CN116892736A - Distributed oil injection device and method for rotary detonation combustion chamber - Google Patents

Abstract

The application provides a distributed oil injection device and method for a rotary detonation combustor, and relates to the field of aircraft engines. The burner is provided with a combustion chamber, an air inlet and an air outlet, wherein the air inlet is used for being communicated with an air inlet device of the engine, and the air outlet is used for discharging combusted gas. The first fuel injection unit comprises a swirl nozzle which is arranged on the burner and is used for injecting fuel into the combustion chamber so that the fuel forms a first atomization flow field at least in the wall surface area of the combustion chamber under the action of air flow. The second fuel injection unit comprises a direct injection nozzle which is arranged on the combustor, the direct injection nozzle is positioned at the downstream of the cyclone nozzle in the airflow flowing direction, and the direct injection nozzle is used for injecting fuel into the combustion chamber so that the fuel forms a second atomization flow field in the area, away from the wall surface, of the combustion chamber under the action of the airflow. The motor can stably and reliably operate under the wide Mach number condition.

Description

Distributed oil injection device and method for rotary detonation combustion chamber

Technical Field

The application relates to the field of jet propulsion devices, in particular to a distributed oil injection device and method for a rotary detonation combustor.

Background

A rotary knock engine belongs to an engine that generates an air flow by combustion, and thrust of the engine is obtained from the air flow according to a reaction force principle. Rotary knock engines operate with knock combustion and have great potential in improving the performance of conventional engines. The rotary detonation engine usually adopts an annular combustion chamber, reactants enter the annular combustion chamber along the axial direction, detonation waves continuously rotate along the circumferential direction, and combustion products are axially discharged out of the engine through a spray pipe, so that the problem that the length and the working frequency of the combustion chamber are limited due to the axial and intermittent movement of the pulse detonation engine is avoided. The rotary detonation engine has high thermodynamic efficiency, small volume and light weight, thereby being capable of improving the thrust-weight ratio of the aircraft.

Currently, the combustion chamber is composed of a diffuser, a flame tube, an oil injection device, a detonation device and the like. The fuel injection device has the functions of atomizing fuel, accelerating the formation of mixed gas, promoting stable combustion of the fuel and improving the combustion efficiency of the fuel, thereby providing stable reaction thrust. Whether a jet propulsion engine works reliably or not depends to a large extent on the reliability of the operation of the injection device in which the fuel supply is the core point.

The inventor researches find that the rotary knocking engine in the prior art has at least the following disadvantages:

under the condition of wide flight Mach number, the atomization quality of fuel in the fuel injection device is poor, and the fuel is insufficiently combusted, so that the performance of the jet propulsion engine is low and the working stability is poor.

Disclosure of Invention

The application aims to provide a distributed oil injection device and a distributed oil injection method for a rotary detonation combustor, which can improve the performance and the working stability of a jet propulsion engine under the condition of wide flight Mach number.

Embodiments of the present application are implemented as follows:

in a first aspect, the present application provides a rotary detonation combustor distributed fuel injection device comprising:

the burner is provided with a combustion chamber, an air inlet and an air outlet which are both communicated with the combustion chamber, wherein the air inlet is used for being communicated with an air inlet device of the engine, and the air outlet is used for discharging combusted gas;

the first oil injection unit comprises a swirl nozzle which is arranged on the combustor and is used for injecting fuel into the combustion chamber so that the fuel forms a first atomization flow field at least in the wall surface area of the combustion chamber under the action of air flow;

and the second oil injection unit comprises a direct injection nozzle, the direct injection nozzle is arranged on the combustor, the direct injection nozzle is positioned at the downstream of the cyclone nozzle in the airflow flowing direction, and the direct injection nozzle is used for injecting fuel into the combustion chamber so as to enable the fuel to form a second atomization flow field in the area, away from the wall surface, of the combustion chamber under the action of airflow.

In an alternative embodiment, the burner comprises a first barrel and a second barrel, the first barrel being sleeved outside the second barrel, the first barrel and the second barrel together defining the annular combustion chamber; one end of the first cylinder and the second cylinder define an annular air inlet, and the other end of the first cylinder and the second cylinder define an annular air outlet; the swirl nozzle and the direct injection nozzle are both arranged on the wall of the first cylinder.

In an alternative embodiment, the first barrel comprises a first guiding barrel section, a first diffusion barrel section and a first combustion barrel section which are sequentially connected, wherein the first guiding barrel section and the first combustion barrel section are equal-diameter sections, and the diameter of the first guiding barrel section is smaller than that of the first combustion barrel section; the diameter of the first diffusion barrel section gradually increases in the direction from the first guide barrel section to the first combustion barrel section; the cylinder wall of the first guide cylinder section is provided with a first inlet, and the cyclone nozzle is arranged on the first guide cylinder section and is communicated with the first inlet.

