Integrated fan compressor of water-air dual-purpose vehicle

Abstract

The application discloses an integrated fan compressor of a water-air dual-purpose aircraft, which comprises a fan rotor, a fan stator, an intermediate casing, a compressor rotor, a compressor stator, an outer-duct nozzle, a mechanical sealing structure and a plurality of water nozzles; the fan rotor shaft and the compressor rotor shaft are connected and are installed on a combustion chamber casing through bearings, and each bearing is sealed by the mechanical sealing structure; the fan stator, the intermediate casing and the outer-duct nozzle casing are sequentially connected, the compressor stator is nestedly installed in the outer-duct nozzle casing, and the front end of the compressor stator penetrates through the rear end of an intermediate casing support plate and is fixed; a plurality of water nozzles are arranged in the circumferential direction at the fan rotor inlet, the compressor rotor inlet and the middle section of the compressor stator, so as to cool the front half and the rear half of the fan part and the compressor part; and the problems of high parallel cost, complex structure, large space occupation and insufficient cross-medium capacity of the power device of the water-air dual-purpose aircraft are solved.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of fan compressor technology, and particularly to an integrated fan compressor for an amphibious vehicle. Background Technology

[0002] With the development of future technology, a new generation of vehicles that can operate both in the air and underwater are needed, capable of high-speed aerial maneuvering and silent underwater navigation, possessing excellent rapid stealth capabilities and the ability to repeatedly enter and exit the water to evade detection.

[0003] Due to the limitations of conventional fan compressor structures, the power systems of most amphibious vehicles currently available are often a parallel structure of two power units for air flight and underwater submersion. This type of vehicle has high costs, complex structure, large space occupation, and insufficient autonomous reciprocating cross-medium capability. Summary of the Invention

[0004] The purpose of this invention is to provide an integrated fan compressor for an amphibious vehicle, in order to solve the problems of high cost, complex structure, large space occupation, and insufficient autonomous reciprocating cross-medium capability caused by the use of two sets of power devices for air flight and underwater submersion in parallel structure in the power system of amphibious vehicles.

[0005] The technical solution of the present invention is as follows: The present invention provides an integrated fan compressor for a dual-purpose water and air vehicle, comprising: a fan rotor 1, a fan stator 2, an intermediate casing 3, a compressor rotor 4, a compressor stator 5, an outer bypass nozzle 6, a mechanical seal structure 7, and multiple water nozzles. Among them, the fan rotor 1 shaft and the compressor rotor 4 shaft are connected and are mounted on the combustion chamber casing of the intermediate casing 3 through bearings, and each bearing is sealed with lubricating oil through the mechanical seal structure 7. The fan stator 2, intermediate casing 3, and outer bypass nozzle 6 housing are connected in sequence. The compressor stator 5 is nested inside the outer bypass nozzle 6 housing, with its front end passing through the rear end of the intermediate casing 3 support plate and fixed. Multiple water nozzles distributed circumferentially are respectively installed at the inlet of the fan rotor 1, the inlet of the compressor rotor 4, and the middle section of the compressor stator 5 for cooling the front and rear halves of the fan and compressor components.

[0006] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The front end of the fan rotor 1 has an annular cavity with an opening facing rearward. The front end of the inner ring shell of the intermediate casing 3 is embedded in the annular cavity and connected by a bearing. The rear end of the inner ring shell of the intermediate casing 3 is connected to the front end of the compressor rotor 4 shaft by a bearing. The rear end of the compressor rotor 4 shaft is mounted on the front end of the combustion chamber casing by a bearing.

[0007] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The fan rotor 1 is composed of two-stage fan rotor blades connected by electron beam welding; the fan stator 2 is a segmented structure, including: a fan casing, and two-stage segmented rectifiers installed axially inside the fan casing; The compressor rotor 4 is composed of four-stage compressor rotor blades connected by electron beam welding; the compressor stator 5 includes: a compressor casing, a four-stage rotor outer ring installed axially inside the compressor casing, and a four-stage split rectifier fixedly installed through the four-stage rotor outer ring.

