Wax module welding tool for turbine blade disc of aero-engine

Abstract

The utility model discloses an aero-engine turbine bladed disc wax mold welding tool, which relates to the technical field of aero-engine turbine bladed discs, and comprises a wheel disc, a groove body is arranged at the center of the top end of the wheel disc, an installation rod is installed in the groove body, the top end of the installation rod is rotatably connected with a micrometer, and the micrometer is connected with a rotating shaft of the aero-engine turbine bladed disc wax mold welding tool. A dial indicator is mounted at one end of the micrometer; the tailor-welding mechanism comprises a limiting groove formed in the outer part of the wheel disc; and the dismounting mechanism is arranged at one end of the micrometer and is used for assisting a worker to quickly dismount, mount and replace the micrometer. The wax mold welding tool has the advantages that the mold is designed and manufactured in a split mode, when the size tolerance of a casting does not meet the requirement, mold repairing can be conducted on a blade and a wheel disc, cost is low, difficulty is small, development cost can be remarkably reduced, the percent of pass of the casting can be improved, and economic losses caused by improper design of the mold are greatly reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to turbine disc technical field of aero -engine, especially turbine disc wax mould group welding frock of aero -engine. BACKGROUND

[0002] Turbine blade is the important component of turbine section in gas turbine engine. The blade of high speed rotation is responsible for the high temperature and high pressure airflow suction into combustor to maintain the work of engine.

[0003] In order to realize energy saving and weight reduction, improve turbine blade life and high temperature strength, advanced aero -engine turbine blade changes traditional split manufacturing and re -welding precision casting process, and adopts integral casting method.

[0004] The existing power turbine disc is represented by the high temperature alloy integral blade of aero -engine, usually by thick disc and 40 more thin -walled blade composition, resulting in the big size shrinkage difference of blade and disc, usually the blade position tolerance and disc diameter size tolerance after casting do not meet the design requirement. UTILITY MODEL CONTENTS

[0005] The utility model discloses a turbine disc wax mould group welding frock of aero -engine, aims at solving the existing power turbine disc is represented by the high temperature alloy integral blade of aero -engine, usually by thick disc and 40 more thin -walled blade composition, resulting in the big size shrinkage difference of blade and disc, usually the blade position tolerance and disc diameter size tolerance after casting do not meet the design requirement technical problem.

[0006] In order to realize the above -mentioned purpose, the utility model adopts the following technical scheme:

[0007] A turbine disc wax mould group welding frock of aero -engine, including disc, the top center of disc is equipped with the groove, the inside installation of groove is equipped with mounting rod, the top rotation of mounting rod is connected with micrometer, one end of micrometer is equipped with micrometer, still include splicing and welding mechanism: the splicing and welding mechanism includes the limit slot setting in the outside of disc, one end of limit slot is connected with limit piece, the other end of limit slot is connected with insert, the inside of disc is equipped with blade, one end of blade is equipped with rectangular square hole, dismounting mechanism: the dismounting mechanism is set up in one end of micrometer, and the dismounting mechanism is used for assisting the staff to dismount the replacement of micrometer.

[0008] Through setting up splicing and welding mechanism, staff can remove the limit connection formed by limit piece and insert by dismounting limit piece installed at the top of limit slot in sequence, and then take out a plurality of inserts from the inside of limit slot in sequence, so that one end of insert and blade are disconnected, and then take the blade upwards, so that the rectangular square hole at one end of blade and boss are disconnected.

[0009] In a preferred scheme, the dismounting mechanism comprises a mounting groove arranged at one end of the micrometer, a spring rod is slidably connected inside the mounting groove, one end of the spring rod is fixedly connected with a mounting assembly for assisting dismounting, and the bottom end of the micrometer is fixedly connected with an insertion rod.

[0010] By arranging the dismounting mechanism, the spring rod penetrating inside the mounting groove can be slid by the worker, the spring rod is slid to release the limiting of the insertion rod, and the insertion rod is taken out from inside the mounting groove, so that the micrometer with the insertion rod fixedly connected at the bottom end is dismounted.

[0011] In a preferred scheme, the mounting assembly comprises a clamping rod arranged at one end of the spring rod, through grooves are formed on the upper and lower sides of the micrometer, and the through grooves and the inside of the mounting groove are mutually penetrated.

[0012] By arranging the mounting assembly, the efficiency of the worker in dismounting the micrometer can be improved.

[0013] In a preferred scheme, one end of the insertion rod is provided with an insertion hole, and the size of the insertion hole is matched with the size of the clamping rod.

[0014] By arranging the insertion hole, the worker can be assisted to quickly dismount and replace the micrometer.

[0015] In a preferred scheme, the blade is aligned with the blade tip conical round hole by using a thimble, and the blade is positioned in the height and circumferential direction of the wheel disc.

[0016] By arranging the blade tip conical round hole, the worker can conveniently quickly dismount and mount a plurality of groups of blades.

[0017] In a preferred scheme, the inner side of the wheel disc is provided with a boss, and the size of the boss is matched with the size of the rectangular square hole.

