CN115491634A - Device for preparing aluminized layer in inner cavity of blade of aero-engine - Google Patents
Device for preparing aluminized layer in inner cavity of blade of aero-engine Download PDFInfo
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- CN115491634A CN115491634A CN202211142001.0A CN202211142001A CN115491634A CN 115491634 A CN115491634 A CN 115491634A CN 202211142001 A CN202211142001 A CN 202211142001A CN 115491634 A CN115491634 A CN 115491634A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
- C23C10/34—Embedding in a powder mixture, i.e. pack cementation
- C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
- C23C10/48—Aluminising
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Abstract
The invention discloses a device for preparing an aluminized layer in an inner cavity of an aero-engine blade, which belongs to the technical field of aero-engine manufacturing and comprises an aluminum powder box, and a clamping plate and a cover plate which are arranged in the aluminum powder box at intervals from bottom to top, wherein a first through hole is formed in the side wall of the aluminum powder box between the clamping plate and the cover plate, a gas pipe adapter is arranged at the first through hole, a plurality of second through holes are formed in the clamping plate, a corundum pipe is arranged in each second through hole, and a third through hole aligned with the corundum pipe is formed in the cover plate. The device is used in cooperation with traditional simple and easy vapor phase aluminizing equipment, active aluminum generated by an aluminizing agent through a high-temperature reaction is directionally guided into a complex/narrow inner cavity of a blade through a corundum tube under the action of carrier gas, the aim of aluminizing the inner cavity is fulfilled, the problem of preparation of an aluminized layer of the complex/narrow inner cavity of the blade of an aircraft engine can be solved, and the prepared inner cavity aluminized layer has the advantages of compact structure, uniform thickness, low cost, low design and manufacturing difficulty, simplicity in operation and maintenance and the like.
Description
Technical Field
The invention relates to the technical field of manufacturing of aero-engines, in particular to a device for preparing an aluminized layer in an inner cavity of an aero-engine blade.
Background
The blade of the aeroengine is corroded by high-temperature gas in the using process, the inner cavity of the blade is widely provided with the aluminized layer in the manufacturing process to prolong the service life of the blade, oxidation-resistant and corrosion-resistant elements in the using process of the blade are gradually consumed along with the increase of the service life, the aluminized layer in the inner cavity of the blade is seriously degraded after a certain service life, the service life of the blade of the engine is seriously influenced, and therefore the aluminized layer needs to be restored again in the repairing process to achieve the purposes of protecting the blade base body and prolonging the service life of the blade. The inner cavity infiltration layer is widely prepared by adopting a CVA method abroad, the method is high in cost, equipment is controlled abroad, the purchasing difficulty is high, the period is long, the operation is complex, the production capacity is small, and the requirement for manufacturing or repairing of blades in large quantities is difficult to meet, so that the method is difficult to be widely applied to the manufacturing and repairing processes of the blades of the aero-engine.
Based on the difficulties, the inner cavity aluminized layer is generally not recovered in the maintenance process of the aviation engine blade in China, the service life of the blade is greatly reduced, the manufacturing and maintenance costs are increased, and in order to ensure the effective development of the inner cavity aluminized layer preparation technology, the inner cavity aluminized layer with uniform thickness and tissue is prepared, a device with low cost and simple operation needs to be designed and developed for preparing the inner cavity aluminized layer.
Disclosure of Invention
In order to overcome the defects of the preparation of the aluminized layer in the inner cavity of the blade of the conventional aircraft engine, the invention aims to solve the technical problems that: the simple and practical device for preparing the aluminized layer in the inner cavity of the blade of the aero-engine is provided.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a device for preparation of aeroengine blade inner chamber aluminized layer, including the aluminium powder box and from up the splint and the apron of interval setting in the aluminium powder box down, the aluminium powder box is equipped with first through-hole on the lateral wall between splint and apron, and first through-hole department is equipped with the trachea adapter, be equipped with a plurality of second through-holes on the splint, install the alundum pipe in the second through-hole, be equipped with the third through-hole that aligns with the alundum pipe on the apron.
Further, the aluminum powder box is formed by welding a side plate and a bottom plate which are enclosed into a cylinder shape.
Further, the welding has the round strengthening rib on the inner wall of aluminium powder box, splint are placed on the strengthening rib, the apron is fixed on splint through peripheral bracing piece.
