Aluminum infiltration tooling and method for turbine components of an aircraft engine

Abstract

The present application relates to the technical field of aero-engine, and especially relates to an aero-engine turbine component aluminizing tool and method. The aero-engine turbine component aluminizing tool comprises a lifting frame, a plurality of trays and a plurality of support rings. The lifting frame comprises a stand and a base, and the stand and the base are connected. The tray is a stainless steel mesh structure, a first through hole is formed in the tray, and the first through hole is detachably arranged on the stand; and the tray is used for placing a turbine component. The support ring comprises a first support part, a second support part and a connecting part, a second through hole is formed in the connecting part, and the second through hole is detachably arranged on the stand. The support ring is located between two adjacent trays, and the support ring is configured to support the trays. The aero-engine turbine component aluminizing tool can save energy and cost, improve work efficiency and improve the product yield of the turbine component.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to an aluminizing tool and method for a turbine component of an aero-engine. Background Art

[0002] Turbine components are the core of aircraft engines. Critical locations such as blades and guide vanes must withstand high temperatures, high airflow, high pressure, and centrifugal forces—the harshest operating environments in aircraft engines. To enhance the components' resistance to high-temperature oxidation and gas corrosion, extending engine life, surface treatments are often used to improve their surface properties and protect the workpiece substrate. Common surface treatment methods currently used in the industry include thermal spraying, laser solution coating, vapor deposition, and chemical heat treatment.

[0003] Vapor phase aluminizing is a method of vapor deposition. Aluminizing tooling is typically used to place turbine components in an aluminizing furnace for the aluminizing process. Verification based on the nine-point temperature measurement method shows that the temperature distribution in the aluminizing furnace is consistent horizontally, but there are temperature differences in the vertical direction. Aircraft engine turbine components are made of different materials and sizes. In actual production, turbine components of different materials and sizes have different aluminizing temperature requirements. If a single aluminizing furnace is used to perform the aluminizing process on turbine components of a single material and size, this will significantly increase costs, waste energy, and reduce processing efficiency. If all turbine components are placed together in the aluminizing furnace for the aluminizing process, the product yield of the turbine components will be reduced, increasing costs.

[0004] Therefore, it is urgent to design an aluminizing tooling and method for aircraft engine turbine components to solve the above technical problems. Summary of the Invention

[0005] The first purpose of the present invention is to provide an aluminizing tool for aircraft engine turbine components, which saves energy and costs, improves work efficiency, and increases the product yield of turbine components.

[0006] To achieve this object, the present invention adopts the following technical solutions:

[0007] The present invention provides an aluminizing tool for an aircraft engine turbine component, comprising:

[0008] A lifting frame, the lifting frame comprising a column and a base, the column and the base being connected;

[0009] A plurality of trays, each of which is a stainless steel mesh structure and has a first through hole formed thereon. The first through hole is detachably inserted through the column. The tray is used to place turbine components.

[0010] A plurality of support rings, the support ring comprising a first support part, a second support part and a connecting part, a second through hole is formed on the connecting part, the second through hole is detachably arranged on the stand, the upper outer edge of the connecting part is protruded with the first support part, and the lower outer edge of the connecting part is protruded with the second support part; the projection area of the first support part is equal to the projection area of the second support part in the vertical direction; the support ring is located between two adjacent trays, and the support ring is configured to support the tray.

[0011] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, the first support part and the second support part are annular, and the first support part and the second support part are coaxially arranged.

[0012] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, a plurality of reinforcing ribs are arranged on the connecting part.

[0013] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, the tray comprises a first support rod and a second support rod, and the first support rod and the second support rod are welded.

[0014] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, the first support rod and the second support rod are arranged to form a mesh hole, and the size of the mesh hole is arranged to be between 10mm*10mm and 15mm*15mm.

[0015] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, a lifting hole is formed on the lifting frame, and the lifting hole is configured to be connected with a crane.

