An engine turbine guide vane assembly method and guide vane

Abstract

The present application relates to the technical field of guider vane assembly, and particularly relates to an engine turbine guider vane assembly method and guider, wherein the first guider vane to the penultimate guider vane is sequentially assembled on the inner support of the guide vane, and the relative position is limited by the adjustable limit, at this time, the vane is not completely locked, and the fine adjustment allowance is reserved; then, the assembled vane is expanded outward along the radial direction, a sufficient gap is formed between the adjacent vanes to provide an insertion channel for the last vane, after the last vane is assembled into the gap, the position of the last vane is fixed again by the adjustable limit, the positioning pin holes of all vanes are aligned, the assembly space is dynamically adjusted, the interference problem is completely eliminated, the damage or rework caused by forced assembly is avoided, after the last vane is limited, all vanes are synchronously contracted inward along the radial direction, the accumulated error is eliminated by the mechanical linkage, and thus the precise assembly is realized, and the interference and precision problems in the turbine guider vane assembly are systematically solved.

Description

Technical Field

[0001] This invention relates to the field of guide vane assembly technology, specifically to an engine turbine guide vane assembly method and guide vane. Background Technology

[0002] As a core component of the modern aviation industry, aero-engines are hailed as the "crown jewel of industry," and their technological level directly determines the overall strength of an aviation industry. With the rapid development of the global air transport industry and the continuous upgrading of military aviation equipment, the performance requirements for aero-engines are becoming increasingly stringent, primarily reflected in higher thrust-to-weight ratios, lower fuel consumption rates, longer service life, and lower emissions and noise levels. Improving these performance indicators relies not only on the optimization of the overall engine design but also on the precision manufacturing and efficient assembly of every key component. The turbine guide vane, as a crucial component of the hot-end of an aero-engine, primarily functions to guide high-temperature, high-pressure combustion gases to the turbine blades in a predetermined direction, ensuring the efficient conversion of combustion energy into the mechanical energy of turbine rotation. The performance of the guide vane directly affects the turbine's efficiency, durability, and reliability, thus impacting the overall engine performance. Therefore, the design, manufacturing, and assembly technologies of turbine guide vanes have always been a key focus and challenge in aero-engine research and development. With continuous advancements in materials science, manufacturing processes, and assembly technologies, the design of turbine guide vanes is becoming increasingly complex, demanding ever higher manufacturing precision and assembly quality. Especially in extreme operating environments of high temperature, high pressure, and high speed, even minute deformations or assembly errors in components such as guide vanes and sealing plates can lead to severe performance degradation or even malfunctions. Therefore, achieving high-precision and high-efficiency assembly of turbine guide vanes has become one of the key factors restricting the improvement of aero-engine performance and mass production.

[0003] Existing turbine guide vanes typically consist of several components, including guide vane blades, guide vane inner supports, locating pins, and sealing plates. The guide vane blades are the core component, and their number depends on the engine design requirements, usually dozens, evenly distributed circumferentially. Each guide vane blade has a locating hole for precise alignment with the corresponding locating hole on the guide vane inner support, and is secured by locating pins to ensure the stability and reliability of the blade under high-speed rotation and high-temperature combustion gas impact. The sealing plate, as an important component of the guide vane, primarily functions to seal the gap between adjacent guide vane blades, preventing high-temperature combustion gas leakage and improving turbine efficiency. The sealing plate is typically installed in sealing grooves on the upper and lower edge plates of the guide vane blades. These sealing grooves are designed to be closed at both ends, and the sealing grooves of adjacent blades together form a sealing cavity. The sealing plate is enclosed within this cavity, connecting the upper and lower edge plates of the guide vane blade into two concentric annular units, forming a sealed airflow channel together with the guide vane blade body. In existing assembly techniques, the assembly sequence is crucial due to the special structural design of the guide vanes and sealing plates. If the guide vanes are assembled first, the sealing plates cannot be installed into the sealing slots due to space constraints; therefore, the sealing plates must be installed into the sealing slots of the vanes first, and then the vanes with sealing plates are assembled one by one onto the inner support of the guide vanes and secured with locating pins. This assembly method is theoretically feasible, but faces many challenges in practical operation. For example, see... Figures 1 to 3 A certain engine guide vane consists of guide vane blades, guide vane inner support, locating pins, a first sealing plate, a second sealing plate, and a third sealing plate. There are 23 guide vane blades in total. Each guide vane has two locating holes, which correspond to the inner support of the guide vane for installation. They are then connected to the inner support as a whole by 46 locating pins. The guide vane blades have three sealing grooves on their upper and lower edges, all of which are closed at both ends. The sealing grooves of adjacent guide vane blades together form a sealing cavity, within which the sealing plate is enclosed. This seals the upper and lower edges of the guide vane blades, connecting them into two concentric annular units, forming a sealed airflow channel together with the guide vane blade body. If the blades are installed first, the sealing plate cannot be installed. Therefore, the sealing plate must be installed into the blade first, and then the blade with the sealing plate is installed on the inner support and fixed with pins. In actual assembly, the blades are assembled one by one along the circumference. Due to the interference of the sealing plate, the last blade cannot be installed. Forced compression or special tools are required, which can easily damage the parts and result in low assembly efficiency. Summary of the Invention

