1. A heat treatment apparatus for an aircraft engine blade, comprising: the device comprises a storage rack (10) and a plurality of blade brackets (20) arranged on the storage rack (10) at intervals;

blade holder (20) include with deposit guide rail (21) that frame (10) are connected and slide respectively and set up adapter (22) and dog (23) on guide rail (21), adapter (22) with dog (23) include respectively with guide rail (21) sliding fit's sliding part (19) and connect portion (18) of suspending in the midair of sliding part (19) below, adapter (22) with dog (23) are big-end-up's echelonment, portion (18) of suspending in the midair of adapter (22) seted up with engine blade tenon complex tongue-and-groove (24).

2. The heat treatment device for aeroengine blades according to claim 1, characterized in that the side walls of the mortise (24) are inclined and are provided with a first projection (17) and a second projection (16) for clamping with the engine blade tenon.

3. The heat treatment device for aircraft engine blades according to claim 2, characterized in that the adapter (22) is arranged adjacent to the stop (23), and the guide rail (21) is provided at its two ends with a stop plate (25) and a stop pin (26), respectively.

4. The heat treatment device for aircraft engine blades according to claim 3, characterized in that the sliding part (19) of the adapter (22) is provided with a threaded hole (27) along the extension direction of the guide rail (21), the stop block (23) is further provided with a countersunk hole (28) corresponding to the threaded hole (27), and the threaded hole (27) and the countersunk hole (28) are connected through a countersunk screw.

5. The heat treatment device for aircraft engine blades according to claim 4, characterized in that the suspension (18) of the adapter (22) is provided with through holes (30) communicating with the mortise (24), and the through holes (30) are respectively snap-fitted with a top block (31).

6. Heat treatment device for aircraft engine blades according to claim 5, characterised in that the overhang (18) of the stop (23) is provided with a nose (32), the nose (32) being inclined close to both faces of the adapter (22).

7. The heat treatment device for aircraft engine blades according to claim 6, characterized in that said guide rail (21) has a plurality of pin holes (33) fitted to said stop pins (26).

8. The heat treatment device for aeroengine blades according to any one of claims 1 to 7, characterized in that said storage rack (10) comprises a plurality of fixed plates (11) connected to said guide rails (21) and support rods (12) connected between said fixed plates (11).

9. The heat treatment device for aeroengine blades according to claim 8, characterized in that a lifting ring (13) is connected to the top surface of the storage frame (10).

10. The heat treatment device for aeroengine blades according to claim 9, characterized in that a plurality of flow-guiding holes (14) are provided in the fixing plate (11).

Background

The low-pressure turbine blade has the characteristics of multiple types, high precision, complex part structure, high cost and difficult material processing, and the vacuum heat treatment technology is a key technology for manufacturing the turbine blade. At present, the suspension type grid structure is adopted when the heat treatment tool is designed domestically, and air flow impacts the blades when the blades are subjected to heat treatment, so that the blades shake, adjacent blades are likely to collide or the blades collide with the clamp, the performance of the blades is affected, and the heat treatment rejection rate is high. Therefore, the problem that the heat treatment device for the blades of the aircraft engine is inconvenient to use exists in the prior art.

Disclosure of Invention

The invention aims to provide a heat treatment device for an aircraft engine blade, which solves the problem that the existing heat treatment device for the aircraft engine blade is inconvenient to use.

The technical scheme for solving the technical problems is as follows:

a heat treatment apparatus for an aircraft engine blade, comprising: the blade storage device comprises a storage rack and a plurality of blade brackets which are arranged on the storage rack at intervals;

the blade support includes and deposits the guide rail that the frame is connected and slide adapter and the dog that sets up on the guide rail respectively, adapter and baffle include respectively with guide rail sliding fit's sliding part and connect the portion of suspending in midair in the sliding part below, adapter and dog are big-end-up's echelonment, the portion of suspending in midair of adapter offer with engine blade tenon complex tongue-and-groove.

The tenon of the engine blade is placed in the mortise of the adapter, the adapter and the stop block are sequentially placed in the guide rail in a sliding manner, the tenon of the engine blade is fixed through the contact fit of the mortise and the tenon, so that the engine blade is suspended and fixed, the surface area of contact with heat treatment airflow is increased, the stop block is used for fixing the position of the adapter, the engine blade is prevented from easily sliding in the guide rail, the distance between the engine blades is increased, the blade part cannot easily shake during heat treatment, the heat treatment effect is ensured, and the problem that the conventional aero-engine blade heat treatment device is inconvenient to use is solved.

