KR102182639B1 - Injector head, liquid rocket engine combustor using the same and shear coaxial injector used to the same - Google Patents

Abstract

An injection head, a liquid rocket combustor including the same, and a coaxial shear injector used therein are disclosed. The injection head includes: a plurality of coaxial swirl injectors provided so that fuel supplied in a turning direction and an oxidizing agent supplied in an axial direction can meet and be injected in the axial direction rearward after splitting; and a plurality of coaxial shear injectors provided so that both the fuel and the oxidizing agent can be axially moved and injected in the axial direction after splitting to attenuate a transverse disturbance wave due to the coaxial swirl injector.

Description

Injection head, liquid rocket combustor including the same, and coaxial shear injector used therein {INJECTOR HEAD, LIQUID ROCKET ENGINE COMBUSTOR USING THE SAME AND SHEAR COAXIAL INJECTOR USED TO THE SAME}

The present invention relates to an injection head, a liquid rocket combustor including the same, and a coaxial shear sprayer used in the injection head.

A liquid rocket engine is a device that obtains thrust by injecting an oxidizing agent and fuel into a combustion chamber and releasing a large amount of high-temperature and high-pressure combustion gas generated after combustion through a nozzle.

However, in such a liquid rocket engine, combustion instability having a certain specific acoustic mode is very likely to occur during combustion in the combustion chamber. Moreover, the occurrence of combustion instability and its amplification causes a fatal problem in which the engine is damaged, thereby deteriorating the reliability of the liquid rocket engine.

Accordingly, conventionally, an injector type baffle has been used to stabilize combustion of a liquid rocket engine. However, when using an injector type baffle, there is an aspect that the weight of the liquid rocket engine is increased by inevitably inserting a structure inside the combustor.

The technology behind the present application is disclosed in Korean Patent Registration No. 10-0638112.

The present application is to solve the problems of the prior art described above, by using a fluid baffle instead of the conventional injector type baffle, the injection head capable of maintaining the combustion stabilization function and reducing the weight of the liquid rocket combustor, a liquid rocket including the same It is an object of the present invention to provide a coaxial shear sprayer used in a combustor and an injection head.

However, the technical problems to be achieved by the embodiments of the present application are not limited to the technical problems as described above, and other technical problems may exist.

As a technical means for achieving the above technical problem, the injection head according to one aspect of the present application is a coaxial swirl provided to be injected in the axial direction after the fuel supplied in the turning direction and the oxidizing agent supplied in the axial direction meet A plurality of sprayers; And a plurality of coaxial shear injectors provided in a form in which both fuel and oxidant are moved in the axial direction and injected in the axial direction after splitting so that the transverse disturbance wave generated by the coaxial swirl injector is attenuated or combustion instability is reduced. can do.

The liquid rocket combustor according to an aspect of the present application may include an injection head according to an aspect of the present application.

In addition, the coaxial shear injector according to an aspect of the present application may be a coaxial shear injector used in the injection head according to an aspect of the present application.

The above-described problem solving means are merely exemplary and should not be construed as limiting the present application. In addition to the above-described exemplary embodiments, additional embodiments may exist in the drawings and detailed description of the invention.

According to the above-described problem solving means of the present application, attenuation for a transverse disturbance wave generated during combustion instability due to a coaxial swirl sprayer or the like can be performed by the coaxial shear sprayer. Accordingly, in the prior art, a structural baffle had to be forcibly inserted into the combustor to control pressure perturbation, but according to the problem solving means of the present application described above, pressure perturbation can be controlled by the flow of fluid by the coaxial shear injector instead of the structural baffle. I can. Accordingly, while the combustion stabilization function is maintained, weight may be reduced compared to a conventional combustor including a structural baffle.

