An interference inspection method for assembly of adjustable blades of aircraft engines

Abstract

The present application belongs to the technical field of interference inspection for adjustable blade assembly of aircraft engines, and specifically relates to an interference inspection method for adjustable blade assembly of aircraft engines, which is an interference inspection method for adjustable blade assembly based on two-dimensional drawing. For three positions where interference is prone to occur during the assembly of adjustable blades, the meridian projection of the largest part contour is used as the inspection graphic, and several typical positions in the assembly movement process of the adjustable blades are inspected respectively. When no interference occurs at the several typical positions and the adjustable blades can smoothly reach the theoretical assembly position, it can be considered that the adjustable blades can be assembled smoothly, and there is no need to build a complex three-dimensional model for motion simulation. The method is convenient and fast, and can meet the needs of rapid iteration of aircraft engine design solutions.

Description

Technical Field

[0001] The present application belongs to the technical field of interference inspection for adjustable blade assembly of aircraft engines, and in particular relates to an interference inspection method for adjustable blade assembly of aircraft engines. Background Art

[0002] In order to adjust the inlet airflow of the aircraft engine, the stator blades in the air intake casing are designed to be adjustable blades. The upper journal of the adjustable blade is installed in the mounting hole of the air intake casing, and the lower journal is installed in the mounting hole of the stator inner ring in the air intake casing. It can rotate around its own axis, but the axis of the adjustable blade is not perpendicular to the axis of the aircraft engine. There is an obvious transition section between the upper journal and the blade body. The transition section is inclined forward, and the trailing edge of the straightening support plate in the air intake casing is an inclined surface at the corresponding position. At the same time, the chord length of the adjustable blade is relatively wide. During the assembly process, the transition section between the blade body of the adjustable blade and the upper journal is prone to interfere with the inclined surface of the trailing edge of the straightening support plate (the first interference position), the turning point between the rear side of the upper journal of the adjustable blade and the blade body is prone to interfere with the mounting hole of the air intake casing (the second interference position), and the upper end of the trailing edge of the adjustable blade is prone to interfere with the air intake casing (the third interference position). Figure 1 shown.

[0003] During the assembly of adjustable blades in the air intake casing of an aircraft engine, if serious interference occurs at the first interference position, the second interference position, and the third interference position, the assembly cannot be completed. Therefore, interference checking is required during the design of the scheme.

[0004] Currently, the interference check of the adjustable blade assembly process in the air intake casing of an aircraft engine is mainly carried out by 3D modeling + motion simulation. This technical solution can truly restore the assembly process of the adjustable blades in the air intake casing of an aircraft engine and reliably realize interference check. However, 3D modeling and its motion simulation are time-consuming, labor-intensive, inefficient, and have a long cycle, making it difficult to adapt to the needs of rapid iteration of aircraft engine design solutions.

[0005] This application is proposed in view of the above-mentioned technical defects.

[0006] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention

[0007] The purpose of the present application is to provide an aircraft engine adjustable blade assembly interference inspection method to overcome or alleviate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] An aircraft engine adjustable blade assembly interference inspection method, comprising:

[0010] Draw the largest plane figure of the air intake casing, rectifier support plate, and adjustable blade meridian projection;

[0011] In plane graphics:

[0012] Insert the upper journal portion of the adjustable blade into the mounting hole of the air intake casing, adjust the axis of the adjustable blade to be parallel to the inclined surface of the trailing edge of the straightening support plate, move the blade body of the adjustable blade to the transition section at the upper journal and the inclined surface of the trailing edge of the straightening support plate, the contact position is point A, and move the upper end of the trailing edge of the adjustable blade to contact the air intake casing, the contact position is point B;

[0013] Rotate the adjustable blade around point A so that the rear side of the upper journal of the adjustable blade contacts the mounting hole, and the contact position is C;

[0014] Move the adjustable blade upward along its axis so that the turning point between the rear side of the upper journal of the adjustable blade and the blade body contacts the air intake casing, and the contact position is point D;

[0015] Move the adjustable blade vertically along its axis toward the direction of the rectifying support plate, so that the blade body of the adjustable blade contacts the transition section at the upper journal with the inclined surface of the trailing edge of the rectifying support plate, and the contact position is point E;

[0016] The adjustable blade is rotated around point E so that the axis of the adjustable blade reaches a theoretical angle, and the adjustable blade is moved upward along its axis so that the adjustable blade reaches a theoretical assembly position.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine adjustable blade assembly interference inspection method, the contours of the air intake casing and the rectifying support plate on the adjustable blade assembly route are compensated in a plane figure.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft engine adjustable blade assembly interference inspection method, the contours of the air intake casing and the straightening support plate on the adjustable blade assembly route are compensated in a plane figure, specifically by offsetting 1 mm in the opposite direction of material removal.

[0019] This application has at least the following beneficial technical effects:

[0020] Provided is an interference inspection method for assembly of adjustable blades of an aero-engine. The method is based on two-dimensional drawing and aims at three positions where interference is prone to occur during the assembly of the adjustable blades. The meridian projection of the largest part outline is used as the inspection figure to inspect several typical positions during the assembly movement of the adjustable blades. If no interference occurs at the several typical positions and the adjustable blades can smoothly reach the theoretical assembly position, it can be considered that the adjustable blades can be assembled smoothly. There is no need to construct a complex three-dimensional model for motion simulation. The method is convenient and fast and can meet the needs of rapid iteration of aero-engine design solutions. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the positions where interference is likely to occur during the assembly of adjustable blades in the air intake casing of an aircraft engine;

[0022] Figure 2-Figure 6 It is a process schematic diagram of an interference inspection method for adjustable blade assembly of an aircraft engine.

