Three-pin two-wire turbine guide vane positioning structure

Abstract

This invention provides a three-pin, two-line turbine guide vane positioning structure, comprising: a guide vane, the guide vane including a blade body, a lug on the upper connecting portion of the blade body, a first pin hole and a second pin hole respectively formed on the lug, a first protruding ridge on the outer side of the lug, a U-shaped pin groove on the inner side of the lower connecting portion, and a second protruding ridge on the outer side of the lower connecting portion; a support ring, the outer ring of the inner sidewall of the support ring having external bolt holes, and multiple third pin holes at corresponding positions on the inner and outer sides of the inner sidewall of the support ring; and an inner casing, the inner side of the inner casing having a first mounting groove adapted to the U-shaped pin groove, and the outer side having a retaining groove corresponding to the position of the second protruding ridge, for the second protruding ridge to engage in the retaining groove when the U-shaped pin groove is assembled with the first mounting groove by a lower positioning pin. This invention structure has good sealing performance and positioning stability, reduces undesigned leakage, increases the service life of the guide vane-related connecting parts, and reduces engine maintenance costs.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a three-pin, two-line turbine guide vane positioning structure. Background Technology

[0002] In modern aero gas turbine engines, turbine guide vanes rectify, guide, and accelerate high-temperature, high-pressure gas, causing it to impact the downstream turbine blades and perform work. Turbine guide vane positioning technology is crucial, directly affecting engine vibration levels, force transmission, and compressor operating conditions, ultimately impacting aircraft flight safety. There are various positioning methods for turbine guide vanes; a good positioning structure design is a prerequisite for achieving optimal engine performance and flight safety, and also ensures good casting and machining capabilities.

[0003] Currently, many turbine guide vanes use bolt connections, ball joints, hooks, etc. for positioning, which has problems such as unintended air leakage during operation, excessive constraint on blade force transmission, and complex casting and machining processes, leading to increased processing and maintenance costs. Furthermore, during assembly, there is a partial blind assembly process when assembling the guide vanes with internal and external fixed structures, making it impossible to control the installation status of parts and resulting in poor assembly operability. Summary of the Invention

[0004] In view of this, the present application provides a three-pin two-line turbine guide vane positioning structure, which has good sealing performance and positioning stability, reduces undesigned leakage, increases the service life of guide vane-related connecting parts, reduces engine maintenance costs, and has good casting, machining and assembly processability.

[0005] This application provides the following technical solution: a three-pin, two-line turbine guide vane positioning structure, comprising:

[0006] The guide blade includes a blade body, an upper connecting part of the blade body is provided with a lug, a first pin hole and a second pin hole are respectively opened on the lug, a first protruding ridge is provided on the outer side of the lug, a U-shaped pin groove is provided on the inner side of the lower connecting part of the blade body, and a second protruding ridge is provided on the outer side of the lower connecting part.

[0007] The support ring is an annular groove structure. The outer ring of the inner sidewall of the support ring has external bolt holes. The inner ring of the inner sidewall and the outer sidewall of the support ring each have a plurality of third pin holes at corresponding positions. The plurality of third pin holes are respectively adapted to the first pin hole and the second pin hole, and are used to assemble the lug between the inner sidewall and the outer sidewall of the support ring through the upper positioning pin, so as to connect the guide blade to the support ring.

[0008] Wherein, when the lug is assembled between the inner and outer sidewalls of the support ring, the contact position between the first protruding ridge and the outer sidewall of the support ring forms a first line sealing structure.

[0009] It also includes an inner casing, the inner side of which has a first mounting groove adapted to the U-shaped pin groove, and the outer side of which has a slot corresponding to the position of the second protruding ridge. When the U-shaped pin groove is assembled with the first mounting groove by the lower positioning pin, the second protruding ridge is engaged in the slot to connect the guide vane to the inner casing, and the contact position between the second protruding ridge and the inner wall of the slot forms a second line sealing structure.

[0010] According to one embodiment of this application, the external bolt holes on the outer ring of the inner sidewall of the support ring correspond to the mounting holes on the outer casing, and are used to fix the support ring to the outer casing by screws.

[0011] According to one embodiment of this application, the first pin hole is a circular hole.

[0012] According to one embodiment of this application, the second pin hole is a waist-shaped hole.

[0013] According to one embodiment of this application, a second mounting groove is further formed on the inner wall of the card slot, and a sealing ring is provided in the second mounting groove.

[0014] According to one embodiment of this application, both the upper positioning pin and the lower positioning pin have axial clearance at their mounting locations.

[0015] According to one embodiment of this application, the upper positioning pin is a center pin with different head diameters at both ends, and the lower positioning pin is a cylindrical, side-shaped, or waist-shaped limiting pin.

[0016] According to one embodiment of this application, the sealing line of the first line sealing structure is parallel to the sealing line of the second line sealing structure.

