Flexible fairing of aero-engine

Abstract

The invention relates to the related technical field of engine fairings, and discloses an aero-engine flexible fairing which comprises an upstream fairing, the upstream fairing is provided with an air inlet, the edge of the air inlet is coated with a flexible leather film capable of being inflated and expanded, and a fairing inner cavity is formed in the upstream fairing. An ice breaking opening facing the flexible leather film is formed in the edge of the air inlet of the upstream fairing, the ice breaking opening communicates with an inner cavity of the fairing, an ice breaking block is slidably arranged in the ice breaking opening, the top of the ice breaking block can abut against the flexible leather film so that the flexible leather film can partially expand outwards to break ice, and a lever forcing device for driving the ice breaking block to pop out is arranged in the inner cavity of the fairing. And an annular impact device for driving a lever forcing device is further arranged in the inner cavity of the fairing, the firmer the ice layer is, the larger the impact on the part is, the place where the ice layer is effectively broken is not impacted again, targeted work is applied, the ice breaking key area is adjusted in a self-adaptive mode, and the ice breaking efficiency is effectively improved.

Description

Technical Field

[0001] The invention belongs to the technical field related to composite yarn cleaning, and more specifically, particularly relates to a flexible fairing for an aircraft engine. Background Art

[0002] As the "heart" of modern aircraft, the core function of aircraft engines is to convert the chemical energy of fuel into mechanical energy, thereby generating thrust or shaft power to provide flight power for aircraft. When aircraft engines operate in a low temperature and high humidity environment, the air inlet, fan blades and other parts are prone to ice formation, affecting engine performance and flight safety. Commonly used ice-breaking methods in the prior art include:

[0003] Hot gas anti-icing: a portion of high-temperature and high-pressure gas is drawn out from the engine compressor and transported through a pipeline to the parts that need anti-icing, using heat to prevent freezing or melt the ice that has already formed; electric heating elements are installed in the parts that need anti-icing, and electrical energy is converted into thermal energy to prevent freezing or melt the ice that has already formed; mechanical de-icing: an inflatable rubber airbag or mechanical device is installed in the parts that need anti-icing, and the ice layer is broken up through periodic expansion and contraction; liquid anti-icing: anti-icing liquid is sprayed in the parts that need anti-icing to lower the freezing point of water, prevent freezing or melt the ice that has already formed.

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

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

[0006] During actual flight, icing conditions are complex and changeable. Factors such as ice thickness, ice type, temperature, and humidity will affect the icing speed and strength of the ice. Existing mechanical icebreaking systems are difficult to cope with these complex and changeable factors and cannot achieve precise icebreaking control, which may result in incomplete icebreaking or excessive icebreaking.

[0007] Therefore, in view of this, the existing structure is studied and improved, and an aircraft engine flexible fairing is provided to achieve a more practical purpose. Summary of the invention

[0008] The present invention provides an aero-engine flexible fairing, which is used to overcome the above-mentioned defects in the prior art.

[0009] The purpose and effect of the flexible fairing of an aircraft engine of the present invention are achieved by the following specific technical means:

[0010] The present invention provides a flexible fairing for an aircraft engine, comprising an upstream fairing, wherein the upstream fairing has an air inlet, an inflatable flexible membrane is coated 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, 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 outwards and breaks the ice, a lever forcing 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 forcing device is also arranged in the fairing inner cavity, the lever forcing device comprises an articulated bracket fixedly mounted on the inner wall of the fairing inner cavity, a force-enhancing bracket is articulatedly arranged in the articulated bracket, and the force-enhancing bracket is in a hook shape. The utility model discloses a kind of ice-breaking device, and it is provided with a long handle and a short handle which are 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 hits the ice-breaking block to pop outward, the annular impact device can hit the long handle and use the lever principle to enhance the thrust applied to the ice-breaking block by the short handle, the annular impact device comprises 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 is provided with a plurality of pop-up holes, the pop-up body is slidably arranged in the pop-up hole, one end of the pop-up body abuts against 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 outward and hit the long handle.

[0011] A further technical solution is that 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 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 mounted 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 to 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, the second ring is provided with a first ventilation hole, the first ventilation hole 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, the first ring is provided with a second ventilation hole, the second ventilation hole is respectively connected to the two first semicircular grooves, the second ventilation hole is connected to a penetration tube, the second ring has an arc-shaped air cavity, the penetration tube slides in the arc-shaped air cavity, and the second ring is also provided with a through groove connecting the arc-shaped air cavity.

