CN217097318U - Machining auxiliary mechanism for aero-engine blade - Google Patents

Abstract

The utility model relates to a processing auxiliary mechanism for an aircraft engine blade, which comprises an upper cover and a lower box body; the upper cover is provided with a bin which is provided with a sand blasting nozzle; a left clamping structure and a right clamping structure are arranged in the lower box body, and the left clamping structure and the right clamping structure are provided with hollow plugs; when the left and right clamping structures clamp the aero-engine blade, the hollow plug is communicated with a channel cavity which is communicated with the left and right of the aero-engine blade, and the channel cavity is connected with a pump through a pump pipeline; and the small hole of the passage of the blade of the aircraft engine is opposite to the sand blasting nozzle on the storage bin, high pressure is formed in the storage bin, and the grinding fluid and the grinding material are sprayed by the sand blasting nozzle. The utility model discloses the beneficial effect who reaches is: two processing modes of flow processing and jet processing are formed, and the processing effect is good.

Description

Machining auxiliary mechanism for aero-engine blade

Technical Field

The utility model relates to an aeroengine blade processing technology field especially is used for processing complementary unit of aeroengine blade.

Background

The blade of an aero-engine of a certain model is provided with a plurality of small passage holes; after the initial machining is completed, in order to prevent peeled objects (such as burrs and curls) from falling off and causing clogging, thereby affecting the performance of the whole engine, further finishing treatment of the small holes of the passages is required.

At present, the better treatment mode in the field is quicksand treatment, namely burrs and curled edges in or of small holes of the channels are ground through the flowing of grinding sand, so that the finishing effect is achieved.

Although the existing method can also achieve certain processing effect and meet certain process requirements, the effect is not particularly ideal. The main reason is that abrasive sand, unlike liquids, is easily clogged during flow and therefore only provides good grinding of the surface (to some extent the orifices of the passage holes), but not the interior of the passage holes.

Therefore, a novel processing auxiliary mechanism is designed, adjustment is carried out on the process, the structure can realize two grinding modes of spraying and flowing, and the grinding auxiliary mechanism plays a very excellent grinding role on the surface of the blade of the aircraft engine and most importantly on small holes of a channel.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to overcome prior art's shortcoming, provide and form mobile processing and spray two kinds of processing methods, process effectual a processing complementary unit for aeroengine blade.

The purpose of the utility model is realized through the following technical scheme: a processing complementary unit for aeroengine blade has the passageway chamber that runs through about having in the aeroengine blade, and aeroengine blade upper surface is opened has a plurality of passageway apertures, and a plurality of passageway apertures link to each other with the passageway chamber, include:

the lower box body is internally provided with a left clamping structure and a right clamping structure;

an upper cover having a bin thereon;

the left and right clamping structures are provided with hollow plugs; after the left and right clamping structures clamp the aero-engine blade from the left side and the right side, the hollow plug is in butt joint with the channel cavity;

the hollow plug is connected with a pump through a pump-out pipeline;

after the upper cover and the lower box body are buckled: the grinding material in the storage bin firstly falls on the upper surface of the aeroengine blade, then flows through the small channel hole, the channel cavity and the pumping-out pipeline, and the finishing processing of the small channel hole is realized.

Furthermore, a front clamping structure and a rear clamping structure are also arranged in the lower box body; the front and rear clamping structures are provided with splicing blocks; the left and right clamping structures are provided with assembling plates; after the left clamping structure and the right clamping structure clamp the aero-engine blade, the splicing blocks and the splicing plates are assembled into a rectangular frame; the abrasive in the bin falls into the rectangular frame to form a structure for preventing the abrasive from overflowing.

Furthermore, the material bin is filled with abrasive and grinding fluid; the pumping pipeline is communicated with the storage bin through a pumping pump; under the action of the pump, the grinding materials and the grinding fluid fall onto the upper surface of the aero-engine blade through the bin and are gathered together by the assembled rectangular frame ring, and then return to the bin again after sequentially passing through the small channel hole, the pump pipeline and the pump to form circulation. Grinding is realized by the grinding materials and the grinding liquid together, and a circulation route is formed by corresponding pipelines and pumps, so that small holes of the passage of the blade of the aircraft engine are fully processed.

Furthermore, when the upper cover and the lower box body are buckled, a sealing gasket is arranged at the buckling position of the upper cover and the lower box body; when the upper cover is buckled with the lower box body, the material bin is abutted against the rectangular frame to form butt joint.

