Gas turbine device and processing method

Abstract

The present invention relates to the technical field of gas turbines, and more specifically, to a gas turbine device and a processing method. The device comprises: a shell assembly and a rotating assembly. The shell assembly comprises a first shell unit, a second shell unit, a third shell unit, a wing unit, and an air supply unit. The air supply unit comprises an air supply pipe and an air supply boss. The second wall body separates the hollow chamber of the first wall body into a first chamber and a second chamber. The first chamber is connected to the third chamber. The second chamber is connected to the fourth chamber. The air supply pipe is connected to the first chamber. The first cooling chamber is connected to the interval area between the first shell unit and the second shell unit through its opening. The first chamber is connected to the first cooling chamber through a first channel. The second chamber is connected to the first cooling chamber through a second channel. The second chamber is connected to the external space of the first shell unit through a third channel. In this way, the problem of how to reduce the influence of high-temperature gas on the internal temperature of the shell assembly is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine device and a processing method thereof. Background Art

[0002] A gas turbine is a device that uses high-temperature, high-pressure gas to drive the turbine to rotate, thereby converting the chemical energy of the fuel into mechanical energy. It has a wide range of applications in many fields, including power generation, ship power, industrial drive, etc. The working principle of a gas turbine involves compressing air, mixing it with fuel and burning it, and then expanding it through the turbine to do work, driving the turbine to rotate and achieve energy conversion. Bearings are key components that support the rotor during the operation of a gas turbine engine. In order to ensure that the bearings can work for a long time, lubricating oil is usually used for lubrication and cooling. However, when using lubricating oil to lubricate and cool the bearings, it is necessary to consider sealing the lubricating oil in the bearing cavity to prevent lubricating oil leakage.

[0003] Gas turbines usually include a casing assembly, a rotor, and bearings. Introducing high-pressure cold air from the compressor into the bearing cavity to seal the lubricating oil is a commonly used method. The bearings in gas turbine engines are usually located at the end of the rotor. The high-pressure cold air from the compressor outlet usually enters the casing assembly through an external pipeline, and then passes through a series of flow channels in adjacent parts to finally reach the bearing cavity. However, the outer casing of the parts through which the high-pressure cold air from the compressor outlet flows will come into contact with the high-temperature combustion gas during the operation of the gas turbine engine. The high-temperature combustion gas will increase the temperature of the high-pressure cold air in the parts through the heat conduction effect, thereby affecting the cooling effect of the high-pressure cold air on the turbine disc and the sealing effect on the bearing cavity. As a result, insufficient bearing lubrication will accelerate bearing wear, and contaminants entering the bearings may also cause bearing damage, reducing the performance and production efficiency of the gas turbine. Summary of the invention

[0004] In order to solve the problem of how to reduce the influence of high-temperature combustion gas on the internal temperature of a casing component, the present invention provides a gas turbine device and a processing method.

[0005] In a first aspect, the present invention provides a gas turbine device, the gas turbine device comprising:

[0006] A shell assembly, the shell assembly includes a first shell unit, a second shell unit, a third shell unit, a wing unit, and an air supply unit; the second shell unit is arranged inside the first shell unit; the third shell unit is arranged inside the second shell unit; the first shell unit, the second shell unit, and the third shell unit are arranged in sequence at intervals; one end of the wing unit is fixedly connected to the inner wall of the first shell unit, and the other end is fixedly connected to the outer wall of the second shell unit; one end of the third shell unit is open and the other end is closed; the air supply unit includes an air supply pipe and an air supply boss; the air supply boss includes a first wall body, a second wall body, a first ring part, a second ring part, a first channel, a second channel, and a third channel; one side of the first wall body is fixedly connected to the inner wall of the second shell unit, and the other side is fixedly connected to the outer wall of the second shell unit. The outer side wall of the third shell unit is fixedly connected; the side wall of the first wall body close to the third shell unit and the outer side wall of the third shell unit surround to form a hollow chamber; the second wall body is arranged in the hollow chamber of the first wall body at intervals; the second wall body divides the hollow chamber of the first wall body into a first chamber and a second chamber; the first chamber is arranged on the side of the second wall body close to the third shell unit; the first ring part is fixedly connected to the outer peripheral wall of the opening end of the third shell unit and surrounds to form an annular chamber; the second ring part is arranged in the annular chamber of the first ring part at intervals; the second ring part divides the annular chamber of the first ring part into a third chamber and a fourth chamber; the first chamber is communicated with the third chamber; the second chamber is communicated with the fourth chamber; the air supply pipe is communicated with the first chamber;

[0007] A rotating assembly, the rotating assembly comprising a rotor unit; the rotor unit comprising a turbine shaft, a turbine disk, and a turbine sheet; one end of the turbine shaft is rotatably connected to the open end of the third housing unit; the inner circumferential wall of the turbine disk is fixedly connected to the outer circumferential wall of the turbine shaft; one end of the turbine sheet is fixedly connected to the outer side wall of the turbine disk, and the other end extends in a direction away from the turbine disk; a side of the turbine disk close to the third housing unit, the outer side wall of the first ring portion, and the inner side wall of the second housing unit surround a first cooling cavity with an opening on one side; the first cooling cavity is connected to the interval area between the first housing unit and the second housing unit through its opening; the first chamber is connected to the first cooling cavity through the first channel; the second chamber is connected to the first cooling cavity through the second channel; the second chamber is connected to the external space of the first housing unit through the third channel.