[0008] Optionally, in the integrated fan compressor of the amphibious vehicle described above, the water nozzle includes: Multiple fan inlet nozzles 8 are installed circumferentially at the inlet of the fan rotor 1 via the air intake casing; Multiple compressor inlet nozzles 9 are circumferentially mounted at the rear end of the intermediate casing 3 via the support of the intermediate casing 3. Multiple compressor intermediate stage water nozzles 10 pass through the wall of the outer bypass nozzle 6 and are installed circumferentially in the middle section of the outer bypass nozzle 6. The ends of each compressor intermediate stage water nozzle 10 pass through the designated stator of the compressor stator 5 and enter the compressor flow channel.

[0009] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The fan inlet nozzle 8 is a swirling nozzle structure that sprays water in a mist form. The water flow rate is obtained through simulation and experimental calculation. The spray angle of the fan inlet nozzle 8 is designed to align with the fan rotor 1 disc drum, that is, near the root of the fan rotor blades, to prevent the water flow from directly impacting the blades. It can also diffuse the water to the entire fan flow channel through centrifugal force.

[0010] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The compressor inlet water nozzle 9 has a swirling nozzle structure, spraying water in a mist-like form. The water flow rate is obtained through simulation and experimental calculation. The spray angle of the compressor inlet water nozzle 9 is designed to align with the compressor rotor 4 disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and to diffuse the water to the entire compressor flow channel through centrifugal force.

[0011] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The intermediate stage water nozzle 10 of the compressor is a direct-flow nozzle structure. The nozzle structure that enters the compressor flow channel is a hemispherical structure, which can reduce the impact of the intermediate stage water nozzle 10 on the compressor performance. At the same time, the hemispherical nozzle structure can optimize the airflow on the wall.

[0012] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The water flow rate of the intermediate stage water nozzle 10 of the compressor is obtained through simulation and experimental calculation; the rear end of the nozzle hemispherical structure is provided with a water spray hole, and the outlet of the water spray hole is designed with a chamfer of 0.3×30° to diffuse the water flow and form a water mist. At the same time, the angle of the water spray hole is designed to align with the compressor rotor disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and to diffuse the water to the entire compressor flow channel through centrifugal force.

[0013] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The intermediate stage water nozzle 10 of the compressor is sealed with the compressor stator 5 by a radial rubber ring, which is used to prevent the internal gas from leaking into the external bypass channel and affecting the performance of the fan compressor in the air operation mode. The intermediate stage water nozzle 10 of the compressor is designed in a blade-like shape within the outer bypass nozzle 6. This reduces airflow turbulence, prevents blockage of the outer bypass channel, and ensures stable performance of the fan compressor.

[0014] Optionally, in the integrated fan compressor of the amphibious vehicle described above, The fan inlet water nozzle 8, the compressor inlet water nozzle 9, and the compressor intermediate stage water nozzle 10 are respectively connected to the corresponding water inlet pipes, and the connection is sealed with a conical surface to prevent water leakage and affect the water spray flow.

[0015] The beneficial effects of this invention are as follows: This invention provides an integrated fan compressor for a dual-purpose water and air vehicle. The fan rotor 1 shaft and the compressor rotor 4 shaft are connected and mounted on the combustion chamber casing of the intermediate casing 3 through bearings, and each bearing is sealed with lubricating oil through a mechanical seal structure 7. The fan stator 2, the intermediate casing 3 and the outer bypass nozzle 6 casing are connected in sequence. The compressor stator 5 is nested in the outer bypass nozzle 6 casing, and its front end passes through the rear end of the support plate of the intermediate casing 3 and is fixed. Multiple water nozzles distributed circumferentially are respectively installed at the inlet of the fan rotor 1, the inlet of the compressor rotor 4 and the middle section of the compressor stator 5 for cooling the front and rear halves of the fan and compressor components.

