CN116513468A - Drainage device for improving performance of helicopter by utilizing coupling of internal flow field and external flow field and helicopter - Google Patents

Abstract

The invention discloses a drainage device for improving the performance of a helicopter by utilizing coupling of an internal flow field and an external flow field and the helicopter, wherein the drainage device comprises: sliding support frame, groove installation fixed wing group and spiral cross-flow fan. The sliding support frame is arranged in a fuselage cabin of the helicopter and is in sliding telescopic arrangement so as to drive the groove stationary vane group and the spiral cross flow fan to extend to be close to the air inlet through the mounting opening. The upper end concave of the groove installation fixed wing group forms an installation groove, and the spiral cross flow fan is rotationally installed in the installation groove and is used for rotating under the effect of rotor downward washing generated when the helicopter rotor rotates, so that the rotor downward washing and forward airflow or side flying vortex are sucked into the installation groove to form accelerated airflow, and the accelerated airflow is accelerated to be discharged out of the installation groove and then enters the air inlet. The drainage device can increase the air inflow and the air inflow pressure of the engine, reduce the installation loss of most of the engine power caused by the coupling of the internal and external processes of the helicopter, and improve the output power of the engine.

Description

Drainage device and helicopter for improving helicopter performance by coupling internal and external flow fields

technical field

The invention relates to the technical field of engines, in particular to a drainage device for improving the performance of a helicopter by coupling internal and external flow fields. In addition, the present invention also relates to a helicopter including the above-mentioned drainage device for improving the performance of the helicopter by coupling the internal and external flow fields.

Background technique

The interference of the rotor downwash of conventional helicopters on the fuselage of the helicopter reduces the aerodynamic efficiency of the helicopter's outflow, and it also has a certain impact on the engine intake. For conventional helicopters, the number of installed engines is between 1 and 3. For helicopters with a single engine arrangement, the air inlet of the turboshaft engine is generally arranged in the middle of the top of the fuselage, facing the direction of incoming flow, and the rotor is washed down. The flow at this place produces a large swirl flow, resulting in installation loss; for helicopters equipped with twin-engine and triple-engine turboshaft engines, the engine air inlets are generally arranged on the upper sides of the fuselage, and the air inlet airflow is located under the rotor. Under the washing flow, there is a certain swirl flow and the difference between the inlets is large. The swirl flow will bring a certain amount of installation loss. At the same time, because the turboshaft engine needs to meet the multi-engine trim requirements, the inconsistent state of each engine will bring additional losses. Generally speaking, when the internal and external flow fields of the helicopter are coupled, the downwash flow of the helicopter rotor will cause an installation loss of about 3-6% of the engine power.

In the existing helicopter design process, due to the great difficulty in the optimization design technology of the internal and external flow coupling involved in the installation loss, how to reduce the loss in this area is basically not considered in the design of the helicopter, and the design is usually carried out in a mode with ample engine power. In terms of turboshaft engine design, although some scholars and engineering designers have carried out work to reduce the loss coefficient of the intake port or particle separator to increase the engine output power, the improvement has not been large, and the helicopter internal and external flow has not been adopted. A method and apparatus for actively increasing performance by means of field coupling. In other aspects, for the forward flight state (corresponding to the cruising state of the turboshaft engine), a diversion groove is designed in front of the air inlet, and the air intake is improved by using the fuselage shape to merge into a channel to guide the airflow into the air inlet. Reduce the loss, and for the helicopter, its power demand is the largest in the hovering state of the helicopter, and the power loss caused by the coupling of internal and external flow in this state has a greater impact on the ability of the helicopter to hover and take off.