[0016] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, the stand and the base are integrally formed.

[0017] As an optional technical solution of the aluminum infiltration tool for the turbine part of the aero-engine, the lifting frame and the support ring are stainless steel parts.

[0018] The second object of the present application is to provide an aluminum infiltration method for the turbine part of the aero-engine, which is simple in steps, convenient to operate, can accurately select the aluminum infiltration temperature area by adjusting the height position of the tray, reduce the influence of temperature difference on the aluminum infiltration process, improve the product yield, and save the cost.

[0019] To achieve this object, the present application adopts the following technical solutions:

[0020] The present invention provides an aluminizing method for an aircraft engine turbine component. The aluminizing method for an aircraft engine turbine component is applied to the above-mentioned aluminizing tool for an aircraft engine turbine component. The aluminizing method for an aircraft engine turbine component comprises the following steps:

[0021] Assemble support rings and pallets: Based on the vapor phase aluminizing process temperature, open the aluminizing furnace and record the temperature conditions in each area of ​​the aluminizing furnace. Find the temperature zone corresponding to each turbine component. Based on the distance from the base and the height of the turbine component, calculate the number of support rings required between each layer of pallets. Assemble the support rings and pallets on the lifting frame.

[0022] Place turbine components: Place turbine components on trays at corresponding positions, and ensure that turbine components on each layer are placed evenly and symmetrically;

[0023] Preparation before entering the furnace: according to the aluminizing process requirements, set the required process parameters on the control panel of the aluminizing furnace;

[0024] Turbine components are placed in the furnace: The aluminizing tooling and turbine components of the aircraft engine turbine components are hoisted into the furnace by a crane. Be careful not to let the edges of the aluminizing tooling scratch the furnace wall of the aluminizing furnace. After entering the furnace, the aluminizing process of vacuuming, passing argon gas, heating, heat preservation, diffusion, and cooling is carried out in sequence.

[0025] Turbine components are taken out of the furnace: After the aluminizing furnace is cooled to 80°C, a crane is used to lift the aluminizing tooling and turbine components of the aircraft engine turbine components out of the furnace. After the temperature drops to room temperature, the turbine components are manually removed.

[0026] As an optional technical solution for aluminizing an aircraft engine turbine component, the steps of placing the turbine component include:

[0027] Place turbine blades on a 4-layer pallet-assembled aluminizing tool for aircraft engine turbine components;

[0028] Place the guides on the aluminizing tooling for the aircraft engine turbine components assembled on a double-layer pallet;

[0029] The large assemblies are placed on the aluminizing tooling for aircraft engine turbine components assembled on a single-layer pallet.

[0030] The beneficial effects of the present invention include at least:

[0031] The application provides an aero-engine turbine part aluminizing tool, which comprises a lifting frame, a plurality of trays and a plurality of support rings. The lifting frame comprises a stand and a base connected with each other. The tray is a stainless steel mesh structure, and a first through hole is formed in the tray and detachably arranged on the stand. The support ring comprises a first support part, a second support part and a connecting part, and a second through hole is formed in the connecting part and detachably arranged on the stand. The support ring is arranged between two adjacent trays and configured to support the trays. The tray, the support ring and the lifting frame are assembled in a detachable manner, so that the number of support rings can be flexibly adjusted according to the turbine parts of different materials and different specifications and sizes, that is, the height position of the tray on the lifting frame is adjusted by increasing or reducing the number of support rings, so that various types of turbine parts can be placed on the tray, and the flexibility and applicability are improved. Meanwhile, the aluminizing temperature area can be accurately selected by adjusting the height position of the tray, the influence of temperature difference on the aluminizing process is reduced, and the product yield is improved. Therefore, the turbine parts of different materials can be placed in one aero-engine turbine part aluminizing tool for aluminizing process, the problems of low work efficiency and energy waste caused by single aluminizing furnace are avoided, and the cost is saved.