[0013] A further technical solution is that the bottom walls of the first semicircular groove and the second semicircular groove are both elastic layers, the elastic layer includes a smooth layer and a rubber layer, the impact body is in contact with the smooth layer, and the rubber layer can elastically shrink when subjected to force to increase the passability of the impact body, and the bottom walls of the first semicircular groove and the second semicircular groove are provided with arc-shaped grooves at positions corresponding to the pop-up holes, the depth of the arc-shaped grooves gradually increases along the moving path of the impact body, and the elastic layer covers the arc-shaped grooves.

[0014] A further technical solution is that the part of the pop-up body extending into the interior of the annular pneumatic slide is the struck head, the part where the pop-up 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 is inclined close to the annular pneumatic slide, and along the length direction of the long handle, the bottom surface of the long handle gradually approaches the pop-up body.

[0015] According to a further technical solution, the middle diameter of the pop-up body expands outward to form a step portion, the diameter of the pop-up hole increases toward the force-enhancing bracket to form a step hole, a return spring is arranged between the step portion and the step hole, and the return spring pushes the pop-up body to abut against the long handle.

[0016] A further technical solution is that a sealing ring is arranged in the inner cavity of the fairing, and 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 is provided with a central groove, the top of the ice-breaking block is provided with an ice-breaking nozzle, the side of the ice-breaking block is provided with a switching port, the ice-breaking nozzle and the switching port are both connected to the central groove, the ice-breaking nozzle faces the flexible membrane, the wall of the ice-breaking port is provided with an air hole, one end of the air hole is connected to the positive and negative air cavities, and the other end is connected to the ice-breaking port, the ice-breaking block moves from the ice-breaking port toward the upper flexible membrane to connect the switching port with the air hole.

[0017] According to a further technical solution, the diameter of one end of the upward flexible membrane of the ice-breaking block 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 is connected to the air hole.

[0018] A further technical solution is to arrange positive and negative pressure generators in the inner cavity of the fairing, the positive and negative pressure generators having a boost pipe and an air intake pipe, the boost pipe passes through a sealing ring and is connected to the positive and negative air cavities, the positive and negative pressure generators also have a negative pressure pipe, the negative pressure pipe passes through a sealing ring and is connected to the positive and negative air cavities, and electromagnetic switch valves are arranged on both the boost pipe and the negative pressure pipe.

[0019] A further technical solution is that a high-pressure generator is also arranged in the inner cavity of the fairing, and the high-pressure generator has an air supply pipe and an air outlet pipe, the air outlet pipe is connected to the switching valve, the switching valve has a second pipe and a first pipe, the first pipe is connected to the first air vent, and the second pipe is connected to the through groove, the switching valve also has an exhaust pipe, the exhaust pipe is connected to the atmosphere, and the switching valve has two ventilation paths. The first ventilation path is that the high-pressure airflow flows through the air outlet pipe, the first pipe, the first air hole, the through groove, the second pipe, and the exhaust pipe in sequence; the second ventilation path is that the high-pressure airflow flows through the second pipe, the through groove, the first air hole, the first pipe, and the exhaust pipe in sequence.

[0020] A further technical solution is that a piston slide is fixedly arranged on the outer wall of the first ring, the first ring rotates in a circular manner in the inner cavity of the fairing, and an annular groove is formed between the first ring and the inner cavity of the fairing, the piston slide slides in a circular manner in the annular groove, a first limit body and a second limit body are protruded from the inner wall of the inner cavity of the fairing, the piston slide slides between the first limit body and the second limit body, a first hole and a second hole are arranged on the sealing ring, the first hole and the second hole are both connected to the annular groove, and the piston slide 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] An aircraft engine flexible fairing of the present invention is provided with a flexible membrane, ice-breaking blocks, a force-enhancing bracket, an annular pneumatic slide rail, etc., which can, on the one hand, ensure the basic function of expanding and breaking ice in the flexible membrane, and on the other hand, add the function of adaptive mechanical ice-breaking. Since the thickness of the ice layer is unevenly distributed circumferentially at the air inlet of the upstream fairing, the impact force required to break the ice layer is different. When the ice layer at a certain location is relatively thin, the ice-breaking blocks at that location can smoothly push the flexible membrane to break through the ice layer. The ice-breaking blocks protrude outward, causing the switching port to be connected with the air hole, and the high-pressure gas in the positive and negative air cavities is ejected outward through the central groove, the switching port, and the ice-breaking nozzle, so that the flexible membrane expands and breaks the ice, thereby realizing the combination of mechanical vibration ice-breaking and inflation ice-breaking.