[0018] By arranging the boss and the rectangular square hole, the worker can be assisted to clamp and mount the blade.

[0019] The utility model discloses an aero-engine turbine blade wax mold group welding tool has the following beneficial effects.

[0020] First, by setting the splicing mechanism, the staff can remove the limiting connection formed by the limiting piece and the plug by disassembling the limiting piece installed at the top end of the limiting groove in sequence, and then the plurality of plugs are extracted from the inside of the limiting groove in sequence, so that the one end of the plug and the blade are disconnected, and then the blade is taken upward, so that the rectangular square hole and the boss opened at one end of the blade are disconnected, and all the blades can be spliced into a whole by positioning and dialing, and the mold is designed in a split body, so that when the size tolerance of the casting does not meet the requirements, the mold of the blade and the disc can be repaired, which is low in cost and small in difficulty, can significantly reduce the development cost, improve the casting qualification rate, and greatly reduce the economic loss caused by improper mold design.

[0021] Second, by setting the dismounting mechanism, the staff can remove the limiting connection formed by the spring rod by sliding the spring rod penetrating in the installation slot, so that the spring rod slides and the limiting connection to the plug rod is removed, and then the plug rod is taken out from the inside of the installation slot, so that the dial gauge with the plug rod fixedly connected at the bottom end is disassembled, which can assist the staff to quickly disassemble and replace the dial gauge, and improve the disassembly efficiency of the staff. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is an axial side view of the wax mold group welding tool for the turbine blade disc of the aero-engine.

[0023] Figure 2 It is a blade perspective view of the wax mold group welding tool for the turbine blade disc of the aero-engine.

[0024] Figure 3 It is another angle axial side view of the wax mold group welding tool for the turbine blade disc of the aero-engine.

[0025] Figure 4 It is another angle axial side view of the wax mold group welding tool for the turbine blade disc of the aero-engine.

[0026] Figure 5 It is a dial gauge perspective sectional view of the wax mold group welding tool for the turbine blade disc of the aero-engine.

[0027] In the drawings: 1, disc; 2, limiting piece; 3, plug; 4, dial gauge; 5, groove body; 6, dial gauge; 7, spring rod; 8, blade; 9, rectangular square hole; 10, mounting rod; 11, installation slot; 12, plug rod; 13, clamping rod; 14, limiting groove. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all the embodiments.

[0029] In the description of the utility model, it needs to be understood that the orientation or position relation indicated by the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer" and the like is the orientation or position relation based on the orientation or position relation shown in the drawings, and is only for the convenience of describing the utility model and simplifying the description, and therefore cannot be understood as a limitation on the utility model.

[0030] The utility model discloses a kind of turbine blade wax mould group welding tool of aero-engine, mainly application existing power turbine blade as representative aero-engine high-temperature alloy integral blade, usually by thick disc and the scene of more than 40 thin-walled blades.

[0031] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 And Figure 5 , a kind of turbine blade wax mould group welding tool of aero-engine, including disc 1, the top center of disc 1 is equipped with slot 5, installation rod 10 is installed in the inside of slot 5, the top of installation rod 10 is rotatably connected with micrometer 4, one end of micrometer 4 is installed with dial gauge 6, further including splicing and welding mechanism: splicing and welding mechanism includes the limiting slot 14 being set at the outside of disc 1, one end of limiting slot 14 is inserted with limiting piece 2, the other end of limiting slot 14 is inserted with insert 3, the inside of disc 1 is clamped with blade 8, and one end of blade 8 is equipped with rectangular square hole 9;Disassembling mechanism: disassembling mechanism is set at one end of micrometer 4, and disassembling mechanism is used to assist staff to quickly disassemble and replace dial gauge 6.

[0032] In the present scheme, when staff splices and welds wax mould, staff can release the limiting connection formed by limiting piece 2 and insert 3 by successively disassembling limiting piece 2 installed at the top of limiting slot 14, and then successively draws out multiple inserts 3 from the inside of limiting slot 14, so that one end of insert 3 and blade 8 are released from limiting connection, and then blade 8 is taken upwards, so that rectangular square hole 9 formed at one end of blade 8 and boss are released from limiting connection, and simultaneously by setting disassembling mechanism, staff can be assisted to quickly disassemble and replace dial gauge 6, to improve the efficiency of staff disassembly.

[0033] Among them, referring to Figure 1 And Figure 5 , in a preferred embodiment, the disassembling mechanism includes installation slot 11 set at one end of micrometer 4, spring rod 7 is slidably connected in the inside of installation slot 11, one end of spring rod 7 is fixedly connected with installation assembly for assisting disassembly, and the bottom end of dial gauge 6 is fixedly connected with inserting rod 12.

[0034] In the scheme, by setting the disassembly mechanism, the staff can make the spring rod 7 slide and release the limiting of the plug rod 12, take out the plug rod 12 from the inside of the installation slot 11, and disassemble the micrometer 6 with the plug rod 12 fixedly connected at the bottom end.

