Ultrahigh pressure aircraft engine

Abstract

The invention discloses an ultrahigh-pressure aircraft engine and a manufacturing method of an ultrahigh-pressure rotor used by the engine, and the ultrahigh-pressure aircraft engine comprises a high-pressure compressor which comprises the ultrahigh-pressure rotor, a supercharger and a high-pressure compressor shell. The ultrahigh-pressure rotor is a turbine rotor with a circle of spiral long blades arranged in order on the periphery of a rotor cylinder, the supercharger comprises a chain type supercharging device and a gear box, the gear box takes out power from an engine axle to drive the chain type supercharging device to operate, and the chain type supercharging device synchronously operates with a blade cavity of the ultrahigh-pressure rotor through a supercharging plate. Air can be divided into a front section and a rear section, the air is sucked in and pushed out in an air compressor mode, the operation efficiency of an aircraft engine is remarkably improved, oil is saved, the speed is high, and the flight cost is low. The ultrahigh-pressure rotor used by the engine adopts a split mortise and tenon joint manufacturing method, and is convenient to manufacture and maintain.

Description

Technical fields:

[0001] This invention relates to an aircraft, and more particularly to an aircraft engine. Background technology:

[0002] Modern aircraft jet engines come in various types, but they all share a drawback or area for improvement: from front to back, the air passes through the fan, low-pressure compressor, high-pressure compressor, combustion chamber, high-pressure turbine, and low-pressure turbine—all of which are open-circuit. The thrust generated by the engine relies solely on the rotation of the blades. The air pressure propelled by the blade rotation cannot reach its maximum potential, resulting in low efficiency. This leads to higher fuel consumption, reduced speed, and higher flight costs. Summary of the Invention:

[0003] To address the aforementioned problem of insufficient thrust in aircraft engines, which hinders their ability to reach their full potential, this invention provides an ultra-high pressure aircraft engine that enables aircraft to generate greater thrust with the same fuel consumption.

[0004] The technical solution of the present invention is: an ultra-high pressure aircraft engine, including a high pressure compressor, wherein the high pressure compressor includes an ultra-high pressure rotor, a booster, and a high pressure compressor housing.

[0005] The ultra-high pressure rotor is a turbine rotor with a ring of neatly arranged helical blades around the outer circumference of the rotor cylinder. The ultra-high pressure rotor is mounted on the main shaft of the aircraft engine via a rotor shaft. Each blade of the ultra-high pressure rotor has 0.1 or more helical turns on the rotor cylinder.

[0006] The booster includes a chain-type booster device and a gearbox. The chain-type booster device includes a chain-type booster housing, a drive sprocket assembly, a driven sprocket assembly, a booster chain assembly, and a tensioning component. The chain-type booster housing includes a chain box-shaped shell, guide rails, guide rail supports, and wing plates. The chain box-shaped shell is composed of two large flat plates and three side plates. It has two opposing guide holes and a shaft hole at the front and a shaft hole at the rear. A guide rail support is located on each of the two lower sides inside the chain box-shaped shell, and a guide rail is located on the inner side of the guide rail support. Wing plates are located on the lower parts of the two outer sides of the chain box-shaped shell. The drive sprocket assembly is installed at the rear of the chain box-shaped shell and includes bearings, a drive sprocket shaft, and a drive sprocket. Two bearings are respectively installed on the two opposing inner walls of the rear side of the chain box-shaped shell. The drive sprocket shaft is mounted on the two bearings, and the drive sprocket is mounted on the drive sprocket shaft. The diameter of the shaft hole in the chain box-shaped shell is larger than that of the drive sprocket shaft. The drive sprocket shaft has a diameter at one end, and the shaft head at this end extends freely from the shaft hole. The driven sprocket assembly is installed at the front of the chain box-shaped housing and includes a bearing seat, a driven sprocket shaft, and a driven sprocket. The bearing seats are installed on both sides inside the chain box-shaped housing, the driven sprocket shaft is installed on the two bearing seats, and the driven sprocket is installed on the driven sprocket shaft. The bearing seat includes a seat body, a bearing, a guide block, a shaft hole, and a fixing hole. The bearing is installed in the bearing cavity at the front of the seat body, and the guide block is located at the rear of the seat body. Its thickness is slightly greater than the wall thickness of the chain box-shaped housing. The shaft hole is a through hole with a diameter larger than the diameters at both ends of the driven sprocket shaft. The guide block can move freely within the guide hole of the chain box-shaped housing, and the guide hole acts as a guide rail for the guide block. The booster chain assembly includes a special-shaped chain and a booster plate. The irregular chain includes regular chain links and irregular chain links. An irregular chain link is composed of two opposing irregular chain plates and a middle plate, integrally formed. Regular and irregular chain links are alternately connected in a loop via pin holes and pin hinges. A pressure plate is located on the outside of the middle plate of the irregular chain link. The irregular chain is mounted on the driving and driven sprockets. The pressure plate moves within the gap between two opposing guide rails on the pressure-boosting side, and moves within the internal space of the chain box-shaped housing on the rotating side. The guide rails of the chain-type pressure boosting device housing are roller bar guide rails, ball bar guide rails, or sliding guide rails.

