An aeroengine nacelle and an aeroengine

Abstract

The present invention relates to an aeroengine, and particularly to an aeroengine nacelle and an aeroengine. An aeroengine nacelle and an aeroengine include an engine pylon. An upper side of the engine pylon is provided with a main body of the aeroengine nacelle. An aeroengine core engine is installed inside the main body of the aeroengine nacelle. An air intake nacelle is connected to a front side of the engine pylon. A nacelle outer casing and an outer casing skeleton are connected to a front side of the main body of the aeroengine nacelle. An opening is provided on a right side of the nacelle outer casing. A fairing ring is connected to a front side of the nacelle outer casing. The nacelle outer casing is connected to an outer side of the outer casing skeleton. An air guide nacelle is connected to a lower side of the outer casing skeleton. A nacelle inner casing member is provided inside the outer casing skeleton. By arranging an array of impact-resistant grille assemblies at the nacelle inner casing member, the present invention can prevent foreign objects from directly hitting the blades of the aeroengine core engine when the foreign objects enter the internal space of the fairing ring, avoiding damage to the blades caused by the foreign objects directly impacting the aeroengine core engine with high kinetic energy or being directly drawn into its core duct.

Description

Technical Field

[0001] The present invention relates to an aeroengine, and particularly to an aeroengine nacelle and an aeroengine. Background Art

[0002] In the field of engines of current aircraft, such as jet airplanes like airliners, many adopt turbofan engines, that is: a turbofan and a combustion chamber etc. constitute the core of the aeroengine, and what wraps and installs the core of the aeroengine is the nacelle. There is a fan for sucking air in the front side of the core of the aeroengine, the middle part of the core of the aeroengine is the combustion chamber, the rear part of the core of the aeroengine is the tail nozzle, and the position between the core of the aeroengine and its nacelle is the bypass duct of the aeroengine, which is also the main output power of a general jet airliner. What is located inside the combustion chamber is the core duct of the aeroengine. The air entering this will mix with fuel and burn to form high-pressure gas and eject it to provide power; and on current jet airplanes, the fan is directly exposed on the windward side. When the aircraft is flying, it is very easy to be impacted by space foreign objects. For example, within 30 meters during the takeoff and landing stages of the airplane, which is also the general activity height of birds. When the aircraft takes off and lands in this height area, the engine is very easy to be impacted by birds. At present, although there are various ways to prevent birds from impacting the engine, such as bird repelling operations at the airport, improvement of the engine blade structure, etc., the bird repelling operations at the airport cannot completely eliminate the hidden danger of birds impacting the engine. And changing the engine blade structure does have an effect, making the birds not directly enter the core duct and combustion chamber of the engine after impacting the engine, but it causes very great damage to the engine blades. Especially when the aircraft is flying at high speed, the increase in the impact kinetic energy brought by the increase in the relative speed is more likely to cause damage to the engine. And during the low-altitude takeoff and landing stages, if the aircraft is impacted by birds and one engine fails, it is very difficult for the pilot to make a timely response to the aircraft about to touch the ground. Such flight safety accidents have caused multiple air crashes; not only is the engine of the aircraft vulnerable to foreign object impacts during the low-altitude takeoff and landing stages, but also in bad weather at high altitudes, especially hail, it will still impact the inside of the engine and cause damage to the engine blades.

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

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

[0005] An aeroengine nacelle and an aeroengine, comprising an engine pylon. An upper side of the engine pylon is provided with a main body of the engine nacelle. An aeroengine core engine is installed inside the main body of the engine nacelle. An air intake cabin is connected to the front side of the engine pylon. A nacelle outer cover and an outer cover framework are connected to the front side of the main body of the engine nacelle. 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 framework. An air guide cabin is connected to the lower side of the outer cover framework. A nacelle inner cover member is arranged inside the outer cover framework. A communication port corresponding to the opening is provided on the right side of the nacelle inner cover member; Two buffer devices are provided on the rear side of the outer cover framework. The two buffer devices are arranged in a staggered manner. A struck grille assembly with an inclined layout is provided between the two groups of buffer devices. The struck grille assembly is inclined towards the opening direction; A guiding device is provided on the right side of the outer cover framework. The guiding device can close or open the opening; A discharging device is provided on the right side of the air intake cabin. The discharging device is used for discharging foreign matters in the air intake cabin.

[0006] Preferably, the nacelle inner cover member includes an inner cover ring. The inner cover ring is fixedly connected to the inner side of the outer cover framework. The inner cover ring has a structure with a discharge port opened on the right side. A closed cover frame is fixedly connected to the right side of the inner cover ring. The struck grille assembly passes through the inner cover ring. A plurality of bidirectional guiding channels are arranged on the left side of the inner cover ring. A wide guiding channel is arranged behind the right side of the inner cover ring.

