Turbine assembly method and injection tool

Abstract

The present invention discloses a turbine assembly method and an injection tool, which relate to the field of aeroengines and are used to improve the installation reliability of the sealing strips. The turbine assembly method includes the following steps: filling a volatile binder into the grooves of each guide vane group; inserting the sealing strips into the grooves of each guide vane group; moving the turbine casing towards the direction of the previous-stage rotor assembly and arranging all the guide vane groups one by one on the previous-stage rotor assembly; wherein, all the guide vane groups enclose a ring shape; moving the turbine casing backward in multiple times, and at the same time moving each guide vane group uniformly in a fixed direction in the circumferential direction, so that the guide vane groups slowly contract to form a stator assembly; the number of times of multiple times is greater than 2 times. By adopting the above installation method, the sealing strips are not easy to fall off, and there is no need to hoist the stator assembly as a whole, reducing the probability of the sealing strips falling off, saving the installation steps, and having higher installation efficiency.

Description

Technical Field

[0001] The present invention relates to the field of aero-engines, and particularly to a turbine assembly method and an injection tool. Background Art

[0002] The low-pressure turbine of an aero-engine is composed of multiple stages of rotors and stators alternately. A plurality of sector-shaped guide vane groups are installed on a turbine casing to form a stator integral ring. The low-pressure turbine guide vane groups adopt a multi-piece structure (formed by casting two or more blades into a group), and the gap between adjacent blades is called a window. To ensure the turbine efficiency, a seal piece is installed between adjacent guide vane groups to fill the assembly gap between adjacent two guide vane groups and prevent high-temperature gas leakage. The seal piece is about 5 mm wide and 0.5 mm thick, and is installed in the installation groove formed by two adjacent guide vane groups. Specifically, each of two adjacent guide vane groups has half of the groove body, and the two groove bodies are pieced together to form a complete installation groove.

[0003] The inventor found that there are at least the following problems in the prior art: the existing installation method makes the seal piece easy to fall into the flow passage of the turbine. Summary of the Invention

[0004] The present invention provides a turbine assembly method and an injection tool to improve the installation reliability of the seal piece.

[0005] An embodiment of the present invention provides a turbine assembly method, including the following steps:

[0006] Filling a volatile binder into the groove body of each guide vane group;

[0007] Inserting a seal piece into the groove body of each of the guide vane groups;

[0008] Changing the axial relative position of the turbine casing and the previous-stage rotor assembly so that the previous-stage rotor assembly corresponds to a first position of the turbine casing, and surrounding all the guide vane groups into a ring shape; wherein, after the turbine is installed in place, the previous-stage rotor assembly corresponds to a second position of the turbine casing; the inner diameter of the turbine casing at the first position is greater than the inner diameter of the turbine casing at the second position;

[0009] Moving the turbine casing backward in multiple times, and simultaneously moving each guide vane group uniformly in a fixed direction in the circumferential direction, so that the guide vane groups slowly contract to form a stator assembly; the number of times of the multiple times is greater than 2 times.

[0010] In some embodiments, the following steps are adopted to change the axial relative position of the turbine casing and the previous-stage rotor assembly:

[0011] Keep the turbine casing stationary and move the entire rotor assembly where the previous-stage rotor assembly is located; or, keep the entire rotor assembly where the previous-stage rotor assembly is located stationary and move the turbine casing; or, move the turbine casing and the entire rotor assembly where the previous-stage rotor assembly is located towards each other.

[0012] In some embodiments, each of the guide vane groups includes at least two fixedly connected guide vanes; the slots are provided on both sides of each of the guide vane groups, and the step of inserting the sealing piece into the slots of the guide vane groups includes:

[0013] Insert the sealing piece into the slot on one side of each of the guide vane groups, and the slot on the other side of each of the guide vane groups is empty to accommodate the sealing piece inserted into the slot on one side of the adjacent guide vane assembly.

[0014] In some embodiments, the step of filling the slots of each guide vane group with a volatile binder includes:

[0015] Inject liquid volatile binder into the slots of each of the guide vane groups;

[0016] Wait for the liquid volatile binder injected into the slots of each of the guide vane groups to cool and solidify into a solid state or a paste state;

[0017] Insert the sealing piece into the slots of each of the guide vane groups, and the volatile binder adheres to the sealing piece.

