Aero-engine nacelle and aero-engine

Abstract

The invention relates to an aero-engine, in particular to an aero-engine nacelle and an aero-engine. The aircraft engine nacelle comprises an aircraft engine hanging frame, an aircraft engine nacelle body is installed on the upper side of the aircraft engine hanging frame, an aircraft engine core machine is installed in the aircraft engine nacelle body, an air inlet cabin is connected to the front side of the aircraft engine hanging frame, a nacelle outer cover and an outer cover framework are connected to the front side of the aircraft engine nacelle body, and an opening is formed in the right side of the nacelle outer cover; the front side of the nacelle outer cover is connected with a rectifying ring, the nacelle outer cover is connected to the outer side of the outer cover framework, the lower side of the outer cover framework is connected with an air guide cabin, and a nacelle inner cover component is arranged in the outer cover framework. By adopting the mode that the array type hit grating assemblies are arranged at the nacelle inner cover component, when entering the inner space of the rectifying ring, foreign matter cannot directly hit the blade of the aero-engine core engine, and the situation that the foreign matter directly impacts the aero-engine core engine with large kinetic energy, so that the blade is damaged or is directly drawn into an inner duct of the aero-engine core engine is avoided.

Description

Technical Field

[0001] The invention relates to an aircraft engine, and in particular to an aircraft engine nacelle and an aircraft engine. Background Art

[0002] In the field of engines for current aircraft, such as jet aircraft such as airliners, many use turbofan engines, that is, a turbofan and a combustion chamber are used to form an aeroengine core, a nacelle is used to wrap and install the aeroengine core, a fan for inhaling air is provided on the front side of the aeroengine core, a combustion chamber is provided in the middle of the aeroengine core, a tail nozzle is provided at the rear of the aeroengine core, the position between the aeroengine core and its nacelle is the outer duct of the aeroengine, which is also the main output power of general jet airliners, and the inner duct of the aeroengine is located in the combustion chamber. The air entering this duct burns the mixed fuel to form high-pressure combustion gas to provide power; however, in current jet aircraft, the fan is directly exposed to the windward side, and the aircraft is very susceptible to impact by foreign objects in space during flight. For example, within 30 meters during take-off and landing, the aircraft is also at the general activity altitude of birds. When the aircraft takes off and lands in this altitude area, the engine is easily affected. Bird strikes. Although there are many ways to prevent bird strikes on engines, such as bird-repelling operations at airports and improvements in engine blade structure, bird-repelling operations at airports cannot completely eliminate the hidden dangers of birds striking engines. Changing the engine blade structure does have some results, so that birds will not directly enter the engine inner duct and combustion chamber after striking the engine, but the damage to the engine blades is very large, especially when the aircraft is flying at high speed. The increase in impact kinetic energy caused by the increase in relative speed can more easily damage the engine. In addition, during low-altitude takeoff and landing, if the aircraft is hit by a bird and one engine fails, it is difficult for the pilot to respond in time and the aircraft is about to touch the ground. This type of flight safety accident has caused many air crashes. It is not only the aircraft engine that is vulnerable to impact by foreign objects during low-altitude takeoff and landing. Severe weather at high altitudes, especially hail, will still impact the inside of the engine and cause damage to the engine blades.

[0003] Based on the above, it is necessary to design an aircraft engine nacelle and aircraft engine that can protect aircraft engine blades from direct impact, reduce the relative impact speed of foreign objects entering the engine nacelle and reduce the impact kinetic energy, and ensure the air intake volume while ensuring engine safety. Summary of the invention

[0004] In order to overcome the shortcoming that current aircraft engines are easily damaged by impacts from foreign objects, the purpose of the present invention is to provide an aircraft engine nacelle and aircraft engine that can protect aircraft engine blades from direct impacts, reduce the relative impact speed of foreign objects entering the engine nacelle and reduce the impact kinetic energy, and ensure the air intake volume under the premise of ensuring engine safety.

[0005] An aircraft engine nacelle and an aircraft engine, comprising an aircraft engine pylon, an aircraft engine nacelle body is mounted on the upper side of the aircraft engine pylon, an aircraft engine core is mounted inside the aircraft engine nacelle body, an air intake cabin is connected to the front side of the aircraft engine pylon, a nacelle outer cover and an outer cover frame are connected to the front side of the aircraft engine nacelle body, an opening is provided on the right side of the nacelle outer cover, a fairing ring is connected to the front side of the nacelle outer cover, the nacelle outer cover is connected to the outside of the outer cover frame, an air guide cabin is connected to the lower side of the outer cover frame, a nacelle inner cover component is provided inside the outer cover frame, a connecting port corresponding to the opening is provided on the right side of the nacelle inner cover component; two buffer devices are provided on the rear side of the outer cover frame, the two buffer devices are staggered, an obliquely arranged impact grille assembly is provided between the two groups of buffer devices, and the impact grille assembly is oblique to the opening direction; a guide device is provided on the right side of the outer cover frame, and the guide device can close or open the opening; a discharge device is provided on the right side of the air intake cabin, and the discharge device is used to discharge foreign matter in the air intake cabin.

