An axisymmetric three-pass adjustable turbine ram combined power nozzle

Abstract

The application discloses a shaft symmetrical three-channel adjustable turbine ram combined power nozzle, wherein an inner channel and an outer channel are turbine engine nozzle and ram engine nozzle respectively, the turbine engine nozzle channel is divided into an inner duct flow channel and an outer duct flow channel, an inner plug cone and an inner duct wall form the flow channel of the inner duct, the inner plug cone can be simply moved in translation, an outer plug cone is in the outer duct and forms the flow channel of the outer duct together with the outer duct wall, and the inner and outer plug cones form physical throat channels, the outer flow channel is a ram channel, the inlet is supersonic airflow and has no contraction section, the opening and closing of the inner and outer ducts are controlled by adjusting the positions of the inner and outer plug cones, the shape of the joint is inclined by a certain angle, the size of the throat channel and the expansion ratio can be adjusted, the movements of the inner and outer plug cones are independent, and the independent and linkage conditions can be realized to achieve different flow rates and working states, and the combined power engine can meet the demand under complex working conditions.

Description

Technical Field

[0001] This invention belongs to the field of combined power nozzle technology for aero-engines, specifically an axisymmetric three-channel adjustable turbo-ramjet combined power nozzle. Background Technology

[0002] Combined propulsion technology integrates engines with different thermodynamic cycles. To meet the needs of various aircraft, it fully utilizes the technological advantages of rocket engines, ramjet engines, and turbine engines across different flight speed and airspace ranges. This combination allows for multiple operating modes adaptable to different missions, achieving wide-range, high-efficiency operation. Common combined propulsion systems include combinations of turbine and ramjet engines, and ramjet and rocket engines. The combined nozzle is the main component that generates thrust in a combined propulsion engine, and its performance is crucial to the overall performance of the engine.

[0003] A major challenge of wide-range flight is the significant variation in engine operating conditions and flow rates as the aircraft's altitude and speed change. For commonly used turbojet-ramjet combined engines, thrust generation at low Mach numbers primarily relies on the turbine engine. As the Mach number increases, the ramjet engine gradually starts generating thrust, while the turbine engine deactivates and gradually shuts down. This process involves substantial flow rate changes, necessitating the design of a regulating mechanism to accurately control the combined nozzle's operating conditions. Furthermore, turbine engines typically have inner and outer bypass ducts, making it another significant challenge to coordinate the flow rates and operating conditions across the three flow channels (ramjet and turbine engines). Summary of the Invention

[0004] Purpose of the invention: To address the aforementioned problems, this invention proposes an axisymmetric, three-channel adjustable turbo-ramjet combined power nozzle. By mechanically adjusting the flow direction and position of the inner and outer plug cones, the throat and expansion ratio of the inner and outer bypass ducts of the turbojet engine are controlled, thereby regulating the operating state and flow rate of the combined power engine nozzle and meeting the different operating conditions required by the combined power engine under a wide operating range.

[0005] Technical solution:

[0006] An axisymmetric three-channel adjustable turbo-ramjet combined power nozzle, wherein the ramjet channel, the turbine channel outer bypass duct, and the turbine channel inner bypass duct of the turbo-ramjet combined power nozzle are arranged in a ring shape;

[0007] The turbo-ramjet combined power nozzle includes an adjustable inner plug cone, an inner duct wall, an adjustable outer plug cone, an outer bypass duct wall, and an outer wall. The annular flow channel formed between the inner surfaces of the adjustable inner plug cone and the inner duct wall is the inner duct of the turbine channel. The outer surface of the inner duct wall, the adjustable outer plug cone, and the inner surface of the outer bypass duct wall form the outer bypass duct of the turbine channel. The outer surface and outer wall of the outer bypass duct wall form the ramjet channel. Different positions of the adjustable inner plug cone and the inner duct wall combine to form the adjustable throat and adjustable outlet of the inner duct flow channel of the turbine channel. Different positions of the adjustable outer plug cone and the outer bypass duct wall combine to form the adjustable throat and adjustable outlet of the outer bypass duct flow channel of the turbine channel.

[0008] Preferably, the opening and closing of the turbine passage outer bypass duct and the turbine passage inner duct, as well as the adjustment of the throat area and expansion ratio, are achieved by the separate translation of the adjustable inner plug cone and the adjustable outer plug cone.