In an alternative embodiment, the first barrel further comprises a first outer flange structure and a second outer flange structure, the first outer flange structure is connected to an end of the first guide barrel section away from the first diffusion barrel section, and the second outer flange structure is connected to an end of the first combustion barrel section away from the first diffusion barrel section.

In an alternative embodiment, the second barrel comprises a second guiding barrel section, a second diffusion barrel section and a second combustion barrel section which are sequentially connected, wherein the second guiding barrel section and the second combustion barrel section are equal-diameter sections, and the diameter of the second guiding barrel section is larger than that of the second combustion barrel section; the diameter of the second diffusion barrel section gradually decreases in a direction from the second guide barrel section to the second combustion barrel section; the cylinder wall of the second guide cylinder section is provided with a second inlet, and the direct injection nozzle is arranged on the second diffusion cylinder section and is communicated with the second inlet; the ends of the first guide cylinder section and the second guide cylinder section define an annular air inlet; the ends of the first combustion can section and the second combustion can section define an annular air outlet;

the combustion chamber comprises a drainage section, a diffusion section and a combustion chamber which are sequentially communicated, the flow section of the drainage section is smaller than that of the combustion chamber, and the flow section of the diffusion section is gradually increased in the direction from the drainage section to the combustion chamber.

In an alternative embodiment, the second barrel further comprises a first inner flange structure and a second inner flange structure, the first inner flange structure is connected to an end of the second guiding barrel section away from the second diffusion barrel section, and the second inner flange structure is connected to an end of the second combustion barrel section away from the second diffusion barrel section.

In an alternative embodiment, the swirl nozzle includes a housing having opposed first open and first closed ends, the first open end for inputting fuel; the cyclone shell is provided with a second opposite opening end and a second closed end, a plurality of cyclone holes are formed in the peripheral wall of the cyclone shell, the plurality of cyclone holes are arranged at intervals in the circumferential direction of the cyclone shell, the axis of each cyclone hole is tangential to the peripheral wall of the cyclone shell, each cyclone hole is communicated with the second opening end, and the second opening end is communicated with the combustion chamber; the cyclone casing is installed in the shell, the second open end penetrates through the first closed end, the cyclone casing is matched with the shell to define an annular oil duct communicated with the cyclone holes, and the annular oil duct is communicated with the first open end.

In an alternative embodiment, the swirl shell has an enlarged bore section, the diameter of which decreases progressively in the direction from the second open end to the second closed end, the end of the enlarged bore section remote from the second closed end being provided as the second open end; the swirl holes are positioned between the second closed end and the expanding hole section.

In an alternative embodiment, the direct injection nozzle is provided with a variable diameter oil jet, the larger open end of the variable diameter oil jet is used for inputting fuel, and the smaller open end of the variable diameter oil jet is communicated with the combustion chamber.

In a second aspect, the present application provides a method for distributed injection of fuel into a rotary detonation combustor, suitable for use in a distributed injection device of a rotary detonation combustor according to any of the preceding embodiments, the method comprising:

when the engine operates at a low Mach number state at high altitude, a first oil injection unit is started, fuel enters a combustion chamber, and is atomized under the action of air flow to form a first atomized flow field uniformly distributed in the combustion chamber;

when the engine operates in a high Mach number state at high altitude, a first oil injection unit and a second oil injection unit are started, fuel enters a combustion chamber, and under the action of air flow, the fuel entering from the first oil injection unit is atomized and forms a first atomization flow field distributed in the combustion chamber; the fuel entering from the second fuel injection unit is atomized and distributed in the second atomized flow field of the combustion chamber; the first atomization flow field and the second atomization flow field are matched and uniformly distributed in the combustion chamber.

