Multifunctional heat treatment tool for main engine case of aircraft engine

Abstract

The utility model discloses a multifunctional heat treatment tool for a main engine case of an aircraft engine, which comprises an annular chassis, a plurality of support rod positioning holes are uniformly distributed on a first circumference close to the periphery of the annular chassis, a plurality of cushion block positioning grooves are uniformly distributed on a second circumference on the inner side of the first circumference, and a concave annular groove is arranged on the inner side of the second circumference. A plurality of inner supporting positioning grooves are evenly distributed in the upper edge of the inner circumference of the annular base plate, and a plurality of hollowed-out water inlet grooves are evenly formed in the neutral position of the circumference where the supporting rod positioning holes and the cushion block positioning grooves are located and the bottom wall of the annular groove respectively. A supporting and positioning assembly is installed in the inner supporting and positioning groove, a T-shaped cushion block with the wide upper portion and the narrow lower portion is embedded in the cushion block positioning groove, and a rotary supporting rod is inserted into the supporting rod positioning hole. And carved water inlet grooves are also uniformly distributed on the circumference of the outer side of the first circumference. The tool can effectively control the heat treatment deformation of the aircraft engine main engine box, and can be suitable for aircraft engine main engine boxes of various models.

Description

TECHNICAL FIELD

[0001] The utility model relates to a heat treatment frock especially relates to a multifunctional heat treatment frock of aircraft engine main case, belongs to casting shaping technical field. BACKGROUND

[0002] After magnesium alloy casting is formed by pouring, it needs to be heat treated by means such as heating, heat preservation and cooling to change the internal structure of the casting to improve its performance and meet the use requirements.

[0003] For aircraft engine main case casting products, a special heat treatment frock needs to be customized to prevent deformation during heat treatment. A reasonable heat treatment device can improve dimensional accuracy, avoid dimensional tolerance and reduce manual correction in the later stage. SUMMARY

[0004] This section aims to outline some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the abstract of the specification and the utility model name, and such simplifications or omissions cannot be used to limit the scope of the utility model.

[0005] In view of the above and / or problems existing in the prior art, the utility model is proposed.

[0006] The utility model aims to overcome the problems existing in the prior art and provide a multifunctional heat treatment frock for aircraft engine main case, which can effectively control the heat treatment deformation of the aircraft engine main case and be applicable to various types of aircraft engine main cases.

[0007] To solve the above technical problems, the utility model provides a multifunctional heat treatment frock for aircraft engine main case, which comprises an annular base plate, a plurality of support rod positioning holes are uniformly distributed on the first circumference of the annular base plate near the periphery, a plurality of pad positioning grooves are uniformly distributed on the second circumference inside the first circumference, a recessed annular groove is arranged on the inner side of the second circumference, a plurality of inner support positioning grooves are uniformly distributed on the inner circumference of the annular base plate, a plurality of hollow water inlet grooves are uniformly arranged in the gaps of the circumferences where the support rod positioning holes and the pad positioning grooves are located and on the bottom wall of the annular groove; a support positioning assembly is installed in the inner support positioning groove, a T-shaped pad with a wide upper part and a narrow lower part is embedded in the pad positioning groove, and a rotating support rod is inserted into the support rod positioning hole.

[0008] Further, the lower flange of the aircraft engine main casing is supported in the annular groove, top parts of the support positioning assembly are supported below an inner step of a center cylinder of the aircraft engine main casing respectively, a top surface of the T-shaped cushion block is supported at a bottom of a lubricating oil tank of the aircraft engine main casing, and upper ends of the rotary support rods are supported below outer bosses of the aircraft engine main casing respectively.

[0009] Further, the outer boss of the aircraft engine main casing comprises a mounting seat, a supporting lug and an oil inlet / outlet port arranged on an outer wall of the lubricating oil tank.

[0010] Further, a diameter adjusting metal ring is embedded at an outer peripheral wall of the annular groove, and an inner periphery of the diameter adjusting metal ring abuts against an outer periphery of the lower flange of the aircraft engine main casing.

[0011] Further, a diameter adjusting metal ring is embedded at an inner peripheral wall of the annular groove, and an outer periphery of the diameter adjusting metal ring abuts against an inner periphery of the lower flange of the aircraft engine main casing.

