JP2016107958A - Boundary layer controller for aircraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a boundary layer controller configured to correspond to the intake side inner peripheral surface shape of a propulsion engine in an aircraft.SOLUTION: The boundary layer controller includes a venturi generator 10 configured such that when a communication path 9 is opened, a partition body 11 in the venturi generator is controlled by a control system to project from a housing part 12 formed into a recessed shape in an intake side inner peripheral surface, an airflow inlet 14 for capturing an airflow flowing in from the intake port front of a propulsion engine is formed toward the intake port front to be opened, a venturi passage 15 for increasing the speed of the airflow captured from the airflow inlet to reduce pressure is formed by a body bottom part 16, inner surfaces of both side parts and the intake side inner peripheral surface behind the airflow inlet, an airflow outlet for outputting the airflow lowered in pressure by increasing the flow speed is formed to be opened in the front of the intake side inner peripheral surface from the opening position of a discharge hole 7, when the communication path 9 is closed, the partition body is controlled by the control system to be housed in the housing part 12, and the bottom outer surface of the partition body and the intake aide inner peripheral surface constitute a continuous curve surface.SELECTED DRAWING: Figure 2

Description

  The present invention relates to a boundary layer control apparatus that controls a boundary layer such as a main wing that generates lift in an aircraft and a flap that increases lift during take-off and landing.

  Various technologies have been devised and put to practical use for the boundary layer control device that controls the boundary layer such as the main wing that generates lift in aircraft and the flap that increases lift during take-off and landing. A boundary layer control device has been devised by Japanese Patent Application No. 2014-141789.

  The technology devised in the above Japanese Patent Application No. 2014-141789 is provided with a single or a plurality of intake ports for taking in air on the upper surface of the main wing on the upper surface of the main wing of the aircraft. A first on-off valve that is controlled to open and close the intake port, and is provided with a single or multiple openings for releasing air taken in by the intake port on the intake side inner peripheral surface of the propulsion engine of the aircraft; The discharge hole is provided with a second on-off valve controlled by the aircraft control system to open and close the discharge hole, and the first on-off valve and the second on-off valve are controlled by the aircraft control system to be in an open state. In some cases, a communication path is provided between the intake port and the discharge hole to communicate between the intake port and the discharge hole.

Problems to be solved by the invention

  In the boundary layer control device Japanese Patent Application No. 2014-141789, the air pressure on the upper surface of the main wing is reduced by the suction force of the intake stroke in the propulsion engine, and the flow velocity of the air flowing on the upper surface of the main wing is set on the lower surface of the main wing. It is faster than the flow velocity of the flowing air and can achieve the effect of imparting high lift to the main wing, achieving the intended purpose, but with the various intake side inner peripheral shape of the propulsion engine in further aircraft In order to cope with this, another means for effectively releasing the air taken in by the intake port from the discharge hole on the inner peripheral surface of the intake side is required.

  It is an object of the present invention to provide a boundary level control apparatus that employs other discharge means that can cope with various intake side inner peripheral surface shapes of a propulsion engine in an aircraft.

Means for solving the problem

  In order to achieve the above object, in the boundary level control apparatus of the present invention, an intake port for taking in air from the upper surface of the main wing is provided at one or more locations on the upper surface of the main wing of the aircraft, and the intake port is provided with an aircraft. A first on-off valve that is controlled by the control system and opens and closes the intake port, and has a single or a plurality of discharge holes that release the air taken in by the intake port on the intake side inner peripheral surface of the aircraft propulsion engine. Provided with a second on-off valve that opens and closes the discharge hole controlled by the aircraft control system, and the first on-off valve and the second on-off valve are controlled by the aircraft control system to be in an open state. In a boundary level control device configured to provide a communication path that communicates between the intake port and the discharge hole sometimes between the intake port and the discharge hole, a venturi generating device when the first on-off valve and the second on-off valve are opened In The main body of the partition is controlled by the aircraft's control system and protrudes from the recessed portion provided on the inner peripheral surface of the intake side, and the air inlet that takes in the air flow flowing in from the front of the intake port of the propulsion engine faces the front of the intake port. Venturi passages that are formed and opened, and that lower the pressure by increasing the flow rate of the air flow taken from the air inlet at the rear of the air inlet, and the inner surfaces of the partition body bottom and both side surfaces and the intake side And an air outlet through which the low-pressure air flow flows out at a higher flow rate than the opening position of the discharge hole is formed in front of the intake side inner peripheral surface, and the first on-off valve and When the second on-off valve is closed, the partition main body is controlled by the aircraft's control system and stored in the storage section provided in a concave shape on the intake side inner peripheral surface, and the bottom outer surface of the partition main body has a continuous curved surface with the intake side inner peripheral surface. Configure bench Characterized by comprising a re-generator.

