Coating gas manufacturing chamber

Abstract

A coating gas manufacturing chamber capable of improving process quality and process efficiency by improving the structure is disclosed. The disclosed coating gas manufacturing chamber is, It includes: a housing having an inlet formed on the side for the inflow of carrier gas; a partition plate formed above the inlet inside the housing and partitioning the internal space of the housing; a gas distribution chamber formed below the partition plate through which the carrier gas introduced through the inlet flows; a gas conduit section equipped with a plurality of gas conduits formed penetrating the partition plate; and a doner case mounted in a mounting space formed by the gas conduit section and filled with coating powder and a catalyst.

Description

Technology Field

[0001] The present invention relates to a coating gas manufacturing chamber for producing a coating gas that coats the interior of a blade with a complex shape. Background Technology

[0003] A turbine is a mechanical device that generates rotational force through impulse or reaction force by utilizing the flow of a compressible fluid, such as steam or gas; examples include steam turbines that use steam and gas turbines that use high-temperature combustion gases.

[0004] Among these, the gas turbine is largely composed of a compressor, a combustor, and a turbine. The compressor is equipped with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged within the compressor housing.

[0005] The combustion device generates high-temperature, high-pressure combustion gas by supplying fuel to the compressed air compressed by the compressor and igniting it with a burner.

[0006] The turbine has multiple turbine vanes and turbine blades arranged alternately within the turbine housing. Additionally, a rotor is positioned to penetrate the center of the compressor, combustor, turbine, and exhaust chamber.

[0007] The above rotor is rotatably supported at both ends by bearings. Additionally, a plurality of discs are fixed to the rotor, and each blade is connected to them, while a drive shaft, such as that of a generator, is connected to the end on the exhaust chamber side.

[0008] Since these gas turbines do not have a reciprocating mechanism like the piston of a four-stroke engine, there are no mutual friction parts like piston-cylinder, so the consumption of lubricating oil is extremely low, and the amplitude characteristic of reciprocating machines is greatly reduced, and high-speed motion is possible.

[0009] To briefly explain the operation of a gas turbine, air compressed by a compressor is mixed with fuel and combusted to produce high-temperature combustion gases, which are then injected toward the turbine. As the injected combustion gases pass through the turbine vanes and blades, they generate rotational force, causing the rotor to rotate. Prior art literature

[0011] Korean Registered Patent No. 10-2252487 (Jig for coating gas turbine rotor blades) The problem to be solved

[0012] The present invention aims to provide a coating gas manufacturing chamber capable of improving process quality and process efficiency by improving the structure. means of solving the problem

[0014] A coating gas manufacturing chamber according to an embodiment of the present invention is,

[0015] It includes: a housing having an inlet formed on the side for the inflow of carrier gas; a partition plate formed above the inlet inside the housing and partitioning the internal space of the housing; a gas distribution chamber formed below the partition plate through which the carrier gas introduced through the inlet flows; a gas conduit section equipped with a plurality of gas conduits formed penetrating the partition plate; and a doner case mounted in a mounting space formed by the gas conduit section and filled with coating powder and a catalyst.

[0016] In a coating gas manufacturing chamber according to an embodiment of the present invention, the housing may be formed of a graphite material.

[0017] In a coating gas manufacturing chamber according to an embodiment of the present invention, a partition plate divides the internal space of a housing into a gas distribution chamber and a reaction chamber, and the reaction chamber is a space where a coating powder vaporized by heat reacts with a carrier gas.

[0018] In a coating gas manufacturing chamber according to an embodiment of the present invention, a plurality of gas conduits may be formed radially with respect to the center of a partition plate.

[0019] In a coating gas manufacturing chamber according to an embodiment of the present invention, a plurality of gas conduits form a plurality of gas conduit lines, and a mounting space may be formed between one gas conduit line and an adjacent gas conduit line.

[0020] In a coating gas manufacturing chamber according to an embodiment of the present invention, the shape of the donor case can be determined according to the shape of the mounting space.

[0021] In a coating gas manufacturing chamber according to an embodiment of the present invention, the carrier gas is hydrogen gas, and the coating powder may be aluminum or aluminum as the main component.