[0004] To address the problems of difficult and inefficient assembly of turbine guide vanes in existing technologies, this invention provides a method for assembling engine turbine guide vanes and a guide vane.

[0005] To achieve the above objectives, the present invention employs the following technical solution: This invention provides a method for assembling engine turbine guide vanes, comprising: The first guide vane to the second to last guide vane are sequentially installed on the inner support of the guide vane, and the adjacent positioning pin holes of the adjacent guide vanes are adjusted and limited in sequence. Adjust all guide vanes that have been installed on the inner support of the guide vane radially outward to create gaps between adjacent vanes; The last guide vane is supported inside the guide vane and its positioning pin hole with the adjacent guide vane is adjusted to limit its movement. After the last guide vane is positioned, all guide vanes are simultaneously retracted radially inward along the inner support of the guide vane, and the locating pin holes of all guide vanes are aligned with the locating pin holes on the inner support of the guide vane. Then, all positioning is removed, and the corresponding locating pins are installed to complete the assembly of the engine turbine guide vane.

[0006] Optionally, a fuse can be used to adjust the positioning pin holes of adjacent guide vanes.

[0007] Optionally, during the process of adjusting all guide vanes already installed on the inner support of the guide vane radially outward to create gaps between adjacent vanes, the width of the gaps between adjacent vanes is 0.15 to 0.4 mm.

[0008] Optionally, during the process of adjusting all guide vanes already installed on the inner support of the guide vane radially outward to create a gap between adjacent vanes, the width of the gap between adjacent vanes is 0.3 mm.

[0009] Optionally, during the process of sequentially installing the first guide vane to the penultimate guide vane on the inner support of the guide vane and sequentially adjusting and limiting the adjacent positioning pin holes of adjacent guide vanes, after adjusting and limiting the adjacent positioning pin holes of adjacent guide vanes, the positioning pin holes of each guide vane and the positioning pin holes on the inner support of the guide vane are respectively aligned radially along the inner support of the guide vane.

[0010] Optionally, after the last guide vane is positioned, the process further includes adjusting the installed guide vane, specifically: Adjust the installed guide vanes to be evenly separated along the inner support of the guide vane, and then simultaneously retract all the guide vanes inward along the inner support of the guide vane.

[0011] Optionally, after adjusting the installed guide vanes to be evenly separated along the inner support radial direction of the guide vanes, the gap between adjacent guide vanes is equal.

[0012] Optionally, it also includes a process for testing the installation reliability of the sealing strip of the guide vane after it has been installed and adjusted for positioning.

[0013] Optionally, the total number of guide vanes is 23.

[0014] The present invention also provides an engine turbine guide, which is assembled using the above-described engine turbine guide blade assembly method.

[0015] Compared with the prior art, the present invention has the following beneficial effects: This invention provides a method for assembling turbine guide vanes. First, the first to the penultimate guide vane are sequentially installed on the inner support of the guide vane, with their relative positions limited by adjustable stops. At this point, the vanes are not completely locked, allowing for fine-tuning. Then, the installed vanes are expanded radially outwards to create sufficient gaps between adjacent vanes, providing an insertion channel for the final vane. After the final vane is inserted into the gap, its position is again fixed by adjustable stops, ensuring that the locating pin holes of all vanes are aligned. By dynamically adjusting the assembly space, interference problems are completely eliminated, avoiding damage or rework caused by forced assembly. After the final vane is positioned, all vanes are synchronously contracted radially inwards, using mechanical linkage to eliminate accumulated errors, thereby achieving precise assembly and improving assembly efficiency. This method is simple, easy to operate, and requires no additional complex tools. It systematically solves the interference and precision problems in turbine guide vane assembly, significantly improving assembly efficiency and reliability, while laying the foundation for automated production. It has broad application prospects and economic value.