[0006] Preferably, the nacelle inner cover component includes an inner cover ring, which is fixedly connected to the inner side of the outer cover frame. The inner cover ring is a structure with a discharge port on the right side. A closed cover frame is fixedly connected to the right side of the inner cover ring. The impact grid assembly passes through the inner cover ring. A plurality of bidirectional guide channels are arranged on the left side of the inner cover ring, and a wide guide channel is arranged at the rear of the right side of the inner cover ring.

[0007] Preferably, the buffer device includes a long arc frame, which is fixedly connected to the left front position of the outer cover frame, and a short arc frame is fixedly connected to the right front position of the outer cover frame. The front extension length of the long arc frame is greater than that of the short arc frame. The front sides of the long arc frame and the short arc frame are both fixedly connected to compressed gas tanks, and the front sides of the compressed gas tanks are connected to multiple groups of telescopic rods.

[0008] Preferably, the impact grille assembly includes a grille component, both ends of which are respectively installed on the front sides of the telescopic rods on both sides, a guide panel is fixedly connected between the right sides of the grille components, a closing plate is fixedly connected to the right position of the rear side of the guide panel, and a two-way guide plate is connected to the left side of the grille components, and the two-way guide plates are respectively matched with adjacent two-way guide channels, and a wide guide plate is fixedly connected to the right side of the grille components, and the wide guide plate matches the wide guide channel.

[0009] Preferably, the grille component includes a titanium alloy frame, which is the rear side structure of the grille component. Both ends of the titanium alloy frame are respectively installed on the front sides of the telescopic rods on both sides. The front side of the titanium alloy frame is a rubber pad, which is divided into an upper and lower layer. The middle part of the front side of the titanium alloy frame is a high-toughness impact layer, which is tightly attached to the rubber pad. The rear side of the titanium alloy frame is fixedly connected with an electric heating wire, and the titanium alloy frame structure can be heated when the electric heating wire is turned on.

[0010] Preferably, the export device includes a propulsion cylinder, which is respectively fixedly connected to the right side of the upper and lower structures of the outer cover frame, and a movable outer cover is fixedly connected between the right ends of the propulsion member structures of the propulsion cylinders, and the movable outer cover can cover the right side opening structure of the nacelle outer cover.

[0011] Preferably, the discharge device includes an electric slide rail, which is fixedly connected to the right inner wall of the air intake cabin. A movable shell is fixedly connected to the moving part of the electric slide rail. The movable shell can cover the right opening structure of the air intake cabin. An air guide grille is fixedly connected to the upper side of the air intake cabin in an array.

[0012] Preferably, it also includes a blocking grille, which is fixedly connected to the front side of the air intake compartment in an array.

[0013] The beneficial effects are as follows: 1. The present invention arranges an array of impact grid components at the inner cover structure of the nacelle, so that when foreign objects enter the internal space of the fairing ring, the foreign objects will not directly hit the blades of the aero-engine core, thereby preventing the foreign objects from directly impacting the aero-engine core with large kinetic energy and causing damage to the blades or being directly drawn into its inner channel.

[0014] 2. The present invention adopts a method of absorbing energy through a buffer device when a foreign object impacts the impacted grid assembly, thereby reducing the impact kinetic energy of the foreign object, or forming relatively low-speed and low-kinetic energy fragments after the foreign object impacts. These foreign object fragments are reduced in speed by the energy absorption of the impact grid assembly and the buffer device, and are thrown into the outer duct of the aero-engine core engine for suction and discharge, thereby preventing the foreign object fragments from being drawn into the inner duct of the aero-engine core engine.

[0015] 3. The present invention can discharge unbroken foreign matter that has entered the inner cover structure of the nacelle by using the inclined impact grid assembly and the function of the discharge device, and when installing the aircraft engine nacelle and the aircraft engine, the discharge devices are installed back to back, so that after the foreign matter is discharged, the horizontal tail and the vertical tail of the aircraft will not be affected by the impact of the discharged foreign matter.

[0016] 4. The present invention adopts an air intake layout method of two air intake channels, namely an air intake cabin and a fairing ring, which are arranged at the windward position of a traditional aero-engine pylon. This can not only keep the windward area of ​​the aircraft from changing too much and maintain the overall layout of the aircraft, but also enable the aero-engine core engine to compensate for the lost air intake through the air intake cabin when the aero-engine core engine is protected by the impact grille assembly but the air intake volume is reduced, thereby ensuring the normal operation of the aero-engine core engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention.

[0018] Figure 2 It is a schematic diagram of the three-dimensional structure of the first viewing angle when the export device of the present invention is opened.

[0019] Figure 3 It is a schematic diagram of the three-dimensional structure of the second viewing angle when the export device of the present invention is opened.

[0020] Figure 4 It is a schematic diagram of the first partial three-dimensional structure of the present invention.

[0021] Figure 5 It is a schematic diagram of the three-dimensional structure of the nacelle outer cover part of the present invention.

[0022] Figure 6 It is a schematic diagram of a second partial three-dimensional structure of the present invention.

[0023] Figure 7 It is a schematic diagram of the three-dimensional structure of the outer cover skeleton part of the present invention.

[0024] Figure 8 It is a schematic diagram of the three-dimensional structure of the air guide cabin part of the present invention.