[0016] The integrated fan compressor provided by this invention reduces the large amount of heat generated by frictional work of rotating parts during underwater idling by adding a water spray structure. It also ensures sealed lubrication through a mechanical seal, allowing for application in amphibious vehicles with integrated propulsion. Because a single propulsion system is used both in the air and underwater, the system achieves the same performance requirements for both modes of operation while being smaller and lighter. All components are designed with an integral structure, significantly reducing the number of parts, and using commonly used structural components with mature and simple manufacturing and assembly processes. The amphibious fan compressor designed in this invention can be applied to amphibious integrated propulsion systems, reducing the number of parts by approximately 10%, the size by approximately 25%, and the cost by approximately 15% compared to existing parallel propulsion devices. Attached Figure Description

[0017] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0018] Figure 1 This invention provides a schematic diagram of the structure of an integrated fan compressor for an amphibious vehicle.

[0019] Explanation of reference numerals in the attached figures: 1—Fan rotor, 2—Fan stator, 3—Intermediate casing, 4—Compressor rotor, 5—Compressor stator, 6—Outer bypass nozzle, 7—Mechanical seal structure, 8—Fan inlet water nozzle, 9—Compressor inlet water nozzle, 10—Compressor intermediate stage water nozzle. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0021] As explained in the background section, due to the limitations of conventional fan compressor structures, the existing amphibious vehicles use two sets of power units in parallel for air flight and underwater submersion. This results in problems such as high parallel costs, complex structure, large space occupation, and insufficient autonomous reciprocating cross-medium capability.

[0022] A conventional fan compressor structure consists of a fan rotor / stator, a compressor rotor / stator, an intermediate casing, and an outer bypass nozzle. This structure utilizes rotational mechanical energy to do work on the air flowing through it. The air enters the fan, is pressurized by the fan, and is then split into two airflow streams—inner and outer bypass—by a splitter on the intermediate casing. The gas in the inner bypass stream is accelerated by the compressor and mixes with fuel in the combustion chamber, forming high-temperature, high-pressure combustion gas. This gas then enters the turbine, expands, and does work, generating power to drive the engine rotor and accessories. The gas in the outer bypass stream is directly discharged into the tailpipe, mixes with the combustion gas discharged from the turbine, continues to expand within the tailpipe, and is ejected at high speed, generating thrust.

[0023] To achieve integrated power for amphibious vehicles, the fan compressor needs to have its inlet closed and operate at normal speed when working underwater. Under these conditions, conventional fan compressors will generate a lot of heat due to friction of rotating parts, leading to excessively high temperatures. Additionally, the failure of the lubricating oil sealing system will cause a large amount of lubricating oil leakage.

[0024] To address the design challenges of integrated power systems in amphibious aircraft, this invention provides an integrated fan compressor for amphibious vehicles, involving fan and compressor components, specifically a fan compressor that can be used both underwater and in the air.

[0025] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0026] This invention provides an integrated fan compressor for an amphibious vehicle that can be used in both air and underwater operating modes and can switch between the two modes. The design challenges of this integrated fan compressor are: conventional fan compressors, when operating at normal speed underwater with a sealed inlet, can cause excessively high temperatures, and the lubricating oil can leak a large amount of lubricating oil due to the failure of the lubricating oil sealing system.

[0027] Figure 1 This is a schematic diagram of the integrated fan compressor of an amphibious vehicle provided in an embodiment of the present invention. Figure 1 As shown, the integrated fan compressor of the amphibious vehicle provided by the present invention includes: a fan rotor 1, a fan stator 2, an intermediate casing 3, a compressor rotor 4, a compressor stator 5, an outer bypass nozzle 6, a mechanical seal structure 7, and multiple water nozzles.

[0028] like Figure 1 The integrated fan compressor shown has a fan rotor 1 shaft connected to a compressor rotor 4 shaft, and is mounted on the intermediate casing 3 housing combustion chamber casing via bearings, with each bearing being sealed with lubricating oil via a mechanical seal structure 7.