[0023] Specific details of embodiments according to various aspects of the present invention are included in the following detailed description. Effects of the invention

[0025] According to an embodiment of the present invention, the structure of the coating gas manufacturing chamber can be improved to enhance process quality and process efficiency. Brief explanation of the drawing

[0027] FIG. 1 is a perspective view showing a gas turbine according to one embodiment of the present invention with a portion cut away. FIG. 2 is a cross-sectional view showing the schematic structure of a gas turbine according to one embodiment of the present invention. Figure 3 is a diagram illustrating a method for coating the inside of a blade. FIG. 4 is a perspective view showing a coating gas manufacturing chamber according to the prior art. FIG. 5 is a perspective view showing a coating gas manufacturing chamber according to one embodiment of the present invention. FIG. 6 is a perspective view showing the state in which the donner case is removed from FIG. 5. Figure 7 is a cross-sectional view taken from the AA' line of Figure 6. FIG. 8 is a perspective view showing the state in which one of the donner cases in FIG. 5 has been removed. Specific details for implementing the invention

[0028] The present invention is capable of various modifications and may have various embodiments, and specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, and it should be understood that it includes all modifications, equivalents, and substitutions that fall within the spirit and scope of the invention.

[0029] The terms used in this invention are used merely to describe specific embodiments and are not intended to limit the invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In this invention, terms such as "comprising" or "having" are intended to indicate the existence of the features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, and should be understood as not precluding the existence or addition of one or more other features, numbers, steps, actions, components, parts, or combinations thereof.

[0030] Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. In this case, identical components in the attached drawings are indicated by the same reference numerals whenever possible. Furthermore, detailed descriptions of known functions and configurations that may obscure the essence of the present invention will be omitted. For the same reason, some components in the attached drawings have been exaggerated, omitted, or schematically illustrated.

[0032] FIG. 1 is a perspective view showing a gas turbine according to an embodiment of the present invention with a portion cut away, and FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.

[0033] As illustrated in FIG. 1, a gas turbine (1000) according to one embodiment of the present invention includes a compressor (1100), a combustor (1200), and a turbine (1300). The compressor (1100) has a plurality of blades (1110) installed radially. The compressor (1100) rotates the blades (1110), and air moves as it is compressed by the rotation of the blades (1110). The size and installation angle of the blades (1110) may vary depending on the installation location. In one embodiment, the compressor (1100) is connected directly or indirectly to the turbine (1300) so that it can receive a portion of the power generated from the turbine (1300) and use it for the rotation of the blades (1110).

[0034] The air compressed in the compressor (1100) moves to the combustor (1200). The combustor (1200) includes a plurality of combustion chambers (1210) arranged in an annular shape and a fuel nozzle module (1220).

[0035] As illustrated in FIG. 2, a gas turbine (1000) according to one embodiment of the present invention is provided with a housing (1010), and a diffuser (1400) is provided at the rear of the housing (1010) to discharge combustion gas that has passed through the turbine. Then, a combustor (1200) is disposed in front of the diffuser (1400) to receive compressed air and combust it.

[0036] When described based on the direction of air flow, a compressor (1100) is located on the upstream side of the housing (1010), and a turbine (1300) is positioned on the downstream side. Additionally, a torque tube (1500) is positioned between the compressor (1100) and the turbine (1300) as a torque transmission member that transmits the rotational torque generated by the turbine (1300) to the compressor (1100).

[0037] The compressor (1100) is equipped with a plurality (e.g., 14) of compressor rotor disks (1120), and each of the compressor rotor disks (1120) is connected by a tie rod (1600) so as not to be separated in the axial direction.

[0038] Specifically, each compressor rotor disk (1120) is aligned along the axial direction with the tie rod (1600) forming the rotation axis passing approximately through the center. Here, each adjacent compressor rotor disk (1120) is positioned so that the opposing surfaces are compressed by the tie rod (1600), making relative rotation impossible.

[0039] A plurality of blades (1110) are radially connected to the outer surface of the compressor rotor disk (1120). Each blade (1110) is equipped with a dovetail portion (1112) and is connected to the compressor rotor disk (1120).

[0040] Between each rotor disk (1120), a vane (not shown) is positioned and fixed to the housing. Unlike the rotor disk, the vane is fixed so as not to rotate and serves to align the flow of compressed air passing through the blade (1110) of the compressor rotor disk (1120) and guide the air to the blade (1110) of the rotor disk (1120) located downstream.

