A combined nozzle and its adjustment method

Abstract

The present invention belongs to the field of combined propulsion systems for hypersonic aircraft, specifically relating to a combined nozzle and its adjustment method. This invention can simultaneously adjust the turbine nozzle throat area while adjusting the diverter plate between the turbine and ramjet channels. This improves the matching between the nozzle's pressure drop ratio and area expansion ratio, alleviates the overexpansion of the ramjet channel during low-Mach-number flight and the underexpansion of the turbine channel during high-Mach-number flight, and enhances the thrust performance of the combined propulsion nozzle across a wide speed range, thereby effectively improving the flight performance of the hypersonic aircraft.

Description

Technical Field

[0001] The present invention belongs to the field of combined power devices for hypersonic aircraft, and relates to a combined power unilateral expansion nozzle with good aerodynamic performance, an adjustable throat and a diverter plate, and an adjustment method thereof. Background Art

[0002] The present invention solves the problem of severe thrust performance degradation encountered when the nozzle of a conventional hypersonic aircraft combined power unit has wide-speed range incoming flow conditions.

[0003] Hypersonic aircraft are generally driven by a combined power unit. Commonly used combined power modes include turbine-based ramjet engines and rocket-based ramjet engines.

[0004] Conventional parallel turbine-based ramjet dual-channel combined nozzles meet the flow requirements of the turbine and ramjet channels solely through throat adjustment, while the rate of change of the area behind the throat is fixed. However, due to the low design point of the combined turbine nozzle and the high design point of the ramjet nozzle in hypersonic vehicles, the ramjet channel tends to overexpand at low Mach numbers, while the turbine channel underexpands at high Mach numbers, resulting in a significant decrease in combined nozzle thrust performance when the nozzle deviates from the design point. Therefore, it is necessary to design a combined power single-sided expansion nozzle with good aerodynamic performance and an adjustable throat and diverter plate to meet the needs of hypersonic vehicles. Summary of the Invention

[0005] The object of the present invention is to provide a combined power unilateral expansion nozzle with an adjustable throat and a diverter plate and an adjustment method thereof, which ensures the functions of a conventional unilateral expansion combined nozzle while having better thrust performance, thereby compensating for the defect of low thrust efficiency of the conventional unilateral expansion combined nozzle when the flow deviates from the design point under wide-speed range conditions.

[0006] The technical solution of the present invention:

[0007] A combined nozzle and an adjustment method thereof, specifically a combined power single-side expansion nozzle with simultaneously adjustable throat and diverter plate, comprising a turbine nozzle upper fixed edge 001, a turbine nozzle upper expansion edge 002, a turbine nozzle lower fixed edge 003, a turbine nozzle throat adjustment edge 004, a turbine nozzle telescopic adjustment edge 005, a ram nozzle movable upper expansion edge 006, a ram nozzle lower wall plate 007, a turbine nozzle actuator 008, and a ram nozzle actuator 009, specifically:

[0008] The front ends of the turbine nozzle's upper fixed edge 001 and lower fixed edge 003 are connected to the turbine engine, serving as a transition between the turbine engine and the turbine nozzle, bridging the circular turbine engine outlet and the square turbine nozzle inlet. The front end of the turbine nozzle's upper expansion edge 002 is affixed to the rear end of the turbine nozzle's upper fixed edge 001, and the rear end of the turbine nozzle's upper expansion edge 002 is connected to the hypersonic vehicle's rear body.

[0009] The front end of the turbine nozzle throat adjustment edge 004 is hinged to the rear end of the turbine nozzle lower fixed edge 003, serving as a fulcrum for turbine nozzle adjustment. The middle of this edge is hinged to one end of the turbine nozzle actuator 008. The front end of the ramjet nozzle's movable upper expansion edge 006 is hinged to the ramjet engine, serving as a fulcrum for ramjet adjustment. The middle of this edge is hinged to one end of the ramjet actuator 009. The front end of the turbine nozzle's retractable edge 005 is hinged to the rear end of the turbine nozzle's throat edge 004. Its other end is also hinged to the rear end of the ramjet nozzle's movable upper expansion edge 006. To compensate for the change in distance between the hinges at both ends of the turbine nozzle's retractable edge 005 when adjusting the turbine nozzle's throat edge 004 and the ramjet nozzle's movable upper expansion edge 006, the turbine nozzle's retractable edge 005 is a retractable flat plate connected by two-stage slide rails. This connection mechanism forms a nozzle motion mechanism with hinges at both ends, allowing for simultaneous adjustment of the throat area and diverter plate.