1 is a schematic perspective view of a spray head according to an embodiment of the present application.
2 is a schematic cross-sectional view of an injection head in a front-rear direction according to an embodiment of the present invention for explaining the rotation of the fuel of the coaxial swirl injector.
3 is a schematic cross-sectional view in a schematic front-rear direction of a spray head according to an embodiment of the present application.
4 is a schematic cross-sectional view of a coaxial swirl injector of a jet head according to an embodiment of the present application in a front-rear direction.
5 is an AA cross-sectional view of FIG. 4.
6 is a schematic cross-sectional view in the front-rear direction of the coaxial shear sprayer of the injection head according to an embodiment of the present application.
7 is a cross-sectional view taken along BB of FIG. 6.
8 is a cross-sectional view taken along the line CC of FIG. 6.

Hereinafter, exemplary embodiments of the present application will be described in detail with reference to the accompanying drawings so that those of ordinary skill in the art may easily implement the present application. However, the present application may be implemented in various different forms and is not limited to the embodiments described herein. In addition, in the drawings, parts not related to the description are omitted in order to clearly describe the present application, and similar reference numerals are attached to similar parts throughout the specification.

Throughout this specification, when a part is said to be "connected" with another part, it is not only the case that it is "directly connected", but also "indirectly connected" or "electrically connected" with another element interposed therebetween. "Including the case.

Throughout this specification, when a member is positioned "on", "upper", "upper", "under", "lower", and "lower" of another member, this means that a member is located on another member. It includes not only the case where they are in contact but also the case where another member exists between the two members.

Throughout the specification of the present application, when a certain part "includes" a certain component, it means that other components may be further included rather than excluding other components unless specifically stated to the contrary.

In addition, in the description of the embodiments of the present application, terms related to directions or positions (front, front, rear, rear, etc.) are set based on the arrangement state of each component shown in the drawings. For example, when looking at Figure 1, the 6 o'clock direction may be the front, the end facing the 6 o'clock direction is the front end, the 12 o'clock direction is the rear, and the end facing the 12 o'clock direction may be the rear end, etc. have. In addition, as another example, when looking at FIG. 2, the overall 12 o'clock direction is the front, the overall 12 o'clock direction is the front end, the 6 o'clock direction is the rear, the overall 6 o'clock end is the rear end, etc. Can be

The present invention relates to an injection head, a liquid rocket combustor including the same, and a coaxial shear sprayer used in the injection head.

First, a description will be given of a spray head (hereinafter referred to as'the main spray head') 1 according to an embodiment of the present application.

1 is a schematic perspective view of an injection head according to an embodiment of the present application, and FIG. 2 is a schematic cross-sectional view of an injection head in a front-rear direction according to an embodiment of the present application for explaining the rotation of fuel of a coaxial swirl injector to be. For reference, FIG. 1 shows the coaxial shear injector 12 with a dotted line in order to distinguish the coaxial swirl injector 11 and the coaxial shear injector 12.

Referring to FIG. 1, the present injection head 1 includes a plurality of coaxial swirl injectors 11. The coaxial swirl injector 11 mixes fuel supplied to him and an oxidizing agent and injects it backwards (injects a propellant (a mixture of fuel and oxidizer)). For reference, in the injection head, the fuel may be a liquid fuel and the oxidizer may be a gaseous oxidizer.

Referring to FIG. 2, the coaxial swirl injector 11 is provided so that the fuel supplied in the rotating direction and the oxidizing agent supplied in the axial direction meet and are injected in the axial direction rearward after being divided. The injection head 1 may be subjected to transverse combustion instability (transverse vibration) in which pressure fluctuation occurs in the transverse direction (shown by a dotted line in FIG. 1). However, since the coaxial swirl injector 11 mixes the fuel supplied in the turning direction and the oxidizing agent supplied in the axial direction and injects it backward, the propellant injected through the coaxial swirl injector 11 rotates and the transverse combustion unstable mode It can have weak disadvantages. However, this transverse combustion instability (transverse combustion instability mode) can be compensated for by the coaxial shear injector 12 described below.

Referring to FIG. 1, the injection head 1 includes a plurality of coaxial shearing injectors 12.

