Preparation method for high-temperature sealing element of aero-engine

Abstract

The invention discloses a preparation method for a high-temperature sealing element of an aero-engine, and belongs to the technical field of preparation of high-temperature sealing elements. Weaving the two ends of the sample to form a hollow-outside and solid-inside structure and a solid-outside and hollow-inside structure respectively; yarn adding treatment is carried out when one end which is hollow outside and solid inside is woven into the middle section part of the sample; and yarn reducing treatment is carried out when the middle section part of the sample is woven into one end which is solid outside and hollow inside. Yarns are flexibly increased or decreased at the structure conversion position in the weaving process to adapt to form changes, the adaptability and reliability of the sealing piece are enhanced, and the requirement for the excellent sealing structure of the guide vane sealing component is met.

Description

Technical Field

[0001] The invention relates to the technical field of high-temperature sealing component preparation, in particular to a method for preparing a high-temperature sealing component for an aerospace engine. Background Art

[0002] The combustion chamber is one of the most important components of a turbine engine. Flexible braided guide vane seals are designed to meet the sealing requirements of the combustion chamber of a turbofan engine.

[0003] At present, high temperature resistant oxide fiber ropes are mainly made of alumina-based fibers and zirconium oxide-modified alumina fibers as the main raw materials. From the fiber morphology, they can be divided into spun fiber yarn braided ropes and continuous fiber braided ropes. Among them, the tensile strength of spun fiber yarn braided ropes is often poor, and they are often modified with metals or organic matter. The continuous fiber yarn braided rope has a higher tensile strength.

[0004] The high-temperature resistant ceramic fiber ropes in the domestic market are mainly aluminosilicate fiber ropes, and domestic high-end fiber ropes are mainly braided ropes made of aluminosilicate spun fiber yarns reinforced with high-temperature resistant metal wires, which are difficult to meet the service requirements in oxidizing environments above 1200°C.

[0005] Ceramic fiber braided fiber ropes can be formed in two-dimensional weaving, 2.5D weaving and three-dimensional weaving. High-temperature sealing structures can be roughly divided into three categories. The first is to directly use metal springs or ceramic springs as elastic elements without fiber-reinforced grid sealing structures; the second is to make ceramic fibers into ropes or sleeves with knitted structures, such as knitted spring tubes + Saffil insulation material thermal resistance seals; the third is to use fibers as reinforcement structures and directly use three-dimensional network structures for overall sealing, such as three-dimensional braided structures of all-ceramic fiber braided ropes. Among them, the three-dimensional four-way and three-dimensional five-way structures are better sealing structures for guide vane sealing components. It is necessary to improve the process of existing three-dimensional braided sealing rings to enhance the adaptability and reliability of the seals. Summary of the invention

[0006] The purpose of this section is to summarize some aspects of embodiments of the present invention and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and the invention title of this application to avoid blurring the purpose of this section, the specification abstract and the invention title, and such simplifications or omissions cannot be used to limit the scope of the present invention.

[0007] In view of the above problems and / or the problems existing in the prior art, the present invention is proposed.

[0008] Therefore, the first object of the present invention is to provide a method for preparing high-temperature seals for aircraft engines, which can flexibly increase or decrease yarns at structural transitions during the weaving process to adapt to morphological changes.

[0009] In order to solve the above technical problems, the present invention provides the following technical solutions: a preparation method for high-temperature seals for aircraft engines, comprising: weaving the middle section of a sample; weaving both ends of the sample, and weaving the two ends of the sample into a structure of hollow outside and solid inside and solid outside and hollow inside respectively; adding yarn when weaving from one end of the hollow outside and solid inside into the middle section of the sample; and reducing yarn when weaving from the middle section of the sample into one end of the solid outside and hollow inside.

[0010] As a preferred solution of the method for preparing a high-temperature seal for an aero-engine of the present invention, the middle section of the sample is woven into a cylindrical shape by a three-dimensional four-way weaving method.

