CN106150757A - A kind of dual pathways becomes geometry rocket based combined cycle electromotor - Google Patents

Abstract

The invention discloses a dual-channel variable-geometry rocket-based combined cycle engine, which adopts a dual-channel structure and realizes good work in a wide flight range through a partitioned combustion mode; the dual channels work simultaneously in a low-speed flight state to complete ejection mode and sub-stage The work in the low-speed section of the combustion mode; in the high-speed flight state, it is converted to the high-speed channel to work alone, and completes the work of the high-speed section of the sub-combustion mode and the super-combustion mode. The variable geometry method that the top pressure plate rotates around the rotating shaft is used to realize the adjustment of the small shrinkage ratio in the low-speed flight state and the large shrinkage ratio in the high-speed flight state, and meet the air capture and airflow compression requirements under different flight Mach numbers in a wide range of the engine. The binary mixed pressure inlet is adopted, the top pressure plate and the side plate of the inlet have good adhesion, and the mechanical dynamic seal is easy to realize, which is suitable for engineering applications; it meets the power requirements of different working modes of the aircraft. The top pressure plate and the conversion plate are respectively connected to the rotating shaft of the double fulcrum structure, the structure is rigid, and the high temperature sealing is easy to realize.

Description

A dual-channel variable geometry rocket-based combined cycle engine

technical field

The invention relates to the field of air-breathing combined ramjet engines, in particular to a dual-channel variable geometry rocket-based combined cycle engine.

Background technique

Rocket-Based Combined Cycle RBCC (Rocket-Based Combined Cycle) engine organically integrates a rocket engine with a high thrust-to-weight ratio and an air-breathing ramjet engine with a high specific impulse in the same flow channel, and is compatible with ejection, sub-combustion, scramjet and pure rockets Mode, to achieve high-performance work in wide speed range and large airspace. How to ensure that the same engine can achieve good operation of each mode in such a wide range of Mach numbers, and the smooth transition between different modes is the key to the success of the rocket-based combined cycle engine. The configuration and working method of the rocket-based combined cycle engine play a decisive role. In particular, how to ensure that the inlet of the rocket-based combined cycle engine meets the performance requirements under different flight conditions, and at the same time ensure a good match between the inlet and the rocket is the key technology in the research.

At present, the commonly used rocket-based combined cycle engine structure scheme is "variable geometry inlet + mid/side rocket + fixed geometry combustion chamber + variable geometry tail nozzle". Usually, in order to facilitate the integration of aircraft/engine, binary rocket-based combined cycle inlets often use the height of the lifting throat to adjust the shrinkage ratio, and at the same time cooperate with flow control technology or boundary layer suction equivariant geometric schemes, such as "built-in Design and Numerical Simulation of Variable Geometry Binary Inlets for Rocket-Based Combined Cycle with Central Support Plate" ("Solid Rocket Technology", Vol. 37, No. 2, 2014, pp. 184-191); side-pressure rocket-based combined cycle The commonly used variable geometry scheme of the inlet is to lift the top pressure plate to adjust the shrinkage ratio, such as "The Strutjet Engine: The Overlooked Option for Space Launch" (AIAA, 95-3124, 1995). These two ways of changing the geometry of the inlet port can realize the adjustment of the compression ratio of the rocket-based combined cycle inlet port under different conditions, but there are also certain shortcomings:

(1) The binary inlet adopts the variable geometry method of the lifting throat, and there must be a follow-up section between it and the combustion chamber, which will not only cause serious high-temperature dynamic sealing problems, but also limit the layout of the rocket engine. The matching between the inlet port and the rocket is poor;

(2) The flow control method of boundary layer suction is adopted in the air inlet, and additional auxiliary devices must be configured, which will bring redundant mass and additional resistance to the aircraft;

(3) The side-pressure air inlet adopts the variable geometry method of lifting the top pressure plate, which will cause the geometric matching between the top pressure plate, the side pressure plate and the support plate to be difficult, and serious mechanical sealing problems will occur.

Contents of the invention

In order to avoid the shortcomings of the prior art, the present invention proposes a double-channel variable geometry rocket-based combined cycle engine.