[0018] In some embodiments, the step of injecting liquid volatile binder into the slots of each of the guide vane groups includes:

[0019] The volatile binder is vaseline, and the vaseline is heated to 80°C - 90°C;

[0020] Use an injection tool to inject liquid vaseline into the respective slots of each guide vane group.

[0021] In some embodiments, the injection tool includes:

[0022] A syringe configured to fill the slots of the guide vane group with a volatile binder; and

[0023] A heater connected to or disposed adjacent to the syringe to heat the volatile binder in the syringe.

[0024] In some embodiments, the syringe includes:

[0025] An injection barrel having a receiving cavity and an injection port communicating with the receiving cavity; and

[0026] A piston, slidably mounted in the accommodating cavity;

[0027] Wherein, the heater wraps the accommodating cavity or abuts against the outer wall of the accommodating cavity.

[0028] In some embodiments, the volatile binder is one or more of the following substances: petrolatum, paraffin wax, beeswax.

[0029] In some embodiments, the groove bodies on each side of the guide vane group each include:

[0030] A first groove, located at the outer edge of the guide vane group;

[0031] A second groove, located at the inner edge of the guide vane group; and

[0032] A third groove, located at the inner edge of the guide vane group and on a side of the second groove away from the first groove, and the second groove and the third groove are in communication;

[0033] Wherein, the first grooves of two adjacent guide vane groups correspond to each other to form a first installation groove, and a sealing piece is installed in the first installation groove; the second grooves of two adjacent guide vane groups correspond to each other to form a second installation groove, and a sealing piece is installed in the second installation groove; the third grooves of two adjacent guide vane groups correspond to each other to form a third installation groove, and a sealing piece is installed in the third installation groove.

[0034] The embodiment of the present invention further provides an injection tool used in a turbine assembly method, including:

[0035] A syringe, configured to fill a volatile binder into the groove body of the guide vane group; and

[0036] A heater, connected to or disposed adjacent to the syringe to heat the volatile binder in the syringe.

[0037] In some embodiments, the syringe includes:

[0038] An injection barrel, having an accommodating cavity and an injection port communicating with the accommodating cavity; and

[0039] A piston, slidably mounted in the accommodating cavity;

[0040] Wherein, the heater wraps the accommodating cavity or abuts against the outer wall of the accommodating cavity.

[0041] The turbine assembly method provided by the above technical solution is applicable to high-pressure turbines, low-pressure turbines, etc. Taking the low-pressure turbine as an example, during the installation process of the sealing strips, the sealing strips are first fixed in the grooves of the guide vane group by using a volatile binder. One side of each guide vane group is pre-installed with a sealing strip, and there is no pre-installed sealing strip in the groove on the other side of the guide vane group. The groove on the other side of the guide vane group without the installed sealing strip faces the groove of the adjacent guide vane group with the installed sealing strip. Then, the turbine casing is moved forward to the previous-stage rotor, and the whole formed by the guide vane group and the sealing strip is stacked at a suitable position in the casing. Compared with the distance between the stator assembly and the adjacent rotor assembly after installation, the distance between this position and the rotor assembly is closer. Since the low-pressure turbine is in a conical divergent shape as a whole, the cross-sectional area of the low-pressure turbine casing is larger the more backward it is. During the installation process, the radius dimension of the stator assembly is large. Actually, because the guide vane group is not installed in place, the gap between two adjacent guide vane groups is larger than the installation requirement. The larger the gap between two guide vane groups, the larger the operating space, and it is easier to place the whole formed by the guide vane group and the sealing strip. It can be seen that the above technical solution, on the one hand, sets a separate fixing step for the sealing strip, and on the other hand, adopts a pre-installed component formed by the guide vane group and the sealing strip, and finally circumferentially squeezes each component surrounded in a circle to realize the assembly of the low-pressure turbine. By using the above installation method, large-scale adjustment of the position of the guide vane group is avoided. During the adjustment process, the sealing strip is subjected to a small external force, which is not enough to damage the bonding state of the sealing strip. Therefore, the probability of the sealing strip falling off is reduced, and the installation steps are saved, and the installation efficiency is higher. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0043] Figure 1 is a schematic flow chart of the turbine assembly method provided by an embodiment of the present invention;

