A flexible fairing for an aeroengine

Abstract

The present invention relates to the technical field related to engine fairings, and discloses an aircraft engine flexible fairing, which includes an upstream fairing. The upstream fairing has an air inlet, and a flexible film capable of inflating and expanding is coated on the edge of the air inlet. There is a fairing inner cavity in the upstream fairing. The upstream fairing is provided with an ice-breaking opening facing the flexible film at the edge of the air inlet. The ice-breaking opening is communicated with the fairing inner cavity. An ice-breaking block is slidably arranged in the ice-breaking opening. The top of the ice-breaking block can abut against the flexible film to cause the flexible film to locally expand outwards to break ice. A lever force-increasing device for driving the ice-breaking block to pop outwards is arranged in the fairing inner cavity, and an annular impact device for driving the lever force-increasing device is also arranged in the fairing inner cavity. The part where the ice layer is stronger receives a greater impact, and the place where the ice layer has been effectively broken will not be impacted again, performing work targeted, adaptively adjusting the key ice-breaking area, and effectively improving the ice-breaking efficiency.

Description

Technical Field

[0001] The present invention belongs to the technical field related to the cleaning of composite yarns, and more specifically, particularly relates to a flexible fairing for an aeroengine. Background Art

[0002] As the "heart" of modern aircraft, the core function of an aeroengine is to convert the chemical energy of fuel into mechanical energy, and then generate thrust or shaft power to provide flight power for the aircraft. When the aeroengine operates in a low-temperature and high-humidity environment, components such as the intake duct and fan blades are prone to icing, which affects the engine performance and flight safety. The common ice-breaking means in the prior art include:

[0003] Hot-air anti-icing: Extract a part of high-temperature and high-pressure gas from the engine compressor, transport it through a pipeline to the parts that need anti-icing, and use the heat to prevent icing or melt the existing ice; Electro-thermal anti-icing: Install an electric heating element at the parts that need anti-icing, and convert electrical energy into heat energy to prevent icing or melt the existing ice; Mechanical de-icing: Install an expandable rubber airbag or mechanical device at the parts that need anti-icing, and break the ice layer through periodic expansion and contraction; Liquid anti-icing: Spray an anti-icing liquid at the parts that need anti-icing to lower the freezing point of water and prevent icing or melt the existing ice.

[0004] The prior art also has the following technical problems:

[0005] The mechanical ice-breaking system usually adopts a fixed ice-breaking force. For example, the expansion pressure of the rubber airbag or the impact force of the mechanical device is preset and cannot be dynamically adjusted according to the actual icing situation. When the ice layer is thin, the excessive ice-breaking force will cause unnecessary energy waste and may even damage the engine components. When the ice layer is thick, the fixed ice-breaking force may not be able to effectively break the ice layer, affecting the engine performance and flight safety.

[0006] During the actual flight process, the icing conditions are complex and changeable. For example, factors such as the ice layer thickness, ice shape, temperature, and humidity will affect the icing speed and ice layer strength. The existing mechanical ice-breaking system is difficult to cope with these complex and changeable factors and cannot achieve precise ice-breaking control, which may lead to incomplete ice-breaking or excessive ice-breaking.

[0007] Therefore, in view of this, research and improvement are carried out on the existing structure, and a flexible fairing for an aeroengine is provided with the expectation of achieving a more practical value. Summary of the Invention

[0008] The present invention provides a flexible fairing for an aeroengine to overcome the above defects in the prior art.

[0009] The purpose and efficacy of a flexible fairing for an aeroengine of the present invention are achieved by the following specific technical means:

[0010] The present invention provides an aircraft engine flexible fairing, comprising an upstream fairing, wherein the upstream fairing has an air inlet, an inflatable flexible membrane is covered at the edge of the air inlet, a fairing inner cavity is provided in the upstream fairing, an ice-breaking port facing the flexible membrane is provided at the edge of the air inlet of the upstream fairing, the ice-breaking port is communicated with the fairing inner cavity, an ice-breaking block is slidably arranged in the ice-breaking port, the top of the ice-breaking block can abut against the flexible membrane so that the flexible membrane partially expands outward and breaks the ice, a lever forcing device for driving the ice-breaking block to pop out outward is provided in the fairing inner cavity, and an annular impact device for driving the lever forcing device is also provided in the fairing inner cavity, the lever forcing device comprises a hinged bracket fixedly mounted on the inner wall of the fairing inner cavity, a force-boosting bracket is hingedly provided in the hinged bracket, and the force-boosting bracket is in a hook shape. It also has a long handle and a short handle connected to each other, the long handle and the short handle are fixedly connected and form an acute angle, the length of the long handle is greater than the length of the short handle, the short handle abuts against the ice block and hits the ice block to pop out, the annular impact device can hit the long handle and use the lever principle to enhance the thrust applied to the ice block by the short handle, the annular impact device includes an annular pneumatic slide rail, an impact body and a pop-up body, the impact body slides in the annular pneumatic slide rail under the action of pneumatic force, the annular pneumatic slide rail has a number of pop-up holes, and the pop-up body is slidably arranged in the pop-up hole, one end of the pop-up body abuts the long handle, and the other end of the pop-up body protrudes into the inside of the annular pneumatic slide rail, an elastic member is arranged between the pop-up body and the annular pneumatic slide rail to push the pop-up body to abut in the direction close to the long handle, and the impact body hits the protruding part of the pop-up body to make the pop-up body pop out and hit the long handle.

[0011] A further technical solution is that the annular pneumatic slide includes a first ring and a second ring, the first ring and the second ring are paired to form a sealed air cavity, the impact body slides in the sealed air cavity, an ejection hole is opened on the first ring, and the second ring is fixedly installed on the inner wall of the fairing cavity, the first ring can rotate relative to the second ring to adjust the distance between the contact point between the ejection body and the long handle and the hinge point between the force booster bracket and the hinged bracket.

