Comprehensive cooling fan suitable for multiple working conditions and helicopter engine oil-gas heat exchange system and method

Abstract

The invention discloses a comprehensive cooling fan suitable for multiple working conditions and a helicopter engine oil-gas heat exchange system and method. The comprehensive cooling fan is mainly composed of a fairing, a variable inlet guide blade assembly, a movable blade assembly, a shell assembly with an anti-surge hole, a rear guide static blade assembly, an inlet guide blade control machine assembly and a fan driving shaft assembly. According to the oil-gas heat exchange system suitable for cooling the heavy helicopter engine, the variable inlet guide blades are adjusted through the inlet guide blade control machine assembly, all the variable inlet guide blades rotate by a certain angle at the same time, then the output flow and pressure of a draught fan can be greatly changed, and therefore the heat exchange power is changed; and finally, the oil temperature in the oil-gas heat exchange system is stabilized in a set range.

Description

Technical Field

[0001] The present invention relates to a comprehensive cooling fan applicable to multiple working conditions, a helicopter engine oil-gas heat exchange system and method, and belongs to the field of the design of fans or aviation engine cooling systems. Background Art

[0002] A helicopter is a multi-functional rotary-wing aircraft designed for vertical takeoff, hovering and precise maneuverability. Compared with a fixed-wing aircraft, a helicopter generates lift by rotating blades, which enables the helicopter to take off and land vertically, hover and perform complex maneuvers. At present, helicopters have been widely used in military, civilian transportation, emergency medical services, search and air fire fighting and other fields. With the wide use of helicopters in many fields, the working conditions they face are extremely variable. Therefore, a fan that can provide a matched flow rate under different working conditions is also needed. Summary of the Invention

[0003] The present invention aims to provide a comprehensive cooling fan applicable to multiple working conditions, a helicopter engine oil-gas heat exchange system and method. By adopting a variable inlet guide vane assembly, all inlet vanes are rotated by a certain angle simultaneously, thereby changing the output flow rate and pressure of the fan to ensure that the oil output by the oil-gas heat exchange system is maintained within a set oil temperature range, and at the same time, it can also ensure that the fan is stable and does not surge during the process of changing the output flow rate and pressure.

[0004] To achieve the above object, the present invention adopts the following technical solutions:

[0005] A comprehensive cooling fan applicable to multiple working conditions includes a variable inlet guide vane assembly and an inlet guide vane control machine assembly, wherein:

[0006] The variable inlet guide vane assembly is located on one side of the air inlet of the comprehensive cooling fan and mainly consists of a blade shaft, variable inlet guide vanes, an inlet guide vane wheel housing, a synchronous rotating disk, an eccentric rod and a rocker, wherein:

[0007] The inlet guide vane wheel housing is a cylindrical shell. The synchronous rotating disk is located inside the inlet guide vane wheel housing. A plurality of blade shafts are arranged radially along the inlet guide vane wheel housing. The central angles between adjacent blade shafts are equal. The first end of the blade shaft penetrates through the inlet guide vane wheel housing and is rotatably connected to the inlet guide vane wheel housing. The second end extends to the outside of the inlet guide vane wheel housing. The variable inlet guide vanes are assembled on the blade shafts and rotate with the blade shafts as the rotation axes. The first end of the blade shaft is connected to the synchronous rotating disk through the eccentric rod and the rocker with spherical joint bearings at both ends, and the eccentric rod is connected to the rocker at one of the spherical joint bearings, and the synchronous rotating disk is connected to the rocker at the other spherical joint bearing;

[0008] The inlet guide vane control machine assembly includes an actuator, and the execution end of the actuator is connected to the second end of one of the plurality of blade shafts.