Furthermore, the side wall of the mortise is inclined, and a first protrusion and a second protrusion which are clamped with the engine blade tenon are arranged on the side wall.

The mortise is provided with the first protrusion and the second protrusion to be used for clamping the engine blade tenon, so that the engine blade can be stably fixed in the mortise.

Furthermore, the adapter and the stop block are arranged adjacently, and the two ends of the guide rail are respectively provided with the baffle and the stop pin.

The two ends of the guide rail are provided with the baffle plates and the stop pins, so that the stop blocks at the two ends are prevented from sliding out, the two sides of each adapter are respectively provided with the stop blocks, and the phenomenon that the adapter is directly contacted to cause abrasion is avoided, so that the fixing effect of the mortise on the tenon of the engine blade is influenced.

Furthermore, the sliding part of the adapter is provided with a screw hole along the extending direction of the guide rail, the stop block is further provided with a counter bore corresponding to the screw hole, and the screw hole is connected with the counter bore through a counter screw.

The adapter and the stop block are respectively provided with a screw hole and a countersunk hole and are fixedly connected through countersunk screws, so that the fixed position between the connected adapter and the stop block is ensured; avoid connecting the back through setting up the counter sink and cause the influence to the adapter of opposite side.

Further, the suspension part of the adapter is provided with a through hole communicated with the mortise, and the through holes are respectively clamped with a top block.

The through holes are formed in the two sides of the mortise and are clamped with the jacking blocks to jack the engine blade tenon in the mortise, so that the abrasion of the mortise and the increase of the clearance between the mortise and the engine blade tenon after multiple use are avoided.

Furthermore, the suspension part of the stop block is also provided with a raised head, and the two surfaces of the raised head close to the adapter are inclined.

Two sides of the raised head are inclined, so that the raised head can be conveniently matched with two inclined side surfaces of adjacent engine blade tenons, and a fixed distance is kept between the top of the stop block and the adapter.

Furthermore, a plurality of pin holes matched with the stop pins are formed in the guide rail.

The guide rail is provided with the plurality of pin holes, so that when the number of the engine blades needing heat treatment is small, the stop pin can be directly moved to be matched with the proper pin hole, and the phenomenon that too many idle adapters and stop blocks are placed to influence the loading and unloading time is avoided.

Furthermore, the storage rack comprises a plurality of fixing plates connected with the guide rails and supporting rods connected between the fixing plates.

The supporting rods are connected with the fixing plates, so that a certain distance is kept between the fixing plates, and the engine blades can be conveniently suspended.

Furthermore, the top surface of the storage rack is connected with a hanging ring.

The invention can conveniently suspend and move the integral storage rack through the lifting ring.

Furthermore, a plurality of flow guide holes are formed in the fixing plate.

The invention increases the airflow among the plurality of fixed plates by arranging the flow guide holes, thereby improving the heat treatment efficiency.

The invention has the following beneficial effects:

the tenon of the engine blade is placed in the mortise of the adapter, the adapter and the stop block are sequentially and adjacently placed in the guide rail, the tenon of the engine blade is fixed through the contact fit of the mortise and the tenon, the engine blade is suspended, the surface area of contact with heat treatment airflow is increased, the stop block is used for fixing the position of the adapter, the stop block is prevented from easily sliding in the guide rail, the distance between the engine blades is increased, the blade part cannot easily shake during heat treatment, the heat treatment effect is ensured, and the problem that the existing aero-engine blade heat treatment device is inconvenient to use is solved.

Drawings

FIG. 1 is a schematic structural view of a heat treatment apparatus for an aircraft engine blade according to the present invention;

FIG. 2 is a schematic view of a blade support of the present invention;

figure 3 is a schematic structural view of an adapter and a top block of the present invention;

FIG. 4 is a schematic view of the structure of the stopper of the present invention;

FIG. 5 is a schematic diagram of a structure of an engine blade.

In the figure: 10-a storage rack; 11-a fixed plate; 12-a support bar; 13-a hoisting ring; 14-diversion holes; 16-a second protrusion; 17-a first projection; 18-a suspension; 19-a slide; 20-a blade support; 21-a guide rail; 22-an adapter; 23-a stopper; 24-a tongue and groove; 25-a baffle plate; 26-a stop pin; 27-screw hole; 28-counter sink; 30-a through hole; 31-a top block; 32-nose; 33-pin hole.

Detailed Description

The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.

Examples

Referring to fig. 1, a heat treatment apparatus for an aircraft engine blade includes a storage rack 10 and a plurality of blade holders 20 spaced apart on the storage rack 10.