[0032] The application provides an aero-engine turbine part aluminizing method, which is simple in steps and convenient to operate. The height position of the tray can be adjusted to accurately select the aluminizing temperature area, reduce the influence of temperature difference on the aluminizing process, improve the product yield and save the cost. BRIEF DESCRIPTION OF DRAWINGS

[0033] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed in the description of the embodiments of the application will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the contents of the embodiments of the application and the drawings.

[0034] Figure 1 A structure schematic diagram of the aero-engine turbine part aluminizing tool provided by the embodiments of the application;

[0035] Figure 2 A partial structure diagram of the tray provided by the embodiments of the application;

[0036] Figure 3 A structure schematic diagram of the support ring provided by the embodiments of the application;

[0037] Figure 4A schematic structural diagram of an aluminizing tooling (four-layer tray) for aircraft engine turbine components provided by an embodiment of the present invention;

[0038] Figure 5 A schematic structural diagram of an aluminizing tooling (double-layer tray) for aircraft engine turbine components provided by an embodiment of the present invention;

[0039] Figure 6 This is a schematic structural diagram of an aluminizing tooling (single-layer tray) for aircraft engine turbine components provided by an embodiment of the present invention.

[0040] Reference numerals

[0041] 100. Lifting frame; 110. Column; 120. Base; 130. Lifting hole; 200. Pallet; 210. First support rod; 220. Second support rod; 230. Mesh; 300. Support ring; 310. First support part; 320. Second support part; 330. Connecting part; 340. Reinforcing rib. DETAILED DESCRIPTION

[0042] In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved more clear, the technical solutions of the present invention are further described below with reference to the accompanying drawings and through specific implementation methods.

[0043] In the description of the present invention, unless otherwise expressly specified or limited, the terms "connected," "connected," and "fixed" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integration; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific circumstances.

[0044] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0045] In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like, orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of description and simplification of operation, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first" and "second" are only used to distinguish in description and have no special meaning.

[0046] Before heating, the gas phase aluminizing is pre-evacuated, and then argon is introduced. The workpiece (for example, it can be a turbine part) is placed in a gas phase aluminizing special tooling (for example, it can be an aero-engine turbine part aluminizing tooling), aluminum-iron (Al-Fe) powder is used as a permeating agent, ammonium chloride (NH4Cl) is used as an activator, and aluminum oxide (Al2O3) powder is used as a filler. Before heating, argon is introduced to remove air, and then the workpiece is heated under argon protection. In the furnace, active aluminum atoms generated by the decomposition of the aluminizing agent at high temperature are carried to the surface of the workpiece by argon as a carrier, and then the active aluminum atoms are absorbed and diffused into the part matrix to form an aluminized layer, thereby improving the high-temperature oxidation and gas corrosion resistance of the part.

[0047] As shown in Figures 1-6 The present embodiment provides an aero-engine turbine part aluminizing tooling, which mainly comprises a lifting frame 100, a plurality of trays 200 and a plurality of support rings 300. The lifting frame 100 comprises a stand 110 and a base 120, and the stand 110 and the base 120 are connected. The tray 200 is a stainless steel mesh structure, and a first through hole is formed in the tray 200, which is detachably arranged on the stand 110; the tray 200 is used for placing turbine parts. The support ring 300 comprises a first support part 310, a second support part 320 and a connecting part 330, a second through hole is formed in the connecting part 330, which is detachably arranged on the stand 110, the upper outer edge of the connecting part 330 protrudes the first support part 310, and the lower outer edge of the connecting part 330 protrudes the second support part 320; in the vertical direction, the projection area of the first support part 310 is equal to the projection area of the second support part 320; the support ring 300 is located between two adjacent trays 200, and the support ring 300 is configured to support the tray 200.