[0025] Fig. 9 It is a schematic diagram of the first stereoscopic structure of the nacelle inner cover component part of the present invention.

[0026] Fig.10 It is a schematic diagram of a second three-dimensional structure of the inner cover component part of the nacelle of the present invention.

[0027] Fig.11 It is a schematic diagram of a third stereoscopic structure of the inner cover component part of the nacelle of the present invention.

[0028] Fig.12 It is a schematic diagram of the first three-dimensional structure of the buffer device part of the present invention.

[0029] Fig.13 It is a schematic diagram of the second three-dimensional structure of the buffer device part of the present invention.

[0030] Fig.14 It is a schematic diagram of the first three-dimensional structure of the impact grille assembly of the present invention.

[0031] Fig.15 It is a schematic diagram of the second three-dimensional structure of the impact grille assembly of the present invention.

[0032] Fig.16 It is a schematic cross-sectional structural diagram of the grid component of the present invention.

[0033] Fig.17 It is a schematic diagram of the three-dimensional structure of the inner cover ring part of the present invention.

[0034] Fig.18 It is a schematic diagram of the three-dimensional structure of the export device part of the present invention.

[0035] Fig.19It is a schematic diagram of the three-dimensional structure of the discharge device part of the present invention.

[0036] Fig. 20 It is a schematic diagram of the three-dimensional structure of the air intake cabin part of the present invention.

[0037] Parts names and serial numbers in the figure: 1_aircraft engine rack, 2_aircraft engine nacelle body, 3_aircraft engine core, 4_air intake cabin, 5_nacelle outer cover, 6_smoothing ring, 7_outer cover frame, 8_air guide cabin, 9_nacelle inner cover component, 10_buffer device, 11_impact grid assembly, 12_export device, 13_discharge device, 91_inner cover ring, 901_closed cover frame, 92_bidirectional guide channel, 93_wide guide channel, 101_long arc frame, 102_short arc shaped frame, 103_compressed gas tank, 104_telescopic rod, 111_grid component, 112_guide panel, 113_closing plate, 114_bidirectional guide plate, 115_wide guide plate, 1111_titanium alloy skeleton, 1112_rubber cushion layer, 1113_high toughness impact layer, 1114_heating wire, 121_propulsion cylinder, 122_movable outer cover, 131_electric slide rail, 132_movable shell, 133_air guide grille, 14_blocking grille. DETAILED DESCRIPTION

[0038] The preferred technical solutions of the present invention are described in detail below with reference to the accompanying drawings.