[0041] The fastening method of the dovetail section (1112) is of the tangential type and the axial type. This can be selected according to the required structure of the commercially available gas turbine and can have a commonly known dovetail or fir-tree shape. In some cases, the blade can be fastened to the rotor disk using a fastening device other than the above shapes, such as a key or a bolt.

[0042] A tie rod (1600) is positioned to penetrate the center of a plurality of compressor rotor disks (1120) and turbine rotor disks (1320), and the tie rod (1600) may consist of one or more tie rods. One end of the tie rod (1600) is fastened within the compressor rotor disk located at the uppermost side, and the other end of the tie rod (1600) is fastened by a fixing nut (1450).

[0043] Since the shape of the tie rod (1600) can be formed in various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 2. That is, as illustrated, it may have a shape where one tie rod penetrates the center of the rotor disk, or a shape where multiple tie rods are arranged circumferentially, and a combination of these is also possible.

[0044] Although not shown in the drawings, a vane acting as a guide vane may be installed at the next position after the diffuser in the compressor of a gas turbine to match the flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the fluid pressure, and this is called a deswirler.

[0045] In the combustor (1200), the introduced compressed air is mixed with fuel and combusted to produce high-energy, high-temperature, high-pressure combustion gas, and the combustion gas temperature is raised to a heat resistance limit that the combustor and turbine parts can withstand through an isostatic combustion process.

[0046] Combustors constituting the combustion system of a gas turbine may be arranged in multiple numbers within a housing formed in a cell shape and are composed of a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a transition piece that serves as a connection part between the combustor and the turbine.

[0047] Specifically, the liner provides a combustion space where fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and combusted. This liner may include a flame chamber that provides a combustion space where the fuel mixed with air is combusted, and a flow sleeve that surrounds the flame chamber and forms an annular space. Additionally, a fuel nozzle is connected to the front end of the liner, and a spark plug is connected to the side wall.

[0048] Meanwhile, a transition piece is connected to the rear end of the liner to allow combustion gases, combusted by a spark plug, to be sent to the turbine side. The outer wall of this transition piece is cooled by compressed air supplied from the compressor to prevent damage caused by the high temperature of the combustion gases.

[0049] To this end, the transition piece is provided with cooling holes to allow air to be injected into the interior, and the compressed air cools the main body inside through the holes before flowing toward the liner.

[0050] Cooling air that has cooled the aforementioned transition piece flows through the annular space of the liner, and compressed air from the outside of the flow sleeve can collide with the outer wall of the liner by being supplied as cooling air through cooling holes provided in the flow sleeve.

[0051] Meanwhile, the combustion gas from the combustion chamber is supplied to the turbine (1300). As the combustion gas expands, it collides with the rotating blades of the turbine, generating a reaction force and causing rotational torque. This rotational torque is transmitted to the compressor via the torque tube (1500), and any power exceeding the power required to drive the compressor is used to drive a generator, etc.

[0052] The turbine (1300) is basically similar in structure to a compressor. That is, the turbine (1300) is also equipped with a plurality of turbine rotor disks (1320) similar to the compressor rotor disks of the compressor. Accordingly, the turbine rotor disks (1320) also include a plurality of turbine blades (1310) arranged radially. The turbine blades (1310) can also be connected to the turbine rotor disks (1320) in a manner such as a dovetail. In addition, turbine vanes fixed to a housing are provided between the blades (1310) of the turbine rotor disks (1320) to guide the flow direction of the combustion gas passing through the blades.

[0054] Meanwhile, a cooling channel is formed inside the turbine blade (1310) through which a cooling fluid flows to cool the turbine blade. The cooling channel is formed in a complex shape throughout the interior of the turbine blade to cool the turbine blade (1310) evenly. An oxidation-resistant coating layer is formed on the inner wall of this cooling channel to protect the inner wall.

[0055] Figure 3 is a diagram illustrating a method for coating the inside of a blade.

[0056] Referring to FIG. 3, conventionally, a turbine blade (1310) is fixed to a fixed jig (J), and then a coating gas stream (CF) is formed inside the turbine blade (1310) to form a coating layer on the inner wall of the cooling channel inside the turbine blade (1310). At this time, the coating gas is generated in a coating gas manufacturing chamber and supplied into the interior of the turbine blade (1310) through an internal conduit formed in the fixed jig (J) connected to the coating gas manufacturing chamber.