[0007] Preferably, the buffer device includes a long arc-shaped frame. The long arc-shaped frame is fixedly connected to the front position on the left side of the outer cover framework. A short arc-shaped frame is fixedly connected to the front position on the right side of the outer cover framework. The front extension length of the long arc-shaped frame is greater than that of the short arc-shaped frame. Compressed air tanks are fixedly connected to the front sides of the long arc-shaped frame and the short arc-shaped frame. A plurality of telescopic rods are connected to the front sides of the compressed air tanks.

[0008] Preferably, the struck grille assembly includes a grille member. The two ends of the grille member are respectively installed on the front sides of the telescopic rods on both sides. A guiding panel is fixedly connected between the right sides of the grille member. A closing plate is fixedly connected to the right rear position of the guiding panel. Bidirectional guiding plates are connected to the left sides of the grille member. The bidirectional guiding plates are respectively matched with the adjacent bidirectional guiding channels. A wide guiding plate is fixedly connected to the right side of the grille member. The wide guiding plate is matched with the wide guiding channel.

[0009] Preferably, the grille member includes a titanium alloy framework. The titanium alloy framework is the rear structure of the grille member. The two ends of the titanium alloy framework are respectively installed on the front sides of the telescopic rods on both sides. Rubber cushion layers are arranged on the front sides of the titanium alloy framework. The rubber cushion layers are divided into upper and lower layers. High-toughness impact layers are arranged in the middle of the front sides of the titanium alloy framework. The high-toughness impact layers are in close contact with the rubber cushion layers. Electric heating wires are fixedly connected to the rear sides of the titanium alloy framework. After the electric heating wires are turned on, the structure of the titanium alloy framework can be heated.

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

[0011] Preferably, the discharge device includes an electric slide rail, which is fixedly connected to the inner wall of the right side of the intake cabin. There is a movable housing fixedly connected to the moving member of the electric slide rail, and the movable housing can cover the right opening structure of the intake cabin. The intake cabin is fixedly connected with air guide grilles in an array on the upper side.

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

[0013] The beneficial effects are as follows: 1. By arranging an array of impacted grille assemblies at the inner cover member of the nacelle, the present invention can prevent foreign objects from directly hitting the blades of the aeroengine core when entering the internal space of the fairing ring, avoiding foreign objects from directly impacting the aeroengine core with high kinetic energy and causing blade damage or being directly drawn into its internal duct.

[0014] 2. By adopting the method that the foreign object impacts the impacted grille assembly and absorbs energy through a buffer device, the present invention can reduce the impact kinetic energy of the foreign object, or cause the foreign object to form relatively low-speed and low-kinetic-energy fragments after impact. These foreign object fragments are thrown to the outer duct by the aeroengine core due to the energy absorption of the impact grille assembly and the buffer device and are discharged after being inhaled, avoiding the foreign object fragments from being drawn into the internal duct of the aeroengine core.

[0015] 3. By the action of the obliquely arranged impacted grille assembly and the export device, and the action of the discharge device, the present invention can discharge the unbroken foreign objects entering the inner cover member of the nacelle. And when installing the aeroengine nacelle and the aeroengine, the export devices are installed back to back, which can prevent the discharged foreign objects from hitting the horizontal tail and vertical tail of the aircraft.

[0016] 4. By adopting the intake layout method of two intake channels of the intake cabin and the fairing ring arranged at the windward position of the traditional aeroengine pylon, the present invention 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 aeroengine core to compensate for the lost intake air volume through the intake cabin when it is protected by the impacted grille assembly but the intake air volume is reduced, ensuring the normal operation of the aeroengine core. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0019] Figure 3 Schematic diagram of the three-dimensional structure of the second perspective when the export device of the present invention is opened.

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

[0021] Figure 5 Schematic diagram of the three-dimensional structure of the nacelle outer cover part of the present invention.

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

[0023] Figure 7 Schematic diagram of the three-dimensional structure of the outer cover skeleton part of the present invention.

[0024] Figure 8 Schematic diagram of the three-dimensional structure of the air guide cabin part of the present invention.

[0025] Figure 9 The first three-dimensional structure schematic diagram of the nacelle inner cover member part of the present invention.

[0026] Figure 10 The second three-dimensional structure schematic diagram of the nacelle inner cover member part of the present invention.

[0027] Figure 11 The third three-dimensional structure schematic diagram of the nacelle inner cover member part of the present invention.