The rotor flow field of existing conventional helicopters has an impact on the whole aircraft, most of which are aerodynamic interference, which reduces aerodynamic efficiency and also affects engine intake. The greater the intake pressure and flow rate, the more beneficial it is to the engine. Conventional engines are either installed in the middle of the top of the fuselage, the air intake is directly facing the incoming flow, and the forward speed directly rushes the air into the engine; The sides of the fuselage are on the upper side, and the air inlet is buried inside the fuselage, and the air is sucked in by the negative pressure of the engine. Regardless of the two types of engine installation methods, due to the addition of the rotating airflow of the rotor, the coupling of the internal and external flow fields of the helicopter causes an installation loss of about 3-6% of the engine power.

Contents of the invention

The invention provides a drainage device and a helicopter that utilize the coupling of internal and external flow fields to improve the performance of the helicopter, so as to solve the technical problem existing in existing helicopters that the coupling of the internal and external flow fields of the helicopter leads to the loss of engine power installation due to the addition of the rotating airflow of the rotor.

The technical scheme that the present invention adopts is as follows:

A drainage device that uses the coupling of internal and external flow fields to improve the performance of a helicopter. An installation port is provided on the fuselage of the helicopter close to its air inlet. The drainage device includes: a sliding support frame that acts as an installation support, and a Grooved stabilizer group, spiral cross-flow fan installed on the grooved stabilizer group; sliding support frame is set in the fuselage cabin of the helicopter, and slides and expands to drive the grooved stabilizer group and the spiral cross-flow fan Extend through the installation port close to the air inlet; the upper end of the groove stabilizer group is concave to form a mounting groove, and the spiral cross-flow fan is rotated and installed in the mounting groove for the rotor downwash effect generated when the helicopter rotor rotates The downward rotation is to suck the rotor downwash flow and forward flight airflow or side flight spoiler into the installation groove to form an accelerated airflow, and make the accelerated airflow accelerate out of the installation groove and enter the air inlet.

Further, the spiral cross-flow fan includes a mounting shaft, a plurality of sets of supporting rotors fixed on the mounting shaft at intervals along the length direction of the mounting shaft, and a plurality of helical blades; On the grooved stabilizer wing group; multiple helical blades are arranged at intervals along the circumferential direction, and each helical blade is fixed on multiple sets of supporting rotors, and extends in a helical shape along the axial direction of the installation rotating shaft.

Further, the supporting rotor includes a mounting plate fixed on the outer circle of the mounting shaft, and a plurality of sets of supporting pieces arranged at intervals along the circumference of the mounting plate; one end of each supporting plate is fixed to the outer peripheral surface of the mounting plate, and the opposite One end extends freely toward the helical blade, or is fixed to the lower surface of the helical blade to support the helical blade.

Further, the helical blade is a positive or reverse helical blade with an installation angle of 20°-90°; the number of helical blades is 3-18; the helical direction of the helical blade is set in accordance with the flow direction of the downwash flow of the rotor, so that the downwash of the rotor The washing flow and the forward flying airflow or the side flying spoiler flow are sucked into the installation groove; the turning direction of the helical blade is set in accordance with the flow direction of the accelerated airflow.

Further, the groove stabilizer wing group is also provided with a guide slope, the guide slope is located on the outflow side of the installation groove, and its upper end is connected with the upper end of the outflow side of the installation groove in a transitional arc, and the guide slope is used to accelerate the airflow The guide corresponds to the air inlet provided; the helical blade and the guide slope have an included angle of 10°-90°.

Further, the installation groove is an arc groove with a concave arc surface; the width of the spiral blade does not exceed 1/4 of the diameter of the arc surface of the arc groove; the maximum thickness of the spiral blade does not exceed 20% of its width ;The height of the inlet side of the installation groove is lower than the height of the guide slope, and the angle formed by the line between the top surface of the inlet side and the top surface of the guide slope and the horizontal plane is not greater than 15°, and the top surface of the intake side and the guide slope The distance between the connecting line between the top surfaces and the center of the arc surface is less than 1/3 of the radius of the arc surface.

Furthermore, the helical cross-flow fan also includes a one-way clutch for making the installation shaft rotate in only one direction; the one-way clutch is fixed on the outer circle of the installation shaft.