[0012] A further technical solution is that the second ring has two second semicircular grooves that are symmetrical on the left and right, and a first air vent is opened on the second ring, and the first air vent is respectively connected to the two second semicircular grooves. The first ring has a first semicircular groove that is symmetrical on the left and right, and a second air vent is opened on the first ring, and the second air vent is respectively connected to the two first semicircular grooves. The second air vent is connected to a penetration tube, and the second ring has an arc-shaped air cavity, and the penetration tube slides in the arc-shaped air cavity. The second ring is also provided with a through groove connecting the arc-shaped air cavity.

[0013] For a further technical solution, the bottom walls of the first semi-circular groove and the second semi-circular groove are both elastic layers. The elastic layer includes a smooth layer and a rubber layer. The impact body contacts the smooth layer, and the rubber layer can elastically contract under force to increase the passing ability of the impact body. Arc-shaped grooves are provided at the positions corresponding to the ejection holes on the bottom walls of the first semi-circular groove and the second semi-circular groove, and the depth of the arc-shaped grooves gradually increases along the moving path of the impact body. The elastic layer covers the arc-shaped grooves.

[0014] For a further technical solution, the part of the ejection body extending into the internal part of the annular pneumatic slide rail is the struck head, the part where the ejection body contacts the long handle is the impact head, and the impact body is a spherical body; the struck head is a wedge-shaped block, or the struck head is spherical; and / or, the long handle inclines towards the annular pneumatic slide rail, and along the length direction of the long handle, the bottom surface of the long handle gradually approaches the ejection body.

[0015] For a further technical solution, the middle diameter of the ejection body expands outwards to form a stepped portion, the diameter of the ejection hole increases towards the side of the force-increasing bracket to form a stepped hole, a return spring is arranged between the stepped portion and the stepped hole, and the return spring pushes the ejection body to abut against the long handle.

[0016] For a further technical solution, a sealing ring is arranged inside the fairing cavity, and a sealing ring is arranged between the second ring and the inner wall of the fairing cavity. The sealing ring isolates the fairing cavity and forms positive and negative air cavities. The center of the ice-breaking block has a central groove, the top of the ice-breaking block has an ice-breaking nozzle, the side of the ice-breaking block has a switching port, both the ice-breaking nozzle and the switching port communicate with the central groove, the ice-breaking nozzle faces the flexible diaphragm, the wall of the ice-breaking opening has air holes, one end of the air holes communicates with the positive and negative air cavities, and the other end communicates with the ice-breaking opening. The ice-breaking block moves upwards from the ice-breaking opening towards the flexible diaphragm so that the switching port communicates with the air holes.

[0017] For a further technical solution, the diameter of one end of the ice-breaking block facing the flexible diaphragm is reduced, so that an exhaust gap is formed between the outer wall of the ice-breaking block and the inner wall of the ice-breaking opening. When the ice-breaking block is hidden in the ice-breaking opening, the exhaust gap communicates with the air holes.

[0018] For a further technical solution, a positive and negative pressure generator is arranged inside the fairing cavity. The positive and negative pressure generator has a pressurizing pipe and an air inlet pipe. The pressurizing pipe passes through the sealing ring and communicates with the positive and negative air cavities. The positive and negative pressure generator also has a negative pressure pipe. The negative pressure pipe passes through the sealing ring and communicates with the positive and negative air cavities. Electromagnetic switching valves are arranged on both the pressurizing pipe and the negative pressure pipe.

[0019] Further technical solution: A high-pressure generator is also provided inside the fairing cavity. The high-pressure generator has a gas supply pipe and an air outlet pipe. The air outlet pipe is connected to a switching valve. The switching valve has a second pipe and a first pipe. The first pipe communicates with a first ventilation hole. The second pipe communicates with a through groove. The switching valve also has an exhaust pipe that communicates with the atmosphere. The switching valve has two ventilation paths. The first ventilation path is that the high-pressure air flow sequentially passes through the air outlet pipe, the first pipe, the first ventilation hole, the through groove, the second pipe, and the exhaust pipe. The second ventilation path is that the high-pressure air flow sequentially passes through the second pipe, the through groove, the first ventilation hole, the first pipe, and the exhaust pipe.

[0020] Further technical solution: A piston slide plate is fixedly provided on the outer wall of the first ring. The first ring rotates annularly inside the fairing cavity, and a ring groove is formed between the first ring and the inner cavity of the fairing. The piston slide plate slides annularly in the ring groove. The inner wall of the fairing cavity protrudes with a first limiting body and a second limiting body. The piston slide plate slides between the first limiting body and the second limiting body. The sealing ring is provided with a first hole and a second hole. Both the first hole and the second hole communicate with the ring groove, and the piston slide plate is located between the first hole and the second hole.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] A flexible fairing of an aeroengine according to the present invention, by providing a flexible film, ice-breaking blocks, force-increasing brackets, annular pneumatic slide rails, etc., on the one hand, can ensure the basic function of expanding and breaking ice into the flexible film, and on the other hand, increases the function of adaptive mechanical ice-breaking. Since the ice layer is uneven in thickness in a circumferential distribution at the air inlet of the upstream fairing, the impact force required to break the ice layer is different. When the ice layer is relatively thin at a certain place, the ice-breaking block at that place can smoothly push the flexible film to break through the ice layer, and the ice-breaking block protrudes outwards, causing the switching port to communicate with the air hole. The high-pressure gas in the positive and negative air cavities is sprayed outwards through the central groove, the switching port, and the ice-breaking nozzle, so that the flexible film expands to break the ice, so as to realize the combination of mechanical vibration ice-breaking and inflatable ice-breaking.