[0007] The tensioning component is installed on the chain box-shaped housing near the driven sprocket and includes a spring support, a movable support, a bearing housing, a tensioning synchronizing shaft, a crank, and a connecting rod. The spring support of the tensioning component includes a seat body, a fixing hole, and a guide hole. The seat body is installed on the outer sides of the front part of the chain box-shaped housing through the fixing hole. The movable support includes a seat body, a shaft hole, a fixing hole, a guide post, and a spring. The spring is concentrically mounted on the guide post. One end of the guide post is fixed to the outer side plate of the seat body, and the other end is inserted into the guide hole of the spring support with clearance fit. The seat body of the movable support is connected and fixed to the fixing hole of the bearing housing of the driven sprocket component through the fixing hole and screws or rivets. The movable support and the bearing housing are aligned with the guide block through the guide hole. The guide rail can move freely, and the diameter of the shaft hole is larger than the diameter of the driven sprocket shaft. The shaft ends of the driven sprocket shaft extend freely from the shaft holes of the bearing seats and the shaft holes of the movable support. There are two bearing seats of the tensioning component, which are respectively set on the two opposite inner walls of the chain box-shaped housing on one side of the driven sprocket shaft. The tensioning synchronous shaft is installed in the two bearing seats, and its two shaft ends extend from the shaft holes of the chain box-shaped housing with clearance fit and are respectively mounted with a crank. The outer end of the crank is hinged to one end of the connecting rod, and the other end of the connecting rod is hinged to the shaft end of the driven sprocket shaft.

[0008] The turbocharger's gearbox includes a primary gearbox, a secondary gearbox, and a tertiary gearbox. The primary gearbox is located in front of the ultra-high pressure rotor and includes a housing, end cover, mounting bracket, gears, and gear shafts. The housing is a short cylindrical shape with a shaft hole at the rear. A bearing seat is located outside the shaft hole, and a bearing is installed inside the bearing seat. A support is located on the inner wall of the housing, and a bearing seat is installed on the support. A flange is located at the front of the housing, connecting it to the end cover. The end cover has a shaft hole at its center, and a bearing seat is located outside the shaft hole, where a bearing is installed. The mounting bracket is fixed in the middle to the outside of the end cover and at both ends to the high-pressure compressor housing. The large gear is mounted on the shaft, the small gear shaft is mounted inside the bearing seat, and the small gear is mounted at one end of the small gear shaft. The large gear and small gear mesh. The secondary gearbox of the turbocharger is located in front of the chain-box-shaped housing. The supercharger comprises a housing, bearing housing, gears, and gear shaft on one outer side. The housing and two bearing housings inside are mounted on the chain-box-shaped outer casing. The other end of the gear shaft driving the first-stage gearbox is mounted in one bearing housing, with a gear mounted at its end. One end of the gear shaft driving the third-stage gearbox is mounted in another bearing housing, with a gear mounted at its end. The two gears mesh. The third-stage gearbox is located at the rear end of the chain-box-shaped outer casing on the same side as the second-stage gearbox. It includes a housing, bearing housing, gear shaft, and gears. The housing and bearing housing are mounted on the outer side of the chain-box-shaped outer casing. The other end of the gear shaft driving the second-stage gearbox is mounted in a bearing housing, with a gear mounted at its end. A gear is mounted on the long shaft end of the drive sprocket shaft near the third-stage gearbox end. The two gears mesh. All gears in the first-stage gearbox are helical gears. All gears in the second-stage and third-stage gearboxes are bevel gears.

[0009] The number of turbochargers installed is one or more. If there is more than one, they are evenly distributed with the central axis of the ultra-high pressure rotor as the reference.

[0010] The center plane of the two large plates of the chain box-shaped outer shell of the supercharger passes through the central axis of the ultra-high pressure rotor. Each supercharger plate within the supercharger working range is inserted into the blade cavity of the ultra-high pressure rotor at the center plane of the two large plates of the chain box-shaped outer shell, so as to push the air and increase the air pressure.

[0011] The high-pressure compressor housing has an opening at the intersection line with the chain-box-shaped housing and the casing. A chain-type booster device is installed at the intersection opening and is connected to the high-pressure compressor housing by wing plates on the lower sides of both sides of the chain-box-shaped housing. The wing plates and the high-pressure compressor housing are connected by rivets, screws, or welding. A sealing structure is provided at the joint installation point of the intersection opening. This sealing structure is welded, a sealing strip, or a stacked edge strip.

