Positioning mechanism for a gas turbine and gas turbine

Abstract

This disclosure provides a positioning mechanism for a gas turbine and a gas turbine, relating to the field of aero-engine technology. The rotor disk has an annular disk groove arranged circumferentially; the blade roots of a plurality of turbine blades are coupled to the rotor disk and each has a skirt that forms a gap with the blade root, with a notch formed between adjacent skirts. The positioning mechanism includes: a plate-shaped main body having a first end and a second end facing each other along the radial direction of the rotor disk, the first end extending into the disk groove; and a connecting portion extending from the second end away from the first end into the notch, so that by pushing the positioning mechanism along the disk groove in the circumferential direction of the rotor disk under the action of an external force, the connecting portion is driven to at least partially move from the notch to the gap, such that the main body covers the gap between the rotor disk and the turbine blades and retains the blade roots of the turbine blades in the rotor disk.

Description

Technical Field

[0001] At least one embodiment of this disclosure relates to the field of aero-engine technology, and more particularly to a positioning mechanism for a gas turbine and a gas turbine. Background Technology

[0002] Gas turbines, as high-efficiency, high-power power plants, play a core role in energy, aviation, and shipbuilding. Turbine blades, also known as turbine blades, operate alongside the rotor in extreme high-temperature, high-pressure, and high-speed environments. The moving blades on the rotor must be reliably fixed to the rotor disk via blade roots to withstand enormous centrifugal forces, aerodynamic loads, and alternating thermal stresses. In this connection system, effectively locking the blades while simultaneously achieving effective interstage gas isolation is a key technical challenge in rotor design. Summary of the Invention

[0003] In view of this, the present disclosure provides a positioning mechanism for a gas turbine and a gas turbine, which can effectively cover and seal the gap between the turbine disk and the turbine blades while enabling convenient disassembly and maintenance of the turbine blades.

[0004] As a first aspect of the present disclosure, a positioning mechanism for a gas turbine is provided, wherein the rotor disk of the gas turbine has an annular disk groove arranged circumferentially; the blade roots of a plurality of turbine blades are coupled to the rotor disk and each has a skirt that forms a gap with the blade root, and a notch is formed between two adjacent skirts; the positioning mechanism includes: a plate-shaped main body having a first end and a second end facing each other in the radial direction of the rotor disk, the first end extending into the disk groove; and a plug-in portion extending from the second end away from the first end into the notch, such that by pushing the positioning mechanism along the disk groove in the circumferential direction of the rotor disk under the action of an external force, the plug-in portion is driven to move at least partially from the notch to the gap, such that the main body covers the gap between the rotor disk and the turbine blades and retains the blade roots of the turbine blades in the rotor disk.

[0005] According to an embodiment of this disclosure, the positioning mechanism further includes: a pair of locking portions extending from the main body portion on both sides of the insertion portion and spaced close to the first end of the insertion portion, configured to respectively engage with both sides of the skirt portion after the insertion portion extends into the gap, preventing the insertion portion from moving out of the gap.

[0006] According to an embodiment of the present disclosure, the locking portion extends obliquely from the main body portion, such that when the insertion portion extends into the gap, the locking portion is elastically deformed by the skirt portion and recovers after passing the skirt portion, so that the free end of the locking portion is held on the side of the skirt portion.

[0007] According to an embodiment of the present disclosure, the aforementioned plug portion is configured to extend obliquely from the aforementioned main body portion toward the direction away from the aforementioned blade root portion; the aforementioned main body portion includes: a body; and a bending member extending obliquely from the aforementioned body portion toward the aforementioned wheel disk groove to cooperate with the aforementioned plug portion, so that the aforementioned body portion elastically abuts against the aforementioned blade root portion and the aforementioned rotor disk.

[0008] According to an embodiment of this disclosure, the first included angle between the plug portion and the main body portion is configured to be greater than or equal to 10° and less than or equal to 30°.

[0009] According to an embodiment of this disclosure, the second included angle between the bent member and the body is configured to be greater than or equal to 10° and less than or equal to 30°.

[0010] As a second aspect of the present disclosure, a gas turbine is provided, comprising: a rotor having a rotor disk having an annular disk groove arranged circumferentially; a plurality of turbine blades having a blade root portion engaging with the rotor disk and a skirt portion forming a gap with the blade root portion, wherein a notch is formed between two adjacent skirt portions; and a plurality of positioning mechanisms disposed between the gap and the disk groove, such that by pushing the positioning mechanism along the disk groove in the circumferential direction of the rotor disk under the action of an external force, the positioning mechanism is driven to move at least partially from the notch to the gap, such that the positioning mechanism covers the gap between the rotor disk and the turbine blade and retains the blade root portion in the rotor disk.