The embodiment of the application has the beneficial effects that:

in summary, in the distributed oil injection device for the rotary detonation combustor provided in this embodiment, the swirl nozzle and the direct injection nozzle in the separate mode are configured on the combustor, and the swirl nozzle and the direct injection nozzle are matched, so that the stable operation of the engine under the wide flight mach number condition can be ensured, and the reliability and stability of the engine working under the wide flight mach number condition can be improved. That is, in order to ensure the stability of the rotary knock engine in the wide speed range, that is, in the high altitude and low mach number state, the fuel atomization quality is required to be high and the fuel penetration capability is required to be high in the high altitude and high mach number state. Therefore, the embodiment adopts a fuel injection scheme of combining and distributing a swirl nozzle and a direct injection nozzle, and the fuel injection scheme is specifically as follows:

when the engine works in a high-altitude low Mach number state, the flow rate of the engine is small, the dynamic pressure of air flow is small, fuel is easy to penetrate in the air flow, a swirl nozzle is opened, after the fuel is sprayed into a combustion chamber through the swirl nozzle, the fuel has flowing speeds in the radial direction and the circumferential direction of the combustion chamber, after the fuel contacts with the air flow, the fuel is torn into droplet-shaped fuel droplets under the combined action of centrifugal force and the air flow, atomization is realized, and finally an atomization flow field is formed in the whole combustion chamber, so that the stable operation of the engine in the low Mach number state can be met.

When the engine works in a high Mach number state, the required fuel flow and penetration depth are large, at the moment, the swirl nozzle and the direct injection nozzle work simultaneously, the swirl nozzle can form a first atomization flow field in a wall area of the combustion chamber, the direct injection nozzle can form a second atomization flow field in a central area of the combustion chamber, so that the first atomization flow field and the second atomization flow field are matched to form a high-quality full atomization flow field, the atomization quality is ensured, the penetration depth is also ensured, the atomization flow field can be uniformly distributed in the combustion chamber, and the stable operation of the engine in the high Mach number state is ensured.

Meanwhile, the swirl nozzle is arranged on the drainage section, the height of a combustion chamber of the drainage section is small, and the swirl nozzle is suitable for the characteristics of high atomization quality and small penetration depth of the swirl nozzle. The direct injection nozzle is arranged on the diffusion section, the height of the combustion chamber of the diffusion section is large, and the direct injection nozzle is suitable for the characteristic of large penetration depth of the direct injection nozzle. The first diffusion cylinder section and the second diffusion cylinder section are respectively provided with a direct injection nozzle, so that the full flow field penetration of fuel in the diffusion section under the high Mach number working condition of the engine is met, the fuel is uniformly distributed, the atomization quality is high, and the combustion efficiency is improved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of a rotary detonation combustor distributed fuel injection device according to an embodiment of the present application;

FIG. 2 is a schematic diagram of another view of a rotary detonation combustor distributed fuel injection device in accordance with an embodiment of the present application;

FIG. 3 is a schematic cross-sectional view of a rotary detonation combustor distributed fuel injection device in accordance with an embodiment of the present application;

FIG. 4 is a schematic view of the structure of a first cartridge according to an embodiment of the present application;

FIG. 5 is a schematic cross-sectional structural view of a second cartridge according to an embodiment of the present application;

FIG. 6 is a schematic cross-sectional view of a swozzle according to an embodiment of the present application;

fig. 7 is a schematic cross-sectional view of a direct injection nozzle according to an embodiment of the application.

Icon:

a 100-burner; 101-an air inlet; 102-an air outlet; 103-combustion chamber; 1031-a drainage segment; 1032—a diffuser; 1033-combustion chamber; 110-a first barrel; 111-a first guiding barrel section; 112-a first diffuser section; 113-a first combustion bowl section; 114-a first external flange structure; 115-a second external flange structure; 116-a first inlet; 117-a second inlet; 120-a second barrel; 121-a second guiding barrel section; 122-a second diffuser section; 123-a second combustion bowl section; 124-a first internal flange structure; 125-a second internal flange structure; 200-a first oil injection unit; 210-a swirl nozzle; 211-a housing; 2111-a first open end; 2112-a first closed end; 212-a swirl shell; 2121-a second open end; 2122-a second closed end; 2123-swirl chamber; 2124-swirl holes; 2125-expanding a hole section; 213-annular oil passage; 220-a first oil delivery pipe; 300-a second oil injection unit; 310-direct injection nozzle; 311-reducing type oil spray hole; 320-a second oil delivery pipe; 400-high frequency pressure sensor.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. The components of the embodiments of the present application generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the application, as presented in the figures, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the present application, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present application and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal," "vertical," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be 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.

In the prior art, a rotary detonation engine belongs to a jet propulsion device, and a combustion device of the rotary detonation engine comprises a diffuser, a flame tube, an oil injection device and a detonation device. The fuel injection device has the functions of atomizing fuel, accelerating the formation of mixed gas, promoting stable combustion and improving combustion efficiency. The reliability of operation of a jet propulsion engine depends to a large extent on the reliability of operation of the injection device. The inventor finds in the study that when the rotary detonation engine works in a low Mach number state, the airflow dynamic pressure is small, and the fuel atomization is relatively simple; when the rotary detonation engine works in a high Mach number state, the dynamic pressure of the air flow is large, so that a large obstruction to the fuel entering the combustion chamber is formed, the penetration depth of the fuel in the air flow is small, and atomization is relatively difficult, so that the conventional rotary detonation engine has poor atomization quality of the fuel under the wide Mach number condition, and insufficient fuel combustion is caused, so that the jet propulsion engine has low performance and poor working stability.

