Anti-icing pipeline device of aero-engine and aero-engine

Abstract

The invention discloses an aero-engine anti-icing pipeline device and an aero-engine, and belongs to the technical field of aero-engines, the aero-engine anti-icing pipeline device comprises an air entraining pipe and a sleeve assembly, an inlet of the air entraining pipe is inserted into an outlet of an anti-icing valve and can slide in the axial direction, and the sleeve assembly comprises a connecting sleeve and a compression spring; a first blocking piece is arranged on the outer wall of the outlet end of the anti-icing valve, a second blocking piece is arranged on the outer wall of the air guiding pipe, the connecting sleeve is used for being arranged at the joint of the anti-icing valve and the air guiding pipe in a sleeving mode and shielding and sealing the joint, the first side of the connecting sleeve abuts against the side wall of the first blocking piece, and the second side of the connecting sleeve abuts against the first end of the compression spring. The second end of the compression spring abuts against the side wall of the second blocking piece. A linear air entraining channel is formed by the air entraining pipe and the anti-icing valve, the air entraining pipe and the anti-icing valve are in axial sliding and radial small clearance fit, and the joint is sealed through the sleeve assembly, so that compensation of axial and radial dimensional deviation is achieved.

Description

Technical Field

[0001] The present application relates to the field of aircraft engine technology, and in particular, to an aircraft engine anti-icing pipeline device. In addition, the present application also relates to an aircraft engine comprising the aircraft engine anti-icing pipeline device. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] When an aircraft flies through an icing-prone environment, tiny water droplets from fog and mist can be drawn into the engine along with the air, freezing in the cooler front end of the engine, impacting engine performance. Excessive ice can cause ice to break off and enter the engine, damaging it and compromising flight safety.

[0004] In order to prevent icing from affecting the engine, the engine will adopt an anti-icing design. Generally, the hot air at the compressor outlet is passed through a pipe system to transport the hot air to the part of the engine front end that needs anti-icing for anti-icing.

[0005] The anti-icing air bleed line connects the compressor and anti-icing components (such as the air intake case or compressor inlet). There are two difficulties in designing it: 1. Anti-icing air bleed pipes are generally thick in diameter (over 20mm), highly rigid, and require connection between the compressor outlet and the engine inlet casing. This creates a large span and leads to a large cumulative deviation in component dimensions, making assembly more difficult. 2. During engine operation, the engine casing and anti-icing pipelines expand and deform due to heat. The uncoordinated thermal deformation (i.e., the axial expansion of the casing is inconsistent with the axial expansion of the anti-icing pipeline system) will cause the pipelines to be subjected to greater thermal stress, which will have an adverse effect on the strength, lifespan and sealing of the anti-icing air bleed pipelines.

[0006] The design of existing engine anti-icing air ducts primarily increases their length and incorporates multiple bends, distributing assembly and thermal deformation deviations over a relatively long duct and associated bends. This design approach not only increases the length and weight of the anti-icing air duct, but also fails to fundamentally address the difficulties of assembly and thermal stress, resulting in poor maintainability and a short lifespan for the anti-icing air duct system. Therefore, further research is urgently needed to improve the anti-icing air duct system in aircraft engines, ensuring the shortest possible routing, axial and radial compensation, and ease of assembly and disassembly. Summary of the Invention

[0007] In view of at least one of the above technical problems, the present application provides an aircraft engine anti-icing pipeline device, which can form a straight air bleed channel through the air bleed pipe and the anti-icing valve. The air bleed pipe and the anti-icing valve are axially slidable and matched with a small radial clearance, and the connection is sealed by a sleeve assembly to achieve compensation for axial and radial dimensional deviations.

[0008] At the same time, the present application also provides an aircraft engine including the above-mentioned aircraft engine anti-icing pipeline device.

[0009] According to one aspect of the present application, an aircraft engine anti-icing piping device is provided, comprising an air bleed pipe for connecting a compressor casing with an air intake casing to bleed air from the air intake casing, and an anti-icing valve provided on the compressor casing, wherein the air bleed pipe is connected to the compressor casing via the anti-icing valve. The aircraft engine anti-icing piping device further comprises a sleeve assembly: The channel inside the anti-icing valve is coaxially connected to the air bleed pipe. The inlet end of the air bleed pipe is inserted into the outlet end of the anti-icing valve and can slide axially relative to the anti-icing valve. The sleeve assembly includes a connecting sleeve and a compression spring. The outer wall of the outlet end of the anti-icing valve is provided with a first stopper, and the outer wall of the air bleed pipe is provided with a second stopper. A limiting cavity is formed between the first stopper and the second stopper. The connecting sleeve is used to be sleeved on the connection between the anti-icing valve and the air bleed pipe and to shield and seal the connection. The first end of the connecting sleeve abuts against the side of the first stopper toward the second stopper, and the compression spring is pressed between the second end of the connecting sleeve and the second stopper. The compression spring is used to provide an elastic force to push the connecting sleeve against the first stopper.

