KR100666161B1 - An Injector Baffle for Liquid Roket Engine - Google Patents

Abstract

The present invention relates to an injector type baffle of a liquid rocket combustor, and is installed on an injection head spray surface of the combustor, and has a self-internal cooling function under high temperature and high pressure conditions generated during combustion of a propellant in a combustion chamber, and thus does not break. The present invention relates to an injector type baffle of a combustor of a liquid rocket which has a function of injecting a liquid fuel and an oxidant and improves combustion efficiency while achieving combustion stabilization of a conventional baffle.

A first aspect of the present invention for achieving the above object is a baffle which is installed on the injection surface of the combustor injection head of the liquid rocket to partition a part of the combustion chamber, the baffle is a plurality of injecting liquid fuel and oxidant into the combustion chamber The plurality of injectors are installed to form an annular partition wall in the center of the injection head injection surface so that the injectors protrude to the injection surface of the injection head to partition a part of the combustion chamber, and the plurality of injectors are radial to the outer periphery of the annular partition wall. Injector-type baffles of a liquid rocket combustor are installed to form a bulkhead.

Liquid Rocket Engine, Rocket, Combustion Chamber, Combustion Stabilizer, Internal Cooling

Description

Injector Baffle for Liquid Rocket Combustor

1 is a conceptual cross-sectional view of a conventional liquid rocket.

2 is a conceptual cross-sectional view of a combustor of a conventional liquid rocket.

3 is a bottom view of a jet head in which a conventional baffle is installed.

Figure 4 is a bottom perspective view of the spray head is installed injector type baffle of the present invention.

5 is a bottom view of an installed jet head of the injector baffle of the present invention.

6 is an injector cross-sectional view of the injector baffle of the present invention.

Figure 7 is a block diagram of the internal cooling jacket in the injector of the injector type baffle of the present invention.

8 is an enlarged cross-sectional view of a vortexer in the injector of the injector type baffle of the present invention.

* Description of the main parts of the drawings *

1: Thrust 10: Combustor 30: Nozzle

40: injection head 41: injection head injector 42: oxidant injector

42a: oxidant injector 42b: oxidant supply pipe 43: liquid fuel injector

43a: liquid fuel injection hole 43b: liquid fuel supply pipe 45: injection surface

47: orifice 48: oxidant manifold

50: combustion chamber 51: combustion wall

60: baffle 61: injector 62: casing

63: internal cooling jacket 63a: cooling projection 63b: oxidant flow path

64: vortex stage 64a: turning flow generation port 64b: flow path

64c: diffuser

The present invention relates to an injector type baffle of a liquid rocket combustor, and is installed on an injection head spray surface of the combustor, and has a self-internal cooling function under high temperature and high pressure conditions generated during combustion of a propellant in a combustion chamber, and thus does not break. The present invention relates to an injector type baffle of a combustor of a liquid rocket which has a function of injecting a liquid fuel and an oxidant and improves combustion efficiency while achieving combustion stabilization of a conventional baffle.

Generally, the liquid rocket engine is composed of a supply part 2 and a thrust part 1 as shown in FIG. 1.

The supply unit 2 is formed by connecting the fuel tank 21 and the oxidant tank 22 to the pump 23 composed of the fuel pump 23a and the oxidant pump 23b by pipes 24, respectively.

The thrust part 1 is composed of a combustor 10 for injecting and combusting fuel and oxidant supplied from the pump 23, and a nozzle 30 for converting the thermochemical energy of the burned propellant into propulsion force.

In particular, the combustor 10, as shown in Figure 2, the injection head 40 for injecting the liquid fuel and oxidant supplied from the fuel and oxidant pump 23 into the combustor 10 through a plurality of injectors 41 ), An ignition source (not shown) for igniting the mixed fuel and oxidant injected through the injector 41 of the injection head 40, and a combustion wall 51 surrounding the outer circumferential surface of the injection head 40. It is formed of a combustion chamber 50, the rear end is connected to the nozzle 30, and the baffle 6 is installed to partition a portion of the combustion chamber 50 on the injection surface 45 of the injection head (40). .

Since the conventional liquid rocket obtains a propulsion force by injecting a high temperature and high pressure gas generated by burning a propellant (a mixture of fuel and an oxidant) injected through the injector 41 through the nozzle 30 to obtain a propulsion force inside the combustion chamber 50. In high temperature, high pressure environment.

As such, vibration occurs due to atomization characteristics of the propellant in the combustion process of the combustor of the liquid rocket, and thus combustion instability occurs.

In order to prevent combustion instability due to vibration generated in the combustion process, a baffle is provided with an annular partition wall and a plurality of radial partition walls outside the annular partition wall in the center of the conventional injection head 40. By configuring (6), vibrations generated in the combustion process are attenuated to induce combustion stabilization of the propellant.