Furthermore, the top of the storage bin is provided with a feeding pipe, and a bottom plate is arranged in the storage bin; the upper surface of the bottom plate is sunken, and a plurality of sand blasting nozzles are arranged on the bottom plate; and the grinding materials and the grinding fluid in the storage bin are sprayed on the aeroengine blades through a sand spraying nozzle. Preferably, the blast nozzle is a simple pipe.

Furthermore, the left and right clamping structure also comprises a clamping block, a slide rail, a cylinder A and a spring; the clamping block is connected with the left wall of the lower box body through an air cylinder A and a spring respectively; the front surface and the rear surface of the clamping block are matched with the slide rail to form limiting; the clamping block is provided with an assembling plate; the inner side surface of the clamping block is provided with a hollow plug, the lower surface of the clamping block is provided with a drawing pipeline, and a cavity channel is formed in the clamping block; the hollow plug is connected with a drawing pipeline through a cavity; the drawing pipeline penetrates out of the lower box body and is sealed by glue, and the middle part of the drawing pipeline is a flexible pipe.

Furthermore, the front and rear clamping structures comprise splicing blocks and air cylinders B; the splicing block is connected with the front wall and the rear wall of the lower box body through a cylinder B; the assembling blocks are provided with assembling grooves matched with the assembling plates.

Furthermore, the bottom of the lower box body is also provided with a water draining nozzle in a threaded mode, and in the process of circulating the grinding materials and the grinding fluid, as the bottom surface of the combined rectangular frame is not sealed, some fluid and a small amount of grinding materials can flow to the bottom surface in the lower box body, and the water draining nozzle can drain the fluid and the small amount of grinding materials. And the inner bottom surface of the lower box body is provided with a supporting block for placing an aircraft engine blade.

Furthermore, the upper cover is provided with a positioning column, and the lower box body is provided with a positioning hole matched with the positioning column; the upper cover and the lower box body are both provided with handles; the lower box body is provided with supporting legs.

The structure of the scheme realizes the processing in the form of grinding material and grinding fluid; the grinding fluid does not add a small amount of fluid to the grinding material, but rather a large amount of grinding fluid is used to add the grinding material to the grinding fluid. Through the pump, the grinding fluid drives the grinding material to flow in the small hole of the channel, thereby achieving the grinding effect (namely the flow processing mode) in the small hole of the channel. Certainly, some booster pumps can be arranged to generate high pressure in the storage bin, and under the action of high pressure, grinding fluid and abrasive in the storage bin are sprayed out together and sprayed to the position of the small hole of the channel, so that the edge of the small hole of the channel is machined, and the surface of the blade of the aero-engine can be machined (namely, a spraying machining mode).

In addition, during machining, the upper cover and the lower box body are buckled to form a whole, the whole is sealed, and the reason for the sealing is that a part of grinding fluid enters the lower box body and may overflow. Certainly, in order to make the processing effect of the flow processing mode and the injection processing mode better, some switch valves can be selectively arranged on the upper cover, so that the air circulation in the whole body is facilitated.

The utility model has the advantages of it is following:

(1) compared with the traditional processing mode of pure abrasive sand, the structure of the scheme realizes the processing mode that the grinding fluid drives the abrasive to flow, namely, the jet processing is formed through the sand blasting nozzle, and the flow processing is formed through the butt joint of the hollow plug and the channel cavity, so that the excellent processing effect is achieved;

(2) control the centre gripping structure: the hollow plugs are arranged to realize butt joint, namely a flow path is formed; the arrangement of the spring realizes the primary clamping of the blade of the aero-engine, the blade is convenient to place, and the cylinder A realizes the further clamping, so that the sealing performance is ensured; the arrangement of the slide rail enables the clamping block to accurately move along the left and right directions during clamping;

(3) the front and back clamping structures and the left and right clamping structures form a rectangular frame, so that excessive grinding materials are prevented from overflowing (grinding fluid cannot be prevented, but the grinding materials are mainly used for processing small holes of the channel), and a good processing effect of the small holes of the channel is ensured;

(4) the setting of sand blasting nozzle in the feed bin, when the feed bin formed high pressure, sand blasting nozzle can spout highly compressed grinding fluid + abrasive material, forms and sprays processing.