[0039] Embodiment 1, as Figure 1-Figure 9 and Figure 19-20As shown, an aircraft engine nacelle and an aircraft engine, including an aircraft engine pylon 1, an aircraft engine nacelle body 2, an aircraft engine core 3, an air intake cabin 4, a nacelle outer cover 5, a fairing ring 6, an outer cover frame 7, an air guide cabin 8, a nacelle inner cover component 9, a buffer device 10, a hit grid assembly 11, a guide device 12 and a discharge device 13, the aircraft engine pylon 1 is equipped with an aircraft engine nacelle body 2 on the upper side, the aircraft engine nacelle body 2 is equipped with an aircraft engine core 3, the front side of the aircraft engine pylon 1 is fixedly connected with an air intake cabin 4, the air intake cabin 4 is a structure in an oblique rearward and upper position, the air intake cabin 4 is a structure with openings on the front side and the upper side, and the air intake cabin 4 is a structure with an exhaust opening on the right side. The structure of the opening of the air inlet cabin 4 is used to discharge foreign matter therein. The air inlet cabin 4 is a cavity structure inclined in the upward and backward direction. The front opening structure of the air inlet cabin 4 is on the windward side of the aircraft. During the flight of the aircraft, the airflow enters its cavity structure from the front opening of the air inlet cabin 4, and then flows out from the upper opening structure through the inclined cavity structure of the air inlet cabin 4 to form an air inlet channel for the air inlet cabin 4. A nacelle cover 5 is fixedly connected to the front side of the aero-engine nacelle main body 2. The outer layer structure of the nacelle cover 5 and the aero-engine nacelle main body 2 are streamlined structures for reducing the air resistance of the nacelle cover 5 and the nacelle main body when flying in the air. The lower side and right side of the outer cover 5 are both open structures. The right side opening structure of the nacelle outer cover 5 is used to discharge foreign matter. The front side of the nacelle outer cover 5 is fixedly connected to a straightening ring 6. The straightening ring 6 is a front arc-shaped structure for straightening the airflow passing through the straightening ring 6. The front side of the aero-engine nacelle main body 2 is fixedly connected to a cover frame 7. The cover frame 7 is located inside the nacelle outer cover 5. The cover frame 7 is a front and rear double annular frame. The front part of the inner wall of the nacelle outer cover 5 is fixedly connected to the outer periphery of the front side of the cover frame 7 for fastening the nacelle outer cover 5. The lower side of the cover frame 7 is fixedly connected to an air guide cabin 8. The lower outer edge of the air guide cabin 8 is butted against and sealed with the lower opening structure of the nacelle outer cover 5. The lower end surface of the air cabin 8 is butted against and sealed with the upper end surface of the air intake cabin 4. The air guide cabin 8 is interconnected with the air intake cabin 4. The airway structures of the air guide cabin 8 and the air intake cabin 4 are unified to be inclined in the rearward and upward direction, and the surface is smooth, which is used to assist the airflow to enter the aero-engine nacelle body 2 through the guide and smooth surface of the inclined airway. A nacelle inner cover component 9 is provided inside the outer cover frame 7. The nacelle inner cover component 9 is a foreign matter discharge opening with a corresponding right opening of the nacelle outer cover 5 on the right side. The nacelle inner cover component 9 constitutes the inner layer area of ​​the aero-engine nacelle and the front side of the aero-engine. The space within the nacelle inner cover component 9 is the aero-engine nacelle and the aero-engine air intake channel;The airflow during the flight of the aircraft enters the internal space of the nacelle inner cover component 9 through the fairing ring 6, which is the main air intake channel of the aircraft engine nacelle and the aircraft engine. The airflow during the flight of the aircraft enters the air guide compartment 8 through the air intake compartment 4 and then enters the internal space of the nacelle inner cover component 9, which is the auxiliary air intake channel of the aircraft engine nacelle and the aircraft engine. That is, the aircraft engine nacelle and the aircraft engine are in a dual air intake duct layout, and because the air intake compartment 4 itself is placed on the front side of the aircraft engine pylon 1, the auxiliary airflow channel entering the aircraft engine nacelle and the aircraft engine through the air intake compartment 4 will not increase the frontal area of ​​the aircraft during flight, and thus will not increase the flight resistance of the aircraft. The aircraft engine nacelle and the nacelle outer cover 5 of the aircraft engine are streamlined in accordance with the traditional method, so they will not increase the frontal area of ​​the aircraft during flight, and similarly will not increase the flight resistance of the aircraft.Buffer devices 10 are provided on the left and right sides of the annular structure at the rear side of the outer cover frame 7. The buffer device 10 located on the left side of the outer cover frame 7 extends forward relative to the other group, so that the two groups of buffer devices 10 are misaligned in the top view plane. An impact grille assembly 11 is provided between the two groups of buffer devices 10. The impact grille assembly 11 is installed between the two misaligned groups of buffer devices 10 to form an oblique layout. The impact grille assembly 11 is oblique to the right opening direction of the nacelle outer cover 5, so that when the impact grille assembly 11 is hit by a foreign object and is not broken, it can be blown out of the nacelle inner cover component 9 through the airflow to discharge the foreign object opening and the right opening of the nacelle outer cover 5 to discharge the internal space of the aircraft engine nacelle and the aircraft engine, so as to avoid entering the inner and outer ducts of the aircraft engine core 3. The grille assembly 11 passes through the nacelle inner cover component 9. The impacted grille assembly 11 constitutes an array-type barrier grid that is horizontally placed and tilted to the right in the internal space of the nacelle inner cover component 9. The impacted grille assembly 11 is slidably sealed at the nacelle inner cover component 9. The sliding sealing cooperation mode of the impacted grille assembly 11 at the nacelle inner cover component 9 can prevent the airflow and foreign matter passing through the impacted grille assembly 11 from entering the space between the nacelle inner cover component 9 and the nacelle outer cover 5. The impacted grille assembly 11 passes through the right side discharge outlet structure of the nacelle inner cover component 9, and the reserved right side discharge outlet structure of the nacelle inner cover component 9 still has a discharge space. When the impacted grille assembly 11 is affected by the airflow in the space containing larger foreign matter, such as low-altitude birds during the take-off and landing phases of the aircraft , birds in the climbing phase, hail in bad weather, etc., when such foreign objects are sucked into the nacelle inner cover component 9, the impacted grille component 11 will reduce the probability of larger foreign objects directly hitting the aeroengine core engine 3, so that larger foreign objects hit the impacted grille component 11. Because the aircraft is very fast in flight, the impacted grille component 11 hit by foreign objects will absorb energy through its own structure. At the same time, after being hit, the impacted grille component 11 will apply the impact force to the buffer device 10, so that the buffer device 10 absorbs the impact energy of the impact, protects the integrity of the structure of the impacted grille component 11 itself, and avoids the impacted grille component 11 from being fragmented into small parts that are sucked into the internal channel of the aeroengine core engine 3. During the flight, the relative speed of the aircraft to the foreign matter in space is high. After the foreign matter hits the impact grid assembly 11, the impact speed will be greatly reduced, thereby reducing the speed of the foreign matter relative to the aircraft and the impact kinetic energy. Even if the foreign matter that enters the nacelle inner cover component 9 is broken by the impact and passes through the impact grid assembly 11, due to its reduced volume and reduced speed, the foreign matter will be thrown to its outer duct by the blades of the high-speed aero-engine core engine 3 itself and discharged, so that the foreign matter will not directly hit the blades of the aero-engine core engine 3 due to the relatively high speed and high kinetic energy, and the foreign matter that hits the blades of the aero-engine core engine 3 and is broken will not be sucked into its inner duct due to the relatively high speed, thereby avoiding the internal combustion chamber of the aero-engine core engine 3 from being damaged by the entry of foreign matter in the inner duct;A guide device 12 is provided on the right side of the outer cover frame 7. The guide device 12 can close or open the right side opening structure of the nacelle outer cover 5. If the guide device 12 closes the right side opening structure of the nacelle outer cover 5, the nacelle outer cover 5 is a closed air intake space. If the guide device 12 opens the right side opening structure of the nacelle outer cover 5, foreign matter in the internal space of the nacelle inner cover component 9 can be discharged from the right side opening structure of the nacelle outer cover 5; a guide device 13 is provided on the right side of the air intake cabin 4. The guide device 13 is used to discharge foreign matter in the air intake cabin 4 to prevent foreign matter from entering the space inside the nacelle inner cover component 9 through the air intake cabin 4 and prevent foreign matter from entering the aero-engine core 3. The aero-engine nacelle and the aero-engine have two air intake passages, namely the air intake cabin 4 and the fairing ring 6. Therefore, the layout of the impact grille assembly 11 in the nacelle inner cover component 9 reduces the air intake area in the direction of the fairing ring 6, but the air intake passage of the air intake cabin 4 can compensate for the reduced air intake area, thereby ensuring the air intake volume of the aero-engine nacelle and the aero-engine. ;