[0028] Figure 12 The first three-dimensional structure schematic diagram of the buffer device part of the present invention.

[0029] Figure 13 The second three-dimensional structure schematic diagram of the buffer device part of the present invention.

[0030] Figure 14 The first three-dimensional structure schematic diagram of the impact grille assembly of the present invention.

[0031] Figure 15 The second three-dimensional structure schematic diagram of the impact grille assembly of the present invention.

[0032] Figure 16 Schematic diagram of the sectional structure of the grille member of the present invention.

[0033] Figure 17 Schematic diagram of the three-dimensional structure of the inner cover ring part of the present invention.

[0034] Figure 18 Schematic diagram of the three-dimensional structure of the export device part of the present invention.

[0035] Figure 19This is a schematic perspective view of the discharge device part of the present invention.

[0036] Figure 20 This is a schematic perspective view of the air intake cabin part of the present invention.

[0037] Names and serial numbers of components in the figure: 1 - engine pylon, 2 - engine nacelle main body, 3 - engine core, 4 - air intake cabin, 5 - nacelle outer cover, 6 - fairing ring, 7 - outer cover skeleton, 8 - air guide cabin, 9 - inner nacelle component, 10 - buffer device, 11 - impact-resistant grille assembly, 12 - export device, 13 - discharge device, 91 - inner cover ring, 901 - closed cover frame, 92 - bidirectional guide path, 93 - wide guide path, 101 - long arc-shaped frame, 102 - short arc-shaped frame, 103 - compressed air tank, 104 - telescopic rod, 111 - grille 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 housing, 133 - air guide grille, 14 - blocking grille. Detailed implementation manners

