving gas inlet channel, it passes through the arc-shaped rectifying groove and enters the inner cavity of the rotor support cylinder. The arc-shaped surface on the arc-shaped rectifying groove guides the gas to impact the windward surface of the rotor in the arc direction, so as to drive the rotor to rotate in the arc direction of the rectifying groove; Step 21: The driving gas flows into the pressure relief groove through the exhaust port, and then flows out through the exhaust hole on the rotor support cylinder.

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