[0048] Based on the above design, in the embodiment, the tray 200, the support ring 300 and the lifting frame 100 are assembled by means of detachable connection, so that the operation personnel can flexibly adjust the number of the support ring 300 according to the turbine components of different materials and different specifications and sizes, that is, the height position of the tray 200 on the lifting frame 100 is adjusted by increasing or reducing the number of the support ring 300, so that various types of turbine components can be placed on the tray 200, and the flexible applicability is improved. At the same time, by adjusting the height position of the tray 200, the aluminizing temperature area can be accurately selected, the influence of temperature difference on the aluminizing process is reduced, and the product yield is improved. Therefore, turbine components of different materials can be placed in one aero-engine turbine component aluminizing tool for aluminizing process, avoiding the problems of low work efficiency and waste of energy caused by single aluminizing furnace, so as to save the cost.

[0049] Optionally, the first support part 310 and the second support part 320 in the embodiment are annular, and the first support part 310 and the second support part 320 are coaxially arranged, so as to improve the stability and reliability of the support ring 300 and improve the uniformity of the stress of the support ring 300. The arrangement of the first support part 310 and the second support part 320 can increase the contact area of the support ring 300 and the tray 200, so as to avoid the phenomenon of stress concentration and improve the stability. The operation personnel can flexibly set the height size of the connecting part 330 according to the actual demand, for example, the height of the connecting part 330 is set to 0.5m, 1m, 1.5m, 2m and the like. Of course, in some optional embodiments, the first support part 310 and the second support part 320 can also be square or other shapes, which will not be described one by one here.

[0050] Further, as shown in Figure 3 The connecting part 330 in the embodiment is provided with a plurality of reinforcing ribs 340, so as to improve the mechanical strength of the support ring 300 and prolong the service life.

[0051] The tray 200 in the embodiment is circular, so that the tray 200 can be more stably assembled on the support ring 300, thereby improving the stability and reliability of the tray 200.

[0052] The principle of gas phase aluminizing is to bring activated Al atoms to the surface of the workpiece with Ar as the carrier, so there should be good argon flow conditions in the aluminizing furnace without obstruction and hindrance. The tray 200 carrying the turbine component needs to meet the conditions of no obstruction or less obstruction and uniform ventilation, so as to ensure that the argon flow speed of each turbine component area is consistent, thereby ensuring that the Al atoms uniformly contact the surface of the turbine component.

[0053] Therefore, as shown in Figure 2As shown, the tray 200 includes a plurality of first support rods 210 and a plurality of second support rods 220, which are welded together. The first support rods 210 and the second support rods 220 are both made of stainless steel. Specifically, the plurality of first support rods 210 are arranged horizontally, and the plurality of second support rods 220 are arranged vertically, so that the first support rods 210 and the second support rods 220 are arranged to form a mesh 230, and the mesh 230 has a size of 10mm*10mm-15mm*15mm, so that the tray 200 not only has good air permeability, but also can prevent small turbine components from falling off.

[0054] The tray 200 is arranged in a stainless steel mesh structure, which reduces the weight of the tray 200, so that the tray 200 is light and can be assembled into the lifting frame 100 by an operator in a handheld manner, and the number of the trays 200 and the positions of the turbine components can be placed as needed.

[0055] As shown, Figure 1 In this embodiment, the lifting frame 100 is provided with a lifting hole 130 configured to be connected with a crane, so that the crane can lift the turbine component aluminizing tool into or out of the aluminizing furnace.

[0056] Optionally, the column 110 and the base 120 in this embodiment are integrally formed, which improves the processing efficiency, improves the stability and reliability of the lifting frame 100, and prolongs the service life.

[0057] Optionally, the lifting frame 100 and the support ring 300 in this embodiment are both stainless steel parts, so that the strength of the turbine component aluminizing tool is improved, and the service life is prolonged.