[0040] The aircraft engine nacelle and the aircraft engine can be installed above the wing through the aircraft engine pylon 1 and the air intake compartment 4, that is, the aircraft engine nacelle and the aircraft engine are more suitable for small aircraft installed on the wing. When installing the aircraft engine nacelle and the aircraft engine, it is necessary to install the aircraft engine nacelle and the aircraft engine with the export device 12 facing the right side on the left wing, and install the aircraft engine nacelle and the aircraft engine with the export device 12 facing the left side on the right wing, that is, the export device 12 is installed back to back, so that the foreign matter discharged by the export device 12 will not hit the horizontal tail and vertical tail of the aircraft; the aircraft installed with the aircraft engine nacelle and the aircraft engine can selectively open the take-off and landing stages. The guide device 12 and the discharge device 13 are turned on. During the flight of the aircraft, the guide device 12 and the discharge device 13 in the turned-on state will affect the flight air resistance of the aircraft. During the flight of the aircraft, the airflow will enter the nacelle inner cover component 9 through the dual channels of the fairing ring 6 and the air intake cabin 4, and the aero-engine core engine 3 will also inhale a large amount of air from the above-mentioned dual channels to perform work. If the aircraft is hit by foreign objects such as birds and hail from space during the take-off and landing stage or other flight stages, especially when the above-mentioned flying foreign objects enter the space within the fairing ring 6, the impact grid assembly 11 will reduce the probability of foreign objects directly hitting the fan blades of the aero-engine core engine 3, and due to the layout of the impact grid assembly 11, larger foreign objects will not directly hit the aero-engine The core engine 3 blades, and the foreign matter that hits the impact grille component 11, the impact grille component 11 will absorb the kinetic energy of the impact through its own structure and the matching buffer device 10, so that the relative speed of the foreign matter is reduced. Even if the foreign matter with reduced speed enters the space between the nacelle inner cover component 9 and the aeroengine core engine 3 blades, the high-speed aeroengine core engine 3 blades will also throw the foreign matter to the inner periphery of the aeroengine nacelle main body 2, so that the aeroengine core engine 3 is sucked in by the outer duct and discharged from the tail nozzle, and it will not enter the inner duct of the aeroengine core engine 3 and enter the combustion chamber. If a larger foreign matter hits the impact grille component 11 and breaks due to the kinetic energy, the broken foreign matter will also be thrown to the inner periphery of the aeroengine nacelle main body 2 by the aeroengine as mentioned above due to the reduced speed due to the impact and energy absorption. The core engine 3 is sucked into the outer duct but not into the inner duct. If a larger foreign object has insufficient impact kinetic energy and is not broken, the foreign object will remain on the impacted grille assembly 11 and will be tilted to the rear side of the impacted grille assembly 11. At this time, the foreign object will affect the intake volume of the aero-engine core engine 3 and the output power of the aero-engine core engine 3 will be reduced. This data can be detected by the aircraft aero-engine controller. If it does not affect the flight, the pilot can selectively control the export device 12 to open so that the larger foreign object remaining at the impacted grille assembly 11 can be discharged. In addition, foreign objects entering the air intake compartment 4 will also be blocked by the discharge device 13 to prevent the foreign objects from entering the nacelle inner cover component 9. The discharge device 13 can also be selectively opened to discharge the foreign objects in the air intake compartment 4.