[0009] The adjustable inner cone is driven to translate by the first mechanical adjustment mechanism. When the adjustable inner cone is closest to the nozzle exit, the inner duct of the turbine passage is closed. As the adjustable inner cone moves towards the nozzle inlet, the inner duct gradually opens, and the throat area and the outlet area gradually increase.

[0010] The adjustable outer plug cone is driven to translate by the second mechanical adjustment mechanism. When the adjustable outer plug cone is closest to the nozzle exit, the turbine passage outer bypass is closed. As the adjustable inner plug cone moves towards the nozzle inlet, the outer bypass gradually opens, and the throat area and exit area gradually increase.

[0011] The first and second mechanical adjustment structures are combined to adjust the flow rate and operating conditions of the nozzle to meet different requirements.

[0012] Preferably, the sliding at the connection between the adjustable outer plug cone and the outer surface of the inner channel wall includes, but is not limited to, leaving a gap between the contact surfaces and sliding by means of a slide rail and pulley. The driving methods of the adjustable inner plug cone and the adjustable outer plug cone include, but are not limited to, connecting rods and gears.

[0013] Beneficial effects:

[0014] This invention proposes an axisymmetric three-channel adjustable turbo-ramjet combined power nozzle and its adjustment scheme, which has the following advantages:

[0015] (1) Adjustment is achieved by the translation of the inner and outer plug cones. The mechanical structure is simple and the adjustment is easy.

[0016] (2) The throats of the inner and outer bypass channels of the turbine engine are individually adjustable and can be combined to adapt to the working adjustment requirements of complex combined power nozzles.

[0017] (3) After the inner and outer plug cones are translated to the point where the throat area is the largest, the translation can continue to increase the cross-sectional area of ​​the corresponding flow channel outlet, thereby increasing the expansion ratio. By adjusting the front and rear positions of the throat formed by the inner and outer plug cones, the expansion degree of the gas under different working conditions can be adjusted in conjunction with the adjustment of the expansion ratio, which is beneficial to having excellent performance under complex working conditions. Attached Figure Description

[0018] Figure 1 This is a cross-sectional view of the throat area of ​​the combined power nozzle when the inner and outer bypass ducts are at their maximum.

[0019] Figure 2 This is a perspective view of the overall structure of the combined power nozzle.

[0020] Figure 3 This is a cross-sectional view of the combined power nozzle with both the inner and outer ducts closed, and the ramjet channel operating alone.

[0021] Figure 4 This is a cross-sectional view of the throat area of ​​the combined power nozzle when the inner and outer bypass ducts are at their maximum.

[0022] Figure 5 This is a schematic diagram of the mechanical adjustment structure.

[0023] Figure 6 This is a cross-sectional view of the combined power nozzle at a certain moment during its operation.

[0024] In the figure: Adjustable inner plug cone (1), inner duct wall (2), adjustable outer plug cone (3), outer bypass wall (4), outer wall (5), adjustable throat of turbine channel inner duct flow channel (6), adjustable outlet of turbine channel inner duct (7), adjustable throat of turbine channel outer bypass duct (8), adjustable outlet of turbine channel outer bypass duct (9). Detailed Implementation

[0025] The invention will now be further explained with reference to the accompanying drawings.

[0026] An axisymmetric three-channel adjustable turbo-ramjet combined power nozzle is provided, in which the different channels are arranged in parallel in a ring. The outermost ring is the ramjet channel, the middle annular flow channel is the turbine channel outer bypass channel, and the inner ring is the turbine channel inner bypass channel. The inner and outer plug cones are used to open and close the inner and outer bypass channels of the turbine engine and regulate the flow.

[0027] The main components include an adjustable inner plug cone 1 that moves along the flow direction via a first mechanical structure, a fixed inner duct wall 2, an adjustable outer plug cone 3 that moves along the flow direction via a second mechanical structure, a fixed outer bypass duct wall 4, and a fixed outer wall 5; the structure includes an adjustable throat 6 and an adjustable outlet 7 formed by different combinations of the adjustable inner plug cone 1 and the inner duct wall 2; the adjustable outer plug cone 3 and the outer bypass duct wall 4 formed by different combinations of the adjustable outer plug cone 3 and the outer bypass duct wall 4 formed the adjustable throat 8 and the adjustable outlet 9 of the turbine channel outer bypass duct; the adjustable inner plug cone 1 and the inner duct wall 2 form the inner duct of the turbine engine nozzle, the adjustable outer plug cone 3, the outer bypass duct wall 4, and the outer surface of the inner duct wall 2 form the outer bypass duct of the turbine engine nozzle, and the outer surface of the outer bypass duct wall 4 and the outer wall 5 form the ramming channel.