The technical scheme that the present invention adopts to solve its technical problem is: comprise inlet port, high-speed passage, low-speed passage, built-in rocket, combustion chamber, tail nozzle, combustion enhancement device, top pressure plate, conversion plate, first rotating shaft, second The rotating shaft, the first actuating mechanism, and the second actuating mechanism, the air inlet is a double-channel structure composed of a high-speed channel and a low-speed channel, the low-speed channel is located above the high-speed channel, and a top pressure plate is installed on the front of the upper wall of the air inlet One end of the top pressure plate is connected to the fuselage through the first rotating shaft, and the upper part of the other end is connected to the first actuating mechanism, which is installed on the fuselage; The body is connected through the second rotating shaft, and the upper part of the other end is connected with the second actuating mechanism, and the second actuating mechanism is installed on the fuselage; the low-speed channel is closed when the top pressure plate and the conversion plate are respectively rotated to contact with the lower wall of the low-speed channel; Built-in rockets are respectively installed on the front and back of the upper wall of the high-speed passage and the low-speed passage, and the rear built-in rocket is located at the front end of the tail nozzle, the combustion chamber is located in the high-speed passage, and a combustion enhancement device is installed in the combustion chamber.

The combustion chamber is a rectangular or circular structure; the tail nozzle is a single-side expansion nozzle.

The combustion enhancement device is one of a fuel support plate or a cavity, or a combination of a fuel support plate and a cavity.

There are multiple built-in rockets.

Beneficial effect

A dual-channel variable geometry rocket-based combined cycle engine proposed by the present invention adopts a dual-channel structure, and realizes good work in a wide flight range through a partitioned combustion mode. The dual channels work simultaneously under low-speed flight conditions to complete ejection mode and The work in the low-speed section of the sub-combustion mode; in the high-speed flight state, it is converted to the high-speed channel to work alone, and completes the work of the high-speed section of the sub-combustion mode and the super-combustion mode; the variable geometry that the top pressure plate rotates around the first rotation axis in a small range The method realizes the adjustment of the small contraction ratio in the low-speed flight state and the large contraction ratio in the high-speed flight state, and meets the air capture and airflow compression requirements of the rocket-based combined cycle engine under different flight Mach numbers in a wide range; the variable geometry inlet adopts binary mixing In the air inlet with pressure structure, the top pressure plate and the side plate of the air inlet have better adhesion, and the mechanical dynamic seal between the two is easier to realize during the variable geometry action, avoiding additional pneumatic control such as boundary layer suction The use of means is suitable for practical engineering applications; through reasonable rocket configuration design and working parameter distribution, flexible and diverse combustion organization methods are formed to effectively meet the power requirements of different working modes of the aircraft; the top pressure plate and the conversion plate are respectively connected to a The rotating shaft with double fulcrum structure has good structural rigidity and is easy to realize high temperature sealing.

Description of drawings

A dual-channel variable geometry rocket-based combined cycle engine of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

Figure 1 is a schematic diagram of the structure of a dual-channel variable geometry rocket-based combined cycle engine.

Fig. 2 is a schematic diagram of the operation of the dual-channel variable geometry rocket-based combined cycle engine in the range of Mach 0 to 3.

Fig. 3 is a schematic diagram of the operation of the dual-channel variable geometry rocket-based combined cycle engine in the range of Mach 3-4.

Fig. 4 is a schematic diagram of the operation of the dual-channel variable geometry rocket-based combined cycle engine in the range of Mach 4 to 7.

Fig. 5 is a performance change curve of the combined cycle engine of the present invention at different Mach numbers.

In the picture:

1. Intake channel 2. High-speed channel 3. Low-speed channel 4. Built-in rocket 5. Combustion chamber 6. Tail nozzle 7. Combustion enhancement device 8. Top pressure plate 9. Conversion plate 10. First shaft 11. Second shaft 12 .First Actuating Mechanism 13.Second Actuating Mechanism

detailed description

This embodiment is a dual-channel variable geometry rocket-based combined cycle engine.