Further, the grooved stabilizer set includes the stabilizer body, two open end plates for supporting and installing the rotating shaft, and bearing seats arranged on each open end plate; the top of the stabilizer body is concaved to form a mounting groove, The installation groove extends along the length direction of the stabilizer body and connects its two ends, so that the two ends of the stabilizer body form a leading edge and a rear edge respectively, and one of the outer side walls of the stabilizer body forms a guiding slope; the two open ends The plates are respectively arranged at both ends of the stabilizer body, and are respectively fixed to the leading edge or the trailing edge of the corresponding ends; the two ends of the installation rotating shaft are respectively rotatably supported on the bearing seats of the two open end plates.

Further, the open end plate is provided with vent holes set through the plate surface; the grooved stabilizer group also includes flaps whose two ends are respectively hinged to the two open end plates, and the flaps are located on the bottom side of the guide slope , and extend along the extension direction of the helical blade.

According to another aspect of the present invention, there is also provided a helicopter, including a fuselage, and any one of the above-mentioned drainage devices utilizing internal and external flow field coupling to improve the performance of the helicopter; the fuselage is provided with air inlets and installation ports ; The drainage device is arranged in the fuselage compartment of the fuselage, and slides close to the air inlet of the air inlet through the installation port.

The present invention has the following beneficial effects:

The drainage device of the present invention makes full use of the characteristics of the downwash flow of the existing helicopter rotor, and introduces the airflow boost at the coupling part of the internal and external flow fields into the engine, thereby increasing the intake air volume and intake pressure of the engine, and reducing the coupling of the internal and external flow of the helicopter. Most of the installation loss of the engine power improves the engine output power by more than 2%; the drainage device of the present invention has a wide range of applications, can be used on conventional helicopters, and can also be applied to the air intakes of other aircraft that use turboshafts and turboprop engines. It can be applied to single-engine, double-engine or multi-engine helicopters, and has broad application prospects; when working, the downwash flow of the rotor rotates in the circumferential direction and flows downward at a high speed, and the flow field is basically symmetrical when hovering. When flying forward, the left and right flow fields of the fuselage are asymmetrical. The device of the present invention adopts different cross-flow fan helical twisting directions for the engine inlets on both sides of the helicopter fuselage, so that it can adapt to the different flow directions of the rotor downwash on different sides of the engine. Difference: the device of the present invention has small additional cost, light weight, and does not require additional power, and the wind resistance caused by the airflow blockage caused by the downwash flow of the rotor and the forward flight is relatively small, accounting for less than 0.5% of the wind resistance of the whole machine, which can be ignored ;

The helicopter of the present invention can not only increase the intake air volume and intake pressure of the engine, reduce the installation loss of most of the engine power caused by the coupling of the internal and external processes of the helicopter, and increase the output power of the engine by more than 2%; and has a wide range of applications, and can be used in It can also be applied to the air inlet of other aircraft with turboshaft and turboprop engines on conventional helicopters. It can be applied to single-engine, twin-engine or multi-engine helicopters. It has broad application prospects; it can also be adapted to rotor washing The difference caused by different flow directions on different sides of the engine; the device of the present invention has small additional cost, light weight, and does not require additional power. Accounting for less than 0.5%, it can be ignored.

In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. Hereinafter, the present invention will be described in further detail with reference to the drawings.

Description of drawings

The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention. In the attached picture:

Fig. 1 is a schematic diagram of the spatial structure of a drainage device utilizing internal and external flow field coupling to improve helicopter performance in a preferred embodiment of the present invention;

Fig. 2 is a schematic diagram of the spatial structure of the spiral cross-flow fan in Fig. 1;

Fig. 3 is a schematic diagram of the spatial structure of the grooved stabilizer group in Fig. 1;

Fig. 4 is a cross-sectional schematic diagram of the drainage device in Fig. 1;

Fig. 5 is a schematic diagram of the working principle of the spiral cross-flow fan;

Fig. 6 is the flow field pressure nephogram of the helical cross-flow fan;

