CN202725978U

CN202725978U - Airborne casting mould of compressor middle casing

Info

Publication number: CN202725978U
Application number: CN 201220172933
Authority: CN
Inventors: 黄丁保; 刘庆平; 刘宇; 李昌海; 石强; 汪兵
Original assignee: ZHONGXIANG DONGFANGHONG FOUNDRY FACTORY
Current assignee: ZHONGXIANG DONGFANGHONG FOUNDRY FACTORY
Priority date: 2012-04-13
Filing date: 2012-04-13
Publication date: 2013-02-13
Anticipated expiration: 2022-04-13

Abstract

The utility model discloses an airborne casting mould of a compressor middle casing. The airborne casting mould of the compressor middle casing comprises a left mould, a right mould, a closed sand mould core, a square hole sand mould core, a covered sand mould core, a pipe position activity sand mould core, a middle core sand mould core, a main core print sand mould core, a base loose core, a pre-embedded stud and a sand mould core mounting plate. The left mould and the right mould are locked to form an entirety through mould assembly, and a casting cavity in line with the appearance of a casting blank is arranged inside the entirety. S-shaped main pouring gates placed symmetrically are arranged at the two sides of the left mould and the right mould. The airborne casting mould of the compressor middle casing has the advantages of being strong in mold filling feeding capacity, excellent in exhaust and scum, good in controlling vortex disturbance and good in comprehensive cost-performance ratio. Compared with the complex casting technique of investment casting, low pressure casting, vacuum injection, pressure regulating casting and the like, the airborne casting mould of the compressor middle casing has the advantage of a grate value of comprehensive cost-performance ratio.

Description

The aircraft casting casting mold of compressor middle casing

Technical field

The utility model relates to the technical field of mould, more particularly relates to the technical field of casting mould and casting mold.

Background technology

The aircraft compressor housings is container and the support framework that the compression pump assembly of compressed-air power is made in aircraft air-operated control and enhancement of environment, and version is divided into " upper and lower casing is combined " and " upper, middle and lower shell combination type " two large classes.Press type and distinguish, " upper and lower casing is combined " is small-sized, and " upper, middle and lower shell combination type " is large-scale.Described middle casing belongs to the core component that aircraft is used the large-scale compressor housings of " upper, middle and lower shell combination type ".Function and environment requires it to have support, resistance to compression and airtight three-dimensional function, its operating pressure by zero point several Mpa do not wait to several Mpa, its structural requirement is meticulous and light and handy, generally all is designed to compactness, complexity, high-strength, ultra-thin, gently little, dexterous high-end aluminium alloy I, II class casting structure form.Its material is considered preferred by operating pressure and the two-way combined factors of environment temperature: generally select ZL101A/JB/T6 to get final product when low temperature, low pressure; Generally select ZL205A/JB/T5 when low temperature, high pressure; Then need select ZL201A (ZL201)/JB/T5 during medium and high temperature even select ZL207/T1.Housing pressure-bearing and sealing ability must not be less than the compressor safe-working pressures, and the wall thickness of housing is generally in 3～5mm scope.The routine casting method is the casting techniques such as model casting, low pressure casting, vacuum suction, and advanced casting method is adjustable pressure casting technique.

Adopt the routine casting method, it is loaded down with trivial details to be faced with foundry technology process, and casting quality is low, mould and the equipment operational failure is many, cast cost occupies high-leveled and difficult inferior drawback; Adopt advanced adjustable pressure casting technique, need effectively to guarantee product quality, but because of its mould, the equipment cost of use surprising, very harsh to conditional requests such as personnel and environment, this class foundry goods of similar described middle casing, adjustable pressure casting technique is quite being grown in one period obviously also without practical value.

The utility model content

The purpose of this utility model provides a kind of casting cost low in order to solve above-mentioned deficiency exactly, and mould dimension is stable, and replicability is good, and can effectively guarantee the casting casting mold of the aircraft usefulness compressor middle casing of product percent of pass.

The technical solution that the utility model adopts in order to solve the problems of the technologies described above is as follows:

The aircraft casting casting mold of compressor middle casing, it mainly includes left mould, right mould, the closed chamber sand core, the square hole sand core, worn-out chamber sand core, pipe position sand core alive, the SMIS sand core, main core print sand core, loose core in the end, pre-buried stud and sand core installing plate, described left mould and right mould are put by the matched moulds lock and are formed integral body, its inside offers the casting mold die cavity consistent with strand spare profile, and the both sides at left mould and right mould offer snakelike main running channel by nearly symmetric configuration, snakelike main running channel connects by bottom die cavity and outer ring, the top annular feeding blind riser of the grading auxiliary running channel of stairstepping and casting mold die cavity again, main core print sand core and closed chamber sand core, worn-out chamber sand core, the SMIS sand core is the bonding integral body that is combined to form according to the order of sequence, by with left mould, right mould be connected with the core print die cavity cooperation and pre-buried stud with carry out precise positioning being connected of sand core installing plate and hang; Its appearance consists of inner chamber and inner ring annular blind riser and the center column open riser of casting mold, and consist of outer ring annular blind riser with left mould and right die combination, described square hole sand core and pipe position sand core alive is independent sand core, is installed in the die cavity of left mould and right mould by sand core core print fixation.

