Engine intake bypass device

Abstract

The present application belongs to the technical field of helicopter air intake system design, and particularly relates to an engine air intake bypass device. The device includes a bypass door assembly, a support frame assembly, and a bypass door drive assembly. The support frame assembly is fixed between the engine air intake port and the sand control assembly. A lateral airflow channel is formed between the airflow outlet port of the sand control device and the engine air intake port. External gas enters the engine air intake through the lateral airflow channel and the engine air intake port in turn to form a bypass air intake. The bypass door assembly includes a bypass door body with two ends connected and a cylindrical structure. The bypass door body is supported and slidably arranged on the linear guide rail support of the support frame assembly, which is used to close or open the lateral airflow channel. The engine air intake bypass device of the present application can be installed, disassembled, debugged and maintained independently as a whole, effectively ensuring the bypass space, reducing the flow resistance during bypass air intake, improving the anti-bird strike and anti-foreign matter performance, and reducing the anti-icing power consumption of the entire system.

Description

Technical Field

[0001] The present application belongs to the technical field of helicopter air intake design, and in particular relates to an engine air intake bypass device. Background Art

[0002] The air intake assembly is an important part of the helicopter's air intake system. By installing an air intake filter at the entrance of the helicopter's engine air intake, large particles of foreign matter can be prevented from entering the engine during flight. By installing a sand prevention device, sand and dust in the air can be filtered to ensure that the air entering the engine is clean.

[0003] After installing the air intake filter and sand prevention device, due to the lack of heating and anti-icing function, when flying for a long time in an icy environment, it will gradually freeze and clog, causing excessive engine power loss or even shutdown. To this end, the Chinese invention patent with application number 201910428787.4 provides a heated mesh grille that can block large foreign particles from entering the engine, while having anti-bird strike safety and heating and anti-icing functions. After the engine is equipped with a sand prevention device, a bypass device can be set between the sand prevention device and the air intake duct to achieve air intake bypass. When the aircraft takes off or flies at high altitude, the bypass device is opened to assist the air intake, thereby increasing the total pressure recovery coefficient of the air intake duct. The bypass intake is assisted by the air intake grille, which is heated to prevent icing, thus solving the problem of preventing foreign objects from entering the engine and preventing ice from clogging the air intake after the bypass is opened.

[0004] Although the prior art provides the principle of bypass air intake and a schematic bypass air intake device, it lacks specific engineering implementation details: on the one hand, the air intake protection grille and the bypass mechanism are isolated from each other, and no organic integration optimization has been carried out. The weight and power consumption are large, the overall efficiency is low, the process implementation is difficult, and how to disassemble, install, use and maintain is not considered. On the other hand, the existing bypass device lacks a duct closing sliding mode and a supporting structure, lacks consideration of structural strength and the impact on the internal wind resistance of the sand control device. At the same time, the bypass mechanism of the prior art adopts a single motor and a single turbine worm drive configuration, lacks electrical and mechanical safety backup functions, and the drive motor and the support structure are placed in the central airflow concentration area of ​​the sand control device, which has the disadvantages of high weight cost and high wind resistance. Summary of the invention

[0005] In order to solve at least one of the above-mentioned technical problems, the present application provides an engine intake bypass device, including a bypass door assembly, a support frame assembly and a bypass door drive assembly, the support frame assembly includes a linear guide rail support, an intake duct lateral support assembly, an intermediate lateral support connection assembly and a sand control end lateral support member, the linear guide rail support member is fixed to the intermediate lateral support connection assembly, one end of the linear guide rail support member extends toward the intake duct, and its end head is connected to the intake duct lateral support assembly, and the other end extends toward the direction of the sand control device arranged outside the engine intake duct, and its end head is connected to the sand control end lateral support member, the intake duct lateral support member An air intake inlet for air intake is arranged in the middle of the support assembly, and a lateral airflow channel is formed between the intermediate lateral support connection assembly and the lateral support assembly of the air intake duct, and external gas enters the engine air intake duct through the lateral airflow channel and the air intake inlet in turn to form a bypass air intake, and the bypass door assembly includes a bypass door body with openings at both ends and a cylindrical structure, and the bypass door body is supported and slidably arranged on the linear guide rail support member for closing or opening the lateral airflow channel, and the bypass door drive assembly is fixed on the lateral support member at the sand control end of the support frame assembly, and is used to drive the bypass door body to slide.

