CN109184957B - A kind of supersonic flow mixing enhanced structure and rocket-based combined engine - Google Patents

Abstract

The invention provides a supersonic incoming flow mixing enhanced structure and a rocket-based combined engine, including a supersonic incoming flow partition, supersonic incoming flow channels are respectively arranged on both sides of the supersonic incoming flow partition, and two supersonic incoming flow channels are located in the The tail end of the supersonic incoming flow partition communicates and forms a supersonic incoming flow mixing zone behind the tail end of the supersonic incoming flow partition, and the supersonic incoming flow mixing zone communicates with at least one supersonic incoming flow channel through at least one drainage tube, and the drainage The tubes are located inside the supersonic incoming flow baffle. By setting a drainage tube inside the supersonic incoming flow partition to connect the side of the supersonic incoming flow partition and the tail end of the supersonic incoming flow partition, since there is a pressure difference between the two ends of the drainage tube, no additional air source is required. Using the flow characteristics of the flow field itself, jets can be formed in the supersonic incoming flow mixing area, so as to realize the enhanced mixing control of the supersonic incoming flow mixing area. The invention is applied in the field of supersonic incoming flow mixing control.

Description

A kind of supersonic flow mixing enhanced structure and rocket-based combined engine

technical field

The invention relates to the field of supersonic incoming flow mixing control, in particular to a supersonic incoming flow mixing enhanced structure and a rocket-based combined engine.

Background technique

As a key process of Rocket Based Combined Cycle (RBCC), ejection plays the role of mixing rocket gas with incoming air. For RBCC, the free flow passes through the intake port and contacts the nozzle gas at the nozzle trailing edge. When the mixture of the two reaches the molecular level, a chemical reaction occurs, and the purpose of using the oxygen in the air to increase the specific impulse of the engine is realized. However, due to the high velocity of the incoming flow, the residence time in the combustion chamber is extremely short (less than 1-3ms), how to realize the rapid and efficient mixing of gas and air is the key issue of injection, that is, to enhance the mixing effect, which determines the entire propulsion system performance.

The supersonic mixed layer as a typical flow form of the ejection process has been widely concerned, and the mixed layer generated by the thin diaphragm is the main research object. However, in the actual process, the temperature of the rocket gas is extremely high (greater than 3500K, and the heat flux density at the throat of the nozzle reaches 107-108W/m ² ), and the temperature at the outlet of the nozzle also exceeds 2500K. In order to protect the geometric structure of the launch rocket, a certain cooling method is required, which will inevitably lead to an increase in the thickness of the trailing edge, forming a supersonic obtuse trailing edge mixed layer, and its flow field structure is shown in Figure 1.

In the prior art, there are two types of control methods for supersonic inflow mixing enhancement, namely active and passive. The passive control scheme mainly focuses on changing the structure of the trailing edge, including tabs, sawtooth, lobes, etc., and is mostly based on changing the structure of the trailing edge, thereby generating flow direction vortices or unstable pulsations. The active control method mainly changes the characteristic structure of the flow field by actively injecting energy and momentum into the controlled flow field to achieve the effect of controlling the mixing enhancement.

The passive control scheme based on changing the structure of the trailing edge has a simple structure and obvious control effects, but it is mainly aimed at the thin trailing edge mixed layer abstracted from practical problems. For the actual blunt trailing edge mixed layer, the partition is thicker and difficult Changing the trailing edge structure and adopting a pointed trailing edge configuration is not conducive to heat protection. Based on the active control scheme of the vibrating plate, the vibrating plate is arranged in the flow field. For the combined engine combustion chamber under real conditions, the high-temperature gas will easily melt the vibrating plate.

Contents of the invention

Aiming at the technical problem that it is difficult to effectively apply the control method for supersonic incoming flow mixing enhancement in the prior art, no matter whether it adopts an active control scheme or a passive control scheme, the purpose of the present invention is to provide a supersonic incoming flow For the hybrid enhanced structure and the rocket-based combined engine, a drainage tube is arranged inside the supersonic incoming flow partition, and the supersonic incoming flow mixing area is connected with the supersonic incoming flow channel by the drainage tube. Provide an additional gas source, and use the flow characteristics of the flow field itself to form a jet in the supersonic incoming flow mixing area, thereby achieving enhanced control of the mixing in the supersonic incoming flow mixing area.

In order to achieve the purpose of the above invention, the present invention provides a supersonic incoming flow mixing enhanced structure, the technical scheme adopted is:

A supersonic incoming flow mixing enhanced structure, including a supersonic incoming flow partition, supersonic incoming flow channels are respectively arranged on both sides of the supersonic incoming flow partition, two supersonic incoming flow channels are at the tail end of the supersonic incoming flow partition Connected and form a supersonic incoming flow mixing zone behind the tail end of the supersonic incoming flow partition, the supersonic incoming flow mixing region communicates with at least one supersonic incoming flow channel through at least one drainage tube, and the drainage tube is arranged on the supersonic incoming flow partition internal.