[0028] When the adjustable inner plug cone 1 approaches the nozzle tail, the surface of the adjustable inner plug cone 1 is connected to the inner channel wall 2, and the turbine channel inner channel is in a closed state. When the adjustable inner plug cone 1 moves towards the nozzle inlet, the inner channel wall 2 at the front end of the connection point is tilted at a certain angle, and the tilt angle at the rear end of the connection point of the adjustable inner plug cone 1 is even greater. Therefore, the tilt of the connection point of the adjustable inner plug cone 1 and the inner channel wall 2 forms the throat with the smallest cross-sectional area in the flow channel. As the adjustable inner plug cone 1 moves, the throat height gradually increases, and the cross-sectional area of ​​the throat gradually increases. During this process, the adjustable throat 6 of the turbine channel's inner duct gradually moves forward. The throat position reaches its maximum when the adjustable inner plug cone 1 forms the starting point of the inclined surface of the inner duct wall corresponding to the throat position. Subsequently, as the adjustable inner plug cone 1 continues to move forward, the throat position moves forward while the throat area remains unchanged. Simultaneously, the nozzle exit height 7 increases, and the nozzle expansion ratio increases. This allows for different throat areas and positions, as well as different expansion ratios, within the turbine engine's inner duct to adapt to different operating conditions. When the ramjet channel operates independently, the adjustable inner plug cone 1 is located at the tail of the combined power nozzle, and the turbine channel's inner duct is closed.

[0029] The turbine engine's bypass duct flow channel is mainly composed of the outer bypass duct wall 4 and the outer surface of the inner bypass duct wall 2. When the adjustable outer plug cone 3 approaches the nozzle tail, its surface connects to both the outer and inner bypass duct walls, blocking the flow channel and keeping the turbine passage bypass duct closed. When the adjustable outer plug cone 3 moves towards the nozzle inlet, due to the inclined angle of the wall near its connection with the outer bypass duct wall, the adjustable outer plug cone 3 and the outer bypass duct wall 4 form the contraction section of the bypass duct flow channel, the adjustable throat 8 of the turbine passage bypass duct flow channel, and the expansion section. Because the outer plug cone and the outer bypass duct wall have different angles, the throat area of ​​the bypass duct increases during this process. As the throat area increases, the area of ​​the bypass duct outlet 9 also increases, changing the expansion ratio of the bypass duct. After the adjustable outer plug cone 3 moves a certain distance, the throat area of ​​the outer bypass duct throat 8 reaches its maximum. At this point, if the adjustable outer plug cone 3 continues to move towards the nozzle inlet, the area of ​​the outer bypass duct outlet 9 will increase. The outer duct outlet area reaches its maximum when the rear end of the plug cone is flush with the rear end of the outer duct wall 4.

[0030] The ramjet engine nozzle flow channel is formed by the outer surface of the outer bypass wall 4 and the outer wall 5. The ramjet channel inlet of the combined power nozzle is connected to the combustion chamber of the scramjet engine. It is a supersonic inlet. After passing through a certain equal cross-sectional area transition section, it is connected to the expansion section. After the gas expands in the expansion section, it is ejected from the outlet.

[0031] When the combined power engine operates in the low-speed range, the turbine engine generates thrust, and the inner and outer bypass channels of the turbine channel change the positions of the inner and outer plug cones according to the specific operating conditions to adjust the size of the throat and outlet. As the operating Mach number increases to a certain level, the ramjet engine starts, and the turbine engine adjusts the positions of the inner and outer plug cones according to the requirements of the operating conditions and the operating state of the ramjet engine. When the operating Mach number continues to increase, the ramjet engine generates the main thrust, the turbine engine gradually stops working, and the inner and outer plug cones move towards the rear end of the combined power engine, gradually closing the inner and outer bypass channels.