[0017] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0018] (1) In the embodiments of the present invention, the radial, axial and circumferential forces and thermal deformation of the guide vane during operation can be well released through the circular pin hole, "waist" pin hole and "U" pin groove structure, without stress concentration and additional stress caused by thermal deformation coordination problem, which can improve the strength and life of the guide vane and corresponding contact parts.

[0019] (2) The upper and lower mounting points of the guide vane adopt a raised ridge structure design to achieve linear contact sealing, and the lower end adopts a lower sealing ring for pre-limiting and sealing, which improves the sealing effectiveness of cooling gas and gas in the flow channel, and will not cause gas or cold air leakage, resulting in problems such as sintering and decomposition of the fixing parts. This increases the working life of the guide vane-related connecting parts and reduces the engine maintenance cost.

[0020] (3) The positioning structure of the guide vane and its related connecting parts are made explicit during the installation and disassembly process, which has good assemblability and processability, and also improves the state control of component installation. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the positioning structure according to an embodiment of the present invention;

[0023] Figure 2 yes Figure 1 Enlarged view of a portion of point A in the middle;

[0024] Figure 3 yes Figure 1 Enlarged view of a portion of point B in the middle;

[0025] Figure 4 This is a schematic diagram of the support ring structure in an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the guide vane structure in an embodiment of the present invention;

[0027] Figure 6 This is a schematic diagram of the inner casing structure in an embodiment of the present invention;

[0028] Figure 7 This is a first schematic diagram of the upper positioning pin structure in an embodiment of the present invention;

[0029] Figure 8 This is a second schematic diagram of the upper positioning pin structure in an embodiment of the present invention;

[0030] Figure 9 This is a schematic diagram of the cylindrical lower positioning pin structure in an embodiment of the present invention;

[0031] Figure 10 This is a schematic diagram of the side-type lower positioning pin structure in an embodiment of the present invention;

[0032] Figure 11This is a schematic diagram of the waist-shaped lower positioning pin structure in an embodiment of the present invention;

[0033] Figure 12 This is a schematic diagram of the counterweight assembly process in an embodiment of the present invention;

[0034] Among them, 1-outer casing, 2-support ring, 3-guide blade, 4-inner casing, 5-upper positioning pin, 6-lower positioning pin, 7-sealing ring, 8-screw, 9-first pin hole, 10-second pin hole, 11-U-shaped pin groove, 12-external bolt hole, 13-third pin hole, 14-first mounting groove, 15-second mounting groove. Detailed Implementation

[0035] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0036] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0037] like Figures 1-12 As shown, this embodiment of the invention provides a three-pin, two-line turbine guide vane positioning structure, comprising:

[0038] Guide blade 3, the guide blade 3 includes a blade body, the upper end connecting part of the blade body is provided with a lug, the lug is respectively provided with a first pin hole 9 and a second pin hole 10, the outer side of the lug is provided with a first protruding ridge, the inner side of the lower end connecting part of the blade body is provided with a U-shaped pin groove 11, and the outer side of the lower end connecting part is provided with a second protruding ridge.

[0039] The support ring 2 is an annular groove structure. External bolt holes 12 are formed on the outer ring of the inner sidewall of the support ring 2. Multiple third pin holes 13 are formed at corresponding positions on the inner and outer rings of the inner sidewall of the support ring 2. These third pin holes 13 are respectively adapted to the first pin hole 9 and the second pin hole 10, and are used to assemble the lug between the inner and outer sidewalls of the support ring 2 via the upper positioning pin 5, thereby connecting the guide vane 3 to the support ring 2. When the lug is assembled between the inner and outer sidewalls of the support ring 2, the contact position between the first protruding ridge and the outer sidewall of the support ring 2 forms a first-line sealing structure (e.g., ...). Figure 2 Line contact a) in the middle;

[0040] It also includes an inner casing 4, the inner side of which has a first mounting groove 14 adapted to the U-shaped pin groove 11, and the outer side of which has a retaining groove corresponding to the position of the second protruding ridge. When the U-shaped pin groove 11 and the first mounting groove 14 are assembled by the lower positioning pin 6, the second protruding ridge engages in the retaining groove to connect the guide vane 3 to the inner casing 4. The contact position between the second protruding ridge and the inner wall of the retaining groove forms a second line sealing structure (e.g., ...). Figure 3 In this embodiment, a second mounting groove 15 is also provided on the inner wall of the slot, and a sealing ring 7 is provided in the second mounting groove 15. The external bolt holes 12 on the outer ring of the inner side wall of the support ring 2 correspond to the assembly holes on the outer casing 1, and are used to fix the support ring 2 to the outer casing 1 by screws 8.