[0010] In some embodiments of the present application, the sleeve assembly also includes a first sealing ring, a sealing cavity is opened on the inner side of the connecting sleeve, and limiting grooves are opened on the opposite sides of the sealing cavity. The limiting grooves are used to limit the first sealing ring, and the first sealing ring is used to seal the connection between the connecting sleeve and the anti-icing valve and the connection between the connecting sleeve and the air bleed pipe respectively.

[0011] In some embodiments of the present application, the first sealing ring is a U-shaped or V-shaped structure made of elastic material. The first sealing ring is elastically pressed in the limiting groove, and during the process of the connecting sleeve being heated and deformed, the first sealing ring is squeezed by the inner wall of the limiting groove to tightly seal the connection between the connecting sleeve and the anti-icing valve and the air bleed pipe.

[0012] In some embodiments of the present application, the air bleed duct includes a main body section and a support section arranged at the inlet end of the main body section, the diameter of the support section is smaller than the diameter of the main body section, and the support section is used to be slidably inserted into the outlet end of the anti-icing valve.

[0013] In some embodiments of the present application, a second connecting boss is provided at the inlet end of the anti-icing valve, and the second connecting boss is used to abut and cooperate with a first connecting boss preset at the connection port of the compressor casing. The aircraft engine anti-icing pipeline device also includes a clamp, which is used to cover the first connecting boss and the second connecting boss to lock and limit the two.

[0014] In some embodiments of the present application, the aircraft engine anti-icing pipeline device also includes a second sealing ring, a sealing groove is opened on the second connecting boss, the second sealing ring is installed in the sealing groove, and the second sealing ring is used to seal the sealing surface between the second connecting boss and the first connecting boss.

[0015] In some embodiments of the present application, a boss-shaped connecting platform is provided on the second connecting boss, and the connecting platform is used to be snapped into a connecting groove preset in the first connecting boss.

[0016] In some embodiments of the present application, the aircraft engine anti-icing pipeline device further includes a support member for being installed on the outer wall of the compressor casing, wherein the support member is connected to the anti-icing valve and supports and limits the anti-icing valve.

[0017] In some embodiments of the present application, the aircraft engine anti-icing pipeline device also includes a connecting flange arranged at the outlet end of the air bleed pipe and used to connect to the air intake casing, a locking piece is arranged in the flange hole of the connecting flange, the locking piece is used to lock the connecting flange, and a locking platform is provided at the driving end of the locking piece, and a gap of 0.4-0.6mm is provided between the locking platform and the end face of the flange hole.

[0018] According to another aspect of the present application, an aircraft engine is also provided, which includes the above-mentioned aircraft engine anti-icing pipeline device.

[0019] This application has the following beneficial effects: The aircraft engine anti-icing piping device disclosed herein connects an air bleed duct with an anti-icing valve to form a linear air bleed passage. This passage connects the compressor casing and the intake casing, achieving the shortest possible connection path, avoiding the use of long or curved pipes and thus reducing overall weight. The air bleed duct inlet and the anti-icing valve are connected in an axially slidable manner, with a small radial gap. A sleeve assembly seals the connection between the air bleed duct and the anti-icing valve. The sleeve is installed in a positional manner using a compression spring to engage a first stopper on the outer wall of the anti-icing valve and a second stopper on the outer wall of the air bleed duct. This makes assembly and disassembly very convenient, and the sealing effect at the connection between the air bleed duct and the anti-icing valve is maintained even when the air bleed duct slides relative to the outlet of the anti-icing valve, thereby reducing gas leakage. The present application adopts a small radial clearance fit between the anti-icing valve and the air bleed pipe, and allows for axial relative sliding, thereby compensating for axial and radial dimensional deviations, effectively coping with the larger thermal stress of the anti-icing pipeline device, and greatly reducing the difficulty of assembly, thereby effectively improving the overall maintainability of the anti-icing air bleed pipe system, and helping to increase the overall life of the anti-icing air bleed pipe device.

