An air discharge system

Abstract

The present invention relates to at least one air inlet (2) in supersonic aircraft, a ramp region (3) that is located at the entrance of the air inlet (2), is the region in contact with the air and has a narrowing form, a throat region (4) that is located in the air inlet (2) after the ramp region (3) and has an expanding form, at least one ramp plenum (5) that is located in the ramp region (3) and allows air to accumulate in the air inlet (2) to prevent boundary layer air and shock-induced flow separations, and a discharge door (6) that is located on the ramp plenum (5) on the aerodynamic surface of the aircraft in contact with the air and is opened when the aircraft reaches a predetermined threshold value speed, thus providing air discharge.

Description

[0001] AN AIR DISCHARGE SYSTEM

[0002] This invention relates to air discharge systems in the air inlets of supersonic aircraft.

[0003] The air intake of supersonic aircraft travelling above the speed of sound usually has specially designed air inlets and engine integrations. One of the main goals in the design of supersonic aircraft is to manage shock wave generation. Shock waves can create a pressure wave in front of an aircraft as it moves faster than the speed of sound. Controlling the pressure wave is important to increase the performance of the air inlet and reduce environmental impacts.

[0004] The performance of an air inlet is affected by the boundary layer development on its walls. Shock-boundary layer interactions at the air inlet surface need to be controlled by various means to maintain a constant shock throughout the flight envelope. If an uncontrollable shock occurs in the air inlet, it can cause the engine to fluctuate, which can lead to devastating consequences.

[0005] In the United States patent document numbered US4000869A in the state of the art, a strong shock-boundary layer interaction control system is mentioned. A control system is described to suppress shock-induced flow separation at the air inlet of supersonic aircraft resulting from the interaction between turbulent boundary layer air and a strong normal shock. The control system is designed to continuously carry out air intake through a predetermined cover and across the shock-boundary layer interaction zone. The discharge of air intake directed to a series of air collection boxes supplied through a perforated cover to the atmosphere is accomplished through a controlled staged gate. The control system is able to control interactions when the strength of the normal shock approaches two Mach values. by means of an air discharge system developed with the present invention, both continuous air discharge is provided from the air inlet in the supersonic aircraft and more air discharge is provided to improve aerodynamic performance above a certain Mach value. Another aim of this invention is to provide efficient air discharge from the air inlet in a supersonic aircraft while at the same time ensuring low visibility of the aircraft.

[0006] The air discharge system defined in the first claim and the claims dependent on this claim, which is realised to achieve the aim of the invention, comprises at least one air inlet in supersonic aircraft. "Supersonic aircraft" refers to an aircraft that travels above the speed of sound in the atmosphere. The speed of sound is the speed of sound in the atmosphere and is called "1 Mach". There is a ramp region at the entrance of the air inlet, and a throat region beyond the ramp region. The ramp region is the first part where air enters the air inlet. In the air inlet, there is a throat region that has an expanding form, beyond the ramp region. There is at least one ramp plenum in the ramp region, which allows air to accumulate. The ramp plenum slows down and pressurises the air flow entering the air inlet. This causes stagnant air or low-velocity air to accumulate. Stagnant air is used to increase the aerodynamic performance of supersonic aircraft. Aircraft travelling at supersonic speeds can create shock waves when they interact with the atmosphere. An aircraft travelling above the speed of sound creates a shock wave. A shock wave is a rapidly moving pressure wave in the environment around the aircraft. The ramp plenum provides controlled air accumulation to control and reduce these shock waves. At the same time, the ramp plenum adjusts the pressure of the air entering the air inlet. Air in the ramp plenum accumulates in a specially designed space to manage the aerodynamic challenges of the supersonic aircraft, optimising its performance and controlling shock waves. The ramp plenum increases the performance of the aircraft by regulating and directing the air flow. There is a discharge door on the ramp plenum that allows the air accumulated in the ramp plenum to be discharged to the atmosphere. When the aircraft reaches a certain Mach value, the discharge door opens and the air accumulated in the ramp plenum is discharged.

[0007] The air discharge system of the invention comprises a throat plenum located in the throat region. There is an opening on the aerodynamic surface to discharge the air carried from the throat plenum to the outside. By means of the opening, air is continuously discharged from the air inlet throughout the aircraft flight. There is a distance between the ramp plenum and the throat plenum predetermined by the manufacturer. When the discharge door is opened during flight, a wake region is formed in the upper part of the throat region, by means of the air discharged from the ramp plenum. The wake region refers to a region of moving airflow. It occurs in the environment where the discharge door moves and affects the air flow. In the wake region, pressure increases and air flow becomes turbulence. It can also create fluctuations and irregularitites in the air flow. By means of the wake region thus formed, more air is discharged through the opening in the throat plenum. At the same time, boundary layer air is discharged from the throat region. The boundary layer is the thin layer of air immediately adjacent to the boundary surface formed by the air flowing across the surface. Shock waves, which are sound wave explosions, can form on this layer and advance to the engine. If it advances to the engine, it reduces the engine's thrust and reduces its performance, and may even stop the engine from time to time. By discharging more air from the throat plenum, the transmission of shock-induced flow separations to the engine is reduced.