Drawings

FIG. 1 is a schematic view of the left and right clamping structures of the present invention;

FIG. 2 is a schematic view of the left and right clamping structures and the front and rear clamping structures of the present invention;

FIG. 3 is a schematic top view of a lower housing having left and right clamp structures, and front and rear clamp structures;

FIG. 4 is a schematic top view of a lower case with left and right clamp structures, front and rear clamp structures during clamping;

FIG. 5 is a schematic bottom view of the upper cover;

FIG. 6 is a schematic structural view of the arrangement of the clamping block, the assembled plate, the hollow plug, and the pump-out pipe;

FIG. 7 is a schematic structural view of a building block;

FIG. 8 is a microscope image of a corresponding blade after being processed with an ordinary abrasive only;

FIG. 9 is a microscope image of the corresponding blade after being processed by the scheme;

FIG. 10 is a schematic structural view of an aircraft engine blade;

in the figure: 1-an aircraft engine blade, 101-a channel small hole, 102-a channel cavity, 2-a lower box body, 201-a water discharging nozzle, 3-an upper cover, 301-a positioning column, 4-a left and right clamping structure, 401-a hollow plug, 402-a drawing-off pipeline, 403-an assembling plate, 404-a clamping block, 405-a sliding rail, 406-an air cylinder A, 407-a spring, 5-a storage bin, 501-a bottom plate, 502-a sand blasting nozzle, 6-a front and back clamping structure, 601-an assembling block, 602-an air cylinder B, 7-a sealing gasket, 8-a supporting block and 9-a handle.

Detailed Description

The invention will be further described with reference to the accompanying drawings, but the scope of the invention is not limited to the following description.

As shown in FIG. 1, the auxiliary machining mechanism for the blade of the aircraft engine comprises a lower box body 2 and an upper cover 3; a left clamping structure 4 and a right clamping structure 4 are arranged in the lower box body 2, and a bin 5 is arranged on the upper cover 3; the left and right holding structures 4 hold the aero-engine blade 1 from the left and right directions.

After being clamped, the aero-engine blade 1 is in a flat lying state; at the moment, a plurality of passage small holes 101 are formed in the upper surface of the aero-engine blade 1, a passage cavity 102 penetrating through the aero-engine blade 1 from left to right is formed in the aero-engine blade 1, and the passage small holes 101 are connected with the passage cavity 102.

In the scheme, the left and right clamping structures 4 are provided with hollow plugs 401; during clamping, the hollow plug 401 is butted with the channel cavity 102; and the hollow plug 401 is connected to a pump via a pump-out line 402. Grinding fluid and abrasive are added into the bin 5.

During grinding, the upper cover 3 and the lower box body 2 are buckled; the grinding fluid and the abrasive material in the bin 5 firstly fall on the upper surface of the aircraft engine blade 1, and sequentially flow through the passage small hole 101, the passage cavity 102 and the extraction pipeline 402 under the action of the extraction pump, so that the finishing processing of the passage small hole 101 is completed.

In this embodiment, the top of the storage bin 5 is provided with a feeding pipe, and a bottom plate 501 is arranged in the storage bin; the upper surface of the bottom plate 501 is concave, and a plurality of sand blasting nozzles 502 are arranged on the bottom plate 501; high pressure is formed in the bin 5, and the abrasive and the grinding fluid are sprayed on the aeroengine blade 1 through the sand blasting nozzle 502.

Optionally, as shown in fig. 2 to 4, the machining auxiliary mechanism for the aircraft engine blade is further provided with a front and rear clamping structure 6 in the lower case 2.

In this embodiment, the left and right clamping structures 4 further include clamping blocks 404, slide rails 405, cylinders a406, and springs 407; a clamping block 404 which is respectively connected with the left wall of the lower box body 2 through a cylinder A406 and a spring 407; the front and back surfaces of the clamping block 404 are matched with the slide rail 405 to form limiting; a clamping block 404 on which the assembling plate 403 is arranged; a clamping block 404, the inner side of which is provided with a hollow plug 401, the lower surface of which is provided with a drawing-off pipeline 402, and a cavity channel is arranged in the clamping block; the hollow plug 401 is connected with a drawing-off pipeline 402 through a cavity channel; the drawing-off pipe 402 passes out of the lower box body 2 and is sealed by glue, and the middle part of the drawing-off pipe is a flexible pipe.

In this embodiment, the left and right holding structures 4 have a built-up plate 403; after the left and right clamping structures 4 clamp the aero-engine blade 1, the splicing blocks 601 and the splicing plates 403 are assembled into a rectangular frame; when the abrasive in the bin 5 falls on the upper surface of the blade 1 of the aircraft engine, the abrasive is gathered by the rectangular frame ring to form a structure for preventing the abrasive from overflowing.