  The partition main body in the venturi generating device is integrally configured with a bottom portion on the rotation center line side of the propulsion engine and both side surface portions rising in parallel with the plane from the both sides of the bottom portion including a plane including the rotation center line of the propulsion engine. The both side surface portions are provided on one side of the intake side inner peripheral surface portion centering on a plane including the rotation center line of the propulsion engine and on one slit and the other slit provided to open through the intake side inner peripheral surface portion. The rear end portions of both side surface portions are fixedly attached to a rotation shaft that is rotatably attached to a bearing portion provided on the base side of the propulsion engine and is fan-shaped around the rotation shaft. Further, the outer surface of the partition main body bottom is formed on the same curved surface as the intake side inner peripheral surface.

  In the boundary level control apparatus of the present invention, a single or a plurality of intake ports for taking in the air of the upper surface of the main wing are provided in the upper surface of the main wing of the aircraft, and the intake is controlled by the aircraft control system. A first on-off valve that opens and closes the opening, and is provided with a single or a plurality of discharge holes for releasing the air taken in by the intake opening on the inner peripheral surface of the intake side of the aircraft propulsion engine; A second on-off valve that is controlled by the control system of the aircraft to open and close the discharge hole, and the intake port and the discharge are released when the first on-off valve and the second on-off valve are controlled by the aircraft control system. In the boundary level control device configured to provide a communication path for communicating between the holes between the intake port and the discharge hole, the valve body in the second on-off valve is on the intake side when the first on-off valve and the second on-off valve are opened. Concave on the inner surface The air inlet that protrudes from the storage portion and takes in the air flow flowing in from the front of the intake port of the propulsion engine is formed to open toward the front of the intake port, and is also taken in from the air inlet behind the air inlet. Venturi passages that reduce the pressure by increasing the flow rate of the air flow are formed by the inner surfaces of the bottom and both side surfaces of the valve body and the inner peripheral surface of the intake side, and the reduced flow of air flows out by increasing the flow rate. An air outlet is formed at the rear side of the inner peripheral surface of the intake side from the opening position of the discharge hole, and the inner surface of the bottom of the valve body becomes the opening of the discharge hole when the first on-off valve and the second on-off valve are closed. The discharge hole is closed closely and the valve body is housed in a housing provided in a concave shape on the intake side inner peripheral surface, and then the bottom outer surface of the valve body forms a continuous curved surface with the intake side inner peripheral surface. And

  In the second on-off valve, the valve body is integrally composed of a bottom portion on the rotation center line side of the propulsion engine and both side surface portions rising in parallel with the plane centering on a plane including the rotation center line of the propulsion engine from both sides of the bottom portion. And one side slits provided on both sides of the intake side inner peripheral surface portion centering on a plane including the rotation center line of the propulsion engine so as to open through the intake side inner peripheral surface portion. While being loosely fitted into the other slit, the rear end portions of the both side surface portions are fixed to a rotation shaft rotatably attached to a bearing portion provided on the base side of the propulsion engine, and the rotation shaft is It operates like a fan at the center of rotation, and the bottom outer surface of the valve body is formed on the same curved surface as the intake side inner peripheral surface.

Effect of the invention

  Since the boundary level control device and the venturi generation device according to the present invention are configured as described above, the following effects can be obtained.

  Since the boundary level control device according to the present invention includes a venturi generating device on the intake side inner peripheral surface of the propulsion engine, the diameter of the intake side inner peripheral surface is the same as that of the propulsion engine employed in a subsonic speed machine or the like. Even in the case of a divergent duct that is set widely toward the compression section, the partition main body in the venturi generator is controlled by the flight control system of the aircraft and protrudes from the storage section provided in a concave shape on the intake side inner peripheral surface. A venturi passage is formed in the intake side inner peripheral surface by the inner surfaces of the bottom and both side surfaces of the partition body and the intake side inner peripheral surface, and the air flow flowing in from the air inlet of the venturi passage is caused by the venturi effect in the passage. When the flow velocity is increased and the pressure is reduced, and the air flows out from the air outlet of the venturi passage, the air on the upper surface of the main wing is sucked from the discharge hole that opens behind the air outlet. Achieving low of the wing upper surface, the flow velocity of the air flowing through the wing upper surface portion of the higher lift by being more accelerated relative flow velocity of the air flowing through the wing lower surface portion can be imparted to the wing.