[0044] Figure 2 is a schematic diagram of the relative position relationship between the stator assembly and the rotor assembly of the low-pressure turbine provided by an embodiment of the present invention;

[0045] Figure 3 is a schematic diagram of the relative position relationship between the guide vane groups of the stator assembly of the low-pressure turbine provided by an embodiment of the present invention;

[0046] Figure 4 is a three-dimensional schematic diagram of the injection tool provided by an embodiment of the present invention;

[0047] Figure 5 is a cross-sectional schematic diagram of the injection tool provided by an embodiment of the present invention;

[0048] Figure 6Schematic diagram of the support of the low-pressure turbine stator assembly and rotor assembly provided by the embodiment of the present invention.

[0049] Reference numerals:

[0050] 1. Stator assembly; 2. Rotor assembly; 3. Casing; 6. Guide vane group; 7. Sealing piece; 8. First adjusting mechanism; 9. Second adjusting mechanism; 10. Turbine casing

[0051] 4. Syringe; 5. Piston; 41. Accommodation cavity; 42. Injection port; 61. Groove body; 61a. First groove; 61b. Second groove; 61c. Third groove. Detailed implementation manners

[0052] The following combines Figures 1 to 6 to elaborate on the technical solution provided by the present invention in more detail.

[0053] Through long-term creative labor, the inventor found that: only after two guide vane groups are assembled and the installation groove for installing the sealing piece forms a closed groove, the sealing piece will not fall off. During the installation of the guide vane group, before the two halves of the installation groove are pieced together to form a closed groove, the sealing piece is in a non-limited state and there is a great risk of falling off. Since the window size between the rotor assembly and the stator assembly is much larger than the size of the sealing piece, once the sealing piece falls out of the installation groove, it will enter the flow channel from the blade window, causing danger, and it is difficult to take out the sealing piece that has fallen into the flow channel. In addition, the guide vane groups are assembled one by one in sequence. The sealing piece on the last guide vane group is restricted by space and the assembly difficulty is extremely high (the sealing piece is installed in the installation groove between adjacent guide vane groups, and the circumferential width of the sealing piece is much larger than the overlapping gap between adjacent guide vane groups). In order to install the sealing piece on the last guide vane group, it is necessary to repeatedly adjust the relative positions of the guide vane groups. Since the sealing piece is in a non-fixed state, the sealing piece is very likely to fall off during the adjustment of the guide vane groups.

[0054] To solve this technical problem and reduce the probability of the sealing piece falling off during the installation of the stator assembly, the inventor proposed the following turbine assembly method.

[0055] Refer to Figures 1 to 3 , the embodiment of the present invention also provides a turbine assembly method. The turbine can be a low-pressure turbine, a high-pressure turbine, etc. The turbine includes multiple stages of stator assemblies 1 and multiple stages of rotor assemblies 2. Each stage of stator assembly 1 includes multiple guide vane groups 6, and the multiple guide vane groups 6 enclose a circle to form one stage of stator assembly 1. The turbine assembly method introduced later is mainly about how to assemble the stator assembly 1. Specifically, the turbine assembly method includes the following steps:

[0056] Step S100: Fill the groove body 61 of each guide vane group 6 with a volatile binder.

[0057] The turbine includes a rotor assembly 2, a stator assembly 1, and a casing 3. Along the axial direction of the turbine, the rotor assembly 2 and the stator assembly 1 are arranged alternately. The stator assembly 1 includes a plurality of guide vane groups 6, which may also be referred to as guide vane assemblies. Each guide vane group 6 includes a plurality of guide vanes welded into a whole. The structure of each guide vane group 6 is the same. The plurality of guide vane groups 6 enclose a circle to form the stator assembly 1. The structure of each stage of the stator assembly 1 is similar, but the size is different. For the installed stator assembly 1, there are other guide vane groups 6 on both sides of each guide vane group 6. The one side and the other side described later are the orientations represented by the two sides here. A groove 61 is provided on each side of each guide vane group 6, and the size of each groove 61 can accommodate half of the sealing piece 7. The grooves 61 of two adjacent guide vane groups 6 are opposite to each other and pieced together to form a complete installation groove. Each installation groove corresponds to a sealing piece 7. The number of grooves 61 on each side of the guide vane group 6 is three: a first groove 61a, a second groove 61b, and a third groove 61c. The first groove 61a is located at the outer edge of the guide vane group 6. The second groove 61b is located at the inner edge of the guide vane group 6. The third groove 61c is located at the inner edge of the guide vane group 6 and on the side of the second groove 61b away from the first groove 61a, and the second groove 61b and the third groove 61c are connected.