[0057] FIG. 4 is a perspective view illustrating a coating gas manufacturing chamber according to the prior art. Here, the prior art is merely a description for explaining the differences from the present invention and does not refer to a known technology widely known to those skilled in the art.

[0058] Referring to FIG. 4, a coating gas manufacturing chamber (10) according to the prior art comprises a housing (11) having an internal space, a radial gas conduit (12) installed inside the housing (11) and having a plurality of gas supply holes (12a) formed therein, and a gas supply pipe (13) for supplying carrier gas to the gas conduit (12).

[0059] A radial gas conduit (12) is formed at a predetermined height from the bottom surface of the housing (11), and the upper part of the housing (11) is closed by a trapezoidal cover (not shown) that is narrow at the top and wide at the bottom, and an outlet for discharging coating gas is formed in the cover by a fixing jig (J).

[0060] After the operator pours the coating powder (P) and catalyst together onto the bottom surface of the housing (11) and applies heat to vaporize the coating powder, the vaporized coating powder (P) is supplied into the interior of the turbine blade (1310) via the fixed jig (J) by the carrier gas supplied through the gas supply hole (12a).

[0061] In the coating gas manufacturing chamber (10) according to this conventional technology, since the coating powder (P) and catalyst are filled in a single space (bottom of the housing (11)), there is a problem that managing the coating powder (P) and catalyst is inconvenient. That is, there is a problem that the work of uniformly distributing the coating powder (P) and catalyst throughout the entire space is required.

[0062] In addition, there is a problem in that it is difficult to manage the quantitative amount of coating powder (P) and catalyst input, as the coating performance decreases after a certain period of time has elapsed after pouring into the bottom surface of the housing (11), and the used coating powder (P) and catalyst must be scooped out and removed and new coating powder (P) and catalyst must be filled.

[0063] In addition, the reaction occurs at a high temperature of approximately 1100°C, and there is a concern that the shape of the housing (11) may deform during long-term use. If the shape of the housing (11) deforms, the entire thing must be repaired or replaced, which increases the process cost.

[0064] Accordingly, the present invention proposes a coating gas manufacturing chamber with a new structure capable of solving these problems, thereby enabling the improvement of process quality and process efficiency.

[0066] FIG. 5 is a perspective view showing a coating gas manufacturing chamber according to one embodiment of the present invention, FIG. 6 is a perspective view showing the state in which the donor case is removed from FIG. 5, FIG. 7 is a cross-sectional view viewed from the AA' line of FIG. 6, and FIG. 8 is a perspective view showing the state in which one of the donor cases is removed from FIG. 5.

[0067] Referring to FIGS. 5 to 8, a coating gas manufacturing chamber (100) according to one embodiment of the present invention includes a housing (110), a partition plate (120), a gas conduit section (130), and a doner case (140).

[0068] The housing (110) is formed in a predetermined shape, for example, a cylindrical shape, and has an internal space. An inlet (111) for introducing a carrier gas is formed on the side of the housing (110). The carrier gas is an inert gas lighter than air, for example, hydrogen (H2) gas.

[0069] The housing (110) is formed of graphite material. The melting point of graphite is approximately 3652 to 3697°C. Therefore, the housing (110) is heat-resistant to approximately 1100°C, at which the coating powder (P) vaporizes, so there is no risk of the shape of the housing (110) being deformed even after long-term use.

[0070] A partition plate (120) is formed inside the housing (110) and divides the internal space of the housing (110) into a gas distribution room (R1) and a reaction room (R2). The partition plate (120) is formed above the inlet (111) inside the housing.

[0071] The gas distribution chamber (R1) is formed at the bottom of the partition plate (120), and carrier gas introduced through the inlet (111) flows through it. The carrier gas is supplied from the gas distribution chamber (R1) to the reaction chamber (R2) through the gas conduit (131). The reaction chamber (R2) is formed at the top of the partition plate (120) and is a space where the coating powder vaporized by heat reacts with the carrier gas.

[0072] The coating powder that reacts with the carrier gas in the reaction chamber (R2) is discharged through an outlet (not shown) formed in a cover (not shown) covering the upper part of the housing (110), and then supplied into the interior of the turbine blade (1310) via a fixed jig (J).

[0073] The gas conduit section (130) includes a plurality of gas conduits (131) formed by vertically penetrating the partition plate (120). The plurality of gas conduits (131) may be formed radially with respect to the center of the partition plate (120).