[0011] According to an embodiment of this disclosure, the distance between the skirt and the leaf root gradually increases from the middle of the skirt along the direction close to the notch, so as to guide the positioning mechanism to be inserted.

[0012] According to embodiments of this disclosure, a plurality of the above-mentioned positioning mechanisms are arranged sequentially along the groove of the wheel disc to form a positioning ring surrounding the rotor wheel disc.

[0013] According to an embodiment of this disclosure, the positioning mechanism is disposed on the exhaust side of the rotor disc.

[0014] According to the positioning mechanism of this disclosure, the plate-shaped main body and the insertion part allow the insertion part to slide into the blade gap simply by circumferential pushing without disassembling the rotor. Simultaneously, the main body covers the gap between the turbine disk and the blade, thus enabling convenient disassembly and locking of individual blades, greatly facilitating maintenance and dynamic balancing. Furthermore, the main body forms a continuous sealing barrier against the high-temperature combustion gas, reducing interstage gas leakage and facilitating the organization and maintenance of directional gas supply to the turbine blades. While providing reliable mechanical constraint on the blade root and preventing turbine blade loosening, the positioning mechanism simultaneously improves the rotor's aerodynamic integrity, operational stability, and maintenance economy. Attached Figure Description

[0015] The above and other objects, features and advantages of this disclosure will become clearer from the following description of embodiments with reference to the accompanying drawings, in which:

[0016] Figure 1 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown from a first perspective.

[0017] Figure 2 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown from a second perspective.

[0018] Figure 3 A perspective view of a positioning mechanism according to an embodiment of the present disclosure is shown schematically;

[0019] Figure 4 A cross-sectional view of a positioning mechanism according to an embodiment of the present disclosure is shown schematically;

[0020] Figure 5 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within a notch;

[0021] Figure 6 A partial side view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within a notch;

[0022] Figure 7 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within the gap;

[0023] Figure 8 A partial side view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is within the gap;

[0024] Figure 9 Schematic illustration Figure 8 A magnified view of part A shown.

[0025] The annotations in the attached figures are explained as follows:

[0026] 1. Positioning mechanism; 11. Main body; 111. Body; 112. Bending component; 12. Insertion part; 13. Locking part;

[0027] 2. Rotor disc; 21. Disc groove;

[0028] 3. Turbine blade; 31. Blade root; 311. Gap; 312. Notch; 313. Skirt; 32. Blade body; 33. Blade tip; 34. Blade crown. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this disclosure clearer, the following detailed description is provided in conjunction with specific embodiments and the accompanying drawings.

[0030] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. The terms “comprising,” “including,” etc., as used herein indicate the presence of the stated features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0031] All terms used herein, including technical and scientific terms, have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein are to be interpreted in a manner consistent with the context of this specification, and not in an idealized or overly rigid way.

[0032] When using expressions such as "at least one of A, B, and C," the meaning should generally be interpreted according to the understanding of someone skilled in the art. For example, "a system having at least one of A, B, and C" should include, but is not limited to, systems having A alone, having B alone, having C alone, having A and B, having A and C, having B and C, and / or having A, B, and C. Similarly, when using expressions such as "at least one of A, B, or C," the meaning should generally be interpreted according to the understanding of someone skilled in the art. For example, "a system having at least one of A, B, or C" should include, but is not limited to, systems having A alone, having B alone, having C alone, having A and B, having A and C, having B and C, and / or having A, B, and C.

[0033] It should also be noted that the directional terms mentioned in the embodiments, such as "up," "down," "front," "back," "left," and "right," are only for reference to the directions in the accompanying drawings and are not intended to limit the scope of protection of this disclosure. Throughout the drawings, the same elements are represented by the same or similar reference numerals. Conventional structures or constructions will be omitted where they may cause confusion in understanding this disclosure.

[0034] In the process of developing this disclosure, it was discovered that turbine blades (also known as turbine blades) are typically assembled and connected to the rotor disk via a tenon-mortise structure. Due to machining accuracy errors of the tenons and mortises, the allowance for assembly gaps, and the thermal expansion and contraction effect during the operation of the gas turbine, small gaps inevitably exist between the tenon-mortise mating surfaces. These gaps form leakage channels between the rotor's intake and exhaust sides, leading to leakage of high-temperature combustion gas, i.e., the tenon-mortise gap leakage phenomenon.