[0012] The manufacturing method of the ultra-high pressure rotor of this invention involves dividing the blades into several small blades and assembling them with the rotor cylinder using a mortise and tenon structure. Each small blade includes a tenon and a blade body, while the rotor cylinder includes mortise grooves. The blades on the outer periphery of the rotor cylinder are divided into several small blades along both warp and weft lines. The mortise grooves of the rotor cylinder are axially arranged and run in a straight line from the front to the rear end of the cylinder, evenly distributed around the circumference. The small blades are inserted into the mortise grooves using tenons and connected to each other until the mortise groove is axially filled. Other mortise grooves are installed in the same way. The number of warp and weft lines is a divisor of the number of mortise grooves in the circumferential direction and is also an evenly distributed number of sections in the axial direction of the rotor cylinder. The structure of the divided small blades is identical. After all the small blades are assembled, the blade bodies of adjacent small blades in the front, back, left, and right directions are connected to each other, thus achieving the purpose of having a ring of neatly arranged spiral blades around the outer periphery of the rotor cylinder.

[0013] The principle of this invention is as follows: Utilizing the screw air compressor principle, it can nearly completely expel the air drawn into the screw teeth. This is because air is impermeable within all the screw teeth from front to back, and is sealed at the meshing point of the two screws. Therefore, the screw can function as an air compressor, unlike a fan. The invention operates as follows: the ultra-high pressure rotor of the high-pressure compressor employs a structure with a ring of neatly arranged helical blades around the outer circumference of the rotor cylinder. The booster utilizes the booster plates of the booster chain component, which are inserted into the cavities of each blade of the ultra-high pressure rotor. This seals the air and isolates the air with different pressure differences between the front and rear sections. When the engine is running, the ultra-high pressure rotor rotates, and the axle synchronously drives the drive sprocket through the gearbox, thereby driving the booster plates of the booster chain. The speed at which each booster plate moves is consistent with the speed at which the blade cavities of the ultra-high pressure rotor move in the same direction. This allows for both the intake of air at the front and the compression of air at the rear. The booster plates act as pistons, significantly increasing the thrust efficiency of the aircraft engine.

[0014] Beneficial effects: The ultra-high pressure rotor uses a ring of neatly arranged spiral blades on its outer circumference. The supercharger uses a supercharger plate of the supercharger chain component inserted into the cavity of each blade of the ultra-high pressure rotor. This can seal the air and isolate the air with different pressure differences between the front and rear. When the engine is running, the supercharger plate will both draw in the air in front and push the air in rear. The supercharger plate acts as a piston supercharger, which can significantly increase the thrust efficiency of the aircraft engine output, fully utilize the engine's compression potential, save fuel, be environmentally friendly, have low operating costs, and achieve high flight speed. Attached image description:

[0015] Figure 1 Front view of the invention (partial components are shown in cross-section)

[0016] Figure 2 Existing aircraft engine front view (some components are cut apart).

[0017] Figure 3 Assembly diagram of the turbocharger and ultra-high pressure rotor of this invention (some components are shown in cross-section).

[0018] Figure 4 Axonometric drawing of an ultra-high pressure aircraft rotor of this invention

[0019] Figure 5 Front view of the integrated component of the pressure plate and irregularly shaped chain link of the present invention

[0020] Figure 6 Top view of the integrated pressure plate and irregularly shaped chain link of the present invention

[0021] Figure 7 AA cross-sectional view of the present invention

[0022] Figure 8 BB cross-sectional view of the present invention

[0023] Figure 9 Partial enlarged view of the present invention III

[0024] Figure 10 CC sectional view of the primary gearbox housing of the present invention

[0025] Figure 11 Cross-sectional view of the primary gearbox housing of this invention (DD)

[0026] Figure 12 Front view of the primary gearbox housing of the present invention

[0027] Figure 13 Front view of the chain box-shaped outer casing of the present invention (with the secondary gearbox casing and the tertiary gearbox casing added).

[0028] Figure 14 Rear view of the chain box-shaped outer shell of the present invention

[0029] Figure 15 Cross-sectional view of the chain box-shaped outer casing EE of the present invention (with the secondary gearbox housing attached).

[0030] Figure 16 Cross-sectional view of the chain box-shaped outer casing of the present invention (with the addition of a three-stage gearbox housing).

[0031] Figure 17 Partial enlarged view of the present invention I

[0032] Figure 18 Partial enlarged view of the present invention II

[0033] Figure 19 Front view of the movable support of the present invention

[0034] Figure 20 Top view of the movable support of the present invention

[0035] Figure 21 Front view of the bearing housing of the driven sprocket component of the present invention

[0036] Figure 22 Cross-sectional view of the bearing housing GG of the driven sprocket component of the present invention.

[0037] Figure 23 Front view of the spring support of the tensioning component of the present invention

[0038] Figure 24 Cross-sectional view of the spring support HH of the tensioning component of the present invention

[0039] Figure 25 This invention provides a latitude and longitude zoning diagram of ultra-high pressure rotor blades.

[0040] Figure 26 Front view of the assembly of the ultra-high pressure rotor blades and rotor cylinder tenon and mortise structure of this invention

[0041] Figure 27 Front view of a single ultra-high pressure rotor blade of the present invention

[0042] Figure 28 Left view of a single ultra-high pressure rotor blade of the present invention

[0043] Figure 29 The coordinate diagram of the ultra-high pressure rotor blades in this invention, showing the latitude and longitude sections.