[0008] In some embodiments, the second shell unit includes a second body and a third body; the second body is arranged at an end of the third body away from the turbine disk; part of the outer side wall of the second body is fixedly connected to the wing unit; the third body includes a first ring wall and a second ring wall; one end of the first ring wall is fixedly connected to the second body, and the other end extends toward the turbine disk; one end of the second ring wall is fixedly connected to the inner side wall of one end of the first ring wall close to the second body, and the other end extends toward the turbine disk; one end of the second ring wall close to the turbine disk is fixedly connected to one end of the air supply boss close to the turbine disk; the inner circumferential wall of the first ring wall and the outer circumferential wall of the second ring wall surround a second cooling cavity with an opening on one side; the second cooling cavity is connected to the first cooling cavity through its opening; the inner circumferential wall of the second ring wall and the outer side wall of the air supply boss surround a third cooling cavity; the third cooling cavity is connected to the external space of the first shell unit.

[0009] In some embodiments, the rotating assembly also includes a sealing unit and a bearing unit; the outer peripheral side of the sealing unit is spaced apart from the inner peripheral wall of the opening end of the third shell unit; the sealing unit includes a sealing ring body, a first sealing lip, and a second sealing lip; the bearing unit is arranged in the internal chamber of the third shell unit; one end of the bearing unit is rotatably connected to the turbine shaft; the sealing ring body is sleeved at the connection between the turbine shaft and the bearing unit; the first sealing lip is arranged on the outer peripheral side of the sealing ring body close to one end of the bearing unit; one end of the first sealing lip is fixedly connected to the outer peripheral wall of the sealing ring body, and the other end is spaced apart from the inner wall of the third shell unit; the second sealing lip is spaced apart from the first sealing lip away from the one side of the bearing unit; one end of the second sealing lip is fixedly connected to the outer peripheral wall of the sealing ring body, and the other end is spaced apart from the inner wall of the third shell unit; the spacing distance between the first sealing lip and the inner wall of the third shell unit is less than or equal to 1 / 2 of the spacing distance between the first sealing lip and the second sealing lip; the spacing distance between the second sealing lip and the inner wall of the third shell unit is less than or equal to 1 / 2 of the spacing distance between the first sealing lip and the second sealing lip; the first sealing lip, the second sealing lip, and the third shell unit surround and form a fifth chamber; the first channel is connected to the first cooling chamber through the fifth chamber; the first channel is connected to the internal chamber of the third shell unit through the fifth chamber.

[0010] In some embodiments, the first channels are evenly spaced along the circumference of the open end of the third housing unit.

[0011] In some embodiments, the cross-sectional area of ​​the first chamber is larger than the cross-sectional area of ​​the second chamber; and the cross-sectional area of ​​the third chamber is larger than the cross-sectional area of ​​the fourth chamber.

[0012] In some embodiments, A≤1 / 2*C, B≤1 / 2*C; wherein A is the spacing distance between the first wall body and the second wall body, B is the spacing distance between the first ring portion and the second ring portion, and C is the wall thickness of the first wall body.

[0013] In some embodiments, D≤1 / 5*F, E≤1 / 5*F; wherein D is the spacing distance between the first annular wall and the second annular wall, E is the spacing distance between the second annular wall and the first wall body; and F is the spacing distance between the first shell unit and the second shell unit.

[0014] In some embodiments, the cross-sectional area of ​​the first channel is less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe; the cross-sectional area of ​​the second channel is less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe; and the cross-sectional area of ​​the third channel is less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe.

[0015] In a second aspect, the present invention provides a gas turbine processing method, the gas turbine processing method is applied to a gas turbine device as described in any one of the first aspects, the gas turbine processing method comprising:

[0016] Step S10, based on the processing requirements of the shell component, obtaining a three-dimensional model of the shell component;

[0017] Step S20, obtaining a first processed body of the housing assembly by additive processing based on the three-dimensional model;

[0018] Step S30, performing post-processing on the first processed body to obtain the shell assembly;

[0019] Step S40, obtaining the gas turbine device based on the completion of the processing of the shell assembly.

[0020] In some embodiments, step S30 includes:

[0021] Step S31, cleaning the first processed object to obtain a first object to be processed;

[0022] Step S32, heat-treating the first body to be processed to obtain a second body to be processed; wherein the heat treatment includes stress relief treatment, hot isostatic pressing treatment, solution treatment, and aging treatment; the stress relief treatment includes keeping the first body to be processed at a first temperature for a first time, and then slowly cooling it to a second temperature with a furnace to obtain a stress relief body; the hot isostatic pressing treatment includes keeping the stress relief body at a third temperature and a first pressure for a second time, and then slowly cooling it to a second temperature with a furnace to obtain a hot isostatic pressing body; the solution treatment includes keeping the hot isostatic pressing body at a fourth temperature for a third time, and then cooling it to a fifth temperature with an inert gas to obtain a solid solution; the aging treatment includes keeping the solid solution at a sixth temperature for a fourth time, and then cooling it to a fifth temperature with an inert gas to obtain the second body to be processed;

[0023] Step S33, performing surface treatment on the second object to be processed to obtain the shell assembly; wherein the surface treatment includes support removal treatment and finishing treatment; the support removal treatment includes separating the second object to be processed from the 3D printing device and removing the bracket supporting the shell assembly; the finishing treatment includes the surface roughness of the shell assembly reaching a set range.