[0020] The aircraft engine of the present application also has the above-mentioned beneficial effects. It also includes an aircraft engine anti-icing air bleed pipe system that can be conveniently installed using the shortest path under conditions of limited axial space, and has the advantages of simple layout, light weight, and the ability to effectively cope with large thermal stresses.

[0021] Of course, any product implementing this application does not necessarily need to achieve all of the advantages described above. In addition to the purposes, features, and advantages described above, this application also has other purposes, features, and advantages. This application will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of this application. The exemplary embodiments and descriptions of this application are intended to explain this application and do not constitute an improper limitation on this application. In the accompanying drawings: Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 2 Schematic diagram of the installation position of the support member of the preferred embodiment of the present application; Figure 3 This is a schematic diagram of the installation position of the clamp in the preferred embodiment of the present application; Figure 4 It is a structural schematic diagram of the sleeve assembly of the preferred embodiment of the present application; Figure 5 This is a schematic diagram of the connection between the air bleed pipe and the air intake casing in a preferred embodiment of the present application; Legend: 1. Compressor casing; 11. First connecting boss; 111. Connecting groove; 2. Anti-icing valve; 21. Electric control valve; 22. First stopper; 23. Second connecting boss; 231. Sealing groove; 232. Connecting platform; 3. Air bleed pipe; 31. Second stopper; 32. Connecting ring; 33. Support section; 4. Air intake casing; 5. Sleeve assembly; 51. Connecting sleeve; 511. Limiting groove; 52. Compression spring; 53. First sealing ring; 6. Support member; 7. Clamp; 8. Second sealing ring; 9. Connecting flange; 91. Locking member. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0024] Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 2 Schematic diagram of the installation position of the support member of the preferred embodiment of the present application; Figure 3 This is a schematic diagram of the installation position of the clamp in the preferred embodiment of the present application; Figure 4 It is a structural schematic diagram of the sleeve assembly of the preferred embodiment of the present application; Figure 5 This is a schematic diagram of the connection between the air duct and the air intake casing in a preferred embodiment of the present application.

[0025] An aircraft engine anti-icing piping device includes an air bleed pipe 3 for connecting a compressor casing 1 with an air intake casing 4 to bleed air from the air intake casing 4, and an anti-icing valve 2 provided on the compressor casing 1. The air bleed pipe 3 is connected to the compressor casing 1 through the anti-icing valve 2. The aircraft engine anti-icing piping device also includes a sleeve assembly 5: The channel inside the anti-icing valve 2 is coaxially connected to the air bleed pipe 3. The inlet end of the air bleed pipe 3 is inserted into the outlet end of the anti-icing valve 2 and can slide axially relative to the anti-icing valve 2. The sleeve assembly 5 includes a connecting sleeve 51 and a compression spring 52. The outer wall of the outlet end of the anti-icing valve 2 is provided with a first stopper 22, and the outer wall of the air bleed pipe 3 is provided with a second stopper 31. A limiting cavity is formed between the first stopper 22 and the second stopper 31. The connecting sleeve 51 is used to be sleeved on the connection between the anti-icing valve 2 and the air bleed pipe 3 and to shield and seal the connection. The first end of the connecting sleeve 51 abuts the side of the first stopper 22 toward the second stopper 31, and the compression spring 52 is pressed between the second end of the connecting sleeve 51 and the second stopper 31. The compression spring 52 is used to provide an elastic force to push the connecting sleeve 51 to press against the first stopper 22.

[0026] The "anti-icing valve 2" here means a key component in the aircraft engine anti-icing system connected to the compressor casing 1, which is mainly used to control the pressure and flow of hot air drawn out of the aircraft engine to prevent the aircraft engine air intake and other parts from icing in low temperature environments. Usually, an electric control valve 21 is provided in the anti-icing valve 2. The pilot can control the switch of the electric control valve 21 through the engine anti-icing control switch located in the cockpit, that is, control the pressure and flow of the anti-icing valve 2 bleed air. When anti-icing is not needed, closing the anti-icing valve 2 to cut off the anti-icing bleed air can save engine power. Usually, in order to avoid failures due to electrical circuit bleed air, the anti-icing valve 2 is designed to remain in the open position when the power is off, so as to improve the reliability of engine anti-icing.