[0008] In one embodiment of the invention, the air discharge system comprises a cover on the throat plenum having a distance to the opening. The cover is positioned almost parallel to the aerodynamic surface in contact with the air. It is located above the opening and partially covers the opening. There is a discharge door opposite the opening and on the ramp plenum. When the discharge door is opened, the air discharged from the ramp plenum flows to be directed between the opening and the cover. Thus, the air in the throat plenum and discharged through the opening is discharged at a greater rate when the discharge door is open than when the discharge door is closed. In this way, the aerodynamic performance of the aircraft improves.

[0009] In one embodiment of the invention, the air discharge system comprises an opening that provides continuous air discharge. The opening is located above the throat plenum, and air flows from the opening to the atmosphere in a variable amount throughout the aircraft flight. The discharge door located on the ramp plenum opens when a predetermined threshold speed value is reached. When the discharge door is opened, more air is discharged from the throat plenum located in the throat region.

[0010] In one embodiment of the invention, the air discharge system comprises multiple holes located on the ramp plenum and / or throat plenum. The air coming to the air inlet passes through many holes aligned in a certain pattern and accumulates in the ramp and / or throat plenums where the air is collected, and the flow cannot be compressed. In this way, low-energy air in the boundary layer within the air inlet accumulates in the ramp plenum and / or throat plenum and is discharged from the aerodynamic surface.

[0011] In one embodiment of the invention, the air discharge system comprises an actuator that triggers the discharge door and enables it to open. When the aircraft reaches a predetermined threshold speed and exceeds a certain Mach value, the actuator activates the discharge door. When the discharge door is opened, the air accumulated in the ramp plenum is discharged out of the ramp plenum. By means of the air discharge system, continuous air discharge can be achieved in the throat region at every Mach number, and the ability to draw in much more air after a certain Mach number is provided.

[0012] In one embodiment of the invention, the air discharge system comprises a first position (I) in which the discharge door is closed and a second position (II) in which the discharge door is opened by rotating around one of its edges. When the aircraft reaches a predetermined speed value, the discharge door opens and moves to the second position (II). The actuator enables the discharge door to be moved from the first position (I) to the second position (II). When the discharge door is opened, the air discharged from the ramp plenum creates a wake region on the throat plenum. By means of the wake region, more air is discharged from the throat plenum.

[0013] In one embodiment of the invention, the air discharge system comprises a control unit that controls the operation of the actuator. The actuator is triggered according to flight speed-related data received from the sensors on the aircraft, the pilot or the flight control computer. Data is received from sensors and based on this data, the actuator is triggered by the pilot and / or flight control computer. The control unit controls the actuator to move the discharge door.

[0014] In one embodiment of the invention, the air discharge system comprises an actuator that is a piston. When the supersonic aircraft reaches a predetermined Mach value, the piston actuator triggers the discharge door and moves it to the second position (II). In one embodiment of the invention, the air discharge system comprises an external compression type air inlet. The external compression type air inlet used in supersonic aircraft is an air inlet system with a design that helps collect air from the atmosphere and compress the collected air as the aircraft moves forward. By means of this system, the performance of the aircraft is optimised while cruising at high speeds.

[0015] In one embodiment of the invention, the air discharge system comprises a discharge door that opens at 1 .4 Mach. The discharge door opens when the supersonic aircraft is at Mach values of 1 .4 Mach and above. The size of the opening in the throat region can be reduced by using the discharge door in the ramp region. This ensures that the aircraft is in low visibility.

[0016] The air discharge system realised to achieve the aim of this invention is shown in the attached figures, and of these figures;

[0017] Figure 1 is the front view of the air inlet.

[0018] Figure 2 is the perspective view of the air inlet.

[0019] The parts in the figures are numbered one by one and the equivalents of these numbers are given below.