[0012] Further, a support positioning sleeve is arranged at a lower end of the rotary support rod, a reduced lower end head of the support positioning sleeve is inserted into a corresponding support rod positioning hole, a rotary screw is threadedly connected into a screw port of an upper end of the support positioning sleeve, and a top part of the rotary screw abuts against the lower boss of the outer boss of the aircraft engine main casing through a circular support block.

[0013] Further, the support positioning assembly comprises a support seat, a support seat boss is arranged at a bottom of the annular base of the support seat, the support seat boss is embedded into a corresponding inner support positioning groove and is fixed by a screw, a vertical guide groove is arranged at the support seat, a support column extending upward is arranged at the vertical guide groove, a top part of the support column abuts against the lower step of the inner step of the center cylinder of the aircraft engine main casing, a close screw is threadedly connected with a side wall of the support seat, and an inner end head of the close screw abuts against the support column.

[0014] Further, the T-shaped cushion block is curved along an arc of a circumference.

[0015] Further, a plurality of perforated water inlets are uniformly distributed on the circumference of the outer side of the first circumference.

[0016] Compared with the prior art, the aircraft engine main casing heat treatment device has the following beneficial effects: 1. The heat treatment deformation problem of the aircraft engine casting can be solved, the size out-of-tolerance can be avoided, the size precision can be improved, and the aircraft engine main casing product can meet the design drawing requirements.

[0017] 2. The heat treatment device can be used for multiple types of aircraft engine main casings, the universality of the device is improved, the production cost is reduced, and the production cycle is shortened.

[0018] 3. The mechanical correction due to heat treatment deformation is avoided, and the labor intensity of workers is reduced. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. The drawings are provided for reference and illustration only and are not intended to limit this utility model. Wherein:

[0020] Figure 1 This is a perspective view of the annular chassis in the multi-functional heat treatment tooling for the main casing of an aircraft engine of this utility model.

[0021] Figure 2 This is a perspective view of the multi-functional heat treatment fixture for the main casing of an aircraft engine according to this utility model.

[0022] Figure 3 This is a three-dimensional enlarged view of the support and positioning component in this utility model;

[0023] Figure 4 This is a three-dimensional enlarged view of the rotating support rod in this utility model;

[0024] Figure 5 This is a three-dimensional enlarged view of the T-shaped pad in this utility model;

[0025] Figure 6 A perspective view of the main casing of an aircraft engine;

[0026] Figure 7 This is a diagram showing the working state of the multi-functional heat treatment tooling for the main casing of an aircraft engine according to this utility model.

[0027] In the diagram: 1. Annular chassis; 1a. Inner support positioning groove; 1b. Support rod positioning hole; 1c. Annular groove; 1d. Pad positioning groove; 1e. Hollowed-out water inlet groove;

[0028] 2. Support positioning assembly; 2a. Support base; 2b. Support base boss; 2c. Support column; 2d. Set screw;

[0029] 3. Rotary support rod: 3a. Support positioning sleeve; 3b. Rotary screw; 3c. Circular support block;

[0030] 4. Adjusting metal ring; 5. T-shaped pad;

[0031] 6. Aircraft engine main casing; 6a. Upper flange; 6b. Internal step of the center tube; 6c. Hollow blade; 6d. Lower flange; 6e. Lubricating oil tank; 6f. Mounting seat; 6g. Lug; 6h. Oil inlet; 6j. Oil outlet. Detailed Implementation

[0032] In the following description of the present application, the terms "upper", "lower", "front", "back", "left", "right", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not mean that the device must have a particular orientation.

[0033] In order to make the technical means, creative features, purposes and effects achieved by the present application easy to understand, the present application will be further described below in conjunction with specific drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, not all.

[0034] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present application belongs. The terminology used in the specification of the present application is only for the purpose of describing specific embodiments and is not intended to limit the present application.