Fig. 7 is a schematic diagram of the main parameters affecting the performance of the drainage device;

Fig. 8 is a schematic diagram of the spatial structure of the helicopter in the preferred embodiment of the present invention.

illustration

10, helicopter; 101, air inlet; 11, fuselage; 21, installation joint; 30, groove stabilizer group; 301, installation groove; 3010, circular arc surface; 302, guiding slope; 31, stabilizer body ; 32, open end plate; 321, ventilation hole; 33, bearing seat; 34, flap sheet; 40, spiral cross-flow fan; 41, install rotating shaft; 42, support rotor; 421, install plate; 422, support sheet; 43, spiral blade; 44, one-way clutch.

Detailed ways

The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

With reference to Fig. 1 and Fig. 8, the preferred embodiment of the present invention provides a kind of drainage device that utilizes the coupling of internal and external flow fields to improve the performance of the helicopter. On the helicopter 10, an installation port is provided on the fuselage 11 close to its air inlet 101, and the drainage device It includes: a sliding support frame for installation and support, a groove stabilizer set 30 fixed on the slide support frame, and a spiral cross-flow fan 40 installed on the groove stabilizer set 30 . The sliding support frame is arranged in the fuselage compartment of the helicopter 10 , and the sliding and telescopic arrangement is used to drive the grooved stabilizer assembly 30 and the spiral cross-flow fan 40 to extend close to the air inlet 101 through the installation opening. The upper end of the groove stabilizer group 30 is recessed to form a mounting groove 301, and the spiral cross-flow fan 40 is rotated and installed in the mounting groove 301, so as to rotate under the action of the rotor downwash flow generated when the rotor of the helicopter 10 rotates, so as to The rotor downwash flow and the forward flight airflow or the side flight spoiler flow are sucked into the installation groove 301 to form an accelerated airflow, and the accelerated airflow is accelerated out of the installation groove 301 and enters the air inlet 101.

During work, the sliding support frame starts, and the sliding drives the grooved stabilizer group 30 and the spiral cross-flow fan 40 to pass through the installation opening provided on the fuselage 11, and then arrive at the air inlet 101 of the air inlet provided on the corresponding side of the helicopter 10, During actual design, how many air inlets are arranged on the fuselage 11, how many groups of drainage devices are arranged accordingly; The downwash flow and the forward flying airflow or the side flying spoiler flow are sucked into the installation groove 301 to form an accelerated airflow, and the accelerated airflow is driven by the spiral cross-flow fan 40, and is accelerated and discharged from the exhaust side of the installation groove 301 and enters the corresponding set. air inlet 101 .

The drainage device of the present invention makes full use of the characteristics of the downwash flow of the existing helicopter rotor, and introduces the airflow boost at the coupling part of the internal and external flow fields into the engine, thereby increasing the intake air volume and intake pressure of the engine, and reducing the coupling of the internal and external flow of the helicopter. Most of the installation loss of the engine power improves the engine output power by more than 2%; the drainage device of the present invention has a wide range of applications, can be used on conventional helicopters, and can also be applied to the air intakes of other aircraft that use turboshafts and turboprop engines. It can be applied to single-engine, double-engine or multi-engine helicopters, and has broad application prospects; when working, the downwash flow of the rotor rotates in the circumferential direction and flows downward at a high speed, and the flow field is basically symmetrical when hovering. When flying forward, the left and right flow fields of the fuselage are asymmetrical. The device of the present invention adopts different cross-flow fan helical twisting directions for the engine inlets on both sides of the helicopter fuselage, so that it can adapt to the different flow directions of the rotor downwash on different sides of the engine. Difference: the device of the present invention has small additional cost, light weight, and does not require additional power, and the wind resistance caused by the airflow blockage caused by the downwash flow of the rotor and the forward flight is relatively small, accounting for less than 0.5% of the wind resistance of the whole machine, which can be ignored .