[0020] 1 . Air discharge system

[0021] 2. Air inlet

[0022] 3. Ramp region

[0023] 4. Throat region

[0024] 5. Ramp plenum

[0025] 6. Discharge door

[0026] 7. Throat plenum

[0027] 8. Opening

[0028] 9. Cover

[0029] 10. Hole

[0030] 1 1 .Actuator

[0031] 12. Control unit The air discharge system (1 ) comprises at least one air inlet (2) in supersonic aircraft, a ramp region (3) that is located at the entrance of the air inlet (2), is the region in contact with the air and has a narrowing form, a throat region (4) that is located in the air inlet (2) after the ramp region (3) and has an expanding form, at least one ramp plenum (5) that is located in the ramp region (3) and allows air to accumulate in the air inlet (2) to prevent boundary layer air and shock-induced flow separations, and a discharge door (6) that is located on the ramp plenum (5) on the aerodynamic surface of the aircraft in contact with the air and is opened when the aircraft reaches a predetermined threshold value speed, thus providing air discharge.

[0032] The air discharge system (1 ) that is the subject of the invention comprises at least one throat plenum (7) that is located in the throat region (4) at a distance predetermined by the manufacturer from the ramp plenum (5), an opening (8) that is located on the aerodynamic surface for the discharge of air carried from the throat plenum (7), thus discharging air from the air inlet (2) throughout the aircraft flight, and an opening (8) through which the boundary layer air is discharged from the throat region (4) and thus almost completely minimises the transfer of shock-induced flow separations to the engine by means of the wake region formed on the upper part of the throat region (4) when the discharge door (6) is opened during flight.

[0033] The air discharge system (1 ) comprises at least one air inlet (2) in supersonic aircraft. There is a ramp region (3) located at the entrance of the air inlet (2), which first comes into contact with the air. The ramp region (3) generally has a narrowing form. Following the ramp region (3), there is a throat region (4) that is located in the air inlet (2) and has an expanding form. There is at least one ramp plenum (5) in the ramp region (3) that allows the air in the air inlet (2) to accumulate. By means of the air accumulated in the ramp plenum (5), boundary layer air and shock-induced flow separations formed in the air inlet (2) are minimised. There is a discharge door (6) on the ramp plenum (5) on the outer aerodynamic surface of the aircraft in contact with the air. The discharge door (6) is opened when the aircraft reaches a predetermined threshold speed, thus providing air discharge from the ramp plenum (5) to the outside of the aircraft. (Figure 1 ) The air discharge system (1 ) comprises a throat plenum (7) located in the throat region (4). There is an opening (8) on the aerodynamic surface to discharge the air transferred from the throat plenum (7) out of the aircraft. By means of the opening (8), air is constantly discharged from the air inlet (2) while the aircraft is moving. When the discharge door (6) is opened while the aircraft is in flight, fluctuations occur in the air above the throat region (4). These fluctuations cause low pressure in the upper part of the throat plenum (7) and more air exits from the opening (8) towards the low pressure. Thus, air that has low energy and will negatively affect the aerodynamic performance of the aircraft is discharged from the throat region (4). (Figure 2)

[0034] In one embodiment of the invention, the air discharge system (1 ) comprises a cover (9) located almost completely parallel to the aerodynamic surface, which partially covers the opening (8) on the throat plenum (7) and provides a distance between it and the opening (8), and a discharge door (6) that is located opposite the opening (8) on the ramp plenum (5) and allows air flow by directing air between the opening (8) and the cover (9) when opened. By means of the cover (9), aerodynamically efficient air exit from the opening (8) is enabled. There is a discharge door (6) opposite the opening (8) on the ramp plenum (5). When the discharge door (6) is opened, more air is discharged from the throat plenum (7). In this way, the aerodynamic performance of the aircraft improves.

[0035] In one embodiment of the invention, the air discharge system (1 ) comprises the opening (8) that allows air flow and the discharge door (6) that opens when the predetermined speed value is reached. By means of the continuous air discharge provided by the opening (8), the air in the throat region (4) that has low energy and is inefficient for the aircraft engine is discharged. By opening the discharge door (6) at and above a certain threshold value, more air is discharged from the throat plenum (7) compared to the situation when the discharge door (6) is closed.

[0036] In one embodiment of the invention, the air discharge system (1 ) comprises multiple holes (10) located in a certain pattern on the ramp plenum (5) and / or throat plenum (7) and where the low-energy air in the boundary layer within the air inlet (2) accumulates in the ramp plenum (5) and / or throat plenum (7), allowing for discharge from the aerodynamic surface. By means of the holes (10), the boundary layer in the air inlet (2) is transported to the air ramp plenum (5) and / or throat plenum (7) and then discharged from the aircraft.

[0037] In one embodiment of the invention, the air discharge system (1 ) comprises at least one actuator (11 ) that triggers the discharge door (6) when the aircraft reaches a predetermined threshold speed and allows the discharge door (6) to open and discharge the air accumulated in the ramp plenum (5). By means of the actuator (1 1 ), the discharge door (6) is moved and opened at a certain threshold speed and above.