[0023] When the ice layer is thicker at a certain place, it is difficult for the icebreaker at that place to move outwards. The booster device adjusts the rotation angle of the first ring, and the pop-up body rotates with the first ring. Since the long handle is inclined and extended, in the initial position, the distance between the long handle and the first ring is large, and the return spring pushes the pop-up body to extend and abut the long handle. At this time, the length of the pop-up body extending into the sealed air cavity is small, and the contact point between the pop-up body and the long handle extends to the distance end of the hinge point of the booster bracket. That is to say, the force amplification effect of the lever is reduced, and the impact force applied by the pop-up body to the long handle will act on the icebreaker in a small-proportion amplified state. At this time, the impact force of the icebreaker on the flexible membrane is small, which is suitable for the situation of thin ice layer and can reduce the sense of vibration; increasing the rotation angle of the first ring, the pop-up body moves toward the low point of the long handle, the lever action is amplified, and the extrusion applied by the pop-up body to the long handle will be amplified, which is suitable for ice layers with high strength.

[0024] In the place where the ice layer is broken after the first impact, the long handle will be pushed by the pop-up body to rotate upward, and the length of the pop-up body extending into the sealed air cavity is small. In the place where the ice layer is not broken or the degree of breaking is small, the long handle is pushed by the pop-up body to rotate upward at a small angle, and the length of the pop-up body extending into the sealed air cavity is large. That is to say, several pop-ups will produce different degrees of protrusions from the sealed air cavity according to different degrees of ice-breaking effects. The more difficult the ice layer is to break through, the more the pop-up body at the corresponding position will extend into the sealed air cavity. The easier the ice layer is to break through, the pop-up body at the corresponding position will reduce the extension into the sealed air cavity under the push of the reset spring. With the high-speed impact of the impact body again, those pop-ups with little or no elongation will be subjected to less impact or no impact, while those pop-ups with a large elongation will be subjected to a greater impact. The stronger the ice layer, the greater the impact will be. The place where the ice layer has been effectively broken will not be impacted again. Targeted work is done to reduce useless work. Each work can effectively target the places where it is difficult to break the ice, adaptively adjust the key icebreaking areas, and effectively improve the icebreaking efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

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

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

[0028] Figure 2 yes Figure 1 A schematic diagram of the enlarged structure at A in the middle;

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

[0030] Figure 4 It is a schematic diagram of the structure after the flexible membrane 11 is separated from the upstream fairing 10 in the present invention;

[0031] Figure 5 It is a disassembly schematic diagram of the ice breaker 16, the force booster bracket 22, the first ring 18 and the second ring 19 in the present invention;

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

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

[0034] Figure 8 It is a cross-sectional view of the air inlet of the upstream fairing 10 of the present invention;

[0035] Fig. 9 yes Figure 8 A schematic diagram of the enlarged structure of the middle ice breaking block 16;

[0036] Fig.10 It is a schematic diagram of the structure of the cooperation between the piston slide plate 57 and the ring groove 58;

[0037] Fig.11 It is a structural schematic diagram of a second embodiment of the present invention;

[0038] Fig.12 is a schematic structural diagram of a rotating ring 72 in a third embodiment of the present invention;

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

[0040] Fig.14 is a schematic diagram of the overall structure of an aircraft engine in a fourth embodiment of the present invention;

[0041] Fig.15 yes Fig.14 A cross-sectional view of an aircraft engine;

[0042] Fig.16 yes Fig.15 Front view of .

[0043] Description of reference numerals:

[0044] Upstream fairing 10, flexible membrane 11, fairing inner cavity 13, ice breaking port 14, ice breaking block 16, first ring 18, second ring 19, ice breaking nozzle 20, hinged bracket 21, force booster bracket 22, ejection body 23, long handle 24, short handle 25, sealed air cavity 27, sealing ring 28, positive and negative air cavity 29, first semicircular groove 31, ejection hole 32, second semicircular groove 33, first vent 34, second vent 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, boost 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, annular groove 58, first hole 59, second hole 60, first limiter 61, second limiter 62, central groove 65, inner fairing 70, engine body 71, rotating ring 72, arc groove 73, smooth layer 75, rubber layer 76, annular body 77, gear ring 78, internal gear 79, motor 80, annular boss 81, step portion 82. DETAILED DESCRIPTION