[0027] Here, the meanings of "first stopper 22" and "second stopper 31" refer to structures provided on the outer wall of the outlet end of the anti-icing valve 2 and the outer wall of the inlet end of the air bleed pipe 3, respectively. In some embodiments, the first stopper 22 and the second stopper 31 are both annular plate-shaped structures, and the limiting cavity formed between the first stopper 22 and the second stopper 31 can limit the position of the sleeve assembly 5. The first stopper 22 abuts the connecting sleeve 51, and the second stopper 31 abuts the compression spring 52, and the compression spring 52 presses the connecting sleeve 51. Of course, in other embodiments, the connecting sleeve 51 and the compression spring 52 can also be interchanged, so long as the connecting sleeve 51 continuously seals the connection between the anti-icing valve 2 and the air bleed pipe 3.

[0028] The present application connects the bleed duct 3 with the anti-icing valve 2 to form a linear bleed passage, connecting the compressor casing 1 and the intake casing 4 via the bleed passage. This achieves the shortest possible connection path, avoids the use of long or curved pipes, and helps reduce overall weight. The inlet of the bleed duct 3 and the anti-icing valve 2 are connected in an axially slidable manner, with a small radial gap. The connection between the bleed duct 3 and the anti-icing valve 2 is sealed by a sleeve assembly 5. A connecting sleeve 51 seals the connection between the bleed duct 3 and the anti-icing valve 2. The connecting sleeve 51 is installed in a positional manner, which is compressed and limited by a compression spring 52 and a first stopper 22 on the outer wall of the anti-icing valve 2 and a second stopper 31 on the outer wall of the bleed duct 3. This makes assembly and disassembly very convenient, and the sealing effect at the connection between the bleed duct 3 and the anti-icing valve 2 is maintained even when the bleed duct 3 slides relative to the outlet of the anti-icing valve 2, thereby reducing gas leakage. The present application adopts a small radial clearance fit between the anti-icing valve 2 and the air duct 3, and allows for relative axial sliding, thereby compensating for axial and radial dimensional deviations, effectively coping with the larger thermal stress of the anti-icing pipeline device, and greatly reducing the difficulty of assembly, thereby effectively improving the overall maintainability of the anti-icing air duct system, and helping to increase the overall life of the anti-icing air duct device.

[0029] Preferably, please refer to Figure 1 and Figure 4As shown, the sleeve assembly 5 also includes a first sealing ring 53, a sealing cavity is opened on the inner side of the connecting sleeve 51, and limiting grooves 511 are opened on the opposite sides of the sealing cavity. The limiting grooves 511 are used to limit the first sealing ring 53. The first sealing ring 53 is used to seal the connection between the connecting sleeve 51 and the anti-icing valve 2 and the connection between the connecting sleeve 51 and the air bleed pipe 3 respectively.

[0030] It is understood that a sealing cavity is defined on the inner side of the connecting sleeve 51, that is, on the side facing the axis of the air duct 3. This sealing cavity seals the connection between the air duct 3 and the anti-icing valve 2. Furthermore, the connections between the connecting sleeve 51, the air duct 3, and the anti-icing valve 2 are reinforced by first sealing rings 53. The first sealing ring 53 is positioned and fixed by a retaining groove 511 within the sealing cavity to ensure that the first sealing ring 53 is fixed in place.

[0031] Optionally, the connecting sleeve 51 is made of rubber material, which can improve the elasticity and ductility of the connecting sleeve 51, so as to cooperate with the compression spring 52 to press the connecting sleeve 51 to ensure the stability of the installation of the connecting sleeve 51, and the end faces of the connecting sleeve 51 can respectively abut and press the outer walls of the anti-icing valve 2 and the air bleed pipe 3 to achieve a sealing effect, and cooperate with the reinforced sealing of the first sealing ring 53 to effectively reduce gas leakage and ensure the efficiency of the air bleed anti-icing.

[0032] In this preferred embodiment, the first sealing ring 53 is a U-shaped or V-shaped structure made of elastic material. The first sealing ring 53 is elastically pressed in the limiting groove 511, and during the process of the connecting sleeve 51 being heated and deformed, the first sealing ring 53 is squeezed by the inner wall of the limiting groove 511 to tightly seal the connection between the connecting sleeve 51 and the anti-icing valve 2 and the air bleed pipe 3.