[0011] As a preferred embodiment of the preparation method of the present invention for high-temperature seals of aircraft engines, the three-dimensional four-way weaving method includes a yarn hanging preparation stage, which includes: reserving a spindle in the middle part at the center of the auxiliary circle, the direction radiating outward from the center along the radial direction is the column direction, and the direction perpendicular to the column direction is the row direction; multiple spindles are equally divided into n groups, n is an even number ≥2; the number of spindles in each group is the same, and each group of spindles is distributed in x rows and y columns, and the connecting lines of the centers of each column of each group of spindles are parallel to each other; the n groups of spindles are evenly arranged around the circumferential direction of the auxiliary circle, and the auxiliary circle is evenly divided into m quadrants, where m=n, and the n groups of spindles are arranged opposite to each other in pairs relative to the center of the auxiliary circle.

[0012] As a preferred solution of the method for preparing high-temperature seals for aircraft engines of the present invention, the number of spindles in the yth column of each group of spindles is set to be one more or one less than the number of spindles in the y+1th column.

[0013] As a preferred solution of the method for preparing a high-temperature seal for an aircraft engine of the present invention, the braided yarns on the spindles are arranged to have the same cross-sectional area.

[0014] As a preferred solution of the method for preparing high-temperature seals for aircraft engines of the present invention, wherein: all the yarns in the column direction are moved, wherein the yth column of one group of spindles is moved toward the y+1th column of another group of spindles arranged oppositely; one column-wise bridge: the yarns on the spindles in the middle part of the yth column of one group of spindles are moved to the y+1th column of another group of spindles on the opposite side; all the yarns in the row direction are moved after passing through the one column-wise bridge, wherein the xth row and the x+1th row of each group of spindles move in opposite directions, and the spindles farthest from the center of the circle of each group of spindles are controlled to remain stationary; one row-wise bridge: the yarns at the edge of the row direction of each quadrant are moved to the spindles in the adjacent quadrant.

[0015] As a preferred solution of the preparation method for high-temperature seals of aircraft engines of the present invention, wherein: all the yarns in the column direction are moved again, and the moving direction is opposite to the direction of the first column direction bridge; the second column direction bridge: the yarns on the spindles in the middle part of the yth column of one group of spindles are moved to the y+1th column of another group of spindles on the opposite side, and the moving direction is opposite to the direction of the first column direction bridge; all the yarns in the row direction after the second column direction bridge are moved, and the moving direction is opposite to the direction of the first row direction bridge, and the spindle farthest from the center of each group of spindles is controlled to remain stationary; the second row direction bridge: the yarns at the edge of the row direction of each quadrant are moved to the spindles in the adjacent quadrant, and the overall direction is opposite to that of the first row direction bridge, and the spindles are controlled to return to the initial state; a weaving cycle is completed; and the above steps are repeated.

[0016] As a preferred solution of the preparation method for high-temperature seals of aircraft engines of the present invention, the solid inner diameter of the end with a hollow exterior and a solid interior is determined, and the end with a hollow exterior and a solid interior is woven by a three-dimensional four-way weaving method, and the weaving method is the same as the weaving method of the middle section of the woven sample.

[0017] As a preferred solution of the method for preparing high-temperature seals for aircraft engines of the present invention, a cylindrical mold is used to guide the weaving at the end which is solid outside and hollow inside.

[0018] The second object of the present invention is to provide a high-temperature seal, which is made by the above-mentioned preparation method for high-temperature seals for aircraft engines, and one end of the outer hollow and inner solid is inserted into the other end of the outer solid and inner hollow, and the connection is sewed after applying adhesive.

[0019] The beneficial effects of the present invention are as follows: by flexibly increasing or decreasing the yarn at the structural conversion point during the weaving process to adapt to the shape change, the adaptability and reliability of the seal are enhanced, and the requirements for a better sealing structure of the guide vane sealing component are met. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative labor. Among them:

[0021] Figure 1 The present invention is a flow chart of a method for preparing high-temperature seals for aircraft engines.