[0035] In related technologies, to reduce gap leakage, independent locking plates or integral cover plate structures are typically used to lock the turbine blades to the rotor disk. Independent locking plate structures allow for the disassembly and assembly of individual blades without complete rotor disassembly, facilitating maintenance and counterweight adjustments during dynamic balancing. However, due to their small structural size, these independent locking plates primarily cover a localized point or area at the blade tenon end, failing to continuously and completely cover the circumferentially extending annular gap between the entire rotor disk and the roots of all blades. This results in limited sealing effectiveness, making it difficult to completely prevent the leakage of high-temperature combustion gases into the rotor, and also hindering the directional air supply to the cooling blades. While integral cover plate structures achieve good airtightness and overall rigidity, replacing or adjusting blade positions often requires the partial or complete disassembly of the rotor, a complex, time-consuming, and labor-intensive process, hindering rapid maintenance and balancing adjustments.

[0036] In view of this, the present disclosure provides a positioning mechanism 1 for a gas turbine in order to solve at least one of the above-mentioned technical problems.

[0037] Figure 1 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown. Figure 2 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown from a second perspective. Figure 3 A perspective view of a positioning mechanism according to an embodiment of the present disclosure is shown schematically.

[0038] As a first aspect of this disclosure, a positioning mechanism 1 for a gas turbine is provided. For example... Figures 1 to 3As shown, the rotor disk 2 of the gas turbine has an annular disk groove 21 arranged circumferentially; the blade roots 31 of a plurality of turbine blades 3 are coupled to the rotor disk 2 and each has a skirt 313 forming a gap 311 with the blade root 31, and a notch 312 is formed between two adjacent skirts 313. The positioning mechanism 1 includes a plate-shaped main body 11 and a plug-in part 12. The main body 11 has a first end and a second end facing each other in the radial direction of the rotor disk 2, and the first end extends into the disk groove 21. The plug-in part 12 extends from the second end away from the first end into the notch 312, so that by pushing the positioning mechanism 1 along the disk groove 21 in the circumferential direction of the rotor disk 2 under the action of an external force, the plug-in part 12 is driven to move at least partially from the notch 312 to the gap 311, so that the main body 11 covers the gap between the rotor disk 2 and the turbine blades 3 and holds the blade roots 31 of the turbine blades 3 in the rotor disk 2.

[0039] According to embodiments of this disclosure, such as Figure 1 and Figure 2 As shown, the turbine blade 3 includes a root portion 31, a blade body portion 32, and a tip portion 33. The transition area between the root portion 31 and the blade body portion 32 is a plateau portion. A skirt portion 313 extends radially inward from the edge of the plateau portion. The root portion 31 forms a tenon, which is mortised and tenoned with the mortise and tenon joint formed by the rotor disk 2, arranging the turbine blade 3 on the outer periphery of the rotor disk 2. Figure 1 (The circle indicated by the dashed line).

[0040] The turbine blade 3 may also include a blade crown 34. The blade crowns 34 of adjacent blades abut against each other after assembly, forming a continuous annular band to reduce tip leakage, provide vibration damping, and enhance blade rigidity.

[0041] The rotor disk 2 has an annular disk groove 21 arranged circumferentially. The disk groove 21 can be opened on the outer edge side of the rotor disk 2, with the groove opening facing the tip of the turbine blade 3. The width and depth of the groove are adapted to the size of the main body 11 of the positioning mechanism 1, ensuring that the first end of the main body 11 can be stably inserted and can move smoothly circumferentially.

[0042] The blade roots 31 of multiple turbine blades 3 are respectively connected to the rotor disk 2. The blade roots 31 can be connected to the rotor disk 2 by means of tenon joint or other means. Each turbine blade 3 has a skirt 313 that forms a gap 311 with the blade root 31. The skirt 313 is located on the side of the blade root 31 near the outer edge of the rotor disk 2 and extends along the edge of the blade root 31. A notch 312 is formed between two adjacent skirts 313 to provide space for the insertion part 12 to extend and move.

[0043] As an example, at least one notch 312 can be formed between the skirts 313 of multiple turbine blades 3.

[0044] Alternatively, the number of notches 312 can be the same as the number of turbine blades 3.

[0045] Alternatively, the number of notches 312 can be half the number of turbine blades 3. It should be understood that the embodiments of this disclosure are not limited thereto; for example, the number of notches 312 can also be one-third the number of turbine blades 3.

[0046] The main body 11 and the plug-in part 12 can adopt an integral molding structure. The material is selected to be a high-temperature resistant and high-strength alloy material that is compatible with the rotor disk 2 and turbine blades 3, so as to avoid deformation or damage to the gas turbine due to the high temperature and high pressure environment during operation.

[0047] Reference Figure 3 As shown, the positioning mechanism can be approximately arc-shaped, and can extend outward along the radial direction of the rotor disc.