Furthermore, the size of the third through hole meets the requirement that the cavity structure of the blade of the aero-engine can just penetrate through the third through hole, and when the aero-engine She Pianka is stably fixed on the cover plate, the lower end of the third through hole is just flush with the upper end of the corundum tube.
Furthermore, the corundum tubes on the clamping plate and the second through holes without the corundum tubes are uniformly arranged at intervals.
Further, a first positioning sleeve is arranged in a first through hole in the aluminum powder box, and the air pipe adapter is fixed at the first through hole in a sealing mode through the first positioning sleeve.
Furthermore, a second positioning sleeve is arranged in a second through hole in the clamping plate, and the corundum tube is fixed at the second through hole in a sealing mode through the second positioning sleeve.
Furthermore, the aluminum powder box, the clamping plate, the cover plate, the reinforcing ribs and the supporting rod are all made of GH3044 nickel-based high-temperature alloy.
The invention has the beneficial effects that:
(1) The device is matched with the traditional vapor phase aluminizing equipment, the aluminizing of the inner cavity of the blade can be realized by adopting the traditional aluminizing mode, complex and expensive equipment matching is not needed, and compared with the CVA technology, the device has the advantages of small design and manufacturing difficulty, low cost, simple operation and maintenance and the like;
(2) The device adopts an atmosphere directional drainage mode, realizes the preparation of the aluminized layer of the complicated/narrow inner cavity of the blade of the aero-engine, and can effectively achieve the purposes of protecting the blade matrix, improving the oxidation resistance and corrosion resistance of the blade of the aero-engine, prolonging the service life of the blade and reducing the manufacturing and maintenance cost of the blade;
(3) The device is used for preparing the inner cavity aluminized layer of the blade of the aero-engine, the inner cavity aluminized layer is compact in structure, uniform in thickness and high in controllability, and is suitable for similar inner cavity aluminizing processes.
Drawings
FIG. 1 is a schematic diagram of the present invention.
FIG. 2 is a schematic illustration of an aircraft engine blade placement of the present invention.
Marked in the figure as 1-aluminum powder box, 2-clamping plate, 3-cover plate, 4-air pipe adapter, 5-corundum tube, 6-supporting rod, 7-aircraft engine blade, 11-first through hole, 12-reinforcing rib, 13-first positioning sleeve, 21-second through hole, 22-second positioning sleeve and 31-third through hole.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, a device for preparation of aeroengine blade inner chamber aluminized layer, including aluminium powder box 1 and follow splint 2 and the apron 3 that up interval set up in aluminium powder box 1 down, aluminium powder box 1 is equipped with first through-hole 11 on the lateral wall between splint 2 and apron 3, and first through-hole 11 department is equipped with trachea adapter 4, be equipped with a plurality of second through-holes 21 on splint 2, install alundum pipe 5 in the second through-hole 21, be equipped with the third through-hole 31 that aligns with alundum pipe 5 on the apron 3.
The aluminizing process of the invention comprises the following steps:
the method comprises the following steps: mixing the aluminizing penetrant according to a proportion and then spreading the mixture in the aluminum powder box 1;
step two: mounting the clamping plate 2, the cover plate 3, the air pipe adapter 4, the corundum tube 5 and other parts;
step three: a small amount of penetrating agent is paved on the splint 2;
step four: the protective atmosphere air inlet pipe is connected through an air pipe adapter 4;
step five: the aero-engine blade 7 is installed on the cover plate 3 in a mode that the tip of the blade is downward, namely the blade has an inner cavity downward, the blade is placed in the third through hole 31 of the cover plate 3, and the inner cavity of the blade is aligned to the corundum tube 5 as much as possible;
step six: the whole device is placed in a high-temperature environment for heating, and under the flowing action of protective gas, the corundum tube 5 directionally guides active aluminum atmosphere generated by a high-temperature penetrating agent in the aluminum powder box 1 into the inner cavity of the blade to realize inner cavity aluminizing.
In order to improve the use efficiency of the equipment, the inner cavity aluminizing is preferably carried out on a plurality of aero-engine blades 7 at the same time, so the size of the aluminum powder box 1 needs to be designed to be a little larger, and for convenience of manufacture, the aluminum powder box 1 is formed by welding a side plate and a bottom plate which are enclosed into a cylindrical shape.