[0041] Embodiment 2, as Figure 9-13 As shown, the nacelle inner cover component 9 includes an inner cover ring 91, a closed cover frame 901, a bidirectional guide channel 92 and a wide guide channel 93. The inner cover ring 91 is fixedly connected to the inner side of the outer cover frame 7. The inner cover ring 91 is a structure with a discharge port on the right side. The discharge port structure on the right side of the inner cover ring 91 is used to discharge foreign matter that is blocked by the impact grid assembly 11 but not broken. The closed cover frame 901 is fixedly connected to the right side of the inner cover ring 91. The closed cover frame 901 surrounds the discharge port structure on the right side of the inner cover ring 91. The upper and lower edges and the front edge of the closed cover frame 901 are all sealed and joined to the inner wall of the nacelle outer cover 5, so that the closed cover frame 901 forms an independent space between the right opening of the inner cover ring 91 and the right opening of the nacelle outer cover 5 for discharging foreign matter, so that the airflow passing through the inner cover ring 91 can flow from the closed cover frame 901 to the right opening structure of the nacelle outer cover 5 through its right opening structure, thereby preventing the airflow from entering the nacelle outer cover 5, the outer cover frame 7, the inner cover ring 91 and the sealing The space within the closed cover frame 901 allows the airflow to only be in the space within the inner cover ring 91 and the closed cover frame 901. The left side of the inner cover ring 91 is an array-type structure with openings. The impacted grille assembly 11 passes through the left array opening and the right discharge opening structure of the inner cover ring 91. A plurality of bidirectional guide channels 92 are arranged at the array opening structure on the left side of the inner cover ring 91. The bidirectional guide channels 92 are used to guide the impacted grille assembly 11 to buffer and absorb energy after being impacted. The bidirectional guide channels 92 are also used to maintain the sealing of the left side of the inner cover ring 91 when the impacted grille assembly 11 generates impact displacement. A wide guide channel 93 is arranged at the rear of the right side of the inner cover ring 91. The wide guide channel 93 is used to guide the impacted grille assembly 11 to buffer and absorb energy after being impacted. The wide guide channel 93 is also used to maintain the sealing of the rear position of the opening on the right side of the inner cover ring 91 when the impacted grille assembly 11 generates impact displacement, so as to prevent foreign matter and airflow from flowing back into the space between the rear side of the impacted grille and the aero-engine core 3.

[0042] After the impacted grid assembly 11 is hit by a foreign object, the impacted grid assembly 11 will be displaced within the inner cover ring 91 to protect the inner cover ring 91 from being directly entered by a larger foreign object and hit the blades of the aero-engine core 3 .

[0043] like Figure 12-13As shown, the buffer device 10 includes a long arc frame 101, a short arc frame 102, a compressed gas tank 103 and a telescopic rod 104. The long arc frame 101 is fixedly connected to the front position of the left side of the outer cover frame 7, and the short arc frame 102 is fixedly connected to the front position of the right side of the outer cover frame 7. The front side extension length of the long arc frame 101 is greater than that of the short arc frame 102, so that the front side end faces of the long arc frame 101 and the short arc frame 102 are closer to the rectifying ring 6, forming that the front side end faces of the long arc frame 101 and the short arc frame 102 are misaligned in the top view plane, and the front sides of the long arc frame 101 and the short arc frame 102 are fixedly connected to the compressed gas tank 103, and the front sides of the compressed gas tank 103 are connected to multiple groups of telescopic rods 104, so that the telescopic rods 104 are always pressed forward under the action of the compressed gas tank 103, and the impact grille assembly 11 is arranged between the front sides of the telescopic rods 104 on both sides.

[0044] After the impacted grille assembly 11 is hit by a foreign object, in addition to absorbing energy itself, the impacted grille assembly 11 will be displaced rearward through the telescopic rod 104 under the propulsion of the kinetic energy of the foreign object, so that the impacted grille assembly 11 is displaced rearward through the telescopic rod 104 under the pneumatic buffering action of the compressed gas tank 103, and the impact kinetic energy of the foreign object is reduced through pneumatic compression, so that the impact speed of the foreign object is reduced or broken.

[0045] like Figure 12-Figure 18As shown, the impact grille assembly 11 includes a grille component 111, a guide panel 112, a closing plate 113, a bidirectional guide plate 114 and a wide guide plate 115. The grille components 111 are respectively installed on the front sides of the telescopic rods 104 on both sides. The guide panel 112 is fixedly connected between the right sides of the grille components 111. The upper and lower edges of the guide panel 112 are slidably sealed with the upper and lower sides of the inner wall of the closed cover frame 901. The guide panel 112 is used to guide the foreign matter that hits the grille component 111 to be discharged through the right opening of the nacelle outer cover 5. The closing plate 113 is fixedly connected to the right position of the rear side of the guide panel 112. The left side of the closing plate 113 is slidably sealed with the surface of the compressed gas tank 103 on the right side. The upper and lower edges of the closing plate 113 are slidably sealed with the upper and lower sides of the inner wall of the closed cover frame 901. The right side of the closing plate 113 is slidably sealed with the inner wall of the nacelle outer cover 5. The sliding sealing arrangement of the closing plate 113 and the surrounding structure can prevent the foreign matter discharged through the guide panel 112 from flowing to the inner cover ring 91 and the nacelle outer cover 5, and also prevent the airflow and foreign matter from flowing back into the space within the inner cover ring 91 from the gap of the telescopic rod 104 under the action of the airflow. The left side of the grille component 111 is connected with a two-way guide plate 114, which cooperates with the adjacent two-way guide channel 92 respectively, and the right side of the two-way guide plate 114 is respectively slidably sealed with the left side surface of the adjacent two-way guide channel 92, so that when the grille component 111 is displaced by impact, the two-way guide plate 114 can be driven to slide and keep sealed at the two-way guide channel 92 to keep the left side of the inner cover ring 91 airtight. The right side of the grille component 111 is fixedly connected with a wide guide plate 115, which cooperates with the wide guide channel 93, and the left side of the wide guide plate 115 is slidably sealed with the right side of the wide guide channel 93, so that when the grille component 111 is displaced by impact, the wide guide plate 115 can be driven to slide and keep sealed at the wide guide channel 93 to keep the space on the rear side of the right side opening of the inner cover ring 91 sealed from the guide panel 112.

