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CN-121993293-A - Mounting structure for adjustable stationary blade, compressor, and gas turbine engine

CN121993293ACN 121993293 ACN121993293 ACN 121993293ACN-121993293-A

Abstract

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

Inventors

  • ZHANG SHIQI
  • LI XIANGPENG
  • NIE CONG

Assignees

  • 中国航发商用航空发动机有限责任公司

Dates

Publication Date
20260508
Application Date
20241106

Claims (10)

  1. 1. A mounting structure (10) for an adjustable vane, comprising: the adjustable stator blade (1) comprises a blade body (11), and a first connecting part (12) and a second connecting part (13) which are respectively connected with the radial inner end and the radial outer end of the blade body (11), wherein the first connecting part (12) is provided with a first platform part (121) connected with the blade body (11) and a first rotating shaft part (122) protruding from the first platform part (121), the second connecting part (13) is provided with a second platform part (131) connected with the blade body (11) and a second rotating shaft part (132) protruding from the second platform part (131), the first platform part (121) and the first rotating shaft part (122) form a first shaft shoulder (123), and the second platform part (131) and the second rotating shaft part (132) form a second shaft shoulder (133); An intermediate casing (2) comprising an intermediate casing outer ring (21), and an intermediate casing inner ring (22) located radially inward of the intermediate casing outer ring (21); A first bushing (31) sleeved on the first connecting part (12); a second bushing (32) sleeved on the second connecting part (13); wherein the intermediate casing outer ring (21) is provided with a first connecting hole (210) which is connected with the shaft hole of the first bushing (31) in a matching way; the intermediate casing inner ring (22) is provided with a second connecting hole (220), the second connecting hole (220) is provided with an upstream mounting ring (41) and a downstream mounting ring (42), and a pore canal (43) formed by an axial space between the upstream mounting ring (41) and the downstream mounting ring (42) is connected with the second bushing (32) in a matching way; The second bushing (32) comprises a bushing body (321) and an extension part (322) which radially and outwards expands from one end of the bushing body (321), the bushing body (321) is matched with the extension part (322) and the second shoulder (133), the extension length of the extension part (322) corresponding to the upstream side of the second shoulder (133) is a first length (3221), the extension length corresponding to the downstream side of the second shoulder (133) is a second length (3222), and the second length (3222) is larger than the first length (3221).
  2. 2. The mounting structure (10) of claim 1, wherein the first length (3221) has a size ranging from 2mm to 3mm, the second length (3222) has a size ranging from 4mm to 5mm, and the second length (3222) is greater than the first length (3221) by a size ranging from 1mm to 3mm.
  3. 3. The mounting structure (10) of claim 2, wherein the extension (322) is shaped as a chamfered ring, the position of the chamfer being on the upstream side of the extension (322), the length of the chamfer being a size range where the second length (3222) is greater than the first length (3221).
  4. 4. A mounting structure (10) according to claim 3, wherein the chamfer surface is a planar structure.
  5. 5. The mounting structure (10) of claim 1, wherein the clearance of the second bushing (32) from the upstream mounting ring (41) is less than 0.2mm.
  6. 6. The mounting structure (10) of claim 1, wherein the material of the second bushing (32) is metal.
  7. 7. The mounting structure (10) of claim 1, wherein the intermediate casing outer ring (21) and intermediate casing inner ring (22) provide support for the adjustable vanes radially inside and outside of the adjustable vane (1), respectively, such that the intermediate casing (2) provides dual point support for the adjustable vane (1).
  8. 8. A compressor comprising the mounting structure of the adjustable vane assembly of any one of claims 1-7.
  9. 9. A gas turbine engine comprising the adjustable vane assembly of any of claims 1-7.
  10. 10. A mounting method for the mounting structure of any one of claims 1-7, the mounting method comprising: Assembling and connecting the adjustable stationary blade (1) with the first bushing (31) and the second bushing (32) to form a first assembly body (101); The second assembly body (102) comprises an intermediate casing outer ring (21), and an upstream mounting ring (41) located at the intermediate casing outer ring (21) and at the radially inner intermediate casing inner ring (22); After the first assembly body (101) is obliquely inserted into the first connecting hole (210) of the second assembly body (102), the assembly body (101) is aligned; And then mounting a downstream mounting ring (41) so that a duct (43) formed by an axial space between the upstream mounting ring (41) and the downstream mounting ring (42) is in matched connection with the second bushing (32), wherein the intermediate casing (2) provides double-point support for the adjustable stator blade (1).