1 to 5, the intake port 1 of the double-channel variable geometry rocket-based combined cycle engine of the present embodiment is a dual-channel structure, consisting of a high-speed channel 2 and a low-speed channel 3, and the low-speed channel 3 is located above the high-speed channel 2. When the engine is in a low-speed flight state, the high-speed channel 2 and low-speed channel 3 work at the same time, and high-pressure combustion is organized in the rear end area where the two channels meet; when the engine is in a high-speed flight state, the low-speed channel 3 is closed, and the high-speed channel 2 is normal Work, organize high-pressure combustion in the combustion chamber 5 of high-speed passage. Wherein, the tail nozzle 6, as a part of the high-speed passage 2, can play the role of accelerating the expansion of the airflow. A top pressure plate 8 is installed on the front part of the upper wall of the air inlet, one end of the top pressure plate 8 is connected with the fuselage through the first rotating shaft 10, the other end of the top pressure plate 8 is connected with the first actuating mechanism 12, and the first actuating mechanism 12 is installed on the machine. body. A conversion plate 9 is installed on the rear portion of the upper wall of the air inlet, and one end of the conversion plate 9 is connected with the fuselage through a second rotating shaft 11, and the upper part of the other end of the conversion plate 9 is connected with the second actuating mechanism 13, and the second actuating mechanism 13 is installed on the machine. body. The top pressure plate 8 and the conversion plate 9 are both attached to the upper wall of the low-speed channel 3 in the low-speed flight state. At this time, the low-speed channel 3 is completely turned on; When the plate 9 rotates an angle around the second rotating shaft 11, both the top pressure plate 8 and the conversion plate 9 are not in contact with the lower wall surface of the low-speed channel 3. At this time, the low-speed channel is partially conducted; when the compression surface of the top pressure plate 8 continues to rotate around the first When the rotating shaft 10 rotates and the conversion plate 9 rotates around the second rotating shaft, both the pressing plate 8 and the conversion plate 9 are in contact with the lower wall of the low-speed passage 3, and at this time, the low-speed passage 3 is closed. The rotational power of the pressing plate 8 and the conversion plate 9 comes from the actuating mechanism, the pressing plate realizes the clockwise rotation under the action of the first actuating mechanism 12 , and the conversion plate realizes the counterclockwise rotation under the action of the second actuating mechanism 13 . The first actuating mechanism 12 and the second actuating mechanism 13 respectively use a hydraulic device or an electric motor as a driving force.

Built-in rockets 4 are respectively installed on the front and back of the upper wall of the high-speed passage 2 and the low-speed passage 3, wherein the rear built-in rocket 4 is installed at the front end of the tail nozzle 6; the number of built-in rockets 4 may be one or multiple; There are multi-stage arrangements at different positions in the engine flow channel, and the installation method of the built-in rocket is center or side.

The combustion enhancement device is arranged in the combustion chamber according to the requirement of zoned combustion, and the combustion enhancement device is one of fuel support plate, concave cavity, or step. The shape of the combustion chamber is rectangular or circular. The tail nozzle is a single-sided expansion nozzle.

Example

In this embodiment, the intake port 1 is arranged at the front of the rocket-based combined cycle engine, wherein the design point of the intake port is selected as Mach 5, and the flight altitude is 21 km. The tail nozzle 6 is a single-side expansion nozzle, which is arranged at the tail of the rocket-based combined cycle engine. The low-velocity channel 3 is located above the high-speed channel 2, and the angle between the flow direction of the two channels is 7°, and they converge at the front of the tail nozzle 6, and the converging angle of the airflow is 10°. Among them, the two-stage external compression angles of the high-speed channel 2 are 6.8° and 11.3°, respectively, and the two-stage external compression angles of the low-speed channel 3 are 6.8° and 4°, respectively. The top pressure plate 8 is connected with the first actuating mechanism and the first rotating shaft, and the conversion plate 9 is connected with the second actuating mechanism and the second rotating shaft. Closes when the walls are in contact. The built-in rocket 4 is a liquid oxygen/kerosene liquid rocket engine, installed in two stages in the rocket-based combined cycle engine, and arranged sideways at the entrance and rear of the combustion chamber 5 respectively. Among them, the duty cycle of the built-in rocket does not exceed 30%, the rated chamber pressure is 10MPa, the mixing ratio is 2.5, and the nozzle expansion ratio is 10. The combustion chamber 5 has a rectangular structure with an aspect ratio of 10 and a unilateral expansion configuration with an expansion ratio of 2. Combustion enhancement device 7 selects the mode of combining two pairs of fuel support plates and one group of concave cavities. Among them, two pairs of fuel support plates are respectively arranged in the middle and rear of the combustion chamber 5, and a group of concave cavities are arranged in the area close to the first group of fuel support plates to form efficient and stable combustion in different modal zones. The exhaust/intake area ratio of the rocket-based combined cycle engine in this embodiment is 2.