[0010] The turbine nozzle actuator cylinder 008 and the ramjet nozzle actuator cylinder 009 are the driving sources of the combined power nozzle. One end of them is connected to the aircraft body through a hinge, and the other end is connected to the turbine nozzle throat adjustment edge 004 and the ramjet nozzle movable upper expansion edge 006 respectively.

[0011] The turbine nozzle upper expansion edge 002 is fixed to the aircraft body and cannot be adjusted.

[0012] The ramjet nozzle lower wall panel 007 is a fixed structure and does not require adjustment. Its shape can be adapted to the aerodynamic shape of the hypersonic aircraft.

[0013] Furthermore, the expansion edge 002 of the turbine nozzle is a plane or a curved surface.

[0014] Furthermore, the optimized designed ramjet nozzle lower wall panel 007 can generate smaller flow resistance under different flight conditions.

[0015] Furthermore, the surface of the ram nozzle lower wall plate 007 is a plane, a curved surface or a combination of different surfaces.

[0016] A method for adjusting a combined nozzle involves the following steps: When the turbine nozzle actuator 008 extends, the turbine nozzle throat adjustment edge 004 rotates upward, reducing the turbine nozzle throat area. The ram nozzle, however, utilizes a thermal throat design, and the throat area is not mechanically adjusted. The ram nozzle actuator 009 adjusts the ram nozzle area expansion ratio. When the ram nozzle actuator 009 shortens, the ram nozzle movable upper expansion edge 006 rotates upward, increasing the ram nozzle area expansion ratio. The turbine nozzle telescopic adjustment edge 005 rotates under the constraints of hinges at both ends, while simultaneously achieving relative motion via slide rails to match the change in spacing between the hinges during movement. At this point, the turbine nozzle telescopic adjustment edge 005 also rotates upward as the turbine nozzle throat adjustment edge 004 and the ram nozzle movable upper expansion edge 006 move, reducing the turbine nozzle area expansion ratio. By adjusting the combined nozzle diverter plate, the area expansion ratio of the turbine nozzle is reduced while the area expansion ratio of the ramjet nozzle is increased, meeting the requirements of a large drop pressure ratio of the ramjet nozzle and a small drop pressure ratio of the turbine nozzle under high Mach number flight conditions; conversely, it can adapt to the requirements of a large drop pressure ratio of the turbine nozzle and a small drop pressure ratio of the ramjet nozzle under low Mach number flight conditions.

[0017] The combined power single-sided expansion nozzle with simultaneously adjustable throat and diverter plate provided by the present invention has the advantages of ensuring the adjustable throat area function of a conventional single-sided expansion nozzle while achieving the distribution of the area expansion ratio of the turbine nozzle and the ramjet nozzle by adjusting the diverter plate between the turbine channel and the ramjet channel, thereby avoiding the over-expansion problem of the ramjet channel during low Mach number flight and the under-expansion problem of the turbine channel during high Mach number flight of the conventional combined power single-sided expansion nozzle, and having the advantage of improving the thrust performance of the combined power nozzle over a wide speed range. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Front view of the adjustable combined power unilateral expansion nozzle.

[0019] Figure 2 Diagram of the adjustment mechanism of the combined power unilateral expansion nozzle with adjustable throat and diverter plate at the same time.

[0020] Figure 3 Comparison of different states of the combined power unilateral expansion nozzle with adjustable throat and diverter plate.

[0021] In the figure: 001 turbine nozzle upper fixed edge; 002 turbine nozzle upper expansion edge; 003 turbine nozzle lower fixed edge; 004 turbine nozzle throat adjustment edge; 005 turbine nozzle retractable adjustment edge; 006 ramjet nozzle movable upper expansion edge; 007 ramjet nozzle lower wall plate; 008 turbine nozzle actuator; 009 ramjet nozzle actuator. DETAILED DESCRIPTION

[0022] The present invention provides a combined power single-sided expansion nozzle with adjustable throat and diverter plate, characterized by comprising: a turbine nozzle upper fixed edge 001, a turbine nozzle upper expansion edge 002, a turbine nozzle lower fixed edge 003, a turbine nozzle throat adjustment edge 004, a turbine nozzle telescopic adjustment edge 005, a ram nozzle movable upper expansion edge 006, a ram nozzle lower wall plate 007, a turbine nozzle actuator 008, and a ram nozzle actuator 009, specifically:

[0023] The front ends of the turbine nozzle's upper fixed edge 001 and lower fixed edge 003 are connected to the turbine engine, serving as a transition between the turbine engine and the turbine nozzle, bridging the circular turbine engine outlet and the square turbine nozzle inlet. The front end of the turbine nozzle's upper expansion edge 002 is affixed to the turbine nozzle's upper fixed edge 001, and its rear end is connected to the hypersonic vehicle's rear body.