Optionally, as shown in FIG. 2 , the helical cross-flow fan 40 includes an installation shaft 41 , multiple sets of supporting rotors 42 fixed on the installation shaft 41 at intervals along the length direction of the installation shaft 41 , and multiple helical blades 43 . The two ends of the installation shaft 41 are rotatably supported on the groove stabilizer set 30 at the two ends of the installation groove 301 . A plurality of helical blades 43 are sequentially arranged at intervals along the circumferential direction, and each helical blade 43 is fixed on a plurality of sets of supporting rotors 42 , and extends helically along the axial direction of the mounting shaft 41 .

In this alternative solution, as shown in FIG. 2 , the supporting rotor 42 includes a mounting plate 421 fixed on the outer circumference of the mounting shaft 41 , and multiple sets of supporting pieces 422 arranged at intervals along the circumference of the mounting plate 421 . One end of each support piece 422 is fixed to the outer peripheral surface of the mounting plate 421 , and the opposite end thereof extends freely toward the helical blade 43 , or is fixed to the lower surface of the helical blade 43 to support the helical blade 43 . In the specific embodiment of this option, as shown in Figure 2, the supporting rotor includes two sets of turbine rotors with the same structure and a set of support frames, and one set of turbine rotors is arranged close to the end of the groove stabilizer wing set 30 . The supporting piece 422 of the turbine rotor is a short blade with an airfoil, and its part is fixed to the lower surface of the helical blade 43; the supporting piece 422 of the support frame is set corresponding to the number of the helical blade 43, and each supporting piece 422 is fixedly supporting a helical blade 43.

In this optional solution, as shown in FIG. 2 , the cross section of the helical blade 43 may be rectangular, willow-shaped, crescent-shaped, or airfoil-shaped. The helical blade 43 is a forward or reverse helical blade with an installation angle of 20° to 90°; the installation angle is set to allow the blade to drive the airflow into the groove stabilizer group 30 when the blade rotates. Pulsating vibration, that is, the linear or small-angle spiral blades will compress the airflow when passing the guide slope 302 closest, and release the pressure after leaving, causing vibration, and the setting of this angle range avoids the occurrence of vibration. The number of helical blades 43 is 3 to 18 pieces; when the number of helical blades 43 is within this range, the aerodynamic performance is the best, and exceeding this range will cause insufficient or too much solidity of the area occupied by the blades, resulting in poor aerodynamic force and flow field performance. decline. The helical direction of the helical blade 43 is set along the flow direction of the rotor downwash, so as to suck the rotor downwash and forward airflow or side flight disturbance into the installation groove 301 . Similarly, the rotation of the helical blade 43 is set in accordance with the flow direction of the accelerated airflow, so as to rotate by itself under the action of the accelerated airflow.

In this alternative, as shown in Figure 2 and Figure 3, the groove stabilizer wing group 30 is also provided with a guide slope 302, the guide slope 302 is located on the outflow side of the installation groove 301, and its upper end is in contact with the installation groove 301 The upper end of the outflow side is connected by a circular arc transition, and the guide slope 302 is used to guide the accelerated airflow to the corresponding air inlet 101; during operation, the guide slope 302 is the rear end of the upper wing surface of the installation groove 301 stabilizer, mainly used for The airflow propelled by the helical blade 43 is extracted to accelerate away from the installation groove 301 . The helical blade 43 has an included angle of 10° to 90° with the guide inclined surface 302; since the helical blade 43 has a forward or reverse helix with an installation angle of 20° to 90°, this angle is caused, for the sake of less air flow Pulsating shock vibration.