In view of this, the designer provides a distributed oil injection device for a rotary detonation combustor, and the engine can ensure stable operation under high altitude and low Mach number conditions and stable operation under high altitude and high Mach number conditions, so that the engine can operate stably and reliably under wide Mach number conditions.

Referring to fig. 1 to 7, in the present embodiment, a rotary detonation combustor distributed fuel injection apparatus includes a combustor 100, a first fuel injection unit 200, and a second fuel injection unit 300. The burner 100 is provided with a combustion chamber 103, and an air inlet 101 and an air outlet 102 both communicating with the combustion chamber 103, the air inlet 101 being for communication with an air intake device of the engine, the air outlet 102 being for discharging combusted gas. The first fuel injection unit 200 includes a swirl nozzle 210, and the swirl nozzle 210 is mounted on the combustor 100 for injecting fuel into the combustion chamber 103 such that the fuel forms a first atomized flow field at least in a wall area of the combustion chamber 103 under the action of the air flow. The second fuel injection unit 300 includes a direct injection nozzle 310, the direct injection nozzle 310 being mounted on the combustor 100, the direct injection nozzle 310 being located downstream of the swozzle 210 in the direction of airflow, the direct injection nozzle 310 being configured to inject fuel into the combustion chamber 103 such that the fuel forms a second atomized flow field in a region of the combustion chamber 103 remote from the wall surface under the influence of the airflow.

In view of the above, the working mode of the distributed oil injection device for the rotary detonation combustor provided by the embodiment is as follows:

when the engine works in a high-altitude low Mach number state, the flow rate of the engine is small, the dynamic pressure of air flow is small, the influence of the dynamic pressure of air flow on the combustion discharge into a combustion channel is small, the obstruction is small, fuel is easy to penetrate in the air flow, the swirl nozzle 210 is started, after the fuel is sprayed into the combustion chamber 103 through the swirl nozzle 210, the fuel simultaneously has the flow speed in the radial direction and the circumferential direction of the combustion chamber 103, after the fuel contacts with the air flow, the fuel is torn into droplet-shaped fuel droplets under the combined action of centrifugal force and air flow shearing, atomization is realized, a first atomization flow field is finally formed in the whole combustion chamber 103, and the first atomization flow field is distributed in the area of the whole cross section of the combustion chamber 103, so that the stable operation of the engine in the low Mach number state can be satisfied.

When the engine works in a high Mach number state, the required fuel flow and penetration depth are large, at this time, the swirl nozzle 210 and the direct nozzle 310 work simultaneously, the swirl nozzle 210 can form a first atomization flow field in the wall area of the combustion chamber 103, the direct nozzle 310 can form a second atomization flow field in the central area of the combustion chamber 103, so that the first atomization flow field and the second atomization flow field cooperate to form a high-quality full atomization flow field, the atomization quality is ensured, the penetration depth is also ensured, the atomization flow field can be uniformly distributed in the combustion chamber 103, and the stable operation of the engine in the high Mach number state is ensured. The uniform distribution can be understood as that in the annular cross section area of the combustion chamber 103, fuel can move from the outer side to the inner side of the cross section area, so that the fuel can be well distributed in the whole cross section area of the combustion chamber 103, and the fuel can be atomized in the cross section area of the combustion chamber 103, so that a full atomization flow field is realized, and therefore, the quality of the atomization flow field is high, and the engine is stable and reliable in operation. The cross section of the combustion chamber 103 is a plane perpendicular to the axis of the combustion chamber 103.

The following examples illustrate the detailed construction of the rotary detonation combustor distributed fuel injection device of the present application.

Referring to fig. 3 and 4, in the present embodiment, optionally, the combustor 100 includes a first barrel 110 and a second barrel 120, the first barrel 110 is sleeved outside the second barrel 120, and the first barrel 110 and the second barrel 120 together define an annular combustion chamber 103, that is, the cross-sectional shape of the combustion chamber 103 is a circular ring. One end of the first and second barrels 110, 120 defines an annular air inlet 101, and the other end of the first and second barrels 110, 120 defines an annular air outlet 102. The swirl nozzles 210 and the direct nozzles 310 are mounted on the wall of the first cylinder 110, and a plurality of direct nozzles 310 are mounted on the wall of the second cylinder 120. Thus, the burner 100 is simple in structure, easy to manufacture, high in assembly quality, and easy to cooperate with other parts of the engine such as an air intake device.