[0016] A fuse is used to adjust the positioning pin holes of adjacent guide vanes. The fuse has plasticity and moderate elasticity, and can temporarily limit the positioning pin holes of adjacent vanes by bending, winding or snapping. It has the characteristics of low cost and good operability.

[0017] During the process of adjusting all guide vanes already installed on the inner support of the guide vane radially outward to create gaps between adjacent vanes, the width of the gaps between adjacent vanes is 0.2–0.4 mm. Preferably, the width of the gaps between adjacent vanes is 0.3 mm. If the gap is too small, excessive friction may cause surface scratches or deformation of the locating pin holes when the last guide vane is inserted; if the gap is too large, the guide vane may deflect due to the excessive gap after insertion, causing misalignment of the locating pin holes. Precisely controlling the gap width between adjacent guide vanes to 0.2–0.4 mm ensures smooth insertion of the last guide vane while improving assembly accuracy.

[0018] During the process of sequentially installing the first guide vane to the penultimate guide vane on the inner support of the guide vane, and then adjusting and limiting the adjacent positioning pin holes of adjacent guide vanes, after adjusting and limiting the adjacent positioning pin holes of adjacent guide vanes, the positioning pin holes of each guide vane and the positioning pin holes on the inner support of the guide vane are respectively aligned radially along the inner support of the guide vane. After aligning them one by one, the difficulty of subsequent fine adjustment can be saved, the error of rework correction can be reduced, and thus the assembly efficiency can be improved.

[0019] After the last guide vane is positioned, the process also includes adjusting the installed guide vanes. Adjusting adjacent guide vanes to have equal gaps ensures the consistency of the subsequent retraction process, avoids local overload of the guide vanes, and improves assembly quality and reliability.

[0020] It also includes a process for testing the installation reliability of the sealing plates of the guide vanes after they have been installed and adjusted for limit, which can ensure the overall stability of the final installation and improve the reliability of the assembly.

[0021] The present invention also provides an engine turbine guide, which is assembled using the above-described engine turbine guide blade assembly method. The engine turbine guide has the characteristics of good structural reliability, low operation and maintenance cost, and good economy. Attached Figure Description

[0022] Figure 1 This is a structural diagram of an existing guide vane.

[0023] Figure 2 for Figure 1 The first sealing strip in the direction of the P1-P1 rotation.

[0024] Figure 3 for Figure 1 The second sealing strip in the P2-P2 rotation direction.

[0025] Figure 4 for Figure 1 The third sealing strip in the P3-P3 rotation direction.

[0026] Figure 5 This is a structural diagram of the guide vane.

[0027] Figure 6 The diagram shows the internal support structure of the guide vane, where a is a partial cross-sectional view and b is a partial side view.

[0028] Figure 7 This is a structural diagram of the assembled guide.

[0029] Figure 8 This is a flowchart illustrating a method for assembling engine turbine guide vanes according to the present invention. Wherein, 1-guide vane, 2-guide vane inner support, 3-positioning pin, 4-first sealing plate, 5-second sealing plate, 6-third sealing plate; 1a-first sealing groove, 1b-second sealing groove, 1c-third sealing groove. Detailed Implementation

[0030] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0031] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0032] The present invention will be further described in detail below with reference to specific embodiments. These descriptions are for explanation purposes only and are not intended to limit the scope of the invention.

[0033] See Figures 1 to 7A certain type of engine guide vane consists of guide vane 1, guide vane inner support 2, positioning pin 3, first sealing plate 4, second sealing plate 5, and third sealing plate 6. There are 23 guide vane pieces in total. Guide vane 1 has two positioning holes, which correspond to the inner support 2 for installation. It is connected to the inner support 2 as a whole by 46 positioning pins. The three sealing grooves at the upper and lower edges of guide vane 1 are the first sealing groove 1a, the second sealing groove 1b, and the third sealing groove 1c, all of which are closed at both ends. In this design, the sealing grooves of adjacent guide vanes 1 together form a sealing cavity, within which the sealing plate is enclosed. This connects the upper and lower flanges of guide vane 1 into two concentric annular units, forming a sealed airflow channel together with the guide vane body. In actual assembly, if guide vane 1 is installed first, the sealing plate cannot be inserted. Therefore, the sealing plate must be installed first, and then the guide vane 1 with the sealing plate is installed on the inner support and secured with the locating pin 3. During actual assembly, the vanes are assembled one by one along the circumference. Due to interference from the sealing plate, the last guide vane 1 cannot be installed, resulting in ineffective assembly.