[0048] Multiple positioning mechanisms 1 are arranged sequentially along the groove 21 of the rotor disk 2, forming a continuous circumferential sealing and restraining ring between the groove 21 and the skirt 313. After installation, the main body 11 of each positioning mechanism 1 is adjacent to each other, forming an uninterrupted or only minimally spaced annular physical covering layer between the surface of the rotor disk 2 and the blade root 31. This effectively blocks the leakage path of high-temperature combustion gas along the entire circumference through the gap between the disk and the blade root, solving the problem of limited sealing effect caused by the discrete distribution and discontinuous coverage of independent locking plates.

[0049] Furthermore, the continuous covering layer, together with the disk surface and the blade root 31, defines a relatively closed annular area. This provides a structural basis for organizing and controlling the flow of cooling air, which is beneficial for constraining and guiding the cooling air to the predetermined cooling air inlet at the blade root, thereby achieving efficient and directional air supply to the cooling blades.

[0050] In addition, the ring structure formed by multiple positioning mechanisms 1 can not only limit the movement of individual blades, but also form a unified and coordinated constraint system in the entire circumferential direction, which enhances the overall rigidity and stability of the rotor components under high-speed rotation.

[0051] The main body 11 has a first end and a second end facing each other along the radial direction of the rotor disk 2. The first end extends into the disk groove 21, and the thickness of the first end is slightly less than the width of the disk groove 21. The length of the first end is adapted to the depth of the disk groove 21 to ensure a sliding fit between the main body 11 and the disk groove 21, while also having sufficient contact area to achieve stable positioning. The insertion part 12 extends from the second end away from the first end into the notch 312. The thickness of the insertion part 12 is adapted to the width of the notch 312, and the extension length ensures that it can move from the notch 312 to the gap 311 between the blade root 31 and the skirt 313. The overall structural design is adapted to the assembly layout of the rotor disk 2 and the turbine blade 3, meeting the installation and working requirements of the positioning mechanism 1.

[0052] In some illustrative embodiments, the main body 11 can be configured as an arc-shaped plate with an arc that matches the circumferential arc of the rotor disk 2. This allows the first end of the main body 11 to better fit the inner wall of the disk groove 21 after it extends into the disk groove 21, reducing resistance during circumferential movement. At the same time, it increases the contact area between the main body 11 and the rotor disk 2, improving the sealing performance and positioning reliability of the covering gap.

[0053] In this embodiment, the first end of the main body 11 extends into the annular groove 21 of the rotor disk 2, which provides a stable mounting base for the positioning mechanism 1 and also serves as a guide for movement. The structural characteristics of the annular groove 21 allow the positioning mechanism 1 to move smoothly along the circumference of the rotor disk 2, while effectively limiting the radial offset of the positioning mechanism 1.

[0054] The insertion part 12 extends from the second end of the main body 11 into the notch 312 formed by two adjacent skirts 313, providing an initial positioning reference for the positioning mechanism 1 and ensuring that the insertion part 12 can move toward the gap 311 between the blade root 31 and the skirt 313 when an external force is applied. Under the drive of the external force, the positioning mechanism 1 moves circumferentially along the wheel groove 21, and the insertion part 12 moves synchronously with the main body 11, extending at least partially into the gap 311 between the blade root 31 and the skirt 313 from the notch 312. With the cooperation of the insertion part 12 with the gap 311 and the notch 312, the radial and circumferential displacement of the blade root 31 of the turbine blade 3 is restricted, and the blade root 31 is reliably positioned.

[0055] The positioning mechanism 1 provided in this disclosure has convenient maintenance characteristics. Operators do not need to disassemble the rotor. They can simply move the positioning mechanism 1 (locking block) in the circumferential direction to make the insertion part 12 exit or enter the gap 311 of the turbine blade 3, and complete the independent disassembly and repositioning of part or all of the turbine blades 3. This simplifies the on-site maintenance, repair and dynamic balance adjustment procedures of the rotor.

[0056] Furthermore, after positioning, the plate-shaped main body 11 of the positioning mechanism 1 can completely cover the gap between the rotor disk 2 and the turbine blade 3, effectively preventing the high-temperature gas from eroding the joint between the rotor disk 2 and the blade root 31 during the operation of the gas turbine. It also further assists in fixing the blade root 31, preventing it from loosening or shifting under high-speed rotation, high temperature, and high pressure operating conditions. Through the structural design and coordinated operation of the components of the positioning mechanism 1, the blade root 31 of the turbine blade 3 can be stably held in the rotor disk 2, ensuring the long-term stable and safe operation of the gas turbine.

[0057] Figure 4 A cross-sectional view of a positioning mechanism according to an embodiment of the present disclosure is shown schematically.

[0058] According to embodiments of this disclosure, such as Figure 4 As shown, the insertion portion 12 is configured to extend obliquely from the main body portion 11 in a direction away from the blade root portion 31. The main body portion 11 includes a body 111 and a bending member 112. The bending member 112 extends obliquely from the body 111 away from the blade root portion 31 to the disc groove 21 to cooperate with the insertion portion 12, so that the body 111 elastically abuts against the blade root portion 31 and the rotor disc 2.