In this optional solution, as shown in FIGS. 4-7 , the installation groove 301 is an arc groove with a concave arc surface 3010 . The width of the helical blade 43 is not more than 1/4 of the diameter of the arc surface 3010 of the arc groove; this setting is to ensure that there is enough space in the arc groove to generate an eccentric low-pressure vortex belt to drain the high-pressure air flow from the outside , resulting in more airflow to the intake tract. The maximum thickness of the helical blade 43 is not more than 20% of its width; this setting is to allow enough airflow to pass through the high-speed rotating helical blade 43 and flow to the guide slope 302, so that more airflow enters the air inlet. The height of the air intake side of the installation groove 301 is lower than the height of the guide slope 302, and the angle formed between the top surface of the air intake side and the top surface of the guide slope 302 and the horizontal plane is not more than 15 °, and the top surface of the air intake side The distance between the line between the top surfaces of the guide slope 302 and the center of the arc surface 3010 is less than 1/3 of the radius of the arc surface 3010; Under the action, a part accelerates through the guide slope 302, and a part rotates to generate an eccentric vortex, so that the aerodynamic efficiency of the whole device is better.

Preferably, as shown in FIG. 2 , the helical cross-flow fan 40 further includes a one-way clutch 44 for making the installation rotating shaft 41 rotate in only one direction. The one-way clutch 44 is fixed on the outer circle of the rotating shaft 41 . When designing, the one-way clutch 44 turns to the design that must make the drainage device absorb airflow from the outside.

Optionally, the drainage device of the present invention also includes a drive source connected to the helicopter, which is connected to the installation shaft 41 to drive it to rotate, and then drives the helical cross-flow fan 40 to rotate.

The working principle of the drainage device of the present invention is shown in Figure 5 and Figure 6, under the rotation of the spiral cross-flow fan 40, the whole device greatly absorbs the airflow in all directions, and the airflow will be collected into the spiral cross-flow fan 40, and then pass through the blades (supporting sheet 422 and the helical blade 43) under the effect of flowing along the trend, when the blade passes the guide inclined surface 302, it breaks away; due to the effect of the installation groove 301 and the rotating blade, the air flow forms a low-pressure vortex that deviates from the center of the circle and goes downward in the whole drainage device. A low static pressure area is also formed at the place where the airflow passes through the guide slope 302. Since the reverse thrust is obtained while the accelerated airflow is discharged from the guide slope 302, the drainage device has a larger lift-to-drag ratio; under less energy consumption, the drainage device absorbs The energy of the external airflow can convert the direction of the airflow and obtain the accelerated rotation of the helical cross-flow fan 40; and the helical blade 43 is helical, which can make better use of the lateral velocity and circumferential velocity of the rotor downwash flow, and absorb the energy conversion of the rotor downwash flow It is the airflow energy entering the air inlet; the addition of the turbine rotor can better absorb the lateral airflow into the installation groove 301, and then transmit it to the guide slope 302 for output through the action of the helical blade 43.

Optionally, as shown in FIG. 3 , the groove stabilizer assembly 30 includes a stabilizer body 31 , two open end plates 32 for supporting and installing the rotating shaft 41 , and a bearing seat 33 arranged on each open end plate 32 . The top of the stabilizer body 31 is recessed to form a mounting groove 301, and the mounting groove 301 extends along the length direction of the stabilizer body 31 to connect with its two ends, so that the two ends of the stabilizer body 31 respectively form a leading edge 311 and a trailing edge, And one of the outer sidewalls of the stabilizer body 31 forms a guiding slope 302 . The two open end plates 32 are separately disposed at two ends of the stabilizer body 31 and are respectively fixed to the leading edge or the trailing edge of the corresponding ends. Both ends of the rotating shaft 41 are respectively rotatably supported on the bearing seats 33 of the two open end plates 32 .

In this optional solution, as shown in FIG. 3 , the open end plate 32 is provided with a vent hole 321 set through the plate surface, and the vent hole 321 is used for ventilation, absorbing external airflow into the drainage device and guiding it to the air intake of the engine. The groove stabilizer set 30 also includes a flap piece 34 hinged to two open end plates 32 at both ends. The flap piece 34 is located at the bottom side of the guide slope 302 and extends along the extension direction of the helical blade 43 . During operation, the flap piece 34 is the trailing edge adjustment piece of the groove stabilizer wing group 30, works like a flap, and can be angled deflected around the guide slope 302 by manipulation to realize the flow direction of the guided airflow.