[0033] It can be understood that the first sealing ring 53 adopts a U-shaped or V-shaped structure and is elastically clamped in the limiting groove 511. Specifically, the outer end of the side wall on one side of the first sealing ring 53 abuts the bottom inner wall of the limiting groove 511, and the outer end of the side wall on the other side of the first sealing ring 53 abuts the outer wall of the anti-icing valve 2 or the air duct 3. During the process of heat deformation of the connecting sleeve 51, the first sealing ring 53 can be squeezed through the inner wall of the limiting groove 511 to strengthen the sealing of the connection between the connecting sleeve 51 and the anti-icing valve 2 and the connection between the connecting sleeve 51 and the air duct 3. The linkage deformation cooperation between the limiting groove 511 and the first sealing ring 53 ensures that the first sealing ring 53 always maintains a sealing effect.

[0034] Optionally, the first sealing ring 53 is a triangular structure made of elastic material, and can also be elastically pressed and clamped in the limiting groove 511 to achieve the effect of being squeezed by the inner wall of the limiting groove 511 to enhance the sealing.

[0035] Preferably, please refer to Figure 1 and Figure 4As shown, the air bleed pipe 3 includes a main body section and a support section 33 provided at the inlet end of the main body section. The diameter of the support section 33 is smaller than that of the main body section. The support section 33 is used to be slidably inserted into the outlet end of the anti-icing valve 2.

[0036] It can be understood that the air bleed pipe 3 is inserted into the anti-icing valve 2 through a support section 33 with a smaller diameter at the outlet end, so as to realize a straight-line connection between the air bleed pipe 3 and the anti-icing valve 2, thereby making the anti-icing air bleed pipeline channel as a whole in a straight line, realizing the arrangement of the anti-icing air bleed channel on the shortest path, which is beneficial to controlling the overall weight of the anti-icing air bleed pipeline device, reducing the span of the pipeline, and improving the air bleed rate and efficiency.

[0037] In this preferred embodiment, the support section 33 is connected to the air duct 3 via a connecting ring 32 , and the cross-section of the connecting ring 32 is a conical structure, that is, the diameter of the end of the connecting ring 32 connected to the air duct 3 is larger than the diameter of the end connected to the support section 33 .

[0038] It should be noted that, by providing a connecting ring 32 on the air bleed pipe 3 and connecting the connecting ring 32 to the support section 33, the support section 33 can have a certain elasticity or ductility to achieve a small gap fit with the outlet of the anti-icing valve 2, and can provide a certain radial compensation to better cope with greater thermal stress.

[0039] Preferably, please refer to Figure 1 and Figure 3 As shown, the inlet end of the anti-icing valve 2 is provided with a second connecting boss 23, which is used to abut and cooperate with the first connecting boss 11 preset at the connecting port of the compressor casing 1. The aircraft engine anti-icing pipeline device also includes a clamp 7, which is used to cover the first connecting boss 11 and the second connecting boss 23 to lock and limit the two.

[0040] It is understood that the first connecting boss 11 of the compressor casing 1 engages with the second connecting boss 23 at the inlet end of the anti-icing valve 2, and the clamp 7 holds the first and second connecting bosses 11, 23 in place, thereby achieving a secure connection and sealing between the first and second connecting bosses 11, 23. The clamp 7 only needs to be tightened with a single locking bolt, significantly simplifying assembly and disassembly of the compressor casing 1 and the anti-icing valve 2.

[0041] It should be noted that the first connecting boss 11 and the second connecting boss 23 are both a circle of raised platform structures. The sealing surfaces of the first connecting boss 11 and the second connecting boss 23 are mainly in the form of plane sealing, and the clamp 7 can clamp and shield the outer ring connection between the first connecting boss 11 and the second connecting boss 23.

[0042] Optionally, a circle of rubber sealing gasket is provided on the inner wall of the clamp 7, which can strengthen the sealing of the connection between the first connecting boss 11 and the second connecting boss 23, while reducing the phenomenon of the clamp 7 causing damage to the first connecting boss 11 and the second connecting boss 23.

[0043] In this preferred embodiment, please refer to Figure 3 As shown, the aircraft engine anti-icing pipeline device also includes a second sealing ring 8. A sealing groove 231 is opened on the second connecting boss 23. The second sealing ring 8 is installed in the sealing groove 231. The second sealing ring 8 is used to seal the sealing surface between the second connecting boss 23 and the first connecting boss 11.