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

[0039] Example 1, as Figures 1 - 9 and Figures 19 - 20As shown in the figure, an aeroengine nacelle and an aeroengine include an engine pylon 1, a nacelle main body 2, an engine core 3, an intake cabin 4, a nacelle outer cover 5, a fairing ring 6, an outer cover framework 7, an air guide cabin 8, an inner nacelle component 9, a buffer device 10, a struck grille assembly 11, a lead-out device 12, and a discharge device 13. The nacelle main body 2 is installed on the upper side of the engine pylon 1, and the engine core 3 is installed inside the nacelle main body 2. The intake cabin 4 is fixedly connected to the front side of the engine pylon 1. The intake cabin 4 is structured to be inclined backward and upward, with openings on the front side and the upper side, and a discharge port on the right side. The discharge port structure on the right side of the intake cabin 4 is used to discharge foreign objects inside it. The intake cabin 4 is an inclined cavity structure facing backward and upward. The front opening structure of the intake cabin 4 is on the windward side of the aircraft. During flight, the airflow enters the cavity structure of the intake cabin 4 through the front opening and flows out through the upper opening structure of the inclined cavity structure of the intake cabin 4, forming the intake passage of the intake cabin 4. The nacelle outer cover 5 is fixedly connected to the front side of the nacelle main body 2. The outer layer structure of the nacelle outer cover 5 and the nacelle main body 2 is a streamlined structure, which is used to reduce the air resistance when the nacelle outer cover 5 and the nacelle main body fly in the air. Both the lower side and the right side of the nacelle outer cover 5 are open structures. The right-side opening structure of the nacelle outer cover 5 is used to discharge foreign objects. The fairing ring 6 is fixedly connected to the front side of the nacelle outer cover 5. The fairing ring 6 is an arc-shaped structure on the front side, which is used to straighten the airflow passing through the fairing ring 6. The outer cover framework 7 is fixedly connected to the front side of the nacelle main body 2. The outer cover framework 7 is located inside the nacelle outer cover 5 and is a double-ring frame body in the front and back directions. The front part of the inner side wall of the nacelle outer cover 5 is fixedly connected to the outer periphery of the front side of the outer cover framework 7 for fastening the nacelle outer cover 5. The air guide cabin 8 is fixedly connected to the lower side of the outer cover framework 7. The outer edge of the lower side of the air guide cabin 8 is butted and sealed with the lower-side opening structure of the nacelle outer cover 5. The lower end face of the air guide cabin 8 is butted and sealed with the upper end face of the intake cabin 4. The air guide cabin 8 communicates with the intake cabin 4. The airway structures of the air guide cabin 8 and the intake cabin 4 are uniformly inclined backward and upward, and the surface is smooth, which is used to assist the airflow to enter the nacelle main body 2 through the inclined airway and the smooth surface. The inner nacelle component 9 is arranged inside the outer cover framework 7. The inner nacelle component 9 has a discharge opening for foreign objects corresponding to the right-side opening of the nacelle outer cover 5 on the right side. The inner nacelle component 9 forms the inner layer area at the front side of the aeroengine nacelle and the aeroengine. The space inside the inner nacelle component 9 is the intake passage of the aeroengine nacelle and the aeroengine;During the flight of the aircraft, the airflow enters the internal space of the nacelle inner cover member 9 through the fairing ring 6, which is the main air intake passage for the aeroengine nacelle and the aeroengine. The airflow during the flight of the aircraft enters the internal space of the nacelle inner cover member 9 through the air intake compartment 4, then through the air guide compartment 8, which is the auxiliary air intake passage for the aeroengine nacelle and the aeroengine. That is, the aeroengine nacelle and the aeroengine have a dual air intake duct layout. Since the air intake compartment 4 is itself located in front of the engine pylon 1, therefore, the auxiliary air flow passage entering the aeroengine nacelle and the aeroengine 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 outer nacelle 5 of the aeroengine nacelle and the aeroengine is streamlined as in the traditional case, so it will not increase the frontal area of the aircraft during flight either, and similarly will not increase the flight resistance of the aircraft;Buffer devices 10 are provided on both the left and right sides of the rear annular structure of the outer cover frame 7. The buffer device 10 on the left side of the outer cover frame 7 extends forward relative to the other group, causing the two groups of buffer devices 10 to be misaligned in the top view plane. A struck grille assembly 11 is provided between the two groups of buffer devices 10. The struck grille assembly 11 is installed between the two misaligned buffer devices 10 to form an inclined layout. The struck grille assembly 11 is inclined towards the right side opening direction of the nacelle outer cover 5, so that when the struck grille assembly 11 is struck by foreign objects and does not break, the foreign objects are blown out of the inner nacelle component 9 through the air flow and discharged through the discharge opening of the inner nacelle component 9 and the right side opening of the nacelle outer cover 5 into the internal space of the aeroengine nacelle and the aeroengine, preventing them from entering the inner and outer bypass ducts of the engine core 3. The struck grille assembly 11 passes through the inner nacelle component 9. The struck grille assembly 11 forms an array of blocking grids that are horizontally arranged and inclined to the right in the internal space of the inner nacelle component 9. The struck grille assembly 11 is slidably sealed at the inner nacelle component 9. The slidable sealing cooperation mode of the struck grille assembly 11 at the inner nacelle component 9 can prevent the air flow and foreign objects passing through the struck grille assembly 11 from entering the space between the inner nacelle component 9 and the nacelle outer cover 5. The struck grille assembly 11 passes through the right side discharge port structure of the inner nacelle component 9, and there is still a discharge space reserved in the right side discharge port structure of the inner nacelle component 9. When the struck grille assembly 11 is struck by relatively large foreign objects contained in the air flow in the space, such as low-altitude birds during the takeoff and landing stages of the aircraft, birds during the climbing stage, and hail in bad weather, etc., when such foreign objects are sucked into the inner nacelle component 9, the struck grille assembly 11 will reduce the probability of the relatively large foreign objects directly hitting the engine core 3, causing the relatively large foreign objects to hit the struck grille assembly 11. Since the aircraft is flying at a very high speed during flight, the struck grille assembly 11 hit by foreign objects will absorb energy through its own structure. At the same time, the struck grille assembly 11 will act on the buffer device 10 after being hit, causing the buffer device 10 to absorb the impact energy of the impact, protecting the integrity of the structure of the struck grille assembly 11 itself, and preventing the struck grille assembly 11 from fragmenting into small parts and being sucked into the bypass duct of the engine core 3. Because the relative speed of the aircraft to space foreign objects is fast during flight, the impact speed of the foreign objects will be greatly reduced after hitting the struck grille assembly 11, thereby reducing the relative speed of the foreign objects to the aircraft and reducing the impact kinetic energy. Even if the foreign objects entering the inner nacelle component 9 break through the struck grille assembly 11 due to the impact, due to their reduced volume and speed, the foreign objects will be thrown to its outer bypass duct by the blades of the engine core 3 running at high speed and discharged, so that the foreign objects will not directly hit the blades of the engine core 3 due to relatively high speed and high kinetic energy, and the foreign objects broken by hitting the blades of the engine core 3 will not be sucked into its bypass duct due to the relatively high speed effect, preventing the internal combustion chamber of the engine core 3 from being damaged by the entry of foreign objects in the bypass duct;On the right side of the outer casing framework 7, there is an outlet device 12. The outlet device 12 can close or open the right-side opening structure of the nacelle outer casing 5. If the outlet device 12 closes the right-side opening structure of the nacelle outer casing 5, the inside of the nacelle outer casing 5 is a closed suction space. If the outlet device 12 opens the right-side opening structure of the nacelle outer casing 5, the foreign objects in the internal space of the inner nacelle member 9 can be discharged from the right-side opening structure of the nacelle outer casing 5; on the right side of the intake compartment 4, there is a discharge device 13. The discharge device 13 is used to discharge the foreign objects in the intake compartment 4, so as to prevent the foreign objects from entering the space inside the inner nacelle member 9 via the intake compartment 4 and prevent the foreign objects from entering the aero-engine core 3. Since the aero-engine nacelle and the aero-engine have two intake channels, namely the intake compartment 4 and the fairing ring 6, therefore, the layout of the impact grille assembly 11 on the inner nacelle member 9 reduces the suction area in the direction of the fairing ring 6, but the intake channel of the intake compartment 4 can compensate for the reduced suction area, thereby ensuring the intake air volume of the aero-engine nacelle and the aero-engine.;

