A method for analyzing measurement results of an aero-engine test test instrument

Abstract

The application belongs to the field of aero-engine test instrument measurement result analysis, and particularly relates to an aero-engine test instrument measurement result analysis method, which designs the distribution of each upstream blade, each test instrument and each height of the measuring point in the circumferential direction, expands according to the equal length 360, and matches the outlet airflow angle, can directly and clearly show the relative position relationship between each measuring point on each test instrument and the upstream blade at the corresponding blade height, can greatly facilitate the test result analysis, and can also be used for aero-engine test instrument arrangement scheme design.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of measurement result analysis of aero-engine test test instruments, and particularly relates to a measurement result analysis method of aero-engine test test instruments. BACKGROUND

[0002] In aero-engine tests, the measurement of parameters such as temperature and pressure is involved. For this purpose, test instruments are arranged along the circumferential direction in the measurement section, such as a pressure test probe, a temperature test probe and a direction test probe, as shown in FIG. 1, for measurement. Figures 1-2

[0003] In aero-engine tests, the distribution of parameters in the measurement section is affected by the upstream blade profile, the outlet flow angle and its wake. The relative positions of the test instruments and the upstream blade are different, and the measurement results of the parameters are also significantly different. Therefore, when analyzing the measurement results, the relative positions between the measurement points distributed along the blade height direction on the test instruments and the upstream blade need to be considered. For this purpose, the current method is to analyze the relative positions by expanding the upstream blade profile and the measurement points on the test instruments along the circumferential direction, as shown in FIG. 2. This method has the following disadvantages: the positions of the measurement points distributed along the blade height direction on the same test instrument are relatively discrete, and the relative positions between the measurement points on the test instruments and the upstream blade cannot be intuitively observed. Figure 3

[0004] The present application is proposed in view of the above technical defects.

[0005] It should be noted that the disclosure of the above background art content is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide a measurement result analysis method of aero-engine test test instruments to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is as follows:

[0008] A measurement result analysis method of aero-engine test test instruments, comprising:

[0009] selecting a certain characteristic position on the circumference as a reference position;

[0010] drawing a circumferential boundary at a length of 180 (the length unit can be optional, as long as the unit is consistent in the subsequent process) on both sides of the reference position, and the circumferential direction between the two boundaries represents the measurement section; ​​

[0011] The blade profile section of the upstream blade at the height of each test point on each test instrument is intercepted, scaled, and the scaling factor γ = 360 / (π*D), wherein D is the diameter of the height of the test point;

[0012] The initial position of each blade profile section is determined corresponding to the installation position of the upstream blade, taking the reference position as a marker (note: the scaling factor of each height is different), and each blade profile section is distributed along the vertical direction (note: a certain interval is left between each blade profile for subsequent measurement of the profile of the blade after drawing);

[0013] The outlet flow angle of each test point on the upstream blade profile section is referenced, and the flow angle a is drawn after each scaled blade profile section;

[0014] Each scaled blade profile section is repeatedly copied to both sides with equal intervals θ = 360 / n from the initial position, wherein n is the number of upstream blades;

[0015] The measurement section line is drawn at S = γ x L after each row of scaled blade profile sections, wherein L is the axial distance between the measurement section and the upstream blade;

[0016] A straight line representing the test instrument is drawn vertically to the circumferential direction corresponding to the distribution position of the test instrument on the engine circumference, taking the reference position as a marker, and the test instrument straight line is repeatedly copied to both sides with equal intervals β, wherein β is the circumferential angle between each test instrument on the engine measurement section;

[0017] The intersection of each measurement section line and the straight line representing the test instrument is marked as a test point.

[0018] According to at least one embodiment of the present application, in the above-mentioned aero-engine test test instrument measurement result analysis method, the reference position selected on the measurement section is the position directly above the measurement section;

[0019] According to at least one embodiment of the present application, in the above-mentioned aero-engine test test instrument measurement result analysis method, the blade profile on the circumference of each height section and the test instrument test point are both expanded according to the equal length 360. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a schematic diagram of the existing aero-engine test in which the test instruments are arranged along the circumference in the measurement section for parameter measurement;

[0021] Figure 2 is a Q view of Figure 1 ;

[0022] Figure 3is a schematic diagram of the existing circumferential development method, which sequentially develops the test instrument at the same blade height and the upstream blade profile section along the circumferential direction for analysis.

[0023] Figure 4 is a schematic diagram of the method for analyzing the measurement results of the test instrument of the aero-engine test provided by the embodiment of the present application.

[0024] In order to better illustrate the embodiment, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present patent. DETAILED DESCRIPTION

[0025] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described in detail below in combination with the drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application, which are used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0026] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be understood as the general meaning understood by the general technical personnel in the field of the present application. The words indicating the relative direction or position relationship, such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application, are only used to indicate the relative direction or position relationship, and not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and the relative position relationship may also change accordingly when the absolute position of the described object changes, therefore, it cannot be understood as a limitation of the present application. The "first", "second", "third" and similar terms used in the description of the present application are only for the purpose of description, and are used to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and similar terms used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as the existence of at least one. The "include" or "contain" and similar terms used in the description of the present application mean that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and do not exclude other elements or objects.