[0006] Preferably, the intermediate lateral support connection assembly is detachably fixed to the airflow outlet end of the sand control device, and the air inlet duct lateral support assembly is non-fixedly elastically abutted against the air inlet duct.

[0007] Preferably, the linear guide support member includes a main support body and an integrated linear guide extending along the axial direction of the main support body, the outside of the bypass door body is provided with a linear bearing slider distributed along the axial direction, the integrated linear guide is adapted to be installed in the axial channel defined by the linear bearing slider, the bypass door body is also provided with a turbine support and a worm cover, a rotatable worm is adapted to be installed in the worm cover, the rotatable worm is driven to rotate by the bypass door drive assembly installed on the sand control end transverse support member, and interacts with the turbine support, thereby driving the bypass door body to move along the axial direction of the linear guide support member.

[0008] Preferably, the bypass door drive assembly includes two independently operable drive motors, which are connected by a linkage synchronization shaft to achieve mechanical synchronization, and each drive motor is connected to a reduction device, which is fixed on a reduction device mounting platform provided on the sand control end lateral support.

[0009] Preferably, the transverse support member at the sand control end is further provided with a detachable support joint extending in the radial direction on its outer ring edge, and the other end of the support joint abuts against the inner wall of the sand control device.

[0010] Preferably, an anti-icing and anti-foreign matter net is provided at the air inlet of the air inlet duct lateral support assembly, and the anti-icing and anti-foreign matter net is connected to the structural body of the air inlet duct lateral support assembly through a connecting frame, and is electrically connected to the power supply device through the connecting frame.

[0011] Preferably, a notch is provided in the middle of the anti-icing and anti-foreign matter net to accommodate an engine air intake straightening cone.

[0012] Preferably, the anti-icing and anti-foreign-object net is configured as an arc-shaped or conical structure with a bulge in the middle.

[0013] Preferably, a through-hole connecting boss is provided on the structural body of the air inlet duct lateral support assembly, and the through-hole connecting boss is detachably connected to the linear guide rail support member.

[0014] Preferably, an inlet end face recess is provided outside the inlet lip at the engine inlet port, the structural body of the inlet duct lateral support assembly is located in the inlet end face recess, and when the inlet duct lateral support assembly is placed in the inlet end face recess, its end face is not higher than the end face at the inlet port.

[0015] Preferably, the airflow outlet end of the sand control device is provided with an end face recess, the middle transverse support connecting assembly is adapted to be installed in the end face recess, and is connected to the sand control device through mounting bolts, and the bolt head of the mounting bolt is lower than the end face of the airflow outlet end of the sand control device.

[0016] The engine intake bypass device of the present application can be installed and disassembled as a whole and can be debugged and maintained independently. The bypass door drive assembly with dual power linkage improves the safety margin of opening and closing the bypass door. The present application integrates the bypass device with the intake duct and the anti-sand device structure, and integrates an anti-icing and anti-foreign matter net, which effectively guarantees the bypass space, reduces the flow resistance during bypass intake, improves the anti-bird strike and anti-foreign matter performance, and reduces the anti-icing power consumption of the entire system. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the helicopter engine intake system structure.

[0018] Figure 2 It is a bypass opening schematic diagram of a preferred embodiment of the engine intake bypass device of the present application.

[0019] Figure 3 It is a bypass closing schematic diagram of a preferred embodiment of the engine intake bypass device of the present application.

[0020] Figure 4 It is a schematic diagram of the connection between the support frame assembly, the sand control device and the air inlet duct.

[0021] Figure 5Schematic diagram of the bypass door assembly structure.

[0022] Figure 6 It is a schematic diagram of the support frame assembly structure.

[0023] Figure 7 It is a schematic diagram of the structure of the linear guide support.

[0024] Figure 8 It is a schematic diagram of the structure of the air intake duct lateral support assembly.

[0025] Fig. 9 yes Figure 8 A-direction diagram of the illustrated embodiment.

[0026] Fig.10 It is a schematic diagram of the structure of the intermediate transverse support connection component.