  Further, the venturi generator provided in the boundary level control device is configured such that when the first on-off valve and the second on-off valve are controlled and opened by the aircraft control system, the partition main body in the venturi generator is the intake side in the propulsion engine. The partition main body protruding from the storage portion provided in a concave shape on the inner peripheral surface forms a venturi passage by the inner surfaces of the bottom and both side surface portions of the partition main body and the intake side inner peripheral surface, and further includes a first on-off valve and When the second on-off valve is controlled and closed by the aircraft control system, the partition main body in the venturi generator is stored in a storage portion provided in a concave shape on the intake side inner peripheral surface, and the bottom outer surface of the partition main body Is formed so as to form a continuous curved surface with the intake side inner peripheral surface, and after the partition body is stored in the storage portion, the intake side inner peripheral surface forms a continuous curved surface. In can flow air stream flowing through the intake-side inner circumferential surface smoothly to the compression unit direction.

  The other boundary level control device according to the present invention can obtain the same effect as the above-described boundary level control device according to the present invention, and the discharge hole opened in the intake side inner peripheral surface is formed by the inner surface portion behind the valve body. Since it is isolated from the intake side inner periphery, the influence from the intake side inner periphery can be reduced, and the air on the upper surface of the main wing can be stably discharged from the discharge hole. In addition, since the release hole is closed by the inner surface behind the bottom of the valve body in the second on-off valve when the second on-off valve is closed, the structure can be simplified and the failure rate can be reduced. Can be reduced.

  The typical side view showing the partial section of the main wing in the airplane to which the present invention is applied.   1 is a schematic longitudinal sectional view including a rotation center line of a propulsion engine [jet engine] in an aircraft to which the present invention is applied.   The external view of the partition main body in the venturi generation apparatus with which the boundary hierarchy control apparatus was equipped.   The external view of the valve body in a 2nd on-off valve.   1 is a schematic longitudinal sectional view including a rotation center line of a propulsion engine [jet engine] in an aircraft to which the present invention is applied.

  Embodiments of the present invention will be described with reference to the drawings. The relative dimensions, structures, and the like shown in the embodiments are merely examples for facilitating understanding of the invention, and do not limit the present invention unless otherwise specified.

  As shown in FIG. 1, the boundary level control apparatus of the present invention is provided with intake ports 3 for taking in air from the main wing upper surface portion 2 in the main wing upper surface portion 2 of the aircraft 1. 3 includes a first on-off valve 4 that is controlled by the control system of the aircraft 1 and opens and closes the intake port 3, and as shown in FIG. 2, the intake side of the propulsion engine 5 of the aircraft 1 (hereinafter referred to as the jet engine 5). A single or a plurality of discharge holes 7 for releasing the air taken in by the intake 3 are provided on the inner peripheral surface 6, and the discharge holes 7 are opened and closed under the control of the control system of the aircraft 1. And a communication passage that communicates between the intake port 3 and the discharge hole 7 when the first on-off valve 4 and the second on-off valve 8 are controlled by the control system of the aircraft 1 and opened. 9 is provided between the intake port 3 and the discharge hole 7. There.

  Further, when the first on-off valve 4 and the second on-off valve 8 are opened, the partition main body 11 (FIGS. 2 and 3) in the venturi generating device 10 is controlled by the control system of the aircraft 1 and the intake air in the jet engine 5 is controlled. An air inflow port 14 that protrudes from a storage portion 12 provided in a concave shape on the side inner peripheral surface 6 and takes in an air flow flowing in from the front of the intake port 13 of the jet engine 5 is formed toward the front of the intake port 13 of the jet engine 5. The venturi passage 15 which opens and increases the flow rate of the air flow taken from the air inlet 14 behind the air inlet 14 to reduce the pressure is provided in the inner surface 17 and both side portions of the bottom portion 16 of the partition body 11. 18 and 19 are formed by the inner surfaces 18a and 19a (Fig. 3) and the intake-side inner peripheral surface 6 and flowed by the venturi passage 15. The air outlet 20 through which the air flow reduced in pressure flows out is formed in front of the opening position of the discharge hole 7 in front of the intake side inner peripheral surface 6, and the first on-off valve 4 and the second on-off valve 4 are opened. When the on-off valve 8 is closed, the partition main body 11 in the venturi generator 10 is controlled by the control system of the aircraft 1 and stored in the storage portion 12 provided in a concave shape on the intake side inner peripheral surface 6, and the bottom of the partition main body 11 The outer surface 21 of 16 is provided with the venturi generator 10 which comprises a continuous curved surface with the inner peripheral surface 6 of the intake side.