[0040] The nacelle of the aero-engine and the aero-engine can be installed above the wing through the engine pylon 1 and the intake nacelle 4. That is, the nacelle of the aero-engine and the aero-engine are more suitable for small aircraft installed above the wing. When installing the nacelle of the aero-engine and the aero-engine, a set of the nacelle of the aero-engine and the aero-engine with the export device 12 facing to the right needs to be installed above the left wing, and the nacelle of the aero-engine and the aero-engine with the export device 12 facing to the left needs to be installed above the right wing. That is, the export devices 12 are installed back to back, so that the foreign objects discharged by the export devices 12 will not hit the horizontal tail and vertical tail of the aircraft; during the takeoff and landing stages of the aircraft installed with the nacelle of the aero-engine and the aero-engine, the export device 12 and the discharge device 13 can be selectively turned on. During the flight of the aircraft, the export device 12 and the discharge device 13 in the open state will affect the flight air resistance of the aircraft. During the flight of the aircraft, the airflow will enter the inner cover member 9 of the nacelle through the double channels of the fairing ring 6 and the intake nacelle 4. The aero-engine core 3 will also inhale a large amount of air from the above double channels to do work; if the aircraft is hit by foreign objects such as birds and hail from space during the takeoff and landing stages or other flight stages, especially when the above-mentioned flying foreign objects enter the space within the fairing ring 6, the impact grille assembly 11 will reduce the probability of foreign objects directly hitting the blades of the aero-engine core 3. Due to the layout of the impact grille assembly 11, larger foreign objects will not directly hit the blades of the aero-engine core 3. For foreign objects hitting the impact grille assembly 11, the impact grille assembly 11 will absorb the kinetic energy of the impact through its own structure and the cooperation buffer device 10, reducing the relative speed of the foreign objects. Even if the foreign objects with reduced speed enter the space between the inner cover member 9 of the nacelle and the blades of the aero-engine core 3, the high-speed rotating blades of the aero-engine core 3 will throw the foreign objects to the outer periphery inside the aero-engine nacelle main body 2, so that the outer duct of the aero-engine core 3 will inhale and then discharge from the tail nozzle, and will not enter the inner duct of the aero-engine core 3 and enter the combustion chamber. If larger foreign objects hit the impact grille assembly 11 and break due to kinetic energy, the broken foreign objects will also be thrown to the outer periphery inside the aero-engine nacelle main body 2 by the impact and energy absorption to reduce the speed and be inhaled by the aero-engine core 3 into the outer duct and will not enter the inner duct. If the impact kinetic energy of larger foreign objects is insufficient and they do not break, the foreign objects will stay on the impact grille assembly 11, at the inclined rear side of the impact grille assembly 11. At this time, the foreign objects will affect the air intake volume of the aero-engine core 3, and the output power of the aero-engine core 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 at this time to discharge the larger foreign objects staying at the impact grille assembly 11; in addition, foreign objects entering the intake nacelle 4 will also be blocked by the discharge device 13 to prevent foreign objects from entering the inner cover member 9 of the nacelle, and the discharge device 13 can also be selectively turned on to discharge the foreign objects in the intake nacelle 4.