[0024] In order to solve the problem of how to reduce the influence of high temperature gas on the internal temperature of the shell component, the present invention has the following advantages:

[0025] The shell assembly can communicate with the outside gas through the inside of the wing plate unit. The second wall of the air supply boss can separate the hollow chamber of the first wall into a first chamber and a second chamber for further heat insulation, which is used to reduce the influence of the heat conduction effect of the high-temperature gas on the temperature rise inside the shell assembly. The second ring part can separate the annular chamber of the first ring part into a third chamber and a fourth chamber. Thus, the high-pressure cold air enters from the air supply pipe, flows through the first chamber and then flows to the second chamber, and the high-pressure cold air flowing through the first chamber can also flow to the third chamber. Thus, multiple chambers are provided, which can realize multi-layer heat insulation, and the heat of the high-temperature gas is isolated as much as possible from being conducted to the inside of the third shell unit to avoid affecting the use of the gas turbine device, so that the high-pressure cold air can be more evenly distributed on the surface of the third shell unit, thereby improving the cooling effect. When the high-pressure cold air flows through the second chamber, a thin air film can be formed, which plays a role in isolating the high-temperature environment and reducing the surface temperature of the third shell unit. The high-pressure cold air can flow from the second chamber to the fourth chamber, thereby realizing the cooling of the third shell unit, and further reducing the influence of the high-temperature gas on the internal temperature of the shell assembly.

[0026] The high-pressure cold air flowing through the first cooling cavity can flow to the interval area between the first shell unit and the second shell unit, so that the high-pressure cold air after heat exchange inside the third shell unit can be discharged, thereby further achieving heat insulation inside the third shell unit. The high-pressure cold air flowing through the first cooling cavity can further cool the turbine disk, reduce the influence of high-temperature combustion gas on the internal temperature of the shell component, and enhance the cooling effect. This can solve the problem of how to reduce the influence of high-temperature combustion gas on the internal temperature of the shell component. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A schematic diagram of a gas turbine apparatus according to an embodiment is shown;

[0028] Figure 2 Shows Figure 1 An enlarged schematic diagram of a gas turbine device at position A in the embodiment;

[0029] Figure 3 Shows Figure 1 An enlarged schematic diagram of a gas turbine device at B in the embodiment;

[0030] Figure 4 A schematic diagram of a gas turbine device according to another embodiment is shown;

[0031] Figure 5 A schematic diagram of a gas turbine device according to another embodiment is shown;

[0032] Figure 6 A flow chart of a gas turbine processing method according to an embodiment is shown.

[0033] Figure markings: 01 shell assembly; 11 first shell unit; 111 flange seat; 112 fixing hole; 113 first body; 12 second shell unit; 121 second body; 122 third body; 1221 first annular wall; 1222 second annular wall; 13 third shell unit; 131 fourth body; 132 mounting cavity; 133 accommodating cavity; 14 wing unit; 15 air supply unit; 151 air supply pipe; 152 air supply boss; 1521 first wall body; 1522 second wall body; 1523 first ring portion; 1524 second ring portion; 1525 first channel; 1526 second channel; 1527 third channel; 02 rotating assembly; 21 rotor unit; 211 turbine shaft; 212 turbine disk; 213 turbine blade; 22 sealing unit; 221 sealing ring body; 222 first sealing lip; 223 second sealing lip; 224 third sealing lip; 23 bearing unit. DETAILED DESCRIPTION

[0034] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, rather than implying any limitation on the scope of the present disclosure.

[0035] As used herein, the term "including" and its variants are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment". The term "another embodiment" is to be interpreted as "at least one other embodiment". The orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like is based on the orientation or position relationship shown in the accompanying drawings. These terms are mainly for better describing the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation. In addition, in addition to being used to indicate an orientation or position relationship, some of the above terms may also be used to indicate other meanings, such as the term "upper" may also be used to indicate a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances. In addition, the terms "install", "set", "provided with", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances. In addition, the terms "first", "second", etc. are mainly used to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components. Unless otherwise specified, "plurality" means two or more.

[0036] At present, gas turbines can be applied in many fields by converting the chemical energy of fuel into mechanical energy. Usually, the turbine disk 212 of the rotating component 02 needs to be cooled. However, the outer shell of the parts through which the cold air flows will come into contact with the high-temperature combustion gas of the gas turbine engine. The high-temperature combustion gas will increase the temperature of the high-pressure cold air in the parts through the heat conduction effect, thereby affecting the cooling effect of the high-pressure cold air on the turbine disk 212, reducing the cooling effect of the turbine disk 212, and reducing the performance and production efficiency of the gas turbine. In order to solve the problem of how to reduce the impact of high-temperature combustion gas on the internal temperature of the casing component 01, a gas turbine device is proposed. Figure 1 As shown, the gas turbine device may include a casing assembly 01 and a rotating assembly 02 .