[0009] Furthermore, the integrated cooling fan applicable to multiple working conditions further includes:

[0010] A housing assembly, the housing assembly is a cylindrical cavity housing, the first axial end and the second axial end of the housing assembly form an air inlet and an air outlet respectively, the variable inlet guide vane assembly is located in the inner cavity at the first axial end of the housing assembly, the inlet guide vane control machine assembly is installed on the outer surface of the housing assembly, and the second end of the blade shaft penetrates the housing assembly and is connected to the actuator of the inlet guide vane control machine assembly.

[0011] Even further, the integrated cooling fan applicable to multiple working conditions further includes:

[0012] A fairing, the fairing is arranged in the cavity at the first axial end of the housing assembly and is connected to the end face on the side corresponding to the air inlet on the inlet guide vane hub of the variable inlet guide vane assembly;

[0013] A rotor blade assembly, the rotor blade assembly is arranged in the cavity of the housing assembly and is located on the side corresponding to the air outlet on the inlet guide vane hub of the variable inlet guide vane assembly. Surge prevention holes penetrating the radial wall thickness direction of the housing assembly are arranged on the circumferential surface of the housing assembly corresponding to the position of the rotor blade assembly, and multiple blades are evenly distributed on the circumferential surface of the rotor blade assembly;

[0014] A stator blade assembly, the stator blade assembly is arranged in the cavity of the housing assembly and is between the rotor blade assembly and the second axial end of the housing assembly. Multiple blades are evenly distributed on the circumferential surface of the stator blade assembly, and the blade tips of the blades are connected to the housing assembly;

[0015] A fan drive shaft assembly, the first end of the fan drive shaft assembly is located in the cavity of the housing assembly, penetrates the stator blade assembly and is connected to the rotor blade assembly.

[0016] As a solution, multiple said surge prevention holes are distributed at equal central angles on the same circumference of the circumferential surface of the housing assembly, and this circumference is located within the rotation area formed by the blade tips when multiple blades on the rotor blade assembly rotate around the fan drive shaft assembly.

[0017] As a solution, the fan drive shaft assembly is mainly composed of a fan drive shaft, a spacer sleeve and bearings, wherein:

[0018] The fan drive shaft is a hollow shaft, its outer surface has a flange structure, its inner surface has a spline, and the fan drive shaft is connected to the rotor blade assembly through the flange structure;

[0019] The inner rings of the two bearings are assembled with the fan drive shaft, and the outer rings of the two bearings are assembled with the rear guide vane assembly;

[0020] The spacer sleeve is sleeved on the fan drive shaft and is located between the two bearings.

[0021] As a solution, the execution end of the actuator is connected to the second end of one of the multiple blade shafts through a crank.

[0022] As an option, the housing assembly, the moving vane assembly, and the rear guide vane assembly are made of magnesium alloy, and the fan drive shaft assembly is made of stainless steel.

[0023] A helicopter engine oil-gas heat exchange system includes a comprehensive cooling fan applicable to multi-condition operation, which mainly consists of a fairing, a variable inlet guide vane assembly, a moving vane assembly, a housing assembly, a rear guide vane assembly, an inlet guide vane control machine assembly, and a fan drive shaft assembly.

[0024] A helicopter engine oil-gas heat exchange method includes: using a comprehensive cooling fan applicable to multi-condition operation, which mainly consists of a fairing, a variable inlet guide vane assembly, a moving vane assembly, a housing assembly, a rear guide vane assembly, an inlet guide vane control machine assembly, and a fan drive shaft assembly. By adjusting the rotation of the variable inlet guide vanes in the variable inlet guide vane assembly around the blade shaft through the inlet guide vane control machine assembly, the changes in the air outlet flow rate and air outlet pressure of the comprehensive cooling fan are realized, and then the oil-gas heat exchange power is changed, and finally the oil temperature after oil-gas heat exchange is controlled within the set range.