[0059] According to an embodiment of the present disclosure, the insertion portion 12 is configured to extend obliquely from the main body portion 11 toward the direction away from the blade root portion 31 (i.e., generally outward along the rotor radial direction). This oblique angle facilitates the insertion portion 12 to be more smoothly inserted into the gap 311 formed by the blade root portion 31 and the skirt portion 313 during circumferential movement, and may lead to the insertion portion 12 forming a line or surface contact with the wall surface of the gap 311.

[0060] The body 111 and the bent part 112 can be integrally formed.

[0061] The bent member 112 starts from the inner side of the body 111 (near the rotor axis) and extends obliquely away from the blade root 31, extending into the annular groove of the rotor disk 2. The obliquely extending bent member 112 and the obliquely extending insertion part 12 form a spatial mating relationship. When the positioning mechanism 1 is pushed to the working position, and the insertion part 12 is fully inserted into the blade gap 311, the bent member 112, due to its specific inclination angle and length, will undergo elastic deformation under the constraint of the disk groove 21, continuously applying an elastic restoring force to the body 111 pointing towards the blade root 31 and the surface of the rotor disk 2, so that the body 111 can elastically and tightly abut against the end face of the blade root 31 and the corresponding surface of the rotor disk 2.

[0062] By bending the insertion part 12 and the bending part 112, the positioning mechanism 1 is elastically pressed in the working position, which can compensate for the machining tolerance of the parts and the difference in thermal expansion, ensuring that the main body 11 covers the gap between the wheel and the blade more tightly and enhances the sealing effect; at the same time, the continuous elastic pressing force can also suppress the micro-movement of the positioning mechanism 1 in the vibration environment, and improve the stability and reliability of the blade root 31.

[0063] According to an embodiment of this disclosure, the first included angle α between the plug portion 12 and the main body portion 11 is configured to be greater than or equal to 10° and less than or equal to 30°. That is, 10°≤α≤30°.

[0064] As an example, the first included angle α can be configured to any value among 10°, 12°, 14°, 16°, 18°, 20°, 22°, 24°, 26°, 28° and 30°.

[0065] In this embodiment, when 10°≤α≤30°, the insertion portion 12, extending obliquely from the main body 11, has a suitable guide slope. Thus, when the positioning mechanism 1 is pushed circumferentially, the insertion portion 12 can smoothly slide into the gap 311 formed by the blade root 31 and the skirt 313, reducing movement resistance and preventing jamming. Furthermore, this angle range also provides the necessary structural rigidity for the insertion portion 12, enabling it and the main body 11 to maintain shape stability when subjected to the load transmitted by the blade during operation, avoiding bending deformation or strength weakening due to excessive tilting. In addition, this angle range also helps to form an optimized contact state between the insertion portion 12 and the wall of the gap 311, more effectively constraining the circumferential and radial displacement of the blade root 31.

[0066] According to embodiments of this disclosure, the second included angle β between the bent member 112 and the body 111 is configured to be greater than or equal to 10° and less than or equal to 30°. That is, 10°≤β≤30°.

[0067] As an example, the second included angle β can be configured to any value among 10°, 12°, 14°, 16°, 18°, 20°, 22°, 24°, 26°, 28° and 30°.

[0068] In this embodiment, when the second included angle is 10°≤β≤30°, the bending member 112 extending obliquely from the body 111 possesses suitable pre-deformation space and elastic stiffness. During the installation of the positioning mechanism 1 into the working position, the bending member 112 at this angle can undergo controllable, primarily elastic deformation bending under the constraint of the wheel groove 21, thereby effectively storing deformation energy as elastic potential energy. This design allows the bending member 112 to act as a highly efficient elastic element, continuously applying a moderately sized and directionally stable radial elastic restoring force to the body 111, ensuring that the body 111 tightly and elastically abuts against the blade root 31 and the side surface of the wheel groove 21.

[0069] Specifically, the lower limit of the second included angle (≥10°) ensures that the bent component 112 has a sufficient initial tilt angle to generate the necessary elastic deformation stroke and restoring force during assembly, avoiding insufficient elastic clamping effect due to an excessively small angle. Its upper limit (≤30°) limits the tilt degree of the bent component 112 to prevent excessive weakening of its structural stiffness, excessive stress in the elastic deformation area, or motion interference within the wheel groove 21 due to an excessively large angle.

[0070] As an example, the positioning mechanism 1 can be integrally formed. The thickness of the positioning mechanism 1 can be about 1mm.

