Mounting structure for adjustable stationary blade, gas compressor and gas turbine engine

Abstract

The invention relates to a mounting structure and a mounting method for an adjustable stationary blade, a gas compressor and a gas turbine engine. The mounting structure comprises an adjustable stationary blade, the adjustable stationary blade comprises a blade body, a first connecting part and a second connecting part, the first connecting part and the second connecting part are connected with the radial inner end and the radial outer end of the blade body respectively, and the first connecting part is provided with a first platform part connected with the blade body and a first rotating shaft part protruding out of the first platform part; the second connecting part is provided with a second platform part connected with the blade body and a second rotating shaft part protruding from the second platform part, the first platform part and the first rotating shaft part form a first shaft shoulder, and the second platform part and the second rotating shaft part form a second shaft shoulder; the intermediate case comprises an intermediate case outer ring and an intermediate case inner ring positioned on the radial inner side of the intermediate case outer ring; the first bushing is arranged on the first connecting part in a sleeving manner; and the second bushing is arranged on the second connecting part in a sleeving manner.

Description

Technical Field

[0001] This invention relates to the field of turbomachinery, and particularly to a mounting structure, mounting method, compressor, and gas turbine engine for adjustable stator vanes. Background Technology

[0002] Variable stator vanes (VSVs) are stator vanes whose installation angle can be changed according to engine operating conditions. The main purpose of using VSVs in engines is to improve engine stability and prevent surge. The VSV adjustment mechanism drives the rotation of the variable stator vanes, changing their installation angle and adjusting the flow rate through the cascade and the angle of attack of the airflow behind the cascade, thus ensuring the normal and stable operation of the compressor.

[0003] VSV (Variable Inlet Valve) adjustment mechanisms are widely used in high-pressure compressors of various gas turbine engines. Aero-engine compressors are equipped with inlet guide vanes to change the intake angle of attack during compressor operation, thereby altering the intake direction and flow rate to prevent compressor surge. The inlet guide vanes have a double-support structure; the upper end is mounted on the adjustable blade mounting seat in the intermediate inner casing, and the lower end is supported on the inner ring assembly. Both the inner and outer journals of the adjustable blades have bushings, ensuring flexible blade rotation while sealing the flow channel to prevent leakage. The IGV (Inner Gas Valve) inner ring adopts a split-half structure to provide support for the IGV blades. Figure 1 As shown.

[0004] like Figure 2A As shown, during the installation process of IGV assembly into the intermediate inner casing assembly, since the inlet guide vane is installed at an angle, in order to prevent interference in the assembly path, the radial clearance between the inlet guide vane inner bushing 32a and the IGV inner ring is designed to be about 0.8mm. However, the inventors found that such a clearance value is not conducive to airtightness and ease of assembly.

[0005] Therefore, there is a need in the art for an installation structure, installation method, compressor, and gas turbine engine for adjustable stator vanes to solve at least one of the above technical problems. Summary of the Invention

[0006] One object of the present invention is to provide an installation structure for an adjustable stator assembly.

[0007] One object of the present invention is to provide an air compressor.

[0008] One object of the present invention is to provide a gas turbine engine.

[0009] One object of the present invention is to provide a method for installing an adjustable stator assembly.

[0010] According to one aspect of the present invention, an mounting structure for an adjustable stator blade assembly includes: an adjustable stator blade, comprising a blade body and a first connecting portion and a second connecting portion respectively connected to a radially inner end and a radially outer end of the blade body; the first connecting portion having a first platform portion connected to the blade body and a first rotating shaft portion protruding from the first platform portion; the second connecting portion having a second platform portion connected to the blade body and a second rotating shaft portion protruding from the second platform portion; the first platform portion and the first rotating shaft portion forming a first shoulder, and the second platform portion and the second rotating shaft portion forming a second shoulder; an intermediate housing, comprising an intermediate housing outer ring and an intermediate housing inner ring located radially inner to the intermediate housing outer ring; and a first bushing fitted onto the first connecting portion. A second bushing is fitted onto the second connecting portion; wherein, the outer ring of the intermediate housing has a first connecting hole that mates with the shaft hole of the first bushing; the inner ring of the intermediate housing has a second connecting hole that accommodates an upstream mounting ring and a downstream mounting ring, and the channel formed by the axial space between the upstream mounting ring and the downstream mounting ring mates with the second bushing; the second bushing includes a bushing body and an extension that extends radially outward from one end of the bushing body, the bushing body and the extension mate with the second shoulder; the extension length of the extension corresponding to the upstream side of the second shoulder is a first length, and the extension length corresponding to the downstream side of the second shoulder is a second length, the second length being greater than the first length.