[0044] It can be understood that since the sealing surface of the first connecting boss 11 and the second connecting boss 23 is mainly sealed in the form of a plane, in order to strengthen the sealing effect of the connecting surface of the first connecting boss 11 and the second connecting boss 23, a sealing groove 231 is opened on the side of the second connecting boss 23 facing the first connecting boss 11, and a second sealing ring 8 is arranged in the sealing groove 231. The second sealing ring 8 can effectively improve the sealing effect of the sealing surface of the first connecting boss 11 and the second connecting boss 23, thereby ensuring the sealing effect of the connection points of the anti-icing air duct and reducing gas leakage.

[0045] In other embodiments, the sealing groove 231 is formed on a side of the first connecting protrusion 11 opposite to the second connecting protrusion 23 , which can achieve the same effect.

[0046] In this preferred embodiment, please refer to Figure 2 As shown, a boss-shaped connecting platform 232 is provided on the second connecting boss 23 , and the connecting platform 232 is used to be snapped into the connecting groove 111 preset on the first connecting boss 11 .

[0047] It can be understood that the first connecting boss 11 and the second connecting boss 23 are clamped in the form of a concave-convex joint, wherein the boss-shaped connecting platform 232 is clamped into the connecting groove 111, and radial and axial positioning can be achieved through the clamping form of the concave-convex joint, which facilitates the connection and assembly of the anti-icing valve 2 and the compressor casing 1, and can also change the form of full-plane sealing, thereby improving the sealing effect of the first connecting boss 11 and the second connecting boss 23.

[0048] It should be noted that when the connecting platform 232 is inserted into the connecting groove 111 , the radial fit adopts a small clearance fit, which can make positioning and disassembly more convenient and reduce the occurrence of sticking and other phenomena.

[0049] Preferably, please refer to Figure 2As shown, the aircraft engine anti-icing pipeline device also includes a support member 6 for installation on the outer wall of the compressor casing 1. The support member 6 is connected to the anti-icing valve 2 and supports and limits the anti-icing valve 2.

[0050] It is understandable that due to the large weight of the anti-icing valve 2, in order to improve the installation stability of the anti-icing valve 2 and reduce the impact on components such as the air bleed pipe 3, a support member 6 is provided on the outer wall of the compressor casing 1. The support member 6 acts as a bracket, thereby strengthening the support connection of the anti-icing valve 2.

[0051] In some embodiments, the support member 6 is a plate-shaped structure, and the support member 6 is connected to the anti-icing valve 2 via a connecting bolt, and the anti-icing valve 2 can be easily disassembled and assembled by removing the connecting bolt.

[0052] Preferably, please refer to Figure 1 and Figure 5 As shown, the aircraft engine anti-icing pipeline device also includes a connecting flange 9 provided at the outlet end of the air bleed pipe 3 and used to connect to the air intake casing 4. A locking member 91 is provided in the flange hole of the connecting flange 9. The locking member 91 is used to lock the connecting flange 9. A locking platform is provided at the driving end of the locking member 91. There is a gap of 0.4-0.6 mm between the locking platform and the end face of the flange hole.

[0053] It can be understood that by connecting the outlet of the air duct 3 to the air intake casing 4 through the connecting flange 9, flange sealing can be achieved, and there is a gap of 0.4-0.6mm between the locking platform at the top of the locking piece 91 and the end face of the flange hole, which can be used to compensate for the position deviation of the anti-icing air duct interface between the compressor and the air intake casing 4. That is, when there is a deviation in the radial dimension during assembly or operation, the radial dimension deviation is compensated by the 0.4-0.6mm gap between the flange hole of the connecting flange 9 of the outlet of the air duct 3 and the locking piece 91, thereby reducing additional assembly stress or thermal stress caused by the cumulative processing deviation of part dimensions or thermal deformation during engine operation.

[0054] Optionally, the locking member 91 is a flange bolt. Using a standard part facilitates procurement, maintenance, and replacement. The flange bolt engages the flange hole to connect the air duct 3 to the intake casing 4. A clearance of 0.4-0.6 mm is provided between the top bolt head of the flange bolt and the end face of the flange hole. A flat gasket is provided on the flange surface of the connecting flange 9 to enhance the flange sealing effect.

[0055] According to another aspect of the present application, an aircraft engine is also provided, which includes the above-mentioned aircraft engine anti-icing pipeline device.