[0023] When the ice layer is relatively thick at a certain place, it is difficult for the ice-breaking block at that place to move outwards. The boosting device adjusts the rotation angle of the first ring, and the ejecting body rotates together with the first ring. Since the long handle extends obliquely, at the initial position, the distance between the long handle and the first ring is large, and the return spring pushes the ejecting body to extend and abut against the long handle. At this time, the length of the ejecting body extending into the sealed air cavity is small, and the distance from the contact point between the ejecting body and the long handle to the hinge point of the force-increasing bracket is the end, that is, the force amplification effect of the lever is reduced. The impact force exerted by the ejecting body on the long handle will act on the ice-breaking block in a small-scale amplified state. At this time, the impact force of the ice-breaking block on the flexible film is small, which is suitable for the situation where the ice layer is thin and can reduce the sense of vibration; increasing the rotation angle of the first ring, the ejecting body moves towards the low point of the long handle, and the lever action is amplified. The extrusion exerted by the ejecting body on the long handle will be amplified, which is suitable for the ice layer with high strength.

[0024] Where the ice layer is broken after the first impact, the long handle will be pushed by the ejector to rotate upward. The length of the ejector extending into the sealed air chamber is small. Where the ice layer is not broken or slightly broken, the long handle is pushed by the ejector to rotate upward at a small angle, and the length of the ejector extending into the sealed air chamber is large. That is to say, several ejectors will protrude from the sealed air chamber to different degrees according to different ice-breaking effects. The more difficult it is to break through the ice layer, the longer the ejector at the corresponding position extends into the sealed air chamber. The easier it is to break through the ice layer, the ejector at the corresponding position will reduce its extension into the sealed air chamber under the push of the return spring. With the high-speed impact of the impact body again, those ejectors with small or no extension will be less impacted or not impacted at all, while those ejectors with large extension will be more impacted. The stronger the ice layer, the greater the impact it receives. The places where the ice layer has been effectively broken will not be impacted again, doing work targeted, reducing useless work, and each work can effectively target the places where it is difficult to break the ice, adaptively adjusting the key ice-breaking areas, and effectively improving the ice-breaking efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0026] The present invention will be further described below in conjunction with the drawings and embodiments.

[0027] Figure 1 is the overall structural schematic diagram of the upstream fairing 10 in the present invention;

[0028] Figure 2 is Figure 1 the enlarged structural schematic diagram at A in

[0029] Figure 3 is the structural schematic diagram of the cooperation between the ice-breaking block 16 and the force-increasing bracket 22 in the present invention;

[0030] Figure 4 is the structural schematic diagram after the flexible film 11 is separated from the upstream fairing 10 in the present invention;

[0031] Figure 5 is the disassembled schematic diagram of the ice-breaking block 16, the force-increasing bracket 22, the first ring 18 and the second ring 19 in the present invention;

[0032] Figure 6 is the front view of the first ring 18 in the present invention;

[0033] Figure 7It is the front view of the second ring 19 in the present invention;

[0034] Figure 8 It is the sectional view at the air inlet of the upstream fairing 10 in the present invention;

[0035] Figure 9 It is Figure 8 the enlarged structural schematic diagram of the ice-breaking block 16 in;

[0036] Figure 10 It is the structural schematic diagram of the cooperation between the piston slide plate 57 and the ring groove 58;

[0037] Figure 11 It is the structural schematic diagram of the second embodiment in the present invention;

[0038] Figure 12 It is the structural schematic diagram of the rotating ring 72 in the third embodiment in the present invention;

[0039] Figure 13 It is the structural schematic diagram of the arc-shaped groove 73 in the third embodiment in the present invention;

[0040] Figure 14 It is the overall structural schematic diagram of the aero-engine in the fourth embodiment in the present invention;

[0041] Figure 15 It is Figure 14 the sectional view of the aero-engine in;

[0042] Figure 16 It is Figure 15 the front view of.

[0043] Explanation of reference numerals:

[0044] Upstream fairing 10, flexible film 11, fairing inner cavity 13, ice-breaking opening 14, ice-breaking block 16, first ring 18, second ring 19, ice-breaking nozzle 20, hinged bracket 21, force-increasing bracket 22, ejecting body 23, long handle 24, short handle 25, sealed air cavity 27, sealing ring 28, positive and negative air cavities 29, first semi-circular groove 31, ejecting hole 32, second semi-circular groove 33, first vent hole 34, second vent hole 35, impact body 36, through groove 39, arc-shaped air cavity 40, return spring 41, switching port 43, exhaust gap 44, air hole 45, positive and negative pressure generator 46, pressure-increasing pipe 47, intake pipe 48, negative pressure pipe 49, high-pressure generator 50, air supply pipe 51, outlet pipe 52, switching valve 53, second pipe 54, first pipe 55, exhaust pipe 56, piston slide plate 57, ring groove 58, first hole 59, second hole 60, first limiting body 61, second limiting body 62, central groove 65, inner fairing 70, engine body 71, rotating ring 72, arc-shaped groove 73, smooth layer 75, rubber layer 76, annular body 77, gear ring 78, internal gear 79, electric motor 80, annular boss 81, stepped portion 82. Detailed implementation mode

[0045] The following further describes in detail the implementation mode of the present invention in conjunction with the drawings and embodiments. The following embodiments are used to illustrate the present invention, but cannot be used to limit the scope of the present invention.