[0044] In the diagram: 1. Fan housing; 2. Fan assembly; 3. Inner and outer bypass ducts; 4. Low-pressure compressor; 5. Air duct; 6. High-pressure compressor; 7. Air duct; 8. Combustion chamber; 9. Axle; 10. High-pressure turbine; 11. Low-pressure turbine; 12. Guide vane; 13. Existing high-pressure compressor; 14. Ultra-high-pressure rotor; 15. Driven sprocket shaft; 16. Driven sprocket; 17. Irregular chain; 18. Bearing housing; 19. Zhang 20. Synchronous shaft; 21. Booster chain assembly; 22. Chain box-shaped housing; 23. Drive sprocket shaft; 24. Bearing housing; 25. Gear; 26. Bearing housing; 27. Housing; 28. Gear shaft; 29. ​​Bearing housing; 30. Gear; 31. Gear; 32. Bearing housing; 33. Housing; 34. Gear shaft; 35. Primary gearbox; 36. Gear; 37. Gear; 38. Bearing housing; 39. Main... 40. Drive sprocket; 41. Rotor cylinder; 42. Blade; 43. Pin hole; 44. Shaped chain plate; 45. Pressure booster plate; 46. High-pressure compressor housing; 47. Intermediate plate; 48. Support; 49. Bearing housing; 50. Guide rail; 51. Guide rail bracket; 52. Wing plate; 53. Housing; 54. End cover; 55. Bearing; 56. Axle hole; 57. Bearing; 58. Axle hole; 59. Bearing housing; 6 0. Flange; 61. Fixing bracket; 62. Guide hole; 63. Shaft hole; 64. Shaft hole; 65. Moving support; 66. Connecting rod; 67. Spring; 68. Spring support; 69. Crank; 70. Seat plate; 71. Shaft hole; 72. Fixing hole; 73. Guide column; 74. Guide block; 75. Shaft hole; 76. Mounting hole; 77. Bearing; 78. Fixing hole; 79. Guide hole; 80. Tenon; 81. Plate. Detailed implementation method:

[0045] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0046] exist Figure 1 In this ultra-high pressure aircraft engine, there is a fan housing 1, a fan assembly 2 installed inside the fan housing 1, an inner and outer bypass duct splitter wall 3 that divides the air in two, a low-pressure compressor 4 at the rear of the fan, an air duct 5, a high-pressure compressor 6 with a supercharger, an air duct 7, a combustion chamber 8, a wheel axle 9, a high-pressure turbine 10, a low-pressure turbine 11, and guide vanes 12. When the aircraft engine is running, air is drawn in through the front fan assembly 2 and expelled through the low-pressure turbine 11. Figure 3 , Figure 4 , Figure 7 , Figure 8 , Figure 9The diagram shows a high-pressure compressor 6 consisting of an ultra-high-pressure rotor 14 and a supercharger. The ultra-high-pressure rotor 14 is a turbine rotor with a ring of neatly arranged helical blades 41 on the outer circumference of the rotor cylinder 40. The ultra-high-pressure rotor 14 is mounted on the main shaft of the aircraft engine via a rotor shaft 9. The number of helical turns of the blades 41 on the rotor cylinder 40 from front to back is 0.1 or more. In a preferred embodiment, the number of helical turns of the blades 41 is 0.3. The blades 41 and the rotor cylinder 40 can be manufactured as one piece or separately. In a preferred embodiment, they are manufactured separately and then assembled. The supercharger includes a chain supercharger device and a gearbox. The chain supercharger device includes a chain supercharger housing, a drive sprocket assembly, a driven sprocket assembly, a supercharger chain assembly 20, and a tensioning component. The chain-type booster housing includes a chain box-shaped shell 21, guide rails 49, guide rail supports 50, and wing plates 51. The chain box-shaped shell 21 is composed of two large flat plates and three side plates, and is made by machining center, casting, or sheet metal, preferably by machining center, and connected by rivets or screws, preferably rivets. It has two opposing guide holes 62 and a shaft hole 63 at the front and a shaft hole 64 at the rear. A guide rail support 50 is provided on each of the two lower sides inside the chain box-shaped shell 21. A guide rail 49 is provided on the inner side of the guide rail support 50. The guide rail 49 is a roller bar guide rail, a ball bar guide rail, or a sliding guide rail, preferably a roller bar guide rail. The chain box-shaped shell 21, guide rail supports 50, and guide rails 49 are connected by rivets, screws, or welding, preferably by rivets. Wing plates 51 are provided on the lower parts of the two outer sides of the chain box-shaped shell 21. The wing plates 51 and the chain box-shaped shell 21 can be made by machining center or casting, or assembled from sheet metal, preferably... The assembly is manufactured using a machining center, with riveting being the preferred connection method. The drive sprocket assembly is installed at the rear of the chain box-shaped housing 21, including a bearing 23, a drive sprocket shaft 22, and a drive sprocket 39. Two bearings 23 are respectively installed on opposite inner walls of the rear side of the chain box-shaped housing 21, preferably connected by riveting. The drive sprocket shaft 22 is mounted on the two bearings 23, and the drive sprocket 39 is mounted on the drive sprocket shaft 22. The diameter of the shaft hole 64 in the chain box-shaped housing 21 is larger than the diameter of one end of the drive sprocket shaft 22, and the shaft end of the drive sprocket shaft 22 extends freely from the shaft hole 64. The driven sprocket assembly is installed at the front of the chain box-shaped housing 21, including a bearing seat 38, a driven sprocket shaft 15, and a driven sprocket 16. The bearing seats 38 are installed on both sides of the inside of the chain box-shaped housing 21, preferably connected by riveting. The driven sprocket shaft 15 is mounted on the two bearing seats 38, and the driven sprocket 16 is mounted on the driven sprocket shaft 15. Figure 21 , Figure 22In the bearing housing 38, there are a housing body, a bearing 77, a guide block 74, a shaft hole 75, and a fixing hole 76. The bearing 77 is installed in the bearing cavity at the front of the housing body. The guide block 74 is located at the rear of the housing body and its thickness is slightly greater than the wall thickness of the chain box-shaped outer shell 21. The shaft hole 75 is a through hole and its diameter is greater than the diameters at both ends of the driven sprocket shaft 15. The guide block 74 can move freely in the guide hole 62 of the chain box-shaped outer shell 21. The guide hole 62 acts as a guide rail for the guide block 74. Figure 3 , Figure 5 , Figure 6 In the process, the booster chain component 20 includes a shaped chain 17 and a booster plate 44. The shaped chain 17 includes conventional chain links and shaped chain links. The shaped chain links are integrally formed by two opposing shaped chain plates 43 and an intermediate plate 46. The conventional links and shaped chain links are alternately connected to form a loop through pin holes 42 and pin hinges. The booster plate 44 is located on the outside of the intermediate plate 46 of the shaped chain links. The two can be machined, cast, or welded together. The shaped chain 17 is mounted on the drive sprocket 22 and the driven sprocket 16. The booster plate 44 moves within the gap between two opposing guide rails 49 on the boosting working side and moves within the internal space of the chain box-shaped outer shell 21 on the rotating side.