Referring to FIG. 2, the coaxial shear injector 12 is supplied in a form in which both fuel and oxidant are moved in the axial direction so that the transverse disturbance wave generated by the coaxial swirl injector 11 is attenuated, and is injected in the axial direction after splitting. It is provided as possible. The coaxial shear injector 12 receives both an oxidizing agent and a fuel in the axial direction, and injects a propellant (a mixture of an oxidizer and a fuel) in the axial direction, thereby compensating for transverse combustion instability. Referring to FIG. 2, the transverse disturbance wave may be attenuated by the propellant injected by the coaxial shear injector 1. Accordingly, the coaxial shear injector 12 may perform the role of a fluid baffle that controls combustion instability instead of a structural baffle. That is, the coaxial shear injector 12 can block a transverse alternating wave (pressure wave) generated by combustion instability. This coaxial shear injector 12 may be referred to as a coaxial shear injector 12 for a fluid baffle.

Further, referring to FIG. 1, at least some of the plurality of coaxial shear injectors 12 may be arranged to partition between one of the plurality of coaxial swirl injectors 11 and the other. In addition, some of the plurality of coaxial shear injectors 12 may be arranged to divide along the width direction of the spray head 1 in which at least a part of the plurality of coaxial swirl injectors 11 is viewed. In addition, at least some of the plurality of coaxial shear injectors 12 may be installed adjacent to each other in order to attenuate the transverse combustion unstable mode in which pressure perturbation occurs in the transverse direction.

For example, referring to FIG. 1, at least some of the plurality of coaxial shear injectors 12 may be provided in an annular shape at the center of the main injection head 1, and the rest may be provided radially around the annular shape. At this time, at least some of the plurality of coaxial swirl injectors 11 may be provided inside the annular shape, and the rest may be provided between the radial shapes.

3 is a schematic cross-sectional view of a spray head according to an embodiment of the present application in a schematic front-rear direction, and FIG. 4 is a schematic cross-sectional view of a coaxial swirl sprayer of a spray head according to an embodiment of the present application, 5 is an AA cross-sectional view of FIG. 4.

Meanwhile, referring to FIGS. 3 to 5, the coaxial swirl sprayer 11 extends in the axial direction so that the supplied oxidizing agent moves backward along the axial direction, the oxidant movement passage 111, the front end of the oxidizer movement passage 111 The oxidant supply hole 112 connected to the oxidant moving passage 111 to supply the oxidant to the side, the fuel moving passage 113 formed in a shape surrounding the oxidant moving passage 111, and the fuel moving passage 113 It is formed with respect to the side of the fuel movement passage 113 to supply fuel to the front end, and at least part of the fuel supplied to the fuel movement passage 113 is rotated in the fuel movement passage 113 in a radial or radial direction. The fuel and oxidant movement passage 111 formed in the rear of the fuel supply hole 114 and the fuel movement passage 113 and the oxidant movement passage 111 formed obliquely inclined to the fuel passage 113 and passed through the fuel movement passage 113 The passed oxidizing agent may be joined and may include a confluence portion 115 in which an injection hole 1151 is formed at a rear end. Accordingly, as described above, the coaxial swirl injector 11 includes the fuel injected through the fuel supply hole 114 along the fuel movement passage 113 (coaxial swirl injector 1 surrounding the fuel movement passage 113) The oxidizing agent injected along the oxidizing agent movement passage 111 and the oxidizing agent injected along the oxidizing agent movement passage 111 meet and break apart at the confluence part 115 while turning and entering the confluence part 115.

Referring to FIG. 5, a plurality of fuel supply holes 114 may be formed. In addition, referring to FIG. 5, the plurality of fuel supply holes 114 are consistent with one side of one side and the other side based on the radial direction so that at least some of the fuel supplied to the fuel movement passage 113 can be rotated. It can be formed in an inclined shape. In other words, referring to FIG. 5, the fuel supply hole 114 may not be formed in a radial direction, but may be formed in a shape that is consistently inclined toward one of one side and the other side based on the radial direction.

In addition, the plurality of fuel supply holes 114 may be formed at the same position with respect to the axial direction. In other words, the plurality of fuel supply holes 114 may be formed to have the same height in the front-rear direction. In addition, the plurality of fuel supply holes 114 may be formed at intervals along the circumferential direction of the fuel passage moving passage 113. The interval can be set to be constant.