[0046] When foreign matter hits the grille component 111 , the foreign matter that is not broken by the impact will flow from the inclined layout of the grille component 111 to the guide panel 112 through the airflow, and be discharged through the guide panel 112 , the right side opening of the nacelle outer cover 5 , and the right side opening of the inner cover ring 91 .

[0047] like Fig.16As shown, the grille component 111 includes a titanium alloy skeleton 1111, a rubber cushion layer 1112, a high-toughness impact layer 1113 and an electric heating wire 1114. The titanium alloy skeleton 1111 is the rear structure of the grille component 111. Both ends of the titanium alloy skeleton 1111 are respectively installed on the front sides of the telescopic rods 104 on both sides. The titanium alloy skeleton 1111 provides strength for the impacted grille component 111 to prevent the grille component 111 from being broken as a whole and being sucked into the aero-engine core 3. The front side of the titanium alloy skeleton 1111 is all rubber cushion layers 1112, and the rubber cushion layers 1112 are divided into upper and lower layers. The middle part of the front side of the titanium alloy skeleton 1111 is all high-toughness impact layers 1113, and the high-toughness impact layers 1113 are tightly attached to the rubber cushion layers 1112. The high-toughness impact layers 1113 are used to be directly impacted by foreign objects. The high-toughness impact layer 1113 provides impact and causes a certain overall deformation, and absorbs a certain impact kinetic energy through deformation, while the rubber pad layer 1112 is also used to indirectly absorb the impact kinetic energy and concentrated stress of deformation generated by the high-toughness impact layer 1113, to avoid excessive concentrated stress caused by local impact kinetic energy acting on the titanium alloy skeleton 1111, to protect the titanium alloy skeleton 1111 from being broken by excessive concentrated stress, and the rear side of the titanium alloy skeleton 1111 is fixedly connected with a heating wire 1114. When the heating wire 1114 is turned on, the titanium alloy skeleton 1111 structure can be heated, so that the titanium alloy skeleton 1111 can maintain a certain temperature when the aircraft is running in high-altitude and low-temperature air, to avoid the titanium alloy being in a low-temperature state for a long time, which increases its brittleness and reduces the required strength performance.

[0048] When a foreign object collides with the high-toughness impact layer 1113, the high-toughness impact layer 1113 will be directly impacted by the foreign object, forming a huge impact kinetic energy. The high-toughness impact layer 1113 can absorb part of the impact kinetic energy acting on itself through deformation, thereby reducing the impact speed of the foreign object. After the high-toughness impact layer 1113 is subjected to the impact kinetic energy, the rubber pad layer 1112 will indirectly absorb the impact kinetic energy and ensure that the concentrated stress generated by the impact kinetic energy will not directly act on the titanium alloy skeleton 1111 too much.

[0049] like Fig.18 As shown, the export device 12 includes a propulsion cylinder 121 and a movable outer cover 122. The propulsion cylinder 121 is fixedly connected to the right side of the upper and lower structures of the outer cover frame 7 respectively. The propulsion cylinder 121 is servo-controlled. The movable outer cover 122 is fixedly connected between the right ends of the propulsion member structure of the propulsion cylinder 121. The movable outer cover 122 can cover the right side opening structure of the nacelle outer cover 5.

[0050] By controlling the propulsion cylinder 121 , the propulsion cylinder 121 can drive the movable outer cover 122 to move, so that the movable outer cover 122 closes or opens the right side opening structure of the nacelle outer cover 5 .

[0051] like Fig.19As shown, the discharge device 13 includes an electric slide rail 131, a movable shell 132 and an air guide grille 133. The electric slide rail 131 is fixedly connected to the right inner wall of the air intake cabin 4. The electric slide rail 131 is servo-controlled. The movable shell 132 is fixedly connected to the moving part of the electric slide rail 131. The movable shell 132 can cover the right opening structure of the air intake cabin 4. The air guide grille 133 is fixedly connected to the upper side of the air intake cabin 4 in an array manner. The air guide grille 133 is used to block foreign objects from entering the air intake cabin 4.

[0052] By controlling the electric slide rail 131 , the electric slide rail 131 can drive the movable housing 132 to move, so that the movable housing 132 closes or opens the right opening structure of the air intake cabin 4 .

[0053] like Fig.19 As shown, a blocking grille 14 is also included. The blocking grille 14 is fixedly connected to the front side of the air intake compartment 4 in an array, and the blocking grille 14 is arc-shaped.

[0054] The arc-shaped blocking grille 14 can change the relative inclination angle of the foreign matter when it enters the air intake compartment 4 , so that the foreign matter is bounced away and does not enter the air intake compartment 4 .

[0055] It should be understood that the above description is only for exemplary purposes and is not meant to limit the present invention. Those skilled in the art will appreciate that variations of the present invention will be included within the scope of the claims herein.