[0027] Fig.11 yes Fig.10 Schematic diagram of the intermediate lateral support structure of the illustrated embodiment.

[0028] Fig.12 It is a schematic diagram of the structure of the lateral support member at the sand control end.

[0029] Fig.13 yes Fig.12 A B-direction view of the illustrated embodiment.

[0030] Fig.14 It is a schematic diagram of the bypass door drive assembly structure.

[0031] Fig.15 It is a schematic diagram of the structural integration of the air intake lateral support assembly and the air intake.

[0032] Fig.16 It is a schematic diagram of the structural integration of the intermediate transverse support connection assembly and the sand control device.

[0033] Fig.17 It is a schematic diagram of the fusion configuration of the anti-icing net and the inlet straightening cone structure of the present application.

[0034] Fig.18 It is a schematic diagram of the configuration of the arc-shaped anti-icing net at the air inlet of the present application.

[0035] Fig.19 It is a schematic diagram of the bypass annular anti-icing net configuration of this application.

[0036] Fig. 20 It is a schematic diagram of the structure of the lateral support member of the sand control end with a support joint.

[0037] Among them, 1-inlet duct, 101-inlet duct lip, 102-inlet duct end face depression, 103-inlet duct O-ring, 104-inlet duct outer plane, 105-inlet duct end lateral support assembly installation plane, 106-inlet duct lip front plane, 107-inlet straightening cone;

[0038] 2-sand prevention device, 201-end face depression, 202-mounting bolt;

[0039] 3-Intake duct bypass device;

[0040] 10-bypass door assembly, 11-bypass door body, 12-bypass sealing rib, 13-linear bearing slider, 14-turbine support, 15-worm cover, 16-end O-type seal;

[0041] 20-support frame assembly, 21-linear guide support, 211-main support body, 212-integrated linear guide, 213-O-ring through hole, 22-inlet duct lateral support assembly, 221-structural body, 222-anti-icing and anti-foreign matter net, 223-connecting frame, 224-inlet duct support member reinforcement flange, 225-through hole connection boss, 23-intermediate lateral support connection assembly, 231-intermediate lateral support structure, 232-O-ring, 234-reinforced flange, 235-through hole connection semi-boss, 236-mounting hole, 24-sand control end lateral support, 241-blind hole boss, 242-speed reduction device mounting platform, 243-worm through hole, 244-sand control support member reinforcement flange, 245-support joint;

[0042] 30-bypass door driving assembly, 31-driving motor, 32-reduction device, 33-rotatable worm, 34-linked synchronous shaft. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0044] The present application provides an engine intake bypass device, which is mainly installed at the inlet of the engine intake duct, such as Figure 1 As shown, the helicopter engine air intake system mainly includes an air intake duct 1, a sand prevention device 2 and an engine air intake bypass device 3. The engine air intake bypass device 3 is axially arranged at the entrance of the air intake duct 1. An air intake bypass is formed between the engine air intake bypass device 3 and the air intake duct. The air intake bypass can be opened and closed by the engine air intake bypass device 3. The structure of the engine air intake bypass device 3 is shown in FIG. Figure 2 As shown, combined Figure 1 and Figure 2 When the engine air intake bypass device 3 is closed, the outside air enters the sand control device 2 through the through hole on the sand control device 2, and then flows into the entrance of the air intake duct 1, and enters the air intake duct 1, and the sand control device 2 achieves the effect of preventing sand and dust. When the aircraft or helicopter is flying at high altitude, or when taxiing on the ground, in order to improve the total pressure recovery coefficient of the air intake duct, the engine air intake bypass device 3 is opened, and the outside air flows through the engine air intake bypass device 3 from the side of the air intake duct entrance to the air intake duct entrance, and then flows into the air intake duct 1, realizing bypass intake.