[0041] The turbine guide vane in this embodiment of the invention adopts a "three-pin, two-line" positioning structure, which fully considers the coordination of stress and heat deformation of the guide vane, inner and outer casings, and other parts. The positioning area of ​​the guide vane is an open area with no abrupt changes, making it easy to cast and machine.

[0042] The "three-pin" structure consists of an upper positioning pin 5 at the upper end of the guide vane 3 and a lower positioning pin 6 at the lower end. The upper positioning pin 5 is installed corresponding to the circular pin hole (first pin hole 9) and the waist-shaped pin hole (second pin hole 10) of the guide vane 3, respectively. The lower positioning pin 6 is installed corresponding to the U-shaped pin groove 11 of the guide vane. This allows for quick and accurate positioning of the guide vane during installation. During engine operation, the "waist-shaped" hole allows the guide vane to undergo circumferential sliding deformation due to heat, releasing the circumferential deformation caused by heat. The "U-shaped" pin groove allows the guide vane to slide radially in the corresponding mounting groove of the inner casing by relying on the lower positioning pin, releasing the radial deformation caused by heat. There is an axial clearance at the installation points of the upper and lower positioning pins of the guide vane. When the outer casing 1 and the inner casing 4 undergo different axial elongations due to heat deformation during engine operation, the axial clearance at the upper and lower positioning pins of the guide vane can release the axial displacement caused by heat deformation. This "three-pin" structure ensures the positioning stability of the guide vane during installation and also guarantees the release of radial, circumferential, and axial heat deformation during operation.

[0043] The "two-line" sealing structure is located at the guide vane mounting edge ( Figure 5 In areas a and b shown, raised ridge structures are designed to contact the support ring surface a and the inner casing surface b, respectively, forming two parallel line-contact seals. During operation, factors such as differences in axial elongation due to thermal deformation of the inner and outer casings cause different axial displacements at the upper and lower ends of the guide vanes. The surfaces formed by these two parallel lines can rotate angularly around either parallel line, allowing for a small angular displacement of the guide vanes while maintaining a good line-contact seal. This reduces undesigned leakage of fuel and cooling gas during operation, preventing problems such as sintering and decomposition difficulties of the fasteners.

[0044] The functions and structures of the various parts involved in the embodiments of the present invention will be described in detail below.

[0045] Figures 1-3 This is a schematic diagram of the guide vane positioning structure. The assembly relationship of each part is as follows: the sealing ring 7 is assembled into the slot of the inner casing 4; the U-shaped pin groove 11 of the single guide vane 3 is correspondingly assembled into the first mounting slot 14 of the inner casing 4; the lower positioning pin 6 provides circumferential limiting for the guide vane 3; the sealing ring 7 provides axial pre-tightening and sealing for the guide vane 3; the upper positioning pin 5 provides radial limiting for the guide vane 3; and finally, screws 8 are used to fix it to the mounting edge of the outer casing 1. The degrees of freedom of each part are mutually constrained, ultimately forming a guide vane assembly system with no redundant degrees of freedom.

[0046] Figure 4To support the ring structure, the external bolt holes 12 are used to fix it to the outer casing 1, and the circumferentially lace-shaped third pin hole 13 is used to assemble and fix the upper positioning pin 5. The surface a of the internal groove provides axial limiting and line contact sealing to the first protruding ridge at the upper end of the guide blade 3. The external bolt holes 12 correspond one-to-one with the mounting side holes of the outer casing 1, and the number of third pin holes 13 corresponds one-to-one with the external circular and oblong pin holes of the guide blade 3.

[0047] Figure 5 The guide vane structure has two lugs at the upper end, each with a circular pin hole (first pin hole 9) and an oblong pin hole (second pin hole 10). The first pin hole 9 is circular and used for radial fixing of the guide vane; the second pin hole 10 is oblong and used to coordinate and release circumferential thermal deformation and thermal stress during operation. A U-shaped pin groove 11 is designed at the lower end of the guide vane for circumferential positioning, and during operation, the guide vane can slide radially within the U-shaped pin groove 11 to release radial thermal deformation and thermal stress. The guide vane mounting edge (… Figure 5 In the areas shown (a and b), raised ridge structures are designed to contact the support ring surface a and the inner casing surface b respectively, forming parallel line contacts for sealing. This ensures that the line contacts are maintained throughout the operation as the upper and lower ends of the guide vanes deform axially, thus guaranteeing the sealing effectiveness of the cooling gas and the combustion gas in the flow channel.

[0048] Figure 6 The internal casing structure includes a first mounting groove 14 for mounting the U-shaped pin groove 11 of the guide vane 3, restricting the circumferential movement of the guide vane 3, and a second mounting groove 15 for assembling the sealing ring 7. Figure 5 The surface b shown in the diagram forms a line contact b with the second convex ridge at the lower end of the guide vane 3. During operation, the inner casing remains in contact with the guide vane even when it deforms.