[0058] A volatile binder is coated in the first groove 61a, the second groove 61b, and the third groove 61c. The volatile binder uses one or more of the following substances: petrolatum, paraffin wax, and beeswax. These substances act as binders during the installation of the sealing piece 7 and fix the sealing piece 7 in the groove 61. During the operation of the low-pressure turbine, due to the high working temperature, these substances will vaporize and evaporate into gases, with almost no residue, which will not affect the normal operation of the low-pressure turbine and will not cause pollution.

[0059] In some embodiments, the step of filling the volatile binder in the groove 61 of each guide vane group 6 includes: injecting a liquid volatile binder into the groove 61 of each guide vane group 6; waiting for the liquid volatile binder injected into the groove 61 of each guide vane group 6 to cool and solidify into a solid state or a paste state; inserting the sealing piece 7 into the groove 61 of each guide vane group 6, and the volatile binder adheres to the sealing piece 7. Since the liquid volatile binder is in a liquid state, it is easy to inject into the groove 61. After the liquid volatile binder is injected into the groove 61, it gradually becomes solid or paste-like under the cooling of the ambient temperature. The volatile binder in these states has strong viscosity and can firmly adhere to the sealing piece 7.

[0060] In some embodiments, the steps of injecting a liquid volatile binder into the slots 61 of each guide vane group 6 include: using petrolatum as the volatile binder, heating the petrolatum to 80°C - 90°C; injecting the liquid petrolatum into each slot 61 of each guide vane group 6 by means of an injection tool. After the petrolatum is heated to the liquid state, the injection tool sucks in the liquid petrolatum. A heater is used to keep the petrolatum in the liquid state in the injection tool, so that the petrolatum can be conveniently injected into the slot 61. The liquid petrolatum will turn back into a solid or paste state after being placed at room temperature for about 30 minutes.

[0061] Step S200: Insert the sealing piece 7 into the slot 61 of the guide vane group 6.

[0062] The turbine is a working component of an aeroengine, and the turbine flow passage is of a diffusive shape. During the assembly process of the guide vane group, taking advantage of the diffusive characteristics of the turbine flow passage, the cross-sectional area of the turbine casing 10 is larger at positions closer to the downstream. The casing is moved forward by a certain distance, and all the guide vane groups 6 are successively placed on the rotor assembly of the previous stage (after the cross-section becomes larger, there will be enough circumferential space for installing the sealing piece when installing the last guide vane group 6). Then, the casing is slowly moved backward in multiple steps, and at the same time, each guide vane group 6 is uniformly moved in the circumferential direction along a fixed direction, so that the guide vane group 6 slowly contracts into the final ring shape.

[0063] In some embodiments, each guide vane group 6 includes at least two fixedly connected guide vanes. Slots 61 are provided on both sides of each guide vane group 6. The steps of inserting the sealing piece 7 into the slots 61 of the guide vane group 6 include: inserting the sealing piece 7 into the slot 61 on one side of each guide vane group 6, and the slot 61 on the other side of each guide vane group 6 is empty, so as to accommodate the sealing piece 7 inserted into the slot 61 on one side of the adjacent guide vane group 6 after forming a ring.

[0064] The first grooves 61a of two adjacent guide vane groups 6 correspond to each other to form a first installation groove, and a sealing piece 7 is installed in the first installation groove. The second grooves 61b of two adjacent guide vane groups 6 correspond to each other to form a second installation groove, and a sealing piece 7 is installed in the second installation groove; the third grooves 61c of two adjacent guide vane groups 6 correspond to each other to form a third installation groove, and a sealing piece 7 is installed in the third installation groove.