[0045] The engine intake bypass device provided by the present application is as follows: Figure 2 As shown, it mainly includes a bypass door assembly 10, a support frame assembly 20 and a bypass door drive assembly 30. The support frame assembly 20 plays a main supporting role and is supported by multiple support rods. Specifically, the support frame assembly 20 includes a linear guide rail support member 21 and an air inlet duct lateral support assembly 22, an intermediate lateral support connecting assembly 23 and a sand control end lateral support member 24. One end face of the air inlet duct lateral support assembly 22 abuts against the engine air inlet duct 1 port, and an air inlet inlet for air intake is provided in the middle. The linear guide rail support member 21 is fixed in a through-hole connecting boss 225 of the air inlet duct lateral support assembly 22, and extends toward the direction of the sand control device 2 provided outside the engine air inlet duct, and its end head is connected to the sand control end lateral support member 24. In an alternative embodiment, one end face of the air inlet duct lateral support assembly 22 is fixed at the engine air inlet duct 1 port, and the linear guide rail support member 21 is fixed in a through-hole connecting boss 225 of the air inlet duct lateral support assembly 22, and extends toward the direction of the sand control device 2 provided outside the engine air inlet duct, and its end head is connected to the sand control end lateral support member 24. In an alternative embodiment, one end face of the air inlet duct lateral support assembly 22 is fixed at the engine air inlet duct 1 port, and the linear The guide rail support 21 can also be used to support the sand control device 2. A lateral airflow channel is formed between the intermediate lateral support connection assembly 23 and the air intake duct lateral support assembly 22. External gas enters the engine air intake duct through the lateral airflow channel and the air intake inlet in turn to form a bypass air intake. The bypass door assembly 10 includes a bypass door body 11 with openings at both ends and a cylindrical structure. The bypass door body 11 is supported and slidably arranged on the linear guide rail support 21 to close or open the lateral airflow channel. The bypass door drive assembly 30 is fixed on the sand control end lateral support 24 of the support frame assembly 20 and is used to drive the bypass door body 11 to slide. The bypass door body 11 can thus move axially along the linear guide rail support 21. When the bypass door assembly 10 moves close to the sand control device 2, the air intake bypass is opened. Otherwise, Figure 3As shown, when the bypass door assembly 10 moves close to the intake passage 1, the intake bypass is closed.

[0046] As described above, the sand control device 2 is usually disposed at one end of the support frame assembly 20 away from the air inlet 1, so as to form an air intake bypass with the air inlet 1. For example, the end of the sand control device 2 is fixed to one end of the support frame assembly 20. In an alternative embodiment, the end of the sand control device 2 can also be fixed to other positions of the support frame assembly 20, as long as a certain distance is ensured between the end of the sand control device 2 and the air inlet 1 to ensure bypass air intake. For example, the support frame assembly 20 is provided with an annular connector in the middle, and the sand control device 2 is fixed to the connector. The portion of the support frame assembly 20 above the annular connector extends into the interior of the sand control device 2 to provide a more reliable connection method. Specifically, as Figure 4 and Figure 6 In the optional embodiment shown, the support frame assembly 20 also includes an intermediate lateral support connection assembly 23 and a sand control end lateral support member 24. The sand control end lateral support member 24 is arranged at the other end of the linear guide rail support member 21 relative to the air inlet duct lateral support assembly 22, and the intermediate lateral support connection assembly 23 is arranged in the middle of the linear guide rail support member 21. The sand control device 2 extends from one end of the sand control end lateral support member 24 of the support frame assembly 20 and is fixed on the intermediate lateral support connection assembly 23.

[0047] In the present application, the bypass door body 11 slides on the linear guide support 21 in a variety of ways, such as the linear guide support 21 provides a slide rail, the bypass door body 11 provides a slider, or the bypass door body 11 provides a slide rail, and the linear guide support 21 itself serves as a slider. In a specific embodiment, Figure 5-Figure 7 As shown, Figure 5 2 is a schematic structural diagram of a bypass door assembly 10 . The bypass door body 11 of the present application is provided with a linear bearing slider 13 distributed along the axial direction on the outside. The integrated linear guide rail 212 is adapted to be installed in the axial channel defined by the linear bearing slider 13 . Figure 6 Schematic diagram of the structure of the support frame assembly 20 , the support frame assembly 20 includes a linear guide rail support member 21 , an inlet end lateral support assembly 22 , an intermediate lateral support connection assembly 23 and a sand control end lateral support member 24 . Figure 7 It is a structural schematic diagram of a linear guide support 21, wherein the linear guide support 21 includes a main support body 211 and an integrated linear guide 212 extending along the axial direction of the main support body 211, and the linear guide support 21 also includes an O-ring through hole 213 for installing the O-ring on the intermediate lateral support connection assembly 23.