[0045] The following embodiments of the present invention are described in further detail in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0046] In the description of the present invention, unless otherwise specified, "plurality" means two or more than two; the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail", etc. are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", etc. are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0047] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" 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 a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0048] Embodiment 1: refer to the attached Figure 1-10A flexible fairing for an aircraft engine includes an upstream fairing 10, the upstream fairing 10 has an air inlet, the edge of the air inlet is covered with an inflatable flexible membrane 11, the upstream fairing 10 has a fairing inner cavity 13, the upstream fairing 10 is provided with an ice-breaking opening 14 facing the flexible membrane 11 at the edge of the air inlet, the ice-breaking opening 14 is connected with the fairing inner cavity 13, an ice-breaking block 16 is slidably arranged in the ice-breaking opening 14, and the top of the ice-breaking block 16 can be The flexible membrane 11 is abutted to make the flexible membrane 11 partially expand outward to break the ice. A lever force device for driving the ice-breaking block 16 to pop outward is arranged in the fairing inner cavity 13, and a ring-shaped impact device for driving the lever force device is also arranged in the fairing inner cavity 13. The lever force device includes an articulated bracket 21 fixedly mounted on the inner wall of the fairing inner cavity 13, and a force-enhancing bracket 22 is hingedly arranged in the articulated bracket 21. The force-enhancing bracket 22 is in a hook shape and has a mutually connected The long handle 24 and the short handle 25 are connected, 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 hits the ice-breaking block 16 to pop outward, the annular impact device can hit the long handle 24 and use the lever principle to enhance the thrust applied to the ice-breaking block 16 by the short handle 25, the annular impact device includes an annular pneumatic slide rail, an impact body 36 and an ejection body 23, the impact body 36 is pneumatically acted on to slide in the annular pneumatic slide rail, a plurality of ejection holes 32 are provided in the annular pneumatic slide rail, and the ejection body 23 is slidably arranged in the ejection hole 32, one end of the ejection body 23 abuts against the long handle 24, and the other end of the ejection body 23 protrudes into the inside of the annular pneumatic slide rail, an elastic member is arranged between the ejection body 23 and the annular pneumatic slide rail to push the ejection body 23 to abut in the direction close to the long handle 24, and the impact body 36 hits the protruding part of the ejection body 23 to make the ejection body 23 pop outward and hit the long handle 24.

[0049] In specific implementation, the impact body 36 itself can be a spherical mass block, or other shapes suitable for 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 a hydraulic system or an electromagnetic drive. The advantage of using a high-pressure gas source is that it is easy 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, while using hydraulic energy to push the impact body 36 cannot push the impact body 36 to move at a high speed, but it has the effect of low speed and high pressure, can provide a larger thrust for the impact body 36, and can adapt to the working conditions of breaking and removing thick ice layers.

[0050] Preferably, the annular pneumatic slide rail includes a first ring 18 and a second ring 19, which are paired to form a sealed air cavity 27, and the impact body 36 slides in the sealed air cavity 27. The first ring 18 is provided with an ejection hole 32, and the second ring 19 is fixedly mounted 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 between the ejection body 23 and the long handle 24 to the hinge point between the force booster bracket 22 and the hinge bracket 21.

[0051] Specifically, the contact point between the pop-up body 23 and the long handle 24 is defined as point A, the hinge point between the force-boosting bracket 22 and the hinged bracket 21 is positioned as point B, and the contact point between 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 left-right symmetrical second semicircular grooves 33, the second ring 19 is provided with a first ventilation hole 34, the first ventilation hole 34 is connected to the two second semicircular grooves 33 respectively, the first ring 18 has a left-right symmetrical first semicircular groove 31, the first ring 18 is provided with a second ventilation hole 35, the second ventilation hole 35 is connected to the two first semicircular grooves 31 respectively, the second ventilation hole 35 is connected to a penetration tube, the second ring 19 is provided with an arc-shaped air cavity 40, the penetration tube slides in the arc-shaped air cavity 40, and the second ring 19 is also provided with a through groove 39 connected to the arc-shaped air cavity 40.

[0053] Preferably, the bottom walls of the first semicircular groove 31 and the second semicircular groove 33 are both 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 shrink when subjected to force to increase the passability of the impact body 36. The bottom wall of the first semicircular groove 31 and the second semicircular groove 33 is provided with an arc-shaped groove 73 at the corresponding position of the pop-up hole 32. The depth of the arc-shaped groove 73 gradually increases along the moving path of the impact body 36, and the elastic layer covers the arc-shaped groove 73.

[0055] Preferably, the part of the pop-up body 23 extending into the interior of 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 is inclined close to the first ring 18, and 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 ejection body 23 impacting the long handle 24 according to a certain ratio.