In this embodiment, the front and rear clamping structures 6 include an assembling block 601 and a cylinder B602; the splicing block 601 is connected with the front wall and the rear wall of the lower box body 2 through a cylinder B602; the assembling block 601 is provided with an assembling groove matched with the assembling plate 403.

Alternatively, for machining aids for aircraft engine blades, the extraction pipe 402 communicates with the silo 5 via an extraction pump.

The grinding materials and the grinding fluid in the bin 5 fall to the upper surface of the aero-engine blade 1 through the bin 5 under the action of the pump, are gathered together by the assembled rectangular frame ring, then sequentially pass through the small channel hole 101, the pump pipeline 402 and the pump and then return to the bin 5 again to form circulation. The grinding is realized by the grinding material and the grinding liquid together, and a circulation route is formed by corresponding pipelines and pumps, so that the small passage hole 101 of the aircraft engine blade 1 is fully processed.

In the embodiment, when the upper cover 3 and the lower box body 2 are buckled, a sealing gasket 7 is arranged at the buckling position of the upper cover and the lower box body; when the upper cover 3 and the lower box body 2 are buckled, the bin 5 abuts against the rectangular frame to form butt joint.

In this embodiment, the bottom of the lower box 2 is further threaded with a drainage nozzle 201, and during the circulation of the grinding material and the grinding fluid, because the bottom surface of the rectangular frame is not sealed, some liquid and a small amount of grinding material will flow to the inner bottom surface of the lower box 1, and the drainage nozzle 201 can drain the liquid and the small amount of grinding material. The inner bottom surface of the lower box body 2 is provided with a supporting block 8 for placing the aeroengine blade 1.

For good matching, the upper cover 3 is provided with a positioning column 301, and the lower box body 2 is provided with a matched positioning hole.

In order to facilitate carrying and taking, the upper cover 3 and the lower box body 2 are both provided with handles 9. And the lower case 2 is provided with support legs.

Before grinding, the aero-engine blade 1 is clamped firstly:

s1, manually butting the channel cavity 102 of the aero-engine blade 1 with the hollow plug 401, and automatically clamping the aero-engine blade 1 by the clamping block 404 under the action of the spring 407;

s2, driving the clamping block 404 to slightly move along the slide rail 405 by the cylinder A406, fully butting the channel cavity 102 with the hollow plug 401, and realizing plugging under the action of pressure;

s3, then, under the action of the cylinder B602, the assembling block 601 acts, and the assembling groove of the assembling block 601 is spliced with the assembling plate 403 on the clamping block 404 to form a rectangular frame;

s4, placing the upper sealing gasket 7 at the upper edge of the lower box body 2, and buckling the upper cover 3 on the lower box body 2; suitably, some load blocks are placed on the upper cover 3.

In the grinding process:

s1, adding grinding fluid and abrasive into the stock bin 5 through a pump (or an additional booster pump), and continuously feeding to maintain high pressure in the stock bin 5; the high pressure enables the sand blasting nozzle 502 to spray grinding fluid and abrasive, the sprayed grinding fluid and abrasive are used for processing the surface of the aircraft engine blade 1, and the edge of the small channel hole 101 is also subjected to deburring processing;

s2, the sprayed grinding fluid and the sprayed grinding materials are also enclosed by the rectangular frame, a part of the grinding fluid flows into the lower box body 3, but more grinding fluid and grinding materials are pumped away under the action of a pumping pump in the rectangular frame, the grinding fluid and the grinding materials flow along the small channel holes 101, and due to the fact that the flow velocity (the grinding materials have kinetic energy), burrs and curled edges at the edges of the small channel holes 101 are subjected to collision grinding processing in the flowing process, and the interior of the small channel holes 101 is also subjected to grinding processing.

The machining experiment was conducted by using the above-described structure and machining procedure, and a microscopic enlarged view of the small via hole 101 after machining is shown in fig. 9. While a general abrasive machining method is shown in fig. 8. It can be clearly seen that the scheme has excellent processing effect.

The above examples only represent preferred embodiments, and the description thereof is more specific and detailed, but not to be construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention.