[0025] Compared with the prior art, the comprehensive cooling fan of the present invention mainly consists of components such as a fairing, a variable inlet guide vane assembly, a moving vane assembly, a housing assembly with anti-surge holes, a rear guide vane assembly, an inlet guide vane control machine assembly, and a fan drive shaft assembly. The present invention is applicable to cooling the oil-gas heat exchange system of a heavy helicopter engine (mainly including the oil-gas heat exchange device of the gearbox, the hydraulic system, the air compressor, the free turbine engine housing, the governor housing, and the generator). The present invention solves the problem of providing air with different flow rates and pressures by the cooling fan under different working conditions to ensure the set oil temperature of the oil-gas heat exchange system, making the application of the helicopter more extensive, efficient, and reliable.

[0026] The working principle of the integrated cooling fan of the present invention is as follows: The parameters (air pressure and flow rate) required for the operation of the integrated cooling fan are determined according to the ambient temperature on board the helicopter. When it is necessary to change the operating parameters of the integrated cooling fan, it is achieved by actively controlling the active rotation of the variable inlet guide vane around the blade axis in the variable inlet guide vane assembly. The specific process is as follows: Start the actuator in the inlet guide vane control machine assembly. The actuator pushes the variable inlet guide vane to rotate around the blade axis, and then drives all the blades to deflect by an angle through the synchronous rotating disk, thereby changing the output wind pressure and flow rate of the integrated cooling fan.

[0027] The integrated cooling fan of the present invention has the following characteristics:

[0028] (1) The output wind pressure and air flow rate can be adjusted at any time according to different working conditions, and the adjustment structure is simple, highly reliable, and of low complexity;

[0029] (2) The adjustment structures of the variable inlet guide vane assembly and the inlet guide vane control machine assembly are compact, occupy little space, have a light self-weight. Only by adjusting one blade, the rest of the blades can follow (a spatial rocker mechanism similar to a planar double-rocker mechanism is adopted between adjacent blades), and the blade adjustment angle range is large (30° - 90°);

[0030] (3) Anti-surge holes are provided in the moving blade area, achieving two-way reduction of the fan surge, ensuring the stable operation of the cooling fan, and avoiding the harm caused by surge that cannot be avoided due to too large a range of airflow changes in general types of fans. The airflow adjustment range of the present invention is much larger than that of general types of fans;

[0031] (4) The rotation of the variable inlet guide vane only requires one driving rod (the operating rod of the actuator) to drive one blade, and the rest of the blades are driven to rotate by being connected by a synchronous rotating disk. Since only one blade is the driving and adjusting blade, the thickness of the rest of the blades can be significantly reduced, ultimately reducing the self-weight of the blades. This can not only improve the sensitivity and response speed during blade angle adjustment, but also reduce the power requirement for the actuator.

[0032] (5) It is applicable to the oil-gas heat exchange system of heavy helicopter engines and can also be popularized and applied to other occasions, with high working efficiency and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 is a schematic structural diagram of the integrated cooling fan applicable to multiple working conditions in the present invention;

[0034] Figure 2 is Figure 1 the front view of

[0035] Figure 3 is Figure 1 the top view of

[0036] Figure 4 is the left view of Figure 1 ;

[0037] Figure 5 is the working principle diagram of the present invention;

[0038] Figure 6 is the schematic structural diagram of the fan drive shaft assembly;

[0039] Figure 7 is the schematic structural diagram of the inlet guide vane control machine assembly;

[0040] Figure 8 is the schematic structural diagram of the variable inlet guide vane assembly;

[0041] In the figure: 1, fairing; 2, variable inlet guide vane assembly; 3, moving vane assembly; 4, housing assembly with surge prevention holes; 5, rear guide vane assembly; 6, inlet guide vane control machine assembly; 7, fan drive shaft assembly; 21, vane shaft; 22, variable inlet guide vane; 23, inlet guide vane hub; 24, synchronous rotating disk; 25, eccentric rod; 26, rocker; 71, fan drive shaft; 72, spacer sleeve; 73, bearing. Specific embodiments

[0042] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. However, it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments. Without departing from the above technical idea of the present invention, all modifications, substitutions, and changes made according to common general knowledge and conventional means in the art are included in the scope of the present invention.