[0034] See Figure 8 To address the aforementioned problems, this invention discloses a method for assembling an engine turbine guide vane 1, comprising: S1: The first guide vane 1 to the second to last guide vane 1 are sequentially installed on the inner support of the guide vane, and the adjacent positioning pin holes of the adjacent guide vane 1 are adjusted and limited in sequence; Optionally, after the adjacent positioning pin holes of the adjacent guide vane 1 are adjusted and limited, the positioning pin holes of each guide vane 1 and the positioning pin holes on the inner support of the guide vane are respectively aligned radially along the inner support of the guide vane.

[0035] S2: Adjust all guide vanes 1 that have been installed on the inner support 2 of the guide vane radially outward to create a gap between adjacent vanes; optionally, the width of the gap between adjacent vanes is 0.15 to 0.4 mm; more preferably 3 mm.

[0036] S3: Place the last guide vane 1 on the inner support 2 of the guide vane and adjust its positioning pin hole with the adjacent guide vane 1. S4: After the last guide vane 1 is limited, all guide vanes 1 are simultaneously retracted radially inward along the inner support of the guide vane, and the positioning pin holes of all guide vanes 1 are aligned with the positioning pin holes on the inner support of the guide vane. Then, all the limitations are removed, and the corresponding positioning pins 3 are installed to complete the assembly of the engine turbine guide vane 1.

[0037] It also includes the adjustment process for the installed guide vane 1, specifically: Adjust the installed guide vane 1 to be evenly separated along the inner support of the guide vane, so that the gap between adjacent guide vane 1 is equal, and then simultaneously retract all guide vane 1 inward along the inner support of the guide vane.

[0038] Optionally, it also includes a process for testing the installation reliability of the sealing plate of the guide vane 1 after it has been installed and adjusted for positioning.

[0039] The following example illustrates the assembly of a guide with 23 guide vanes: First, install two blades on the inner support 2 of the guide vane without installing the limit pin. Insert the safety wire through the adjacent positioning pin holes of the two blades and gently activate the safety to ensure that the sealing plate does not fall off.

[0040] Then, install the 3rd, 4th, ... up to the 22nd guide blade 1 in sequence, without installing the limit pin, and insert the limit holes of the 2nd and 3rd, 4th and 5th ... 21st and 22nd adjacent guide blades 1 into the fuse in sequence, and gently activate the safety to ensure that the sealing plate does not fall off.

[0041] Adjust the 22 blades that have already been installed radially outwards by an appropriate amount of size, so that a circumferential gap of 3mm is created between each blade, thus creating installation space for the 23rd blade with a sealing plate.

[0042] Install the 23rd blade into the inner support 2 of the guide vane without installing the limit pin. Insert the 22nd and 23rd blades, and the 23rd blade and the 1st blade of the guide vane 1 into the adjacent positioning pin holes of the fuse, and gently activate the fuse to ensure that the sealing plate does not fall off.

[0043] The 23 blades are evenly separated in sequence, with a circumferential gap of about 0.3mm between each pair of adjacent guide vanes. Then, the 23 blades are simultaneously contracted radially. After correcting them one by one so that the positioning pin holes of the guide vane 1 are aligned with the positioning pin holes on the inner support 2 of the guide vane, the fuses are pulled out one by one, the positioning pins 3 are installed, and the corresponding positioning pins 3 are inserted to complete the assembly of the engine turbine guide vane 1.

[0044] As can be seen, this method involves first sequentially installing the first to the penultimate guide vane blades 1 onto the inner support of the guide vane, and then limiting their relative positions using adjustable limiters. At this point, the blades are not completely locked, leaving room for fine-tuning. Next, the installed blades are expanded radially outward (e.g., through the expansion structure of the inner support of the guide vane or an external thrust device) to create sufficient gaps between adjacent blades, providing an insertion channel for the last blade. After the last blade is inserted into the gap, its position is again fixed using adjustable limiters, ensuring that the locating pin holes of all blades are aligned. By dynamically adjusting the assembly space, interference problems are completely eliminated, avoiding damage or rework caused by forced assembly. After the last blade is limited, all blades are synchronously contracted radially inward, using mechanical linkage to eliminate accumulated errors, thereby achieving precise assembly and improving assembly efficiency. This method is simple, easy to operate, and requires no additional complex tools. It systematically solves the interference and precision problems in the assembly of turbine guide vane blades 1, significantly improving assembly efficiency and reliability, while laying the foundation for automated production. It has broad application prospects and economic value.