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

[0058] Since the long handle 24 is arranged at an angle, as the first ring 18 rotates, the pop-up body 23 is squeezed by the long handle 24 and extends downward into the sealed air cavity 27. The extension amount of the pop-up 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 breaking. When the ice layer is not broken, the pop-up body 23 can only extend toward the sealed air cavity 27, and the pop-up body 23 will be impacted by the impact body 36. After the ice layer is effectively broken, the force-enhancing bracket 22 will swing outward, and the long handle 24 will not cause the pop-up body 23 to squeeze the reset 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, and 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, and the side of the ice-breaking block 16 has a switching port 43. The ice-breaking nozzle 20 and the switching port 43 are both connected to the central groove 65, the ice-breaking nozzle 20 faces the flexible membrane 11, and the wall of the ice-breaking port 14 has an air hole 45, one end of the air hole 45 is connected to the positive and negative air cavities 29, and the other end is connected to the ice-breaking port 14. The ice-breaking block 16 moves from the ice-breaking port 14 toward the upper flexible membrane 11 to connect the switching port 43 with the air hole 45.

[0060] Preferably, the diameter of one end of the ice-breaking block 16 facing the upper flexible membrane 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 is connected to the air hole 45 .

[0061] In this embodiment, when the ice-breaking block 16 does not protrude and squeeze the flexible membrane 11 outward, the high-pressure airflow in the positive and negative air cavities 29 can still pass through the air holes 45 and the exhaust gap 44, and provide airflow for the expansion of the flexible membrane 11. That is to say, the device can simultaneously have dual working modes of mechanical vibration deicing or air pressure expansion deicing, and the air pressure expansion deicing is not limited by mechanical vibration deicing and works relatively independently.

[0062] Preferably, a positive and negative pressure generator 46 is arranged in the inner cavity 13 of the fairing, and the positive and negative pressure generator 46 has a boost pipe 47 and an air intake pipe 48. The boost pipe 47 passes through the sealing ring 28 and is connected with the positive and negative air cavities 29. The positive and negative pressure generator 46 also has a negative pressure pipe 49, which passes through the sealing ring 28 and is connected with the positive and negative air cavities 29. Electromagnetic switch valves are arranged on the boost pipe 47 and the negative pressure pipe 49.

[0063] In this embodiment, the function of the positive and negative pressure generators 46 is to provide a high-pressure or negative-pressure environment for the positive and negative air cavities 29. The high-pressure environment means that the positive and negative pressure generators 46 draw air from the air inlet pipe 48 and discharge it into the positive and negative air cavities 29 through the boost pipe 47, forming a high-pressure environment. The high-pressure gas provides kinetic energy for the expansion of the flexible membrane 11; the negative-pressure environment means that the positive and negative pressure generators 46 draw air from the positive and negative air cavities 29 and discharge it through the negative pressure pipe 49 and the air inlet pipe 48, forming a low-pressure environment in the positive and negative air cavities 29, so that the flexible membrane 11 shrinks and fits tightly against the aerodynamic shape of the upstream fairing 10.

[0064] Preferably, a high-pressure generator 50 is also provided in the inner cavity 13 of the fairing, and the high-pressure generator 50 has an air supply pipe 51 and an air outlet pipe 52, the air outlet pipe 52 is connected to the switching valve 53, the switching valve 53 has a second pipe 54 and a first pipe 55, the first pipe 55 is connected to the first air hole 34, the second pipe 54 is connected to the through groove 39, the switching valve 53 also has an exhaust pipe 56, the exhaust pipe 56 is connected to the atmosphere, and the switching valve 53 has two ventilation paths, the first ventilation path is that the high-pressure airflow flows through the air outlet pipe 52, the first pipe 55, the first air hole 34, the through groove 39, the second pipe 54, and the exhaust pipe 56 in sequence; the second ventilation path is that the high-pressure airflow flows through the second pipe 54, the through groove 39, the first air hole 34, the first pipe 55, and the exhaust pipe 56 in sequence.

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

[0066] Preferably, a piston slide 57 is fixedly provided on the outer wall of the first ring 18, the first ring 18 rotates in a circular manner in the inner cavity 13 of the fairing, and an annular groove 58 is formed between the first ring 18 and the inner cavity 13 of the fairing, the piston slide 57 slides in a circular manner in the annular groove 58, a first limiting body 61 and a second limiting body 62 are protruded from the inner wall of the inner cavity 13 of the fairing, the piston slide 57 slides between the first limiting body 61 and the second limiting body 62, a first hole 59 and a second hole 60 are provided on the sealing ring 28, the first hole 59 and the second hole 60 are both connected to the annular groove 58, and the piston slide 57 is located between the first hole 59 and the second hole 60.