[0058] This embodiment also provides an aircraft engine turbine component aluminizing method, which is applied to the above-mentioned aircraft engine turbine component aluminizing tool, and includes the following steps:

[0059] Assembling the support ring 300 and the tray 200: according to the temperature of the gas phase aluminizing process and the air gap aluminizing furnace, the temperature conditions of each region in the aluminizing furnace are recorded; the temperature regions corresponding to each turbine component are found, the number of support rings 300 needed to be added between each layer of trays 200 is calculated according to the size of the distance from the base 120 and the height of the turbine component, and the support ring 300 and the tray 200 are assembled on the lifting frame 100;

[0060] Placing the turbine component: the turbine component is placed in the tray 200 at the corresponding position, and the turbine components in each layer are uniformly and symmetrically placed, so as to improve the uniformity of the stress of the tray 200.

[0061] Specifically, the operator can flexibly set the actual position of the tray 200 according to the type of the turbine component. Figures 4-6 As shown, when the turbine component is a turbine blade, the operator can place the turbine blade on the 4-layer tray 200 assembled aero-engine turbine component aluminizing tool; when the turbine component is a guide vane, the operator can place the guide vane on the double-layer tray 200 assembled aero-engine turbine component aluminizing tool; when the turbine component is a large assembly, the operator can place the large assembly on the single-layer tray 200 assembled aero-engine turbine component aluminizing tool. When multiple turbine components are placed in the furnace, they can be assembled according to their sizes and appropriate temperature layers.

[0062] Preparation before entering the furnace: according to the requirements of the aluminizing process, set the required process parameters on the control panel of the aluminizing furnace. For example, check whether the gas pipeline is faulty, whether the gas pressure meets the production requirements, whether the cooling system is normal, etc.

[0063] Turbine component into the furnace: use the crane to hoist the aero-engine turbine component aluminizing tool and the turbine component into the furnace, and pay attention to not scratch the edge of the aero-engine turbine component aluminizing tool to the furnace wall; after entering the furnace, sequentially perform the aluminizing process of vacuum pumping, argon passing, temperature rising, temperature keeping, diffusion, and cooling;

[0064] Turbine component out of the furnace: after the aluminizing furnace is cooled to 80℃, the crane hoists the aero-engine turbine component aluminizing tool and the turbine component out of the furnace, and after being cooled to room temperature, the turbine component is manually removed.

[0065] Disassembly of the aero-engine turbine component aluminizing tool: after removing the turbine component, disassemble the aero-engine turbine component aluminizing tool and place it in the placement area for next use.

[0066] The aero-engine turbine component aluminizing method has simple steps and convenient operation, can accurately select the aluminizing temperature region by adjusting the height position of the tray 200, reduce the influence of temperature difference on the aluminizing process, improve the product yield, and save costs.

[0067] Obviously, the above is only a preferred embodiment of the present application and the technical principle applied. Those skilled in the art will understand that the present application is not limited to the specific embodiments herein, and those skilled in the art can make various obvious changes, re-adjustments and substitutions without departing from the scope of the present application. Therefore, although the present application has been described in more detail through the above embodiments, the present application is not limited to the above embodiments, and can include more other equivalent embodiments without departing from the concept of the present application, and the scope of the present application is determined by the scope of the appended claims.

[0068] Note that, in describing the present application, the description of the terms "some embodiments," "other embodiments," etc. means that the particular feature, structure, material, or characteristic being described is included in at least one embodiment or example of the application. Such descriptions are not necessarily referring to the same embodiment or example. Furthermore, the described features, structures, materials, or characteristics can be combined in any suitable manner in one or more embodiments or examples.