[0046] In the description of the present invention, unless otherwise specified, "a plurality of" means two or more; the orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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 a limitation to the present invention. In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0047] [[ID=,11]]In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "connected" and "connected" should be understood in a broad sense. For example, it 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 directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0048] Example 1: Refer to the attached Figure 1-10, an aircraft engine flexible fairing, including an upstream fairing 10. The upstream fairing 10 has an air inlet, and a flexible film 11 that can be inflated and expanded is coated on the edge of the air inlet. There is a fairing inner cavity 13 inside the upstream fairing 10. The upstream fairing 10 is provided with an ice-breaking opening 14 facing the flexible film 11 at the edge of the air inlet. The ice-breaking opening 14 is communicated with the fairing inner cavity 13. An ice-breaking block 16 is slidably arranged in the ice-breaking opening 14. The top of the ice-breaking block 16 can abut against the flexible film 11 to cause the flexible film 11 to bulge outwards locally to break the ice. A lever force-increasing device for driving the ice-breaking block 16 to pop outwards is arranged in the fairing inner cavity 13, and an annular impact device for driving the lever force-increasing device is also arranged in the fairing inner cavity 13. The lever force-increasing device includes a hinged bracket 21 fixedly installed on the inner wall of the fairing inner cavity 13. A force-increasing bracket 22 is hingedly arranged in the hinged bracket 21. The force-increasing bracket 22 is in a hook shape and has a long handle 24 and a short handle 25 connected to each other. The long handle 24 and the short handle 25 are fixedly connected and form an acute angle. The length of the long handle 24 is greater than the length of the short handle 25. The short handle 25 abuts against the ice-breaking block 16 and impacts the ice-breaking block 16 to pop outwards. The annular impact device can impact the long handle 24 and use the lever principle to enhance the thrust exerted by the short handle 25 on the ice-breaking block 16. The annular impact device includes an annular pneumatic slide rail, an impact body 36 and a pop-up body 23. The impact body 36 slides in the annular pneumatic slide rail under the action of air pressure. A number of pop-up holes 32 are opened in the annular pneumatic slide rail. The pop-up body 23 is slidably arranged in the pop-up holes 32. One end of the pop-up body 23 abuts against the long handle 24, and the other end of the pop-up body 23 protrudes into the annular pneumatic slide rail. An elastic member is arranged between the pop-up body 23 and the annular pneumatic slide rail to push the pop-up body 23 to abut against the long handle 24 along the direction close to the long handle 24. The impact body 36 impacts the protruding part of the pop-up body 23 to cause the pop-up body 23 to pop outwards and impact the long handle 24.

[0049] In specific implementation, the impact body 36 itself can be a spherical mass block, or other shapes adapted to the annular pneumatic slide rail, such as an arc block, etc. In this embodiment, the power source of the impact body 36 is high-pressure gas. In other embodiments, the power source of the impact body 36 can also be selected as a hydraulic system or an electromagnetic drive method. The advantage of using a high-pressure gas source is that it is convenient to convert the internal energy of the high-pressure gas source into the kinetic energy of the impact body 36 itself to produce a high-speed impact effect. However, using hydraulic energy to push the impact body 36 cannot push the impact body 36 to move at high speed, but it has the effect of low speed and high pressure, can provide a large thrust for the impact body 36, and can adapt to the working conditions of breaking particularly thick ice layers.

[0050] Preferably, the annular pneumatic slide rail includes a first ring 18 and a second ring 19. The first ring 18 and the second ring 19 are paired to form a sealed air chamber 27. The impact body 36 slides within the sealed air chamber 27. A pop-up hole 32 is formed on the first ring 18. The second ring 19 is fixedly installed on the inner wall of the fairing cavity 13. The first ring 18 can rotate relative to the second ring 19 to adjust the distance between the contact point of the pop-up body 23 and the long handle 24 and the hinge point between the force-increasing bracket 22 and the hinge bracket 21.

[0051] Specifically, the contact point of the pop-up body 23 and the long handle 24 is defined as point A, the hinge point of the force-increasing bracket 22 and the hinge bracket 21 is positioned as point B, and the contact point of the short handle 25 and the ice-breaking block 16 is defined as point C. The distance between point A and point B is L1, and the distance between point C and point B is L2. L1 is greater than L2. As the first ring 18 rotates, point A moves to adjust the size of L1, thereby adjusting the impact force of the short handle 25 on the ice-breaking block 16.

[0052] Preferably, the second ring 19 has two second semi-circular grooves 33 that are symmetric about the left and right. A first ventilation hole 34 is formed on the second ring 19. The first ventilation hole 34 communicates with the two second semi-circular grooves 33 respectively. The first ring 18 has two first semi-circular grooves 31 that are symmetric about the left and right. A second ventilation hole 35 is formed on the first ring 18. The second ventilation hole 35 communicates with the two first semi-circular grooves 31 respectively. The second ventilation hole 35 is connected with a penetration tube. An arc-shaped air chamber 40 is formed on the second ring 19. The penetration tube slides within the arc-shaped air chamber 40. The second ring 19 is further provided with a through groove 39 that communicates with the arc-shaped air chamber 40.

[0053] Preferably, the bottom walls of both the first semi-circular groove 31 and the second semi-circular groove 33 are elastic layers.

[0054] Specifically, the elastic layer includes a smooth layer 75 and a rubber layer 76. The impact body 36 contacts the smooth layer 75. The rubber layer 76 can elastically contract under force to increase the passing performance of the impact body 36. Arc-shaped grooves 73 are formed at the positions corresponding to the pop-up hole 32 on the bottom walls of the first semi-circular groove 31 and the second semi-circular groove 33. The depth of the arc-shaped grooves 73 gradually increases along the moving path of the impact body 36. The elastic layer covers the arc-shaped grooves 73.

[0055] Preferably, the part of the pop-up body 23 extending into the annular pneumatic slide rail is the struck head, the part where the pop-up body 23 contacts the long handle 24 is the impact head, and the impact body 36 is a spherical body; the struck head is a wedge-shaped block, or the struck head is spherical. The long handle 24 inclines towards the first ring 18. Along the length direction of the long handle 24, the bottom surface of the long handle 24 gradually approaches the pop-up body 23.