[0071] Figure 5 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within a notch. Figure 6 A partial side view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within a notch. Figure 7 A partial perspective view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within the gap. Figure 8 A partial side view of a gas turbine according to an embodiment of the present disclosure is schematically shown, wherein the insertion portion is located within the gap. Figure 9 Schematic illustration Figure 8 A magnified view of part A shown.

[0072] According to embodiments of this disclosure, see Figures 1 to 9 As shown, the positioning mechanism 1 also includes a pair of locking parts 13. The two locking parts 13 extend from the main body 11 on both sides of the insertion part 12 and are spaced apart from the first end of the insertion part 12. They are configured to lock the insertion part 12 on both sides of the skirt 313 after the insertion part 12 is inserted into the gap 311, preventing the insertion part 12 from moving out of the gap 311.

[0073] During installation, see Figure 6 and Figure 7As shown, when the insertion part 12 is within the notch, the bent member 112 is inserted into the rotor groove, and the insertion part 12 is located within the notch 312. When the insertion part 12 is within the gap, the bent member 112 is inserted into the rotor groove, and the insertion part 12 is located within the gap 311.

[0074] Under the action of external force, the positioning mechanism 1 is pushed to move along the groove 21 of the wheel disk in the circumferential direction of the rotor wheel disk 2, so that the insertion part 12 can switch between the notch and the gap.

[0075] By providing a pair of locking parts 13, the insertion part 12 can be kept within the gap, and the wall positioning mechanism 1 can be disengaged from the gap 311.

[0076] In this embodiment, two locking parts 13 extend from the main body 11 at intervals from both sides of the insertion part 12 and close to the first end of the insertion part 12. They are configured to abut or hold against both sides of the skirt part 313 after the insertion part 12 extends into the gap 311. Through the geometric interference and cooperation between the locking parts 13 and the sides of the skirt part 313, a mechanical constraint is formed in the circumferential direction to prevent the positioning mechanism 1 from moving in the opposite direction. This prevents the insertion part 12 from accidentally moving out of the working gap 311, ensuring the long-term stability of the positioning state and the reliability of the locking function. It also prevents the insertion part 12 from shifting due to factors such as vibration and airflow impact during the operation of the gas turbine, ensuring a stable positioning effect.

[0077] As an example, the locking part 13 can be warped by a tool. When the locking part 13 is in a warped state, it can lock the skirt 313, thereby achieving a circumferential stopping function.

[0078] Compared with traditional blade locking plates, the positioning mechanism 1 provided in this disclosure can achieve axial stop while also having the functions of blocking air and counterweight, enabling the turbine blades 3 to be disassembled and assembled without disassembling the rotor.

[0079] According to an embodiment of the present disclosure, the locking portion 13 extends obliquely from the main body portion 11 so that when the insertion portion 12 extends into the gap 311, the locking portion 13 is squeezed by the skirt portion 313 and undergoes elastic deformation, and returns to its original state after passing over the skirt portion 313, so that the free end of the locking portion 13 is held against the side of the skirt portion 313.

[0080] According to embodiments of this disclosure, the structural design of the locking portion 13 extending obliquely from the main body 11 achieves a reliable elastic locking function. When the positioning mechanism 1 is pushed by an external force to move circumferentially and the insertion portion 12 enters the gap 311 between the blade root portion 31 and the skirt portion 313, the obliquely extending locking portion 13 contacts the side edge of the skirt portion 313. During continued movement, the skirt portion 313 applies pressure to the locking portion 13, forcing the locking portion 13 to undergo elastic bending deformation toward the blade root portion 31. As the movement continues, the free end of the locking portion 13 gradually slides past the side edge of the skirt portion 313. Once the free end of the locking portion 13 has passed the edge of the skirt portion 313, the compressive force acting on it disappears, and the locking portion 13 rebounds in the initial oblique direction by the elastic restoring force of the material itself, so that its free end is finally positioned and locked in the side position of the skirt portion 313. This process allows the locking part 13 to automatically complete elastic deformation and reset without additional operation, thereby forming a mechanical block in the circumferential direction against the reverse movement of the positioning mechanism 1, effectively preventing the plug part 12 from accidentally coming out of the working gap 311, and improving the vibration resistance and loosening resistance of the positioning state.

[0081] As an example, the positioning mechanism 1 can be a shield-shaped integrated protection and fixing unit, which not only provides a large area of ​​effective coverage to seal critical gaps, but also achieves convenient and reliable installation and locking through a sophisticated connection mechanism, providing stable and durable protection for the joint between the rotor disk 2 and the blades in harsh turbine environments.

[0082] In some illustrative embodiments, the plate-shaped main body 11 of a positioning mechanism 1 can be designed in the circumferential direction to cover the area corresponding to a turbine blade 3.