[0022] Figure 2 The motion law of a Ф5mm three-dimensional four-directional solid round rod spindle used in the preparation method of high-temperature seals for aircraft engines.

[0023] Figure 3The motion law of a Ф6.3mm three-dimensional four-directional solid round rod spindle used in the preparation method of high-temperature seals for aircraft engines.

[0024] Figure 4 The motion law of a Ф6.6mm three-dimensional four-directional solid round rod spindle used in the preparation method of high-temperature seals for aircraft engines.

[0025] Figure 5 A structural perspective view of a high-temperature seal for an aircraft engine.

[0026] Figure 6 The cross-sectional view is a structural plug-in state of a high-temperature seal for an aircraft engine.

[0027] Figure 7 It is a cross-sectional view of the structural plug-in state of the high-temperature seal for an aircraft engine in Example 7. DETAILED DESCRIPTION

[0028] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0029] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0030] Secondly, the present invention is described in detail with reference to schematic diagrams. When describing the embodiments of the present invention in detail, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general scale, and the schematic diagrams are only examples, which should not limit the scope of protection of the present invention. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0031] Furthermore, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0032] Example 1

[0033] Reference Figure 1 , which is the first embodiment of the present invention, provides a method for preparing a high-temperature seal for an aircraft engine.

[0034] S100: The middle part of the braided specimen is braided into a cylindrical shape using a three-dimensional four-way braiding method;

[0035] S200: The two ends of the sample are braided into a structure of hollow outside and solid inside and a structure of solid outside and hollow inside respectively; it is worth noting that the structure of hollow outside and solid inside means that one end of the seal looks hollow on the outside, while the inside is solid. In practical applications, a solid core is maintained inside to provide the necessary strength and stability; the structure of solid outside and hollow inside means that the other end of the seal looks solid on the outside, while the inside is hollow. This design can provide external strength and protection, and the internal cavity can be used as the installation space for other components;

[0036] S300: Adding yarn when weaving from the hollow end to the solid end into the middle part of the sample;

[0037] S400: Yarn reduction is performed when weaving from the middle part of the sample into the end which is solid outside and hollow inside.

[0038] By flexibly adding or reducing yarns at the structural transition points during the weaving process to adapt to morphological changes, the adaptability and reliability of the seal are enhanced.

[0039] Example 2

[0040] This is the third embodiment of the present invention, which is based on the first embodiment.

[0041] Specifically, the three-dimensional four-way weaving method includes a yarn hanging preparation stage, and the yarn hanging preparation stage includes the following steps:

[0042] S101: A middle spindle is reserved at the center of the auxiliary circle, the direction diverging from the center along the radial direction is the column direction, and the direction perpendicular to the column direction is the row direction;

[0043] S102: Divide the plurality of spindles into n groups, where n is an even number ≥ 2;

[0044] S103: The number of spindles in each group is the same, and the spindles in each group are distributed in x rows and y columns, and the lines connecting the centers of the columns of each group of spindles are parallel to each other;

[0045] S104: n groups of spindles are evenly arranged around the circumference of the auxiliary circle, and the auxiliary circle is evenly divided into m quadrants, where m=n, and the n groups of spindles are arranged opposite to each other in pairs relative to the center of the auxiliary circle; the number of spindles in the yth column of each group of spindles is set to be one more or one less than the number of spindles in the y+1th column, and the braided yarns on the spindles are set to have the same cross-sectional area;

[0046] S105: moving all the yarns in the column direction, wherein the yth column of one group of spindles moves toward the y+1th column of another group of spindles arranged oppositely;

[0047] S106: One-column bridge crossing: the yarn on the spindle in the middle of the y-th column of one group of spindles is moved to the y+1-th column of another group of spindles on the opposite side;