[0037] The shell assembly 01 may include a first shell unit 11, a second shell unit 12, a third shell unit 13, a wing unit 14, and an air supply unit 15. The air supply unit 15 is used to provide a cold air flow to flow through the internal structure of the shell assembly 01 to cool it. The second shell unit 12 may be arranged inside the first shell unit 11. The third shell unit 13 may be arranged inside the second shell unit 12. The first shell unit 11, the second shell unit 12, and the third shell unit 13 may be arranged in sequence and spaced apart, and the high-temperature combustion gas may be discharged from the engine combustion chamber and enter the turbine blades 213 of the rotor unit 21, and then flow through the area between the inner wall of the first shell unit 11 and the outer wall of the second shell unit 12 and be discharged from the external space. One end of the wing unit 14 may be fixedly connected to the inner wall of the first shell unit 11, and the other end may be fixedly connected to the outer wall of the second shell unit 12. The fixed connection may enhance the stability of the wing unit 14. The wing unit 14 may guide and divert the high-temperature combustion gas to improve the flow efficiency of the high-temperature combustion gas. As Figure 5As shown, a cavity can be formed inside the wing unit 14, so as to reduce the weight of the housing assembly 01. In this connection mode, the internal space of the second housing unit 12 can also be connected to the external space of the first housing unit 11. One end of the third housing unit 13 can be open, and the other end can be closed. The air supply unit 15 can include an air supply pipe 151 and an air supply boss 152. The air supply boss 152 can include a first wall body 1521, a second wall body 1522, a first ring portion 1523, a second ring portion 1524, a first channel 1525, a second channel 1526, and a third channel 1527. One side of the first wall body 1521 can be fixedly connected to the inner side wall of the second housing unit 12, and the other side can be fixedly connected to the outer side wall of the third housing unit 13, so that the side wall of the first wall body 1521 close to the third housing unit 13 can be surrounded by the outer side wall of the third housing unit 13 to form a hollow chamber, and high-pressure cold air can flow through the hollow chamber to cool the third housing unit 13. The second wall 1522 can be arranged in the hollow chamber of the first wall 1521 at intervals, so that the second wall 1522 can separate the hollow chamber of the first wall 1521 into a first chamber and a second chamber for further heat insulation, so as to reduce the influence of the heat conduction effect of the high-temperature gas on the temperature rise of the shell assembly 01. The first chamber can be arranged on the side of the second wall 1522 close to the third shell unit 13, and the second chamber can be arranged on the side of the second wall 1522 away from the third shell unit 13. The first ring portion 1523 and the outer peripheral wall of the opening end of the third shell unit 13 can be fixedly connected and surrounded to form an annular chamber, and the second ring portion 1524 can be arranged in the annular chamber of the first ring portion 1523 at intervals, and the second ring portion 1524 can separate the annular chamber of the first ring portion 1523 into a third chamber and a fourth chamber. The first chamber can be connected to the third chamber, and the gas supply pipe 151 can be connected to the first chamber. Thus, high-pressure cold air enters from the air supply pipe 151, flows through the first chamber and then is diverted to the second chamber. The high-pressure cold air flowing through the first chamber can also flow to the third chamber. Thus, by providing multiple chambers, multi-layer heat insulation can be achieved. The high-pressure cold air flows through multiple chambers to isolate the heat from being conducted to the inside of the third shell unit 13 as much as possible, thereby avoiding affecting the use of the gas turbine device, so that the high-pressure cold air can be more evenly distributed on the surface of the third shell unit 13, thereby improving the cooling effect. When the high-pressure cold air flows through the second chamber, a thin air film can be formed. This air film plays a role in isolating the high-temperature environment and reducing the surface temperature of the shell component 01. The second chamber can be connected to the fourth chamber, and the high-pressure cold air can flow from the second chamber to the fourth chamber. The high-pressure cold air flows through the inner circumferential wall of the second ring portion 1524, thereby cooling the third shell unit 13, further reducing the influence of the high-temperature gas on the internal temperature of the shell component 01.

[0038] The rotating assembly 02 may include a rotor unit 21. The rotor unit 21 may include a turbine shaft 211, a turbine disk 212, and a turbine blade 213. One end of the turbine shaft 211 may be rotatably connected to the open end of the third housing unit 13. The turbine shaft 211 carries the turbine blade 213 rotating at a high speed to ensure the stable operation of the entire transmission system. The inner peripheral wall of the turbine disk 212 may be fixedly connected to the outer peripheral wall of the turbine shaft 211. The main function of the turbine disk 212 is to convert part of the heat energy and potential energy in the high-temperature combustion gas into mechanical energy. One end of the turbine blade 213 may be fixedly connected to the outer side wall of the turbine disk 212, and the other end may extend in a direction away from the turbine disk 212. The turbine blade 213 is an important component of the rotor unit 21 in the gas turbine device, and may rotate at a high speed to guide the high-temperature combustion gas to be discharged into the interval area between the first housing unit 11 and the second housing unit 12. The side of the turbine disk 212 close to the third housing unit 13, the outer side wall of the first ring portion 1523, and the inner side wall of the second housing unit 12 can surround and form a first cooling cavity with an opening on one side. The first cooling cavity can be connected to the spacing area between the first housing unit 11 and the second housing unit 12 through its opening. The high-pressure cold air flowing through the first cooling cavity can flow to the spacing area between the first housing unit 11 and the second housing unit 12 so that the high-pressure cold air after heat exchange inside the third housing unit 13 can be discharged, thereby further achieving heat insulation inside the third housing unit 13. At the same time, the high-pressure cold air flowing through the first cooling cavity can further cool the turbine disk 212, reducing the influence of high-temperature combustion gas on the internal temperature of the housing assembly 01 and enhancing the cooling effect. The first chamber can be connected to the first cooling cavity through the first channel 1525, and the second chamber can be connected to the first cooling cavity through the second channel 1526. The high-pressure cold air in the first chamber and the second chamber can be discharged to the first cooling cavity. After the high-pressure cold air in the first chamber and the second chamber undergoes heat exchange with the third shell assembly 01, it can be discharged to the first cooling chamber, and then the turbine disk 212 can be further cooled in the first cooling chamber. After that, the high-pressure cold air can be discharged from the first cooling chamber to the interval area between the first shell unit 11 and the second shell unit 12 after the heat exchange, thereby achieving the heat insulation effect on the third shell unit 13. In this way, the cooling efficiency can be improved to achieve rapid cooling and reduce the waste of high-pressure cold air, forming a stable and uniform cooling environment to cool the third shell unit 13. The second chamber can be connected to the external space of the first shell unit 11 through the third channel 1527, and the high-pressure cold air in the second chamber can flow to the external space after heat exchange.