[0047] Figure 3 , Figure 17 , Figure 18 In this structure, a tensioning component is installed on the chain box-shaped housing 21 near the driven sprocket 16, including a spring support 68, a movable support 65, a bearing housing 18, a tensioning synchronous shaft 19, a crank 69, and a connecting rod 66. The spring support 68 of the tensioning component includes a seat body, a fixing hole 78, and a guide hole 79. The seat body is installed on the outer sides of the front part of the chain box-shaped housing 21 through the fixing hole 78, and can be connected by riveting, screws, or welding, preferably by riveting. The movable support 65 includes a seat body 70, a shaft hole 71, a fixing hole 72, a guide post 73, and a spring 67. The spring 67 is concentrically mounted on the guide post 73. One end of the guide post 73 is fixed to the outer side of the side plate of the seat body 70, and the other end is inserted into the guide hole 79 of the spring support 68 with clearance fit. The seat body 70 is fixed by screws or rivets through the fixing hole 72 and the fixing hole 76 of the bearing housing 38 of the driven sprocket component, preferably by rivets. The movable support 65 and the bearing housing 38... The 8 connecting body can move freely through the guide hole 62 and the guide rail action of the guide block 74. The diameter of the shaft hole 71 is larger than the diameter of the driven sprocket shaft 15. The shaft ends of the driven sprocket shaft 15 extend freely from the shaft holes 75 of the bearing seat 38 and the shaft holes 71 of the movable support 65. There are two bearing seats 18, which are respectively set on the two opposite inner walls of the chain box-shaped outer shell 21 on one side of the driven sprocket shaft 15. The tensioning synchronous shaft 19 is installed in the two bearing seats 18. The shaft ends of the shafts extend from the shaft holes 63 of the chain box-shaped outer shell 21 with clearance fit and are respectively mounted with a crank 69. The outer end of the crank 69 is hinged to one end of the connecting rod 66, and the other end of the connecting rod 66 is hinged to the shaft end of the driven sprocket shaft 15.