[0049] Figures 7-11 The upper and lower positioning pins are respectively structured as upper and lower positioning pins. The upper positioning pin 5 adopts a center pin with different diameters at both ends, which is used for radial limiting and force transmission support of the guide blade. The lower positioning pin 6 can adopt "cylindrical", "side" or "waist" type positioning pins for circumferential limiting of the guide blade and to cooperate with the U-shaped pin groove 11 of the guide blade to guide the radial thermal deformation direction.

[0050] When assembling turbine guide vanes and related components, the number and arrangement of the guide vanes should be considered according to... Figure 12 The process shown will install the guide vanes into place to form a stator assembly with easily controllable status. The specific steps are as follows:

[0051] 1. First, insert the sealing ring 7 into the second mounting slot 15 of the inner casing part;

[0052] 2. According to the arrangement of the guide vanes, the U-shaped pin groove 11 is assembled into the first mounting groove 14 of the inner casing and the lower positioning pin 6 is installed for circumferential limiting and axial pre-tightening to achieve contact of the lower end area b of the guide vanes;

[0053] 3. Install support ring 2 to ensure that the third pin hole 13 corresponds one-to-one with the outer round and waist-shaped pin holes of the guide vane 3, and install positioning pin 5 in a uniform manner for radial limiting;

[0054] 4. The support ring 2 is fixed to the mounting edge of the outer casing 1 using screws 8, forming a guide vane assembly system with no extra degrees of freedom and a stator assembly whose state is easy to control.

[0055] This invention discloses a three-pin, two-line turbine guide vane positioning structure, which features excellent sealing and positioning stability, reduces undesigned leakage, increases the service life of guide vane-related connecting components, and lowers engine maintenance costs. Furthermore, this positioning structure does not impose excessive constraints on the vane during operation, and provides excellent deformation release for the axial thermal shock force, radial thermal stress, and torque transmitted by the guide vane, meeting the requirements of various operating conditions. Moreover, this positioning structure has no abrupt structural changes (such as hooks or ball joints), possessing excellent casting, machining, and assembly processability.

[0056] 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 three-pin, two-line turbine guide vane positioning structure, characterized in that, include: The guide blade includes a blade body, an upper connecting part of the blade body is provided with a lug, a first pin hole and a second pin hole are respectively opened on the lug, a first protruding ridge is provided on the outer side of the lug, a U-shaped pin groove is provided on the inner side of the lower connecting part of the blade body, and a second protruding ridge is provided on the outer side of the lower connecting part. The support ring is an annular groove structure. The outer ring of the inner sidewall of the support ring has external bolt holes. The inner ring of the inner sidewall and the outer sidewall of the support ring each have a plurality of third pin holes at corresponding positions. The plurality of third pin holes are respectively adapted to the first pin hole and the second pin hole, and are used to assemble the lug between the inner sidewall and the outer sidewall of the support ring through the upper positioning pin, so as to connect the guide blade to the support ring. Wherein, when the lug is assembled between the inner and outer sidewalls of the support ring, the contact position between the first protruding ridge and the outer sidewall of the support ring forms a first line sealing structure. It also includes an inner casing, the inner side of which has a first mounting groove adapted to the U-shaped pin groove, and the outer side of which has a slot corresponding to the position of the second protruding ridge. When the U-shaped pin groove is assembled with the first mounting groove by the lower positioning pin, the second protruding ridge is engaged in the slot to connect the guide vane to the inner casing, and the contact position between the second protruding ridge and the inner wall of the slot forms a second line sealing structure.

2. The three-pin, two-line turbine guide vane positioning structure according to claim 1, characterized in that, The outer bolt holes on the inner sidewall of the support ring correspond to the mounting holes on the outer casing, and are used to fix the support ring to the outer casing with screws.

3. The three-pin, two-line turbine guide vane positioning structure according to claim 1, characterized in that, The first pin hole is a circular hole.

4. The three-pin, two-line turbine guide vane positioning structure according to claim 1, characterized in that, The second pin hole is a slotted hole.

5. The three-pin, two-line turbine guide vane positioning structure according to claim 1, characterized in that, A second mounting groove is also provided on the inner wall of the card slot, and a sealing ring is provided in the second mounting groove.

6. The three-pin, two-line turbine guide vane positioning structure according to claim 1, characterized in that, Both the upper and lower positioning pins have axial clearance at their mounting points.

7. The three-pin, two-line turbine guide vane positioning structure according to claim 6, characterized in that, The upper positioning pin is a center pin with different diameters at both ends, and the lower positioning pin is a cylindrical, side-shaped, or waist-shaped limiting pin.

8. The three-pin, two-line turbine guide vane positioning structure according to claim 1, characterized in that, The sealing lines of the first line sealing structure and the sealing lines of the second line sealing structure are parallel to each other.

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