[0024] The front end of the turbine nozzle throat adjustment edge 004 is hinged to the turbine nozzle lower fixed edge 003, serving as a fulcrum for turbine nozzle adjustment. The middle portion of the turbine nozzle throat adjustment edge 004 is hinged to the turbine nozzle actuator 008. The front end of the ramjet nozzle movable upper expansion edge 006 is hinged to the ramjet engine, serving as a fulcrum for ramjet adjustment. The middle portion of the ramjet nozzle movable upper expansion edge 006 is hinged to the ramjet actuator 009. The front end of the turbine nozzle telescopic adjustment edge 005 is hinged to the turbine nozzle throat adjustment edge 004, and the other end is hinged to the ramjet movable upper expansion edge 006. To compensate for the change in distance between the hinges at both ends of the turbine nozzle telescopic adjustment edge 005 during adjustment of the turbine nozzle throat adjustment edge 004 and the ramjet movable upper expansion edge 006, the turbine nozzle telescopic adjustment edge 005 is a retractable flat plate connected to two sections of sliding rails. The connection mechanism forms a nozzle movement mechanism with hinges at both ends, in which the throat area and the diverter plate can be adjusted simultaneously.

[0025] The turbine nozzle actuator 008 and the ramjet nozzle actuator 009 are the driving sources for the combined power nozzle. One end is hinged to the aircraft body, and the other end is connected to the turbine nozzle throat adjustment edge 004 and the ramjet nozzle movable upper expansion edge 006, respectively. When the turbine nozzle actuator 008 extends, the turbine nozzle throat adjustment edge 004 rotates upward, reducing the turbine nozzle throat area. The ramjet nozzle, on the other hand, utilizes a thermal throat design, and the throat area is not mechanically adjusted. The ramjet actuator 009 adjusts the ramjet area expansion ratio. When the ramjet actuator 009 shortens, the ramjet movable upper expansion edge 006 rotates upward, increasing the ramjet area expansion ratio. The turbine nozzle telescopic adjustment edge 005 rotates under the constraints of the hinges at both ends, while slide rails enable relative motion to match the changes in spacing between the hinges during movement. At this point, the turbine nozzle's retractable adjustment edge 005 also rotates upward along with the movement of the turbine nozzle throat adjustment edge 004 and the ramjet nozzle's movable upper expansion edge 006, reducing the turbine nozzle's area expansion ratio. By adjusting the combined nozzle manifold, the turbine nozzle's area expansion ratio decreases while the ramjet nozzle's area expansion ratio increases, meeting the requirements of a high ramjet nozzle's high pressure drop ratio and a low turbine nozzle's low pressure drop ratio under high Mach number flight conditions. Conversely, the requirements of a high turbine nozzle's high pressure drop ratio and a low ramjet nozzle's low pressure drop ratio can be met under low Mach number flight conditions.

[0026] The turbine nozzle upper expansion edge 002 is fixed to the aircraft body and cannot be adjusted.

[0027] The expansion edge 002 of the turbine nozzle is a plane or a curved surface.

[0028] The ramjet nozzle lower panel 007 is a fixed structure that does not require adjustment. Its shape can be adapted to the aerodynamic shape of the hypersonic vehicle. The optimized design of the ramjet nozzle lower panel 007 can produce less flow resistance under different flight conditions.

[0029] The 007 surface of the ram nozzle lower wall plate is a plane, a curved surface or a combination of different surfaces.

[0030] The present invention provides a high-performance combined power single-sided expansion nozzle and adjustment method for simultaneously adjusting the throat and diverter plate. This invention can simultaneously adjust the turbine nozzle throat area and the diverter plate between the turbine and ramjet channels, better matching the nozzle pressure drop ratio with the area expansion ratio. This alleviates the overexpansion problem of the ramjet channel during low Mach number flight and the underexpansion problem of the turbine channel during high Mach number flight, improving the thrust performance of the combined power nozzle across a wide speed range, thereby effectively enhancing the flight performance of hypersonic aircraft.