[0043] As Figures 1 to 8 shown, a comprehensive cooling fan applicable to multi - operating conditions designed by the present invention mainly consists of components such as a fairing 1, a variable inlet guide vane assembly 2, a moving vane assembly 3, a housing assembly 4 with surge prevention holes, a rear guide vane assembly 5, an inlet guide vane control machine assembly 6, and a fan drive shaft assembly 7. The fairing 1, the variable inlet guide vane assembly 2, the moving vane assembly 3, the rear guide vane assembly 5, and the fan drive shaft assembly 7 are coaxially assembled inside the housing assembly 4 with surge prevention holes, and the inlet guide vane control machine assembly 6 is installed on the outer surface of the housing assembly 4.

[0044] The fairing 1 ensures that the air flow direction is the most utilizable by contacting the air. There are 10 bolt holes on the fairing 1, and it is connected to the inlet guide vane hub 23 in the variable inlet guide vane assembly 2 by bolts.

[0045] The variable inlet guide vane assembly 2 is composed of 13 equally-spaced variable inlet guide vanes 22, an inlet guide vane hub 23, a synchronous rotating disc 24 connecting the 13 variable inlet guide vanes 22, an eccentric rod 25, a rocker 26, and multiple ball bearings, etc. Each variable inlet guide vane 22 rotates around the vane shaft 21 through two ball bearings (one ball bearing is respectively arranged on the housing assembly 4 and the inlet guide vane hub 23) so as to change the deflection angle of the 13 equally-spaced variable inlet guide vanes 22. Only one of the 13 vane shafts 21 is the driving shaft, and the rest are driven shafts. They are driven through the eccentric rod 25, the rocker 26, and the synchronous rotating disc 24 (the synchronous rotating disc 24 is of a disc structure, and there are 13 protrusions on its circumferential surface for connecting with the eccentric rod 25 through the rocker 26 with spherical joint bearings at both ends). When the vane shaft 21 connected to the inlet guide vane control machine assembly 6 rotates self-driven, the remaining 12 vane shafts 21 connected to the synchronous rotating disc 24 are driven to rotate synchronously through the transmission of the eccentric rod 25, the rocker 26, and the synchronous rotating disc 24. The synchronous rotation principle between any two variable inlet guide vanes 22 is similar to that of a planar double-rocker mechanism. Among them, the vane shaft 21 is fixedly connected to the eccentric rod 25, while the connection between the eccentric rod 25 and the rocker 26 is a movable joint connection, and the connection between the rocker 26 and the synchronous rotating disc 24 is a movable joint connection. When the vane shaft 21 is driven by the inlet guide vane control machine assembly 6 to rotate self-driven, the movable joint at the connection between the eccentric rod 25 and the rocker 26 makes a circular motion around the vane shaft 21, and the movable joint at the connection between the rocker 26 and the synchronous rotating disc 24 generates a corresponding spatial displacement. Since the synchronous rotating disc 24 is a rigid part, the same spatial displacement will be generated at the protrusion positions corresponding to the remaining 12 vane shafts 21 on the synchronous rotating disc 24. This spatial displacement is converted into the rotation of the remaining 12 vane shafts 21 through the rocker 26 and the eccentric rod 25. In the present invention, the rotation range of the vane shaft 21 is 30° to 90°.

[0046] The moving vane assembly 3 is composed of blades serving as moving vanes and a rotor hub, etc. The rotor hub is connected to the flange on the fan drive shaft 71. There are splines inside the fan drive shaft 71, and external power is input to the fan drive shaft 71 through the splines to drive the rotor hub and the blades to rotate together.