  The venturi generating apparatus 10 includes a partition body 11 in the venturi generating apparatus 10 (FIG. 3), a bottom portion 16 positioned on the rotation center line AA ′ side of the jet engine 5, and jet engines from both sides of the bottom portion 16. 5 is formed integrally with both side surfaces 18 and 19 rising in parallel with the plane around a plane including the rotation center line A-A ′, and the partition main body 11 includes both side surface portions 18 and 18 of the partition main body 11. 19 is provided on both sides of the intake side inner peripheral surface 6 part centering on a plane including the rotation center line AA ′ of the jet engine 5 and is opened through the intake side inner peripheral surface part 6 The slits 22 and [parts indicated by dotted lines in FIG. 3] are inserted into the other slits 23 [parts indicated by dotted lines in FIG. Rear portion is constituted is fixed to the rotary shaft 25 rotatably attached to the base side bearing portion 24 provided on the [drawing 2] of the jet engine 5.

  The partition main body 11 in the venturi generator 10 is controlled by the control system of the aircraft 1 when the first on-off valve 4 and the second on-off valve 8 are opened, and operates in a fan shape around the rotation shaft 25 as the center of rotation. By projecting from the storage portion 12 provided in a concave shape on the surface 6, an air inlet 14 for taking in an air flow flowing in from the front of the intake port 13 of the jet engine 5 is formed and opened toward the front of the intake port 13. The space surrounded by the inner surface 17 of the bottom portion 16 and the inner surfaces 18a and 19a of the side surface portions 18 and 19 and the intake side inner peripheral surface 6 of the storage portion 12 in the partition body 11 forms the venturi passage 15. Further, an air outlet 20 through which the low-pressure air flow passes through the venturi passage 15 to increase the flow velocity and flows out is formed in front of the intake-side inner peripheral surface 6 from the opening position of the discharge hole 7. Opening Te.

  Further, when the first on-off valve 4 and the second on-off valve 8 are closed, the partition main body 11 is controlled by the control system of the aircraft 1, and the partition main body 11 operates in a fan shape around the rotation shaft 25 as the center of rotation. An outer surface 21 (FIG. 2) at the bottom 16 of the partition body 11 which is housed in a housing portion 12 provided in a concave shape on the surface 6 and is formed in the same curved surface as the intake-side inner peripheral surface 6 is continuous with the intake-side inner peripheral surface 6. Construct a curved surface.

  The partition main body 11 in the venturi generating device 10 moves in a fan shape around the rotation shaft 25 when protruding from the storage portion 12 provided in a concave shape on the intake side inner peripheral surface 6, but the partition moved in the fan shape. The bottom portion 16 of the main body 11 and the front end portions of the arc-shaped side surface portions 18 and 19 have a large moving distance with respect to the bottom portion 16 of the partition main body 11 and the rear end portions of the arc-shaped side surface portions 18 and 19, respectively. The air inlet 14 formed by the front end of the partition body 11 has a larger opening area than the air outlet 20 formed by the rear end of the partition body 11, and each of the inner surface 17 of the bottom 16 and the side surfaces 18, 19 of the partition body 11. A space surrounded by the inner surfaces 18 a and 19 a and the intake-side inner peripheral surface 6 of the storage portion 12 constitutes a venturi passage 15.

  The bottom 16 of the partition main body 11 that forms the air inlet 14 and the front end portions of the side surfaces 18 and 19 are formed so as to become thinner toward the outside of the front end, and the partition main body 11 that forms the air outlet 20 is formed. The rear end portions of the bottom portion 16 and the side surface portions 18 and 19 are formed so as to become thinner toward the rear end outer side.

  Further, the opening / closing timing of the first opening / closing valve 4 and the second opening / closing valve 8 and the operation timing of the partition main body 11 in the venturi generator 10 are all set so that the opening / closing and operation are performed at the same time. A case where the order of the timing and the closing timing is set differently may be considered. For example, at the opening time, the partition main body 11 in the venturi generating device 10 is first actuated to protrude from the storage portion 12 provided in the intake side inner peripheral surface 6 in a concave shape, and then the second on-off valve 8 is opened, and the first It is conceivable to set the opening timing for opening the on-off valve 4, and at the closing timing, the second on-off valve 8 is closed first, and then the partition main body 11 in the venturi generating device 10 is operated to close the intake side. It is possible to consider a closing timing setting in which the first opening / closing valve 4 is finally closed, which is stored in a storage portion 12 provided in a concave shape on the peripheral surface 6. With regard to the opening / closing timing setting, the purpose is to prevent negative pressure from affecting the opening / closing of the first opening / closing valve 4. However, the opening / closing timing setting is not limited to this, and the most effective opening / closing timing setting may be appropriately selected.