[0048] The bypass door body 11 is connected to the integrated linear guide rail 212 on the linear guide rail support member 21 through the linear bearing slider 13, so as to realize effective support and sliding of the bypass door. When the bypass door is closed, the end O-shaped seal 16 of the bypass door assembly 10 and the transverse support member 22 at the inlet end form an air intake seal.

[0049] refer to Figure 5 The bypass door assembly 10 also includes a bypass sealing rib 12, which is arranged at one end of the bypass door body 11 and is arranged on the outside of the bypass door body 11 in the form of a flange. When the bypass door is closed, the bypass sealing rib 12 can fit on the middle transverse support connection assembly 23, or on the inner flange of the sand prevention device fixed on the middle transverse support connection assembly 23, so as to improve the sealing effect of the air intake bypass end.

[0050] refer to Figure 5 The bypass door assembly 10 also includes a turbine support 14 and a worm cover 15. A rotatable worm 33 is adapted to be installed in the worm cover. The rotatable worm 33 is a part of the bypass door drive assembly 30 and can be combined with the attached Fig.14 , the rotatable worm 33 is driven by the bypass door drive assembly 30 installed on the sand control end transverse support 24 to rotate, interacting with the turbine support 14, thereby driving the bypass door body 11 to move along the axial direction of the linear guide support 21. The bypass door drive assembly 30 includes two drive motors 31, which are connected by a linkage synchronization shaft 34 for mechanical synchronization. Each drive motor 31 is connected to a reduction device 32, and the reduction device is fixed on the reduction device mounting platform 242 provided on the sand control end transverse support 24. The present application adopts two drive motors for driving, and mechanical synchronization is achieved by the linkage synchronization shaft 34 to ensure that the two rotatable worms 33 rotate synchronously. When one motor fails, it is driven by the other motor alone. It can be understood that the bypass door can still be opened normally when a single drive motor fails, which improves the safety margin; on the other hand, the double worm linkage symmetrical drive configuration makes the bypass door assembly 10 more evenly loaded.

[0051] like Figure 6As shown, the support frame assembly 20 provided in the present application is divided into two parts by three transverse support assemblies, and the three transverse support assemblies are respectively the transverse support assembly 22 at the air inlet end, the intermediate transverse support connection assembly 23 and the transverse support member 24 at the sand control end. The first part between the intermediate transverse support connection assembly 23 and the transverse support assembly 22 at the air inlet end serves as an air intake bypass, and the second part between the transverse support member 24 at the sand control end and the intermediate transverse support connection assembly 23 extends into the interior of the sand control assembly 2, and the bypass door assembly 10 is used to slide between the first part and the second part. The transverse support assembly 22 at the air inlet end, the intermediate transverse support connection assembly 23 and the transverse support member 24 at the sand control end are described in detail below.

[0052] like Figure 8 and Fig. 9 As shown, the inlet end lateral support assembly 22 is composed of a structural body 221 and an anti-icing and anti-foreign matter net 222. The structural body 221 is provided with: a structural and electrical connection frame 223 for connecting the anti-icing and anti-foreign matter net 222, an inlet support member reinforcement flange 224, and a through-hole connection boss 225 for connecting the linear guide support member 21. The through-hole connection boss 225 and the linear guide support member 21 are detachably connected to facilitate subsequent disassembly maintenance and installation recovery. Figure 2 The anti-icing and anti-foreign-object net 222 is a planar structure, connected to the structural body 221 of the inlet lateral support assembly 22 through a connecting frame 223, and electrically connected to the power supply device through the connecting frame 223. In some optional embodiments, reference Fig.17 , the anti-icing and anti-foreign-matter net 222 can also be configured to protrude from one end of the self-connecting structure main body 221 toward the direction of the anti-sand device 2 to form a hemispherical structure. In the above two embodiments, the anti-icing and anti-foreign-matter net 222 with a planar configuration is simple in process, and it uses a tension field to resist bird strikes, which is simple and reliable; the anti-icing and anti-foreign-matter net 222 is arranged on the transverse support assembly 22 at the air inlet end of the support frame assembly 20, at the entrance of the air inlet, with a small airflow passing area, a light structure weight, and low anti-icing power consumption; the anti-icing and anti-foreign-matter net 222 is arranged in a curved surface structure, which can enhance the anti-collision capability and appropriately increase the air inlet net area; Fig.19 Another embodiment of the installation of the anti-icing and foreign matter protection net is provided. The anti-icing and foreign matter protection net 222 is arranged in an annular structure and is arranged between the middle lateral support connection assembly 23 and the inlet end lateral support assembly 22 .