Claims (9)

1. A processing complementary unit for aeroengine blade has about in aeroengine blade (1) and controls passageway chamber (102) of running through, and aeroengine blade (1) upper surface is opened has a plurality of passageway apertures (101), and a plurality of passageway apertures (101) link to each other with passageway chamber (102), its characterized in that: the method comprises the following steps:

a lower box body (2) which is internally provided with a left clamping structure and a right clamping structure (4);

the upper cover (3) is provided with a bin (5);

the left clamping structure and the right clamping structure (4) are provided with hollow plugs (401); after the left clamping structure and the right clamping structure (4) clamp the aero-engine blade (1) from the left side and the right side, the hollow plug (401) is in butt joint with the channel cavity (102);

the hollow plug (401) is connected with a pumping-out pump through a pumping-out pipeline (402);

after the upper cover (3) and the lower box body (2) are buckled: the abrasive material in the storage bin (5) firstly falls on the upper surface of the aeroengine blade (1), then flows through the channel small hole (101), the channel cavity (102) and the extraction pipeline (402), and the finishing processing of the channel small hole (101) is realized.

2. A machining aid for aircraft engine blades according to claim 1, characterised in that: a front clamping structure and a rear clamping structure (6) are also arranged in the lower box body (2);

the front and rear clamping structures (6) are provided with splicing blocks (601);

the left clamping structure and the right clamping structure (4) are provided with assembling plates (403);

after the left clamping structure and the right clamping structure (4) clamp the aero-engine blade (1), the splicing blocks (601) and the splicing plates (403) are assembled into a rectangular frame; the abrasive in the bin (5) falls into the rectangular frame to form a structure for preventing the abrasive from overflowing.

3. A machining aid for aircraft engine blades according to claim 2, characterised in that: the material bin (5) is filled with abrasive and grinding fluid;

the pumping pipeline (402) is communicated with the storage bin (5) through a pumping pump;

the grinding material and the grinding fluid fall to the upper surface of the aero-engine blade (1) through the stock bin (5) under the action of the pump, are gathered together by the assembled rectangular frame ring, and then return to the stock bin (5) again through the small channel hole (101), the pump pipeline (402) and the pump to form circulation.

4. A machining aid for aircraft engine blades according to claim 3, characterised in that: when the upper cover (3) and the lower box body (2) are buckled, a sealing gasket (7) is arranged at the buckling position of the upper cover and the lower box body;

when the upper cover (3) is buckled with the lower box body (2), the storage bin (5) abuts against the rectangular frame to form butt joint.

5. A machining aid for aircraft engine blades according to claim 3 or 4, characterised in that: the top of the storage bin (5) is provided with a feeding pipe, and a bottom plate (501) is arranged in the storage bin;

the upper surface of the bottom plate (501) is concave, and a plurality of sand blasting nozzles (502) are arranged on the bottom plate (501); the grinding materials and the grinding fluid in the bin (5) are sprayed on the aeroengine blade (1) through a sand spraying nozzle (502).

6. A machining aid for aircraft engine blades according to claim 5, characterised in that: the left clamping structure and the right clamping structure (4) further comprise clamping blocks (404), sliding rails (405), air cylinders A (406) and springs (407);

the clamping block (404) is connected with the left wall of the lower box body (2) through a cylinder A (406) and a spring (407) respectively;

the front surface and the rear surface of the clamping block (404) are matched with the sliding rail (405) to form limiting;

the clamping block (404) is provided with a splicing plate (403);

the inner side surface of the clamping block (404) is provided with a hollow plug (401), the lower surface of the clamping block is provided with a drawing-out pipeline (402), and a cavity channel is formed in the clamping block; the hollow plug (401) is connected with a drawing pipeline (402) through a cavity channel;

the drawing-off pipeline (402) penetrates out of the lower box body (2) and is sealed by glue, and the middle part of the drawing-off pipeline is a flexible pipe.

7. A machining aid for aircraft engine blades according to claim 6, characterised in that: the front and rear clamping structures (6) comprise splicing blocks (601) and air cylinders B (602);

the splicing block (601) is connected with the front wall and the rear wall of the lower box body (2) through a cylinder B (602);

the splicing block (601) is provided with a splicing groove matched with the splicing plate (403).

8. A machining aid for aircraft engine blades according to claim 7, characterised in that: the bottom of the lower box body (2) is also provided with a drainage nozzle (201) in a threaded manner;

the inner bottom surface of the lower box body (2) is provided with a supporting block (8) for placing an aircraft engine blade (1).

9. A machining aid for aircraft engine blades according to claim 8 in which: the upper cover (3) is provided with a positioning column (301), and the lower box body (2) is provided with a matched positioning hole;

the upper cover (3) and the lower box body (2) are both provided with handles (9);

the lower box body (2) is provided with supporting legs.

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