[0065] In Figure 3As shown, two guide vane groups 6 are schematically shown. Each guide vane group 6 includes five guide vanes. First grooves 61a, second grooves 61b, and third grooves 61c are provided on the flange plates of the two outermost guide vanes. The two opposite first grooves 61a of the two guide vane groups 6 together form a first installation groove, and a sealing piece 7 is installed in the first installation groove. The sealing piece 7 is generally a rectangular thin sheet. The two opposite second grooves 61b of the two guide vane groups 6 together form a second installation groove, and a sealing piece 7 is also installed in the second installation groove. The two opposite third grooves 61c of the two guide vane groups 6 together form a third installation groove, and a sealing piece 7 is also installed in the third installation groove. The structures and dimensions of the three sealing pieces 7 match the installation grooves where they are located respectively.

[0066] Step S300: Change the axial relative position between the turbine casing 10 and the previous-stage rotor assembly 2 so that the previous-stage rotor assembly corresponds to the first position of the turbine casing 10, and enclose all the guide vane groups 6 in a ring. Among them, after the turbine is installed in place, the previous-stage rotor assembly corresponds to the second position of the turbine casing 10. The inner diameter of the turbine casing 10 at the first position is larger than the inner diameter of the turbine casing 10 at the second position.

[0067] The previous-stage rotor assembly 2 refers to the rotor assembly 2 of the previous stage of these guide vane groups 6 to be installed. Before installing the stator assembly 1, the rotor assemblies 2 of each stage have been installed to form an integral body. Since there is a definite mating relationship between the guide vane group 6 and the previous-stage rotor assembly 2. Changing the axial relative position between the turbine casing 10 and the previous-stage rotor assembly 2 actually changes the axial position of the guide vane group 6 in the turbine casing 10 when the guide vane group 6 is pre-installed. The turbine is divergent, and the inner diameter of the turbine is larger in the direction closer to the outlet. The guide vane group 6 originally corresponds to the second position with a small inner diameter of the turbine casing 10. After adopting the above step S300, when the guide vane group 6 is pre-installed, the guide vane group 6 corresponds to the second position with a large inner diameter of the turbine casing 10. Then, in the circumferential direction of the ring formed by the guide vane group 6, the guide vane group 6 has a larger installation space, which is convenient for operating and inserting the sealing piece 7, and making the sealing piece 7 overlap in the corresponding half grooves. The guide vane group 6 enclosed in a ring is supported by the previous-stage rotor assembly to provide positioning.

[0068] As introduced above, the stator assembly 1 includes a plurality of guide vane groups 6. For the installation of the stator assembly 1, it mainly includes two steps: The first step is achieved by step S300, pre-installing to form a rough annular structure of the stator assembly 1. The second step is achieved by step S400, shrinking the annulus of the stator assembly 1 formed in step S300 to meet the dimensions of the stator assembly 1 required by the installation standard. In the first step, pre-installing the stator assembly 1 means placing each guide vane group 6 on the previous-stage rotor assembly. In this state, each guide vane group 6 is also placed in the annular groove of the turbine casing 10, but not at the final installation position in the annular groove, but slightly away from the final installation position in the annular groove. The final installation position refers to the position of the guide vane group 6 in the annular groove of the turbine casing 10 required by the turbine installation specification. Therefore, after pre-installation, the circumferential gap between each guide vane group 6 is relatively large, that is to say, the gap between each guide vane group 6 is greater than the gap between adjacent two guide vane groups 6 after the stator assembly 1 is installed. Since the gap between adjacent guide vane groups 6 is large, the sealing piece 7 only needs to slightly overlap with the respective other half of the groove body 61, and there is a large operating space when overlapping the sealing piece 7, which is convenient for operation. After each guide vane group 6 is placed in place, the second step is step S400.