[0053] In some optional embodiments, reference Fig.18 The anti-icing and foreign body prevention net 222 is provided with a notch in the middle to accommodate the engine air intake straightening cone 107. The notch in the middle of the anti-icing and foreign body prevention net 222 can also be structurally and electrically connected to the air intake straightening cone 107, thereby realizing an integrated fusion design of the anti-icing and foreign body prevention net 222 and the engine air intake straightening cone 107.

[0054] The present application can greatly reduce the design and verification pressure of the front-end sand control device against bird strikes by setting the anti-icing and anti-foreign object net 222 at the very end of the sand control device air intake and the bypass air intake, and at the same time completely solve the problem of foreign object entry, including the possible detachment of foreign objects from the sand control device and the bypass mechanism, and has the advantages of high structural efficiency and high safety.

[0055] like Fig.10 and Fig.11 As shown, the intermediate transverse support connection assembly 23 includes: an intermediate transverse support structure 231 and an O-ring 232. When the bypass door is closed, the O-ring 232 forms an air intake seal with the bypass sealing rib 12 on the bypass door assembly 10. The intermediate transverse support structure 231 is provided with: a mounting flange 233 for connecting with the sand control device 2, a mounting hole 236, a reinforcing flange 234, and a through-hole connecting semi-boss 235 for connecting with the linear guide support member 21. The through-hole connecting semi-boss 235 and the linear guide support member 21 are fixedly welded or riveted. The mounting flange 233 is screwed with the sand control device 2 through the mounting hole 236, which is convenient for disassembly and installation.

[0056] like Fig.12 and Fig.13 As shown, the sand control end transverse support member 24 is provided with a blind hole boss 241, a speed reducer mounting platform 242 and a worm through hole 243. The blind hole boss 241 and the linear guide rail support member 21 are fixedly welded or riveted.

[0057] In some optional embodiments, such as Fig. 20 As shown, the sand-control end transverse support member 24 is also provided with a detachable support joint 245 extending radially on its outer ring edge, and the other end of the support joint 245 is fixedly abutted against the inner wall of the sand-control device 2 to improve the installation stability of the engine intake bypass device.

[0058] The engine forward bypass device 3 of the present application is integrated with the air intake duct 1 and the anti-sand device 2 to effectively ensure the bypass space, reduce the flow resistance during the bypass intake, and reduce the anti-icing power consumption of the whole system. Fig.15 and 16 shown.

[0059] In some optional embodiments, the engine inlet port is provided with an inlet end face recess 102 outside the inlet lip 101, the structural body of the inlet lateral support assembly 22 is located in the inlet end face recess 102, and when the inlet lateral support assembly 22 is placed in the inlet end face recess 102, its end face is not higher than the end face at the inlet port, such as Fig.15As shown, this design can prevent the lateral support assembly 22 at the inlet end from protruding and causing additional flow resistance, and prevent the protruding step from causing more severe icing. The front plane 106 of the inlet lip is set to be lower than the installation plane 105 of the lateral support assembly at the inlet end, which is convenient for the installation of the anti-icing and anti-foreign matter net 222. The inlet O-ring seal 103 is used to prevent sand and dust from passing through.

[0060] In some optional embodiments, the airflow outlet end of the sand control device 2 is provided with a sand control end face recess 201, the middle transverse support connection assembly 23 is adapted to be installed in the sand control end face recess 201, and is connected to the sand control device 2 through a mounting bolt 202, and the bolt head of the mounting bolt 202 is lower than the airflow outlet end face of the sand control device 2. Fig.16 As shown, after the middle transverse support connection assembly 23 is buried, it is connected to the sand control device 2 by installing bolts 202, and the bolt head is lower than the end face of the sand control device 2 to prevent the structure from protruding and causing additional flow resistance, and to prevent the structure from protruding and causing more serious icing. The sand control device 2 can be supported on the structural platform through the joint, and the intake duct bypass device 3 is supported at the same time.