[0041] Example 2, asFigures 9 - 13 As shown, the nacelle inner cover member 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 framework 7. The inner cover ring 91 has 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 objects that are not broken after being blocked by the impacted grille assembly 11 inside it. A closed cover frame 901 is fixedly connected to the right side of the inner cover ring 91. The closed cover frame 901 surrounds the upper and lower edges and the front edge of the discharge port structure on the right side of the inner cover ring 91. The right sides of the upper and lower edges and the front edge of the closed cover frame 901 are hermetically joined to the inner wall of the nacelle outer cover 5, so that the closed cover frame 901 forms an independent and interconnected space between the right opening of the inner cover ring 91 and the right opening of the nacelle outer cover 5 for discharging foreign objects, enabling the air flow passing through the inner cover ring 91 to flow from its right opening structure through the closed cover frame 901 to the right opening structure of the nacelle outer cover 5, preventing the air flow from entering the space inside the nacelle outer cover 5, the outer cover framework 7, the inner cover ring 91, and the closed cover frame 901, and making the air flow only in the space inside the inner cover ring 91 and the closed cover frame 901. The left side of the inner cover ring 91 has an array of openings. The impacted grille assembly 11 passes through the array of openings on the left side and the discharge port structure on the right side of the inner cover ring 91. A plurality of bidirectional guide channels 92 are arranged at the array of openings 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, and also to maintain the left-side sealing of the inner cover ring 91 when the impacted grille assembly 11 generates impact displacement. A wide guide channel 93 is arranged behind 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, and also to maintain the sealing of the position behind the right opening of the inner cover ring 91 when the impacted grille assembly 11 generates impact displacement, preventing foreign objects and air flow from flowing back into the space between the rear of the impacted grille and the aeroengine core 3.

[0042] After the impacted grille assembly 11 is impacted by a foreign object, the impacted grille assembly 11 will displace inside the inner cover ring 91 to ensure that the inner cover ring 91 is not directly impacted by relatively large foreign objects entering and hitting the blades of the aeroengine core 3.

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

[0044] After the impacted grille assembly 11 is impacted by foreign objects, in addition to absorbing energy by itself, the impacted grille assembly 11 will displace backward through the telescopic rod 104 under the propulsion of the kinetic energy of the foreign objects, so that the impacted grille assembly 11 displaces backward under the pneumatic buffering action of the compressed gas tank 103 through the telescopic rod 104, thereby reducing the impact kinetic energy of the foreign objects through pneumatic compression, and reducing the impact speed or breaking the foreign objects.

[0045] As Figures 12 - 18As shown, the struck grille assembly 11 includes a grille member 111, a guiding panel 112, a closing plate 113, a two-way guiding plate 114, and a wide guiding plate 115. The grille member 111 is respectively installed on the front sides of the two telescopic rods 104. A guiding panel 112 is fixedly connected between the right sides of the grille members 111. The upper and lower edges of the guiding panel 112 are slidably sealed with the upper and lower surfaces of the inner wall of the closing cover frame 901. The guiding panel 112 is used to guide the foreign objects striking the grille member 111 to be discharged through the right opening of the nacelle outer cover 5. A closing plate 113 is fixedly connected at the position on the rear right side of the guiding panel 112. The left side surface of the closing plate 113 is slidably sealed with the surface of the compressed air tank 103 on the right side. The upper and lower edges of the closing plate 113 are slidably sealed with the upper and lower surfaces of the inner wall of the closing 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 slidable sealing arrangement of the closing plate 113 with the surrounding structure can prevent the foreign objects discharged through the guiding panel 112 from flowing into the space between the inner shroud ring 91 and the nacelle outer cover 5, and also avoid the air flow and foreign objects from flowing back into the space inside the inner shroud ring 91 through the gaps of the telescopic rods 104 under the action of the air flow. Two-way guiding plates 114 are connected to the left sides of the grille members 111 respectively. The two-way guiding plates 114 are respectively matched with the adjacent two-way guiding channels 92. The right side surfaces of the two-way guiding plates 114 are slidably sealed with the left side surfaces of the adjacent two-way guiding channels 92 respectively, so that when the grille member 111 is displaced under impact, it can drive the two-way guiding plate 114 to slide at the two-way guiding channel 92 and maintain the seal, so as to keep the left side of the inner shroud ring 91 airtight. A wide guiding plate 115 is fixedly connected to the right side of the grille member 111. The wide guiding plate 115 is matched with the wide guiding channel 93. The left side surface of the wide guiding plate 115 is slidably sealed with the right side of the wide guiding channel 93, so that when the grille member 111 is displaced under impact, it can drive the wide guiding plate 115 to slide at the wide guiding channel 93 and maintain the seal, so as to keep the opening on the right side of the inner shroud ring 91 airtight from the space behind the guiding panel 112.

[0046] When foreign objects strike the grille member 111, the foreign objects that are not struck and broken will flow from the inclined layout of the grille member 111 to the guiding panel 112 under the action of the air flow, and are discharged through the guiding panel 112, the right opening of the nacelle outer cover 5, and the right opening of the inner shroud ring 91.

