A connecting positioning structure of a turbine disk and a disk front seal plate

Abstract

The application provides a connecting and positioning structure of a turbine disc and a front seal disc, which comprises a turbine disc, a drum shaft extending axially and integrated with the turbine disc, a radial protrusion and an axial protrusion provided on the drum shaft and the turbine disc respectively, and an installation groove formed between the radial protrusion and the axial protrusion; and a front seal disc, a seal disc air channel provided at a corresponding position of the front seal disc, a seal disc protrusion formed between two adjacent seal disc air channels, a step structure provided on a disc core part of the front seal disc corresponding to the installation groove, and a stop structure formed between the step structure and the axial protrusion and / or the radial protrusion to stop and limit the front seal disc; and an elastic ring installed in the installation groove.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a connection and positioning structure for a turbine disk front sealing disk. Background Technology

[0002] The front end of an aero-engine turbine disk is usually designed with a front sealing disk (also called a guide disk). Its main function is to axially fix the turbine blades. The front sealing disk is equipped with grates, which form a sealing structure with the honeycomb at the lower end of the guide blades. The front sealing disk and the turbine disk work together to form a flow path for providing cooling air to the turbine blades.

[0003] like Figure 1 The diagram shows a common front sealing disc connection and positioning structure 10. The front sealing disc 12 and the high-pressure turbine disc 11 are centered by a stop, and the turbine disc 11, the front sealing disc 12 and the drum shaft 13 are axially connected by long bolts 14 and locked by self-locking bracket nuts 15.

[0004] like Figure 2 As shown, the bottom of each tenon of the turbine disk 11 corresponds to a turbine disk air intake groove 111, and a turbine disk protrusion 112 is formed between two turbine disk air intake grooves 111. Figure 3 As shown, the sealing disk 12 and the turbine disk air duct 111 are respectively opened at the corresponding positions of the sealing disk air duct 12 and the sealing disk air duct 111, and a sealing disk protrusion 122 is formed between the two sealing disk air ducts 121.

[0005] The circumferential width of the protrusions on the turbine disk 11 and the front sealing disk 12 is smaller than the width of the air intake groove of the other. During assembly, the protrusions of the two are first made to pass through the air intake groove of the other, and then rotated by an angle to align the air intake grooves of the two, so as to realize the air intake function through the air intake groove.

[0006] To ensure centering, the stop between the front sealing disc 12 and the turbine disc 11 is an interference fit. To ensure blade fixation, the outer edge of the front sealing disc 12 and the front end face of the turbine disc 11 have a certain axial tightness. When these two tightnesses exist, the front sealing disc 12 and the turbine disc 11 cannot rotate relative to each other. To ensure that they can rotate relative to each other, during assembly, a tooling is used to apply an axial external force F to the front sealing disc 12 at three radial heights, causing the front sealing disc to deform and the tight parts to disengage. Figure 4 As shown. After rotating to the correct position, remove the external force, tighten the bolts, and the assembly is complete.

[0007] However, in the existing technology, the long bolts 14 pass through the bolt holes on the three parts, namely the drum shaft 13, the front sealing disc 12, and the turbine disc 11, at the same time. Therefore, the bolt holes on these three parts need to have a high degree of coaxiality to ensure that the multiple long bolts 14 distributed in the circumference can pass through the three parts. This places high demands on the machining accuracy.

[0008] Furthermore, during the dynamic balancing of the turbine rotor as a whole, the front sealing plate 12 and the turbine disk 11 need to rotate relative to each other by a certain angle. The rotation angle must ensure that the air bleed grooves of the front sealing plate 12 and the turbine disk 11 are aligned. However, the air bleed grooves are not visible during the rotation process. Therefore, it is stipulated that the number of long bolts must be rotated in an integer multiple of 14 during the dynamic balancing process. If the rotation is incorrect, it will cause the air bleed grooves to become blocked, which will lead to insufficient cooling air supply to the turbine blades and cause turbine blade ablation. It is difficult to detect the blockage of the air bleed grooves before the failure occurs.

[0009] Finally, in order to withstand centrifugal loads, the front sealing disc 12 needs to be made relatively thick, resulting in a large weight and increasing the overall weight of the aero engine. Summary of the Invention

[0010] The purpose of this application is to provide a connection and positioning structure between a turbine disk and a front sealing disk to solve or alleviate at least one of the problems in the prior art.

[0011] The technical solution of this application is: a connection and positioning structure between a turbine disk and a front sealing disk, the connection and positioning structure comprising:

[0012] The turbine disk has several turbine disk air intake grooves formed at the bottom of the tenon groove, and a turbine disk protrusion is formed between two adjacent turbine disk air intake grooves. The turbine disk is provided with an axially extending drum shaft integrally formed with the turbine disk. Radial protrusions and axial protrusions are provided from the drum shaft and the turbine disk on the upper side of the drum shaft toward the front sealing side of the disk, and an installation groove is formed between the radial protrusions and the axial protrusions.