Described on die joint, be provided with the sled groove of being convenient to manual die sinking.

The beneficial effect that the utility model adopts above-mentioned technical solution to reach is: this mould adopts the snakelike ladder in both sides grading type casting and top two ring shape blind riser feeding and the center column open riser feeding technology of filling that vert, the order casting, the consecutive solidification process is perfect, it is strong to fill the type feeding capacity, exhaust scum silica frost ability is excellent, the eddy current disorder is controlled well, success solves ultra-thin-wall, the low-cost casting of an intricate casting difficult problem, casting qualified rate is high, comprehensive cost performance is excellent, with model casting, low pressure casting, the vacuum suction, the complicated casting technique such as adjustable pressure casting is compared, and all has the superiority of effectiveness that overflows.

Description of drawings

Fig. 1 is cross-sectional view of the present utility model;

Fig. 2 is the structural representation of the utility model strand spare;

Fig. 3 is the split type perspective view of the utility model.

The specific embodiment

By Fig. 1, Fig. 2 and shown in Figure 3, aircraft is with the casting casting mold of compressor middle casing, and it mainly includes, and left mould 1, right mould 2, closed chamber sand core 3, square hole sand core 4, worn-out chamber sand core 5, pipe position live that a sand core 6, SMIS sand core 7, main core print sand core 8, the end loose core 9, pre-buried stud 10 and sand core installing plate 11.Described left mould 1 and right mould 2, locked by the casting machine automatic die assembly during machinery casting, artificial matched moulds and lock with locking tool during manual mould casting, its inside offers the casting mold die cavity 12 consistent with strand spare profile, and the both sides at left mould 1 and right mould 2 offer snakelike main running channel 13 by nearly symmetric configuration, and snakelike main running channel 13 connects by bottom die cavity and outer ring, the top annular feeding blind riser 15 of the grading auxiliary running channel 14 of stairstepping with casting mold die cavity 12 again; Main core print sand core 8 is bearing part and keepers of combined suspension closed chamber sand core 3, worn-out chamber sand core 5 and SMIS sand core 7; Main core print sand core 8 and closed chamber sand core 3, worn-out chamber sand core 5 and SMIS sand core 7 be the bonding integral body that is combined to form according to the order of sequence, by the cooperation of being connected with left mould 1, right mould 2 and core print die cavity and pre-buried stud 10 with carry out precise positioning being connected of sand core installing plate 11 and hang, its appearance consists of inner chamber and inner ring annular blind riser 16 and the center column open riser 17 of casting mold, and constitutes outer ring annular blind riser 15 with left mould 1 and right mould 2; Described square hole sand core 4 and pipe position sand core 6 alive is independent sand core, be installed in by sand core core print fixation in the die cavity of left mould 1 and right mould 2, hand ejection during for the ease of manual mould casting in the die joint corresponding position of left mould 1 and right mould 2, is provided with paired hand ejection sled groove 19.

The die sinking pickup.When adopting mechanical mould, the pre-buried stud 10 of manual removal is connected with sand core installing plate 11, extracts the end out by the tilting type gravity force casting machine in advance and looses core 9, and then directly die sinking separates left mould 1 and also directly ejects synchronously foundry goods with right mould 2; When adopting manual mould, the pre-buried stud 10 of manual removal is connected with sand core installing plate 11, and the device of loosing core is extracted the end and loosed core 9, removes locked mode, and crowbar inserts that sled groove 19 prizes left mould 1 and right mould 2 is carried out die sinkings, and foundry goods is taken out in the demoulding of hammering push rod.

Remove molding sand, the excision foundry goods casting system of risers of strand spare inside, strand completes.

Claims

1. aircraft is with the casting casting mold of compressor middle casing, it is characterized in that: it mainly includes left mould, right mould, the closed chamber sand core, the square hole sand core, worn-out chamber sand core, pipe position sand core alive, the SMIS sand core, main core print sand core, loose core in the end, pre-buried stud and sand core installing plate, described left mould and right mould are put by the matched moulds lock and are formed integral body, its inside offers the casting mold die cavity consistent with strand spare profile, and the both sides at left mould and right mould offer snakelike main running channel by nearly symmetric configuration, snakelike main running channel connects by bottom die cavity and outer ring, the top annular feeding blind riser of the grading auxiliary running channel of stairstepping and casting mold die cavity again, main core print sand core and closed chamber sand core, worn-out chamber sand core, the SMIS sand core is the bonding integral body that is combined to form according to the order of sequence, by with left mould, right mould be connected with the core print die cavity cooperation and pre-buried stud with carry out precise positioning being connected of sand core installing plate and hang; Its appearance consists of inner chamber and inner ring annular blind riser and the center column open riser of casting mold, and consist of outer ring annular blind riser with left mould and right die combination, described square hole sand core and pipe position sand core alive is independent sand core, is installed in the die cavity of left mould and right mould by sand core core print fixation.

2. aircraft according to claim 1 is characterized in that: on die joint, be provided with the sled groove of being convenient to manual die sinking with the casting casting mold of compressor middle casing.