[0083] In some other illustrative embodiments, the plate-shaped main body 11 of a positioning mechanism 1 can be designed to cover the area corresponding to multiple turbine blades 3 in the circumferential direction, and the insertion part 12 is also configured to be multiple, which can simultaneously enter the gap 311 between multiple adjacent blades to achieve common locking and sealing of a group of blades.

[0084] As a second aspect of this disclosure, a gas turbine is provided. For example... Figure 1As shown, the gas turbine includes a rotor, multiple turbine blades 3, and multiple positioning mechanisms 1 as described above. The rotor has a rotor disk 2 with an annular disk groove 21 arranged circumferentially. The turbine blades 3 have blade roots 31 that engage with the rotor disk 2, and skirts 313 that form gaps 311 with the blade roots 31, with a notch 312 formed between adjacent skirts 313. The multiple positioning mechanisms 1 are disposed between the gaps 311 and the disk grooves 21, so that by pushing the positioning mechanisms 1 along the disk grooves 21 in the circumferential direction of the rotor disk 2 under the action of an external force, the positioning mechanisms 1 are driven to at least partially move from the notch 312 to the gaps 311, such that the positioning mechanisms 1 cover the gap between the rotor disk 2 and the turbine blades 3 and retain the blade roots 31 in the rotor disk 2.

[0085] In this implementation, by correspondingly arranging multiple positioning mechanisms 1 on the rotor assembly, the systematic fixation and sealing of the turbine blade group 3 along the entire rotor circumference is achieved. During assembly or maintenance, by sequentially or selectively applying circumferential external force to each positioning mechanism 1, its insertion part 12 is driven to move from the notch 312 into the blade gap 311, and the main body 11 covers the gap between the rotor disk and the blade root. This process ensures that the blade root 31 of all turbine blades 3 is stably constrained in the rotor disk 2, effectively suppressing the circumferential and radial movement of the blades under working load. At the same time, the main body 11 of all positioning mechanisms 1 are connected on the rotor surface to form a continuous or segmented continuous covering layer. This covering layer can block the leakage channel between the surface of the rotor disk 2 and the blade root platform of the high-temperature gas over a large area, which not only protects the tenon-tooth connection structure, but also helps to maintain the pressure difference between the turbine stages and the aerodynamic integrity of the cooling air system, thereby ensuring the overall operating efficiency, reliability and safety of the gas turbine.

[0086] According to an embodiment of the present disclosure, the distance between the skirt portion 313 and the leaf root portion 31 gradually increases from the middle of the skirt portion 313 in the direction close to the notch 312, so as to guide the positioning mechanism 1 to be inserted.

[0087] According to embodiments of this disclosure, the gap 311 between the skirt 313 and the root 31 of the turbine blade 3 is configured with a specific geometry to optimize assembly guidance. The width of this gap 311 is not uniform, but gradually increases from the central region of the skirt 313 along the circumferential direction towards the notch 312 formed near the adjacent blade. This gradually widening geometric profile forms a guide ramp or flared structure between the notch 312 and the main body of the gap 311.

[0088] Thus, when the operator applies external force to push the positioning mechanism 1 circumferentially, attempting to move the insertion part 12 from the notch 312 into the gap 311, the gradually widening wall of the gap 311 can effectively guide the end or side of the insertion part 12 (and the locking part 13). The gradually widening profile allows the insertion part 12 to have greater tolerance in the initial stage, and during continuous movement, the inclined contact gradually corrects and guides the insertion part 12 to the correct final position inside the gap 311, reducing the stringent requirements for operational precision in the assembly process. This allows the insertion part 12 to slide into the predetermined gap 311 more smoothly and reliably, reducing the risk of possible jamming or misalignment, thereby improving the operability and efficiency of the entire positioning mechanism 1 assembly.

[0089] According to embodiments of this disclosure, a plurality of positioning mechanisms 1 are arranged sequentially along the wheel disc groove 21 to form a positioning ring surrounding the rotor wheel disc 2.

[0090] According to embodiments of this disclosure, after installation, multiple positioning mechanisms 1 are arranged adjacent to each other along the wheel disc groove 21 to form a continuous or quasi-continuous positioning ring around the rotor wheel disc 2.

[0091] In this embodiment, the positioning ring forms a complete mechanical constraint and sealing ring in the circumferential direction of the rotor. The positioning ring achieves uniform circumferential limiting of the root 31 of all turbine blades 3 on the rotor disk 2, ensuring a uniform distribution of constraint force. At the same time, the main body 11 of each positioning mechanism 1 is adjacent to or closely arranged with each other in this annular state, eliminating discontinuities between the covered areas and establishing a continuous physical barrier between the surface of the rotor disk 2 and the blade platform. This can prevent high-temperature combustion gas from leaking through the gap between the disk and the blade root at any position in the circumferential direction, thus improving the interstage gas sealing effect.