[0023] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0024] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0025] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0026] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0027] The following is combined with Figures 1 to 6 This application is described in further detail.

[0028] An aircraft engine adjustable blade assembly interference inspection method, comprising:

[0029] Draw the largest plane figure of the air intake casing, rectifier support plate, and adjustable blade meridian projection;

[0030] In plane graphics:

[0031] Insert the upper journal part of the adjustable blade into the mounting hole of the air intake casing, adjust the axis of the adjustable blade to be parallel to the inclined surface of the trailing edge of the straightening support plate, move the adjustable blade so that the blade body and the transition section at the upper journal contact the inclined surface of the trailing edge of the straightening support plate, and the contact position is point A, and move the upper end of the trailing edge of the adjustable blade to contact the air intake casing, and the contact position is point B. Figure 2 As shown;

[0032] Rotate the adjustable blade around point A so that the rear side of the upper journal of the adjustable blade contacts the mounting hole. The contact position is C. Figure 3 As shown;

[0033] Move the adjustable blade upward along its axis so that the turning point between the rear side of the upper journal of the adjustable blade and the blade body contacts the intake casing. The contact position is point D. Figure 4 As shown;

[0034] Move the adjustable blade along the vertical direction of its axis toward the rectifying support plate, so that the blade body of the adjustable blade contacts the transition section at the upper journal with the inclined surface of the trailing edge of the rectifying support plate. The contact position is point E. Figure 5 As shown;

[0035] The adjustable blade is rotated around point E so that the axis of the adjustable blade reaches the theoretical angle, and the adjustable blade is moved upward along its axis so that the adjustable blade reaches the theoretical assembly position, such as Figure 6 shown.

[0036] As for the interference inspection method for assembly of adjustable blades of aircraft engines disclosed in the above-mentioned embodiment, it can be understood by technicians in the field that it is an interference inspection method for assembly of adjustable blades based on two-dimensional drawing. For the three positions where interference is prone to occur during the assembly of adjustable blades, the meridian plane projection with the largest part contour is used as the inspection graphic, and several typical positions during the assembly movement of the adjustable blades are inspected respectively. When no interference occurs at these typical positions and the adjustable blades can smoothly reach the theoretical assembly position, it can be considered that the adjustable blades can be assembled smoothly. There is no need to build a complex three-dimensional model for motion simulation. It is convenient and fast, and can meet the needs of rapid iteration of aircraft engine design solutions.

[0037] In some optional embodiments, in the above-mentioned aircraft engine adjustable blade assembly interference inspection method, the influence of factors such as dimensional tolerance during the processing process is taken into account, and the contours of the air intake casing and the straightening support plate on the adjustable blade assembly route are compensated in the plane figure.

[0038] In some optional embodiments, in the above-mentioned aircraft engine adjustable blade assembly interference inspection method, the contours of the air intake casing and the straightening support plate on the adjustable blade assembly route are compensated in the plane figure, specifically by offsetting 1 mm in the opposite direction of material removal.

[0039] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0040] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A method for checking interference of adjustable blade assembly of an aircraft engine, characterized in that: include: Draw the largest plane figure of the air intake casing, rectifier support plate, and adjustable blade meridian projection; In plane graphics: Insert the upper journal portion of the adjustable blade into the mounting hole of the air intake casing, adjust the axis of the adjustable blade to be parallel to the inclined surface of the trailing edge of the straightening support plate, move the blade body of the adjustable blade to the transition section at the upper journal and the inclined surface of the trailing edge of the straightening support plate, the contact position is point A, and move the upper end of the trailing edge of the adjustable blade to contact the air intake casing, the contact position is point B; Rotate the adjustable blade around point A so that the rear side of the upper journal of the adjustable blade contacts the mounting hole, and the contact position is C; Move the adjustable blade upward along its axis so that the turning point between the rear side of the upper journal of the adjustable blade and the blade body contacts the air intake casing, and the contact position is point D; Move the adjustable blade vertically along its axis toward the direction of the rectifying support plate, so that the blade body of the adjustable blade contacts the transition section at the upper journal with the inclined surface of the trailing edge of the rectifying support plate, and the contact position is point E; The adjustable blade is rotated around point E so that the axis of the adjustable blade reaches a theoretical angle, and the adjustable blade is moved upward along its axis so that the adjustable blade reaches a theoretical assembly position.

2. The method for checking the interference of adjustable blades of an aircraft engine according to claim 1, characterized in that: In the plane figure, the contours of the air intake casing and the rectifying support plate on the adjustable blade assembly route are compensated.

3. The method for checking the interference of adjustable blades of an aircraft engine according to claim 1, characterized in that: In the plane figure, the contours of the air intake casing and the rectifier support plate on the adjustable blade assembly route are compensated, specifically by offsetting them 1mm in the opposite direction of material removal.

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