[0035] As shown in Figures 1 to 7 The present application aircraft engine main casing multifunctional heat treatment tooling includes annular base plate 1, support positioning assembly 2, rotating support rod 3, adjustable diameter metal ring 4 and T-shaped pad 5, a plurality of support rod positioning holes 1b are uniformly distributed on the first circumference close to the periphery of annular base plate 1, a plurality of pad positioning grooves 1d are uniformly distributed on the second circumference inside the first circumference, the inside of the second circumference is provided with a recessed annular groove 1c, a plurality of inner support positioning grooves 1a are uniformly distributed on the inner circumference of annular base plate 1, a plurality of open water inlets 1e are uniformly provided on the clearance of the circumference where the support rod positioning hole 1b and the pad positioning groove 1d are located and on the bottom wall of the annular groove 1c. The circumference outside the first circumference is also uniformly distributed with open water inlets 1e, which is convenient for rapid immersion in water during cooling.

[0036] The aircraft engine main casing 6 includes a circular casing shell, and a lubricating oil cavity is integrated on the outer periphery of the lower part of the casing shell to form a lubricating oil tank 6e covering the outer periphery of the lower part of the casing shell; the outer wall of the lubricating oil tank 6e is provided with a mounting seat 6f, a lug 6g, an oil inlet 6h and an oil outlet 6j, etc., thereby forming a plurality of outer bosses on the outer wall of the lubricating oil tank 6e. The outer boss part is thicker and heavier, and is prone to sagging under the action of gravity during heat treatment, so it is necessary to support the above-mentioned part.

[0037] The upper center of the casing shell is provided with a center cylinder extending upward, the upper part of the center cylinder exceeds the casing shell and is provided with an upper flange 6a, and the lower end of the center hole of the center cylinder is provided with a center cylinder inner step 6b with an expanded diameter. The annular space between the lower part of the outer wall of the center cylinder and the inner wall of the upper part of the casing shell is connected as a whole through a plurality of hollow blades 6c. One end of the inner cavity space of each hollow blade 6c is connected with the lower cavity of the center cylinder, and the other end is connected with the annular partition cavity in the thin wall of the upper part of the casing shell. The receiving capacity of the hollow blade 6c is limited, and it is easy to sag and deform under the action of gravity during heat treatment. During the heat treatment process, the center cylinder inner step 6b needs to be supported.

[0038] The lower flange 6d of the aircraft engine main casing 6 is supported in the annular groove 1c. The size of the lower flange 6d of different types of main casings is different. Therefore, a diameter adjusting metal ring 4 is embedded at the outer peripheral wall of the annular groove 1c. The inner periphery of the diameter adjusting metal ring 4 abuts against the outer periphery of the lower flange 6d of the aircraft engine main casing 6 to fix the lower flange 6d.

[0039] A T-shaped cushion block 5 with a wide upper part and a narrow lower part is embedded in the cushion block positioning groove 1d. The T-shaped cushion block 5 is curved along the arc of the circumference. The lower thin wall part of the T-shaped cushion block 5 is inserted into the cushion block positioning groove 1d to play a positioning role. The top surface of the T-shaped cushion block 5 supports the bottom of the lubricating oil tank 6e of the aircraft engine main casing 6.

[0040] A support positioning assembly 2 is installed in the inner support positioning groove 1a. The support positioning assembly 2 includes a support seat 2a. The support seat 2a is provided with a support seat boss 2b facing the bottom of the annular base plate 1. The support seat boss 2b is embedded in the corresponding inner support positioning groove 1a and is fixed by screws. The support seat 2a is provided with a vertical guide groove. The vertical guide groove is provided with a support column 2c extending upward. The top of the support column 2c abuts against the lower part of the center cylinder inner step 6b of the aircraft engine main casing 6. The side wall of the support seat 2a is screwed with a set screw 2d. The inner end of the set screw 2d abuts against the support column 2c.

[0041] A rotating support rod 3 is inserted into the support rod positioning hole 1b. The lower end of the rotating support rod 3 is provided with a support positioning sleeve 3a. The reduced diameter lower end of the support positioning sleeve 3a is inserted into the corresponding support rod positioning hole 1b. The upper end of the support positioning sleeve 3a is screwed with a rotating screw 3b through a threaded connection. The top of the rotating screw 3b abuts against the lower part of the outer boss of the aircraft engine main casing 6 through a circular support block 3c. The installation position of the rotating support rod 3 can be selected according to the position and height of the outer boss, and adjusted to an appropriate jacking height to support and limit the casting, thereby preventing the thermal expansion and contraction effect during heat treatment.