The drainage device of the present invention is easy to operate, and the angle of flaps 34 and the rotating speed of the spiral cross-flow fan 40 can be automatically adjusted by adopting the present invention, which can accompany the change of the wind speed and direction of the downwash flow of the helicopter caused by the change of the load of the rotor disc of the helicopter, as well as the different flight of the helicopter. speed or according to the change of the rotor downwash wind direction caused by the helicopter's hovering and forward flight at small and medium speeds, and maintain a sufficient amount of airflow to the inlet; When the air in X, Y, and Z directions enters the device of the present invention, it will push the spiral cross-flow fan 40 to rotate normally, and the spiral cross-flow fan 40 will guide the airflow into the air inlet.

Optionally, as shown in FIG. 3 , the sliding support frame includes a mounting joint 21 fixed to the end of the grooved fin assembly 30 , and a telescopic cylinder connected to the mounting joint 21 . The telescopic cylinder is arranged in the fuselage compartment of the fuselage 11, stretches out the fuselage when working, and is stored in the fuselage compartment when not working.

Referring to FIG. 8 , a preferred embodiment of the present invention also provides a helicopter, including a fuselage 11 , and any of the above-mentioned drainage devices that use internal and external flow field coupling to improve the performance of the helicopter. The fuselage 11 is provided with an air inlet and an installation port. The drainage device is arranged in the fuselage compartment of the fuselage 11 and slides close to the air inlet 101 of the air inlet through the installation opening. The helicopter of the present invention, owing to comprise as above-mentioned any one utilizes the drainage device that utilizes internal and external flow field coupling to improve helicopter performance, so it can increase the air intake volume and air intake pressure to engine, reduce the engine power that helicopter internal and external process coupling causes Most of the installation loss can increase the engine output power by more than 2%; and it has a wide range of applications. It can be used not only on conventional helicopters, but also on the air intake of other aircraft with turboshaft and turboprop engines. It can also be applied to single-engine , can also be used on twin-engine or multi-engine helicopters, and has broad application prospects; it can also adapt to the difference caused by the flow direction of the rotor downwash on different sides of the engine; the device of the present invention has small additional cost, light weight, and does not require additional power. The wind resistance caused by rotor downwash and airflow blockage caused by forward flight is relatively small, accounting for less than 0.5% of the overall wind resistance, which can be ignored.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (10)