[0027] In addition, it needs to be explained that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and similar words used in the description of the application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integrally connected; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal connection of two elements, and those skilled in the art can understand the specific meaning of the application according to the specific circumstances.

[0028] The specific embodiments of the application will be further described below with reference to the accompanying drawings Figures 1 to 4 The application will be further described in detail.

[0029] An aero-engine test test instrument measurement result analysis method, comprising:

[0030] Select a certain characteristic position on the circumference as the reference position, which can correspond to the 0° position;

[0031] Draw the circumferential boundary 180mm on both sides of the reference position, and each 1mm can correspond to 1° on the engine circumference;

[0032] Intercept the blade profile section of the upstream blade at the blade height of each test point on each test instrument, and scale, the scaling factor γ = 360 / (π*D), wherein D is the diameter of the blade height where the test point is located;

[0033] Corresponding to the installation position of the upstream blade, the initial position of each blade profile section is determined with the reference position as the marker, and each blade profile section is distributed along the vertical direction perpendicular to the circumference;

[0034] Referring to the outlet flow angle of the upstream blade profile section at the blade height of each test point, draw the flow angle α behind each scaled blade profile section;

[0035] Copy each scaled blade profile section repeatedly to both sides of the boundary with the initial position as the starting point, and the interval θ = 360 / n, wherein n is the number of upstream blades, and θ is equal to the angle between the upstream blades in value;

[0036] Draw the measurement section line at S = γ x L behind each row of scaled blade profile sections, wherein L is the axial distance between the measurement section and the upstream blade;

[0037] Corresponding to the distribution position of the test instrument on the engine circumference, draw a straight line representing the test instrument vertically to the circumferential direction with the reference position as the marker, and copy the test instrument straight line repeatedly to both sides of the boundary with the interval β, wherein β is the circumferential angle between each test instrument on the engine measurement section;

[0038] The intersection of each measurement section line and the straight line representing the test instrument is marked as a test point.

[0039] For the aero-engine test instrument measurement result analysis method disclosed in the above embodiments, those skilled in the art can understand that the upstream blades, the test instruments and the measurement points at each height are designed to be distributed in the circumferential direction, to be expanded according to the equal length 360, and to be matched with the outlet airflow angle. In addition, by drawing the measurement section line after the scaling of each row of blade profile sections and the straight line representing the test instrument, the measurement points on each test instrument can be determined conveniently, and the relative positional relationship between the measurement points on each test instrument and the upstream blades at the corresponding blade height can be indicated intuitively and clearly, which can greatly facilitate the test result analysis.

[0040] In some optional embodiments, the aero-engine test instrument measurement result analysis method disclosed above selects a reference position on the measurement section, which is generally the position directly above the measurement section.

[0041] In some optional embodiments, the aero-engine test instrument measurement result analysis method disclosed above expands the blade profile and the test instrument measurement point on each blade height section circle according to the equal length 360, to reflect the actual test instrument by the straight line representing the test instrument, and to reflect the actual measurement point on the test instrument by the intersection of the downstream measurement section of the blade and the straight line of the test instrument.

[0042] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts between each embodiment can be understood by referring to each other.

[0043] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A method for analyzing measurement results from an aero-engine testing instrument, characterized in that, include: Select a reference position on the circumference of the aero-engine; Draw the circumferential boundary 180mm to both sides of the reference position; The blade profile of the blade upstream of each measuring point on each testing instrument is captured and scaled. The scaling factor is γ=360 / (π*D), where D is the diameter of the blade at the measuring point. Corresponding to the installation position of the upstream blade, at the reference position, the scaled airfoil sections are drawn sequentially along the axial direction corresponding to the blade height of each measuring point. Referring to the outlet airflow angle of the blade profile section upstream of each measuring point, draw the airflow angle after each scaled blade profile section; Each scaled blade section is copied at equal intervals of θ=360 / n to both circumferential boundaries, where θ is numerically equal to the angle between the upstream blades, and n is the number of upstream blades. Draw the measurement section line at S=γ×L after each row of scaled airfoil sections, where L is the axial distance between the measurement section and the upstream blade; Corresponding to the distribution position of the test instruments in the circumferential direction, at the reference position, draw the test instrument straight line along the axial direction, and repeat the test instrument straight line at equal intervals β to both sides of the circumferential boundary, where β is the angle between each test instrument; Mark the intersections of each measurement section line with the straight line of the testing instrument as measurement points.

2. The method for analyzing measurement results of aero-engine test instruments according to claim 1, characterized in that, Select a reference position on the measurement section, specifically the position directly above the measurement section.

3. The method for analyzing measurement results of aero-engine test instruments according to claim 1, characterized in that, The distance between the scaled airfoil sections of each row is equal to the radial distance between adjacent measuring points of each test instrument.

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