[0039] In other embodiments, Figure 4As shown, the first housing unit 11 may include a flange seat 111, a fixing hole 112, and a first body 113. The flange seat 111 may be fixedly connected to the first body 113, and the fixing holes 112 may be arranged at intervals along the circumference of the flange seat 111. The flange seat 111 may connect the gas turbine device to other components (such as pipelines, support structures, etc.). The fixing holes 112 may be used for installation and fixing.

[0040] In some embodiments, the second housing unit 12 may include a second body 121 and a third body 122. The second body 121 may be disposed at an end of the third body 122 away from the turbine disk 212, and a portion of the outer sidewall of the second body 121 may be fixedly connected to the wing unit 14. Figure 2 As shown, the third body 122 may include a first annular wall 1221 and a second annular wall 1222. One end of the first annular wall 1221 may be fixedly connected to the second body 121, and the other end may extend in a direction close to the turbine disk 212. One end of the second annular wall 1222 may be fixedly connected to the inner side wall of one end of the first annular wall 1221 close to the second body 121, and the other end may extend in a direction close to the turbine disk 212. One end of the second annular wall 1222 close to the turbine disk 212 may be fixedly connected to one end of the air supply boss 152 close to the turbine disk 212, whereby the inner peripheral wall of the first annular wall 1221 may be surrounded by the outer peripheral wall of the second annular wall 1222 to form a second cooling cavity with an opening on one side. The second cooling cavity may be connected to the first cooling cavity through its opening. The high-pressure cold air flowing into the first cooling cavity may flow to the second cooling cavity, thereby better cooling the first annular wall 1221 and the second annular wall 1222 to achieve cooling, while enhancing the heat insulation effect and improving the cooling efficiency. The inner circumferential wall of the second annular wall 1222 can be surrounded by the outer wall of the air supply boss 152 to form a third cooling cavity. The third cooling cavity can be connected to the external space of the first shell unit 11. In this way, a separation space can be provided, further increasing the heat-insulating cavity, thereby further reducing the influence of heat conduction of high-temperature fuel gas on the internal temperature of the third shell unit 13.

[0041] In other embodiments, the second annular wall 1222 may be provided with a fourth channel, and the second cooling cavity may be connected to the third cooling cavity through the fourth channel. High-pressure cold air in the second cooling cavity may be discharged into the third cooling cavity to cool the outer wall of the air supply boss 152 .

[0042] In some embodiments, the rotating assembly 02 may further include a sealing unit 22 and a bearing unit 23. The outer peripheral side of the sealing unit 22 may be spaced apart from the inner peripheral wall of the opening end of the third housing unit 13. This facilitates the formation of a space for lubricating oil to lubricate and cool the bearing. Figure 3As shown, the sealing unit 22 may include a sealing ring body 221, a first sealing lip 222, and a second sealing lip 223. The bearing unit 23 may be arranged in the inner chamber of the third housing unit 13, and one end of the bearing unit 23 may be rotatably connected to the turbine shaft 211. The sealing ring body 221 may be sleeved at the connection between the turbine shaft 211 and the bearing unit 23. In this way, the sealing performance of the sealing unit 22 may be improved to prevent the leakage of lubricating oil used for lubrication, and foreign matter may be prevented from entering, thereby extending the service life of the bearing unit 23. The first sealing lip 222 may be arranged on the outer peripheral side of the sealing ring body 221 near one end of the bearing unit 23. One end of the first sealing lip 222 may be fixedly connected to the outer peripheral wall of the sealing ring body 221, and the other end may be spaced apart from the inner wall of the third housing unit 13. The second sealing lip 223 may be spaced apart on the side of the first sealing lip 222 away from the bearing unit 23, one end of the second sealing lip 223 may be fixedly connected to the outer peripheral wall of the sealing ring body 221, and the other end may be spaced apart from the inner wall of the third housing unit 13. The distance between the first sealing lip 222 and the inner wall of the third housing unit 13 may be less than or equal to 1 / 2 of the distance between the first sealing lip 222 and the second sealing lip 223. The distance between the second sealing lip 223 and the inner wall of the third housing unit 13 may be less than or equal to 1 / 2 of the distance between the first sealing lip 222 and the second sealing lip 223. Avoid the distance between the first sealing lip 222 and the inner wall of the third housing unit 13 and the distance between the second sealing lip 223 and the inner wall of the third housing unit 13 being too large, resulting in the pressure in the fifth chamber being less than the external environmental pressure, affecting the sealing effect, making it easy for the lubricating oil to leak and reducing the lubrication effect. The first sealing lip 222, the second sealing lip 223, and the third housing unit 13 can surround and form a fifth chamber. The first channel 1525 can be connected to the first cooling chamber through the fifth chamber. The high-pressure cold air in the first chamber flows to the fifth chamber through the first channel 1525 and then flows into the first cooling chamber. When the high-pressure cold air flows to the fifth chamber, it can seal the lubricating oil in the mounting surface of the bearing unit 23, thereby preventing the lubricating oil from leaking outward and enhancing the sealing effect. At the same time, the high-pressure cold air flowing into the fifth chamber can also cool the bearing unit 23 for heat exchange and then flow to the first cooling chamber, thereby reducing the waste of high-pressure cold air by reasonably distributing the high-pressure cold air.

