Engine rotor blade tip assembling clearance measuring method

Abstract

The invention provides an engine rotor blade tip assembly clearance measurement method, which comprises the following steps of S1, determining a plurality of axial positions of a blade tip according to the blade tip, rotating a rotor and measuring the average diameter of the determined positions through an optical measurement method; s2, determining the position of a casing corresponding to the position of a rotor blade tip, and measuring the average diameter of the position through an optical or three-coordinate measurement method; and S3, the actual clearance of the rotor blade tip is obtained through the measured casing diameter and the measured rotor blade tip diameter. Compared with a traditional method for measuring the blade tip clearance through a feeler gauge, the measuring error is greatly reduced. According to the measurement method, the diameter size measured through optics or three coordinates is the average size obtained by integrating all the blades, the measurement coverage is wide, and the credibility is high. In addition, detection at a fixed position can be met through advanced optical or three-coordinate measurement, the repeatability is high, and the precision of gap measurement can be further ensured.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and in particular to a method for measuring the assembly clearance of engine rotor blade tips. Background Technology

[0002] In the field of aero-engines, the control of rotor blade tip clearance has a significant impact on engine safety and performance, both domestically and internationally. If the blade tip clearance is too small, there is a risk that the blade tip may scrape the coating or even the metal substrate of the casing under extreme operating conditions or maneuvering loads, thus affecting the safe operation of the engine. If the blade tip clearance is too large, it may lead to performance not meeting the overall matching requirements, significantly impacting the overall engine performance.

[0003] However, for mass-produced engines, blade tip clearance sensors are generally no longer installed, and the actual measured clearance during assembly is the only standard for determining whether the clearance is qualified.

[0004] In traditional assembly processes, the clearance is typically measured by inserting a feeler gauge into the gap between the casing and the blade tip. This method has the following problems:

[0005] 1. There is a radial gap between the blades and the wheel; when measured with a feeler gauge, the blades will move closer to the wheel. For example... Figure 1 As shown, due to the gap 30 between the wheel 10 and the blade 20, the blade will displace in the B direction when measuring the blade tip gap 40. The measured gap is larger than the actual gap, which leads to inaccurate measurement and large error.

[0006] Second, using a feeler gauge can only inspect a small number of blades in the circumferential direction. The number of blades inspected is small, and it can only show the local blade tip gap. It cannot truly reflect the overall blade tip gap of that stage.

[0007] Third, the measurement results are greatly affected by the operator's technique. Different measurement positions and the force applied by the feeler gauge will result in different measurement results, and the consistency of repeated measurements is poor.

[0008] In view of this, the inventors of this application have designed a method for measuring the assembly clearance of engine rotor blade tips in order to overcome the above-mentioned technical problems. Summary of the Invention

[0009] The technical problem to be solved by the present invention is to overcome the defects of the prior art, such as large measurement error of rotor blade assembly clearance and small number of test samples, and to provide a method for measuring the assembly clearance of engine rotor blade tips.

[0010] The present invention solves the above-mentioned technical problems through the following technical solution:

[0011] A method for measuring the assembly clearance of engine rotor blade tips, characterized in that the method includes the following steps:

[0012] S1, determining several axial positions of the blade tip, rotating the rotor and measuring the average diameter of the determined positions by optical measurement method;

[0013] S2, determining the casing positions corresponding to the positions of the rotor tip, measuring the average diameter of the positions by optical or three-coordinate measurement method;

[0014] S3, calculating the actual clearance of the rotor tip by the measured casing diameter and rotor tip diameter.

[0015] According to one embodiment of the present application, the step S1 comprises:

[0016] S 11 , determining several axial positions P1, P2…P n of the rotor tip, which can be selected uniformly according to the width of the blade;

[0017] S 12 , rotating the rotor at high speed, and measuring the diameter size of each position P1, P2…P n by optical measurement method, and recording as DP1, DP2…DP n .

[0018] According to one embodiment of the present application, the step S 12 further comprises: during the grinding of the rotor tip, directly measuring the average diameter size of each position P1, P2…P n by the rotor tip grinding equipment.

[0019] According to one embodiment of the present application, the step S2 comprises:

[0020] S 21 , according to the assembly relationship of the rotor and the stator, calculating the corresponding casing positions K1, K2…K n of P1, P2…P n by the size chain of related parts.