[0061] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An engine intake bypass device, characterized in that: The invention comprises a bypass door assembly (10), a support frame assembly (20) and a bypass door drive assembly (30), wherein the support frame assembly (20) comprises a linear guide rail support member (21), an air inlet duct lateral support member (22), an intermediate lateral support connection member (23) and a sand control end lateral support member (24), wherein the linear guide rail support member (21) is fixed to the intermediate lateral support connection member (23), one end of which extends in the direction of the air inlet duct (1) and the end of which is connected to the air inlet duct lateral support member (22), and the other end of which extends in the direction of a sand control device (2) arranged outside the air inlet duct and the end of which is connected to the sand control end lateral support member (24), wherein the intermediate end of the air inlet duct lateral support member (22) is arranged An air intake inlet is provided for air intake, a lateral airflow channel is formed between the intermediate lateral support connection assembly (23) and the air intake duct lateral support assembly (22), external air enters the engine air intake duct through the lateral airflow channel and the air intake inlet in sequence, forming a bypass air intake, the bypass door assembly (10) comprises a bypass door body (11) with openings at both ends and a cylindrical structure, the bypass door body (11) is supported and slidably arranged on the linear guide rail support member (21), and is used to close or open the lateral airflow channel, the bypass door drive assembly (30) is fixed to the sand control end lateral support member (24) of the support frame assembly (20), and is used to drive the bypass door body (11) to slide; The intermediate lateral support connection assembly (23) is detachably fixed to the airflow outlet end of the sand control device (2), the air inlet lateral support assembly (22) is non-fixedly elastically abutted against the air inlet (1), and the sand control end lateral support member (24) is further provided with a detachable support joint (245) extending in the radial direction on its outer ring edge, and the other end of the support joint (245) abuts against the inner wall of the sand control device (2); An anti-icing and anti-foreign-matter net (222) is provided at the air inlet of the air inlet duct lateral support assembly (22); the anti-icing and anti-foreign-matter net (222) is connected to the structural body (221) of the air inlet duct lateral support assembly (22) via a connecting frame (223), and is electrically connected to a power supply device via the connecting frame (223); a notch is provided in the middle of the anti-icing and anti-foreign-matter net (222) to accommodate the engine air inlet straightening cone (107).

2. The engine intake bypass device according to claim 1, characterized in that: The linear guide support member (21) comprises a main support body (211) and an integrated linear guide rail (212) extending along the axis direction of the main support body (211); a linear bearing slider (13) distributed along the axial direction is arranged outside the bypass door body (11); the integrated linear guide rail (212) is adapted to be installed in the axial channel defined by the linear bearing slider (13); the bypass door body (11) is also provided with a turbine support (14) and a worm cover (15); a rotatable worm (33) is adapted to be installed in the worm cover; the rotatable worm (33) is driven to rotate by the bypass door drive assembly (30) installed on the sand control end transverse support member (24), interacts with the turbine support (14), and thus drives the bypass door body (11) to move along the axial direction of the linear guide support member (21).

3. The engine intake bypass device according to claim 2, characterized in that: The bypass door drive assembly (30) comprises two independently operable drive motors (31), the two drive motors (31) being connected via a linkage synchronizing shaft (34) for achieving mechanical synchronization, each drive motor (31) being connected to a reduction gear (32), the reduction gear being fixed to a reduction gear mounting platform (242) provided on the sand control end transverse support member (24).

4. The engine intake bypass device according to claim 1, characterized in that: A through-hole connection boss (225) is provided on the structural body of the air inlet duct lateral support assembly (22), and the through-hole connection boss (225) is detachably connected to the linear guide rail support component (21).

5. The engine intake bypass device according to claim 1, characterized in that: The engine air inlet port is provided with an air inlet end face recess (102) outside the air inlet lip (101), the structural body of the air inlet lateral support assembly (22) is located in the air inlet end face recess (102), and when the air inlet lateral support assembly (22) is placed in the air inlet end face recess (102), the air inlet end lateral support assembly installation plane (105) is not higher than the air inlet outer plane (104).

Images