[0029] In this embodiment of the invention, the fan stator 2, the intermediate casing 3, and the outer bypass nozzle 6 housing are connected in sequence. The compressor stator 5 is nested inside the outer bypass nozzle 6 housing, and its front end passes through the rear end of the support plate of the intermediate casing 3 and is fixed. Multiple water nozzles distributed circumferentially are respectively installed at the inlet of the fan rotor 1, the inlet of the compressor rotor 4, and the middle section of the compressor stator 5 for cooling the front and rear halves of the fan component and the compressor component.

[0030] In one embodiment of the present invention, the front end of the fan rotor 1 is formed with an annular cavity opening to the rear. The front end of the inner ring shell of the intermediate casing 3 is embedded in the annular cavity and connected by a bearing. The rear end of the inner ring shell of the intermediate casing 3 is connected to the front end of the compressor rotor 4 shaft by a bearing. The rear end of the compressor rotor 4 shaft is mounted on the front end of the combustion chamber casing by a bearing.

[0031] In one embodiment of the present invention, the fan rotor 1 is composed of two-stage fan rotor blades connected by electron beam welding; the fan stator 2 is a segmented structure, including: a fan casing, and two-stage segmented rectifiers installed axially inside the fan casing.

[0032] In this implementation, the compressor rotor 4 is composed of four-stage compressor rotor blades connected by electron beam welding; the compressor stator 5 includes: a compressor casing, a four-stage rotor outer ring installed axially in the compressor casing, and a four-stage split rectifier fixedly installed through the four-stage rotor outer ring.

[0033] In one implementation of this invention, the water nozzle includes: a plurality of fan inlet water nozzles 8 circumferentially installed at the inlet of the fan rotor 1 via the intake casing; a plurality of compressor inlet water nozzles 9 circumferentially assembled at the tail end of the intermediate casing 3 via the rear end of the bracket of the intermediate casing 3; and a plurality of compressor intermediate stage water nozzles 10 passing through the wall of the outer bypass nozzle 6 and circumferentially installed in the middle section of the outer bypass nozzle 6, wherein the end of each compressor intermediate stage water nozzle 10 passes through a designated stator of the compressor stator 5 and enters the compressor flow channel.

[0034] In this implementation, the specific structural forms of the various water nozzles mentioned above are as follows: (1) Fan inlet spray nozzle 8: The fan inlet nozzle 8 is a swirling nozzle structure that sprays water in a mist. The water flow rate is obtained through simulation and experimental calculation. The spray angle of the fan inlet nozzle 8 is designed to align with the fan rotor 1 disc drum, that is, near the root of the fan rotor blades, to prevent the water flow from directly impacting the blades. It can also diffuse the water to the entire fan flow channel through centrifugal force.

[0035] (2) Compressor inlet water nozzle 9: The compressor inlet water nozzle 9 has a swirling nozzle structure, spraying water in a mist form. The water flow rate is obtained through simulation and experimental calculation. The spray angle of the compressor inlet water nozzle 9 is designed to align with the compressor rotor 4 disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and to diffuse the water to the entire compressor flow channel through centrifugal force.

[0036] (3) Compressor intermediate stage water nozzle 10: The intermediate stage water nozzle 10 of the compressor is a direct-flow nozzle structure. The nozzle structure that enters the compressor flow channel is a hemispherical structure, which can reduce the impact of the intermediate stage water nozzle 10 on the compressor performance. At the same time, the hemispherical nozzle structure can optimize the airflow on the wall.

[0037] In this embodiment of the invention, the water flow rate of the intermediate stage water nozzle 10 of the compressor is obtained through simulation and experimental calculation; a water spray hole is provided at the rear end of the nozzle hemispherical structure, and the outlet of the water spray hole is designed with a chamfer of 0.3×30° to diffuse the water flow and form a water mist. At the same time, the angle of the water spray hole is designed to align with the compressor rotor disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and to diffuse the water to the entire compressor flow channel through centrifugal force.