[0067] Specifically, the device also has a booster device, which is used to pass hydraulic oil into the first hole 59. The liquid enters the annular groove 58 to push the piston slide 57 to rotate. The liquid in the annular groove 58 flows back to the booster device through the second hole 60, thereby controlling the angle of the piston slide 57 in the annular groove 58 to adjust the rotation angle of the first ring 18.

[0068] Example 2, refer to the attached Fig.11 The present invention also provides a kinetic energy device for driving the pop-up body 23 to be squeezed toward the long handle 24. The kinetic energy device is an annular body 77. The annular body 77 replaces the second ring 19 in Example 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 the pop-up body 23, so that the pop-up body 23 protrudes outward to squeeze the long handle 24, thereby realizing the function of squeezing and breaking ice.

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

[0070] Example 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, and the impact body 36 is arranged on the rotating ring 72. In order to drive the rotating ring 72, the transmission device and the motor in Example 2 are arranged in the inner cavity 13 of the fairing.

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

[0072] Preferably, the depth of the arcuate chute increases gradually, so that the height of the impact body 36 protruding from the arcuate chute changes as the position of the impact body 36 in the arcuate chute changes.

[0073] In this embodiment, when the rotating ring 72 drives the impact body 36 to rotate at a high speed, the impact body 36 will hit the pop-up body 23. If the length of the pop-up body 23 is too large, the impact body 36 cannot push the pop-up body 23 outward in the first time. Under the obstruction of the pop-up body 23, the impact body 36 will move in the arc-shaped slide groove and pressurize the elastic device. In this embodiment, the elastic device can be a spring, an elastic pad, a rubber layer, etc. The impact body 36 gradually reduces the exposed height, thereby staggering the contact with the pop-up body 23 to ensure the smoothness of the rotation process of the rotating ring 72.

[0074] Example 4, see attached Figure 14-16 The present invention also provides an aircraft engine, which includes the fairing of embodiment 1, an inner fairing 70 is arranged inside the fairing, and an engine body 71 is arranged in the inner fairing 70.

[0075] Working process of the present invention:

[0076] Under low temperature conditions, an ice shell will form on the surface of the flexible membrane 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 in the gas from the intake pipe 48 and injects it into the positive and negative air cavities 29 through the boost pipe 47. The high-pressure gas in the positive and negative air cavities 29 passes through the air holes 45 and the exhaust gap 44 to expand and deform the flexible membrane 11 to facilitate ice breaking.

[0077] If the thickness of the ice layer is large and the increase in air pressure cannot effectively expand the flexible membrane 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 the gas is sucked in from the air supply pipe 51. After being pressurized by the high-pressure generator 50, the gas passes through the outlet pipe 52, the first pipe 55, the first air hole 34, the groove 39, the second pipe 54, and the exhaust pipe 56 in sequence. When the air flow flows in the sealed air cavity 27, the impact body 36 is pushed to move at high speed from the end close to the first air hole 34 to the end close to the groove 39. The impact body 36 moves at high speed in the sealed air cavity 27 and hits the protruding part of the pop-up body 23. The pop-up body 23 is hit and pops out, hitting the long handle 24. The long handle 24 swings and drives the short handle 25 to hit the ice-breaking block 16. The ice-breaking block 16 moves from a state hidden in the ice-breaking port 14 to a state protruding outward. The flexible membrane 11 is hit by the ice-breaking block 16 and protrudes, so as to achieve the effect of mechanical vibration ice breaking.

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

[0079] The thickness of the ice layer at the air inlet of the upstream fairing 10 is unevenly distributed around the circumference, resulting in different impact forces required to break the ice layer. When the ice layer is relatively thin at a certain location, the ice-breaking block 16 at that location can smoothly push the flexible membrane 11 to break through the ice layer. The ice-breaking block 16 protrudes outward, causing the switching port 43 to communicate with the air hole 45, and the high-pressure gas in the positive and negative air cavities 29 to be ejected outward through the central groove 65, the switching port 43, and the ice-breaking nozzle 20 to expand the flexible membrane 11 to break the ice, thereby realizing the combination of mechanical vibration ice-breaking and inflation ice-breaking. When the ice layer is relatively thick at a certain location, the ice-breaking block 16 at that location is difficult to move outward, and the impact body 36 impacts the ejection body 23 to move outward. The ejection 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 membrane 11 itself, but the ice layer will not be broken.