[0035] Further, referring to Figure 1 and Figure 5 In a preferred embodiment, the mounting assembly includes a clamping rod 13 arranged at one end of the spring rod 7, and the micrometer 4 is provided with a through slot on both upper and lower sides, which is penetrated with the inside of the installation slot 11. By setting the mounting assembly, the efficiency of the staff in disassembling the micrometer 6 can be improved.

[0036] Among them, referring to Figure 2 and Figure 4 In a preferred embodiment, the plug rod 12 is provided with a plug hole at one end, and the size of the plug hole is matched with the size of the clamping rod 13. By setting the plug hole, the staff can quickly disassemble and replace the micrometer 6.

[0037] Further, referring to Figure 3 and Figure 4 In a preferred embodiment, the blade 8 is provided with a leaf tip conical round hole aligned with the thimble, and the blade 8 is positioned at the height and circumferential direction of the wheel disc 1. By setting the leaf tip conical round hole, the staff can quickly disassemble and replace the plurality of blades 8.

[0038] Among them, referring to Figure 1 and Figure 2 In a preferred embodiment, the wheel disc 1 is provided with a boss on the inside, and the size of the boss is matched with the size of the rectangular square hole 9. By setting the boss and the rectangular square hole 9, the staff can assist in clamping and installing the blade 8.

[0039] Working principle: when the staff is welding the wax mold;

[0040] Firstly, the staff can disassemble the limiting piece 2 installed at the top end of the limiting slot 14 in sequence, release the limiting connection formed by the limiting piece 2 and the plug-in 3, and then take out the plurality of plug-ins 3 from the inside of the limiting slot 14 in sequence, so that one end of the plug-in 3 is released from the limiting connection with the blade 8, and then the blade 8 is taken upward, so that the rectangular square hole 9 provided at one end of the blade 8 is released from the limiting connection with the boss;

[0041] Then, the staff can make the spring rod 7 slide in the through slot by sliding the spring rod 7 through the installation slot 11, and make the clamping rod 13 fixedly connected to the inner side of the spring rod 7 from the insertion hole opened at one end of the insertion rod 12, so as to remove the insertion of the insertion rod 12, take out the insertion rod 12 from the inside of the installation slot 11, and disassemble the micrometer 6 with the insertion rod 12 fixedly connected to the bottom end.

[0042] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this. The replacement can be the replacement of part of the structure, device, method step, or the complete technical solution. According to the technical solution and the utility model concept of the present application, equivalent replacement or change should be covered in the protection scope of the present application.

Claims

1. An aero-engine turbine blade and disc wax mold assembly welding tool, comprising a wheel disc (1), a groove (5) is formed at the top center of the wheel disc (1), an installation rod (10) is installed inside the groove (5), a micrometer (4) is rotationally connected to the top end of the installation rod (10), and a micrometer gauge (6) is installed at one end of the micrometer (4), characterized in that, Also include: Splicing mechanism: the splicing mechanism includes a limiting slot (14) arranged outside the wheel disc (1), one end of the limiting slot (14) is inserted into a limiting piece (2), the other end of the limiting slot (14) is inserted into an insert (3), the inner side of the wheel disc (1) is clamped with a blade (8), one end of the blade (8) is provided with a rectangular square hole (9); Disassembling mechanism: the disassembling mechanism is arranged at one end of the micrometer (4), and is used for assisting workers to quickly disassemble and replace the micrometer (6).

2. The wax pattern assembling and welding tooling for a turbine disk of an aero-engine according to claim 1, characterized in that, The disassembling mechanism includes a mounting groove (11) arranged at one end of the micrometer (4), a spring rod (7) is slidably connected inside the mounting groove (11), one end of the spring rod (7) is fixedly connected with a mounting assembly for assisting disassembly, and a plug rod (12) is fixedly connected to the bottom end of the micrometer (6).

3. The wax pattern assembly welding tooling for a turbine blade and vane of a gas turbine engine of claim 2, wherein, The mounting assembly includes a clamping rod (13) arranged at one end of the spring rod (7), and through grooves are formed on the upper and lower sides of the micrometer (4), the through grooves and the interiors of the mounting grooves (11) are mutually penetrated.

4. The wax pattern assembly welding tooling for a turbine blade and disk of a gas turbine engine of claim 3, wherein, One end of the plug rod (12) is provided with a plug hole, and the size of the plug hole is matched with the size of the clamping rod (13).

5. The wax pattern assembly welding tooling for a turbine blade and vane of a gas turbine engine as defined in claim 4, wherein, The plug hole and the clamping rod (13) are arranged on the same center axis.

6. The wax pattern assembly welding tooling for a turbine blade and vane of a gas turbine engine of claim 5, wherein, The blade (8) adopts a needle alignment blade tip conical circular hole, and the blade (8) is located in the height and circumferential direction of the wheel disc (1).

7. The wax pattern assembly welding tooling for a turbine blade and vane of a gas turbine engine of claim 6, wherein, The inner side of the wheel disc (1) is provided with a boss, and the size of the boss is matched with the size of the rectangular square hole (9).

Images