  The operation of the partition main body 11 in the venturi generator 10 is controlled by the aircraft control system in the same manner as the first on-off valve 4 and the second on-off valve 8 that are controlled by the aircraft control system to open and close. 4 and the second on-off valve 8 are interlocked with the opening / closing of the second on-off valve 8, and the rotation shaft 25 is used as a center of rotation by the driving device 45 such as a mechanical type, hydraulic type, pneumatic type or the like directly or via a link mechanism. Moreover, it is good also as driving with the said drive device by directly connecting one end parts, such as a link mechanism and a wire, to the partition main body 11 by making the rotating shaft 25 into the rotation center.

  The partition main body 11 in the venturi generator 10 protrudes from the storage portion 12 provided in a concave shape on the intake side inner peripheral surface 6 when the first on-off valve 4 and the second on-off valve 8 are opened, but the amount of protrusion can be adjusted. When the driving mechanism 45 is provided in the driving device 45, the amount of air taken in the main wing upper surface portion 2 from the intake port 3 can be adjusted, and the amount of lift contributing to the main wing upper surface portion 2 can be adjusted. .

  Both side surface portions 18 and 19 of the partition main body 11 in the venturi generating apparatus 10 are disposed on both sides of the intake side inner peripheral surface 6 centering on a plane including the rotation center line AA ′ of the jet engine 5 on the intake side inner periphery. Since the first slit 22 and the other slit 23 provided so as to open through the surface 6 portion are loosely fitted, the side surface 18 and the one slit 22 and the side surface 19 and the other slit There is a gap between the slits 23. Although it is desirable to set the gap as narrow as possible, both side portions 18 and 19 of the partition body 11 are necessary for moving the slits 22 and 23, and in order to reduce the air flow in the gap. In addition to the one slit 22 and the other slit 23, the side surface portions 18, 19 and the bearing portions 24 of the side surface portions 18, 19 provided on the base side of the jet engine 5, and the bearing portion 24 are rotatably mounted. Measures are taken such as adopting a structure that reduces the flow of air from the gap when the jet shaft 5 is covered with the cover or the engine nacelle that covers the jet engine 5 body is covered. Good.

  Further, when covered with a cover, one or both ends of the rotary shaft 25 are sealed inside and outside the cover and project outside the cover, and mechanical, hydraulic, pneumatic, etc. directly or via a link mechanism etc. The partition main body 11 is driven by the driving device.

  As the second on-off valve 8 for opening and closing the discharge hole 7 in the embodiment of the present invention, a slidable on-off valve 8a (FIG. 2) that slides on the radiation of the jet engine rotation center line A-A 'is employed. . A part of the intake-side inner peripheral surface 6 is formed on the side of the jet engine rotation center line A-A 'of the valve element 26 (FIGS. 2 and 4) in the sliding on-off valve 8a and when the sliding on-off valve 8a is closed. The outer surface 27 is formed in the same curved surface as the intake-side inner peripheral surface 6, and the outer surface 27 forms a continuous curved surface with the intake-side inner peripheral surface 6 when the slide type on-off valve 8 a is closed. Thus, the resistance of the intake side inner peripheral surface 6 is reduced. Further, in the valve body 26 in FIG. 4, the plane orthogonal to the radiation of the jet engine rotation center line AA ′ is a square, but the plane is a valve body, a columnar shape, or an ellipse whose four corners are curved. A valve body having a shape is also conceivable, and the second on-off valve 8 is not limited to the slide-type on-off valve 8a, and it is sufficiently conceivable to employ on-off valves having different structures.

  Further, when the valve body 26 of the slide type on-off valve 8a is closed, the on-off valve driving device having a valve body return mechanism using a spring or fluid having a repulsive force causes the base side of the jet engine 5 to move to the base side. The front peripheral surface 29 of the valve body 26 is in surface contact with the provided valve seat 28 and the space between the two is sealed. FIG. 2 is a side view including the rotation center line AA ′ of the jet engine. However, the valve body 26 is shown not in cross section but in an external appearance, and the shape of the outer surface 27 of the valve body 26 is shown in a planar shape. Further, the center line in the front-rear direction (dotted line in FIG. 4) is not shown by the dotted line. Also in the valve seat 28 and the discharge hole 7, the dotted line that represents the outline of the valve seat 28 that should be visible on the back side of the side view and the solid line that represents the outline of the discharge hole 7 are omitted. The reason is omitted because writing makes it difficult to understand the drawing.