However, since the rear end portion of the baffle 6 is close to the location of the ignition point of the propellant, it becomes the environment of the largest high temperature and high pressure at the portion thereof, so that the baffle 6 is not damaged, as shown in FIG. A separate cooling device 46 was provided around the baffle 6, and only the liquid fuel was injected into the baffle 6 to cool the baffle 6.

This causes a problem that the combustion efficiency is lowered because the complete combustion is not achieved in the combustor by the liquid fuel injected into the baffle (6).

Accordingly, the present invention has been made to solve the above problems, the baffle installed in the injection head of the combustor to have the injection function of the fuel and oxidant to increase the combustion efficiency, and the baffle itself having the injection function has an internal cooling function It is to provide an injector-type baffle that does not break in an environment of high temperature and high pressure in the combustion chamber.

A first aspect of the present invention for achieving the above object is a baffle which is installed on the injection surface of the combustor injection head of the liquid rocket to partition a part of the combustion chamber, the baffle is a plurality of injecting liquid fuel and oxidant into the combustion chamber The plurality of injectors are installed to form an annular partition wall in the center of the injection head injection surface so that the injectors protrude to the injection surface of the injection head to partition a part of the combustion chamber, and the plurality of injectors are radial to the outer periphery of the annular partition wall. Injector-type baffles of a liquid rocket combustor are installed to form a bulkhead.

In addition, the second aspect of the present invention for achieving the above object is the first feature, the injector is a casing is provided on the injection surface of the injection head of the other end in the shape of a circular cylinder; It is installed in the casing and the other end of the outer peripheral surface becomes a flow path of the liquid fuel supplied through the orifice in the injection head, a spiral cooling projection is formed on the outer peripheral surface so that the liquid fuel is rotated and sprayed from one end of the casing, the injection is in the inner circumference An internal cooling jacket connected with the oxidant manifold in the head to form an oxidant flow path for moving the oxidant; It is installed at one end of the oxidant flow path of the internal cooling jacket and a plurality of swing flow generating holes are formed on the outer circumference of the other end so that the oxidant swings and flows, and a flow path communicating with the swing flow generating hole is formed at the inner circumference and a diffusion hole is formed at one end thereof. It is in the injector type baffle of the liquid rocket combustor;

Further, a third aspect of the present invention for achieving the above object is in the injector type baffle of the liquid rocket combustor of the second aspect, wherein the cooling projection of the internal cooling jacket has a rectangular cross section.

In addition, a fourth aspect of the present invention for achieving the above object is the injector-type baffle of the liquid rocket combustor of the second feature, wherein the casing is made of a copper alloy material.

In addition, a fifth aspect of the present invention for achieving the above object is the injector-type baffle of the liquid rocket combustor made of a stress material in the second aspect, the internal cooling jacket.

Hereinafter, a configuration of the present invention will be described with reference to FIGS. 4 to 8.

The configuration of the injector type baffle of the liquid rocket combustor of the present invention is installed in the injection surface 45 of the injection head 40 of the combustor 10 of the liquid rocket as shown in FIGS. In the baffle to be partitioned, the baffle 60 is provided with a plurality of injectors 61 for injecting the liquid fuel and the oxidant into the combustion chamber so as to protrude to the injection surface 45 of the injection head 40, a part of the combustion chamber 50 The plurality of injectors 61 are installed to form an annular partition wall in the center on the injection head spraying surface 45 so as to define a plurality of injectors 61, and the plurality of injectors 61 are formed to form a radial partition wall outer periphery of the annular partition wall. will be.

In particular, the injector 61 is configured to protrude on the spray surface 45 of the spray head 40 as shown in FIG. 6, and the known spray head 40 is supplied from the oxidant pump 23b. An oxidant injector 42 which receives the oxidant supplied through the oxidant supply pipe 42b and injects the oxidant into the combustion chamber 50 through the oxidant injection hole 42a located in the injection surface 45 of the injection head, and the oxidant injector 42. Liquid having a liquid fuel injection hole (43a) which is installed on the outer periphery and is supplied from the liquid fuel supply pipe (43b) to be supplied from the liquid fuel supply pipe (43b) to be injected from the outer circumference of the oxidant injection hole to be mixed in the combustion chamber A plurality of injection head injectors 41 formed of the fuel injectors 43 are embedded.

The injector 61 has a circular cylinder shape, the other end of which is installed on the injection surface 45 of the injection head and is made of a copper alloy material having high thermal conductivity, thereby cooling the internal cooling jacket 63 to explain the heat of combustion in the combustion chamber 50. A casing 62 which delivers the projection 63a to the flowing liquid fuel to cool the baffle 60;

As shown in Figure 6 and 7, is made of a stainless material, is installed in the casing 62 and the other end of the outer peripheral surface becomes a flow path of the liquid fuel supplied through the orifice 47 in the injection head 40, on the outer peripheral surface A spiral cooling projection (63a) is formed in the liquid fuel is rotated to be injected from one end of the casing 62, and the cooling projection (63a) is formed in a cross-sectional shape of the cooling projection (63a) An oxidant flow path 63b for smoothly absorbing the combustion heat transmitted by the casing 62 and the oxidant manifold 48 in the injection head 40 to move the oxidant is formed on the inner circumference thereof. Internal cooling jacket (63),

6 and 8, the oxidant flow path 63b of the internal cooling jacket 63 is installed at one end, and a plurality of swing flow generating holes 64a are formed at the outer circumference of the other end to allow the oxidant to swing and flow. A flow path 64b communicating with the swing flow generating port 64a is formed, and a diffusion hole 64c is formed at one end thereof, and is composed of a vortex device 64 for spraying the oxidizing agent to move.