[0047] Such as Figure 16As shown in the figure, the grille member 111 includes a titanium alloy skeleton 1111, a rubber cushion layer 1112, a high-toughness impact layer 1113, and heating wires 1114. The titanium alloy skeleton 1111 is the rear structure of the grille member 111. The two 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 the strength of the grille member 111 under impact, preventing the entire grille member 111 from breaking and being sucked into the aero-engine core 3. The front side of the titanium alloy skeleton 1111 is entirely a rubber cushion layer 1112. The rubber cushion layer 1112 is divided into upper and lower layers. The middle part of the front side of the titanium alloy skeleton 1111 is entirely a high-toughness impact layer 1113. The high-toughness impact layer 1113 is in close contact with the rubber cushion layer 1112. The high-toughness impact layer 1113 is used to directly receive the impact of foreign objects. The high-toughness impact layer 1113 provides impact and causes a certain overall deformation, absorbing a certain amount of impact kinetic energy through the deformation. The rubber cushion layer 1112 is also used to indirectly absorb the impact kinetic energy generated by the high-toughness impact layer 1113 and the concentrated stress of the deformation, preventing the concentrated stress generated by the local impact kinetic energy from acting on the titanium alloy skeleton 1111 too greatly, so as to protect the titanium alloy skeleton 1111 from breaking due to excessive concentrated stress. Electric heating wires 1114 are fixedly connected to the rear sides of the titanium alloy skeleton 1111. After the electric heating wires 1114 are turned on, they can heat up the structure of the titanium alloy skeleton 1111, enabling the titanium alloy skeleton 1111 to maintain a certain temperature when the aircraft operates in the high-altitude low-temperature air, preventing the titanium alloy from becoming brittle due to long-term exposure to low temperatures and reducing the required strength performance.

[0048] When impacted by foreign objects, the high-toughness impact layer 1113 will directly receive the impact of the foreign objects, forming a huge impact kinetic energy. The high-toughness impact layer 1113 can absorb part of the kinetic energy through deformation of the impact kinetic energy acting on itself, reducing the impact speed of the foreign objects. After the high-toughness impact layer 1113 receives the impact kinetic energy, the rubber cushion layer 1112 will indirectly absorb the impact kinetic energy and ensure that the concentrated stress generated by the impact kinetic energy does not act directly on the titanium alloy skeleton 1111 too greatly.

[0049] As Figure 18 As shown in the figure, the export device 12 includes a propulsion cylinder 121 and a movable outer cover 122. The propulsion cylinder 121 is respectively fixedly connected to the right sides of the upper and lower layer structures of the outer cover skeleton 7. The propulsion cylinder 121 is servo-controlled. A movable outer cover 122 is fixedly connected between the right ends of the propulsion members of the propulsion cylinder 121. The movable outer cover 122 can cover the right 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, making the movable outer cover 122 close or open the right opening structure of the nacelle outer cover 5.

[0051] As Figure 19As shown, the discharging device 13 includes an electric slide rail 131, a movable housing 132, and an air guide grille 133. The electric slide rail 131 is fixedly connected to the right inner wall of the intake chamber 4. The electric slide rail 131 is servo-controlled. A movable housing 132 is fixedly connected to the moving member of the electric slide rail 131. The movable housing 132 can cover the right opening structure of the intake chamber 4. The air guide grille 133 is fixedly connected to the upper side of the intake chamber 4 in an array. The air guide grille 133 is used to block foreign objects entering the intake chamber 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 intake chamber 4.

[0053] As Figure 19 shown, it further includes a blocking grille 14. The blocking grille 14 is fixedly connected to the front side of the intake chamber 4 in an array. The blocking grille 14 is arc-shaped.

[0054] The arc-shaped blocking grille 14 can change the inclination angle of the foreign object's relative movement when the foreign object enters the intake chamber 4, so that the foreign object is bounced off and does not enter the intake chamber 4.