Specifically, the first barrel 110 includes a first guide barrel section 111, a first diffuser barrel section 112, a first combustion barrel section 113, a first circumscribing flange structure 114, and a second circumscribing flange structure 115. Wherein, the first external flange structure 114, the first guiding barrel section 111, the first diffusion barrel section 112, the first combustion barrel section 113 and the second external flange structure 115 are sequentially connected, it is to be understood that the first barrel 110 can be provided as an integrated structure, which is convenient for processing and manufacturing, and has good integral structural integrity, high structural strength, strong deformation resistance and long service life. Meanwhile, the first guide cylinder section 111 and the first combustion cylinder section 113 are equal-diameter sections, the cross-sectional shapes of the first guide cylinder section 111 and the first combustion cylinder section 113 are circular, and the diameter of the first guide cylinder section 111 is smaller than that of the first combustion cylinder section 113. The wall of the first guiding barrel section 111 is provided with a plurality of first inlets 116, and the plurality of first inlets 116 are uniformly spaced in the circumferential direction of the first guiding barrel section 111, for example, in this embodiment, the number of the first inlets 116 is five, and the axis of each first inlet 116 extends in the radial direction of the first guiding barrel section 111. The cross-sectional profile of the first diffusion cylinder section 112 is circular, and the diameter of the first diffusion cylinder section 112 gradually increases in the direction from the first guide cylinder section 111 toward the first combustion cylinder section 113, that is, the diameter of the end of the first diffusion cylinder section 112 connected to the first guide cylinder section 111 is smaller than the diameter of the end of the first diffusion cylinder section 112 connected to the first combustion cylinder section 113, and the diameter of the end of the first diffusion cylinder section 112 communicating with the first guide cylinder section 111 is equal to the diameter of the first guide cylinder section 111, and at the same time, the diameter of the end of the first diffusion cylinder section 112 communicating with the first combustion cylinder section 113 is equal to the diameter of the first combustion cylinder section 113. The first diffusion barrel section 112 is further provided with a plurality of second inlets 117, and the plurality of second inlets 117 are uniformly spaced apart in the circumferential direction of the first diffusion barrel section 112, for example, in this embodiment, the number of the second inlets 117 may be eight, and an axis of each second inlet 117 is perpendicular to a circumferential wall of the first diffusion barrel section 112.

Referring to fig. 3 and 5 in combination, the second barrel 120 includes a second guide barrel section 121, a second diffuser barrel section 122, a second combustion barrel section 123, a first internal flange structure 124, and a second internal flange structure 125. Wherein, first inscribed flange structure 124, second guide section of thick bamboo 121, second diffusion section of thick bamboo 122, second combustion bowl section of thick bamboo 123 and second inscribed flange structure 125 connect gradually, and it should be understood that second section of thick bamboo 120 can set up as an organic whole structure, and the manufacturing of being convenient for, and overall structural integrity is good, and structural strength is high, and anti deformability is strong, long service life. Meanwhile, the second guiding cylinder section 121 and the second combustion cylinder section 123 are both equal-diameter sections, the cross-sectional shapes of the second guiding cylinder section 121 and the second combustion cylinder section 123 are circular, and the diameter of the second guiding cylinder section 121 is smaller than that of the second combustion cylinder section 123. The cross-sectional profile of the second diffusion barrel section 122 is circular, and the diameter of the second diffusion barrel section 122 gradually decreases in the direction from the second guide barrel section 121 to the second combustion barrel section 123, that is, the diameter of the end of the second diffusion barrel section 122 connected to the second guide barrel section 121 is larger than the diameter of the end of the second diffusion barrel section 122 connected to the second combustion barrel section 123, and the diameter of the end of the second diffusion barrel section 122 communicating with the second guide barrel section 121 is equal to the diameter of the second guide barrel section 121, and at the same time, the diameter of the end of the second diffusion barrel section 122 communicating with the second combustion barrel section 123 is equal to the diameter of the second combustion barrel section 123.

