CN116906937A - Injection structure, combustion system and rotary detonation engine - Google Patents

Abstract

The application provides an injection structure, a combustion system and a rotary detonation engine. The injection structure is used for injecting fuel and oxidant into the rotary detonation combustion chamber, the injection structure is provided with a first injection flow passage, a second injection flow passage and a third injection flow passage, the first injection flow passage and the second injection flow passage are arranged to inject the oxidant into the rotary detonation combustion chamber, and the third injection flow passage is arranged to inject the fuel into the rotary detonation combustion chamber; the injection port of the first injection flow channel is a first nozzle, the injection port of the second injection flow channel is a second nozzle, and the injection port of the third injection flow channel is a third nozzle; the first nozzle and the second nozzle are annular nozzles, and the first nozzle is sleeved on the radial outer side of the second nozzle and is arranged at intervals with the second nozzle; the third nozzle is positioned between the first nozzle and the second nozzle. The scheme can weaken the negative influence of heat generated by detonation combustion on the wall surface of the combustion chamber, and is favorable for the stable operation of the rotary detonation combustion chamber for a long time.

Description

Injection structure, combustion system and rotary detonation engine

Technical Field

The present disclosure relates to, but is not limited to, detonation engine technology, and more particularly to an injection structure, combustion system, and rotary detonation engine.

Background

Slow combustion and detonation combustion are two main combustion modes of fuel energy release. The slow combustion is to transfer heat into the unburned mixture through heat conduction, heat diffusion and heat radiation, and heat layer by layer to burn, so as to realize propagation of slow combustion waves. The propagation velocity of the slow combustion wave is low, generally about several meters to tens of meters per second. Detonation combustion is achieved by a high-speed chemical reaction of the layer-by-layer intense impact compression of the detonation mixture by a shockwave, which can be considered to be a strong shockwave coupled with the chemical reaction. Detonation waves all propagate at supersonic speeds, typically on the order of 1000m/s or more. Slow combustion is a combustion mode widely adopted in the current industrial production, but detonation combustion has many incomparable advantages such as self-pressurization, fast flame propagation speed, high combustion efficiency, low pollutant emission and the like.

The existing various aerospace power devices are basically based on an isobaric combustion mode, the technical level of the existing aerospace power devices tends to be mature, and further breakthroughs are difficult to obtain. Knocking combustion theoretically has higher thermal cycle efficiency and faster heat release rate than the isobaric combustion mode. Engines based on knock combustion mode have potential performance advantages. The rotary detonation engine (Rotating Detonation Engine, RDE for short) is used as one of the detonation engines with new concepts, and the annular combustion chamber adopting the detonation combustion mode has the advantages of simple structure, high working frequency, single detonation and the like.

At present, most rotary detonation combustors adopt a non-premixed mode to inject fuel and oxidant, the oxidant is injected from an air inlet flow passage, the fuel is injected from the wall surface of the combustor, a large amount of heat is generated after combustion, and great challenges are brought to the heat protection of the wall surface of the combustor.

Disclosure of Invention

The embodiment of the application provides an injection structure, a combustion system and a rotary detonation engine, which can weaken the negative influence of heat generated by detonation combustion on the wall surface of a combustion chamber, and are beneficial to the stable operation of the rotary detonation combustion chamber for a long time.

To this end, an embodiment of the present application provides an injection structure for injecting fuel and oxidant into a rotary detonation combustor, the injection structure being provided with a first injection runner, a second injection runner, and a third injection runner, the first injection runner and the second injection runner being arranged to inject oxidant into the rotary detonation combustor, the third injection runner being arranged to inject fuel into the rotary detonation combustor; the injection port of the first injection flow channel is a first nozzle, the injection port of the second injection flow channel is a second nozzle, and the injection port of the third injection flow channel is a third nozzle; the first nozzle and the second nozzle are annular nozzles, and the first nozzle is sleeved on the radial outer side of the second nozzle and is arranged at intervals with the second nozzle; the third spout is located between the first spout and the second spout.

In this way, the oxidant in the first injection flow channel and the second injection flow channel is two air flows which are mutually separated, and the two air flows are respectively sprayed out through the first nozzle and the second nozzle to form two annular air flows, and the two annular air flows can be diffused to the middle in the subsequent flowing process. The third nozzle is positioned between the first nozzle and the second nozzle, so that fuel can be sprayed out from the middle of the two annular air flows and then mixed with the inner annular air flow and the outer annular air flow to form a combustible mixture, and after the combustible mixture is formed, detonation waves are generated through ignition detonation, and the rotary detonation combustion chamber can work normally.

