阅读说明：本技术 内腔带扰流柱结构的薄壁空心叶片尾劈缝的保护工装 (Protection tool for thin-wall hollow blade tail splitting seam with inner cavity provided with turbulence column structure ) 是由 杨泽南 王祯 陈晶阳 苏云 张强 于 2020-04-30 设计创作，主要内容包括：本发明涉及内腔带扰流柱结构的薄壁空心叶片尾劈缝的保护工装,采用Fe-Mn-Si系形状记忆合金制作。在其插入叶片尾劈缝一端设有与叶片内腔扰流柱结构相嵌的半圆形凹槽,其外露部分设有凹槽与绳索或皮筋配合防止使用过程工装脱落,其外露部分设有两个圆孔与销钉等相配合便于取出。工装表面经过渗碳处理,在其表面形成耐磨层以提高其使用寿命。本发明的制备工艺简单易行,可有效降低薄壁叶片运输、加工过程中磕碰伤及打磨修整造成的排气边变形及涂层制备过程中造成的尾劈缝漏渗,以提高铸件尾缘尺寸精度,进而大幅提高产品合格率,减少经济损失,可满足大规模生产需求,同时该工装可重复使用,形状记忆效应避免了铸件尺寸波动对工装精度的影响,可降低成本。(The invention relates to a protective tool for a thin-wall hollow blade tail cleavage seam with a spoiler column structure in an inner cavity, which is made of Fe-Mn-Si series shape memory alloy. One end of the tail cleft joint, which is inserted into the blade, is provided with a semicircular groove embedded with a spoiler column structure in the inner cavity of the blade, the exposed part of the tail cleft joint is provided with a groove matched with a rope or a rubber band to prevent the tool from falling off in the using process, and the exposed part of the tail cleft joint is provided with two round holes matched with pins and the like to be taken out conveniently. The surface of the tool is carburized, and a wear-resistant layer is formed on the surface of the tool so as to prolong the service life of the tool. The preparation process is simple and easy to implement, the deformation of the exhaust edge caused by collision and polishing in the transportation and processing processes of the thin-wall blade and the leakage of the tail cleft joint caused in the coating preparation process can be effectively reduced, the dimensional precision of the tail edge of the casting is improved, the product percent of pass is greatly improved, the economic loss is reduced, the requirement of large-scale production can be met, meanwhile, the tool can be repeatedly used, the influence of the dimensional fluctuation of the casting on the tool precision is avoided by the shape memory effect, and the cost can be reduced.)

1. The protection frock of thin wall hollow blade tail split of vortex column structure is taken to inner chamber, characterized in that: one end of the protective tool inserted into the inner cavity of the thin-wall hollow blade is provided with a tooth-shaped structure, the tooth-shaped structure corresponds to the outermost drain flow column structure and size of the thin-wall hollow blade, the tooth bottom (1) of the tooth-shaped structure is in a runway shape, and the tooth top (2) of the tooth-shaped structure is provided with a straight section; a plurality of groove structures (3) are arranged on the edge of one exposed end of the protection tool; and circular holes (4) are respectively arranged at the positions of the exposed end of the protection tool close to the blade tip and the two sides of the blade root.

2. The protection tool of claim 1, wherein: the whole thickness of the tool is the same as the width of the tail splitting seam of the thin-wall hollow blade, and the tooth tip region of the tool inserted between the flow disturbing columns of the thin-wall hollow blade is protected to be smaller than the width of the tail splitting seam.

3. The protection tool of claim 1, wherein: the tooth space of the tooth-shaped structure of the protection tool is the same as the circle center space of the adjacent turbulent flow columns at the outermost row of the thin-wall hollow blades.

4. The protection tool of claim 1, wherein: the diameter of the semi-circular arc at the bottom of the tooth of the protection tool is larger than or equal to the diameter of the outermost discharge flow column of the thin-wall hollow blade.

5. The protection tool of claim 1, wherein: when the protection tool is in a complete insertion state, a plurality of grooves of the edge at the exposed end of the protection tool are positioned outside the edge of the exhaust edge of the thin-wall hollow blade.

6. The protection tool of claim 1, wherein: when the protection tool is in a complete insertion state, the round hole (4) is completely positioned outside the edge of the exhaust edge of the thin-wall hollow blade.

7. The protection tool of claim 1, wherein: the protective tool is made of Fe-Mn-Si series shape memory alloy, and the surface of the protective tool is carburized.