[0013] The front sealing disc has an air duct groove at the corresponding position of the front sealing disc and the turbine disc. A sealing disc protrusion is formed between two adjacent air duct grooves. The front sealing disc has a stepped structure on the side facing the radial protrusion and the axial protrusion respectively on the disc center part corresponding to the mounting groove. The stepped structure and the axial protrusion and / or radial protrusion form a stop structure to stop and limit the front sealing disc.

[0014] An elastic ring is installed in the mounting groove to axially position the center of the front sealing disc within the mounting groove.

[0015] In a preferred embodiment of this application, the center of the front sealing disc is a rectangular rounded corner structure.

[0016] In a preferred embodiment of this application, the elastic ring has an open structure, and the elastic ring is elastic through the opening.

[0017] In a preferred embodiment of this application, the cross-section of the elastic ring is L-shaped, the right angle of the L-shaped structure matches the corner of the front sealing disc, and the back of the L-shaped structure contacts the radial protrusion to form a limiting structure.

[0018] In a preferred embodiment of this application, the end face of the front sealing disc facing the turbine disc is provided with several circumferentially distributed positioning grooves, and the turbine disc is provided with positioning bosses that match the position and number of the positioning grooves. The circumferential positioning of the front sealing disc and the turbine disc is achieved through the cooperation of the positioning grooves and the positioning bosses.

[0019] In a preferred embodiment of this application, the number of positioning slots is an approximation of the number of air ducts in the sealing disc.

[0020] The connection and positioning structure between the turbine disk and the front sealing disk provided in this application can make the disk core size of the front sealing disk smaller and lighter. Moreover, the connection and positioning structure does not require the use of long bolts to pass through three parts, and does not require the machining of bolt holes with high positional accuracy, thereby reducing the machining difficulty. Attached Figure Description

[0021] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0022] Figure 1 This is a schematic diagram of a typical pre-panel sealing and positioning structure in existing technology.

[0023] Figure 2 for Figure 1 A schematic diagram of the turbine disk air intake groove and boss structure in the enlarged area I.

[0024] Figure 3 for Figure 1 A schematic diagram of the pre-sealing air duct and boss structure in the enlarged area I.

[0025] Figure 4 This diagram illustrates the force application during the pre-sealing assembly process in existing technologies.

[0026] Figure 5 This is a schematic diagram of the connection and positioning structure between the turbine disk and the front sealing disk of this application.

[0027] Figure 6 This is a schematic diagram of the elastic ring in this application.

[0028] Figure 7 This is a schematic diagram of the pre-market sealing board in this application.

[0029] Figure 8 This is a schematic diagram of the turbine disk in this application.

[0030] Figure 9 This is a schematic diagram of the force application for the pre-sealing disc assembly in this application. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0032] like Figure 5 As shown, this application provides a novel connection and positioning structure for a front sealing disc and a turbine disc. The connection and positioning structure 20 includes a front sealing disc 22, a turbine disc 21, and an elastic ring 23.

[0033] Among them, the air duct structure near the tenon of the turbine disk 21 and the front sealing disk 22 is no different from the traditional scheme. That is, several turbine disk air ducts are formed at the bottom of the tenon of the turbine disk 21, and a turbine disk protrusion is formed between two adjacent turbine disk air ducts. The front sealing disk 22 and the turbine disk 21 are provided with sealing disk air ducts at the corresponding positions, and a sealing disk protrusion is formed between two adjacent sealing disk air ducts.

[0034] A drum shaft 211, extending axially and integrally formed with the turbine disk 21, is provided near the center of the turbine disk 21. Radial protrusions 215 and axial protrusions 214 are provided from the drum shaft 211 and the turbine disk 21 above the drum shaft 211 toward the front sealing disk 22, respectively. A mounting groove 213 is formed between the radial protrusions 215 and the axial protrusions 214. The portion of the center of the front sealing disk 22 corresponding to the mounting groove 213 is configured as a rectangular rounded corner structure. The side of this rectangular rounded corner structure facing the radial protrusions 215 and the axial protrusions 214 is set as a stepped structure. The stepped structure, together with the axial protrusions 214 and the radial protrusions 215, forms a stop structure for stopping and limiting the front sealing disk 22.

[0035] like Figure 6 As shown, the elastic ring 23 has an open structure with an approximately L-shaped cross section. The right angle of the L-shaped structure matches the corner of the front sealing disc 22. The elastic ring 23 is set in the mounting groove 213, and its L-shaped structure is limited at the radial protrusion 215 on the back. The center of the front sealing disc 22 in the mounting groove 213 is axially positioned by the elastic ring 23.

[0036] In the scheme of this application, the direction of the stop near the center of the front sealing disc 22 is opposite to that of the conventional scheme. The front sealing disc 22 is pressed by the axial protrusion 214 of the turbine disc 21, so that the stop structure not only plays a centering role, but also transfers the centrifugal force borne by the front sealing disc 22 to the turbine disc 21. Therefore, it is not necessary to make the center of the front sealing disc 22 very thick, thereby reducing the overall weight of the rotor.

[0037] like Figure 7 and Figure 8 As shown, several circumferentially distributed positioning grooves 221 are provided on the right end face of the stop of the front sealing plate 22, and the turbine plate 21 is provided with the same number of positioning bosses 212 at the corresponding positions. The circumferential positioning of the front sealing plate 22 and the turbine plate 21 is achieved by the cooperation of the positioning grooves 221 and the positioning bosses 212.