[0043] In other embodiments, the sealing unit 22 may further include a third sealing lip 224, which may be spaced apart on a side of the second sealing lip 223 away from the bearing unit 23, one end of the third sealing lip 224 may be fixedly connected to the outer peripheral wall of the sealing ring body 221, and the other end may be spaced apart from the inner wall of the third housing unit 13. The third sealing lip 224 is provided to provide an additional sealing barrier. This multiple sealing mechanism can more effectively prevent external impurities from entering the sealing area, improve the overall sealing performance, and at the same time increase the life of the sealing unit 22, saving maintenance costs. The spacing distance between the third sealing lip 224 and the inner wall of the third housing unit 13 may be less than or equal to 1 / 2 of the spacing distance between the first sealing lip 222 and the second sealing lip 223, and the distance between the second sealing lip 223 and the third sealing lip 224 may be less than or equal to the spacing distance between the first sealing lip 222 and the second sealing lip 223. In this way, the pressure difference between the fifth chamber and the external environment can be within a suitable range, and the third sealing lip 224 forms an effective sealing barrier to prevent lubricating oil leakage, thereby improving the reliability and durability of the seal. The third housing unit 13 may also include a fourth body 131, an installation cavity 132, and an accommodating cavity 133. The installation cavity 132 may be disposed on a side close to the turbine disk 212 for installing the bearing unit 23. The accommodating cavity 133 may be disposed on a side away from the turbine disk 212 for placing lubricating oil to lubricate the bearing unit 23. The high-pressure cold air in the fifth chamber may flow through one side of the installation cavity 132 of the third housing unit 13 to seal the lubricating oil in the mounting surface of the bearing unit 23, thereby preventing the lubricating oil from leaking outward, thereby enhancing the sealing effect, and at the same time cooling the bearing unit 23 to enhance the cooling effect. The fourth body 131 may be disposed at one end of the third housing unit 13 away from the turbine disk 212.

[0044] In some embodiments, the first channel 1525 can be evenly spaced along the circumferential opening of the third housing unit 13. This allows high-pressure cold air to flow evenly and quickly through the first channel 1525 from the first chamber to the fifth chamber and then to the first cooling chamber, thereby cooling the housing assembly 01 and improving the cooling efficiency, thereby reducing the impact of high-temperature combustion gas on the internal temperature of the housing assembly 01. The high-pressure cold air in the fifth chamber flows through one side of the mounting cavity 132 of the third housing unit 13 to seal the lubricating oil in the mounting surface of the bearing unit 23, thereby preventing the lubricating oil from leaking out and enhancing the sealing effect.

[0045] In some embodiments, since the high-pressure cold air is provided by the environmental control system, the amount of high-pressure cold air available is limited. The cross-sectional area of ​​the first chamber can be greater than the cross-sectional area of ​​the second chamber, and the cross-sectional area of ​​the third chamber can be greater than the cross-sectional area of ​​the fourth chamber. In this way, when the amount of high-pressure cold air is limited, by controlling the flow rate and flow path of the cold air, the high-pressure cold air distribution can be flexibly adjusted while ensuring the cooling effect of the high-pressure cold air on the shell assembly 01, thereby reducing the consumption of high-pressure cold air and improving the cooling efficiency.

[0046] In some embodiments, the spacing distance A between the first wall 1521 and the second wall 1522 may be less than or equal to 1 / 2 of the spacing distance B between the first ring portion 1523 and the second ring portion 1524, and the high-pressure cold air may be more evenly distributed in the second cooling cavity, thereby improving the cooling effect. The spacing distance B between the first ring portion 1523 and the second ring portion 1524 may be less than or equal to 1 / 2 of the wall thickness C of the first wall 1521. In this way, the consumption of high-pressure cold air may be reduced, thereby improving the cooling efficiency, while ensuring the cooling effect on the housing assembly 01 and the sealing effect on the bearing assembly.

[0047] In some embodiments, the spacing distance D between the first annular wall 1221 and the second annular wall 1222 may be less than or equal to 1 / 5 of the spacing distance E between the second annular wall 1222 and the first wall body 1521, and the spacing distance E between the second annular wall 1222 and the first wall body 1521 may be less than or equal to 1 / 5 of the spacing distance F between the first shell unit 11 and the second shell unit 12. In this way, the high-pressure cold air flowing through the second cooling cavity and the third cooling cavity can still be better evenly distributed to reduce the temperature. Under the condition of ensuring the cooling effect on the shell assembly 01 and the sealing effect on the bearing assembly, by controlling the volume of the second cooling cavity and the third cooling cavity, the consumption of high-pressure cold air can be reduced and the cooling efficiency can be improved.

[0048] In some embodiments, the cross-sectional area of ​​the first channel 1525 may be less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe 151, the cross-sectional area of ​​the second channel 1526 may be less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe 151, and the cross-sectional area of ​​the third channel 1527 may be less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe 151. In this way, when the high-pressure cold air flows out from the first channel 1525, the second channel 1526, and the third channel 1527, it can still be better evenly distributed to cool the housing assembly 01. While ensuring the cooling effect on the housing assembly 01 and the sealing effect on the bearing assembly, by controlling the cross-sectional areas of the first channel 1525, the second channel 1526, and the third channel 1527, the flow rate of the high-pressure cold air can be controlled, reducing the consumption of the high-pressure cold air while improving the cooling efficiency.

[0049] This embodiment discloses a gas turbine processing method, such as Figure 6As shown, the gas turbine processing method may include steps S10 to S40, and each step is described in detail as follows:

[0050] Step S10: Based on the processing requirements of the shell component 01, a three-dimensional model of the shell component 01 may be obtained, so as to facilitate subsequent additive processing according to the three-dimensional model.