[0011] In one or more embodiments of the mounting structure, the first length ranges from 2 mm to 3 mm, the second length ranges from 4 mm to 5 mm, and the second length being greater than the first length ranges from 1 mm to 3 mm.

[0012] In one or more embodiments of the mounting structure, the extension is shaped as a chamfered annular shape, the chamfer is located on the upstream side of the extension, and the length removed is within the range where the second length is greater than the first length.

[0013] In one or more embodiments of the mounting structure, the chamfered surface is a planar structure.

[0014] In one or more embodiments of the mounting structure, the gap between the second bushing and the upstream mounting ring is less than 0.2 mm.

[0015] In one or more embodiments of the mounting structure, the second bushing is made of metal.

[0016] According to one aspect of the present invention, a compressor includes the mounting structure of the adjustable stator assembly described in any of the above-mentioned claims.

[0017] According to one aspect of the present invention, a gas turbine engine includes the mounting structure of the adjustable stator assembly described in any of the above-mentioned claims.

[0018] According to one aspect of the present invention, a method for installing an adjustable stator vane assembly includes:

[0019] The adjustable stationary blade is assembled and connected with the first bushing and the second bushing to form a first assembly.

[0020] The second assembly includes an intermediate casing outer ring, an upstream mounting ring located on the intermediate casing outer ring, and an intermediate casing inner ring located radially inward;

[0021] After inserting the assembly obliquely into the first connecting hole of the second assembly, straighten the assembly.

[0022] The downstream mounting ring is then installed so that the channel formed by the axial space between the upstream and downstream mounting rings is connected to the second bushing, and the intermediate casing provides dual-point support for the adjustable stator vane.

[0023] The positive effects of this case include, but are not limited to:

[0024] By using a structure where the second bushing has a length greater than the first bushing, the upstream and downstream mounting rings of the bushing structure and the mounting structure can be configured with small gaps to ensure airtightness and prevent leakage. This bushing structure facilitates assembly, and since bushings are prone to localized wear, the bushing structure used in this patent also facilitates disassembly, localized repair, and replacement. Furthermore, this structure is simple to implement, easy to manufacture, requires minimal modification to the main body structure, and has good manufacturability and feasibility. Simultaneously, it improves the performance and reliability of the compressor and gas turbine engine. Attached Figure Description

[0025] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments. It should be noted that the drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by the present invention, wherein:

[0026] Figure 1 It is the existing technology for the installation structure of adjustable stator vanes.

[0027] Figures 2A to 2C This is a schematic diagram of the steps in an embodiment of an adjustable stator blade installation method.

[0028] Figure 3A , Figure 3B This is a schematic diagram of the second bushing of the mounting structure of the adjustable stator vane according to one embodiment.

[0029] Figure 4 This is a schematic flowchart of an embodiment of an adjustable stator blade installation method.

[0030] Figure label:

[0031] 10-Installation Structure

[0032] 101-First Assembly

[0033] 102-Second Assembly

[0034] 1-Adjustable still leaf

[0035] 11-Blade body

[0036] 12-First connecting part

[0037] 121-First Platform Department

[0038] 122-First rotating shaft section

[0039] 123-First Shoulder

[0040] 13-Second connecting part

[0041] 131-Second Platform Department

[0042] 132-Second rotating shaft

[0043] 133-Second Shoulder

[0044] 2-Intermediate casing

[0045] 21-Intermediate casing outer ring

[0046] 210-First connecting hole

[0047] 22-Intermediate casing inner ring

[0048] 220-Second connecting hole

[0049] 31-First Bushing

[0050] 32-Second Bushing

[0051] 321-Bushing Body

[0052] 322-Extension

[0053] 3221 - First Length

[0054] 3222 - Second Length

[0055] 41-Upstream Installation Ring

[0056] 42-Downstream mounting ring. Detailed Implementation

[0057] The following discloses various implementation methods or embodiments of the described subject matter. To simplify the disclosure, specific examples of the elements and arrangements are described below. Of course, these are merely examples and are not intended to limit the scope of protection of the present invention.

[0058] Furthermore, it should be understood that terms such as "an embodiment," "one embodiment," and / or "some embodiments," or "one or more embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," "some embodiments," or "one or more embodiments" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. Moreover, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0059] The adjustable stator vanes described below use the adjustable stator vanes of a gas turbine engine compressor as an example, but are not limited to this. Gas turbine engines can take the form of aircraft engines, marine gas turbines, and land-based gas turbines, etc.