[0042] The heat treatment tooling is installed in the following order: first, measure the outer diameter of the lower flange of the engine main casing, select a suitable diameter adjusting metal ring 4; then install the T-shaped block 5 on the annular base 1, then put the lower flange 6d of the aircraft engine main casing 6 into the annular groove 1c on the annular base 1, then embed the diameter adjusting metal ring 4 between the annular groove 1c and the outer periphery of the main casing lower flange, and fix the lower flange 6d; at this time, the T-shaped block 5 is supported at the bottom of the main casing oil tank, and shims can be inserted below the T-shaped block 5 to adjust the height of the top surface thereof.

[0043] Then, the rotating support rod 3 is installed in the support rod positioning hole 1b, and the height of the top of the rotating screw rod 3b is adjusted so that the circular support block 3c abuts against the lower side of the corresponding outer boss.

[0044] Finally, each support positioning assembly 2 is installed in the corresponding inner support positioning groove 1a, the height of the top of the support column 2c is adjusted so that it abuts against the lower side of the inner step 6b of the center cylinder, and the locking screw 2d is locked.

[0045] The above only describes the preferred embodiments of the present application, shows and describes the basic principles, main features and advantages of the present application, and is not limited to the patent protection range of the present application. Those skilled in the art should understand that the present application is not limited by the above embodiments. In addition to the above embodiments, the present application can have other implementation manners without departing from the spirit and scope of the present application. The present application can also have various changes and improvements, and any technical solution formed by equivalent replacement or equivalent transformation falls within the protection scope of the present application. The protection scope of the present application is defined by the appended claims and their equivalents. The technical features not described in the present application can be realized by or using existing technology, and will not be described here.

Claims

1. A multifunctional heat treatment tooling for an aircraft engine main housing, comprising a ring-shaped base plate, characterized in that: The annular base disc is provided with a plurality of support rod positioning holes uniformly distributed on a first circumference close to the periphery, a plurality of cushion positioning grooves uniformly distributed on a second circumference inside the first circumference, and a recessed annular groove inside the second circumference.

2. The multifunctional heat treatment tooling for aircraft engine main housing according to claim 1, characterized in that: The lower flange of the aircraft engine main casing is supported in the annular groove, and the top part of the support positioning assembly is supported below the inner step of the center cylinder of the aircraft engine main casing.

3. The multifunctional heat treatment tooling for an aircraft engine main housing according to claim 2, characterized in that: The outer boss of the aircraft engine main casing comprises a mounting seat, a supporting lug and an oil inlet / outlet provided on the outer wall of the lubricating oil tank.

4. The aircraft engine main housing multifunctional heat treatment tooling of claim 2, wherein: A diameter-adjusting metal ring is embedded at the outer wall of the annular groove, and the inner circumference of the diameter-adjusting metal ring abuts against the outer circumference of the lower flange of the aircraft engine main casing.

5. The aircraft engine main housing multifunctional heat treatment tooling of claim 1, wherein: The lower end of the rotating support rod is provided with a support positioning sleeve, the reduced lower end of the support positioning sleeve is inserted into the corresponding support rod positioning hole, a rotating screw is threadedly connected in the upper end of the support positioning sleeve, and the top of the rotating screw abuts against the lower part of the outer boss of the aircraft engine main casing through a circular support block.

6. The aircraft engine main housing multifunctional heat treatment tooling of claim 1, wherein: The support positioning assembly comprises a support seat, the support seat is provided with a support seat boss facing the bottom of the annular base disc, the support seat boss is embedded in the corresponding inner support positioning groove and fixed by a screw, the support seat is provided with a vertical guide groove, the vertical guide groove is provided with a support column extending upward, the top of the support column abuts against the lower part of the inner step of the center cylinder of the aircraft engine main casing, a set screw is screwed on the side wall of the support seat, and the inner end of the set screw abuts against the support column.

7. The aircraft engine main housing multifunctional heat treatment tooling of claim 1, wherein: The T-shaped cushion block is curved along the arc of the circumference.

8. The multifunctional heat treatment tooling for an aircraft engine main housing according to any one of claims 1 to 7, characterized in that: The outer circumference of the first circumference is also uniformly provided with the notched water inlet groove.

Images