[0092] In addition, the positioning ring enhances the rigidity of the positioning system itself, which helps to maintain shape stability under high-speed rotation and may simplify the process of checking and confirming the locking status during maintenance.

[0093] According to an embodiment of this disclosure, the positioning mechanism 1 is disposed on the exhaust side of the rotor disk 2.

[0094] According to embodiments of this disclosure, in a turbine stage, the exhaust side is typically located in a relatively low pressure and temperature region (compared to the inlet side or blade leading edge region), but it is still a critical area through which high-temperature combustion gases flow. By centrally locating the positioning mechanism 1 on the exhaust side, the plate-like structure of the main body 11 can be used to form an effective sealing barrier on the exhaust side, directly blocking the leakage path of high-temperature combustion gases from the exhaust side to the inlet side.

[0095] It should be understood that the embodiments disclosed herein are not limited thereto, and the positioning mechanism 1 may also be disposed on the air intake side of the rotor disk 2. Alternatively, the positioning mechanism 1 may be disposed on both the air intake side and the air exhaust side of the rotor disk 2.

[0096] The embodiments of this disclosure have been described above. However, these embodiments are for illustrative purposes only and are not intended to limit the scope of this disclosure. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. The scope of this disclosure is defined by the appended claims and their equivalents. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of this disclosure, and all such substitutions and modifications should fall within the scope of this disclosure.

Claims

1. A positioning mechanism for a gas turbine, wherein the rotor disk of the gas turbine has an annular disk groove arranged circumferentially; the blade roots of a plurality of turbine blades are coupled to the rotor disk and each has a skirt that forms a gap with the blade root, and a notch is formed between two adjacent skirts, characterized in that, The positioning mechanism includes: The plate-shaped main body has a first end and a second end facing each other along the radial direction of the rotor disk, the first end extending into a groove in the disk; and The insertion portion extends from the second end away from the first end into the notch, so as to drive the positioning mechanism to move along the disk groove in the circumferential direction of the rotor disk under the action of an external force, thereby driving the insertion portion to move at least partially from the notch to the gap, such that the main body covers the gap between the rotor disk and the turbine blade and holds the root of the turbine blade in the rotor disk.

2. The positioning mechanism according to claim 1, characterized in that, Also includes: The locking portions, which are arranged in pairs, extend from the main body on both sides of the insertion portion and are spaced apart from the insertion portion near the first end. They are configured to respectively engage with both sides of the skirt portion after the insertion portion is inserted into the gap, preventing the insertion portion from moving out of the gap.

3. The positioning mechanism according to claim 2, characterized in that, The locking portion extends obliquely from the main body portion so that when the insertion portion extends into the gap, the locking portion is elastically deformed by the skirt portion and returns to its original position after passing the skirt portion, so that the free end of the locking portion is engaged with the side of the skirt portion.

4. The positioning mechanism according to any one of claims 1-3, characterized in that, The insertion portion is configured to extend obliquely from the main body portion in a direction away from the leaf root portion; The main body includes: The subject; and A curved member extends obliquely from the body away from the blade root to the disc groove to engage with the insertion portion, so that the body elastically abuts against the blade root and the rotor disc.

5. The positioning mechanism according to claim 4, characterized in that, The first included angle between the plug portion and the main body portion is configured to be greater than or equal to 10° and less than or equal to 30°.

6. The positioning mechanism according to claim 4, characterized in that, The second included angle between the bent element and the body is configured to be greater than or equal to 10° and less than or equal to 30°.

7. A gas turbine, characterized in that, include: A rotor having a rotor disk having annular disk grooves arranged circumferentially; Multiple turbine blades, each turbine blade having a blade root that engages with the rotor disk and a skirt that forms a gap with the blade root, with a notch formed between two adjacent skirts; as well as A plurality of positioning mechanisms as described in any one of claims 1-6 are disposed between the gap and the disc groove, such that by pushing the positioning mechanism along the disc groove in the circumferential direction of the rotor disc under the action of an external force, the positioning mechanism is driven to move at least partially from the notch to the gap, such that the positioning mechanism covers the gap between the rotor disc and the turbine blade and retains the blade root in the rotor disc.

8. The gas turbine according to claim 7, characterized in that, The distance between the skirt and the leaf root gradually increases from the middle of the skirt towards the notch to guide the positioning mechanism into place.

9. The gas turbine according to claim 7, characterized in that, Multiple positioning mechanisms are arranged sequentially along the groove of the rotor disc to form a positioning ring surrounding the rotor disc.

10. The gas turbine according to any one of claims 7-9, characterized in that, The positioning mechanism is located on the exhaust side of the rotor disc.

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