[0048] S107: moving all the row-wise yarns after passing through the column-wise bridge once, wherein the xth row and the x+1th row of each group of spindles move in opposite directions, and the spindle farthest from the center of the circle of each group of spindles is controlled to remain stationary;

[0049] S108: One-way bridge: move the yarn at the edge of each quadrant to the spindle in the adjacent quadrant;

[0050] S109: moving all the yarns in the column direction again in the column direction, and the moving direction is opposite to the direction when the column direction passes through the bridge once;

[0051] S1010: Secondary row-to-bridge: Move the yarn on the middle spindle of the yth column of one group of spindles to the y+1th column of another group of spindles on the opposite side, and the moving direction is opposite to the primary row-to-bridge direction;

[0052] S1011: moving all the yarns in the row direction after passing through the bridge in the column direction twice, the moving direction is opposite to the direction of passing through the bridge in the row direction once, and controlling the spindle farthest from the center of the circle of each group of spindles to remain stationary;

[0053] S1012: Secondary row-direction bridge: the yarn at the row-direction edge of each quadrant is transferred to the spindle of the adjacent quadrant. The overall direction is opposite to the primary row-direction bridge, and the control spindle returns to the initial state.

[0054] S1013: Complete a knitting cycle;

[0055] S1014: Repeat the above steps.

[0056] Furthermore, the inner diameter of the solid core of the outer hollow inner solid end is determined, and the outer hollow inner solid end is also woven by a three-dimensional four-way weaving method, and the weaving method is the same as the weaving method of the middle section of the woven sample.

[0057] Furthermore, a cylindrical mold is used to guide the braiding of the solid outer end and the hollow inner end. Using a cylindrical mold to guide the braiding can ensure that the solid outer end and the hollow inner end have a precise geometric shape and size, which is crucial for the installation of high-temperature seals.

[0058] Example 3

[0059] See also Figure 2 , which is the third embodiment of the present invention, and this embodiment is based on embodiment 2.

[0060] When the spindle model is a solid round rod spindle of Ф5mm, the total number of spindles is 28. In S102, the 28 spindles are equally divided into n groups, where n is an even number ≥2. In this embodiment, n is 4, that is, the 28 spindles are equally divided into 4 groups; the 4 groups of spindles are evenly arranged in the circumferential direction of the auxiliary circle, and the auxiliary circle is equally divided into 4 quadrants, and the 4 quadrants are respectively located on the horizontal and vertical midlines of the auxiliary circle.

[0061] The number of spindles in each group is 7, and they are divided into two columns when viewed in the clockwise direction. The number of spindles in the yth column of each group of spindles is set to be one less than the number of spindles in the y+1th column. That is, in the initial state, the number of spindles in each group of spindles in the clockwise direction in this embodiment are 4 and 3 respectively.

[0062] Example 4

[0063] See also Figure 3 , which is the fourth embodiment of the present invention, and this embodiment is based on embodiment 2.

[0064] When the spindle model is a solid round rod spindle of Ф6.3mm, the total number of spindles is 42. In S102, the 42 spindles are equally divided into n groups, where n is an even number ≥2. In this embodiment, n is 2, that is, the 42 spindles are equally divided into 2 groups, and the number of spindles in each group is 21.

[0065] And viewed along the clockwise direction, there are 6 columns in total, that is, in the initial state, the number of columns of spindles in each group of the present embodiment along the clockwise direction are 3, 4, 3, 4, 3 and 4 respectively, which are arranged alternately.

[0066] Example 5

[0067] See also Figure 4 , which is the fifth embodiment of the present invention.

[0068] When the spindle model is a solid round rod spindle of Ф6.6mm, the total number of spindles is 49. In S102, the 42 spindles are equally divided into n groups, where n is an even number ≥2. In this embodiment, n is 2, that is, the 49 spindles are equally divided into 2 groups. The number of spindles in the first group is 24, and the number of spindles in the second group is 25.