[0048] Figure 3 , Figure 7 , Figure 8 Figure 10 , Figure 11 , Figure 12 In the turbocharger, the gearbox includes a primary gearbox 35, a secondary gearbox, and a tertiary gearbox. The primary gearbox 35 is located in front of the ultra-high pressure rotor 14 and includes a housing 52, an end cover 53, a fixing frame 61, gears 37 and 36, and a gear shaft 34. The housing 52 is a short cylindrical shape, with a shaft hole 58 at the rear of the cylinder. A bearing seat 59 is located outside the shaft hole 58, and a bearing 57 is installed inside the bearing seat 59. A seal can also be installed outside the bearing seat 59. A support 47 is located on the inner wall of the housing 52, and a bearing seat 48 is installed on the support 47. A flange 60 is located at the front of the housing 52. The flange 60 and end cover 53 are connected as a single unit. The end cover 53 has a wheel axle hole 55 at its center. A bearing seat 56 is located outside the wheel axle hole 55, and a bearing 54 is installed inside the bearing seat 56. A seal can also be installed outside the bearing seat 56. The fixing bracket 61 is fixed in the middle to the outside of the end cover 53 and at both ends to the high-pressure compressor housing 45. Gear 37 is mounted on the wheel axle 9, gear shaft 34 is mounted inside the bearing seat 48, and gear 36 is mounted on one end of gear shaft 34. Gear 36 and gear 37 are helical gears that mesh with each other. The secondary gearbox is equipped with... Located on one outer side of the front end of the chain box-shaped outer shell 21, the assembly includes a housing 33, bearing seats 32 and 29, gears 31 and 30, and gear shafts 34 and 28. The housing 33 and the bearing seats 32 and 29 inside it are mounted on the chain box-shaped outer shell 21 by riveting, screwing, or welding, preferably by riveting. The other end of the gear shaft 34 is mounted inside the bearing seat 32, and a gear 31 is mounted on its end. One end of the gear shaft 28 is mounted inside the bearing seat 29, and a gear 30 is mounted on its end. Gears 31 and 30 are bevel gears. The gears mesh with each other; the third-stage gearbox is located at the rear end of the chain box-shaped housing 21 on the same side as the second-stage gearbox, and includes a housing 27, a bearing seat 26, a gear shaft 28, a gear 25, and a gear 24. The housing 27 and the bearing seat 26 are installed on the outside of the chain box-shaped housing 21 and can be connected by riveting, screws, or welding, preferably by riveting. The other end of the gear shaft 28 is installed in the bearing seat 26 and a gear 25 is installed at its end. A gear 24 is installed on the long shaft end of the sprocket shaft 22 near the end of the third-stage gearbox. The gears 25 and 24 are bevel gears that mesh with each other.

[0049] The number of boosters installed is one or more. When there is more than one, they are evenly distributed around the central axis of the ultra-high pressure rotor 14. When there are multiple boosters, the number of spiral turns of the blades 41 of the ultra-high pressure rotor 14 should be increased accordingly. The standard is that when one booster plate 44 is about to push out of the rear end of the cavity between two adjacent blades, another booster plate 44 has entered the front end of the cavity. In this embodiment, there are four boosters. See Figure 1 , Figure 3 , Figure 7 , Figure 8 .

[0050] Figure 1 , Figure 3 In the compressor, the center surfaces of the two large flat plates of the chain box-shaped outer shell 21 pass through the central axis of the ultra-high pressure rotor 14. The high-pressure compressor housing 45 has an opening at the intersection line where it meets the chain box-shaped outer shell 21 and the housing 33. A chain-type booster device is installed at the intersection line opening. Each booster plate 44 within the boosting working range is inserted into the cavity of each adjacent blade 41 of the ultra-high pressure rotor 14 at the center surface of the two large flat plates of the chain box-shaped outer shell 21, so as to seal the air, push the air, and increase the air pressure. The chain box-shaped outer shell 21 is connected to the high-pressure compressor housing 45 by the wing plates 51 on the lower part of both sides. The connection method is rivet, screw, or welding, preferably rivet. A sealing structure is provided at the joint installation point of the above-mentioned installation intersection line opening. It is a superimposed edge strip, welded or sealing strip, preferably a superimposed edge strip, and riveted connection.

[0051] Manufacturing method of ultra-high pressure rotor 14: In Figures 25 to 29 In the process, the blades 41 on the outer periphery of the rotor cylinder 40 are divided into several small blades according to the latitude and longitude lines. Each small blade includes a tenon 80 and a blade body 81. The small blades and the rotor cylinder 40 are assembled using a tenon and mortise structure. The tenon grooves of the rotor cylinder 40 are axially set and run in a straight line from front to back, and are evenly distributed on the circumference. The small blades are inserted into the tenon grooves using the tenon 80 and connected to each other until the tenon groove is axially filled. Other tenon grooves are installed in the same way.

[0052] The number of divisions of the latitude and longitude lines is an approximation of the number of tenons and slots in the circumferential direction of the rotor cylinder 40, and an even number of divisions of the length in the axial direction. In this embodiment, there are 20 divisions in the circumferential direction and 4 divisions in the axial direction. The structure of the small blades in each division is the same. After assembly, the small blades that are adjacent to each other in the front, back, left and right are connected to form a spiral long blade 41.