[0038] In one embodiment of the invention, the air discharge system (1 ) comprises a first position (I) on the ramp plenum (5) where the discharge door (6) is completely closed, a second position (II) in which the discharge door (6) is opened by rotating around one side when a predetermined speed value is reached, and an actuator (1 1 ) that enables the discharge door (6) to be moved from the first position (I) to the second position (II), thus allowing the air discharged from the ramp plenum (5) to create a wake region on the throat plenum (7). By means of the actuator (1 1 ), the discharge door (6) is moved from the first position (I) to the second position (II).

[0039] In one embodiment of the invention, the air discharge system (1 ) comprises a control unit (12) that is located on the aircraft and controls the operation of the actuator (11 ) triggered according to flight speed-related data received from the sensors, the pilot or the flight control computer. By means of the control unit (12), the actuator (11 ) is controlled to open or close the discharge door (6).

[0040] In one embodiment of the invention, the air discharge system (1 ) comprises an actuator (1 1 ) that is a piston.

[0041] In one embodiment of the invention, the air discharge system (1 ) comprises an external compression type air inlet (2).

[0042] In one embodiment of the invention, the air discharge system (1 ) comprises a discharge door (6) that opens at 1 .4 Mach value.

Claims

CLAIMS1. An air discharge system (1 ) comprising at least one air inlet (2) in supersonic aircraft; a ramp region (3) that is located at the entrance of the air inlet (2), is the region in contact with the air and has a narrowing form; a throat region (4) that is located in the air inlet (2) following the ramp region (3) and has an expanding form; at least one ramp plenum (5) that is located in the ramp region (3) and allows air to accumulate in the air inlet (2) to prevent boundary layer air and shock-induced flow separations; and a discharge door (6) that is located on the ramp plenum (5) on the aerodynamic surface of the aircraft in contact with the air and is opened when the aircraft reaches a predetermined threshold value speed, thus providing air discharge, characterised by at least one throat plenum (7) that is located in the throat region (4) at a distance predetermined by the manufacturer from the ramp plenum (5); an opening (8) that is located on the aerodynamic surface for the discharge of air carried from the throat plenum (7), thus discharging air from the air inlet (2) throughout the aircraft flight; and an opening (8) through which the boundary layer air is discharged from the throat region (4) and thus almost completely minimises the transfer of shock-induced flow separations to the engine by means of the wake region formed on the upper part of the throat region (4) when the discharge door (6) is opened during flight.

2. An air discharge system (1 ) according to Claim 1 , characterised by a cover (9) that is located to have a certain distance to the opening (8) and almost completely parallel to the aerodynamic surface, and partially covers the opening (8) on the throat plenum (7); discharge door (6) that is located opposite the opening (8) on the ramp plenum (5) and allows air flow by directing air between the opening (8) and the cover (9) when opened.

3. An air discharge system (1 ) according to Claim 1 or Claim 2, characterised by the opening (8) that allows continuous air flow; and the discharge door (6) that opens when the predetermined speed value is reached.

4. An air discharge system (1 ) according to any of the previous claims, characterised by multiple holes (10) that are located in a certain pattern on the ramp plenum (5) and / or throat plenum (7) and allow the discharge of the low-energy air in the boundary layer within the air inlet (2) that accumulates in the ramp plenum (5) and / or throat plenum (7) through the aerodynamic surface.

5. An air discharge system (1 ) according to any of the previous claims, characterised by at least one actuator (11 ) that triggers the discharge door (6) when the aircraft reaches a predetermined threshold speed and allows the discharge door (6) to open and discharge the air accumulated in the ramp plenum (5).

6. An air discharge system (1 ) according to Claim 5, characterised by a first position (I) where the discharge door (6) is completely closed on the ramp plenum (5), a second position (II) in which the discharge door (6) is opened by rotating around one side when a predetermined speed value is reached, and an actuator (11 ) that enables the discharge door (6) to be moved from the first position (I) to the second position (II), thus allowing the air discharged from the ramp plenum (5) to create a wake region on the throat plenum (7).

7. An air discharge system (1 ) according to Claim 5 or Claim 6, characterised by a control unit (12) that is located on the aircraft and controls the operation of the actuator (11 ), triggered according to flight speed-related data received from the sensors, the pilot or the flight control computer.

8. An air discharge system (1) according to Claims 5 to 7, characterised by an actuator (11) that is a piston.

9. An air discharge system (1 ) according to any of the previous claims, characterised by an external compression type air inlet (2)10. An air discharge system (1 ) according to any of the previous claims, characterised by a discharge door (6) that opens at 1 .4 Mach.

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