[0069] There are the following three ways to change the axial relative position between the turbine casing 10 and the previous-stage rotor assembly: First, keep the turbine casing 10 stationary and move the entire rotor assembly where the previous-stage rotor assembly is located. Second, keep the entire rotor assembly where the previous-stage rotor assembly is located stationary and move the turbine casing 10. Third, make the turbine casing 10 and the entire rotor assembly where the previous-stage rotor assembly is located move towards each other. During the assembly process of the turbine, an assembly table will be used. Refer to Figure 6 , the assembly table has a first adjustment mechanism 8 for adjusting the axial position of the rotor assembly and a second adjustment mechanism 9 for adjusting the axial position of the stator assembly. With the help of the first adjustment mechanism 8 and the second adjustment mechanism 9, the respective axial relative positions of the turbine casing 10 and the previous-stage rotor assembly can be adjusted.

[0070] The fixed direction introduced above refers to the direction in which the guide vane group 6 is inserted into the installation groove of the turbine casing 10. Therefore, uniformly moving each guide vane group 6 in the circumferential direction along the fixed direction is to insert the guide vane group 6 into the final installation position of the installation groove of the turbine casing 10, which causes the guide vane group 6 to slowly contract to form the stator assembly.

[0071] In step S400, move the turbine casing 10 backward in multiple times, and at the same time uniformly move each guide vane group in the circumferential direction along the fixed direction, so that the guide vane group slowly contracts to form the stator assembly. The number of times for multiple times is greater than 2 times.

[0072] The stator assembly 1 and the rotor assembly 2 have a clear relative position relationship. The stator assembly 1 is installed one by one along the circumference of the stator assembly 1. This installation method can prevent the sealing sheet 7 from falling off in step S400, and there is no need to hoist the entire stator assembly 1, which is more efficient, convenient and efficient.

[0073] In the above technical solution, the guide vane group 6 is first assembled into a complete ring at the downstream (also called the high position), and then slowly returns to the position required for installation at the upstream (also called the low position), folds into a compact body, and finally presses into the slot of the turbine casing 10. Specifically, after the guide vane group 6 is installed in place, it should be installed at the b position of the slot of the turbine casing 10. However, when the guide vane group 6 is pre-installed, the guide vane group 6 is not directly stuck in the b position of the slot of the turbine casing 10, but by raising the rotor assembly a little distance or lowering the stator assembly a little distance, the guide vane group 6 is placed at the b1 position about 3mm to 5mm downstream of the slot b position of the turbine casing 10, which provides more space for the installation of the sealing piece 7 matched with the guide vane group 6. Then, the guide vane group 6 that is surrounded in a circle is folded again, so that the guide vane group 6 and the turbine casing 10 and the rotor assembly that match it are returned to the position required by the installation standard.

[0074] See also Figure 4 and Figure 5 An embodiment of the present invention further provides an injection tool used in a turbine assembly method, which is used to fill a volatile adhesive into the groove body 61 of the guide vane group 6 in the turbine assembly method provided by the above technical solution.

[0075] The injection tool includes a syringe and a heater. The heater is connected to the syringe or arranged adjacent to the syringe to heat the volatile binder in the syringe to prevent the liquid volatile binder in the syringe from decreasing in temperature and becoming solid or paste-like. The heater is, for example, an electric heater or hot water as a heat exchange medium.

[0076] The injection tool improved by the above technical solution is used to fill the groove body 61 of the guide vane group 6 with liquid vaseline, and the sealing piece 7 is adhered to the installation groove through the vaseline, which effectively prevents the sealing piece 7 from falling off and entering the flow channel during the installation process, causing assembly rework. Because the groove body 61 of the sealing piece 7 is small in size, it is difficult to manually pour vaseline into the groove body 61. The vaseline is squeezed into the installation groove by injection with a syringe, which improves the uniformity of vaseline filling and reduces pollution. In order to facilitate the filling of vaseline into the accommodating chamber 41, the vaseline ointment is pre-heated to 80-90 degrees Celsius. The vaseline ointment is liquid at this temperature. The piston 5 can directly draw the liquid vaseline into the accommodating chamber 41, and the vaseline is filled into the accommodating chamber 41 with relatively high efficiency.