[0056] The aircraft engine of the present application also has the above-mentioned beneficial effects. It also includes an anti-icing air bleed pipe system for the aircraft engine, which can be conveniently installed with the shortest path under the condition of small axial space, and has the advantages of simple layout, light weight, and the ability to effectively cope with large thermal stress. The anti-icing air is drawn out from the compressor outlet, and passes through a pipe system composed of components such as the compressor casing 1, the anti-icing valve 2, and the air bleed pipe 3, and directly enters the air intake casing 4 along a straight line to provide the anti-icing part. The anti-icing air bleed pipe path is the shortest; the anti-icing valve 2 is electrically controlled, and the electric control valve 21 on the anti-icing air bleed flow path is controlled by an electric signal to realize the opening / closing of the anti-icing air bleed; considering that the anti-icing valve 2 is heavy, a support 6 is provided under the compressor casing 1 as a bracket for the anti-icing valve 2 to provide reinforced support for the anti-icing valve 2; the inlet of the anti-icing valve 2 is connected and locked with the compressor casing 1 by a clamp 7, and the two are radially and axially positioned using a concave-convex joint form of a first connecting boss 11 and a second connecting boss 23, wherein the radial fit A small clearance fit is adopted, which makes disassembly and assembly more convenient, and a sealing groove is provided between the first connecting boss 11 and the second connecting boss 23, and a second sealing ring 8 is placed to strengthen the sealing; the outlet of the anti-icing valve 2 is connected to the air bleed pipe 3 through the sleeve assembly 5, and the air bleed pipe 3 is inserted into the outlet of the anti-icing valve 2 to provide support for the outlet of the anti-icing valve 2, and the connection between the two adopts a small clearance fit in the radial direction, and can slide relative to each other without unlimited axial position, so as to realize compensation of axial dimensional deviation; the outlet of the air bleed pipe 3 is connected to the air intake casing 4 by a connecting flange 9, and the flange is sealed with a flat sealing gasket, and there is a gap of 0.4-0.6mm between the locking platform at the top of the locking piece 91 and the flange hole, which can be used to compensate for the position deviation of the anti-icing air bleed interface between the compressor and the air intake casing 4.

[0057] In summary, the anti-icing air bleed pipe device of the present application compensates for significant radial dimensional deviations during assembly or operation by providing a 0.4-0.6mm gap between the flange hole of the connecting flange 9 at the outlet of the bleed pipe 3 and the locking member 91. Furthermore, the clamping connection between the inlet of the bleed pipe 3 and the outlet of the anti-icing valve 2 also allows for a certain degree of clearance compensation via the support section 33. Axial dimensional deviations are compensated for by the sleeve-type connection structure between the bleed pipe 3 and the anti-icing valve 2. The device is extremely easy to assemble and disassemble, and the compensation structure is well-designed, eliminating additional assembly or thermal stresses due to cumulative machining deviations in component dimensions or thermal deformation during engine operation.

[0058] The anti-icing air bleed pipe system of the present application can be completely disassembled, making the disassembly process much simpler and faster. During use, a specific disassembly procedure involves removing the clamp 7 between the anti-icing valve 2 and the compressor (only one bolt locking the clamp 7 is required), removing the support 6 between the anti-icing valve 2 and the compressor casing 1 (only one mounting bolt is required), and removing the locking member 91 (i.e., two flange bolts) between the anti-icing air bleed pipe 3 and the intake casing 4. A total of only four bolts are required to completely disassemble the anti-icing pipe system. Reassembly is the reverse of the disassembly process. The overall operation is extremely convenient and quick, facilitating the disassembly, assembly, and maintenance of the entire anti-icing pipe system.

[0059] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements that are inherent to such process, method, article or apparatus.

[0060] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression, there are objectively infinite specific structures. For ordinary technicians in this technical field, without departing from the principles of this application, they can make several improvements, modifications or changes, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as protected by this application.