In addition, referring to FIG. 3, the injection head 1 may include a fuel manifold 13 that supplies fuel through a fuel supply hole 114. The fuel manifold 13 is formed so that at least a portion of the internal space corresponds to the position where the fuel supply hole 114 is formed in the axial direction so as to be directly connected with the fuel supply hole 114 of the coaxial swirl injector 11. I can.

FIG. 6 is a schematic cross-sectional view of a coaxial shear sprayer of a spray head according to an embodiment of the present application, FIG. 7 is a cross-sectional view taken along line B-B of FIG. 6, and FIG. 8 is a cross-sectional view taken along line C-C of FIG. 6.

3, 6, and 7, the coaxial shear injector 12 includes a fuel movement passage 121 and a fuel movement passage 121 extending in the axial direction so that the supplied fuel moves backward along the axial direction. The fuel supply hole 122 connected to the fuel movement passage 121 to supply fuel to the front end side of the fuel supply hole 122 is formed extending in the axial direction so that the supplied oxidizing agent moves backward along the axial direction, the fuel movement passage 121 The oxidant moving passage 123 formed in a shape surrounding the circumference, the oxidant supply hole 124 and the fuel moving passage 121 connected to the oxidant moving passage 123 to supply the oxidant to the front end of the oxidant moving passage 123 The confluence of the fuel passing through the fuel transfer passage 121 and the oxidizing agent passing through the oxidant transfer passage 123 are joined, and the injection hole 1251 is formed at the rear end (125) may be included.

Accordingly, in the coaxial shear injector 12, the fuel and the oxidizing agent may have a mechanism in which the fuel and the oxidizing agent are divided by joining each other at the confluence portion 125 without turning.

In addition, referring to FIGS. 6 and 7, the fuel movement passage 121 through which fuel is supplied for the atomization performance of the coaxial shear injector 12 may be located at a central portion of the coaxial shear injector 12. In other words, for the atomization performance of the coaxial shear injector 12, the fuel must be supplied to the confluence 124 through the fuel movement passage 121, which is the central part of the coaxial shear injector 12, and the oxidizing agent must be supplied to the fuel movement passage ( It may have to be supplied to the oxidizing agent movement passage 123 surrounding the circumference 121. Therefore, the fuel movement passage 121 and the oxidant movement passage 123 of the coaxial shear injector 12 may have positions inverted with the fuel movement passage 113 and the oxidant movement passage 111 of the coaxial swirl injector 11. have.

The fuel supply hole 122 of the coaxial shear injector 12 is formed with respect to the side of the fuel movement passage 121 to supply fuel to the front end of the fuel movement passage 121, and the main injection head 1 is coaxial Includes a fuel manifold 13 for supplying fuel through the fuel supply hole 121 of the shear injector 12, and the fuel manifold 13 includes the fuel supply hole 122 of the coaxial shear injector 12 and In order to be directly connected, at least a portion of the inner space may be formed to correspond to a position in which the fuel supply hole 122 of the coaxial shear injector 12 is formed in the axial direction.

3, a fuel manifold 13 connected to the fuel supply hole 122 of the coaxial shear injector 12 and a fuel manifold 13 connected to the fuel supply hole 114 of the coaxial swirl injector 11 ) May be the same fuel manifold 13. That is, the injection head 1 can supply fuel to the coaxial swirl injector 11 and the coaxial shear injector 12 using the same fuel manifold 13.

In addition, referring to FIG. 6, the oxidant supply hole 124 of the coaxial shear injector 12 extends axially forward from the front end side of the oxidant supply passage 123 so as to prevent interference with the fuel manifold 13. I can. Also, referring to FIG. 8, a plurality of oxidant supply holes 124 may be formed at intervals from each other.