Deposit frame 10 and include a plurality of fixed plates 11 and set up bracing piece 12 between fixed plate 11, a plurality of connecting holes have been seted up on fixed plate 11 for connect fixed blade support 20, and fixed plate 11 is close to central point and puts the fretwork, and has seted up four water conservancy diversion holes 14, thereby gas flow when being convenient for heat treatment avoids solid fixed plate 11 to cause the wall to the thermal treatment air current, thereby causes the influence to thermal treatment effect. The top surface of the top fixing plate 11 is connected with a hanging ring 13, and the integral storage rack 10 can be conveniently suspended and moved through the hanging ring 13.

Referring to fig. 1 and 2, the blade mount 20 includes a guide rail 21 connected to the fixing plate 11, and an adapter 22 and a stopper 23 slidably disposed on the guide rail 21, respectively, the opening of the guide rail 21 faces downward, and the adapter 22 and the stopper 23 include a sliding portion 19 slidably engaged with the guide rail 21, and a suspending portion 18 connected below the sliding portion 19, respectively, so that the adapter 22 and the stopper 23 are stepped in a large-small manner, thereby facilitating the suspension on the guide rail 21. The suspension part 18 of the adapter 22 is provided with a mortise 24 matched with the tenon of the engine blade, the side wall of the mortise 24 is inclined, and is provided with a first bulge 17 and a second bulge 16 which are clamped with the tenon of the engine blade, so that the inner wall of the mortise 24 is matched with the shape of the tenon of the engine blade, and the engine blade can be fixedly suspended below the adapter 22 through the matching of the tenon and the mortise 24 as well as the first bulge 17 and the second bulge 16. Stop blocks 23 are respectively arranged on two sides of the adapter 22, and the adapter 22 and the stop blocks 23 are adjacently arranged, so that a plurality of engine blades can be conveniently placed, abrasion caused by direct contact between the adapter 22 can be avoided, and a certain fixed gap is reserved between the engine blades which are close to each other.

Referring to fig. 2, 3 and 4, the sliding portion 19 of the adapter 22 is provided with a screw hole 27 along the extending direction of the guide rail 21, the stopper 23 is also provided with a counter bore 28 corresponding to the screw hole 27 along the extending direction of the guide rail 21, the screw hole 27 and the counter bore 28 are connected by a counter screw, so that the position between the adapter 22 and the stopper 23 is ensured to be fixed, and the head of the counter screw is placed in the counter bore 28 to avoid affecting the adapter 22 on the other side. Through-hole 30 with the tongue-and-groove 24 intercommunication is seted up to the lateral wall of the portion of suspending 18 of adapter 22 to through-hole 30 joint respectively has kicking block 31, and kicking block 31 is used for pushing up tightly the engine blade tenon, thereby avoids causing wearing and tearing after tongue-and-groove 24 uses for a long time and lead to and the engine blade tenon between the clearance increase. The bottom of the stop 23 is also provided with a raised head 32, the two surfaces of the raised head 32 close to the adapter 22 are inclined, and the inclined surfaces are matched with the two side surfaces of the engine blade tenon, so that a fixed distance is kept between the top of the stop 23 and the adapter 22.

The two ends of the guide rail 21 are respectively provided with a baffle 25 and a baffle pin 26 for limiting the stop 23 on the guide rail 21 and preventing the stop 23 at the two ends of the guide rail 21 from sliding out. The guide rail 21 is provided with a plurality of threaded holes fixedly connected with the fixing plate 11 and a plurality of pin holes 33 matched with the stop pin 26, and when the number of the engine blades needing heat treatment is small, the stop pin 26 can be directly moved to be matched with the proper pin holes 33, so that the phenomenon that too many idle adapters 22 and the stop blocks 23 are placed to influence the assembling and disassembling time is avoided.

The operation process of the invention is as follows: (1) placing the engine blade tenon needing heat treatment into the mortise 24; (2) the adapter 22 and the stop block 23 are connected through countersunk screws; (3) sequentially placing the adapter 22 and the stop block 23 into the guide rail 21, and mounting the top block 31 to enable the engine blade to be in a suspension state; (4) the baffle plate 25 and the stop pin 26 are respectively used for limiting the stop blocks 23 at the two ends; (5) moving the storage rack 10 to a heat treatment area through the hanging ring 13 for heat treatment; (6) taking out the storage rack 10 after the heat treatment is finished; (7) disassembling the stop pin 26, and sequentially disassembling the adapter 22 and the stop block 23; (8) the top block 31 is released and the tenon of the engine blade is taken out of the mortise 24.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.