[0051] In step S20 , after obtaining the three-dimensional model of the shell component 01 , a first processed body of the shell component 01 may be obtained by additive processing, thereby ensuring the accuracy of the processing.

[0052] Step S30, post-processing the first processed body to obtain the housing component 01. In this way, defects generated during the processing can be eliminated, and the durability and reliability of the housing component 01 can be improved.

[0053] Step S40, when the shell assembly 01 is processed, the gas turbine device can be obtained. The integrated structure of the gas turbine device can improve the sealing effect, improve the utilization rate of high-pressure cold air, thereby reducing the consumption of high-pressure cold air, facilitate processing and reduce weight, reduce material waste and processing steps, and thus reduce production costs. 3D printing can produce complex geometric shapes and structures, improving the flexibility of design and manufacturing.

[0054] In some embodiments, step S30 may include:

[0055] In step S31, the first processed object may be cleaned to remove impurities, residues or uncured materials on the surface to obtain a first object to be processed, and subsequent steps are ensured to be performed in a clean and interference-free environment.

[0056] In step S32, the first body to be processed can be heat treated to obtain the second body to be processed. The heat treatment may include stress relief treatment, hot isostatic pressing treatment, solution treatment, and aging treatment. The stress relief treatment may include the first body to be processed being kept at a first temperature for a first time, and then slowly cooling it to a second temperature with the furnace to obtain a stress relief body. It is used to reduce or eliminate the internal stress generated during the processing process to prevent the parts from deforming or cracking due to stress concentration during use. The hot isostatic pressing treatment may include the stress relief body being kept at a third temperature and a first pressure for a second time, and then slowly cooling it to a second temperature with the furnace to obtain a hot isostatic pressing body. Through the high temperature and high pressure environment, the material is made denser, the internal defects are reduced, and the mechanical properties and corrosion resistance of the stress relief body are improved. The solution treatment may include the hot isostatic pressing body being kept at a fourth temperature for a third time, and then being filled with inert gas and cooled to a fifth temperature to obtain a solid solution. A uniform solid solution can be formed to prepare for the subsequent aging treatment. The aging treatment may include the solid solution being kept at a sixth temperature for a fourth time, and then being filled with inert gas and cooled to a fifth temperature to obtain the second body to be processed. The alloy elements in the solid solution are precipitated in the form of fine dispersed precipitation phases, thereby improving the hardness and strength of the second body to be processed while maintaining good plasticity and toughness.

[0057] In step S33, the second object to be processed may be subjected to surface treatment to obtain the shell component 01. Through the surface treatment, the shell component 01 is further precisely formed and the surface quality is improved. The surface treatment may include a support removal treatment and a finishing treatment. The support removal treatment may include separating the second object to be processed from the 3D printing device and removing the bracket supporting the shell component 01. This ensures the net size and shape of the final shell component 01. The finishing treatment may include the surface roughness of the shell component 01 reaching a set range. This may improve the surface finish and precision to meet the assembly and use requirements of the shell component 01. The quality and reliability of the shell component 01 are improved, and the efficient performance of the gas turbine device is ensured.

[0058] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present disclosure, and in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present disclosure.

Claims

1. A gas turbine device, characterized in that: The gas turbine device comprises: A shell assembly, the shell assembly includes a first shell unit, a second shell unit, a third shell unit, a wing unit, and an air supply unit; the second shell unit is arranged inside the first shell unit; the third shell unit is arranged inside the second shell unit; the first shell unit, the second shell unit, and the third shell unit are arranged in sequence at intervals; one end of the wing unit is fixedly connected to the inner wall of the first shell unit, and the other end is fixedly connected to the outer wall of the second shell unit; one end of the third shell unit is open, and the other end is closed; the air supply unit includes an air supply pipe and an air supply boss; the air supply boss includes a first wall body, a second wall body, a first ring portion, a second ring portion, a first channel, a second channel, and a third channel; one side of the first wall body is fixedly connected to the inner wall of the second shell unit, and the other side is fixedly connected to the outer wall of the third shell unit; The side wall of the first wall body close to the third shell unit and the outer side wall of the third shell unit surround to form a hollow chamber; the second wall body is arranged in the hollow chamber of the first wall body at intervals; the second wall body divides the hollow chamber of the first wall body into a first chamber and a second chamber; the first chamber is arranged on the side of the second wall body close to the third shell unit; the first ring part is fixedly connected to the outer peripheral wall of the opening end of the third shell unit and surrounds to form an annular chamber; the second ring part is arranged in the annular chamber of the first ring part at intervals; the second ring part divides the annular chamber of the first ring part into a third chamber and a fourth chamber; the first chamber is communicated with the third chamber; the second chamber is communicated with the fourth chamber; the air supply pipe is communicated with the first chamber; high-pressure cold air enters from the air supply pipe, flows through the first chamber and then is diverted to the second chamber; A rotating assembly, the rotating assembly comprising a rotor unit; the rotor unit comprising a turbine shaft, a turbine disk, and a turbine sheet; one end of the turbine shaft is rotatably connected to the open end of the third housing unit; the inner peripheral wall of the turbine disk is fixedly connected to the outer peripheral wall of the turbine shaft; one end of the turbine sheet is fixedly connected to the outer side wall of the turbine disk, and the other end extends in a direction away from the turbine disk; a side of the turbine disk close to the third housing unit, the outer side wall of the first ring portion, and the inner side wall of the second housing unit surround a first cooling cavity with an opening on one side; the first cooling cavity is connected to the interval area between the first housing unit and the second housing unit through its opening; the first chamber is connected to the first cooling chamber through the first channel; the second chamber is connected to the first cooling chamber through the second channel; the second chamber is connected to the external space of the first housing unit through the third channel; The second shell unit includes a second body and a third body; the second body is arranged at an end of the third body away from the turbine disk; part of the outer side wall of the second body is fixedly connected to the wing unit; the third body includes a first ring wall and a second ring wall; one end of the first ring wall is fixedly connected to the second body, and the other end extends toward the turbine disk; one end of the second ring wall is fixedly connected to the inner side wall of one end of the first ring wall close to the second body, and the other end extends toward the turbine disk; one end of the second ring wall close to the turbine disk is fixedly connected to one end of the air supply boss close to the turbine disk; the inner circumferential wall of the first ring wall and the outer circumferential wall of the second ring wall surround a second cooling cavity with an opening on one side; the second cooling cavity is connected to the first cooling cavity through its opening; the inner circumferential wall of the second ring wall and the outer side wall of the air supply boss surround a third cooling cavity; the third cooling cavity is connected to the external space of the first shell unit.