In summary, the injection head 1 applies a damping role for transverse mode generated during combustion instability to a fluid baffle rather than a structural baffle, while maintaining the combustion stabilization function of a conventional structural baffle. Development costs can be reduced through weight reduction of the combustor. To this end, the present injection head 1 is a fluid baffle injector, a coaxial shear sprayer 12 that is strong against transverse vibration, and a gas-centered coaxial swirl injector 11 can be applied as a main injector. Accordingly, the injection head 1 removes the baffle structure used for combustion instability control in the liquid rocket engine, and is a controllable system using a fluid baffle, that is, a main injector (coaxial swirl injector 11) that is not a structural baffle. )) and other types of fluid baffle injectors (coaxial shear injectors 12) to control pressure perturbation.

In the conventional injection head, an injector type baffle is installed. On the other hand, this injection head 1 includes a coaxial shear sprayer 12 and a coaxial swirl sprayer 11 for a fluid baffle, and the injection head 1 is an injector of a liquid rocket engine using gaseous oxidizer and liquid fuel. A fluid baffle can be used instead of a structural baffle. In other words, in the related art, a structure is forcibly inserted into the combustor to control pressure perturbation, but the injection head 1 may allow the fluid to take over its role. Accordingly, the injection head 1 has a coaxial shear sprayer 12 for a fluid baffle installed on the injection head to stabilize combustion as in a conventional injector type baffle, and reduce weight.

Combustion stability can be a very important factor in the development of liquid rocket engine combustors. The injection head 1 can be expected to obtain the same effect as the combustion stabilization of the conventional injector type baffle by applying the coaxial shearing injector 12 for fluid baffle instead of the conventional injector type baffle. In addition, the coaxial shear sprayer 1 for the fluid baffle of the injection head 1 can be easily secured in payload weight by reducing the weight of the liquid rocket engine by removing the existing structural baffle.

In addition, according to the above description, different types of injectors (coaxial swirl injector 11 and coaxial shear injector 12) may receive fuel from the same manifold 13 in the injection head 1.

On the other hand, in the manufacture of the spray head 1, the coaxial shear sprayer 12 for fluid baffle must have a different supply position from the coaxial swirl sprayer 11, so it is difficult to implement with the existing metal/cutting process, and additive processing is required. It can be implemented through

In addition, the present application may provide a liquid rocket combustor according to an embodiment of the present application. The liquid rocket combustor according to an embodiment of the present application includes the injection head 1 according to an embodiment of the present application described above. Since this has been described above, detailed descriptions are omitted.

In addition, the present application may provide a coaxial shearing injector 12 according to an embodiment of the present application. The coaxial shear injector 12 according to an exemplary embodiment of the present application may be a coaxial shear injector 12 used in the injection head 1 according to the exemplary embodiment of the present application. Since this has been described above, detailed descriptions are omitted.

The foregoing description of the present application is for illustrative purposes only, and those of ordinary skill in the art to which the present application pertains will be able to understand that it is possible to easily transform it into other specific forms without changing the technical spirit or essential features of the present application. Therefore, it should be understood that the embodiments described above are illustrative in all respects and not limiting. For example, each component described as a single type may be implemented in a distributed manner, and similarly, components described as being distributed may also be implemented in a combined form.

The scope of the present application is indicated by the claims to be described later rather than the detailed description, and all changes or modified forms derived from the meaning and scope of the claims and their equivalent concepts should be construed as being included in the scope of the present application.

1: spray head
11: Coaxial swirl sprayer
111: oxidant passage
112: oxidizing agent supply hole
113: fuel passage
114: fuel supply hole
115: confluence
1151: nozzle
12: coaxial shearing injector
121: fuel passage
122: fuel supply hole
123: oxidant passage
124: oxidizing agent supply hole
125: confluence
1251: nozzle
13: fuel manifold

Claims (15)