[0056] In this embodiment, the struck head is a wedge-shaped block, and the force applied by the impact body 36 to the wedge-shaped block can be decomposed into the force of the pop-up body 23 hitting the long handle 24 according to a certain ratio.

[0057] Preferably, the middle diameter of the ejector body 23 expands outward to form a stepped portion 82, the diameter of the ejection hole 32 increases toward the side of the force-increasing bracket 22 to form a stepped hole, a return spring 41 is arranged between the stepped portion 82 and the stepped hole, and the return spring 41 pushes the ejector body 23 to abut against the long handle 24.

[0058] Since the long handle 24 is inclined, as the first ring 18 rotates, the ejector body 23 is squeezed by the long handle 24 and extends downward into the sealed air cavity 27. The elongation of the ejector body 23 is determined by two factors. One is the rotation angle of the first ring 18, and the other is the amount of ice layer broken. When the ice layer is not broken, the ejector body 23 can only extend into the sealed air cavity 27, and the ejector body 23 will be impacted by the impact body 36. After the ice layer is effectively broken, the force-increasing bracket 22 will swing outward, and the long handle 24 will not cause the ejector body 23 to squeeze the return spring 41 and extend into the sealed air cavity 27.

[0059] Preferably, a sealing ring 28 is arranged in the inner cavity 13 of the fairing. A sealing ring 28 is arranged between the second ring 19 and the inner wall of the inner cavity 13 of the fairing. The sealing ring 28 isolates the inner cavity 13 of the fairing and forms positive and negative air cavities 29. The center of the ice-breaking block 16 has a central groove 65, the top of the ice-breaking block 16 has an ice-breaking nozzle 20, the side of the ice-breaking block 16 has a switching port 43, both the ice-breaking nozzle 20 and the switching port 43 communicate with the central groove 65, the ice-breaking nozzle 20 faces the flexible diaphragm 11, the wall of the ice-breaking opening 14 has air holes 45, one end of the air holes 45 communicates with the positive and negative air cavities 29, and the other end communicates with the ice-breaking opening 14. The ice-breaking block 16 moves upward from the ice-breaking opening 14 toward the flexible diaphragm 11 so that the switching port 43 communicates with the air holes 45.

[0060] Preferably, the diameter of one end of the ice-breaking block 16 facing the flexible diaphragm 11 is reduced, so that an exhaust gap 44 is formed between the outer wall of the ice-breaking block 16 and the inner wall of the ice-breaking opening 14. When the ice-breaking block 16 is hidden in the ice-breaking opening 14, the exhaust gap 44 communicates with the air holes 45.

[0061] In this embodiment, when the ice-breaking block 16 does not protrude and extrude the flexible diaphragm 11 outward, the high-pressure air flow in the positive and negative air cavities 29 can still pass through the air holes 45 and the exhaust gap 44 and provide air flow for the expansion of the flexible diaphragm 11. That is to say, the device can simultaneously have dual working modes of mechanical vibration deicing or pneumatic expansion deicing, and the pneumatic expansion deicing works relatively independently without being restricted by the mechanical vibration deicing.

[0062] Preferably, a positive and negative pressure generator 46 is arranged in the inner cavity 13 of the fairing. The positive and negative pressure generator 46 has a pressure-increasing pipe 47 and an air inlet pipe 48. The pressure-increasing pipe 47 passes through the sealing ring 28 and communicates with the positive and negative air cavities 29. The positive and negative pressure generator 46 also has a negative pressure pipe 49. The negative pressure pipe 49 passes through the sealing ring 28 and communicates with the positive and negative air cavities 29. Electromagnetic switching valves are arranged on both the pressure-increasing pipe 47 and the negative pressure pipe 49.

[0063] In this embodiment, the function of the positive and negative pressure generator 46 is to provide a high-pressure or negative-pressure environment for the positive and negative air chambers 29. The high-pressure environment means that the positive and negative pressure generator 46 sucks air from the intake pipe 48 and discharges it into the positive and negative air chambers 29 through the booster pipe 47, forming a high-pressure environment. The high-pressure gas provides kinetic energy for the expansion of the flexible diaphragm 11. The negative-pressure environment means that the positive and negative pressure generator 46 sucks air from the positive and negative air chambers 29 and discharges it through the negative-pressure pipe 49 and the intake pipe 48, creating a low-pressure environment inside the positive and negative air chambers 29, so that the flexible diaphragm 11 contracts and clings to the aerodynamic shape of the upstream fairing 10.

[0064] Preferably, a high-pressure generator 50 is further provided inside the fairing cavity 13. The high-pressure generator 50 has a supplementary air pipe 51 and an outlet pipe 52. The outlet pipe 52 is connected to a switching valve 53. The switching valve 53 has a second pipe 54 and a first pipe 55. The first pipe 55 communicates with the first ventilation hole 34, and the second pipe 54 communicates with the through groove 39. The switching valve 53 also has an exhaust pipe 56, and the exhaust pipe 56 communicates with the atmosphere. The switching valve 53 has two ventilation paths. The first ventilation path is that the high-pressure air flow sequentially passes through the outlet pipe 52, the first pipe 55, the first ventilation hole 34, the through groove 39, the second pipe 54, and the exhaust pipe 56. The second ventilation path is that the high-pressure air flow sequentially passes through the second pipe 54, the through groove 39, the first ventilation hole 34, the first pipe 55, and the exhaust pipe 56.

[0065] In this embodiment, the high-pressure generator 50 will suck gas from the supplementary air pipe 51 and pressurize it. The pressurized gas enters the switching valve 53 through the outlet pipe 52. The switching valve 53 switches the ventilation path to provide a power source for the bidirectional movement of the impact body 36 in the sealed air chamber 27.