[0021] S 22 , measuring the diameter size of each position of the casing K1, K2…K n by three-coordinate or optical measurement method, and recording as DK1, DK2…DK n .

[0022] According to one embodiment of the present application, the axial distance data used in the size chain calculation in the step S 21 is the measured data of the parts, or the design data of the drawings.

[0023] According to one embodiment of the present application, the step S3 comprises: calculating the tip clearance by the measured casing diameter and the rotor tip diameter, and the tip clearance at each position is denoted as δ n , δ n =(DK n -DPn n ) / 2.

[0024] The positive progress effect of the present application is that:

[0025] The engine rotor tip assembly clearance measuring method has the following advantages:

[0026] I. Compared with the traditional method of measuring the tip clearance by using a plug gauge, the measurement error is greatly reduced.

[0027] II. The diameter size measured by the optical or three-coordinate measurement method is the average size obtained by integrating all the blades, and the measurement coverage is wide and the reliability is high.

[0028] III. In addition, the advanced optical or three-coordinate measurement can meet the detection in a fixed position, and the repeatability is high, which can further ensure the accuracy of the gap measurement and provide a strong guarantee for the safe operation and high-performance operation of the aero-engine. BRIEF DESCRIPTION OF DRAWINGS

[0029] The above and other features, properties and advantages of the present application will become more apparent from the following description with reference to the accompanying drawings and embodiments, in which the same reference numerals represent the same features throughout the drawings, in which:

[0030] Figure 1 is a mounting schematic diagram of a tenon blade.

[0031] Figure 2 is a rotor-stator assembly schematic diagram.

[0032] Figure 3 is a tip clearance condition schematic diagram in the engine rotor tip assembly clearance measuring method of the present application. DETAILED DESCRIPTION

[0033] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0034] The embodiments of the present application will now be described in detail with reference to the accompanying drawings. The preferred embodiments of the present application will now be described in detail with reference to the drawings. In all the drawings, the same reference numerals will be used to represent the same or similar parts.

[0035] Furthermore, although the terms used in the present application are selected from publicly known and used terms, some of the terms mentioned in the description of the present application can be created by the applicant in his or her own judgment, and the detailed meanings thereof are described in relevant parts of the description.

[0036] Furthermore, the present application is to be understood based on its meaning, not only by the actual terms used.

[0037] Figure 3 For the engine rotor blade tip assembly gap measurement method, the blade tip gap condition schematic diagram.

[0038] As Figure 3 shown, the present application discloses an engine rotor blade tip assembly gap measurement method, which comprises the following steps:

[0039] Step S1, determine the blade tip axial position, rotate the rotor and measure the average diameter of the determined position by optical measurement method.

[0040] Preferably, the step S1 comprises:

[0041] Step S 11 , determine the rotor blade tip axial position P1, P2…P n , which can be selected according to the blade width axial uniformity;

[0042] Step S 12 , high-speed rotation of the rotor, and measure the diameter size of P1, P2…P n each position by optical measurement method, record as DP1, DP2…DP n .

[0043] Further preferably, the step S 12 in the rotor blade tip grinding, the average diameter size of P1, P2…P n each position is directly measured by the rotor blade tip grinding equipment.

[0044] Step S2, determine the casing position corresponding to the rotor blade tip position, and measure the average diameter of the position by optical or three coordinate measurement method.

[0045] Preferably, the step S2 comprises:

[0046] Step S 21 , according to the assembly relationship of the rotor and the stator, the size chain of the related parts is calculated to obtain P1, P2…P n corresponding casing position K1, K2…K n .

[0047] Further preferably, in the step S 21 The axial distance data used in the middle size chain calculation can be preferably the measured data of the part, or can also be simplified as the design data of the drawing.

[0048] As shown in the drawings, Figure 2 The assembly relationship of the rotor and the stator in the application is that the rotor 60 and the casing 50 are matched together through the force-bearing casing 70 and the support structure 80.

[0049] Step S 22 , the diameters of the positions of the casings K1, K2…K n are measured by the three-coordinate or optical measurement method, and are recorded as DK1, DK2…DK n .