[0069] And looking along the clockwise direction, it is divided into 7 columns, that is, in the initial state, the number of columns of the first group of spindles in the clockwise direction of this embodiment are 3, 4, 3, 4, 3, 4 and 3 staggered arrangements respectively; the number of columns of the first group of spindles along the clockwise direction are 4, 3, 4, 3, 4, 3 and 4 staggered arrangements respectively.

[0070] Example 6

[0071] See also Figure 5and Figure 6 , which is the sixth embodiment of the present invention, and is based on Embodiment 1 and Embodiment 2. This embodiment provides a high temperature seal.

[0072] The high temperature seal of this embodiment is made by the above-mentioned preparation method for high temperature seals for aircraft engines, and the end with a hollow outer surface and a solid inner surface is inserted into the end with a solid outer surface and a hollow inner surface, and the connection is sewed after applying adhesive. In this embodiment, the two ends are butt-jointed and aviation glue is applied to stabilize the shape, and fine stitching is performed using a crochet needle to ensure that the braided sealing rope is tightly and firmly connected.

[0073] Example 6

[0074] See also Figure 7 , which is the seventh embodiment of the present invention. This embodiment also provides a high temperature seal.

[0075] This embodiment uses a three-dimensional four-way braiding method to weave the middle section of the sample into a rectangular cross-sectional shape. The middle section of the sample is braided at the same time; then the two ends of the sample are braided into a structure that is hollow outside and solid inside. When in use, the two ends are plugged into each other, and then aviation glue is applied to the connection to stabilize the shape, and a crochet needle is used to sew finely to ensure that the braided sealing rope is tightly and firmly connected.

[0076] Based on the above, the beneficial effects of the present invention are: the present invention enhances the adaptability and reliability of the seal by flexibly increasing or decreasing the yarn at the structural conversion point during the weaving process to adapt to the shape changes, thereby meeting the requirements of the guide vane sealing component for a better sealing structure.

[0077] Importantly, it should be noted that the construction and arrangement of the present application shown in a plurality of different exemplary embodiments are only exemplary. Although only a few embodiments are described in detail in this disclosure, it should be readily understood by those who refer to this disclosure that many modifications are possible (e.g., the size, scale, structure, shape and proportion of various elements, and parameter values ​​(e.g., temperature, pressure, etc.), installation arrangement, use of materials, color, directional changes, etc.) without substantially departing from the novel teachings and advantages of the subject matter described in the application. For example, the element shown as integrally formed can be composed of multiple parts or elements, the position of the element can be inverted or otherwise changed, and the nature or number or position of the discrete element can be changed or changed. Therefore, all such modifications are intended to be included in the scope of the present invention. The order or sequence of any process or method steps can be changed or reordered according to alternative embodiments. In the claims, any "device plus function" clause is intended to cover the structure of performing the function described herein, and is not only structurally equivalent but also equivalent structure. Without departing from the scope of the present invention, other replacements, modifications, changes and omissions can be made in the design, operating conditions and arrangement of the exemplary embodiments. Therefore, the invention is not limited to a specific embodiment, but extends to numerous modifications still falling within the scope of the appended claims.

[0078] Additionally, in order to provide a concise description of exemplary embodiments, all features of an actual embodiment (ie, those features that are not relevant to the best mode presently contemplated for carrying out the invention or those that are not relevant to implementing the invention) may not be described.

[0079] It will be appreciated that in the development of any actual implementation, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort may be complex and time-consuming, but will be a routine task of design, fabrication, and production for those of ordinary skill having the benefit of this disclosure without undue experimentation.

[0080] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. A method for preparing a high-temperature seal for an aerospace engine, characterized in that: include: The middle section of the braided specimen; The two ends of the sample are braided to form a structure of hollow outside and solid inside and a structure of solid outside and hollow inside respectively; When weaving from the hollow end to the solid end into the middle part of the sample, add yarn; The yarn reduction process is carried out when weaving from the middle part of the sample to the end which is solid outside and hollow inside.