It should be noted that, the first barrel 110 is sleeved outside the second barrel 120, and the two barrels define an annular combustion chamber 103, where the combustion chamber 103 includes a drainage section 1031, a diffuser section 1032, and a combustion chamber 1033 that are sequentially communicated. Specifically, the first guide cylinder section 111 and the second guide cylinder section 121 cooperate to define a flow guiding section 1031, the first diffusion cylinder section 112 and the second diffusion cylinder section 122 cooperate to define a diffusion section 1032, the first combustion cylinder section 113 and the second combustion cylinder section 123 cooperate to define a combustion chamber 1033, a flow cross section of the flow guiding section 1031 is smaller than a flow cross section of the combustion chamber 1033, and a flow cross section of the diffusion section 1032 gradually increases in a direction from the flow guiding section 1031 to the combustion chamber 1033. Thus, the fuel enters the flow-directing section 1031 at a small penetration depth and the fuel enters the diffuser section 1032 and combustion chamber 1033 at a large penetration depth. Wherein the flow cross-section is a plane perpendicular to the axis of the combustion chamber 103. Thus, the plurality of first inlets 116 communicate with the flow-directing section 1031 and the plurality of second inlets 117 communicate with the diffuser section 1032.

Referring to fig. 3 and 6, in this embodiment, optionally, the first fuel injection unit 200 includes a first fuel delivery pipe 220 and a plurality of swirl nozzles 210, where the first fuel delivery pipe 220 may be an annular pipe, and the first fuel delivery pipe 220 is used for communicating with a fuel delivery device of an engine. One end of each of the plurality of swirl nozzles 210 is communicated with the wall of the first oil delivery pipe 220, and the other end is communicated with the corresponding first inlet 116. For example, in the present embodiment, the number of the swirl nozzles 210 is equal to the number of the first inlets 116 and is five, it should be understood that the structures of the five swirl nozzles 210 may be the same, and in the present embodiment, only one structure of the swirl nozzles 210 is used for illustration in order to avoid redundancy of description.

Specifically, swirl nozzle 210 includes an outer housing 211 and a swirl shell 212. The housing 211 is a circular shell having opposed first open and closed ends 2111 and 2112, the first open end 2111 being adapted to be coupled to an oil delivery device of an engine for delivering fuel. The cyclone casing 212 is a circular casing having a second open end 2121 and a second closed end 2122 opposite to each other, the cyclone casing 212 has a cyclone chamber 2123, a plurality of cyclone holes 2124 communicating with the cyclone chamber 2123 are provided on a peripheral wall of the cyclone casing 212, and the number of the cyclone holes 2124 is selected as required, which is not particularly limited in this embodiment. The swirl holes 2124 are arranged at intervals in the circumferential direction of the swirl shell 212, the axis of each swirl hole 2124 is tangential to the circumferential wall of the swirl shell 212, each swirl hole 2124 is communicated with the second open end 2121, one end of the swirl chamber 2123, which is far away from the second closed end 2122, is the second open end 2121, and the second open end 2121 is communicated with the combustion chamber 103 through the first inlet 116. Meanwhile, the swirl shell 212 is mounted within the housing 211 with the second open end 2121 extending through the first closed end 2112, the second closed end 2122 being opposite the first open end 2111, the swirl shell 212 cooperating with the housing 211 to define an annular oil gallery 213 in communication with the plurality of swirl holes 2124, the annular oil gallery 213 being in communication with the first open end 2111, the housing 211 being connected to the first oil delivery pipe 220, the first open end 2111 being in communication with the first oil delivery pipe 220. In this way, after entering from the first oil delivery pipe 220, the fuel flows into the annular oil duct 213, then enters into the swirl chamber 2123 from the plurality of swirl holes 2124 distributed on the peripheral wall of the swirl shell 212, forms a swirl in the swirl chamber 2123, and then is discharged from the second open end 2121 and enters into the combustion chamber 103, and when entering into the combustion chamber 103, the fuel in the swirl state has circumferential and radial speeds, so that the fuel can be better distributed in the combustion chamber 103, contacts with the airflow, is atomized, and forms an atomized flow field.

Further, the swirl chamber 2123 of the swirl shell 212 has an enlarged bore section 2125, the diameter of the enlarged bore section 2125 gradually decreases in a direction from the second open end 2121 toward the second closed end 2122, an end of the enlarged bore section 2125 away from the second closed end 2122 is provided as the second open end 2121, and a plurality of swirl holes 2124 are each located between the second closed end 2122 and the enlarged bore section 2125. Thus, the fuel in the swirl chamber 2123 can be injected into the combustion chamber 103 in a conical surface form, the distribution area is wider, the contact effect with the air flow is good, and the atomization effect is good.