[0047] The housing assembly 4 is a cylindrical housing, and a surge prevention hole structure is added to the housing assembly 4, which can ensure that the air flow of the comprehensive cooling fan is within a certain range to ensure the stable operation of the cooling fan, thereby avoiding affecting the normal operation of the comprehensive cooling fan due to surging. For example Figure 1, the housing assembly 4 is divided into two sections. The housing corresponding to the variable inlet guide vane assembly 2 is the first section, and the housing corresponding to the moving blade assembly 3 and the rear guide stationary vane assembly 5 is the second section. The two sections of the housing are connected by a flange structure. The surge prevention holes are provided on the second section of the housing and are located within the rotation area of the blades in the moving blade assembly 3. The surge prevention holes are specifically a circle of waist-shaped through holes that penetrate the wall thickness of the housing assembly 4, and the axis of the waist-shaped through holes is along the radial direction of the housing assembly 4.

[0048] The rear guide stationary vane assembly 5 consists of blades serving as stationary vanes and a wheel hub, etc. The wheel hub is a double-layer rotating body structure, where the outer layer is connected to the blade roots of the blades, and the inner layer serves as a cavity through which the fan drive shaft 71 passes. The blade tips of the blades are connected to the housing assembly 4. The rear guide stationary vane assembly 5 converts the kinetic energy of the air flow passing through the integrated cooling fan into pressure energy, giving it the required speed and direction and improving the utilization efficiency of the air flow.

[0049] The inlet guide vane control machine assembly 6 includes a bracket, a crank, an electric actuator, a control rod, etc. The bracket is installed on the housing assembly 4 through studs. A boss for installing the control rod and the crank is provided on the bracket. As the operating rod of the electric actuator moves, the operating rod drives the crank to drive the blade shaft 21 to rotate, thereby changing the angle of the variable inlet guide vane 22.

[0050] The fan drive shaft 71 in the fan drive shaft assembly 7 is a stepped shaft with a flange at one end. The fan drive shaft assembly 7 includes the fan drive shaft 71, a thrust ring, a spacer sleeve 72, bearings 73, and a bearing cover. The spacer sleeve 72 is sleeved outside the fan drive shaft 71 to separate the two bearings 73. The inner rings of the two bearings 73 cooperate with the fan drive shaft 71, and the outer rings cooperate with the inner rotating structure of the wheel hub in the rear guide stationary vane assembly 5. The moving blade assembly 3 is connected to the flange of the fan drive shaft 71 through bolts. A spline is provided inside the fan drive shaft 71 and is connected to the output shaft of the main reducer.

[0051] The housing assembly 4, the wheel hub in the rear guide stationary vane assembly 5, and the rotor wheel hub in the moving blade assembly 3 are made of magnesium alloy. The fan drive shaft 71 is made of stainless steel. The remaining components are connected together by connection methods such as bolts.

[0052] As Figure 6 shown, it is a schematic structural diagram of the fan drive shaft assembly 7. The fan drive shaft 71 is a stepped shaft with a flange at one end. The fan drive shaft assembly 7 includes the fan drive shaft 71, a thrust ring, a spacer sleeve 72, bearings 73, and a bearing cover. The moving blade assembly 3 is connected to the outer flange of the fan drive shaft 71 in the fan drive shaft assembly 7 through bolts. A spline is provided inside the fan drive shaft 71 and is connected to the output shaft of the main reducer.

[0053] As Figure 7As shown in the figure, it is a schematic structural diagram of the inlet guide vane control machine assembly 6, which consists of a bracket, a crank, an electric actuator, a joystick, etc. The bracket is installed on the outer surface of the assembly housing 4 through studs. A boss of the joystick and the crank is installed on the bracket. As the operating rod of the electric actuator moves, the crank converts the linear displacement of the operating rod into the rotation of the vane shaft 21, thereby changing the angle of a variable inlet guide vane 22. The circumferential rotation of the synchronous rotating disk 24 drives the other variable inlet guide vanes 22 to deflect by the same angle in cooperation.