In the injection head of a liquid rocket combustor,
A plurality of coaxial swirl injectors provided so that the fuel supplied in the turning direction and the oxidizing agent supplied in the axial direction meet and are injected in the axial direction rearward after division; And
In order to attenuate the transverse disturbance wave generated by the coaxial swirl injector, both the fuel and the oxidizing agent are supplied in a form in which both fuel and oxidizer are moved in the axial direction, and include a plurality of coaxial shear injectors provided to be injected in the axial direction after division,
At least a portion of the plurality of coaxial shear injectors is arranged to partition between any one of the plurality of coaxial swirl injectors and the other. The method of claim 1,
The coaxial shear sprayer is to perform the role of a fluid baffle for controlling combustion instability instead of a structural baffle, injection head. delete The method of claim 1,
Some of the plurality of coaxial shear injectors are arranged to partition at least a part of the plurality of coaxial swirl injectors along the width direction of the injection head,
Another part of the plurality of coaxial shear injectors is arranged to partition at least a part of the plurality of coaxial swirl injectors along the circumferential direction of the injection head. The method of claim 4,
The injection head is provided in an annular shape at the central portion of the injection head, and the rest is provided radially around the annular shape. The method of claim 5,
At least some of the plurality of coaxial swirl injectors are provided inside the annular shape, and the rest is provided between the radial shapes, the injection head. The method of claim 1,
The coaxial swirl injector,
An oxidant movement passage extending in the axial direction so that the supplied oxidant moves backward along the axial direction;
An oxidant supply hole connected to the oxidant passage to supply an oxidant to a front end side of the oxidant passage;
A fuel movement passage formed to surround the circumference of the oxidant movement passage;
It is formed with respect to the side of the fuel movement passage to supply fuel to the front end side of the fuel movement passage, with respect to a radial direction or a radial direction so that at least a part of the fuel supplied to the fuel movement passage is rotated within the fuel movement passage A fuel supply hole formed to be obliquely inclined; And
And a confluence portion formed at the rear of the fuel movement passage and at the rear of the oxidant movement passage, where the fuel passing through the fuel movement passage and the oxidizing agent passing through the oxidant movement passage merge, and an injection hole formed at a rear end thereof, Spray head. The method of claim 7,
A plurality of the fuel supply holes are formed,
The plurality of fuel supply holes are formed in a form that is consistently inclined toward one of one side and the other side with respect to a radial direction so that at least a part of the fuel supplied to the fuel movement passage can be rotated. The method of claim 7,
The injection head includes a fuel manifold for supplying fuel through the fuel supply hole,
The fuel manifold, the injection head, so as to be directly connected to the fuel supply hole of the coaxial swirl injector, at least a portion of the inner space is formed to correspond to the position where the fuel supply hole is formed in the axial direction. The method of claim 1,
The coaxial shearing injector,
A fuel movement passage extending in the axial direction so that the supplied fuel moves backward along the axial direction;
A fuel supply hole connected to the fuel movement passage to supply fuel to a front end side of the fuel movement passage;
An oxidant movement passage extending in the axial direction so that the supplied oxidant moves backward along the axial direction, the oxidant movement passage formed in a shape surrounding the circumference of the fuel movement passage;
An oxidant supply hole connected to the oxidant passage to supply an oxidant to a front end side of the oxidant passage; And
And a confluence portion formed at the rear of the fuel movement passage and at the rear of the oxidant movement passage, where the fuel passing through the fuel movement passage and the oxidizing agent passing through the oxidant movement passage merge, and an injection hole formed at a rear end thereof, Spray head. The method of claim 10,
The fuel supply hole of the coaxial shear injector is formed with respect to a side surface of the fuel movement passage to supply fuel to the front end side of the fuel movement passage,
The injection head includes a fuel manifold for supplying fuel through a fuel supply hole of the coaxial shear injector,
The fuel manifold, so as to be directly connected to the fuel supply hole of the coaxial shear injector, at least a portion of the inner space is formed to correspond to a position in the axial direction of the fuel supply hole of the coaxial shear injector is formed, injection head. The method of claim 11,
The fuel manifold connected to the fuel supply hole of the coaxial shear injector and the fuel manifold connected to the fuel supply hole of the coaxial swirl injector are the same fuel manifold. The method of claim 11
The oxidizing agent supply hole of the coaxial shear injector extends axially forward from the front end side of the oxidizing agent movement passage so as to prevent interference with the fuel manifold. A liquid rocket combustor comprising an injection head according to claim 1. A coaxial shear sprayer used for the injection head according to claim 1.

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