8. The protection tool of claim 1, wherein: the whole protection tool is of a sheet-like structure.

Technical Field

The invention belongs to the technical field of investment precision casting of high-temperature alloy, and particularly relates to a protective tool for a trailing edge exhaust edge of a thin-wall hollow blade with a spoiler column structure in an inner cavity, which can prevent the deformation of the exhaust edge of the hollow blade caused by external force in the processes of transportation, polishing, trimming and machining and prevent a coating in the coating preparation process from leaking into the inner cavity through a blade tail cleft joint.

Background

The turbine blade is used as an important part of the aircraft engine, and the reliability of the turbine blade is important for the stability and the service life of the aircraft engine when the turbine blade is used in a severe high-temperature and high-pressure working environment for a long time. In order to improve the working efficiency of the engine, the inlet temperature of the turbine needs to be correspondingly increased, so that the high-performance aircraft engine adopts cast high-temperature alloy hollow turbine blades, and cooling air flow is introduced into the inner cavity of the turbine blades to cool the blade body. In order to optimize the cooling air utilization rate to the maximum extent, a flow disturbing column structure is usually designed in an inner cavity of the tail edge of the blade to enhance heat exchange.

In order to pursue excellent aerodynamic performance, the thickness of the exhaust edge of the tail edge of a typical aircraft engine blade is usually thin (0.5 mm-1 mm), while the thickness of the exhaust edge of a small-size turboshaft engine blade for a helicopter can even reach 0.4 mm. The wall thickness dimension of the cast blade fluctuates to a certain degree, and the condition that the tail splitting seam is closed due to the external force action in the polishing and trimming process of the tail edge dimension occurs occasionally. In addition, the blade also has the risk of bruising in each process flow and machining process, and causes that the local seam width is smaller or is completely closed. When the size of the blade tail cleft gap is out of tolerance, the cooling air in the inner cavity cannot effectively flow through the tail cleft gap and enter the inner flow channel, so that the local over-temperature of the blade body is caused, and the risk of ablation and fracture is increased. Therefore, the dimensional accuracy of the blade discharge edge is critical to the reliability of the turbine blade, which in turn is related to the safety and reliability of the aircraft engine. Blade part development and production units need a hollow thin-wall blade exhaust edge protection tool urgently, the size precision of the tail edge of the blade in the polishing, transporting and machining processes is ensured, and the blade scrapping caused by exhaust edge deformation is avoided. In addition, in the process of preparing the coating by adopting EB-PVD or APS and other methods, if a specific protection tool is not adopted, the coating is easy to permeate into the inner cavity of the tail-splitting seam, the flow of cooling air of the tail-splitting seam in a service state is seriously influenced, and further the local overtemperature of the blade is possibly caused.

Disclosure of Invention

The invention aims to make deformation protection measures aiming at the exhaust edge of the cast high-temperature alloy hollow thin-wall blade tail edge, avoid the conditions of exhaust edge deformation, gouge, cracks and the like caused by the action of external force, further ensure the dimensional accuracy of the exhaust edge of the blade tail edge, and provide a simple, feasible and reusable deformation protection tool for a high-quality aeroengine turbine blade.

In order to achieve the purpose, the technical solution of the invention is as follows:

the protection tool for the tail splitting seam of the thin-wall hollow blade with the spoiler column structure in the inner cavity is characterized in that a tooth-shaped structure is arranged at one end, inserted into the inner cavity of the thin-wall hollow blade, of the protection tool, the tooth-shaped structure corresponds to the outermost spoiler column structure and size of the thin-wall hollow blade, the tooth bottom 1 of the tooth-shaped structure is in a runway shape, and the tooth top 2 of the tooth-shaped structure is provided with a straight section; a plurality of groove structures 3 are arranged on the edge of the exposed end of the protection tool; and circular holes 4 are respectively formed in the positions, close to the blade tips and the blade roots, of the exposed end of the protection tool.

Preferably, the whole thickness of the tool is the same as the width of the tail splitting seam of the thin-wall hollow blade, and the tooth tip region of the tool, which is inserted between the thin-wall hollow blade turbulence columns, is protected to be smaller than the width of the tail splitting seam.

Preferably, the tooth space of the tooth-shaped structure of the protection tool is the same as the circle center space of the adjacent turbulent flow columns at the outermost row of the thin-wall hollow blades.

Preferably, the diameter of the semi-circular arc at the bottom of the tooth of the protection tool is larger than or equal to the diameter of the outermost drain flow column of the thin-wall hollow blade.

Preferably, when the protection tool is in a fully inserted state, the plurality of grooves of the edge at the exposed end of the protection tool are positioned outside the edge of the exhaust edge of the thin-wall hollow blade.