[0054] As Figure 8 shown in the figure, it is a schematic structural diagram of the variable inlet guide vane assembly 2, which consists of 13 equally spaced variable inlet guide vanes 22, an inlet guide vane wheel housing 23, a synchronous rotating disk 24 connecting the variable inlet guide vanes 22, an eccentric rod 25, a rocker 26 (spherical joint bearings are installed at both ends), and ball bearings assembled at the upper and lower ends of the vane shaft 21. The variable inlet guide vane 22 rotates relative to the housing assembly 4 and the inlet guide vane wheel housing 23 through the ball bearing and the vane shaft 21, thereby changing the blade angle at the inlet of the integrated cooling fan. In the design scheme of the present invention, only one set of inlet guide vane control machine assembly 6 is required to control all the variable inlet guide vanes 22, reducing the control complexity and self-weight.

[0055] As Figure 5 , the angle of the variable inlet guide vane 22 is controlled by an aircraft engineer. The aircraft engineer uses a push switch to turn on the electric actuator. The operating rod of the actuator moves in the X direction ( Figure 2 the direction horizontally to the left in the front view), and the crank connected to the operating rod drives the vane shaft 21 to rotate. The end of the eccentric rod 25 at the lower end of the vane shaft 21 (the end far from the vane shaft 21) generates an eccentric circular motion. The eccentric rod 25 is connected to the synchronous rotating disk 24 through a rocker 26 with a spherical joint bearing at each end. The eccentric rod 25 rotates and drives the rocker 26 to drive the synchronous rotating disk 24 to generate a spatial displacement, thereby driving the other variable inlet guide vanes 22 to rotate by a certain angle simultaneously, finally changing the output wind pressure and flow rate, changing the heat exchange efficiency, and maintaining the oil temperature set by the oil-gas heat exchange system.

[0056] The above is only a specific embodiment 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 those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claimed claims.

Claims

1. A comprehensive cooling fan suitable for multiple working conditions, characterized by: The invention comprises a variable inlet guide vane assembly (2) and an inlet guide vane control machine assembly (6), wherein: The variable inlet guide vane assembly (2) is located at one side of the air inlet of the integrated cooling fan, and is mainly composed of a blade shaft (21), a variable inlet guide vane (22), an inlet guide vane wheel shell (23), a synchronous rotating disk (24), an eccentric rod (25) and a rocker (26), wherein: The inlet guide blade wheel shell (23) is a cylindrical shell, the synchronous rotating disk (24) is located on the inner side of the inlet guide blade wheel shell (23), a plurality of blade shafts (21) are arranged along the radial direction of the inlet guide blade wheel shell (23), the center angles between adjacent blade shafts (21) are equal, the first end of the blade shaft (21) passes through the inlet guide blade wheel shell (23) and is rotatably connected to the inlet guide blade wheel shell (23), and the second end extends to the outer side of the inlet guide blade wheel shell (23), the variable inlet guide blade (22) is assembled on the blade shaft (21) and uses the blade shaft (21) as a rotating shaft, the first end of the blade shaft (21) is connected to the synchronous rotating disk (24) via an eccentric rod (25) and a rocker (26) with spherical joint bearings at both ends, and the eccentric rod (25) and the rocker (26) are connected to one of the spherical joint bearings, and the synchronous rotating disk (24) and the rocker (26) are connected to the other spherical joint bearing; The inlet guide vane control machine assembly (6) comprises an actuator, the actuating end of which is connected to the second end of one of the plurality of vane shafts (21).

2. The comprehensive cooling fan applicable to multiple working conditions according to claim 1, characterized in that: Also includes: A shell assembly (4), wherein the shell assembly (4) is a cylindrical cavity shell, wherein the axial first end and the axial second end of the shell assembly (4) respectively form an air inlet and an air outlet, the variable inlet guide vane assembly (2) is located in the inner cavity of the axial first end of the shell assembly (4), the inlet guide vane control machine assembly (6) is mounted on the outer surface of the shell assembly (4), and the second end of the blade shaft (21) passes through the shell assembly (4) and is connected to an actuator of the inlet guide vane control machine assembly (6).