[0080] In order to cope with the uneven distribution of ice thickness, the booster device injects hydraulic oil into the annular groove 58 through the first hole 59 to push the piston slide 57 to rotate in the annular groove 58 and adjust the rotation angle of the first ring 18. The pop-up body 23 rotates with the first ring 18. Since the long handle 24 extends obliquely, in the initial position, the distance between the long handle 24 and the first ring 18 is large, and the return spring 41 pushes the pop-up body 23 to extend and abut the long handle 24. At this time, the length of the pop-up body 23 extending into the sealed air cavity 27 is small, and the pop-up body 23 and the long handle are close to each other. The contact point of the spring 23 extends to the distance end of the hinge point of the force-enhancing bracket 22, that is, the force amplification effect of the lever is reduced, and the impact force applied by the pop-up body 23 to 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 membrane 11 is relatively small; the rotation angle of the first ring 18 is increased to displace the pop-up body 23 toward the low point of the long handle 24. The long handle 24 will be pushed upward by the pop-up body 23 to rotate at the place where the ice layer is broken after the first impact, and the compression amount of the reset spring 41 is small, and the pop-up body 23 The length of the ejection body 23 extending into the sealed air cavity 27 is small. In places where the ice layer is not broken or is broken to a small extent, the long handle 24 is pushed upward by the ejection body 23 to rotate at a small angle, the compression amount of the reset spring 41 increases, and the length of the ejection body 23 extending into the sealed air cavity 27 is large. That is to say, a plurality of ejection bodies 23 will produce different degrees of protrusions from the sealed air cavity 27 according to different degrees of ice-breaking effects. The more difficult it is to break through the ice layer, the longer the ejection body 23 at the corresponding position extends into the sealed air cavity 27. The easier it is to break through the ice layer, the more the ejection body 23 at the corresponding position will extend into the sealed air cavity 27. Under the push of the spring 41, the elongation into the sealed air cavity 27 is reduced. With the high-speed impact of the impact body 36 again, those pop-up bodies 23 with little or no elongation will be subjected to a smaller impact or no impact, while those pop-up bodies 23 with a large elongation will be subjected to a larger impact. The stronger the ice layer, the greater the impact will be. The place where the ice layer has been effectively broken will not be impacted again. Targeted work is done to reduce useless work. Each work can effectively target places where it is difficult to break the ice, adaptively adjust the key ice-breaking areas, and effectively improve the ice-breaking efficiency.

[0081] The embodiments of the present invention are given for the purpose of illustration and description, and are not intended to be exhaustive or to limit the invention to the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific uses.

Claims

1. An aircraft engine flexible fairing, comprising an upstream fairing, wherein the upstream fairing has an air inlet, characterized in that: The edge of the air inlet is covered with an inflatable flexible membrane, the upstream fairing is provided with a fairing inner cavity, the upstream fairing is provided with an ice-breaking hole facing the flexible membrane at the edge of the air inlet, the ice-breaking hole is connected with the fairing inner cavity, an ice-breaking block is slidably arranged in the ice-breaking hole, the top of the ice-breaking block can abut against the flexible membrane to make the flexible membrane partially expand outward and break the ice, a lever force device for driving the ice-breaking block to pop out outward is arranged in the fairing inner cavity, and an annular impact device for driving the lever force device is also arranged in the fairing inner cavity, the lever force device includes an articulated bracket fixedly mounted on the inner wall of the fairing inner cavity, a force-enhancing bracket is articulatedly arranged in the articulated bracket, the force-enhancing bracket is in the shape of a hook, 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 a The cam is an annular pneumatic slide rail, an impact body and an ejection body, the impact body slides in the annular pneumatic slide rail under the action of pneumatic force, the annular pneumatic slide rail is provided with a plurality of ejection holes, and an ejection body is slidably arranged in the ejection holes, one end of the ejection body abuts against the long handle, and the other end of the ejection body protrudes into the interior of the annular pneumatic slide rail, an elastic member is arranged between the ejection body and the annular pneumatic slide rail to push the ejection body to abut in a direction close to the long handle, and the impact body hits the protruding part of the ejection body so that the ejection body pops out and hits the long handle.

2. The flexible fairing of an aircraft engine according to claim 1, characterized in that: 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 cavity, the impact body slides in the sealed air cavity, the first ring is provided with the ejection hole, the second ring is fixedly mounted 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 between the ejection body and the long handle and the hinge point between the force booster bracket and the hinge bracket.