Preferably, when the protection tool is in the fully inserted state, the circular hole 4 is completely positioned outside the edge of the exhaust edge of the thin-wall hollow blade.

Preferably, the protection tool is made of Fe-Mn-Si series shape memory alloy, and the surface of the protection tool is subjected to carburizing treatment.

Preferably, the protection tool is of a sheet-like structure as a whole.

The invention has the beneficial effects that:

at present, the turbine blade of the domestic aero-engine does not effectively protect the exhaust edge in the production, processing and transportation processes, and the position is very easy to deform under the action of external force, so that the reliability and safety of the service of the turbine blade are influenced. According to the invention, by designing the exhaust edge deformation-preventing protection tool, the dimensional accuracy of the tail edge of the turbine blade can be improved, and the conditions of collision damage, undetected microcracks and the like caused by external force are avoided. Because the width of the tail splitting seam is narrow, a plate with fixed thickness is selected and only needs to be processed and formed in the two-dimensional direction. In order to adapt to the three-dimensional composite bending die cavity structure of the blade, the thin sheet cut and formed by a special process is placed in the inner cavity of the blade sample piece to perform initial sizing on the tool, so that the problem of forming the bending thin sheet is solved. On the other hand, the shape memory effect of the shape memory alloy can enable the tool to recover the shape through simple heat treatment, and the requirement of batch production can be met. In conclusion, the exhaust edge protection tool designed by the invention is easy to machine and mold, convenient to use repeatedly, low in cost, capable of being popularized and applied in a large scale and providing a technical basis for the exhaust edge protection of the turbine blade of the high-performance aircraft engine.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention, illustrate embodiments and description thereof, and are not to be construed as limiting the invention in any way. In the drawings:

FIG. 1 is a schematic view of a protective tool for the trailing edge of a hollow turbine blade with a spoiler column structure in an inner cavity

FIG. 2 is a view of the exhaust edge of the trailing edge of a hollow turbine blade with a spoiler column structure in the inner cavity

FIG. 3 is a sectional view B-B of the trailing edge of a hollow turbine blade with a spoiler column structure in the inner cavity along the center line of the blade profile

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention is further described in detail with reference to the following embodiments, and it should be understood that the specific embodiments described herein are only used for explaining the present invention and are not used for limiting the present invention.

The utility model provides a thin wall hollow blade tail crack protection frock of vortex post structure is taken to inner chamber, overall structure is lamellar, inserts the blade inner chamber and is dentate structure with outermost row's vortex post cooperation one end at it, and the tooth bottom has straight section for runway shape, tooth top, and the frock exposes one end design recess and round hole, and its part two-dimensional design scheme sees attached 1, and the design is according to seeing attached 2 and 3 sizes as follows:

the thickness s of the tool is equal to the lower tolerance of the width t of the exhaust edge tail splitting seam of the blade;

the distance H between adjacent teeth is equal to the center distance D between adjacent turbulent flow columns in the outermost row;

the tooth bottom width h is more than or equal to the diameter d of the outermost discharge flow column;

the tooth top width P is less than or equal to the adjacent tooth space H-tooth root width H;

in order to facilitate the insertion of the tool and prevent the warping edge from deforming, the tooth-shaped position embedded between the turbulence columns in the inserted state of the tool is polished to reduce the thickness, in order to ensure that the tooth top thickness is not less than 0.2mm after polishing the tooth top rigidity, the tooth bottom thickness is the same as the thickness of the tool main body, and the tooth surface thickness is in smooth transition from the tooth top to the tooth bottom; in order to facilitate the fixation of the tool in the polishing and transferring processes, a plurality of groove structures are arranged on the edge of the exposed end of the tool, and the tool is bound on the blade body by matching with a rope or a leather sheath to prevent the blade body from falling off in the using process; in order to facilitate the pulling-out of the tool, round holes are arranged at the two sides of the exposed end of the tool, which are close to the blade tip and the blade root, and the positions and the apertures of the round holes are such that when the tool is in a completely inserted state (the tooth bottom is attached to the spoiler column), the round holes are completely positioned outside the edges of the exhaust edge of the blade and are matched with round bars to complete the pulling-out in the use process; the manufacturing material of the tool is Fe-Mn-Si series shape memory alloy, when the tool is used for the first time, a standard blade sample piece with qualified tail edge size is inserted for high-temperature furnace heat treatment, so that the initial shape formed by the tool is matched with the theoretical profile of the inner cavity of the blade, and when the tool deforms due to the action of external force, the tool is subjected to heat treatment in a vacuum heat treatment furnace to recover the initial shape. The surface of the tool can be carburized to improve the wear resistance;