Because the fuel is positioned between the inner air flow and the outer air flow, the shearing force between the inner annular air flow and the outer annular air flow can be utilized to atomize the fuel, so that a better atomization effect is achieved. In addition, the fuel is positioned between the inner air flow and the outer air flow, so that the combustion area is positioned in the middle area of the rotary detonation combustion chamber and is not clung to the inner wall surface and the outer wall surface of the rotary detonation combustion chamber. Therefore, the inner and outer two air flows are not only used for combustion, but also can serve as an air film of the inner wall surface and the outer wall surface of the rotary detonation combustion chamber, isolate the burnt high-temperature tail gas from the inner wall surface and the outer wall surface of the rotary detonation combustion chamber, and are equivalent to playing a role in cooling the inner wall surface and the outer wall surface of the rotary detonation combustion chamber, so that the negative influence of heat generated by detonation combustion on the wall surface of the combustion chamber can be reduced, and the rotary detonation combustion chamber can work stably for a long time.

In an exemplary embodiment, the first injection runner and the second injection runner are annular runners, and the first injection runner is sleeved on the radial outer side of the second injection runner and is arranged at intervals with the second injection runner; the third injection flow passage is located between the first injection flow passage and the second injection flow passage.

In an exemplary embodiment, the injection structure is provided with an oxidant input flow channel located on an upstream side of the first and second injection flow channels and in communication with the inlets of the first and second injection flow channels.

In an exemplary embodiment, a flow guiding portion is provided in the oxidant input flow channel, the flow guiding portion being provided with a first flow guiding inclined surface and a second flow guiding inclined surface arranged opposite to each other, the first flow guiding inclined surface being arranged to guide the oxidant into the first injection flow channel, and the second flow guiding inclined surface being arranged to guide the oxidant into the second injection flow channel.

In an exemplary embodiment, the central axis of the third nozzle extends in the axial direction of the annular nozzle.

In an exemplary embodiment, along the injection direction of the first injection flow channel, the first injection flow channel includes a first constant diameter section and a first expansion section which are sequentially communicated, the first expansion section is provided with a third diversion inclined plane, and the third diversion inclined plane is arranged to extend obliquely to a direction approaching the third nozzle; along the injection direction of second injection runner, the second injection runner is including second constant diameter section and the second expansion section of intercommunication in proper order, the second expansion section is equipped with the fourth water conservancy diversion inclined plane, the fourth water conservancy diversion inclined plane sets up to be close to the direction slope of third spout extends.

In an exemplary embodiment, the first expansion section is further provided with a fifth flow guiding slope disposed opposite to the third flow guiding slope, the fifth flow guiding slope being disposed to extend obliquely in a direction away from the third nozzle; the second expansion section is also provided with a sixth diversion inclined plane which is arranged opposite to the fourth diversion inclined plane, and the sixth diversion inclined plane is arranged to extend obliquely in a direction away from the third nozzle.

In an exemplary embodiment, the third injection runner includes a fuel delivery channel, the fuel delivery channel is an annular runner, and the fuel delivery channel is sleeved between the first injection runner and the second injection runner and is spaced apart from the first injection runner and the second injection runner.

In an exemplary embodiment, the third injection flow passage further includes an injection flow passage that is located on a downstream side of the fuel delivery passage and communicates with the fuel delivery passage, a cross-sectional area of the injection flow passage is smaller than a cross-sectional area of the fuel delivery passage, and an outlet of the injection flow passage forms the third nozzle; the injection flow passage comprises a plurality of sub flow passages which are arranged at intervals along the circumferential direction of the fuel conveying passage; alternatively, the injection flow channel is an annular flow channel.

In an exemplary embodiment, the injection structure is provided with a fuel supply channel in communication with the third injection flow channel arranged to deliver fuel thereto; wherein the fuel supply passage is provided radially outward of the third injection flow passage; and/or the number of the fuel supply channels is a plurality of, and the plurality of the fuel supply channels are arranged at intervals along the circumferential direction of the annular nozzle.

In an exemplary embodiment, the injection structure includes: injecting the shell; an injection inner shell sleeved on the inner side of the injection outer shell and arranged at intervals with the injection outer shell; and the middle ring is sleeved between the injection inner shell and the injection outer shell, a space between the middle ring and the injection outer shell forms the first injection flow channel, a space between the middle ring and the injection inner shell forms the second injection flow channel, and the third injection flow channel is arranged on the middle ring.

In an exemplary embodiment, the injection structure further comprises: a first connecting piece located between the intermediate ring and the inner housing and connecting the intermediate ring and the inner housing; and/or a second connection between the intermediate ring and the insufflating housing and connecting the intermediate ring and the insufflating housing.

The embodiment of the application also provides a combustion system for a rotary detonation engine, the combustion system comprising: a combustion chamber body provided with a rotary detonation combustion chamber; and an injection structure as in any of the above embodiments having first, second and third ports in communication with the rotary detonation combustor.

In an exemplary embodiment, the combustion chamber body is of unitary construction with the injection structure.

The embodiment of the application also provides a rotary detonation engine, comprising the combustion system according to any one of the above embodiments.

Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application. Other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and drawings.