[0053] Existing aircraft engine high-pressure compressor rotors consist of multiple sets of short blades arranged coaxially, one in front and one behind. Each set is separated by stator guide vanes. Air is expelled through the high-pressure compressor by the combined thrust of these multiple sets of blades. The space between the front and rear of the high-pressure compressor is open, lacking a sealed structure. Therefore, the high-pressure compressor's potential is not fully realized, resulting in low efficiency. Figure 2This invention employs a helical long blade 41 and a pressure-boosting plate 44 that functions similarly to a piston. During aircraft engine operation, the long blade 41 and pressure-boosting plate 44 work together to separate air at different pressures in the front and rear sections, forcefully expelling the air in a manner similar to an air compressor, significantly improving the operating efficiency of the aircraft engine. The ultra-high pressure rotor of this invention is manufactured using a modular method, facilitating manufacturing and maintenance. The pressure-boosting high-pressure compressor structure principle of this invention can also be applied to gas turbines.

Claims

1. An ultra-high pressure aircraft engine, comprising: The high-pressure compressor (6) is characterized in that it includes an ultra-high pressure rotor (14), a booster, and a high-pressure compressor housing (45).

2. The ultra-high pressure aircraft engine according to claim 1, characterized in that, The ultra-high pressure rotor (14) is a turbine rotor with a ring of neatly arranged spiral blades (41) on the outer circumference of the rotor cylinder (40), and is mounted on the main shaft of the aircraft engine through a wheel axle (9). Each blade (41) of the ultra-high pressure rotor (14) has 0.1 or more spiral turns from front to back on the rotor cylinder (40); the booster includes a chain booster device and a gearbox.

3. The ultra-high pressure aircraft engine according to claim 2, characterized in that, The chain booster device includes a chain booster housing, a drive sprocket assembly, a driven sprocket assembly, and a booster chain assembly (20). The chain booster housing includes a chain box-shaped shell (21), a guide rail (49), a guide rail bracket (50), and a wing plate (51). The chain box-shaped shell (21) is composed of two large flat plates and three side plates. It has two opposing guide holes (62) and a shaft hole (63) at the front and a shaft hole (64) at the rear. A guide rail bracket (50) is provided on each of the two lower sides inside the chain box-shaped shell (21). A guide rail (49) is provided on the inner side of the guide rail bracket (50). A wing plate (51) is provided on each of the two lower sides of the chain box-shaped shell (21). The drive sprocket assembly is installed on... The rear part of the chain box-shaped housing (21) includes a bearing (23), a drive sprocket shaft (22), and a drive sprocket (39). The two bearings (23) are respectively installed on the two opposite inner walls of the rear side of the chain box-shaped housing (21). The drive sprocket shaft (22) is installed on the two bearings (23), and the drive sprocket (39) is installed on the drive sprocket shaft (22). The diameter of the shaft hole (64) of the chain box-shaped housing (21) is larger than the diameter of one end of the drive sprocket shaft (22), and the shaft end of the drive sprocket shaft (22) extends freely from the shaft hole (64). The driven sprocket component is installed at the front part of the chain box-shaped housing (21) and includes a bearing seat (38), a driven sprocket shaft (15), and a driven sprocket (16). (38) Installed on both sides inside the chain box-shaped outer shell (21), the driven sprocket shaft (15) is installed on the two bearing seats (38), and the driven sprocket (16) is installed on the driven sprocket shaft (15). The bearing seat (38) includes a seat body, a bearing (77), a guide block (74), a shaft hole (75), and a fixing hole (76). The bearing (77) is installed in the bearing cavity at the front of the seat body. The guide block (74) is located at the rear of the seat body, and its thickness is slightly greater than the wall thickness of the chain box-shaped outer shell (21). The shaft hole (75) is a through hole with a diameter greater than the diameters at both ends of the driven sprocket shaft (15). The guide block (74) can move freely within the guide hole (62) of the chain box-shaped outer shell (21). The pressure boosting chain component (20) serves as a guide rail for the guide block (74). The pressure boosting chain component (20) includes a special-shaped chain (17) and a pressure boosting plate (44). The special-shaped chain (17) includes a regular chain link and a special-shaped chain link. The special-shaped chain link is integrally formed by two opposite special-shaped chain plates (43) and a middle plate (46). The regular link and the special-shaped chain link are alternately connected to form a circle through pin holes (42) and pin hinges. The pressure boosting plate (44) is set outside the middle plate (46) of the special-shaped chain link. The special-shaped chain (17) is installed on the driving sprocket (22) and the driven sprocket (16). The pressure boosting plate (44) moves inside the gap between two opposite guide rails (49) on the pressure boosting working side, and moves inside the chain box-shaped outer shell (21) on the rotating side.