To splint 2 and apron 3's installation, in order to overhaul the maintenance and place the penetrant for convenient dismantlement the welding has round strengthening rib 12 on the inner wall of aluminium powder box 1, splint 2 is placed on strengthening rib 12, apron 3 is fixed on splint 2 through peripheral bracing piece 6, specifically can adopt welding or screw connection etc. take off splint 2 and apron 3 when can be very convenient like this.
In order to prolong the service life of the device, the aluminum powder box 1, the clamping plate 2, the cover plate 3, the reinforcing ribs 12 and the supporting rod 6 are preferably made of GH3044 nickel-based high-temperature alloy.
As shown in fig. 2, for the third through hole 31, the size of the third through hole 31 is such that the cavity structure of the aero-engine blade 7 can just penetrate through the third through hole 31, and when the aero-engine blade 7 is clamped and stabilized on the cover plate 3, the lower end of the third through hole is just flush with the upper end of the corundum tube 5, or a small part of the upper end of the corundum tube 5 can be inserted into the cavity. Thus, the overflow of gas can be reduced and the aluminizing effect can be improved.
Furthermore, corundum tube 5 on splint 2 and the even interval setting of second through-hole 21 that does not install corundum tube 5 can guarantee that protective gas can evenly get into the bottom of aluminium powder box 1 to drive active aluminium atmosphere and evenly get into corundum tube 5.
Because the aluminum powder box 1 and the clamping plate 2 are thin, in order to fix the air pipe adapter 4 and the corundum tube 5 well, a first positioning sleeve 13 is arranged in a first through hole 11 on the aluminum powder box 1, and the air pipe adapter 4 is fixed at the first through hole 11 in a sealing manner through the first positioning sleeve 13; and a second positioning sleeve 22 is arranged in a second through hole 21 on the clamping plate 2, and the corundum tube 5 is sealed and fixed at the second through hole 21 through the second positioning sleeve 22. First position sleeve 13 and second position sleeve 22 can adopt the flexible glue material that has certain thickness, and trachea adapter 4 and corundum pipe 5 directly insert respectively and establish in first position sleeve 13 and second position sleeve 22, can play sealed fixed action, can conveniently regularly take off again and wash the maintenance.
The foregoing is illustrative of the preferred embodiments of this invention, and it is to be understood that the invention is not limited to the precise form disclosed herein and that various other combinations, modifications, and environments may be resorted to, falling within the scope of the concept as disclosed herein, either as described above or as apparent to those skilled in the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A device for preparation of aluminized layer in aircraft engine blade inner chamber, characterized by: including aluminium powder box (1) and from down splint (2) and apron (3) that up interval set up in aluminium powder box (1), aluminium powder box (1) is equipped with first through-hole (11) on the lateral wall between splint (2) and apron (3), and first through-hole (11) department is equipped with trachea adapter (4), be equipped with a plurality of second through-holes (21) on splint (2) to install alundum pipe (5) in partial second through-hole (21), be equipped with third through-hole (31) that align with alundum pipe (5) on apron (3).
2. The apparatus for the preparation of aluminized layers for aeroengine blades according to claim 1, characterized in that: the aluminum powder box (1) is formed by welding a side plate and a bottom plate which are enclosed into a cylinder shape.
3. The device for preparing the aluminized layer on the inner cavity of the aircraft engine blade according to claim 1, characterized in that: the welding has round strengthening rib (12) on the inner wall of aluminium powder box (1), place on strengthening rib (12) splint (2), apron (3) are fixed on splint (2) through peripheral bracing piece (6).
4. The device for preparing the aluminized layer on the inner cavity of the aircraft engine blade according to claim 1, characterized in that: the size of the third through hole (31) meets the requirement that the cavity structure of the aero-engine blade (7) can just penetrate through the third through hole (31), and when the aero-engine blade (7) is clamped and stabilized on the cover plate (3), the lower end of the third through hole is just flush with the upper end of the corundum tube (5).
5. The device for preparing the aluminized layer on the inner cavity of the aircraft engine blade according to claim 1, characterized in that: the corundum tubes (5) on the clamping plate (2) and the second through holes (21) without the corundum tubes (5) are uniformly arranged at intervals.
6. The device for preparing the aluminized layer on the inner cavity of the aircraft engine blade according to claim 1, characterized in that: be equipped with first positioning sleeve (13) in first through-hole (11) on aluminium powder box (1), trachea adapter (4) are sealed to be fixed in first through-hole department (11) through first positioning sleeve (13).