[0074] Multiple gas conduits (131) can form multiple gas conduit lines. The drawing illustrates that multiple gas conduits (131) form three lines (L1, L2, L3). Between one gas conduit line (L1) formed by some of the multiple gas conduits (131) and the adjacent gas conduit line (L2), a mounting space (R3) is formed in which a donner case (140) can be mounted.

[0075] The interior of the donner case (140) is filled with coating powder (P) and a catalyst. The coating powder (P) is a powder of an oxidation-resistant material, for example, aluminum (Al) or a powder of a composition having aluminum as the main component. And, the catalyst may be aluminum fluoride.

[0076] The donor case (140) is formed in a shape that can be mounted in the mounting space (R3) formed by the gas conduit section (130). In the drawing, the donor case (140) is exemplified as being formed in the shape of an equilateral triangular prism with an open top, but the shape of the donor case (140) is not limited thereto. The shape of the donor case (140) can be determined according to the shape of the mounting space (R3). For example, if the gas conduit line is formed in four parts, the mounting space (R3) can be eight parts, and in this case, the shape of the donor case (140) is formed in the shape of an isosceles triangular prism, and the donor cases (140) form an octagonal shape.

[0078] Next, the operation process of a coating gas manufacturing chamber according to one embodiment of the present invention configured as described above will be explained.

[0079] Each of the multiple donor cases (140) is filled with coating powder (P) and catalyst in a certain ratio, and then placed in the mounting space (R3). Of course, each of the multiple donor cases (140) can be placed in the mounting space (R3), and then filled with coating powder (P) and catalyst in a certain ratio.

[0080] A high temperature of approximately 1100°C is applied to vaporize the coating powder (P), and a carrier gas is introduced through the inlet (111). The introduced carrier gas is supplied from the gas distribution room (R1) to the reaction room (R2) through the gas pipe (131), reacts with the vaporized coating powder, is discharged through the outlet (not shown), and then passes through the fixed jig (J) to be supplied into the interior of the turbine blade (1310).

[0082] According to the coating gas manufacturing chamber of one embodiment of the present invention as described above, the housing (110) is formed of a graphite material, so there is no risk of deformation of its shape even after long-term use. In addition, among the plurality of donor cases (140), it is sufficient to repair / replace only the donor case (140) that has a problem, thereby reducing maintenance and management costs. Furthermore, since the coating powder (P) and catalyst are filled and used separately for each donor case (140), the management of the coating powder (P) and catalyst is easy. Therefore, the overall process quality and process efficiency can be improved.

[0084] Although an embodiment of the present invention has been described above, those skilled in the art may modify and change the present invention in various ways by adding, changing, deleting, or adding components, etc., without departing from the spirit of the present invention as described in the claims, and such modifications and changes are also to be included within the scope of the rights of the present invention. Explanation of the symbols

[0086] 1100 : Compressor 1200 : Combustor 1300 : Turbine 1310 : Turbine blade 100 : Coating gas manufacturing chamber 110 : Housing 120 : Partition board 130: Gas pipeline section 140: Doner case

Claims

Claim 1 A coating gas manufacturing chamber comprising: a housing made of graphite material having an inlet formed on the side for the introduction of a carrier gas and an outlet formed on the top; a partition plate formed above the inlet within the housing and partitioning the internal space of the housing; a gas distribution chamber formed below the partition plate and through which the carrier gas introduced through the inlet flows; a reaction chamber formed above the partition plate and through which a coating powder vaporized by heat reacts with the carrier gas; a gas conduit section having a plurality of gas conduits that protrude into the reaction chamber by vertically penetrating the partition plate and are formed radially with respect to the center of the partition plate to form a plurality of gas conduit lines; and a donner case that is replaceably mounted in a mounting space formed between one of the plurality of gas conduit lines and an adjacent gas conduit line; wherein the carrier gas of the gas distribution chamber is supplied to the reaction chamber through the gas conduit and reacts with the coating powder vaporized in the donner case and is discharged through the outlet. Claim 2 delete Claim 3 delete Claim 4 delete Claim 5 delete Claim 6 A coating gas manufacturing chamber according to claim 1, wherein the shape of the donor case is determined according to the shape of the mounting space. Claim 7 A coating gas manufacturing chamber according to claim 1 or claim 6, wherein the carrier gas is hydrogen gas and the coating powder is a composition comprising aluminum or aluminum.

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