[0077] See also Figure 4 and Figure 5, in some embodiments, the syringe includes a syringe barrel 4 and a piston 5. The syringe barrel 4 has a receiving cavity 41 and an injection port 42 communicating with the receiving cavity 41. The piston 5 is slidably mounted in the receiving cavity 41. Among them, the heater wraps around the receiving cavity 41 or fits against the outer wall of the receiving cavity 41. The opening size of the injection port 42 is smaller than the opening size of the receiving cavity 41. By arranging the heater in this way, the form of the volatile binder in the receiving cavity 41 can be well maintained and kept in a liquid state.

[0078] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation on the protected content of the present invention.

[0079] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some of the technical features, but these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A turbine assembly method, characterized in that, Including the following steps: Filling a volatile binder into the slots of the guide vane group; Inserting a sealing piece into the slots of the guide vane group; Changing the axial relative position between the turbine casing and the previous-stage rotor assembly so that the previous-stage rotor assembly corresponds to a first position of the turbine casing, and surrounding all the guide vane groups in a ring shape; wherein, after the turbine is installed in place, the previous-stage rotor assembly corresponds to a second position of the turbine casing; the inner diameter of the turbine casing at the first position is greater than the inner diameter of the turbine casing at the second position; Moving the turbine casing backward in multiple times, and simultaneously moving each guide vane group uniformly in a fixed direction in the circumferential direction so that the guide vane groups slowly contract to form a stator assembly; the number of times of the multiple times is greater than 2 times.

2. The turbine assembly method according to claim 1, characterized in that, Changing the axial relative position between the turbine casing and the previous-stage rotor assembly by using the following steps: Keeping the turbine casing stationary and moving the entire rotor assembly where the previous-stage rotor assembly is located; or, keeping the entire rotor assembly where the previous-stage rotor assembly is located stationary and moving the turbine casing; or, moving the turbine casing and the entire rotor assembly where the previous-stage rotor assembly is located toward each other.

3. The turbine assembly method according to claim 1, characterized in that, Each guide vane group includes at least two fixedly connected guide vanes; slots are arranged on both sides of each guide vane group, and the step of inserting a sealing piece into the slots of the guide vane group includes: Inserting the sealing piece into the slot on one side of each guide vane group, and the slot on the other side of each guide vane group is empty to accommodate the sealing piece inserted into the slot on the one side of the adjacent guide vane group.

4. The turbine assembly method according to claim 1, characterized in that, The step of filling a volatile binder into the slots of the guide vane group includes: Injecting a liquid volatile binder into the slots of each guide vane group; Waiting for the liquid volatile binder injected into the slots of each guide vane group to cool and solidify into a solid state or a paste state; Inserting the sealing piece into the slots of each guide vane group, and the volatile binder adheres to the sealing piece.

5. The turbine assembly method according to claim 4, wherein The step of injecting a liquid volatile binder into the slots of each guide vane group includes: Using vaseline as the volatile binder, heating the vaseline to 80°C - 90°C; Injecting the liquid vaseline into the slots of each guide vane group by using an injection tool.

6. The turbine assembly method according to claim 5, characterized in that, The injection tool includes: A syringe; and A heater, connected to or arranged adjacent to the syringe to heat the volatile binder in the syringe.

7. The turbine assembly method according to claim 6, wherein The syringe includes: An injection barrel having a receiving cavity and an injection port communicating with the receiving cavity; and A piston slidably mounted in the receiving cavity; Wherein, the heater wraps the receiving cavity or fits against the outer wall of the receiving cavity.

8. The turbine assembly method according to claim 1, characterized in that, The volatile binder uses one or more of the following substances: vaseline, paraffin wax, beeswax.

9. The turbine assembly method according to claim 1, characterized in that, The slots on each side of the guide vane group each include: A first groove located at the outer edge of the guide vane group; A second groove located at the inner edge of the guide vane group; and A third groove located at the inner edge of the guide vane group and on the side of the second groove away from the first groove, and the second groove and the third groove communicate; Among them, the first grooves of two adjacent guide vane groups correspond to each other to form a first installation groove, and one sealing piece is installed in the first installation groove; the second grooves of two adjacent guide vane groups correspond to each other to form a second installation groove, and one sealing piece is installed in the second installation groove; the third grooves of two adjacent guide vane groups correspond to each other to form a third installation groove, and one sealing piece is installed in the third installation groove.

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