In this embodiment, the first actuating mechanism is driven by a hydraulic device or a motor to make the pressing plate rotate clockwise around the first rotating shaft; the second actuating mechanism is driven by a hydraulic device or a motor to make the conversion plate rotate counterclockwise around the second rotating shaft . When the pressing plate 8 rotates 7.3° clockwise around the first rotating shaft 10, the conversion of the engine from the dual-channel to the single-channel is realized. In order to realize the complete closure of the low-speed channel 3 , the conversion plate 9 needs to rotate counterclockwise by 12° around the second rotating shaft 11 .

In this example, the working Mach number range of the rocket-based combined cycle engine is selected to be Mach 0 to Mach 7, and the specific working method is as follows: the two channels of the engine work simultaneously in the range of Mach 0 to Mach 3; the top pressure plate 8 passes through the first Driven by the actuating mechanism, it rotates clockwise in a small range around the first rotating shaft 10, and at the same time, driven by the second actuating mechanism, the conversion plate 9 rotates counterclockwise around the second rotating shaft 11, gradually closing the low-speed channel 3 and switching to the high-speed channel 2 working alone to complete the channel conversion; the high-speed channel 2 works alone in the range of Mach 4 to 7.

In this embodiment, it can be seen from the variation curve of the air capture flow coefficient of the rocket-based combined-cycle engine at a typical flight point that the rocket-based combined-cycle engine can operate at a wide range of Mach 0 to Mach 7 through a simple and feasible dual-channel variable geometry adjustment structure. In the flight range, it has obtained comprehensively better air capture characteristics and engine performance, and has better practical application value.

In this embodiment, the rocket-based combined cycle engine adopts a dual-channel structure, and realizes good work in a wide flight range through the zoned combustion mode. Under the low-speed flight state, the dual channels work simultaneously to complete the low-speed section of the ejection mode and the sub-combustion mode. In the high-speed flight state, it is converted to the high-speed channel to work alone, and completes the work of the high-speed section of the sub-combustion mode and the super-combustion mode. The rocket-based combined cycle engine adopts a variable geometry method in which the top pressure plate rotates around the first rotating shaft in a small range to realize the adjustment of small shrinkage ratio in low-speed flight state and large shrinkage ratio in high-speed flight state.

Claims (4)

1. the dual pathways becomes geometry rocket based combined cycle electromotor, it is characterised in that: include air intake duct, high-speed channel, low Speed passage, built-in rocket, combustor, jet pipe, burning intensifier, top pressing board, change-over panel, the first rotating shaft, the second rotating shaft, the One actuation mechanism, the second actuation mechanism, described air intake duct is the channel structure of high-speed channel and slow channels composition, and low speed leads to Road is positioned at above high-speed channel, and air intake duct upper wall surface front portion is provided with top pressing board, and top pressing board one end and fuselage are by first turn Axle connects, and other end top is connected with the first actuation mechanism, and the first actuation mechanism is arranged on fuselage；Air intake duct upper wall surface rear portion Being provided with change-over panel, change-over panel one end is connected by the second rotating shaft with fuselage, and other end top is connected with the second actuation mechanism, the Two actuation mechanism are arranged on fuselage；Slow channels rotates respectively with change-over panel to the lower wall surface with slow channels at top pressing board and connects Guan Bi when touching；Before and after high-speed channel and slow channels upper wall surface, position is separately installed with built-in rocket, the built-in rocket of its postmedian Being positioned at jet pipe front end, combustor is positioned at high-speed channel, is provided with burning intensifier in combustor.

The dual pathways the most according to claim 1 becomes geometry rocket based combined cycle electromotor, it is characterised in that: described burning Room is rectangle or circular configuration；Described jet pipe is unilateral expansion nozzle.

The dual pathways the most according to claim 1 becomes geometry rocket based combined cycle electromotor, it is characterised in that: described burning Intensifier is the one of fuel support plate or cavity, or fuel support plate and cavity combination form.

The dual pathways the most according to claim 1 becomes geometry rocket based combined cycle electromotor, it is characterised in that: described built-in Rocket is multiple.