[0066] Preferably, a piston slide plate 57 is fixedly provided on the outer wall of the first ring 18. The first ring 18 rotates annularly inside the fairing cavity 13, and a ring groove 58 is formed between the first ring 18 and the inner wall of the fairing cavity 13. The piston slide plate 57 slides annularly in the ring groove 58. First limit bodies 61 and second limit bodies 62 protrude from the inner wall of the fairing cavity 13. The piston slide plate 57 slides between the first limit body 61 and the second limit body 62. A first hole 59 and a second hole 60 are provided on the sealing ring 28. Both the first hole 59 and the second hole 60 communicate with the ring groove 58, and the piston slide plate 57 is located between the first hole 59 and the second hole 60.

[0067] Specifically, the device further has a boosting device. The boosting device is used to introduce hydraulic oil into the first hole 59. The liquid enters the ring groove 58 and pushes the piston slide plate 57 to rotate. The liquid in the ring groove 58 flows back to the boosting device through the second hole 60, thereby controlling the angle of the piston slide plate 57 in the ring groove 58 to adjust the rotation angle of the first ring 18.

[0068] Embodiment 2, refer to the appendixFigure 11 : The present invention also provides a kinetic energy device for driving the ejector body 23 to extrude towards the long handle 24. The kinetic energy device is an annular body 77. The annular body 77 replaces the second ring 19 in Embodiment 1. The outer wall surface of the first ring 18 has an external thread, and the inner wall surface of the annular body 77 has an internal thread. The internal thread cooperates with the external thread. The annular body 77 has an annular boss 81 on the side facing the first ring 18. As the first ring 18 and the annular body 77 rotate relative to each other, the annular boss 81 can abut against the ejector body 23, so that the ejector body 23 protrudes outward to extrude the long handle 24, realizing the function of extrusion and ice breaking.

[0069] To drive the rotation of the annular body 77, a transmission device and a motor 80 are arranged in the fairing cavity 13. The transmission device includes an internal gear 79 and a gear ring 78. The gear ring 78 is concentrically fixed on the annular body 77. The internal gear 79 meshes with the gear ring 78. The internal gear 79 is connected to the shaft of the motor 80 through a coupling.

[0070] Embodiment 3, refer to the attached Figure 12-13 : The present invention also provides a rotating device for driving the impact body 36 to move. The device includes a rotating ring 72 with a large mass. The impact body 36 is arranged on the rotating ring 72. To drive the rotating ring 72, the transmission device and the motor in Embodiment 2 are arranged in the fairing cavity 13.

[0071] Preferably, a plurality of impact bodies 36 distributed circumferentially are arranged on the rotating ring 72, and arc-shaped grooves 73 with the same number as the impact bodies 36 are arranged on the rotating ring 72. The impact bodies 36 slide in the arc-shaped grooves 73. A cavity for accommodating an elastic device is formed between the impact bodies 36 and the two walls of the arc-shaped grooves 73. The elastic device is used to keep the impact bodies 36 in position in the arc-shaped chutes.

[0072] Preferably, the depth of the arc-shaped chute gradually increases, so that the height of the impact body 36 protruding from the arc-shaped chute changes with the position of the impact body 36 in the arc-shaped chute.

[0073] In this embodiment, when the rotating ring 72 drives the impact bodies 36 to rotate at a high speed, the impact bodies 36 will impact the ejector body 23. If the length of the ejector body 23 is too long, resulting in the impact bodies 36 being unable to push the ejector body 23 outward immediately, under the block of the ejector body 23, the impact bodies 36 will move in the arc-shaped chute and press the elastic device. In this embodiment, the elastic device can adopt a spring, an elastic pad, a rubber layer, etc. The height of the impact bodies 36 gradually decreases, so as to stagger the contact with the ejector body 23 to ensure the smoothness of the rotation process of the rotating ring 72.

[0074] Embodiment 4, refer to the attached Figure 14-16 : The present invention also provides an aeroengine, which includes the fairing of Embodiment 1. An inner fairing 70 is arranged in the fairing, and an engine body 71 is arranged in the inner fairing 70.

[0075] Working process of the present invention:

[0076] In the low-temperature state, an ice shell will form on the surface of the flexible diaphragm 11. In order to remove the ice shell and ensure the original aerodynamic shape, the positive and negative pressure generator 46 starts the positive pressure working mode, sucks gas from the intake pipe 48 and injects it into the positive and negative air chambers 29 through the booster pipe 47. The high-pressure gas in the positive and negative air chambers 29 passes through the air holes 45 and the exhaust gap 44, so that the flexible diaphragm 11 expands and deforms to facilitate ice breaking.

[0077] If the ice layer is thick and the increase in air pressure cannot cause effective expansion of the flexible diaphragm 11, the high-pressure generator 50 is started, and the switching valve 53 is switched to the first working state. The first ventilation path is opened, and gas is sucked from the supplementary air pipe 51. After being pressurized by the high-pressure generator 50, it passes through the outlet pipe 52, the first pipe 55, the first ventilation hole 34, the through groove 39, the second pipe 54, and the exhaust pipe 56 in sequence. When the air flow flows in the sealed air chamber 27, it pushes the impact body 36 to move at high speed from one end close to the first ventilation hole 34 to one end close to the through groove 39. The impact body 36 moving at high speed in the sealed air chamber 27 will impact the protruding part of the ejector body 23. The ejector body 23 is ejected by the impact, impacts the long handle 24, the long handle 24 swings and drives the short handle 25 to impact the ice-breaking block 16. The ice-breaking block 16 moves from the state hidden in the ice-breaking opening 14 to the state protruding outward. The flexible diaphragm 11 is impacted by the ice-breaking block 16 and thus protrudes, so as to achieve the effect of mechanical vibration ice breaking.