4. The ultra-high pressure aircraft engine according to claim 3, characterized in that, The chain-type booster device also includes a tensioning component, installed on the chain box-shaped housing (21) near the driven sprocket (16), including a spring support (68), a movable support (65), a bearing seat (18), a tensioning synchronous shaft (19), a crank (69), and a connecting rod (66). The spring support (68) includes a seat body, a fixing hole (78), and a guide hole (79). The seat body is installed on the outside of the front two sides of the chain box-shaped housing (21) through the fixing hole (78). The movable support (65) includes a seat body (70), a shaft hole (71), a fixing hole (72), a guide post (73), and a spring (67). The spring (67) is concentrically installed on the guide post (73). One end of the guide post (73) is fixed to the outside of the side plate of the seat body (70), and the other end is inserted into the guide hole (79) of the spring support (68) with clearance fit. The seat body (70) is installed on the outside of the guide hole (79) through the fixing hole (72) and the bearing seat (18). 8) The fixing hole (76) is fixed by screws or rivets. The movable support (65) and the bearing seat (38) can move freely through the guide hole (62) on the guide block (74). The diameter of the shaft hole (71) is larger than the diameter of the driven sprocket shaft (15). The shaft ends of the driven sprocket shaft (15) extend freely from the shaft hole (75) of the bearing seat (38) and the shaft hole (71) of the movable support (65). There are two bearing seats (18). The two inner walls of the chain box-shaped housing (21) are respectively set on one side of the driven sprocket shaft (15); the tensioning synchronous shaft (19) is installed in the two bearing seats (18), and the shaft ends of the shafts at both ends extend out from the shaft holes (63) of the chain box-shaped housing (21) with clearance fit and respectively install a crank (69). The outer end of the crank (69) is hinged to one end of the connecting rod (66), and the other end of the connecting rod (66) is hinged to the shaft head of the driven sprocket shaft (15).

5. The ultra-high pressure aircraft engine according to claim 3, characterized in that, The guide rail (49) is a roller bar guide rail, a ball bar guide rail, or a sliding guide rail.

6. The ultra-high pressure aircraft engine according to claim 2, characterized in that, The gearbox of the booster includes a primary gearbox (35), a secondary gearbox, and a tertiary gearbox. The primary gearbox (35) is located in front of the ultra-high pressure rotor (14) and includes a housing (52), an end cover (53), a fixing frame (61), a gear (37), a gear (36), and a gear shaft (34). The housing (52) is a short cylindrical shape with a wheel axle hole (58) at the rear. A bearing seat (59) is located outside the wheel axle hole (58), and a bearing (57) is installed inside the bearing seat (59). A support (47) is located on the inner wall of the housing (52), and a bearing (57) is installed on the support (47). There is a bearing housing (48), and a flange (60) is provided at the front of the casing (52). The flange (60) and the end cover (53) are connected as a whole. The end cover (53) has a wheel axle hole (55) in the center. A bearing housing (56) is provided on the outside of the wheel axle hole (55). A bearing (54) is installed in the bearing housing (56). The middle part of the fixing bracket (61) is fixed to the outside of the end cover (53) and the two ends are fixed to the high pressure compressor casing (45). The gear (37) is installed on the wheel axle (9). The gear shaft (34) is installed in the bearing housing (48). The gear (36) is installed at one end of the gear shaft (34). 6) Engagement with gear (37): The secondary gearbox is located on one outer side of the front end of the chain box-shaped housing (21), including housing (33), bearing seat (32) and bearing seat (29), gear (31) and gear (30), gear shaft (34) and gear shaft (28). The housing (33) and the bearing seat (32) and bearing seat (29) provided inside it are all mounted on the chain box-shaped housing (21). The other end of the gear shaft (34) is mounted in the bearing seat (32) and the gear (31) is mounted at its end. The other end of the gear shaft (28) is mounted in the bearing seat (29) and the gear (30) is mounted at its end. The gears (31) and (30) mesh; the third-stage gearbox of the turbocharger is located at the rear end of the chain box-shaped housing (21) on the same side as the second-stage gearbox, including housing (27), bearing seat (26), gear shaft (28), gear (25), and gear (24). Housing (27) and bearing seat (26) are installed on the outside of chain box-shaped housing (21). The other end of gear shaft (28) is installed in bearing seat (26) and gear (25) is installed at its end. The sprocket shaft (22) has a long shaft end with gear (24) installed near the end of the third-stage gearbox. Gear (25) and gear (24) mesh.

7. The ultra-high pressure aircraft engine according to claim 6, characterized in that, The gears (37) and (36) are helical gears, and the gears (31), (30), (25), and (24) are bevel gears.

8. The ultra-high pressure aircraft engine according to claim 2, characterized in that, The number of boosters installed is one or more. When there is more than one, they are evenly distributed around the central axis of the ultra-high pressure rotor (14).

9. An ultra-high pressure aircraft engine according to any one of claims 1 to 8, characterized in that, The center plane of the two large plates of the chain box-shaped outer shell (21) of the booster passes through the central axis of the ultra-high pressure rotor (14). Each booster plate (44) within the boosting working range is inserted into the cavity of each blade (41) of the ultra-high pressure rotor (14) at the center plane of the two large plates of the chain box-shaped outer shell (21) to push the air and increase the air pressure.

10. The ultra-high pressure aircraft engine according to claim 9, characterized in that, The chain box-shaped outer shell (21) together with the shell (33) has an opening at the intersection line with the high-pressure compressor shell (45). A chain-type pressurizing device is installed at the intersection line opening. The chain box-shaped outer shell (21) and the high-pressure compressor shell (45) are connected as one unit through the wing plates (51) on the lower part of both sides. A sealing structure is provided at the joint installation point of the intersection line opening.

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