[0038] In a specific implementation of this invention, the intermediate stage water nozzle 10 of the compressor is sealed with a radial rubber ring between itself and the compressor stator 5. This seal is used to prevent the internal gas from leaking into the bypass channel and affecting the performance of the fan compressor during in-flight operation. In addition, the intermediate stage water nozzle 10 of the compressor is designed in a blade-like shape within the bypass nozzle 6. This reduces airflow turbulence, prevents blockage of the bypass channel, and ensures stable performance of the fan compressor.

[0039] It should be noted that the fan inlet spray nozzle 8, the compressor inlet spray nozzle 9, and the compressor intermediate stage spray nozzle 10 are respectively connected to the corresponding water inlet pipes, and the connection is sealed with a conical surface to prevent water leakage and affect the water spray flow.

[0040] This invention provides an integrated fan compressor for an amphibious vehicle. The fan rotor 1 shaft and the compressor rotor 4 shaft are connected and mounted on the combustion chamber casing of the intermediate casing 3 via bearings. Each bearing is sealed with lubricating oil by a mechanical seal structure 7. The fan stator 2, the intermediate casing 3, and the outer bypass nozzle 6 casing are connected in sequence. The compressor stator 5 is nested inside the outer bypass nozzle 6 casing, with its front end passing through the rear end of the support plate of the intermediate casing 3 and fixed thereon. Multiple water nozzles distributed circumferentially are respectively installed at the inlet of the fan rotor 1, the inlet of the compressor rotor 4, and the middle section of the compressor stator 5 for cooling the front and rear halves of the fan and compressor components.

[0041] The integrated fan compressor provided by this invention reduces the large amount of heat generated by frictional work of rotating parts during underwater idling by adding a water spray structure. It also ensures sealed lubrication through a mechanical seal, allowing for application in amphibious vehicles with integrated propulsion. Because a single propulsion system is used both in the air and underwater, the system achieves the same performance requirements for both modes of operation while being smaller and lighter. All components are designed with an integral structure, significantly reducing the number of parts, and using commonly used structural components with mature and simple manufacturing and assembly processes. The amphibious fan compressor designed in this invention can be applied to amphibious integrated propulsion systems, reducing the number of parts by approximately 10%, the size by approximately 25%, and the cost by approximately 15% compared to existing parallel propulsion devices.

[0042] The following examples illustrate the implementation of the integrated fan compressor for the amphibious vehicle provided by the present invention.

[0043] Implementation Example This embodiment provides an integrated fan compressor for an amphibious vehicle, including: a fan rotor 1, a fan stator 2, an intermediate casing 3, a compressor rotor 4, a compressor stator 5, an outer bypass nozzle 6, a mechanical seal structure 7, a fan inlet water nozzle 8, a compressor inlet water nozzle 9, and a compressor intermediate stage water nozzle 10.

[0044] In this embodiment, fan rotor 1 is composed of two-stage fan rotor disks connected by electron beam welding. Fan stator 2 is a segmented structure, machined as a single forging. Compressor rotor 4 is composed of four-stage compressor rotor disks connected by electron beam welding. Compressor stator 5 consists of compressor casing, four-stage segmented rectifier, and four-stage rotor outer ring.

[0045] In this implementation example, the fan inlet water nozzles 8 are located at the inlet of the fan rotor 1, with three evenly distributed around the circumference, used for cooling the fan components. Specifically, the fan inlet water nozzles 8 are swirling nozzles that spray water in a mist-like pattern. The water flow rate is calculated through simulation and experimental results. Simultaneously, the spray angle is designed to align with the fan rotor disc drum, near the root of the fan rotor blades, preventing direct water impact on the blades and allowing centrifugal force to diffuse the water throughout the entire fan flow channel.

[0046] In this implementation example, the compressor inlet water nozzle 9 is assembled at the tail of the intermediate casing 3, located at the inlet of the compressor rotor 4. Two nozzles are distributed circumferentially and are used for cooling the front half of the compressor components. In specific implementation, the compressor inlet water nozzle 9 has a swirling nozzle structure, spraying water in a mist-like manner. The water flow rate is obtained through simulation and experimental calculation. Simultaneously, the spray angle is designed to align with the compressor rotor disc drum, i.e., near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades and to diffuse the water throughout the entire compressor flow channel through centrifugal force.