In particular, the swirl flow generating port 64a induces oxidant moving through the oxidant flow path 63b to swing in the flow path 64b formed at the center of the circumference, as shown in View A and View B of FIG. In (64c) turn to flow and spray.

Injector type baffle of the liquid rocket combustor of the present invention configured as described above

The injection head injector 41 of the combustor 10 receives the liquid fuel and the oxidant from the fuel and the oxidant pump 23 when the liquid rocket is in operation, thereby dispensing the liquid fuel and the oxidant into the liquid fuel injection hole 43a and the oxidant, respectively. It is injected into the combustion chamber 50 through the hole 42a and combusts, and at the same time, the injector 61 of the injector type baffle 60 according to the present invention is supplied from the orifice 47 provided in the injection head 40. Is rotated between the cooling projection (63a) of the inner cooling jacket 63 and the inner surface of the casing 62 and is injected into the combustion chamber 50 at a predetermined angle from one end of the casing (62).

In addition, the oxidant supplied from the oxidant manifold 48 of the injection head 40 is supplied to the oxidant flow path 63b, which passes through the swirl flow generator 64a of the vortex 64 and flow path 64b. It is injected into the combustion chamber 50 through the diffusion hole 63c while turning flow in ().

As such, the propellant (mixed with the oxidant and the liquid fuel is injected from the injector and simultaneously mixed) injected from the injector 61 is ignited and burned by the ignition source to generate a propulsion force. Injecting the propellant in the same way as the injector 41 of the combustion, so that the combustion source is separately combusted in the combustion space partitioned by the baffle (60) to combine the combustion efficiency of the conventional baffle (6) Higher than the combustor.

In addition, the combustion heat is transmitted to the casing 62 of the injector 61 is transferred between the casing 62 and the cooling projection 63a of the internal cooling jacket 63 is transferred to the liquid fuel flowing through the injector of the present invention, so The mold baffles are not broken by the heat of combustion.

As described above, since the baffle has an injection function, the combustion sources that are individually combusted in the space partitioned by the baffle are combined into one combustion source, thereby increasing the combustion efficiency, and the heat of the baffle itself is the internal heat of the liquid. Since it has a cooling function to cool the delivery to the fuel has an effect that does not break in the environment of high temperature and high pressure in the combustion chamber.

Claims (5)

In the baffle (60) which is installed on the injection surface (45) of the combustion head (40) and the injection head (40) of the liquid rocket, The baffle 60 is installed so that a plurality of injectors 61 for injecting liquid fuel and oxidant into the combustion chamber protrude on the injection surface 45 of the injection head 40 to partition a portion of the combustion chamber 50. The injector 61 is installed to form an annular partition wall in the center portion on the injection head injection surface 45, and a plurality of injectors 61 are installed to form a radial partition wall outer periphery of the annular partition wall, The injector 61 of the injector type baffle of the liquid rocket combustor, characterized in that the injector 61 is provided with an internal cooling jacket 63 formed with a spiral cooling projection 63a for moving the oxidant therein and turning the liquid fuel on the outer circumferential surface thereof. . The method of claim 1, The internal cooling jacket 63 is installed in a circular casing 62 provided on the spray surface 45 of the spray head, and is orifice 47 in the spray head 40 by the spiral cooling projection 63a on the outer circumferential surface. The liquid fuel supplied to the outer circumferential surface is rotated to be injected from one end of the casing 62, and an oxidant flow path 63b connected to the oxidant manifold 48 in the injection head 40 to move the oxidant is provided on the inner circumference. Formed, One end of the oxidant flow path 63b of the internal cooling jacket 63 is provided with a vortex 64, and the vortex 64 is formed with a plurality of swirl flow generating holes 64a formed at the outer circumference of the other end thereof. The liquid rocket combustor, characterized in that the swing flow, and the inner circumference is formed with a flow path (64b) in communication with the swing flow generating port (64a), the diffusion hole (64c) is injected into one end of the swing oxidizing agent Injector type baffle. The method of claim 2, Cooling projection (63a) of the internal cooling jacket (63) is an injector type baffle of a liquid rocket combustor, characterized in that the cross-sectional shape. The method of claim 2, The casing 62 is an injector type baffle of a liquid rocket combustor, characterized in that the copper alloy material. The method of claim 2, The internal cooling jacket 63 is an injector type baffle of a liquid rocket combustor, characterized in that it is made of a stress material.

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