As a further improvement of the above technical solution, the supersonic incoming flow mixing zone communicates with at least one supersonic incoming flow channel through at least one drainage tube, specifically:

The supersonic incoming flow mixing area communicates with the two supersonic incoming flow channels respectively through at least one drainage tube.

As a further improvement of the above technical solution, the supersonic incoming flow mixing zone communicates with the two supersonic incoming flow channels through at least one drainage tube, specifically:

The supersonic incoming flow mixing area communicates with the two supersonic incoming flow channels respectively through a drainage tube.

As a further improvement of the above technical solution, the drainage tube is a combination of one or more structures among linear structure, curved structure and zigzag structure.

In order to realize the above-mentioned purpose of the invention, the present invention also provides a kind of rocket-based combined engine, and the technical scheme that it adopts is:

A rocket-based composite engine having the above-mentioned supersonic incoming flow mixing enhanced structure, comprising an engine body and a nozzle trailing edge arranged on the engine body, the head end of the supersonic incoming flow partition is fixedly connected to the nozzle trailing edge , the supersonic incoming flows in the two supersonic incoming flows are rocket gas and air respectively.

Beneficial technical effect of the present invention:

The present invention connects the supersonic incoming flow mixing area with the supersonic incoming flow channel by setting a drainage tube inside the supersonic incoming flow partition. Since the supersonic incoming flow channel flows in the supersonic incoming flow, two high-pressure supersonic incoming flows flow through the supersonic incoming flow. After the two sides of the flow partition, a low-pressure recirculation zone is formed at the tail end of the supersonic incoming flow partition, so that there is a pressure difference between the two ends of the drainage tube, no additional air source is needed, and the flow of the flow field itself is used The characteristic can form a jet in the supersonic incoming flow mixing area, thereby realizing the enhanced control of mixing in the supersonic incoming flow mixing area.

Description of drawings

Figure 1 is a schematic diagram of the supersonic obtuse trailing edge mixed layer flow field;

Fig. 2 is a schematic diagram of the first embodiment of the supersonic incoming flow mixing enhanced structure;

Fig. 3 is a schematic diagram of a second embodiment of the supersonic incoming flow mixing enhanced structure;

Fig. 4 is a schematic diagram of a third embodiment of a supersonic incoming flow mixing enhanced structure;

Figure 5 is a schematic diagram of a rocket-based combined engine.

Detailed ways

In order to facilitate the implementation of the present invention, further description will be given below in conjunction with specific examples.

As shown in Figure 2, the supersonic incoming flow mixing enhanced structure includes a supersonic incoming flow partition 1, and the two sides of the supersonic incoming flow partition 1 are respectively provided with a supersonic incoming flow channel 2, and two supersonic incoming flow channels 2 The tail end of the flow partition 1 is connected and forms a supersonic incoming flow mixing zone 3 behind the tail end of the supersonic incoming flow partition, wherein, the tail end of the supersonic incoming flow partition 1 refers to the direction of the supersonic incoming flow At the end of the flow direction of the supersonic flow, the supersonic incoming flow mixing zone 3 communicates with at least one supersonic incoming flow channel through at least one drainage tube. A connecting channel excavated inside the partition 1 for connecting the supersonic incoming flow mixing area 3 and the supersonic incoming flow channel 2 .

In this embodiment, the supersonic incoming flow mixing zone 3 is communicated with the supersonic incoming flow channel 2 by setting the drainage tube 4 inside the supersonic incoming flow partition 1. Since there is a supersonic incoming flow flowing in the supersonic incoming flow channel 2, two high-pressure After the supersonic incoming flow flows through the upper and lower surfaces of the supersonic incoming flow partition 1, a low-pressure recirculation zone is formed at the tail end of the supersonic incoming flow partition 1. At this time, a pressure difference is formed at both ends of the drainage tube 4, thereby generating a jet. No need to provide an additional gas source, the flow characteristics of the flow field itself can be used to form a jet in the supersonic incoming flow mixing zone 3, and interact with the flow separated by the two supersonic incoming flows at the end of the supersonic incoming flow partition 1, thereby The mixing enhanced control of the supersonic incoming flow mixing zone 3 is realized.

Further preferably, the above-mentioned supersonic incoming flow mixing zone 3 communicates with at least one supersonic incoming flow channel through at least one drainage tube specifically: the supersonic incoming flow mixing zone 3 communicates with two supersonic incoming flow channels through at least one drainage tube respectively.