Drawings

The accompanying drawings are included to provide an understanding of the principles of the application, and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain, without limitation, the principles of the application.

FIG. 1 is a schematic perspective view of a combustion system according to some embodiments of the present application;

FIG. 2 is a schematic perspective view of another view of the combustion system of FIG. 1;

FIG. 3 is a right side schematic view of the combustion system of FIG. 1;

FIG. 4 is a left side schematic view of the combustion system of FIG. 1;

FIG. 5 is a schematic cross-sectional view of the structure of FIG. 4 in the direction A-A;

FIG. 6 is an enlarged schematic view of the portion B in FIG. 5;

FIG. 7 is a schematic cross-sectional view of a combustion system provided by other embodiments.

Wherein, the reference numerals are as follows:

100 injection structure, 11 first injection runner, 111 first constant diameter section, 112 first expansion section, 113 first nozzle, 12 second injection runner, 121 second constant diameter section, 122 second expansion section, 123 second nozzle, 13 third injection runner, 131 fuel delivery channel, 132 injection runner, 1321 sub-runner, 133 third nozzle, 14 oxidant input runner, 141 flow guide portion, 1411 first flow guide slope, 1412 second flow guide slope, 15 fuel supply channel, 16 injection outer shell, 161 fifth flow guide slope, 17 injection inner shell, 171 sixth flow guide slope, 18 middle ring, 181 third flow guide slope, 182 fourth flow guide slope, 191 first connector, 192 second connector;

200 combustion chamber body, 21 combustion chamber outer shell, 22 combustion chamber inner shell, 23 rotary detonation combustion chamber, 231 outer wall surface, 232 inner wall surface.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the present application more apparent, embodiments of the present application will be described in detail hereinafter with reference to the accompanying drawings. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be arbitrarily combined with each other.

In order to solve the problem of heat protection of the wall surface of the rotary detonation combustion chamber, the technical means adopted in the field are as follows: the additional design of the cooling structure to cool the wall surface of the combustion chamber results in complex structure of the combustion system or improves the material quality of the combustion chamber to improve the heat resistance of the combustion chamber, resulting in higher cost of the combustion system.

The inventor of the present application opens up a new way to study at a new angle. It has been found through research that, at present, the reason why the heat protection challenge of the combustion chamber wall surface of the rotary detonation engine is great is that: the fuel is sprayed out from the wall surface of the combustion chamber, and the oxidant and the fuel are sprayed at a certain included angle, so that the fuel and the oxidant are fully mixed for increasing the atomization effect of the fuel. However, the fuel is ejected from the wall of the combustion chamber, so that the ejected fuel is closer to the wall of the combustion chamber, and a large amount of heat generated after combustion is easier to act on the wall of the combustion chamber, thereby bringing great challenges to the heat protection of the wall of the combustion chamber. In addition, the oxidant and fuel are injected at a certain angle, which increases the flow loss.

Based on the above-mentioned research, the embodiment of the application provides an injection structure, a combustion system and a rotary detonation engine, and solves the problem that the heat protection of the wall surface of the combustion chamber is challenging by improving the injection structure. Compared with the method for cooling the wall surface of the combustion chamber by additionally designing a cooling structure or improving the material of the combustion chamber to improve the heat resistance of the combustion chamber, the solution of the application has lower cost, simpler structure and easier realization.

Specifically, the rotary knock engine (not shown in the drawings) includes a combustion system, and may further include a fuel supply system, an oxidant supply system, an exhaust system, a control system, and the like.

As shown in fig. 1 and 7, the combustion system includes a combustion chamber body 200 and an injection structure 100. The combustion chamber body 200 is provided with a rotary detonation combustion chamber 23 as shown in fig. 5 and 7. The combustion system may also include an initiation device (not shown). Injection structure 100 is used to inject fuel and oxidant into rotary detonation combustor 23. The initiating device enables the rotary detonation combustor 23 to generate a stable self-sustaining detonation wave by detonating the fuel and the oxidizer. The initiation device may be, but is not limited to, a pre-burst tube initiation device, a thermal jet initiation device, or the like.

The rotary detonation combustor 23 is generally an annular combustor as shown in fig. 5 and 7. The inner wall surface 232 and the outer wall surface 231 of the rotary detonation combustor 23 are disposed at an opposing interval, and as shown in fig. 5, the outer wall surface 231 is located radially outward of the inner wall surface 232. The space between the inner wall surface 232 and the outer wall surface 231 of the rotary detonation combustor 23 is a space in which the fuel and the oxidant are detonated and combusted.

Wherein the states of the oxidant and the fuel are not limited. Such as: the oxidizing agent may be a gaseous oxidizing agent, or may be a liquid oxidizing agent or a solid powder oxidizing agent. The fuel may be a liquid fuel, or may be a gaseous fuel or a solid powdered fuel. For solid powder oxidizer and solid powder fuel, a fluidization device may be correspondingly disposed to fluidize the solid powder and then enter the injection structure 100, i.e. to have gas flow properties.