  Then, the valve element 26 of the slide type on-off valve 8a slides on the radiation of the jet engine rotation center line A-A 'to the opposite side of the jet engine rotation center line A-A', and the outlet 9a of the communication passage 9 Is opened on the side surface of the slide type on-off valve 8a, the communication passage 9 and the discharge hole 7 are communicated with each other, and the intake port 3 and the discharge hole 7 of the main wing upper surface portion 2 are communicated with each other through the communication passage 9.

  In the boundary level control apparatus described above, a single or a plurality of discharge holes 7 for releasing the air taken in from the intake port 3 for taking in air in the upper surface portion 2 of the main wing are provided on the intake side inner peripheral surface 6 of the jet engine 5 of the aircraft 1 or A plurality of openings are provided, and the discharge hole 7 is provided with a second on-off valve 8 that is controlled by the control system of the aircraft 1 and opens and closes the discharge hole 7, and a sliding on-off valve 8a is adopted as the second on-off valve 8. When the valve element 26 of the slide type on-off valve 8a slides and the outlet of the communication path 9 is opened on the side surface of the slide type on-off valve 8a, the communication path 9 and the discharge hole 7 are communicated with each other. However, the other boundary layer control apparatus described below has both the function of the partition main body 11 in the above-described venturi generating apparatus 10 to open and close the discharge hole as the valve body of the second on-off valve and the function of configuring the venturi passage. This It is characterized in. This will be described below.

  The other boundary layer control apparatus of the present invention has a configuration substantially similar to the above-described boundary layer control apparatus, and has a single intake port 3 for taking in air from the main wing upper surface portion 2 into the main wing upper surface portion 2 of the aircraft 1 in FIG. The intake port 3 is provided with a first on-off valve 4 that is controlled by the control system of the aircraft 1 and opens and closes the intake port 3, and the intake-side inner peripheral surface of the jet engine 30 in FIG. A release hole 32 for releasing air taken in by the intake 3 is provided at 31 at a single or a plurality of places, and a second on-off valve 33 that opens and closes the release hole 32 under the control of an aircraft control system. And the communication port 9 that communicates between the intake port 3 and the discharge hole 32 when the first on-off valve 4 and the second on-off valve 33 are controlled by the aircraft control system to be in the open state. And discharge hole 32 It is configured provided on.

  The second on-off valve 33 is characterized in that the partition body 11 in the venturi generator 10 provided in the above-described boundary layer control device is a valve body 34, and thus the configuration of the valve body 34 and the above-described partition body 11 of the partition body 11. Since the configuration is similar, the description will be simplified.

  The valve element 34 of the second on-off valve 33 in FIG. 5 has a bottom 35 located on the rotation center line AA ′ side of the jet engine 30 and a rotation center line AA ′ of the jet engine 30 from both sides of the bottom 35. The valve body 34 is integrally formed with both side surface portions rising in parallel with the plane, and the valve body 34 is centered on the plane including the rotation center line AA ′ of the jet engine 30. The both sides of the intake side inner peripheral surface 31 are loosely fitted and assembled into one slit and the other slit provided so as to open through the intake side inner peripheral surface 31 portion. The rear portion is fixed to a rotary shaft 37 rotatably attached to a bearing portion 36 provided on the base side of the jet engine 30 and operates in a fan shape with the rotary shaft 37 as a rotation center. The outer surface 38 of the 35 are formed on the same curved surface as the intake-side inner circumferential surface 31.

  In particular, the valve body 34 in the second opening / closing valve 33 is different from the partition main body 11 in the venturi generating device 10 described above, because the inner surface 39 of the bottom 35 of the valve body 34 opens and closes the discharge hole 32, so that the second opening / closing is performed. When the valve 33 is closed, the inner surface 39 of the bottom 35 is in close contact with the opening of the discharge hole 32 to close the discharge hole 32.

  When the first on-off valve 4 and the second on-off valve 33 are opened, the valve body 34 in the second on-off valve 33 protrudes from the storage portion 40 provided in a concave shape on the intake side inner peripheral surface 31, and the jet engine 30 An air inlet 42 that takes in an air flow that flows in from the front of the air inlet 41 is formed to open toward the front of the air inlet 41, and the flow velocity of the air flow that is taken in from the air inlet 42 behind the air inlet 42. The venturi passage 43 for lowering the pressure is formed by the inner surface 39 of the bottom 35 of the valve body 34, the inner surfaces of both side surfaces and the intake-side inner peripheral surface 31, and the air pressure is reduced by increasing the flow rate. An air outlet 44 through which the flow flows is formed and opened behind the intake side inner peripheral surface 31 from the opening position of the discharge hole 32.