Further preferably, the above-mentioned supersonic incoming flow mixing zone 3 communicates with the two supersonic incoming flow channels respectively through at least one drainage tube specifically: the supersonic incoming flow mixing zone 3 communicates with the two supersonic incoming flow channels respectively through a drainage tube. That is, there are two drainage tubes inside the supersonic incoming flow partition 1, one of which is connected to the tail end of the supersonic incoming flow partition 1 and one side of the supersonic incoming flow partition 1, and the other drainage tube is connected to the supersonic incoming flow partition 1 and the other side of the supersonic incoming flow partition 1.

Further preferably, the drainage tube 4 is a combination of one or more structures in a linear structure, a curved structure, and a zigzag structure. The structure of the drainage tube 4 can be adjusted according to the actual demand. The length of the flow path of the airflow in the drainage tube 4 with different linear structures is different, and the degree of weakening of the airflow velocity is different, so that the final jet intensity is also different. Therefore, different linear shapes The draft tube 4 of the structure has a different enhancing effect on the admixture.

As shown in Figure 2 is the drainage tube 4 with a curved structure, the length of the air flow path is relatively moderate, and the jet strength formed is also relatively moderate, so the final mixing enhancement effect is also relatively moderate; the one shown in Figure 3 is a straight line structure of the drainage tube 4, the length of the airflow flow path is shorter, and the jet strength formed is also greater, so the final mixing enhancement effect is also higher; Figure 4 shows the drainage tube 4 with a broken line structure, the airflow The length of the flow path is longer, and there are more obstacles, and the strength of the formed jet is also weakened, so the effect on the final mixing enhancement is relatively low.

Present embodiment also provides a kind of rocket-based combination engine, and the technical scheme that it adopts is:

As shown in Figure 5, a rocket-based combined engine with the above-mentioned supersonic incoming flow mixing enhanced structure includes the engine body 5 and the nozzle trailing edge 6 arranged on the engine body 5, and the head end of the supersonic incoming flow baffle 1 Fixedly connected to the nozzle trailing edge 6, the supersonic inflows in the two supersonic inflow channels 2 are respectively rocket gas and air.

The description of the preferred embodiment of the present invention is included above, which is to describe the technical characteristics of the present invention in detail, and is not intended to limit the content of the invention to the specific form described in the embodiment. Other modifications and Variations are also protected by this patent. The gist of the present invention is defined by the claims rather than by the detailed description of the embodiments.

Claims (4)

1. a kind of Supersonic Stream blends enhancing structure, which is characterized in that including Supersonic Stream partition, the Supersonic Stream The two sides of partition are respectively equipped with Supersonic Stream channel, and two Supersonic Stream channels are connected in the tail end of Supersonic Stream partition And Supersonic Stream dilution zone, Supersonic Stream dilution zone and two supersonic speeds are formed at the rear of Supersonic Stream partition tail end Carry out circulation road and pass through at least one drainage tube respectively to be connected to, the drainage tube is located at the inside of Supersonic Stream partition, drainage tube It is be used to be connected to Supersonic Stream dilution zone and Supersonic Stream channel one cut in Supersonic Stream diaphragm internal A interface channel；

In the inside of Supersonic Stream partition, Supersonic Stream dilution zone is connected to by setting drainage tube with Supersonic Stream channel, by There is Supersonic Stream in flowing in Supersonic Stream channel, the Supersonic Stream of two bursts of high pressures flows through the upper of Supersonic Stream partition Behind lower surface, the recirculating zone of a low pressure is formed at Supersonic Stream partition tail end, the both ends of drainage tube is caused to be formed at this time Pressure difference is separated with two strands of Supersonic Streams in Supersonic Stream partition tail end to form jet stream in Supersonic Stream dilution zone Flow interaction, so that realizing enhances control to the blending of Supersonic Stream dilution zone.

2. Supersonic Stream blends enhancing structure according to claim 1, which is characterized in that the Supersonic Stream dilution zone Pass through at least one drainage tube respectively with two Supersonic Stream channels to be connected to specifically:

Supersonic Stream dilution zone passes through a drainage tube with two Supersonic Stream channels respectively and is connected to.

3. Supersonic Stream according to claim 1 or claim 2 blends enhancing structure, which is characterized in that the drainage tube is straight line The combination of one of shape structure, curved configuration, fold-line-shaped structure or various structures.

4. a kind of rocket base combined engine with claims 1 or 2 or the 3 Supersonic Stream blending enhancing structures, It is characterized in that, including engine body and the jet pipe trailing edge being located on engine body, the head of the Supersonic Stream partition End is fixedly connected on jet pipe trailing edge, and the Supersonic Stream in two Supersonic Stream channels is respectively rocket combustion gas and air.