Claims

1. An anti-icing piping device for an aircraft engine, comprising an air bleed pipe (3) for connecting a compressor casing (1) with an air intake casing (4) to bleed air from the air intake casing (4), and an anti-icing valve (2) provided on the compressor casing (1), wherein the air bleed pipe (3) is connected to the compressor casing (1) through the anti-icing valve (2), and is characterized in that: The aircraft engine anti-icing pipeline device also includes a sleeve assembly (5): The passage in the anti-icing valve (2) is coaxially connected to the air bleed pipe (3), the inlet end of the air bleed pipe (3) is inserted into the outlet end of the anti-icing valve (2) and can slide axially relative to the anti-icing valve (2), the sleeve assembly (5) includes a connecting sleeve (51) and a compression spring (52), the outer wall of the outlet end of the anti-icing valve (2) is provided with a first stopper (22), the outer wall of the air bleed pipe (3) is provided with a second stopper (31), and the first stopper (22) and the second stopper (31) are connected. A limiting cavity is formed between the connecting sleeve (51), the connecting sleeve (51) is used to be sleeved on the connection between the anti-icing valve (2) and the air bleed pipe (3) and to shield and seal the connection, the first end of the connecting sleeve (51) abuts against the side of the first stopper (22) toward the second stopper (31), the compression spring (52) is pressed between the second end of the connecting sleeve (51) and the second stopper (31), and the compression spring (52) is used to provide an elastic force to push the connecting sleeve (51) to press against the first stopper (22).

2. The aircraft engine anti-icing pipeline device according to claim 1, characterized in that: The sleeve assembly (5) further includes a first sealing ring (53), a sealing cavity is provided on the inner side of the connecting sleeve (51), and limiting grooves (511) are provided on opposite sides of the sealing cavity. The limiting grooves (511) are used to limit the first sealing ring (53), and the first sealing ring (53) is used to seal the connection between the connecting sleeve (51) and the anti-icing valve (2) and the connection between the connecting sleeve (51) and the air bleed pipe (3).

3. The aircraft engine anti-icing pipeline device according to claim 2, characterized in that: The first sealing ring (53) is a U-shaped or V-shaped structure made of elastic material. The first sealing ring (53) is elastically pressed in the limiting groove (511). When the connecting sleeve (51) is deformed by heat, the inner wall of the limiting groove (511) squeezes the first sealing ring (53) to press the connection between the sealing connecting sleeve (51) and the anti-icing valve (2) and the air bleed pipe (3).

4. The aircraft engine anti-icing pipeline device according to claim 1, characterized in that: The air bleed pipe (3) comprises a main body section and a support section (33) provided at the inlet end of the main body section. The diameter of the support section (33) is smaller than the diameter of the main body section. The support section (33) is used for slidingly inserting into the outlet end of the anti-icing valve (2).

5. The aircraft engine anti-icing pipeline device according to claim 1, characterized in that: A second connecting boss (23) is provided at the inlet end of the anti-icing valve (2), and the second connecting boss (23) is used to abut and cooperate with a first connecting boss (11) preset at the connecting port of the compressor casing (1). The aircraft engine anti-icing pipeline device also includes a clamp (7), and the clamp (7) is used to cover the first connecting boss (11) and the second connecting boss (23) to lock and limit the two.

6. The aircraft engine anti-icing pipeline device according to claim 5, characterized in that: The aircraft engine anti-icing pipeline device also includes a second sealing ring (8), a sealing groove (231) is provided on the second connecting boss (23), the second sealing ring (8) is installed in the sealing groove (231), and the second sealing ring (8) is used to seal the sealing surface between the second connecting boss (23) and the first connecting boss (11).

7. The aircraft engine anti-icing pipeline device according to claim 5, characterized in that: A boss-shaped connecting platform (232) is provided on the second connecting boss (23), and the connecting platform (232) is used for snapping into a preset connecting groove (111) of the first connecting boss (11).

8. The aircraft engine anti-icing pipeline device according to claim 1, characterized in that: The aircraft engine anti-icing pipeline device also includes a support member (6) for being installed on the outer wall of the compressor casing (1); the support member (6) is connected to the anti-icing valve (2) and supports and limits the anti-icing valve (2).

9. The aircraft engine anti-icing pipeline device according to claim 1, characterized in that: The aircraft engine anti-icing pipeline device also includes a connecting flange (9) provided at the outlet end of the air bleed pipe (3) and used for connecting to the air intake casing (4), a locking member (91) is provided in the flange hole of the connecting flange (9), the locking member (91) is used for locking the connecting flange (9), a locking platform is provided at the driving end of the locking member (91), and a gap of 0.4-0.6 mm is provided between the locking platform and the end face of the flange hole.

10. An aircraft engine, characterized in that: The invention comprises an aircraft engine anti-icing pipeline device according to any one of claims 1 to 9.

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