Claims

1. An aluminizing tool for turbine components of an aeroengine, characterized in that, The utility model relates to a kind of aviation engine turbine component aluminizing method and aviation engine turbine component aluminizing tooling, and the aviation engine turbine component aluminizing method comprises the following steps: Hoist frame (100) comprising column (110) and base (120), column (110) and base (120) are connected; Multiple trays (200), the tray (200) is stainless steel mesh structure, first through-hole is set on the tray (200), and the first through-hole is detachably arranged on the column (110);The tray (200) is used to place turbine component; Multiple support rings (300), the support ring (300) includes first support part (310), second support part (320) and connecting part (330), second through-hole is set on the connecting part (330), and the second through-hole is detachably arranged on the column (110), and the upper outer edge of the connecting part (330) is provided with the first support part (310), and the lower outer edge of the connecting part (330) is provided with the second support part (320);Along vertical direction, the projection area of the first support part (310) is equal to the projection area of the second support part (320);The support ring (300) is located between two adjacent trays (200), and the support ring (300) is configured to support the tray (200);The height position of the tray (200) on the hoist frame (100) is adjusted by changing the number of support rings (300); The tray (200) includes first support rod (210) and second support rod (220), and the first support rod (210) and the second support rod (220) are weldedly connected;The first support rod (210) and the second support rod (220) are enclosed to form a mesh (230), and the size of the mesh (230) is set to be between 10mm*10mm~15mm*15mm.

2. The aircraft engine turbine component aluminizing tooling of claim 1, wherein, The first support part (310) and the second support part (320) are annular, and the first support part (310) and the second support part (320) are coaxially arranged.

3. The aircraft engine turbine component aluminizing tooling of claim 2, wherein, The connecting part (330) is provided with a plurality of reinforcing ribs (340).

4. The aircraft engine turbine component aluminizing tooling of claim 1, wherein, The hoist frame (100) is provided with a lifting hole (130), and the lifting hole (130) is configured to be connected with a crane.

5. The aircraft engine turbine component aluminizing tooling of claim 4, wherein, The column (110) and the base (120) are integrally formed.

6. The aircraft engine turbine component aluminizing tooling of any one of claims 1-5, wherein, The hoist frame (100) and the support ring (300) are stainless steel parts.

7. A method of aluminizing a turbine component of an aircraft engine, characterized in that, The aviation engine turbine component aluminizing method is applied to the aviation engine turbine component aluminizing tooling of any one of claims 1-6, and the aviation engine turbine component aluminizing method comprises the following steps: Assemble support ring (300) and tray (200): according to the temperature of gas phase aluminizing process, air gap aluminizing furnace, record the temperature of each area in aluminizing furnace;Find the temperature area corresponding to each turbine component, according to the size of distance from base (120) and the height of turbine component, calculate the number of support rings (300) needed to be increased between each layer of trays (200), assemble support ring (300) and tray (200) on hoist frame (100); Placing turbine components: placing turbine components in the corresponding position of the tray (200), and placing turbine components of each layer uniformly and symmetrically; Preparation before entering the furnace: according to the requirements of aluminizing process, setting the required process parameters on the control panel of the aluminizing furnace; Turbine component into the furnace: using the way of hoisting by crane, hoisting the aero-engine turbine component aluminizing tooling and turbine component into the furnace, and paying attention to the edge of the aero-engine turbine component aluminizing tooling not to scratch the furnace wall of the aluminizing furnace; after entering the furnace, sequentially performing the aluminizing process of vacuum pumping, argon passing, temperature rising, temperature keeping, diffusion and cooling; Turbine component out of the furnace: after the aluminizing furnace is cooled to 80℃, the crane hoists the aero-engine turbine component aluminizing tooling and turbine component out of the furnace, and after being cooled to room temperature, manually taking down the turbine component.

8. The aircraft engine turbine component aluminizing method of claim 7 wherein, The step of placing turbine components includes: When the turbine component is a turbine blade, placing the turbine blade on the aero-engine turbine component aluminizing tooling assembled by four layers of trays (200); When the turbine component is a guide, placing the guide on the aero-engine turbine component aluminizing tooling assembled by double-layer trays (200); When the turbine component is a large assembly, placing the large assembly on the aero-engine turbine component aluminizing tooling assembled by single-layer trays (200).

Images