[0050] Step S3, the actual tip clearance of the rotor is obtained through the measured diameters of the casings and the rotor blade tip.

[0051] Preferably, the step S3 comprises: calculating the tip clearance through the measured diameters of the casings and the rotor blade tip, and the tip clearance at each position is recorded as δ n , δ n =(DK n -DP n ) / 2.

[0052] According to the above description, the engine rotor blade tip assembly clearance measurement method provides a blade tip measurement method that can be implemented in the assembly process, and can effectively avoid the problems of large measurement error, few detection samples and inability to truly reflect the blade tip clearance of each stage of blade tip in the traditional plug gauge measurement of blade tip clearance.

[0053] The measurement method rotates the rotor, avoids the case that the blade cannot be measured accurately due to the installation clearance, and measures the size of each blade and gives an average value when the rotor rotates, so that the detection sample is sufficient and the blade tip size can be truly reflected. Meanwhile, the fixed measurement position is determined, and the measurement is repeatable. In addition, the three-coordinate and optical equipment have high precision, which provides guarantee for accurate measurement.

[0054] In summary, the engine rotor blade tip assembly clearance measurement method has the following advantages:

[0055] I. Compared with the traditional plug gauge measurement method of blade tip clearance, the measurement error is greatly reduced.

[0056] II. The diameter size measured by the optical or three-coordinate measurement method is the average size obtained by comprehensively considering all the blades, and the measurement coverage is wide and the reliability is high.

[0057] III. In addition, advanced optical or three-coordinate measurement can be used to detect the gap at a fixed position, with high repeatability, and further ensure the accuracy of the gap measurement, providing a strong guarantee for the safe and high-performance operation of the aero-engine.

[0058] The above-described disclosure of the application is merely exemplary and does not limit the application. Although the application is not explicitly described, those skilled in the art can make various modifications, improvements and corrections to the application. Such modifications, improvements and corrections are suggested in the application, and still fall within the spirit and scope of the exemplary embodiments of the application.

[0059] At the same time, the application uses specific words to describe the embodiments of the application. As "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that the "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different places in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the application can be properly combined.

[0060] Similarly, it should be noted that, in order to simplify the description of the disclosure and to help understand one or more embodiments of the application, the above description of the embodiments of the application sometimes combines various features into one embodiment, figure or description thereof. However, this method of disclosure does not mean that the features required by the application are more than those mentioned in the claims. In fact, the features of the embodiments are less than all the features of the above-mentioned single embodiment.

[0061] Although the above describes specific embodiments of the application, those skilled in the art should understand that these are only illustrative, and the scope of protection of the application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the application, and such changes and modifications fall within the scope of protection of the application.

Claims

1. An engine rotor tip shroud fit clearance measurement method, characterized by, The engine rotor tip assembly gap measuring method comprises the following steps: S1, determining several axial positions of the blade tip, rotating the rotor and measuring the average diameter of the determined position by optical measuring method; S2, determining the position of the casing corresponding to the position of the rotor tip, and measuring the average diameter of the position by optical or three-coordinate measuring method; S3, calculating the actual gap of the rotor tip by measuring the casing diameter and the rotor tip diameter.

2. The method of claim 1, wherein, The step S1 comprises: S 11 , determining several axial positions P1, P2...P n , which can be selected uniformly in the axial direction according to the blade width. S 12 , high speed rotating rotor, and measuring P1, P2...P n the diameter size of each position, recorded as DP1, DP2...DP n .

3. The method of claim 2, wherein, The step S 12 Further included in the step S n The average diameter size at each location.

4. The method of claim 1, wherein, The step S2 comprises: S 21 , according to the assembly relationship of the rotor and the stator, P1, P2...P n corresponding to the positions K1, K2...K n ; S 22 The diameters of the positions in each chamber K1, K2...K n are measured by three-coordinate or optical measurement methods, and recorded as DK1, DK2...DK n .

5. The method of claim 4, wherein, The step S 21 The axial distance data used in the medium size chain calculation is the measured data of the part or the design data of the drawing.

6. The method of claim 1, wherein, The step S3 includes: calculating the tip clearance by the measured casing and rotor tip diameter data, the clearance at each point of the tip is denoted as δ n , δ n =(DK n -DP n ) / 2.

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