Description

Mounting structure for adjustable stationary blade, compressor, and gas turbine engine Technical Field The invention relates to the field of impeller machinery, in particular to a mounting structure and a mounting method for an adjustable stationary blade, a gas compressor and a gas turbine engine. Background The adjustable stator blade, namely the adjustable stationary blade (Variable Stator Vane, VSV) for short, is the stator blade which can change the installation angle according to the operation condition of the engine. The main purpose of applying VSV on an engine is to improve the working stability of the engine and prevent surge. The VSV adjusting mechanism is used for driving the adjustable stator blade to rotate, changing the installation angle of the adjustable stator blade, and adjusting the through flow of the blade grid and the attack angle of the airflow behind the grid so as to ensure the normal and stable operation of the compressor. The VSV regulating mechanism is widely applied to aeroengine compressors in high-pressure compressors of multi-type gas turbine engines, and is provided with inlet guide vanes for changing an inlet attack angle when the compressor works, so that the inlet direction and flow are changed, and the compressor is prevented from surging. The inlet guide vane is of a double-fulcrum structure, the upper end of the inlet guide vane is arranged on an adjustable blade mounting seat of the intermediate inner casing, and the lower end of the inlet guide vane is supported on the inner ring assembly. The inner and outer axle journals of the adjustable blades are provided with bushings, so that the flexible rotation of the blades can be ensured, the flow channels can be sealed, and leakage loss is prevented. The IGV inner ring adopts a front-rear split structure to provide support for the IGV blades, as shown in fig. 1. As shown in fig. 2A, during the installation of the IGV assembly into the intermediate inner casing assembly, since the inlet guide vanes are mounted in an oblique insertion, the radial clearance between the inlet guide vane inner liner 32A and the IGV inner ring is designed to be about 0.8mm in order to prevent the interference of the assembly path, but the inventors found that such clearance is disadvantageous in terms of air tightness and assembly convenience. Accordingly, there is a need in the art for a mounting structure, mounting method, compressor, and gas turbine engine for an adjustable vane that address at least one of the above technical problems. Disclosure of Invention It is an object of the present invention to provide a mounting structure for an adjustable vane assembly. It is an object of the present invention to provide a compressor. It is an object of the present invention to provide a gas turbine engine. It is an object of the present invention to provide a method of mounting an adjustable vane assembly. An adjustable stator blade assembly mounting structure according to one aspect of the invention comprises an adjustable stator blade, a rotor blade and a stator blade assembly, wherein the adjustable stator blade comprises a blade body, a first connecting part and a second connecting part, wherein the first connecting part and the second connecting part are respectively connected with the radial inner end and the radial outer end of the blade body, the first connecting part is provided with a first platform part connected with the blade body and a first rotating shaft part protruding from 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 casing comprises an intermediate casing outer ring, an intermediate casing inner ring, a first bushing, a second bushing, a first connecting hole, a second connecting hole, a hole channel, a bushing body and an extending part, wherein the intermediate casing inner ring is positioned on the radial inner side of the intermediate casing outer ring and is sleeved on the first connecting part, the first bushing is sleeved on the second connecting part, the intermediate casing outer ring is provided with the first connecting hole and is connected with the first bushing shaft hole in a matched mode, the intermediate casing inner ring is provided with the second connecting hole, the second connecting hole is used for accommodating an upstream mounting ring and a downstream mounting ring, a hole channel formed in an axial space between the upstream mounting ring and the downstream mounting ring is connected with the second bushing in a matched mode, the bushing body is matched with the second shaft hole, the extending part is expanded outwards from one end of the bushing body in