[0078] Since the ice-breaking blocks 16 are annularly distributed on the edge of the air inlet of the upstream fairing 10, the ice layer can be broken evenly in the circumferential direction.

[0079] The ice layer is uneven in thickness in the circumferential distribution at the air inlet of the upstream fairing 10, resulting in different impact forces required to break the ice layer. When the ice layer is relatively thin at a certain place, the ice-breaking block 16 at that place can smoothly push the flexible diaphragm 11 to break through the ice layer, and the ice-breaking block 16 protrudes outward, causing the switching port 43 to communicate with the air hole 45. The high-pressure gas in the positive and negative air chambers 29 is ejected outward through the central groove 65, the switching port 43, and the ice-breaking nozzle 20, so that the flexible diaphragm 11 expands to break the ice, so as to achieve the combination of mechanical vibration ice breaking and inflation ice breaking. When the ice layer is relatively thick at a certain place, the ice-breaking block 16 at that place is difficult to move outward. The impact body 36 impacts the ejector body 23 and moves outward. The ejector body 23 transmits the impact force to the long handle 24 and the short handle 25 to the ice-breaking block 16. The ice-breaking block 16 will squeeze the flexible diaphragm 11 itself, but the ice layer will not be damaged.

[0080] In order to cope with the uneven distribution of ice layer thickness, the pressurizing device injects hydraulic oil into the annular groove 58 through the first hole 59 to drive the piston slide plate 57 to rotate in the annular groove 58 and adjust the rotation angle of the first ring 18. The ejector body 23 rotates together with the first ring 18. Since the long handle 24 extends obliquely, at the initial position, the distance between the long handle 24 and the first ring 18 is large. The return spring 41 pushes the ejector body 23 to extend and abut against the long handle 24. At this time, the length of the ejector body 23 extending into the sealed air chamber 27 is small, and the contact point between the ejector body 23 and the long handle 24 extends to the distance end of the hinge point of the force-increasing bracket 22. That is to say, the force amplification effect of the lever is reduced. The impact force exerted by the ejector body 23 on the long handle 24 will act on the ice-breaking block 16 in a small-proportion amplified state. At this time, the impact force of the ice-breaking block 16 on the flexible diaphragm 11 is small; increase the rotation angle of the first ring 18 to displace the ejector body 23 towards the low point of the long handle 24. At the place where the ice layer is broken after the first impact, the long handle 24 will be pushed upwards by the ejector body 23, and the compression amount of the return spring 41 is small, and the length of the ejector body 23 extending into the sealed air chamber 27 is small. At the place where the ice layer is not broken or the degree of breakage is small, the angle by which the long handle 24 is pushed upwards by the ejector body 23 is small, the compression amount of the return spring 41 increases, and the length of the ejector body 23 extending into the sealed air chamber 27 is large. That is to say, the lengths of several ejector bodies 23 protruding from the sealed air chamber 27 will vary according to different ice-breaking effects. The more difficult it is to break through the ice layer, the longer the corresponding ejector body 23 extends into the sealed air chamber 27. The easier it is to break through the ice layer, the corresponding ejector body 23 will reduce its extension into the sealed air chamber 27 under the push of the return spring 41. With the repeated high-speed impact of the impact body 36, those ejector bodies 23 with small or no elongation will receive less or no impact, while those ejector bodies 23 with large elongation will receive greater impact. The stronger the ice layer, the greater the impact it receives. The places where the ice layer has been effectively broken will not be impacted again, doing work targeted, reducing useless work, and each work can effectively target the places where it is difficult to break the ice, adaptively adjusting the key ice-breaking areas, and effectively improving the ice-breaking efficiency.

[0081] The embodiments of the present invention are given for purposes of illustration and description, and are not exhaustive or limit the invention to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are chosen and described in order to better illustrate the principles of the invention and its practical application, and to enable those of ordinary skill in the art to understand the invention so as to design various embodiments with various modifications suitable for a particular purpose.

Claims

1. A flexible fairing for an aeroengine, comprising an upstream fairing which has an air inlet, characterized in that, A flexible film capable of inflating and expanding is coated on the edge of the air inlet. There is a fairing inner cavity in the upstream fairing. The upstream fairing is provided with an ice-breaking opening facing the flexible film at the edge of the air inlet. The ice-breaking opening is communicated with the fairing inner cavity. An ice-breaking block is slidably arranged in the ice-breaking opening. The top of the ice-breaking block can abut against the flexible film to cause the flexible film to bulge outwards locally for ice breaking. A lever force-increasing device for driving the ice-breaking block to pop outwards is arranged in the fairing inner cavity. And an annular impact device for driving the lever force-increasing device is also arranged in the fairing inner cavity. The lever force-increasing device includes a hinge bracket fixedly installed on the inner wall of the fairing inner cavity. An increasing-force bracket is hingedly arranged in the hinge bracket. The increasing-force bracket is in a shape of a fishhook and has a long handle and a short handle connected to each other. The long handle and the short handle are fixedly connected and form an acute angle. The length of the long handle is greater than the length of the short handle. The short handle abuts against the ice-breaking block and impacts the ice-breaking block to pop outwards. The annular impact device can impact the long handle and use the lever principle to enhance the thrust applied by the short handle to the ice-breaking block. The annular impact device includes an annular pneumatic slide rail, an impact body and a pop-out body. The impact body slides in the annular pneumatic slide rail under the action of air pressure. The annular pneumatic slide rail is provided with a plurality of pop-out holes. The pop-out body is slidably arranged in the pop-out holes. One end of the pop-out body abuts against the long handle. The other end of the pop-out body protrudes into the interior of the annular pneumatic slide rail. An elastic member is arranged between the pop-out body and the annular pneumatic slide rail to push the pop-out body to abut against the long handle along the direction close to the long handle. The impact body impacts the protruding part of the pop-out body to cause the pop-out body to pop outwards and impact the long handle.