[0045] The present invention also provides an engine turbine guide, which is assembled using the above-described engine turbine guide blade 1 assembly method. The engine turbine guide has the characteristics of good structural reliability, low operation and maintenance cost, and good economy.

[0046] In summary, this invention provides an assembly method for engine turbine guide vane 1 and a guide vane. It ingeniously utilizes an adjustable limit, reserved installation space, and synchronous retraction installation method, and cleverly uses inexpensive fuses. With the mounting surface on the inner support side of the guide vane as a reference, it realizes radial and circumferential adjustment during the installation of the vane. This achieves precise and efficient installation of the guide vane 1 while preventing the sealing plate from falling off during vane movement, thus overcoming the assembly difficulties of this type of vane with sealing plate.

[0047] The above description is merely a preferred embodiment of the present invention and is not intended to limit the technical solution of the present invention in any way. Those skilled in the art should understand that, without departing from the spirit and principles of the present invention, the technical solution can be modified and replaced in several simple ways, and these modifications and replacements are all within the scope of protection covered by the claims.

Claims

1. A method for assembling engine turbine guide vanes, characterized in that, include: Insert the sealing strip into the guide vane to be assembled; The first guide vane to the second to last guide vane are sequentially installed on the inner support of the guide vane, and the adjacent positioning pin holes of the adjacent guide vanes are adjusted and limited in sequence. Adjust all guide vanes that have been installed on the inner support of the guide vane radially outward to create a gap between adjacent guide vane blades; The last guide vane is installed on the inner support of the guide vane and its positioning pin hole is adjusted to limit its movement with that of the adjacent guide vane; wherein, a fuse is used to adjust the positioning pin hole of the adjacent guide vane. After the last guide vane is positioned, all guide vanes are simultaneously retracted radially inward along the inner support of the guide vane, and the locating pin holes of all guide vanes are aligned with the locating pin holes on the inner support of the guide vane. Then, all positioning is removed, and the corresponding locating pins are installed to complete the assembly of the engine turbine guide vane.

2. The engine turbine guide vane assembly method according to claim 1, characterized in that, During the process of adjusting all guide vanes already installed on the inner support of the guide vane radially outward to create gaps between adjacent vanes, the width of the gaps between adjacent vanes is 0.15 to 0.4 mm.

3. The engine turbine guide vane assembly method according to claim 2, characterized in that, During the process of adjusting all guide vanes already installed on the inner support of the guide vane radially outward to create gaps between adjacent vanes, the width of the gaps between adjacent vanes is 0.3 mm.

4. The engine turbine guide vane assembly method according to claim 1, characterized in that, During the process of sequentially installing the first guide vane to the second-to-last guide vane on the inner support of the guide vane, and then adjusting and limiting the adjacent positioning pin holes of the adjacent guide vane, after adjusting and limiting the adjacent positioning pin holes of the adjacent guide vane, the positioning pin holes of each guide vane and the positioning pin holes on the inner support of the guide vane are respectively aligned radially along the inner support of the guide vane.

5. The engine turbine guide vane assembly method according to claim 1, characterized in that, After the last guide vane is positioned, the process also includes adjusting the installed guide vane, specifically: Adjust the installed guide vanes to be evenly separated along the inner support of the guide vane, and then simultaneously retract all the guide vanes inward along the inner support of the guide vane.

6. The engine turbine guide vane assembly method according to claim 5, characterized in that, After adjusting the installed guide vanes to be evenly separated along the inner support radial direction of the guide vane, the gap between adjacent guide vane blades is equal.

7. The engine turbine guide vane assembly method according to claim 1, characterized in that, It also includes the process of testing the installation reliability of the sealing strip of the guide vane after it has been installed and adjusted for limit.

8. The method for assembling engine turbine guide vanes according to any one of claims 1-7, characterized in that, The guide vanes have a total of 23 blades.

9. An engine turbine guide vane, characterized in that, The engine turbine guide vane is assembled using the assembly method according to any one of claims 1-8.

Images