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

Claims

1. An aeroengine nacelle and an aeroengine, comprising an engine pylon (1), an upper side of the engine pylon (1) is provided with a nacelle main body (2), and an aeroengine core engine (3) is installed inside the nacelle main body (2), and the features are as follows: An aero-engine pylon (1) is connected to an air intake cabin (4) at the front side. The front side of the aero-engine nacelle main body (2) is connected to a nacelle outer cover (5) and an outer cover skeleton (7). An opening is provided on the right side of the nacelle outer cover (5). The front side of the nacelle outer cover (5) is connected to a fairing ring (6). The nacelle outer cover (5) is connected to the outside of the outer cover skeleton (7). An air guide cabin (8) is connected to the lower side of the outer cover skeleton (7). A nacelle inner cover member (9) is arranged inside the outer cover skeleton (7). A communication port corresponding to the opening is provided on the right side of the nacelle inner cover member (9). Two buffer devices (10) are provided at the rear side of the outer cover skeleton (7). The two buffer devices (10) are arranged in a staggered manner. A struck grille assembly (11) with an inclined layout is provided between the two groups of buffer devices (10). The struck grille assembly (11) is inclined towards the opening direction. An outlet device (12) is provided on the right side of the outer cover skeleton (7). The outlet device (12) can close or open the opening. A discharge device (13) is provided on the right side of the air intake cabin (4). The discharge device (13) is used to discharge foreign objects in the air intake cabin (4). The nacelle inner cover member (9) includes an inner cover ring (91). The inner cover ring (91) is fixedly connected to the inner side of the outer cover skeleton (7). The inner cover ring (91) has a structure with a discharge port opened on the right side. A closed cover frame (901) is fixedly connected to the right side of the inner cover ring (91). The struck grille assembly (11) passes through the inner cover ring (91). A plurality of bidirectional guide channels (92) are arranged on the left side of the inner cover ring (91). A wide guide channel (93) is arranged at the rear right side of the inner cover ring (91). The struck grille assembly (11) includes a grille member (111). The two ends of the grille member (111) are respectively installed on the front sides of the two telescopic rods (104) on both sides. A guide panel (112) is fixedly connected between the right sides of the grille member (111). A closing plate (113) is fixedly connected to the position at the rear right side of the guide panel (112). Bidirectional guide plates (114) are connected to the left sides of the grille member (111). The bidirectional guide plates (114) are respectively matched with the adjacent bidirectional guide channels (92). A wide guide plate (115) is fixedly connected to the right side of the grille member (111). The wide guide plate (115) is matched with the wide guide channel (93).

2. The aeroengine nacelle and aeroengine according to claim 1, characterized in that: The buffer device (10) includes a long arc-shaped frame (101). The long arc-shaped frame (101) is fixedly connected to the position at the front left side of the outer cover skeleton (7). A short arc-shaped frame (102) is fixedly connected to the position at the front right side of the outer cover skeleton (7). The front extension length of the long arc-shaped frame (101) is greater than that of the short arc-shaped frame (102). Compressed air tanks (103) are fixedly connected to the front sides of the long arc-shaped frame (101) and the short arc-shaped frame (102). Multiple groups of telescopic rods (104) are connected to the front sides of the compressed air tanks (103).

3. The aeroengine nacelle and aeroengine according to claim 2, characterized in that: The grille member (111) includes a titanium alloy skeleton (1111). The titanium alloy skeleton (1111) is the rear structure of the grille member (111). The two ends of the titanium alloy skeleton (1111) are respectively installed on the front sides of the telescopic rods (104) on both sides. The front sides of the titanium alloy skeleton (1111) are all rubber cushions (1112). The rubber cushions (1112) are divided into upper and lower layers. The middle parts of the front sides of the titanium alloy skeleton (1111) are all high-toughness impact layers (1113). The high-toughness impact layers (1113) are in close contact with the rubber cushions (1112). Electric heating wires (1114) are fixedly connected to the rear sides of the titanium alloy skeleton (1111). After the electric heating wires (1114) are turned on, the structure of the titanium alloy skeleton (1111) can be heated up.

4. An aeroengine nacelle and an aeroengine according to claim 3, characterized in that: The export device (12) includes a propulsion cylinder (121). The propulsion cylinder (121) is respectively fixedly connected to the right sides of the upper and lower layer structures of the outer cover skeleton (7). A movable outer cover (122) is fixedly connected between the right ends of the propulsion member structures of the propulsion cylinder (121). The movable outer cover (122) can cover the right-side opening structure of the nacelle outer cover (5).

5. A nacelle for an aeroengine and an aeroengine according to claim 4, characterized in that: The discharge device (13) includes an electric slide rail (131). The electric slide rail (131) is fixedly connected to the right inner wall of the intake cabin (4). A movable housing (132) is fixedly connected to the moving member of the electric slide rail (131). The movable housing (132) can cover the right-side opening structure of the intake cabin (4). Air guide grilles (133) are fixedly connected to the upper side of the intake cabin (4) in an array.

6. The aeroengine nacelle and aeroengine according to claim 5, characterized in that: It further includes a blocking grille (14). The blocking grille (14) is fixedly connected to the front side of the intake cabin (4) in an array.

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