Referring to fig. 3 and 7, in the present embodiment, optionally, the second fuel injection unit 300 includes a second fuel delivery pipe 320 and a plurality of direct injection nozzles 310, where the second fuel delivery pipe 320 may be an annular pipe, and the second fuel delivery pipe 320 is used to communicate with a fuel delivery device of an engine so as to input fuel. One end of each of the plurality of direct injection nozzles 310 is connected to a pipe wall of the second oil delivery pipe 320, the plurality of direct injection nozzles 310 are uniformly spaced apart in an extending direction of the second oil delivery pipe 320, and the other ends of the plurality of direct injection nozzles 310 are respectively communicated with the plurality of second inlets 117. For example, in the present embodiment, the number of the direct nozzles 310 is equal to the number of the second inlets 117 and is five. The structure of each of the direct nozzles 310 may be identical, and in this embodiment, only one direct nozzle 310 is illustrated to avoid redundancy of description.

Alternatively, the direct injection nozzle 310 is provided with a variable diameter type oil injection hole 311, wherein one end of the variable diameter type oil injection hole 311 with a larger opening is communicated with the second oil delivery pipe 320 for inputting fuel, and one end of the variable diameter type oil injection hole 311 with a smaller opening is communicated with the corresponding second inlet 117. The fuel injected into the combustion chamber 103 from the direct injection nozzle 310 has an acceleration effect by the variable diameter injection hole 311, and the penetration depth is greater.

It should be appreciated that in other embodiments, the number of second fuel injection units 300 may be two. One of the second fuel injection units 300 is installed on the first diffusion cylinder section 112, the other second fuel injection unit 300 is installed on the second diffusion cylinder section 122, fuel is injected into the combustion chamber 103 by the two second fuel injection units 300, the required penetration depth of the fuel injected into the combustion chamber 103 by each second fuel injection unit 300 is reduced, the fuel injection pressure of the second fuel injection units 300 can be reduced, and the cost is reduced.

In other embodiments, a high frequency pressure sensor 400 that detects detonation waves may be optionally provided on the wall of the first barrel 110. By analyzing the high frequency pressure signal, whether detonation is successful or not is determined, thereby determining whether the fuel nozzle and the direct nozzle 310 are operating.

In the distributed oil injection device for the rotary detonation combustor provided by the embodiment, five swirl nozzles 210 are configured in the drainage section 1031, sixteen direct injection nozzles 310 are configured in the diffusion section 1032, and the swirl nozzles 210 and the direct injection nozzles 310 are controlled to operate cooperatively, so that the engine can stably operate under the working conditions of low Mach number and high Mach number.

The embodiment also provides a distributed oil injection method for the rotary detonation combustor, and the engine can adapt to working conditions of different Mach numbers based on the distributed oil injection device for the rotary detonation combustor, so that the engine can stably and reliably operate under the wide Mach number condition.

In this embodiment, the mach number is between 2 and 4, which represents a wide speed range and a wide mach number range; wherein, the Mach number is lower than 3.0 and is in a low Mach number state; higher than mach 3.0, is a high mach number state.

The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims (10)

1. A rotary detonation combustor distributed fuel injection device comprising:

the burner is provided with a combustion chamber, an air inlet and an air outlet which are both communicated with the combustion chamber, wherein the air inlet is used for being communicated with an air inlet device of the engine, and the air outlet is used for discharging combusted gas;

the first oil injection unit comprises a swirl nozzle which is arranged on the combustor and is used for injecting fuel into the combustion chamber so that the fuel forms a first atomization flow field at least in the wall surface area of the combustion chamber under the action of air flow;

and the second oil injection unit comprises a direct injection nozzle, the direct injection nozzle is arranged on the combustor, the direct injection nozzle is positioned at the downstream of the cyclone nozzle in the airflow flowing direction, and the direct injection nozzle is used for injecting fuel into the combustion chamber so as to enable the fuel to form a second atomization flow field in the area, away from the wall surface, of the combustion chamber under the action of airflow.

2. The rotary detonation combustor distributed fuel injection device of claim 1, wherein:

the burner comprises a first cylinder and a second cylinder, the first cylinder is sleeved outside the second cylinder, and the first cylinder and the second cylinder jointly define an annular combustion chamber; one end of the first cylinder and the second cylinder define an annular air inlet, and the other end of the first cylinder and the second cylinder define an annular air outlet; the swirl nozzle and the direct injection nozzle are both arranged on the wall of the first cylinder.