[0060] like Figures 2A to 2C ,as well as Figure 3A , Figure 3B As shown, in some embodiments, the mounting structure 10 for the adjustable stator vane includes the components described below.

[0061] The adjustable stator blade 1 includes a blade body 11 and a first connecting portion 12 and a second connecting portion 13 connected to the radially inner end and radially outer end of the blade body 11, respectively. The first connecting portion 12 has a first platform portion 121 connected to the blade body 11 and a first rotating shaft portion 122 protruding from the first platform portion 121. The second connecting portion 13 has a second platform portion 131 connected to the blade body 11 and a second rotating shaft portion 132 protruding from the second platform portion 131. The first platform portion 121 and the first rotating shaft portion 122 form a first shoulder 123, and the second platform portion 131 and the second rotating shaft portion 132 form a second shoulder 133.

[0062] Intermediate housing 2 includes an outer ring 21 and an inner ring 22 located radially inside the outer ring 21.

[0063] A first bushing 31 is fitted onto the first connecting portion 12; a second bushing 32 is fitted onto the second connecting portion 13. The structure of the first bushing 31 may include a sleeve portion 311 and a table portion 312.

[0064] The intermediate housing outer ring 21 has a first connecting hole 210, which is connected to the shaft hole of the first bushing 31; the intermediate housing inner ring 22 has a second connecting hole 220, which accommodates an upstream mounting ring 41 and a downstream mounting ring 42, and the channel 43 formed by the axial space between the upstream mounting ring 41 and the downstream mounting ring 42 is connected to the second bushing 32.

[0065] It can be understood that the upstream mounting ring 41 and the downstream mounting ring 42 are separate components, and the two can be connected axially by means of connectors such as bolts. This is a connection structure well known to those skilled in the art, and therefore is not shown in the figure.

[0066] This forms a dual-point support structure. In some embodiments, the intermediate casing outer ring 21 and the intermediate casing inner ring 22 respectively provide support for the adjustable stationary blade 1 on the radial inner and outer sides, so that the intermediate casing 2 provides dual-point support for the adjustable stationary blade 1.

[0067] The second bushing 32 includes a bushing body 321 and an extension 322 that extends radially outward from one end of the bushing body 321. The bushing body 321 and the extension 322 mate with the second shoulder 133. The extension length of the extension 322 corresponding to the upstream side of the second shoulder 133 is a first length 3221, and the extension length corresponding to the downstream side of the second shoulder 133 is a second length 3222. The second length 3222 is greater than the first length 3221.

[0068] The material of the second bushing 32 is generally metal, which makes the connection structure more reliable. However, this is not a limitation.

[0069] Continue to refer to Figures 2A to 3B As shown, in one or more embodiments, the first length 3221 has a size range of 2 mm to 3 mm, the second length 3222 has a size range of 4 mm to 5 mm, and the second length 3222 is 1 mm to 3 mm larger than the first length 3221.

[0070] Continue to refer to Figures 2A to 3B As shown, in one or more embodiments, the extension 322 is shaped as a chamfered annular shape, with the chamfer located on the upstream side of the extension 322, and the length removed being within the range where the second length 3222 is greater than the first length 3221. In some embodiments, the chamfered surface is a planar structure.

[0071] like Figures 2A to 2C As shown, by using the installation structure described in the above embodiments, the gap between the second bushing 32 and the upstream mounting ring 41 can be less than 0.2mm.

[0072] refer to Figure 4 The installation method for adjustable stator vanes may include the following steps:

[0073] S100. Assemble the adjustable stationary blade 1 with the first bushing 31 and the second bushing 32 to form a first assembly 101;

[0074] S200. The second assembly 102 includes an intermediate housing outer ring 21, and an upstream mounting ring 41 located on the intermediate housing outer ring 21 and an intermediate housing inner ring 22 located radially inward.

[0075] S300. After inserting the assembly 101 obliquely into the first connecting hole 210 of the second assembly 102, straighten the assembly 101;

[0076] The meaning of "slanted insertion" here is as shown in the figure, that the axis of the first connecting part 12 and the first connecting hole 210 does not coincide, but is tilted. The meaning of "aligned" here is to place the first connecting part 12 from the position tilted with the axis of the first connecting hole 210 to the position where the axis of the first connecting part 12 and the first connecting hole 210 coincide.

[0077] S400. Then the downstream mounting ring 41 is installed so that the channel 43 formed by the axial space between the upstream mounting ring 41 and the downstream mounting ring 42 is connected to the second bushing 32, and the intermediate casing 2 provides dual-point support for the adjustable stator 1.

