CN-121997473-A - Rotor blade tip profiling design method, rotor blade and compressor

Abstract

A rotor blade tip profiling design method includes the steps of arranging a scraping coating on one side of a casing, facing a rotor blade, arranging a plurality of bosses in the chord length direction at the blade tip of the rotor blade, scraping the bosses with the casing in an initial state, operating an engine to enable the rotor blade to be in a working state and keep scraping with the casing, acquiring scraping data of the scraping coating in the chord length direction of the blade after the working state is ended, and reversely designing the radial dimension of the rotor blade tip according to the scraping data. The method is based on the relation between the blade tip shape and the blade tip gap, and the gap along the chord length direction of the blade can be flexibly, accurately and multiply designed and controlled reversely through scraping data of the scraping coating. A rotor blade and a compressor are also provided.

Inventors

• ZHANG SHIQI
• LIN QINGSONG
• XIAO YARU

Assignees

• 中国航发商用航空发动机有限责任公司

Dates

Publication Date

20260508

Application Date

20241101

Claims (10)

1. 1. The profiling design method for the tip of the rotor blade is characterized by comprising the following steps of: A scraping coating is arranged on one side of the casing facing the rotor blade, a plurality of bosses are arranged at the blade tip of the rotor blade along the chord length direction, and each boss is scraped with the casing in an initial state; the engine is operated, so that the rotor blade is in a working state and is kept scraped with the case; after the working state is finished, scraping data of the scraping coating along the chord length direction of the blade are obtained; and reversely designing the radial dimension of the rotor blade tip according to the scraping data.
2. 2. The rotor blade tip profiling method as recited in claim 1, wherein a radial height of the boss is no greater than 0.5mm.
3. 3. The rotor blade tip profile design method of claim 1, wherein the engine is operated and brought to a cruise condition.
4. 4. The rotor blade tip profiling design method of claim 1, wherein the rotor blade tip comprises a reference radial dimension, and wherein the reference radial dimension is subtracted from the scraping data sequentially along the blade chord direction to obtain a designed radial dimension of the rotor blade tip along the blade chord direction.
5. 5. The method for profiling a rotor blade tip according to claim 1, wherein after the scraping data of each point along the chord length direction of the blade is obtained, a scraping change line of a scraping coating is obtained by adopting a fitting method, and the shape of the blade tip is obtained by using the scraping change line.
6. 6. The rotor blade tip profiling method of claim 1, wherein the thickness of the scratch coating ranges from 1mm to 100mm.
7. 7. The rotor blade tip profile design method as set forth in claim 1, wherein the engine is maintained at cruise for a period of time.
8. 8. The rotor blade tip profiling design method of claim 1, wherein 20-30 bosses are arranged along a chord direction.
9. 9. Rotor blade, characterized in that it is obtained using a rotor blade tip profiling method according to any of claims 1-8.
10. 10. A compressor comprising the rotor blade of claim 9.

Description

Rotor blade tip profiling design method, rotor blade and compressor Technical Field The invention relates to the field of rotor blades of aeroengines, in particular to the field of profiling of tips of rotor blades. Background The compressor is one of the important components of an aeroengine, and the design, testing and control of blade tip clearances are critical to the performance of the compressor. The change of the blade tip clearance is usually formed by coupling factors such as a blade, a case deformation amount, eccentricity, bearing play and the like, and the influence factors are numerous, so that the accurate simulation calculation is difficult in design. Chinese patent CN112343855 proposes a method for on-wing evaluation of the tip clearance of an aeroengine, in which an abradable coating is applied to the inner surface of a casing, at least two grooves are provided on the tip of at least one rotor blade, the depth of each groove being different from the depth of any other groove, and at least two marker blocks are provided at the portion of the abradable coating facing the rotor blade, each marker block having a thickness different from the thickness of any other marker block. The monitoring device is extended into the interior of the aircraft engine via the probe holes and aligned with the area including the grooves on the blade tip and the marker blocks on the abradable coating to acquire an image of the area. When the blade tip clearance changes due to the fact that the rotor blade and the casing scrape against each other in the wing operation process, the abrasion loss of the easily-ground coating and the blade tip can be quickly and simply determined by identifying the number of the marking blocks remained on the easily-ground coating of the casing and the number of the grooves remained on the blade tip of the rotor blade, meanwhile, the abrasion loss is determined by acquiring the number of the marking blocks remained on the easily-ground coating and the number of the grooves remained on the blade tip, and the change of the blade tip clearance in the wing operation process can be easily and accurately acquired. When designing a rotor blade profile, aerodynamic performance and strength requirements are mainly considered, the size of the rotor blade tip is usually determined by a straight line or two straight lines with a certain angle, the clearance in the chord length direction cannot be accurately designed, and the problem that the rotor blade tip is deformed in an uncoordinated manner often occurs. If the clearance of the rotor blade tip is smaller, the risk of scraping the inner wall of the casing exists, the safety cannot be ensured, and if the clearance of the rotor blade tip is larger, the efficiency and the performance of the compressor may not reach standards. Disclosure of Invention The invention provides a rotor blade tip profiling design method based on the relationship between the blade tip shape and the blade tip clearance. The profiling design method for the tip of the rotor blade for achieving the purpose comprises the following steps of: A scraping coating is arranged on one side of the casing facing the rotor blade, a plurality of bosses are arranged at the blade tip of the rotor blade along the chord length direction, and each boss is scraped with the casing in an initial state; the engine is operated, so that the rotor blade is in a working state and is kept scraped with the case; after the working state is finished, scraping data of the scraping coating along the chord length direction of the blade are obtained; and reversely designing the radial dimension of the rotor blade tip according to the scraping data. In one or more embodiments, the radial height of the boss is no greater than 0.5mm. In one or more embodiments, the engine is operated and brought to a cruise condition. In one or more embodiments, the rotor blade tip includes a reference radial dimension, and the scraping data is subtracted from the reference radial dimension in sequence along the blade chord direction to obtain a designed radial dimension of the rotor blade tip along the blade chord direction. In one or more embodiments, after the scraping data of each point along the chord length direction of the blade is obtained, a fitting method is adopted to obtain a scraping change line of the scraping coating, and the scraping change line is used to obtain the blade tip shape. In one or more embodiments, the thickness of the scratch coating ranges from 1 mm to 100mm. In one or more embodiments, the engine is maintained at a cruise condition for a period of time. In one or more embodiments, 20 to 30 bosses are provided along the chord direction. It is a further object of the present invention to provide a rotor blade obtained using the above rotor blade tip profiling design method. It is a further object of the present invention to provide a compressor characterized by comprising the above rotor blade. Ac