3. The rotary detonation combustor distributed fuel injection device of claim 2, wherein:

the first cylinder comprises a first guide cylinder section, a first diffusion cylinder section and a first combustion cylinder section which are sequentially connected, wherein the first guide cylinder section and the first combustion cylinder section are equal-diameter sections, and the diameter of the first guide cylinder section is smaller than that of the first combustion cylinder section; the diameter of the first diffusion barrel section gradually increases in the direction from the first guide barrel section to the first combustion barrel section; the cylinder wall of the first guide cylinder section is provided with a first inlet, and the cyclone nozzle is arranged on the first guide cylinder section and is communicated with the first inlet.

4. The rotary detonation combustor distributed fuel injection device of claim 3, wherein:

the first cylinder further comprises a first outer flange structure and a second outer flange structure, the first outer flange structure is connected to one end of the first guide cylinder section, which is far away from the first diffusion cylinder section, and the second outer flange structure is connected to one end of the first combustion cylinder section, which is far away from the first diffusion cylinder section.

5. The rotary detonation combustor distributed fuel injection device of claim 3, wherein:

the second cylinder comprises a second guide cylinder section, a second diffusion cylinder section and a second combustion cylinder section which are sequentially connected, the second guide cylinder section and the second combustion cylinder section are equal-diameter sections, and the diameter of the second guide cylinder section is larger than that of the second combustion cylinder section; the diameter of the second diffusion barrel section gradually decreases in a direction from the second guide barrel section to the second combustion barrel section; the cylinder wall of the second guide cylinder section is provided with a second inlet, and the direct injection nozzle is arranged on the second diffusion cylinder section and is communicated with the second inlet; the ends of the first guide cylinder section and the second guide cylinder section define an annular air inlet; the ends of the first combustion can section and the second combustion can section define an annular air outlet;

the combustion chamber comprises a drainage section, a diffusion section and a combustion chamber which are sequentially communicated, the flow section of the drainage section is smaller than that of the combustion chamber, and the flow section of the diffusion section is gradually increased in the direction from the drainage section to the combustion chamber.

6. The rotary detonation combustor distributed fuel injection device of claim 5, wherein:

the second cylinder further comprises a first inner flange structure and a second inner flange structure, the first inner flange structure is connected with one end of the second guiding cylinder section far away from the second diffusion cylinder section, and the second inner flange structure is connected with one end of the second combustion cylinder section far away from the second diffusion cylinder section.

7. The rotary detonation combustor distributed fuel injection device of claim 1, wherein:

the swirl nozzle comprises a housing and a swirl shell, wherein the housing is provided with a first opposite open end and a first closed end, and the first open end is used for inputting fuel; the cyclone shell is provided with a second opposite opening end and a second closed end, a plurality of cyclone holes are formed in the peripheral wall of the cyclone shell, the plurality of cyclone holes are arranged at intervals in the circumferential direction of the cyclone shell, the axis of each cyclone hole is tangential to the peripheral wall of the cyclone shell, each cyclone hole is communicated with the second opening end, and the second opening end is communicated with the combustion chamber; the cyclone casing is installed in the shell, the second open end penetrates through the first closed end, the cyclone casing is matched with the shell to define an annular oil duct communicated with the cyclone holes, and the annular oil duct is communicated with the first open end.

8. The rotary detonation combustor distributed fuel injection device of claim 7, wherein:

the swirl shell is provided with an expanding hole section, the diameter of the expanding hole section gradually decreases in the direction from the second open end to the second closed end, and the end of the expanding hole section away from the second closed end is arranged as a second open end; the swirl holes are positioned between the second closed end and the expanding hole section.

9. The rotary detonation combustor distributed fuel injection device of claim 1, wherein:

the direct injection nozzle is provided with a variable-diameter oil spray hole, one end of the variable-diameter oil spray hole, which is larger in opening, is used for inputting fuel, and one end of the variable-diameter oil spray hole, which is smaller in opening, is communicated with the combustion chamber.

10. A method of rotary detonation combustor distributed injection, adapted for use with a rotary detonation combustor distributed injection device as claimed in any one of claims 1 to 9, the method comprising:

when the engine operates at a low Mach number state at high altitude, a first oil injection unit is started, fuel enters a combustion chamber, and is atomized under the action of air flow to form a first atomized flow field uniformly distributed in the combustion chamber;

when the engine operates in a high Mach number state at high altitude, a first oil injection unit and a second oil injection unit are started, fuel enters a combustion chamber, and under the action of air flow, the fuel entering from the first oil injection unit is atomized and forms a first atomization flow field distributed in the combustion chamber; the fuel entering from the second fuel injection unit is atomized and distributed in the second atomized flow field of the combustion chamber; the first atomization flow field and the second atomization flow field are matched and uniformly distributed in the combustion chamber.