[0078] In summary, the beneficial effects of the adjustable stator vane installation structure and method described in the above embodiments, as well as the compressor and gas turbine engine, include, but are not limited to:

[0079] By using a structure where the second bushing has a length greater than the first bushing, the upstream and downstream mounting rings of the bushing structure and the mounting structure can be configured with small gaps to ensure airtightness and prevent leakage. This bushing structure facilitates assembly, and since bushings are prone to localized wear, the bushing structure used in this patent also facilitates disassembly, localized repair, and replacement. Furthermore, this structure is simple to implement, easy to manufacture, requires minimal modification to the main body structure, and has good manufacturability and feasibility. Simultaneously, it improves the performance and reliability of the compressor and gas turbine engine.

[0080] While the present invention has been disclosed above with reference to the embodiments described, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A mounting structure (10) for adjustable stator vanes, characterized in that, include: An adjustable stator blade (1) includes a blade body (11) and a first connecting portion (12) and a second connecting portion (13) respectively connected to the inner radial end and the outer radial end of the blade body (11). The first connecting portion (12) has a first platform portion (121) connected to the blade body (11) and a first rotating shaft portion (122) protruding from the first platform portion (121). The second connecting portion (13) has a second platform portion (131) connected to the blade body (11) and a second rotating shaft portion (132) protruding from the second platform portion (131). The first platform portion (121) and the first rotating shaft portion (122) form a first shoulder (123), and the second platform portion (131) and the second rotating shaft portion (132) form a second shoulder (133). Intermediate housing (2), including intermediate housing outer ring (21) and intermediate housing inner ring (22) located radially inside the intermediate housing outer ring (21); The first bushing (31) is fitted onto the first connecting part (12); The second bushing (32) is fitted onto the second connecting part (13); The outer ring (21) of the intermediate casing has a first connecting hole (210) that is connected to the shaft hole of the first bushing (31). The inner ring (22) of the intermediate casing has a second connecting hole (220), which accommodates an upstream mounting ring (41) and a downstream mounting ring (42). The channel (43) formed by the axial space between the upstream mounting ring (41) and the downstream mounting ring (42) is connected to the second bushing (32). The second bushing (32) includes a bushing body (321) and an extension (322) extending radially outward from one end of the bushing body (321). The bushing body (321) and the extension (322) mate with the second shoulder (133). The extension (322) has a first length (3221) corresponding to the upstream side of the second shoulder (133) and a second length (3222) corresponding to the downstream side of the second shoulder (133). The second length (3222) is greater than the first length (3221).

2. The mounting structure (10) as described in claim 1, characterized in that, The first length (3221) has a size range of 2 mm to 3 mm, the second length (3222) has a size range of 4 mm to 5 mm, and the second length (3222) is greater than the first length (3221) by a size range of 1 mm to 3 mm.

3. The mounting structure (10) as described in claim 2, characterized in that, The extension (322) is shaped as a chamfered ring, with the chamfer located on the upstream side of the extension (322), and the length removed is within the range where the second length (3222) is greater than the first length (3221).

4. The mounting structure (10) as described in claim 3, characterized in that, The chamfered surface has a planar structure.

5. The mounting structure (10) as described in claim 1, characterized in that, The gap between the second bushing (32) and the upstream mounting ring (41) is less than 0.2 mm.

6. The mounting structure (10) as described in claim 1, characterized in that, The material of the second bushing (32) is metal.

7. The mounting structure (10) as described in claim 1, characterized in that, The intermediate casing outer ring (21) and the intermediate casing inner ring (22) respectively provide support for the adjustable stationary blade (1) on the radial inner and outer sides, so that the intermediate casing (2) provides dual-point support for the adjustable stationary blade (1).

8. A compressor, characterized in that, The mounting structure includes the adjustable stator assembly as described in any one of claims 1-7.

9. A gas turbine engine, characterized in that, Includes the adjustable stator assembly as described in any one of claims 1-7.

10. An installation method for the installation structure as described in any one of claims 1-7, the installation method comprising: The adjustable stationary blade (1) is assembled and connected with the first bushing (31) and the second bushing (32) to form a first assembly (101); The second assembly (102) includes an intermediate casing outer ring (21) and an upstream mounting ring (41) located on the intermediate casing outer ring (21) and an intermediate casing inner ring (22) located radially inward; After inserting the first assembly (101) obliquely into the first connecting hole (210) of the second assembly (102), straighten the assembly (101); The downstream mounting ring (41) is then installed so that the channel (43) formed by the axial space between the upstream mounting ring (41) and the downstream mounting ring (42) is connected to the second bushing (32), and the intermediate casing (2) provides two-point support for the adjustable stator (1).

Images