  Further, when the first on-off valve 4 and the second on-off valve 33 are opened, the air outlet 44 of the venturi passage 43 is formed and opened behind the intake side inner peripheral surface 31 from the opening position of the discharge hole 32. Since the opening of the discharge hole 32 is isolated from the inside of the intake side inner peripheral surface 31 by the bottom 35 of the valve body 34, the influence from the inside of the intake side inner peripheral surface 31 can be reduced. The air of the upper surface portion 2 of the main wing taken in from 3 can be stably discharged from the discharge hole 32.

  When the first on-off valve 4 and the second on-off valve 33 are closed, the valve body 34 of the second on-off valve 33 is stored in the storage portion 40 provided in a concave shape on the intake side inner peripheral surface 31. Since the outer surface 38 of the bottom portion 35 is formed in a shape that forms a continuous curved surface with the intake side inner peripheral surface 31, the outer surface 38 of the bottom portion 35 of the valve body 34 has a continuous curved surface with the intake side inner peripheral surface 31. Further, the opening of the discharge hole 32 is closed by the inner surface 39 of the bottom 35 of the valve body 34.

  The jet engine 5 and the jet engine 30 are a turbojet engine, a turbofan engine, a turboprop engine, a turboshaft engine, or the like, which compresses inhaled air, adds fuel to the compressed air, and burns it. This is an engine that obtains thrust by vigorously injecting high-temperature and high-pressure combustion gas from the exhaust port, and the boundary level control device is provided on the intake side inner peripheral surface in front of the compression section in these various jet engines.

  In addition, the position of the boundary level control device in the turbofan type engine is not limited to the intake side inner peripheral surface in front of the compression unit in the turbofan type engine, but the fan fixed to the rotation shaft in front of the compression unit in the turbofan type engine. An embodiment arranged inside the engine nacelle covering the air compressor is also conceivable, and the air flow generated by the fan of the portion larger than the diameter of the compression portion of the air flow generated by the fan fixed to the rotating shaft in front of the compression portion is also considered. An embodiment in which the boundary layer control device is arranged in the fan nozzle portion is also conceivable.

  Furthermore, in the boundary layer control device of Japanese Patent Application No. 2014-141789 filed by the same applicant as the present applicant, in the case of a jet engine of a turbofan engine, the intake side inner peripheral surface in front of the above-described compression section In addition, an embodiment in which the boundary layer control device is disposed inside the engine nacelle covering the fan fixed to the rotation shaft in front of the compression unit in the turbofan engine is also conceivable, and the rotation shaft in front of the compression unit is also considered. An embodiment in which the boundary layer control device is easily arranged in the fan nozzle portion which is the outlet of the air flow generated by the fan in the portion larger than the diameter of the compression portion in the air flow generated by the fixed fan can be easily considered.

  As described above, the embodiments of the present invention have been described with reference to the accompanying drawings. However, the present invention is not limited to such embodiments, and those skilled in the art will be able to perform various types within the scope of the claims. It is clear that changes or modifications can be conceived, and also in the boundary layer control device of the present invention and the boundary layer control device of Japanese Patent Application No. 2014-141789 filed by the same applicant as the present applicant. It is obvious that embodiments in which the respective technologies are combined can be conceived, and these are naturally understood to belong to the technical scope of the present invention.

1. Aircraft 2, Main wing upper surface 3, Intake port 4, First on-off valve 5, 30 Propulsion engine (jet engine)
6, 31 Intake side inner peripheral surface 7, 32 Discharge hole 8, 8a, 33 Second on-off valve 9, communication passage 9a, communication passage outlet 10, venturi generator 11, partition body 12, 40 storage portion 13, 41 intake port 14, 42 Air inlet 15, 43 Venturi passage 16, Partition body bottom 17, Bottom inner surface 18, 19 Both side surfaces 18 a, 19 a Both side surfaces 18, 44 Air outlet 21, Bottom outer surface 22 , One slit 23, the other slit 24, 36 bearing portion 25, 37 rotating shaft 26, valve body 27 of the sliding on-off valve 8 a, outer surface 28 of the valve body on the jet engine rotation center line AA ′ side, valve Seat 29, valve body tip peripheral surface 34, second on-off valve body 35, second on-off valve body bottom 38, valve body bottom outer surface 39, valve body bottom inner surface 45, driving device

Claims (4)