2. The flexible fairing of an aeroengine according to claim 1, wherein The annular pneumatic slide rail includes a first ring and a second ring. The first ring and the second ring are paired to form a sealed air chamber. The impact body slides in the sealed air chamber. The pop-out holes are formed in the first ring. The second ring is fixedly installed on the inner wall of the fairing inner cavity. The first ring can rotate relative to the second ring to adjust the distance between the contact point of the pop-out body and the long handle and the hinge point of the increasing-force bracket and the hinge bracket.

3. The flexible fairing of an aeroengine according to claim 2, characterized in that The second ring has two second semi-circular grooves that are symmetric about the left and right. The first ventilation holes are formed in the second ring. The first ventilation holes communicate with the two second semi-circular grooves respectively. The first ring has two first semi-circular grooves that are symmetric about the left and right. The second ventilation holes are formed in the first ring. The second ventilation holes communicate with the two first semi-circular grooves respectively. The second ventilation holes are connected with penetration pipes. An arc-shaped air chamber is formed in the second ring. The penetration pipes slide in the arc-shaped air chamber. The second ring is also provided with a through groove communicating with the arc-shaped air chamber; And / or, the bottom walls of the first semi-circular groove and the second semi-circular groove are both elastic layers, the elastic layer includes a smooth layer and a rubber layer, the impact body contacts the smooth layer, and the rubber layer can elastically contract under force to increase the passing ability of the impact body. Arc-shaped grooves are provided at the corresponding positions of the bottom walls of the first semi-circular groove and the second semi-circular groove corresponding to the ejection hole, and the depth of the arc-shaped groove gradually increases along the moving path of the impact body, and the elastic layer covers the arc-shaped groove.

4. The flexible fairing of an aeroengine according to claim 1, characterized in that, The part of the ejection body extending into the annular pneumatic slide rail is the impacted head, the part of the ejection body in contact with the long handle is the impact head, and the impact body is a spherical body; the impacted head is a wedge-shaped block, or the impacted head is spherical; And / or, the long handle is inclined towards the annular pneumatic slide rail, and along the length direction of the long handle, the bottom surface of the long handle gradually approaches the ejection body.

5. The flexible fairing of an aeroengine according to claim 1, characterized in that, The middle diameter of the ejection body expands outwards to form a stepped portion, the diameter of the ejection hole increases towards the side of the force-increasing bracket to form a stepped hole, and a return spring is arranged between the stepped portion and the stepped hole, and the return spring pushes the ejection body to abut against the long handle.

6. The flexible fairing of an aeroengine according to claim 2, characterized in that A sealing ring is arranged in the inner cavity of the fairing, a sealing ring is arranged between the second ring and the inner wall of the inner cavity of the fairing, the sealing ring isolates the inner cavity of the fairing and forms positive and negative air cavities. The center of the ice-breaking block has a central groove, the top of the ice-breaking block has an ice-breaking nozzle, the side of the ice-breaking block has a switching port, both the ice-breaking nozzle and the switching port communicate with the central groove, the ice-breaking nozzle faces the flexible diaphragm, the wall of the ice-breaking port has air holes, one end of the air hole communicates with the positive and negative air cavities, and the other end communicates with the ice-breaking port. The ice-breaking block moves upwards from the ice-breaking port towards the flexible diaphragm so that the switching port communicates with the air hole.

7. The flexible fairing of an aeroengine according to claim 6, characterized in that The diameter of the end of the ice-breaking block facing upwards the flexible diaphragm is reduced, so that an exhaust gap is formed between the outer wall of the ice-breaking block and the inner wall of the ice-breaking port. When the ice-breaking block is hidden in the ice-breaking port, the exhaust gap communicates with the air hole.

8. The flexible fairing of an aeroengine according to claim 6, characterized in that A positive and negative pressure generator is arranged in the inner cavity of the fairing. The positive and negative pressure generator has a pressurizing pipe and an air inlet pipe. The pressurizing pipe passes through the sealing ring and communicates with the positive and negative air cavities. The positive and negative pressure generator also has a negative pressure pipe. The negative pressure pipe passes through the sealing ring and communicates with the positive and negative air cavities. Electromagnetic switching valves are arranged on both the pressurizing pipe and the negative pressure pipe.

9. The flexible fairing of an aeroengine according to claim 3, characterized in that A high-voltage generator is also arranged in the inner cavity of the fairing. The high-voltage generator has a supplementary air pipe and an air outlet pipe. The air outlet pipe is connected to a switching valve. The switching valve has a second pipe and a first pipe. The first pipe communicates with the first ventilation hole. The second pipe communicates with the through groove. The switching valve also has an exhaust pipe. The exhaust pipe communicates with the atmosphere. The switching valve has two ventilation paths. The first ventilation path is that high-pressure air flows through the air outlet pipe, the first pipe, the first ventilation hole, the through groove, the second pipe, and the exhaust pipe in sequence; The second ventilation path is that high-pressure air flows through the second pipe, the through groove, the first ventilation hole, the first pipe, and the exhaust pipe in sequence.

10. The flexible fairing of an aeroengine according to claim 6, characterized in that, A piston slide plate is fixedly arranged on the outer wall of the first ring. The first ring rotates annularly within the inner cavity of the fairing, and a ring groove is formed between the first ring and the inner cavity of the fairing. The piston slide plate slides annularly within the ring groove. First and second limit bodies protrude from the inner wall of the inner cavity of the fairing, and the piston slide plate slides between the first limit body and the second limit body. A first hole and a second hole are provided on the sealing ring. Both the first hole and the second hole communicate with the ring groove, and the piston slide plate is located between the first hole and the second hole.

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