The following description will take an example in which an oxidizing agent is a gaseous oxidizing agent and a fuel is a liquid fuel.

Embodiments of the present application provide an insufflating structure 100. As shown in fig. 5, the injection structure 100 is provided with a first injection flow passage 11, a second injection flow passage 12, and a third injection flow passage 13. The first injection flow passage 11 and the second injection flow passage 12 are provided to inject an oxidant into the rotary detonation combustion chamber 23, and the third injection flow passage 13 is provided to inject a fuel into the rotary detonation combustion chamber 23. As shown in fig. 6, the injection port of the first injection runner 11 is a first nozzle 113, the injection port of the second injection runner 12 is a second nozzle 123, and the injection port of the third injection runner 13 is a third nozzle 133.

Referring to fig. 3, 5 and 6, the first nozzle 113 and the second nozzle 123 are annular nozzles, and the first nozzle 113 is sleeved on the radial outer side of the second nozzle 123 and is spaced from the second nozzle 123. The third nozzle 133 is located between the first nozzle 113 and the second nozzle 123.

In this way, the oxidant in the first injection flow channel 11 and the second injection flow channel 12 is two air flows separated from each other, and the two air flows are respectively ejected through the first nozzle 113 and the second nozzle 123 to form two annular air flows, and can be diffused to the middle in the following flowing process. Since the third nozzle 133 is located between the first nozzle 113 and the second nozzle 123, fuel is ejected from the middle of the two annular air flows and then mixed with the inner annular air flow and the outer annular air flow to form a combustible mixture, and then a detonation wave is generated by ignition and detonation, so that the rotary detonation combustor 23 can work normally.

Because the fuel is positioned between the inner air flow and the outer air flow, the shearing force between the inner annular air flow and the outer annular air flow can be utilized to atomize the fuel, so that a better atomization effect is achieved. Further, since the fuel is located in the middle of the inner and outer air flows, the combustion region is also located in the middle region of the rotary detonation combustor 23, and does not abut against the inner and outer wall surfaces 231 of the rotary detonation combustor 23. In this way, the inner and outer air flows are not only used for combustion, but also can serve as air films of the inner and outer wall surfaces 231 of the rotary detonation combustion chamber 23, isolate the burnt high-temperature tail gas from the inner and outer wall surfaces 231 of the rotary detonation combustion chamber 23, and are equivalent to the cooling effect of the inner and outer wall surfaces 231 of the rotary detonation combustion chamber 23, so that the negative influence of heat generated by detonation combustion on the wall surfaces of the combustion chamber can be weakened, and the rotary detonation combustion chamber 23 can work stably for a long time.

In some exemplary embodiments, as shown in fig. 6, the central axis of the third nozzle 133 extends in the axial direction of the annular nozzle. The first nozzle 113 and the second nozzle 123 may also be provided to extend in the axial direction of the annular nozzle. The axial direction of the annular nozzle is coincident with the axial direction of the rotary detonation combustor 23.

In this way, the oxidant and the fuel are coaxially injected, so that the flow loss caused by the opposite impact of the fuel and the oxidant can be effectively reduced, and the combustion area is stabilized in the radial middle area of the rotary detonation combustor 23, so that the thermal shock caused by the inner and outer wall surfaces 231 of the rotary detonation combustor 23 is reduced.

In some exemplary embodiments, please refer to fig. 2, 3, 4 and 5 together, the first injection runner 11 and the second injection runner 12 are both annular runners, and the first injection runner 11 is sleeved on the radial outer side of the second injection runner 12 and is disposed at a distance from the second injection runner 12. The third injection flow channel 13 is located between the first injection flow channel 11 and the second injection flow channel 12.

In this way, the oxidant can stably flow in the first injection flow channel 11 and the second injection flow channel 12, and two stable air flows are formed and then are sprayed out from the first nozzle 113 and the second nozzle 123, so that the two sprayed air flows can be stably attached to the inner wall surface and the outer wall surface 231 of the rotary detonation combustor 23, and a good air film protection effect is achieved.

In addition, the arrangement makes the structural layout of the injection structure 100 more regular, which is convenient for processing and forming, and also makes the first injection runner 11 and the second injection runner 12 smoother, which is beneficial to further reducing air flow loss.

The first and second injection flow passages 11, 12 may be straight annular flow passages arranged concentrically at intervals, as shown in fig. 2, 5.

Of course, the first injection flow channel 11 and the second injection flow channel 12 may have other shapes, as long as the two annular air flows can be formed to be ejected.

In some exemplary embodiments, the injection structure 100 is provided with an oxidant input flow channel 14, as shown in fig. 5 and 6. The oxidant input flow passage 14 is located on the upstream side of the first and second injection flow passages 11, 12 in the oxidant flow direction, and communicates with the inlet of the first injection flow passage 11 and the inlet of the second injection flow passage 12.