  An intake port for taking in air from the upper surface of the main wing is provided at the upper surface of the main wing of the aircraft so as to be opened at one or a plurality of locations, and the intake port is provided with a first on-off valve that is controlled by an aircraft control system to open and close the intake. A single or a plurality of discharge holes for releasing the air taken in by the intake port are provided on the inner peripheral surface of the intake side of the aircraft propulsion engine, and the discharge hole is controlled by the aircraft control system in the discharge hole. A second on-off valve that opens and closes, and the first on-off valve and the second on-off valve are controlled by an aircraft control system to be in an open state, and a communication passage that communicates between the intake and the discharge hole In the boundary level control device configured to be provided between the air outlet and the discharge hole, the partition main body in the venturi generator is controlled by the aircraft control system when the first on-off valve and the second on-off valve are opened, and the intake side inner peripheral surface An air inlet that protrudes from the concavely provided storage portion and takes in an air flow flowing in from the front of the intake port of the propulsion engine is formed to open toward the front of the intake port, and from the air inlet to the rear of the air inlet Venturi passages that reduce the pressure by increasing the flow rate of the air flow taken in are formed by the inner surfaces of the partition body bottom and both side surfaces and the inner peripheral surface of the intake side, and the air flow reduced by increasing the flow rate is reduced. The air outlet that flows out is formed in front of the air intake side inner peripheral surface from the opening position of the discharge hole, and the partition main body is controlled by the aircraft control system when the first on-off valve and the second on-off valve are closed. A boundary layer control device comprising a venturi generating device that is housed in a recessed portion provided on the inner peripheral surface of the intake side, and that the outer surface of the bottom of the partition main body forms a continuous curved surface with the inner peripheral surface of the intake side.   The partition main body in the venturi generating device is integrally configured with a bottom portion on the rotation center line side of the propulsion engine and both side surface portions rising in parallel with the plane from the both sides of the bottom portion including a plane including the rotation center line of the propulsion engine. The both side surface portions are provided on one side of the intake side inner peripheral surface portion centering on a plane including the rotation center line of the propulsion engine and on one slit and the other slit provided to open through the intake side inner peripheral surface portion. It is loosely fitted and incorporated, and the rear part of both side surface parts is fixed to a rotating shaft rotatably attached to a bearing part provided on the base side of the propulsion engine, and is fan-shaped around the rotating shaft. 2. The venturi generating device according to claim 1, wherein the venturi generating device operates and the outer surface of the partition main body bottom is formed on the same curved surface as the intake side inner peripheral surface.   An intake port for taking in air from the upper surface of the main wing is provided at the upper surface of the main wing of the aircraft so as to be opened at one or a plurality of locations, and the intake port is provided with a first on-off valve that is controlled by the aircraft control system to open and close the intake A single or a plurality of discharge holes for releasing the air taken in by the intake port are provided on the inner peripheral surface of the intake side of the aircraft propulsion engine, and the discharge hole is controlled by the aircraft control system in the discharge hole. A second on-off valve that opens and closes, and the first on-off valve and the second on-off valve are controlled by an aircraft control system to be in an open state, and a communication passage that communicates between the intake and the discharge hole In the boundary layer control device configured to be provided between the first and second release valves, a storage portion in which the valve body of the second on-off valve is provided in a concave shape on the intake side inner peripheral surface when the first on-off valve and the second on-off valve are opened. Protruding engine The air inlet that takes in the air flow that flows in from the front of the mouth is formed to open toward the front of the air inlet, and the flow rate of the air flow that is taken in from the air inlet is increased behind the air inlet to reduce the pressure. The venturi passage to be formed is formed by the inner surfaces of the bottom and both side portions of the valve body and the inner peripheral surface of the intake side, and an air outlet through which a low-pressure air flow flows out by increasing the flow velocity is the opening position of the discharge hole. The valve is shaped and opened to the rear of the inner peripheral surface of the intake side, and when the first on-off valve and the second on-off valve are closed, the inner surface of the bottom of the valve body is in close contact with the opening of the discharge hole to close the discharge hole. A boundary layer control device characterized in that the outer surface of the bottom of the valve body forms a continuous curved surface with the inner peripheral surface of the intake side after the body is stored in a storage portion provided concavely on the inner peripheral surface of the intake side.   In the second on-off valve, the valve body is integrally composed of a bottom portion on the rotation center line side of the propulsion engine and both side surface portions rising in parallel with the plane centering on a plane including the rotation center line of the propulsion engine from both sides of the bottom portion. And one side slits provided on both sides of the intake side inner peripheral surface portion centering on a plane including the rotation center line of the propulsion engine so as to open through the intake side inner peripheral surface portion. While being loosely fitted into the other slit, the rear end portions of the both side surface portions are fixed to a rotation shaft rotatably attached to a bearing portion provided on the base side of the propulsion engine, and the rotation shaft is 4. The second on-off valve according to claim 3, wherein the second on-off valve operates in a fan shape at the center of rotation, and the outer surface of the bottom of the valve body is formed on the same curved surface as the inner peripheral surface of the intake side.

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