Claims

1. A combined nozzle, characterized in that: It includes a turbine nozzle upper fixed edge (001), a turbine nozzle upper expansion edge (002), a turbine nozzle lower fixed edge (003), a turbine nozzle throat adjustment edge (004), a turbine nozzle telescopic adjustment edge (005), a ram nozzle movable upper expansion edge (006), a ram nozzle lower wall plate (007), a turbine nozzle actuator (008), and a ram nozzle actuator (009), specifically: The front ends of the turbine nozzle upper fixed edge (001) and the turbine nozzle lower fixed edge (003) are connected to the turbine engine, serving as a transition section between the turbine engine and the turbine nozzle, thereby achieving the connection between the circular turbine engine outlet and the square turbine nozzle inlet; the front end of the turbine nozzle upper expansion edge (002) is fixedly connected to the rear end of the turbine nozzle upper fixed edge (001), and the rear end of the turbine nozzle upper expansion edge (002) is connected to the rear body of the hypersonic aircraft; The front end of the turbine nozzle throat adjustment edge (004) is connected to the rear end of the turbine nozzle lower fixed edge (003) through a hinge, serving as a fulcrum for the turbine nozzle adjustment. The middle of the turbine nozzle throat adjustment edge (004) is connected to one end of the turbine nozzle actuator (008) through a hinge. The front end of the ramjet nozzle movable upper expansion edge (006) is hinged to the ramjet engine, serving as a fulcrum for the ramjet nozzle adjustment. The middle of the ramjet nozzle movable upper expansion edge (006) is connected to one end of the ramjet actuator (009) through a hinge. The front end of the turbine nozzle telescopic adjustment edge (005) is connected to the turbine nozzle throat adjustment edge (004) through a hinge. ) is connected to the rear end, and the other end is connected to the rear end of the ramjet nozzle movable upper expansion edge (006) through a hinge. In order to compensate for the change in the distance between the hinges at both ends of the turbine nozzle telescopic adjustment edge (005) when the turbine nozzle throat adjustment edge (004) and the ramjet nozzle movable upper expansion edge (006) are adjusted, the turbine nozzle telescopic adjustment edge (005) is a telescopic flat plate plugged into a two-section slide rail; the turbine nozzle throat adjustment edge (004), the turbine nozzle telescopic adjustment edge (005), and the ramjet nozzle movable upper expansion edge (006) together form a nozzle movement mechanism with hinges at both ends and the throat area and the diverter plate being adjustable at the same time; The turbine nozzle actuator (008) and the ramjet nozzle actuator (009) are driving sources of the combined power nozzle, one end of which is connected to the hypersonic aircraft through a hinge, and the other end is respectively connected to the turbine nozzle throat adjustment edge (004) and the ramjet nozzle movable upper expansion edge (006); the turbine nozzle upper expansion edge (002) is fixed to the hypersonic aircraft and cannot be adjusted; The ramjet nozzle lower wall plate (007) is a fixed structure and does not need to be adjusted. Its shape can be designed to adapt to the aerodynamic shape of the hypersonic aircraft.

2. A combined nozzle according to claim 1, characterized in that: The expansion edge (002) of the turbine nozzle is a plane or a curved surface.

3. A combined nozzle according to claim 1, characterized in that: The ram nozzle lower wall plate (007) has a surface that is a plane, a curved surface, or a combination of different surfaces.

4. A method for adjusting a combined nozzle according to any one of claims 1 to 3, characterized in that: The specific process is as follows: when the turbine nozzle actuator (008) is extended, the turbine nozzle throat adjustment edge (004) rotates upward, and the turbine nozzle throat area is reduced; while the ramjet nozzle adopts a thermal throat design, the throat area is not mechanically adjusted, and the ramjet nozzle actuator (009) is used to adjust the ramjet nozzle area expansion ratio. When the ramjet nozzle actuator (009) is shortened, the ramjet nozzle movable upper expansion edge (006) rotates upward, and the ramjet nozzle area expansion ratio increases; the turbine nozzle telescopic adjustment edge (005) rotates under the constraints of the hinges at both ends, and at the same time realizes relative movement through the slide rail to match The distance between the two end hinges changes during the movement; at this time, the telescopic adjustment edge (005) of the turbine nozzle also rotates upward with the movement of the turbine nozzle throat adjustment edge (004) and the movable upper expansion edge (006) of the ramjet nozzle, so that the area expansion ratio of the turbine nozzle is reduced; by adjusting the combined nozzle diverter plate, the area expansion ratio of the turbine nozzle is reduced and the area expansion ratio of the ramjet nozzle is increased, meeting the requirements of the ramjet nozzle for a large pressure drop ratio and the turbine nozzle for a small pressure drop ratio under high Mach number flight conditions; conversely, it can adapt to the requirements of the turbine nozzle for a large pressure drop ratio and the ramjet nozzle for a small pressure drop ratio under low Mach number flight conditions.

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