[0038] In a preferred embodiment of this application, the number of positioning grooves 221 is an approximation of the number of air ducts, thereby ensuring that when the front sealing plate 22 and the turbine plate 21 rotate relative to each other by an angle of one positioning groove 221, the air ducts also rotate through an integer number of positions. This ensures that regardless of the rotation, as long as the positioning grooves 221 engage with the positioning boss 212, the air ducts on the front sealing plate 22 and the turbine plate 21 always remain aligned. For example, in this application example, the number of air ducts near the tenon grooves of the turbine plate 21 and the front sealing plate 22 is 70, and the number of positioning grooves 221 can be set to 7.

[0039] During assembly, first, the elastic ring 23 is pressed into the mounting groove 213 of the turbine disk 21 so that the front sealing disk 22 can pass radially. Then, pressure is applied to the three different radial heights of the front sealing disk 22 as follows: Figure 9 The force shown causes deformation. The deformation is similar to that of a conventional solution, but this deformation not only separates the tight stop and end face of the front sealing disc 22 from the turbine disc 21, but also axially separates the positioning groove 221 on the front sealing disc 22 from the positioning boss 212 on the turbine disc 21, allowing the two discs to rotate relative to each other. When the positioning groove 221 and the positioning boss 212 are circumferentially aligned, the external force F on the front sealing disc 22 is removed. The center of the front sealing disc 22 is moved to the right, and the external force on the elastic ring 23 is removed, allowing the elastic ring 23 to return to its original shape. This limits the front sealing disc 22 within the mounting groove 213 of the turbine disc 21. The external force on the center of the front sealing disc is then removed, completing the assembly. The elasticity of the front sealing disc 22 itself causes the center to tend to move to the left, but due to the presence of the elastic ring 23, it cannot move to the left, thus achieving axial positioning and ensuring a certain axial tightness at the fit between the outer edge and the tenon end face.

[0040] In a preferred embodiment of this application, the principle of the front sealing disc 22 is that a flange structure 222 is provided on one side of the turbine disc 21 near the center of the disc. The flange structure 22 serves as the point of force to apply the deformation force to the front sealing disc 22 during the assembly process, and can also serve as the material removal part when balancing a single piece.

[0041] The connection and positioning structure between the turbine disk and the front sealing disk provided in this application can make the disk core size of the front sealing disk smaller and lighter. Moreover, the connection and positioning structure does not require the use of long bolts to pass through three parts, and does not require the machining of bolt holes with high positional accuracy, thereby reducing the machining difficulty.

[0042] This invention enables the turbine disk and the front sealing disk to be connected and positioned using a positioning boss on the turbine disk and a positioning groove on the front sealing disk for circumferential positioning. By controlling the relationship between the number of positioning grooves and air ducts, it ensures that when the rotor is balanced, the turbine disk and the front sealing disk rotate relative to each other. As long as they are assembled in place, the air ducts on the turbine disk and the front sealing disk will be aligned, thus avoiding the possibility of incorrect angular positioning from the root.

[0043] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A connection and positioning structure, characterized in that, The connection positioning structure includes: The turbine disk has several turbine disk air intake grooves formed at the bottom of the tenon groove, and a turbine disk protrusion is formed between two adjacent turbine disk air intake grooves. The turbine disk is provided with an axially extending drum shaft integrally formed with the turbine disk. Radial protrusions and axial protrusions are provided from the drum shaft and the turbine disk on the upper side of the drum shaft toward the front sealing side of the disk, and an installation groove is formed between the radial protrusions and the axial protrusions. A sealing disc is provided in front of the turbine disk. Air venting grooves are provided at corresponding positions on the sealing disc and the turbine disk. A sealing disc protrusion is formed between two adjacent air venting grooves. Stepped structures are provided on the sides of the disc core portion corresponding to the mounting groove, facing both radial and axial protrusions. These stepped structures, together with the axial and / or radial protrusions, form a stop structure to stop and limit the movement of the sealing disc. Several circumferentially distributed positioning grooves are provided on the end face of the sealing disc facing the turbine disk. Positioning bosses, matching the positions and numbers of the positioning grooves, are provided on the turbine disk. Circumferential positioning of the sealing disc and the turbine disk is achieved through the cooperation of the positioning grooves and positioning bosses. The number of positioning grooves is an approximation of the number of air venting grooves on the sealing disc. An elastic ring is installed in the mounting groove to axially position the center of the front sealing disc within the mounting groove.

2. The connection and positioning structure as described in claim 1, characterized in that, The center of the front-sealing plate is a rectangular structure with rounded corners.

3. The connection and positioning structure as described in claim 1, characterized in that, The elastic ring has an open structure, and the opening allows the elastic ring to generate elasticity.

4. The connection and positioning structure as described in claim 3, characterized in that, The cross-section of the elastic ring is L-shaped. The right angle of the L-shaped structure matches the corner of the front sealing disc. The back of the L-shaped structure contacts the radial protrusion to form a limiting structure.

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