3. The flexible fairing of an aircraft engine according to claim 2, characterized in that: The second ring has two second semicircular grooves that are symmetrical to each other, the second ring is provided with a first vent hole, the first vent hole is connected to the two second semicircular grooves respectively, the first ring has a first semicircular groove that is symmetrical to each other, the first ring is provided with a second vent hole, the second vent hole is connected to the two first semicircular grooves respectively, the second vent hole is connected to a penetration tube, the second ring is provided with an arc-shaped air cavity, the penetration tube slides in the arc-shaped air cavity, and the second ring is also provided with a through groove connected to the arc-shaped air cavity; And / or, the bottom walls of the first semicircular groove and the second semicircular groove are both elastic layers, the elastic layer includes a smooth layer and a rubber layer, the impact body is in contact with the smooth layer, the rubber layer can elastically shrink when subjected to force to increase the passability of the impact body, the bottom walls of the first semicircular groove and the second semicircular groove are provided with arc-shaped grooves at positions corresponding to the pop-up hole, the depth of the arc-shaped grooves gradually increases along the moving path of the impact body, and the elastic layer covers the arc-shaped grooves.

4. The flexible fairing for an aircraft engine according to claim 1, characterized in that: The part of the ejection body extending into the annular pneumatic slide rail is the struck head, the part of the ejection body contacting the long handle is the impact head, 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 is inclined close to 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 for an aircraft engine according to claim 1, characterized in that: The middle diameter of the pop-up body expands outward to form a step portion, and the diameter of the pop-up hole increases toward one side of the force-enhancing bracket to form a step hole. A return spring is arranged between the step portion and the step hole, and the return spring pushes the pop-up body to abut against the long handle.

6. The flexible fairing for an aircraft engine according to claim 2, characterized in that: A sealing ring is arranged in the inner cavity of the fairing, and 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 is provided with a central groove, the top of the ice-breaking block is provided with an ice-breaking nozzle, the side of the ice-breaking block is provided with a switching port, the ice-breaking nozzle and the switching port are both connected to the central groove, the ice-breaking nozzle faces the flexible membrane, the wall of the ice-breaking port is provided with an air hole, one end of the air hole is connected to the positive and negative air cavities, and the other end is connected to the ice-breaking port, the ice-breaking block moves from the ice-breaking port toward the flexible membrane to connect the switching port with the air hole.

7. The flexible fairing for an aircraft engine according to claim 6, characterized in that: The diameter of one end of the ice-breaking block facing upward toward the flexible membrane 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 is connected to the air hole.

8. The flexible fairing for an aircraft engine according to claim 6, characterized in that: A positive and negative pressure generator is arranged in the inner cavity of the fairing, and the positive and negative pressure generator has a boost pipe and an air intake pipe. The boost pipe passes through the sealing ring and is connected with the positive and negative air cavities. The positive and negative pressure generator also has a negative pressure pipe, and the negative pressure pipe passes through the sealing ring and is connected with the positive and negative air cavities. Electromagnetic switch valves are arranged on the boost pipe and the negative pressure pipe.

9. The flexible fairing for an aircraft engine according to claim 3, characterized in that: A high-pressure generator is also arranged in the inner cavity of the fairing, and the high-pressure generator has an air 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 is connected to the first vent hole, the second pipe is connected to the through slot, the switching valve also has an exhaust pipe, the exhaust pipe is connected to the atmosphere, and the switching valve has two ventilation paths, and the first ventilation path is that the high-pressure airflow flows through the air outlet pipe, the first pipe, the first vent hole, the through slot, the second pipe, and the exhaust pipe in sequence; The second ventilation path is that the high-pressure airflow flows through the second pipe, the groove, the first ventilation hole, the first pipe, and the exhaust pipe in sequence.

10. The flexible fairing of an aircraft engine according to claim 6, characterized in that: A piston slide is fixedly arranged on the outer wall of the first ring, the first ring rotates in a circular manner in the inner cavity of the fairing, and an annular groove is formed between the first ring and the inner cavity of the fairing, the piston slide slides in a circular manner in the annular groove, a first limiting body and a second limiting body are protruded from the inner wall of the inner cavity of the fairing, the piston slide slides between the first limiting body and the second limiting body, a first hole and a second hole are arranged on the sealing ring, the first hole and the second hole are both connected to the annular groove, and the piston slide is located between the first hole and the second hole.

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