In this way, the oxidant can be delivered from the same oxidant inlet channel 14 and then split into two annular streams via the first and second injection channels 11, 12 without the need for two oxidant inlet channels 14, thereby facilitating the simplification of the injection structure 100 and the reduction of production costs.

In some exemplary embodiments, a deflector 141 is provided within the oxidant inlet flow passage 14, as shown in fig. 6. The diversion portion 141 is provided with a first diversion slope 1411 and a second diversion slope 1412 disposed opposite to each other, as shown in fig. 4 and 6. The first diversion ramp 1411 is configured to direct the oxidant into the first injection runner 11 and the second diversion ramp 1412 is configured to direct the oxidant into the second injection runner 12.

This facilitates that the oxidant in the oxidant inlet flow passage 14 can be smoothly separated in two directions and respectively enter the first injection flow passage 11 and the second injection flow passage 12, so as to further reduce the flow loss of the oxidant in the flow process.

In some exemplary embodiments, referring to fig. 5 and 6 together, the oxidant input channel 14 is an annular channel, and the radial width of the oxidant input channel 14 is greater than the sum of the radial width of the first injection channel 11 and the radial width of the second injection channel 12. This ensures that the first and second injection runners 11, 12 are able to provide sufficient oxidant to the rotary detonation combustor 23.

In some exemplary embodiments, as shown in fig. 6, the first injection runner 11 includes a first constant diameter section 111 and a first diverging section 112 that are sequentially communicated in an injection direction of the first injection runner 11. The first expansion section 112 is provided with a third diversion slope 181, and the third diversion slope 181 is provided to extend obliquely in a direction approaching the third nozzle 133.

As shown in fig. 6, the second injection flow path 12 includes a second constant diameter section 121 and a second expanded section 122 that are sequentially communicated in the injection direction of the second injection flow path 12. The second expansion section 122 is provided with a fourth diversion ramp 182, and the fourth diversion ramp 182 is arranged to extend obliquely in a direction approaching the third nozzle 133.

The first constant diameter section 111 ensures a stable annular air flow within the first injection flow passage 11. The second constant diameter section 121 may ensure a stable annular gas flow within the second injection flow passage 12. The third guiding inclined plane 181 may guide the airflow ejected from the first nozzle 113 to diffuse toward the third nozzle 133, and the fourth guiding inclined plane 182 may guide the airflow ejected from the second nozzle 123 to diffuse toward the third nozzle 133. This facilitates atomization of the fuel ejected from the third nozzle 133 by utilizing the shearing force of the inner and outer air streams, so that the fuel and the oxidizer can be sufficiently mixed.

In some exemplary embodiments, as shown in fig. 7, the first expansion section 112 is further provided with a fifth diversion ramp 161 disposed opposite the third diversion ramp 181, the fifth diversion ramp 161 being disposed to extend obliquely away from the third nozzle 133.

As shown in fig. 7, the second expansion section 122 is further provided with a sixth flow guiding slope 171 disposed opposite to the fourth flow guiding slope 182, and the sixth flow guiding slope 171 is disposed to extend obliquely in a direction away from the third nozzle hole 133.

The fifth diversion slope 161 can guide the airflow to diffuse to the outer wall surface 231 of the rotary detonation combustor 23, so that part of the airflow ejected by the first nozzle 113 can be used as an air film of the outer wall surface 231 of the rotary detonation combustor 23, and the outer wall surface 231 of the rotary detonation combustor 23 can be well protected.

Similarly, the sixth flow guiding inclined surface 171 can guide the airflow to diffuse to the inner wall surface 232 of the rotary detonation combustor 23, so that part of the airflow ejected from the second nozzle 123 can be used as an air film of the inner wall surface 232 of the rotary detonation combustor 23, and the inner wall surface 232 of the rotary detonation combustor 23 can be well protected.

Of course, the fifth diversion slope 161 may not be provided in the first expansion section 112, and the sixth diversion slope 171 may not be provided in the second expansion section 122.

In some exemplary embodiments, as shown in FIG. 6, the third injection runner 13 includes a fuel delivery channel 131. The fuel delivery passage 131 is an annular flow passage. The fuel conveying channel 131 is sleeved between the first injection runner 11 and the second injection runner 12, and is arranged at intervals from the first injection runner 11 and the second injection runner 12.

Thus, the injection structure 100 has a regular structural layout, and is convenient for processing and molding.

The first injection flow channel 11, the third injection flow channel 13 and the second injection flow channel 12 may be three annular flow channels concentrically arranged at intervals.

In some exemplary embodiments, the third injection runner 13 further includes an injection runner 132, as shown in fig. 6. The injection flow passage 132 is located on the downstream side of the fuel delivery passage 131 and communicates with the fuel delivery passage 131. The cross-sectional area of the injection flow passage 132 is smaller than the cross-sectional area of the fuel delivery passage 131, as shown in fig. 6. The outlet of the injection flow passage 132 forms a third nozzle 133.