2. A gas turbine device according to claim 1, characterized in that: The rotating assembly also includes a sealing unit and a bearing unit; the outer peripheral side of the sealing unit is spaced apart from the inner peripheral wall of the opening end of the third housing unit; the sealing unit includes a sealing ring body, a first sealing lip, and a second sealing lip; the bearing unit is arranged in the internal chamber of the third housing unit; one end of the bearing unit is rotatably connected to the turbine shaft; the sealing ring body is sleeved at the connection between the turbine shaft and the bearing unit; the first sealing lip is arranged on the outer peripheral side of the sealing ring body close to one end of the bearing unit; one end of the first sealing lip is fixedly connected to the outer peripheral wall of the sealing ring body, and the other end is spaced apart from the inner wall of the third housing unit The second sealing lip is arranged at a distance from the first sealing lip on a side away from the bearing unit; one end of the second sealing lip is fixedly connected to the outer peripheral wall of the sealing ring body, and the other end is arranged at a distance from the inner wall of the third housing unit; the distance between the first sealing lip and the inner wall of the third housing unit is less than or equal to 1 / 2 of the distance between the first sealing lip and the second sealing lip; the distance between the second sealing lip and the inner wall of the third housing unit is less than or equal to 1 / 2 of the distance between the first sealing lip and the second sealing lip; the first sealing lip, the second sealing lip, and the third housing unit surround and form a fifth chamber; The first passage is in communication with the first cooling chamber through the fifth chamber; the first passage is in communication with the inner chamber of the third housing unit through the fifth chamber.

3. A gas turbine device according to claim 2, characterized in that: The first channels are evenly spaced along the circumference of the open end of the third housing unit.

4. A gas turbine device according to claim 3, characterized in that: The cross-sectional area of ​​the first chamber is larger than the cross-sectional area of ​​the second chamber; the cross-sectional area of ​​the third chamber is larger than the cross-sectional area of ​​the fourth chamber.

5. A gas turbine device according to claim 4, characterized in that: A≤1 / 2*C, B≤1 / 2*C; wherein A is the spacing distance between the first wall body and the second wall body, B is the spacing distance between the first ring portion and the second ring portion, and C is the wall thickness of the first wall body.

6. A gas turbine device according to claim 1, characterized in that: D≤1 / 5*F, E≤1 / 5*F; wherein D is the spacing distance between the first annular wall and the second annular wall, E is the spacing distance between the second annular wall and the first wall body; and F is the spacing distance between the first shell unit and the second shell unit.

7. A gas turbine device according to claim 1, characterized in that: The cross-sectional area of ​​the first channel is less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe; the cross-sectional area of ​​the second channel is less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe; the cross-sectional area of ​​the third channel is less than or equal to 1 / 4 of the cross-sectional area of ​​the air supply pipe.

8. A gas turbine machining method, the gas turbine machining method being applied to a gas turbine device as claimed in any one of claims 1 to 7, characterized in that: The gas turbine processing method comprises: Step S10, based on the processing requirements of the shell component, obtaining a three-dimensional model of the shell component; Step S20, obtaining a first processed body of the housing assembly by additive processing based on the three-dimensional model; Step S30, performing post-processing on the first processed body to obtain the shell assembly; Step S40, obtaining the gas turbine device based on the completion of the processing of the shell assembly.

9. A gas turbine machining method according to claim 8, characterized in that: The step S30 comprises: Step S31, cleaning the first processed object to obtain a first object to be processed; Step S32, heat-treating the first body to be processed to obtain a second body to be processed; wherein the heat treatment includes stress relief treatment, hot isostatic pressing treatment, solution treatment, and aging treatment; the stress relief treatment includes keeping the first body to be processed at a first temperature for a first time, and then slowly cooling it to a second temperature with a furnace to obtain a stress relief body; the hot isostatic pressing treatment includes keeping the stress relief body at a third temperature and a first pressure for a second time, and then slowly cooling it to a second temperature with a furnace to obtain a hot isostatic pressing body; the solution treatment includes keeping the hot isostatic pressing body at a fourth temperature for a third time, and then cooling it to a fifth temperature with an inert gas to obtain a solid solution; the aging treatment includes keeping the solid solution at a sixth temperature for a fourth time, and then cooling it to a fifth temperature with an inert gas to obtain the second body to be processed; Step S33, performing surface treatment on the second object to be processed to obtain the shell assembly; wherein the surface treatment includes support removal treatment and finishing treatment; the support removal treatment includes separating the second object to be processed from the 3D printing device and removing the bracket supporting the shell assembly; the finishing treatment includes the surface roughness of the shell assembly reaching a set range.

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