7. The device for preparing the aluminized layer on the inner cavity of the aircraft engine blade according to claim 1, characterized in that: a second positioning sleeve (22) is arranged in a second through hole (21) which is used for installing the corundum tube (5) on the clamping plate (2), and the corundum tube (5) is hermetically fixed at the second through hole (21) through the second positioning sleeve (22).
8. The device for preparing the aluminized layer on the inner cavity of the aircraft engine blade according to claim 3, characterized in that: the aluminum powder box (1), the clamping plate (2), the cover plate (3), the reinforcing ribs (12) and the supporting rod (6) are all made of GH3044 nickel-based high-temperature alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211142001.0A CN115491634A (en) | 2022-09-20 | 2022-09-20 | Device for preparing aluminized layer in inner cavity of blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211142001.0A CN115491634A (en) | 2022-09-20 | 2022-09-20 | Device for preparing aluminized layer in inner cavity of blade of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115491634A true CN115491634A (en) | 2022-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211142001.0A Pending CN115491634A (en) | 2022-09-20 | 2022-09-20 | Device for preparing aluminized layer in inner cavity of blade of aero-engine |
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|---|---|
| CN (1) | CN115491634A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002047567A (en) * | 2000-07-28 | 2002-02-15 | Mitsubishi Heavy Ind Ltd | Thermal cvd treatment method |
| US20110293825A1 (en) * | 2009-02-18 | 2011-12-01 | Rolls-Royce Plc | Method and an arrangement for vapour phase coating of an internal surface of at least one hollow article |
| CN102978565A (en) * | 2012-11-20 | 2013-03-20 | 西安航空动力股份有限公司 | Seepage prevention method and fixture for aerial engine blade rabbet |
| CN103600053A (en) * | 2013-12-06 | 2014-02-26 | 湖南航天诚远精密机械有限公司 | Accurate forming tool of aluminum silicon carbide composite IGBT (insulated gate bipolar translator) baseplate |
| EP3527686A1 (en) * | 2018-02-15 | 2019-08-21 | MTU Aero Engines GmbH | Device and method for gas phase coating of workpieces |
| CN211170845U (en) * | 2019-11-12 | 2020-08-04 | 武汉铭高新材料有限公司 | Calorization heat treatment furnace convenient for placing workpieces |
| CN112430802A (en) * | 2020-10-09 | 2021-03-02 | 北京航空航天大学 | Method and device for cleaning fluorine ions of blades with complex inner cavities and preparing aluminide coatings |
| CN213803952U (en) * | 2020-11-24 | 2021-07-27 | 沈阳梅特科航空科技有限公司 | Vapor phase aluminizing device for outer surface of workpiece |
-
2022
- 2022-09-20 CN CN202211142001.0A patent/CN115491634A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002047567A (en) * | 2000-07-28 | 2002-02-15 | Mitsubishi Heavy Ind Ltd | Thermal cvd treatment method |
| US20110293825A1 (en) * | 2009-02-18 | 2011-12-01 | Rolls-Royce Plc | Method and an arrangement for vapour phase coating of an internal surface of at least one hollow article |
| CN102978565A (en) * | 2012-11-20 | 2013-03-20 | 西安航空动力股份有限公司 | Seepage prevention method and fixture for aerial engine blade rabbet |
| CN103600053A (en) * | 2013-12-06 | 2014-02-26 | 湖南航天诚远精密机械有限公司 | Accurate forming tool of aluminum silicon carbide composite IGBT (insulated gate bipolar translator) baseplate |
| EP3527686A1 (en) * | 2018-02-15 | 2019-08-21 | MTU Aero Engines GmbH | Device and method for gas phase coating of workpieces |
| CN211170845U (en) * | 2019-11-12 | 2020-08-04 | 武汉铭高新材料有限公司 | Calorization heat treatment furnace convenient for placing workpieces |
| CN112430802A (en) * | 2020-10-09 | 2021-03-02 | 北京航空航天大学 | Method and device for cleaning fluorine ions of blades with complex inner cavities and preparing aluminide coatings |
| CN213803952U (en) * | 2020-11-24 | 2021-07-27 | 沈阳梅特科航空科技有限公司 | Vapor phase aluminizing device for outer surface of workpiece |
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