In this way, the third nozzle 133 is relatively small in size, so that the sprayed fuel is sufficiently atomized, and further, the fuel and the oxidant are sufficiently mixed.

In some embodiments, the injection runner 132 is an annular runner.

In other words, the injection runner 132 corresponds to a circumferential design, which is advantageous in improving the uniform distribution of the fuel in the circumferential direction of the rotary detonation combustion chamber 23, thereby improving the combustion uniformity.

In other embodiments, the injection runner 132 includes a plurality of sub-runners 1321 spaced apart along the circumference of the fuel delivery channel 131, as shown in FIG. 3.

In other words, each of the sub-flow passages 1321 corresponds to one nozzle. Compared with the scheme of circular seam design, the cross section area of the single sub-flow passage 1321 is smaller, the cross section area of the single sub-flow passage 1321 can be designed to be relatively larger, the processing and the forming are convenient, the processing cost is reduced, and in addition, a nozzle is not required to be additionally arranged.

As for the number of the sub-flow passages 1321, there is no particular limitation. In the case of being workable, the greater the number of sub-runners 1321, the better this facilitates uniform distribution of fuel in the circumferential direction of the rotary detonation combustor 23, thereby improving combustion uniformity.

Of course, the third injection flow path 13 may not include the injection flow path 132, and a common nozzle may be directly provided at the end of the fuel delivery path 131 to inject fuel.

In some exemplary embodiments, the injection structure 100 is provided with a fuel supply channel 15, as shown in fig. 2, 5 and 6, the fuel supply channel 15 being in communication with the third injection flow channel 13, arranged to deliver fuel to the third injection flow channel 13.

The number of the fuel supply passages 15 is not limited, and may be appropriately designed as needed, and one, two, three or more may be used.

In some embodiments, the number of fuel supply channels 15 is plural, and the plural fuel supply channels 15 are arranged at intervals along the circumferential direction of the annular nozzle. This facilitates rapid supply of the third injection runner 13 with sufficient fuel.

Such as: the number of the fuel supply passages 15 is four, and the four fuel supply passages 15 are provided at uniform intervals in the circumferential direction of the injection housing 16.

In some exemplary embodiments, as shown in fig. 5 and 6, the fuel supply passage 15 is provided radially outward of the third injection flow passage 13. Such as: the fuel supply passage 15 may extend generally in the radial direction of the injection structure 100.

Of course, the position of the fuel supply passage 15 is not limited to the radially outer side of the third injection flow passage 13, and may be located radially inner side of the third injection flow passage 13, or located axially upstream side of the third injection flow passage 13, as long as fuel can be supplied to the third injection flow passage 13.

In some exemplary embodiments, please refer to fig. 2, 4, 5 and 7 together, the injection structure 100 includes: an outer housing 16, an inner housing 17 and an intermediate ring 18.

The injection housing 16 is a hollow cylindrical structure. The inner housing 17 may have a hollow cylindrical structure or a solid columnar structure, as shown in fig. 2, 4, 5, and 7.

As shown in fig. 5 and 6, the inner injecting shell 17 is sleeved on the inner side of the outer injecting shell 16 and is spaced from the outer injecting shell 16. The intermediate ring 18 is sleeved between the inner and outer insufflating shells 17 and 16. The space between the intermediate ring 18 and the injector housing 16 forms the first injector flow path 11. The space between the intermediate ring 18 and the inner injector housing 17 forms the second injector flow path 12. The third injection flow channel 13 is provided in the intermediate ring 18.

As shown in fig. 5 and 6, the intermediate ring 18 may have an axial length that is less than the axial length of the outer insufflating shell 16 and less than the axial length of the inner insufflating shell 17. Thus, the area between the outer and inner injector housings 16, 17 where there is no intermediate ring 18 is the oxidant inlet flow passage 14.

Further, the third diversion ramp 181 and the fourth diversion ramp 182 are disposed on the middle ring 18, as shown in fig. 6. The fifth flow guiding inclined surface 161 is provided on the injection outer casing 16, and the sixth flow guiding inclined surface 171 is provided on the injection inner casing 17, as shown in fig. 7.

Further, as shown in fig. 6, the flow guiding portion 141 may be provided at an end of the intermediate ring 18 remote from the rotary detonation combustor 23, and integrally formed with the intermediate ring 18.

In some exemplary embodiments, the insufflating structure 100 further comprises a first connector 191 and a second connector 192, as shown in fig. 2, 3, 4 and 6.

Wherein the first connector 191 is located between the intermediate ring 18 and the inner injector housing 17 and connects the intermediate ring 18 and the inner injector housing 17. The second connector 192 is located between the intermediate ring 18 and the insufflating shell 16 and connects the intermediate ring 18 and the insufflating shell 16.

This allows the connection of the outer and intermediate rings 16, 18, 17 to be achieved, resulting in the injection structure 100 being formed as a single piece.