3. The comprehensive cooling fan applicable to multiple working conditions according to claim 2, characterized in that: Also includes: A fairing (1), the fairing (1) being arranged in a cavity at a first axial end of a housing assembly (4) and connected to an end surface on a side of an inlet guide vane wheel shell (23) in a variable inlet guide vane assembly (2) corresponding to an air inlet; A moving blade assembly (3), the moving blade assembly (3) being arranged in a cavity of a shell assembly (4) and being located on a side of an inlet guide blade wheel shell (23) in a variable inlet guide blade assembly (2) corresponding to an air outlet, an anti-surge hole penetrating the radial wall thickness direction of the shell assembly (4) being arranged on a circumferential surface of the shell assembly (4) corresponding to the position of the moving blade assembly (3), and a plurality of blades being evenly distributed on the circumferential surface of the moving blade assembly (3); A rear guide vane assembly (6), the rear guide vane assembly (6) being arranged in a cavity of the housing assembly (4) and between the moving blade assembly (3) and the second axial end of the housing assembly (4), a plurality of blades being evenly distributed on the circumferential surface of the rear guide vane assembly (6), and the blade tips of the blades being connected to the housing assembly (4); A fan drive shaft assembly (7), wherein the first end of the fan drive shaft assembly (7) is located in the cavity of the housing assembly (4) and passes through the rear guide vane assembly (6) and is connected to the moving blade assembly (3).

4. The integrated cooling fan applicable to multiple working conditions according to claim 3 is characterized in that: The plurality of anti-surge holes are distributed at equal center angles on the same circumference of the circumferential surface of the housing assembly (4), and the circumference is located within a rotation area formed by the blade tips of the plurality of blades on the moving blade assembly (3) when the blades rotate around the fan drive shaft assembly (7).

5. The comprehensive cooling fan applicable to multiple working conditions according to claim 3 is characterized in that: The fan drive shaft assembly (7) is mainly composed of a fan drive shaft (71), a spacing sleeve (72) and a bearing (73), wherein: The fan drive shaft (71) is a hollow shaft, the outer surface of which is provided with a flange structure, and the inner surface of which is provided with a spline. The fan drive shaft (71) is connected to the moving blade assembly (3) via the flange structure. The inner rings of the two bearings (73) are assembled with the fan drive shaft (71), and the outer rings of the two bearings (73) are assembled with the rear guide vane assembly (6); The spacing sleeve (72) is sleeved on the fan driving shaft (71) and is located between the two bearings (73).

6. The comprehensive cooling fan applicable to multiple working conditions according to claim 1, characterized in that: The actuator's execution end is connected to the second end of one of the plurality of blade shafts (21) via a crank.

7. The comprehensive cooling fan applicable to multiple working conditions according to claim 1, characterized in that: The housing assembly (4), the moving blade assembly (3) and the rear guide and stator blade assembly (6) are made of magnesium-aluminum alloy, and the fan drive shaft assembly (7) is made of stainless steel.

8. A helicopter engine oil-gas heat exchange system, characterized in that: Including the comprehensive cooling fan applicable to multiple working conditions as described in claim 3.

9. A helicopter engine oil-gas heat exchange method, characterized in that: include: By adopting the integrated cooling fan applicable to multiple working conditions as described in claim 3, the variable inlet guide vane (22) in the variable inlet guide vane assembly (2) is adjusted to rotate around the blade shaft (21) through the inlet guide vane control machine assembly (6), thereby realizing the change of the air flow rate and air pressure of the integrated cooling fan, thereby changing the oil-gas heat exchange power, and finally controlling the oil temperature after the oil-gas heat exchange to be within the set range.

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