[0032] Since the outer surfaces of the outer plug cone 3 and the inner channel wall 2 are geometrically connected, when the outer plug cone translates, it moves relative to the outer surface of the inner channel wall, generating friction and mechanical wear on the structure. A certain gap or lubrication can be set at the junction, and a slide rail can be added to the outer surface of the inner channel wall 2. Several slide rails are set on the annular junction surface, and corresponding rollers are set on the outer plug cone and connected. A sealing ring is set on the side of the slide rail to reduce air leakage and protect the structure of the nozzle wall during relative movement.

[0033] according to Figure 1 and Figure 2 The combined power nozzle of this invention has an annular axisymmetric structure. The flow channel has an annular structure, with different flow channels arranged in inner and outer rings. The innermost ring is the turbine channel inner duct, the middle ring is the turbine channel outer bypass duct, and the outermost ring is the ramjet channel flow channel.

[0034] Figure 3 When the flight Mach number is high, according to the operating conditions, both the inner and outer plug cones move to a position close to the rear end of the combined power unit, so that both the inner and outer bypass ducts are closed, the turbine channel stops working, and the ramjet channel works independently.

[0035] Figure 4 According to the operating conditions, both the inner and outer cones are moved to a certain position to maximize the outlet area of ​​the inner and outer ducts. Figure 1 The areas of the middle larynx are all the same, representing the largest larynx area. Figure 4 The expansion ratio is greater in the middle.

[0036] Figure 5 The diagram shows the translational motion of the inner and outer piston cones controlled by the first and second mechanical adjustment structures, respectively.

[0037] Figure 6 The middle section is a cross-sectional diagram showing the adjustment position of the inner and outer piston cones in a certain intermediate working state of a certain combined power engine, according to the working conditions required.

Claims

1. An axisymmetric three-channel adjustable turbo-ramjet combined power nozzle, characterized in that, The ramming channel, turbine channel outer bypass duct, and turbine channel inner bypass duct of the turbo-ramjet combined power nozzle are arranged in a ring shape. The turbo-ramjet combined power nozzle includes an adjustable inner plug cone (1), an inner duct wall (2), an adjustable outer plug cone (3), an outer bypass duct wall (4), and an outer wall (5); the annular flow channel formed between the inner surfaces of the adjustable inner plug cone (1) and the inner duct wall (2) is the inner duct of the turbine channel; the outer surface of the inner duct wall (2), the adjustable outer plug cone (3), and the inner surface of the outer bypass duct wall (4) form the outer bypass duct of the turbine channel; the outer surface of the outer bypass duct wall (4) and the outer wall (5) form the ramjet channel; the different positions of the adjustable inner plug cone (1) and the inner duct wall (2) form the adjustable throat (6) and the adjustable outlet (7) of the inner duct flow channel of the turbine channel; the different positions of the adjustable outer plug cone (3) and the outer bypass duct wall (4) form the adjustable throat (8) and the adjustable outlet (9) of the outer bypass duct flow channel of the turbine channel.

2. The axisymmetric three-channel adjustable turbo-ramjet combined power nozzle according to claim 1, characterized in that, The opening and closing of the turbine passage outer bypass duct and the adjustment of the throat area and expansion ratio are achieved by the separate translation of the adjustable inner plug cone (1) and the adjustable outer plug cone (3); The adjustable inner cone (1) is driven to translate by the first mechanical adjustment mechanism. When the adjustable inner cone (1) is closest to the nozzle outlet, the inner duct of the turbine passage is closed. As the adjustable inner cone (1) moves towards the nozzle inlet, the inner duct of the turbine passage gradually opens, and the throat area and outlet area gradually increase. The adjustable outer plug cone (3) is driven to translate by the second mechanical adjustment mechanism. When the adjustable outer plug cone (3) is closest to the nozzle outlet, the turbine passage outer bypass is closed. As the adjustable inner plug cone (1) moves towards the nozzle inlet, the turbine passage outer bypass gradually opens, and the throat area and outlet area gradually increase. The first and second mechanical adjustment structures are combined to adjust the flow rate and operating conditions of the nozzle to meet different requirements.

3. The axisymmetric three-channel adjustable turbo-ramjet combined power nozzle according to claim 2, characterized in that, The sliding at the connection between the adjustable outer plug cone (3) and the outer surface of the inner channel wall (2) includes, but is not limited to, leaving a gap between the contact surfaces and sliding through a slide rail and pulley. The driving methods of the adjustable inner plug cone (1) and the adjustable outer plug cone (3) include, but are not limited to, connecting rods and gears.

Images