In some embodiments, the fuel supply passage 15 extends through the injector housing 16, the second connector 192, and the intermediate ring 18, as shown in FIG. 6.

In some embodiments, the number of first connectors 191 and the number of second connectors 192 are equal and correspond one-to-one. Such as: the number of the first connectors 191 is four, the number of the second connectors 192 is four, the four first connectors 191 are uniformly spaced along the circumferential direction of the injection inner housing 17, and the four second connectors 192 are uniformly spaced along the circumferential direction of the injection outer housing 16.

In some embodiments, the first connector 191, the second connector 192, the intermediate ring 18, the support inner housing, and the support outer housing may be a unitary structure, as shown in fig. 6. The first connector 191 and the second connector 192 may be, but are not limited to, a connection post, a connection plate, or the like.

Of course, the injection structure 100 may not include the first connector 191 and the second connector 192. Since the injection structure 100 is to be connected to the combustion chamber body 200, the fuel supply system, and the oxidant supply system, the injection inner case 17, the injection outer case 16, and the intermediate ring 18 may be fixed to other structures than the injection structure 100, not to each other, as a single body.

Of course, by adopting the scheme of the first connecting piece 191 and the second connecting piece 192, the whole structure is simpler, and the flow passage of the oxidant is smoother, so that the flow resistance can be effectively reduced, and the air flow loss can be reduced.

As shown in fig. 1 to 7, an embodiment of the present application also provides a combustion system for a rotary knock engine, including: a combustion chamber body 200 and an injection structure 100 as in any of the above embodiments. The combustion chamber body 200 is provided with a rotary detonation combustion chamber 23. The first, second and third ports 113, 123, 133 of the injection structure 100 are in communication with the rotary detonation combustor 23.

The combustion system provided in the embodiment of the present application includes the injection structure 100 according to any one of the above embodiments, so that all the above advantages are achieved, and will not be described herein.

In some exemplary embodiments, the combustion chamber body 200 is of unitary construction with the injection structure 100, as shown in fig. 5 and 7.

Therefore, the assembly process of the combustion system can be simplified, the assembly efficiency can be improved, and the production cost can be reduced.

In some embodiments, as shown in fig. 3, 5 and 7, the combustion chamber body 200 includes a combustion chamber outer case 21 and a combustion chamber inner case 22 sleeved inside the combustion chamber outer case 21, and a space between the combustion chamber outer case 21 and the combustion chamber inner case 22 forms a rotary detonation combustion chamber 23. The combustion chamber outer casing 21 may have a hollow cylindrical structure, and the combustion chamber inner casing 22 may have a hollow cylindrical structure or a solid cylindrical structure.

Wherein the combustion chamber outer shell 21 and the injection outer shell 16 are integrated, and the combustion chamber inner shell 22 and the injection inner shell 17 are integrated.

Further, as shown in fig. 5 and 7, the outer side wall of the combustion chamber housing 21 may be disposed flush with the outer side wall of the injector housing 16. The outer side wall of the combustor inner casing 22 may be disposed flush with the outer side wall of the injection inner casing 17 as shown in FIG. 5.

The embodiment of the application also provides a rotary detonation engine, which comprises the combustion system according to any one of the above embodiments, so that the rotary detonation engine has all the beneficial effects and is not repeated herein.

In summary, the injection structure, the combustion system and the rotary detonation engine provided by the embodiment of the application have the advantages of smooth intake runners, small flow resistance and small total pressure loss; the fuel and the oxidant are coaxially injected, and the combustion area is relatively far away from the inner wall surface and the outer wall surface of the rotary detonation combustion chamber, so that the wall surface of the rotary detonation combustion chamber is low in temperature, and the rotary detonation combustion chamber can work stably for a long time.

In the description of the present application, it should be noted that, directions or positional relationships indicated by terms "upper", "lower", "one side", "the other side", "one end", "the other end", "the side", "the opposite", "four corners", "the periphery", "the" mouth "character structure", etc., are directions or positional relationships based on the drawings, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the structures referred to have a specific direction, are configured and operated in a specific direction, and thus are not to be construed as limiting the present application.

In the description of embodiments of the present application, unless explicitly stated and limited otherwise, the terms "connected," "directly connected," "indirectly connected," "fixedly connected," "mounted," "assembled" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; the terms "mounted," "connected," and "fixedly connected" may be directly connected or indirectly connected through intervening media, and may also be in communication between two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.

Although the embodiments of the present application are described above, the embodiments are only used for facilitating understanding of the present application, and are not intended to limit the present application. It should be noted that the above-described examples or implementations are merely exemplary and not limiting. Accordingly, the application is not limited to what has been particularly shown and described herein. Various modifications, substitutions, or omissions may be made in the form and details of the embodiments without departing from the scope of the application.