Claims

1. An aircraft engine nacelle and an aircraft engine, comprising an aircraft engine pylon (1), an aircraft engine nacelle body (2) being mounted on the upper side of the aircraft engine pylon (1), and an aircraft engine core (3) being mounted inside the aircraft engine nacelle body (2), wherein: The front side of the aeroengine pylon (1) is connected to an air intake cabin (4), the front side of the aeroengine nacelle body (2) is connected to a nacelle cover (5) and a cover frame (7), an opening is provided on the right side of the nacelle cover (5), a fairing ring (6) is connected to the front side of the nacelle cover (5), the nacelle cover (5) is connected to the outside of the cover frame (7), an air guide cabin (8) is connected to the lower side of the cover frame (7), a nacelle inner cover component (9) is provided inside the cover frame (7), and a connecting hole (8) corresponding to the opening is provided on the right side of the nacelle inner cover component (9). An opening; two buffer devices (10) are arranged on the rear side of the outer cover frame (7), the two buffer devices (10) are arranged in a staggered manner, an obliquely arranged impact grille assembly (11) is arranged between the two groups of buffer devices (10), and the impact grille assembly (11) is obliquely arranged in the direction of the opening; a guide device (12) is arranged on the right side of the outer cover frame (7), and the guide device (12) can close or open the opening; a discharge device (13) is arranged on the right side of the air intake cabin (4), and the discharge device (13) is used to discharge foreign matter in the air intake cabin (4).

2. The aircraft engine nacelle and aircraft engine according to claim 1, characterized in that: The nacelle inner cover component (9) comprises an inner cover ring (91), the inner cover ring (91) is fixedly connected to the inner side of the outer cover frame (7), the inner cover ring (91) is a structure with a discharge port on the right side, a closed cover frame (901) is fixedly connected to the right side of the inner cover ring (91), a strike grid assembly (11) passes through the inner cover ring (91), a plurality of bidirectional guide paths (92) are arranged on the left side of the inner cover ring (91), and a wide guide path (93) is arranged at the rear of the right side of the inner cover ring (91).

3. The aircraft engine nacelle and aircraft engine according to claim 2, characterized in that: The buffer device (10) comprises a long arc frame (101), the long arc frame (101) is fixedly connected to the front position of the left side of the outer cover frame (7), and a short arc frame (102) is fixedly connected to the front position of the right side of the outer cover frame (7), the front side extension length of the long arc frame (101) is greater than that of the short arc frame (102), the front sides of the long arc frame (101) and the short arc frame (102) are both fixedly connected to compressed gas tanks (103), and the front sides of the compressed gas tanks (103) are both connected to multiple groups of telescopic rods (104).

4. The aircraft engine nacelle and aircraft engine according to claim 3, characterized in that: The impact grille assembly (11) comprises a grille component (111), the two ends of the grille component (111) are respectively mounted on the front sides of the telescopic rods (104) on both sides, a guide panel (112) is fixedly connected between the right sides of the grille component (111), a closing plate (113) is fixedly connected at the right position of the rear side of the guide panel (112), a bidirectional guide plate (114) is connected to the left side of the grille component (111), the bidirectional guide plates (114) are respectively matched with the adjacent bidirectional guide paths (92), and a wide guide plate (115) is fixedly connected to the right side of the grille component (111), and the wide guide plate (115) is matched with the wide guide path (93).

5. The aircraft engine nacelle and aircraft engine according to claim 4, characterized in that: The grille component (111) comprises a titanium alloy frame (1111), which is the rear structure of the grille component (1111), two ends of the titanium alloy frame (1111) are respectively installed on the front sides of telescopic rods (104) on both sides, the front side of the titanium alloy frame (1111) is a rubber cushion layer (1112), the rubber cushion layer (1112) is divided into an upper and lower layer, the middle part of the front side of the titanium alloy frame (1111) is a high-toughness impact layer (1113), the high-toughness impact layer (1113) is tightly attached to the rubber cushion layer (1112), and the rear side of the titanium alloy frame (1111) is fixedly connected with a heating wire (1114), and the heating wire (1114) can heat the titanium alloy frame (1111) structure when it is turned on.

6. The aircraft engine nacelle and aircraft engine according to claim 5, characterized in that: The export device (12) comprises a propulsion cylinder (121), which is respectively fixedly connected to the right sides of the upper and lower structures of the outer cover frame (7), and a movable outer cover (122) is fixedly connected between the right ends of the propulsion member structure of the propulsion cylinder (121), and the movable outer cover (122) can cover the right side opening structure of the nacelle outer cover (5).

7. The aircraft engine nacelle and aircraft engine according to claim 6, characterized in that: The discharge device (13) comprises an electric slide rail (131), the electric slide rail (131) is fixedly connected to the right inner wall of the air intake cabin (4), a movable housing (132) is fixedly connected to the moving part of the electric slide rail (131), the movable housing (132) can cover the right opening structure of the air intake cabin (4), and an air guide grille (133) is fixedly connected to the upper side of the air intake cabin (4) in an array.

8. The aircraft engine nacelle and aircraft engine according to claim 7, characterized in that: It also comprises a blocking grille (14), which is fixedly connected to the front side of the air intake compartment (4) in an array.

Images