[0047] In this embodiment, the intermediate stage water nozzle 10 of the compressor passes through the wall of the outer bypass nozzle 6, is assembled in the middle section of the outer bypass nozzle 6, and enters the compressor flow channel after passing through the second stage stator of the compressor stator 5. Two nozzles are distributed circumferentially for cooling the rear half of the compressor components. In specific implementation, the intermediate stage water nozzle 10 of the compressor has a direct-flow nozzle structure, and the nozzle structure entering the compressor flow channel is a hemispherical structure, which can reduce the impact of the intermediate stage water nozzle 10 on the compressor performance. At the same time, the hemispherical nozzle structure can optimize the airflow on the wall. In addition, the water flow rate of the intermediate stage water nozzle 10 is obtained through simulation and experimental calculation. The rear end of the hemispherical nozzle structure is provided with a water spray hole, and the outlet of the water spray hole is designed with a chamfer of 0.3×30° to diffuse the water flow and form a water mist. At the same time, the spray angle is designed to align with the compressor rotor disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and the water can be diffused to the entire compressor flow channel by centrifugal force. In this embodiment, the intermediate stage water nozzle 10 of the compressor is sealed to the compressor stator 5 by a radial rubber ring to prevent internal gas leakage into the bypass duct and affecting the performance of the fan compressor during in-flight operation. Furthermore, the intermediate stage water nozzle 10 is designed in a blade-like shape within the bypass nozzle 6 to reduce airflow turbulence, prevent blockage of the bypass duct, and ensure stable performance of the fan compressor.

[0048] It should be noted that the fan inlet spray nozzle 8, the compressor inlet spray nozzle 9, and the compressor intermediate stage spray nozzle 10 are respectively connected to the corresponding water inlet pipes, and the connection is sealed with a conical surface to prevent water leakage and affect the water spray flow.

[0049] The mechanical seal structure 7 is located at the two support points before and after the fan compressor. It is used to seal the lubricating oil and prevent the lubricating oil from leaking into the fan compressor flow channel. At the same time, it prevents the water used for cooling from flowing into the lubricating oil chamber. It can play a sealing role during air and underwater operation without being affected by the air system.

[0050] Implementation Cases The integrated fan compressor for an amphibious vehicle provided in the above embodiments of the present invention has been applied to a small cross-medium engine, connected to an integrated amphibious combustion chamber and turbine, enabling a single engine to simultaneously operate in three modes: underwater navigation, rapid water exit, and aerial cruise, with the ability to switch between them as needed. The core components are reduced by approximately 30% compared to common parallel engines, the size is reduced by approximately 35%, and the cost is reduced by approximately 25%.

[0051] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. An integrated fan compressor for an amphibious vehicle, characterized in that, include: Fan rotor, fan stator, intermediate casing, compressor rotor, compressor stator, outer bypass nozzle, mechanical seal structure, and multiple water nozzles; The fan rotor shaft and the compressor rotor shaft are connected and mounted on the intermediate casing housing combustion chamber casing via bearings, and each bearing is sealed with lubricating oil through a mechanical seal structure. The fan stator, intermediate casing, and outer bypass nozzle housing are connected in sequence. The compressor stator is nested inside the outer bypass nozzle housing, with its front end passing through the rear end of the intermediate casing support plate and fixed. Multiple water nozzles distributed circumferentially are respectively installed at the fan rotor inlet, the compressor rotor inlet, and the middle section of the compressor stator for cooling the front and rear halves of the fan and compressor components.

2. The integrated fan compressor for an amphibious vehicle according to claim 1, characterized in that, The front end of the fan rotor has an annular cavity with an opening facing rearward. The front end of the inner ring shell of the intermediate casing is embedded in the annular cavity and connected by a bearing. The rear end of the inner ring shell of the intermediate casing is connected to the front end of the compressor rotor shaft by a bearing, and the rear end of the compressor rotor shaft is mounted on the front end of the combustion chamber casing by a bearing.