Claims (15)

1. An injection structure for injecting fuel and oxidant into a rotary detonation combustor, characterized in that the injection structure is provided with a first injection runner, a second injection runner, and a third injection runner, the first injection runner and the second injection runner being arranged to inject oxidant into the rotary detonation combustor, the third injection runner being arranged to inject fuel into the rotary detonation combustor;

the injection port of the first injection flow channel is a first nozzle, the injection port of the second injection flow channel is a second nozzle, and the injection port of the third injection flow channel is a third nozzle;

the first nozzle and the second nozzle are annular nozzles, and the first nozzle is sleeved on the radial outer side of the second nozzle and is arranged at intervals with the second nozzle;

the third spout is located between the first spout and the second spout.

2. The injection structure of claim 1 wherein the first and second injection flow passages are annular flow passages and the first injection flow passage is sleeved radially outward of the second injection flow passage and spaced from the second injection flow passage; the third injection flow passage is located between the first injection flow passage and the second injection flow passage.

3. The injection structure of claim 2 wherein the injection structure is provided with an oxidant input runner located on an upstream side of the first and second injection runners and in communication with an inlet of the first and second injection runners.

4. An injection structure according to claim 3 wherein a deflector is provided in the oxidant inlet flow passage, the deflector being provided with a first deflector ramp and a second deflector ramp disposed opposite each other, the first deflector ramp being arranged to direct oxidant into the first injection flow passage and the second deflector ramp being arranged to direct oxidant into the second injection flow passage.

5. The insufflating construction of any one of claims 1 to 4 wherein,

the central axis of the third nozzle extends along the axial direction of the annular nozzle.

6. The insufflating construction of any one of claims 1 to 4 wherein,

the first injection flow passage comprises a first constant diameter section and a first expansion section which are sequentially communicated, a third diversion inclined plane is arranged on the first expansion section, and the third diversion inclined plane is arranged to extend obliquely to the direction close to the third nozzle;

along the injection direction of second injection runner, the second injection runner is including second constant diameter section and the second expansion section of intercommunication in proper order, the second expansion section is equipped with the fourth water conservancy diversion inclined plane, the fourth water conservancy diversion inclined plane sets up to be close to the direction slope of third spout extends.

7. The insufflating structure of claim 6 wherein,

the first expansion section is also provided with a fifth diversion inclined plane which is arranged opposite to the third diversion inclined plane, and the fifth diversion inclined plane is arranged to extend obliquely in a direction away from the third nozzle;

the second expansion section is also provided with a sixth diversion inclined plane which is arranged opposite to the fourth diversion inclined plane, and the sixth diversion inclined plane is arranged to extend obliquely in a direction away from the third nozzle.

8. The structure of any one of claims 1 to 4, wherein the third injection flow passage comprises a fuel delivery passage, the fuel delivery passage being an annular flow passage, the fuel delivery passage being nested between and spaced apart from the first and second injection flow passages.

9. The injection structure of claim 8 wherein the third injection runner further comprises an injection runner located on a downstream side of the fuel delivery channel and in communication with the fuel delivery channel, the injection runner having a cross-sectional area that is smaller than a cross-sectional area of the fuel delivery channel, an outlet of the injection runner forming the third orifice;

the injection flow passage comprises a plurality of sub flow passages which are arranged at intervals along the circumferential direction of the fuel conveying passage; alternatively, the injection flow channel is an annular flow channel.

10. An injection structure according to any one of claims 1 to 4, wherein the injection structure is provided with a fuel supply channel in communication with the third injection flow passage arranged to deliver fuel thereto;

wherein the fuel supply passage is provided radially outward of the third injection flow passage; and/or

The number of the fuel supply channels is a plurality of the fuel supply channels, and the plurality of the fuel supply channels are arranged at intervals along the circumferential direction of the annular nozzle.

11. The jetting structure of any one of claims 1 to 4, wherein the jetting structure comprises:

injecting the shell;

an injection inner shell sleeved on the inner side of the injection outer shell and arranged at intervals with the injection outer shell; and

the middle ring is sleeved between the injection inner shell and the injection outer shell, a space between the middle ring and the injection outer shell forms the first injection flow channel, a space between the middle ring and the injection inner shell forms the second injection flow channel, and the third injection flow channel is arranged on the middle ring.

12. The insufflating structure of claim 11, further comprising:

a first connecting piece located between the intermediate ring and the inner housing and connecting the intermediate ring and the inner housing; and/or

And the second connecting piece is positioned between the middle ring and the injection shell and is used for connecting the middle ring and the injection shell.

13. A combustion system for a rotary knock engine, the combustion system comprising:

a combustion chamber body provided with a rotary detonation combustion chamber; and

the injection structure of any one of claims 1 to 12, a first, a second and a third nozzle of the injection structure in communication with the rotary detonation combustor.

14. The combustion system of claim 13 wherein said combustion chamber body is of unitary construction with said injection structure.

15. A rotary knock engine, comprising: combustion system according to claim 13 or 14.