1. A drainage device utilizing internal and external flow field coupling to improve helicopter performance is characterized in that, on the helicopter (10), an installation port is provided on the fuselage (11) close to its air inlet (101), and the drainage device comprises: A sliding support frame for installation and support, a groove stabilizer set (30) fixed on the slide support frame, and a spiral cross-flow fan (40) installed on the groove stabilizer set (30); The sliding support frame is arranged in the fuselage compartment of the helicopter (10), and the sliding and telescopic arrangement is used to drive the grooved stabilizer group (30) and the spiral cross-flow fan (40) to extend through the installation opening close to the air inlet (101) ; The upper end of the groove stabilizer wing group (30) is recessed to form a mounting groove (301), and the spiral cross-flow fan (40) is rotated and installed in the mounting groove (301), so as to generate Rotate under the action of the rotor downwash, so that the rotor downwash and forward flight airflow or side flight turbulence are sucked into the installation groove (301) to form an accelerated airflow, and the accelerated airflow is accelerated out of the installation groove (301) and then enters the inlet Air port (101). 2. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 1, characterized in that, The spiral cross-flow fan (40) includes a mounting shaft (41), multiple sets of supporting rotors (42) fixed on the mounting shaft (41) at intervals along the length direction of the mounting shaft (41), and a plurality of helical blades (43); The two ends of the installation shaft (41) are respectively rotated and supported on the groove stabilizer group (30) at the two ends of the installation groove (301); A plurality of helical blades (43) are sequentially arranged at intervals in the circumferential direction, and each helical blade (43) is fixed on multiple sets of supporting rotors (42), and extends helically along the axial direction of the installation shaft (41). 3. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 2, characterized in that, The supporting rotor (42) includes a mounting plate (421) fixed on the outer circle of the mounting shaft (41), and multiple sets of supporting pieces (422) arranged at intervals along the circumference of the mounting plate (421); One end of each support piece (422) is fixed to the outer peripheral surface of the mounting plate (421), and its opposite end extends freely toward the helical blade (43), or is fixed with the lower surface of the helical blade (43) to support the helical blade (43) ). 4. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 2, characterized in that, The helical blade (43) is a positive or reverse helical blade with an installation angle of 20° to 90°; The number of spiral blades (43) is 3 to 18; The helical direction of the helical blade (43) is arranged in accordance with the flow direction of the rotor downwash flow, so as to suck the rotor downwash flow and the forward flight airflow or the side flight spoiler into the installation groove (301); The turning direction of the helical blade (43) is set in compliance with the flow direction of the accelerated airflow. 5. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 2, characterized in that, The groove stabilizer wing group (30) is also provided with a guide slope (302), and the guide slope (302) is located on the outflow side of the installation groove (301), and its upper end is connected with the upper end of the outflow side of the installation groove (301). The circular arc transition connection, the guide slope (302) is used to guide the accelerated air flow to the corresponding air inlet (101); The helical blade (43) and the guide slope (302) have an included angle of 10°-90°. 6. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 5, characterized in that, The installation groove (301) is an arc groove with a concave arc surface (3010); The width of the spiral blade (43) does not exceed 1/4 of the diameter of the arc surface (3010) of the arc groove; The maximum thickness of the helical blade (43) does not exceed 20% of its width; The height of the air inlet side of the installation groove (301) is lower than the height of the guide slope (302), and the angle formed between the top surface of the air inlet side and the top surface of the guide slope (302) and the horizontal plane is not more than 15 °, The distance between the connection line between the top surface of the air intake side and the top surface of the guide inclined surface (302) and the center of the arc surface (3010) is less than 1/3 of the radius of the arc surface (3010). 7. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 2, characterized in that, The helical cross-flow fan (40) also includes a one-way clutch (44) for making the installation shaft (41) only rotate in one direction; The one-way clutch (44) is fixed on the outer circle of the rotating shaft (41). 8. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 5, characterized in that, The groove stabilizer wing group (30) includes the stabilizer wing body (31), two open end plates (32) for supporting and installing the rotating shaft (41), and bearing seats ( 33); The top of the stabilizer body (31) is recessed to form a mounting groove (301), and the mounting groove (301) extends along the length direction of the stabilizer body (31) to communicate with its two ends, so that the two ends of the stabilizer body (31) ends respectively form a leading edge (311) and a trailing edge, and one of the outer sidewalls of the stabilizer body (31) forms a guiding slope (302); Two open end plates (32) are respectively arranged at both ends of the stabilizer body (31), and are respectively fixed to the leading edge or the trailing edge of the corresponding end; The two ends of the rotating shaft (41) are installed to rotate respectively on the bearing seats (33) of the two open end plates (32). 9. The drainage device utilizing internal and external flow field coupling to improve helicopter performance according to claim 8, characterized in that, The open end plate (32) is provided with a ventilation hole (321) set through the plate surface; The groove stabilizer wing group (30) also includes flaps (34) whose two ends are respectively hinged with two open end plates (32), and the flaps (34) are positioned at the bottom side of the guide slope (302), and along the The extension direction of the helical blade (43) extends. 10. A helicopter, characterized in that it comprises a fuselage (11), and the drainage device utilizing internal and external flow field coupling to improve helicopter performance as described in any one of claims 1-9; The fuselage (11) is provided with an air inlet and an installation port; The drainage device is arranged in the fuselage compartment of the fuselage (11), and slides close to the air inlet (101) of the air inlet through the installation opening.