3. The integrated fan compressor for an amphibious vehicle according to claim 1, characterized in that, The fan rotor is composed of two-stage fan rotor blades connected by electron beam welding; the fan stator is a segmented structure, including: a fan casing, and two-stage segmented rectifiers installed axially inside the fan casing; The compressor rotor is composed of four-stage compressor rotor blades connected by electron beam welding; the compressor stator includes: a compressor casing, a four-stage rotor outer ring installed axially inside the compressor casing, and a four-stage split rectifier fixedly installed through the four-stage rotor outer ring.

4. The integrated fan compressor for an amphibious vehicle according to any one of claims 1 to 3, characterized in that, The water nozzle includes: Multiple fan inlet nozzles are installed circumferentially at the fan rotor inlet via the intake casing; Multiple compressor inlet nozzles are circumferentially mounted at the rear end of the intermediate casing via the support of the intermediate casing. Multiple compressor intermediate stage water nozzles pass through the wall of the outer bypass nozzle and are installed circumferentially in the middle section of the outer bypass nozzle. The ends of each compressor intermediate stage water nozzle pass through the designated stator of the compressor stator and enter the compressor flow channel.

5. The integrated fan compressor for an amphibious vehicle according to claim 4, characterized in that, The fan inlet spray nozzle is a swirling nozzle structure that sprays water in a mist form. The spray flow rate is obtained through simulation and experimental calculation. The spray angle of the fan inlet spray nozzle is designed to align with the fan rotor disc drum, that is, near the root of the fan rotor blades, to prevent the water flow from directly impacting the blades. It can also diffuse the water to the entire fan flow channel through centrifugal force.

6. The integrated fan compressor for an amphibious vehicle according to claim 4, characterized in that, The compressor inlet water nozzle has a swirling nozzle structure, spraying water in a mist-like form. The water flow rate is obtained through simulation and experimental calculation. The spray angle of the compressor inlet water nozzle is designed to align with the compressor rotor disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and to diffuse the water to the entire compressor flow channel through centrifugal force.

7. The integrated fan compressor for an amphibious vehicle according to claim 4, characterized in that, The intermediate stage water nozzle of the compressor is a DC nozzle structure, and the nozzle structure entering the compressor flow channel is a hemispherical structure, which can reduce the impact of the intermediate stage water nozzle on the compressor performance. At the same time, the hemispherical nozzle structure can optimize the airflow on the wall.

8. The integrated fan compressor for an amphibious vehicle according to claim 7, characterized in that, The water flow rate of the intermediate stage water nozzle of the compressor is obtained through simulation and experimental calculation; the rear end of the nozzle hemispherical structure is provided with a water spray hole, and the outlet of the water spray hole is designed with a chamfer of 0.3×30° to diffuse the water flow and form a water mist. At the same time, the angle of the water spray hole is designed to align with the compressor rotor disc drum, that is, near the root of the compressor rotor blades, to prevent the water flow from directly impacting the blades, and to diffuse the water to the entire compressor flow channel through centrifugal force.

9. The integrated fan compressor for an amphibious vehicle according to claim 4, characterized in that, The intermediate stage water nozzle of the compressor is sealed with the compressor stator by a radial rubber ring to prevent the internal gas from leaking into the external bypass channel and affecting the performance of the fan compressor in the air operation mode. The intermediate stage water nozzle of the compressor is designed in a blade-like shape inside the bypass nozzle. This reduces airflow turbulence, prevents blockage of the bypass channel, and ensures stable performance of the fan compressor.

10. The integrated fan compressor for an amphibious vehicle according to claim 4, characterized in that, The fan inlet water nozzle, the compressor inlet water nozzle, and the compressor intermediate stage water nozzle are respectively connected to the corresponding water inlet pipes, and the connection is sealed with a conical surface to prevent water leakage and affect the water spray flow.

Images