2. The method for preparing a high temperature seal for an aircraft engine according to claim 1, characterized in that: The middle part of the sample is woven into a cylindrical shape using a three-dimensional four-way weaving method.

3. The method for preparing a high temperature seal for an aircraft engine according to claim 2, characterized in that: The three-dimensional four-way weaving method includes a preparation stage for hanging yarns, which includes: A middle spindle is reserved at the center of the auxiliary circle. The direction radiating outward from the center along the radius is the column direction, and the direction perpendicular to the column direction is the row direction. Divide the multiple spindles into n groups equally, where n is an even number ≥ 2; The number of spindles in each group is the same, and the spindles in each group are distributed in x rows and y columns, and the lines connecting the centers of the columns of each group of spindles are parallel to each other; The n groups of spindles are evenly arranged around the circumference of the auxiliary circle, and the auxiliary circle is evenly divided into m quadrants, where m=n, and the n groups of spindles are arranged opposite to each other in pairs relative to the center of the auxiliary circle.

4. The method for preparing a high temperature seal for an aircraft engine according to claim 3, characterized in that: The number of spindles in the yth column of each group of spindles is set to be one more or one less than the number of spindles in the y+1th column.

5. The method for preparing a high temperature seal for an aircraft engine according to claim 3 or 4, characterized in that: The braiding yarns on the spindles are arranged to have the same cross-sectional area.

6. The method for preparing a high temperature seal for an aircraft engine according to claim 3, characterized in that: Move all the yarns in the column direction, where the yth column of one group of spindles moves toward the y+1th column of another group of spindles arranged oppositely; Crossing the bridge in a row: move the yarn on the middle spindle of the yth column of a group of spindles to the y+1th column of another group of spindles on the opposite side; Move all the yarns in the row direction after passing through the bridge in the column direction, wherein the xth row and the x+1th row of each group of spindles move in opposite directions, and the spindle farthest from the center of the circle in each group of spindles is controlled to remain stationary; One-way bridge: transfer the yarn at the row edge of each quadrant to the spindle in the adjacent quadrant.

7. The method for preparing a high temperature seal for an aircraft engine according to claim 6, characterized in that: Move all the yarns in the column again, and the moving direction is opposite to the direction when the column passes the bridge once; Secondary row-to-bridge: Move the yarn on the middle spindle of the yth column of a group of spindles to the y+1th column of another group of spindles on the opposite side, and the moving direction is opposite to the primary row-to-bridge direction; Move all the yarns in the row direction after passing through the bridge in the secondary column direction, the moving direction is opposite to the direction of the primary row direction bridge, and control the spindle farthest from the center of the circle of each group of spindles to remain stationary; Secondary row-direction bridge: the yarn at the row edge of each quadrant is transferred to the spindle in the adjacent quadrant. The overall direction is opposite to the primary row-direction bridge, and the control spindle returns to the initial state. Complete one knitting cycle; Repeat the above steps.

8. The method for preparing a high temperature seal for an aircraft engine according to claim 2, characterized in that: To determine the solid inner diameter of the end that is hollow outside and solid inside, the end that is hollow outside and solid inside is also woven using a three-dimensional four-way weaving method, and the weaving method is the same as the weaving method for the middle section of the woven sample.

9. The method for preparing a high temperature seal for an aircraft engine according to claim 2, characterized in that: A cylindrical die is used to guide the weaving at the end which is solid outside and hollow inside.

10. A high temperature seal, characterized in that: The high-temperature seal for an aircraft engine is made by the preparation method of any one of claims 1 to 7, wherein one end of the outer hollow and inner solid seal is inserted into one end of the outer solid and inner hollow seal, and the joint is sewed after being coated with adhesive.

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