CN117450095A - Method for measuring rotation angle of adjustable flow blade of aero-engine compressor - Google Patents

Method for measuring rotation angle of adjustable flow blade of aero-engine compressor Download PDF

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Publication number
CN117450095A
CN117450095A CN202311408807.4A CN202311408807A CN117450095A CN 117450095 A CN117450095 A CN 117450095A CN 202311408807 A CN202311408807 A CN 202311408807A CN 117450095 A CN117450095 A CN 117450095A
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CN
China
Prior art keywords
measuring
engine
dial indicator
rocker arm
actuating ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202311408807.4A
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Chinese (zh)
Inventor
张国俊
秦家禄
安富权
孙浩
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AECC Guizhou Liyang Aviation Power Co Ltd
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AECC Guizhou Liyang Aviation Power Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by AECC Guizhou Liyang Aviation Power Co Ltd filed Critical AECC Guizhou Liyang Aviation Power Co Ltd
Priority to CN202311408807.4A priority Critical patent/CN117450095A/en
Publication of CN117450095A publication Critical patent/CN117450095A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/003—Measuring of motor parts

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A method of measuring the rotational angle of an adjustable flow vane of an aircraft engine compressor, comprising the steps of: s1, determining a measuring surface: selecting the right end face A of the actuating ring as a measuring surface; s2, setting a measuring tool: selecting a dial indicator as a measuring tool, so that a measuring head of the dial indicator abuts against the right end face A of the actuating ring; the axis of the dial indicator measuring head is vertical to the right end face A of the actuating ring; s3, measuring displacement of a measuring surface in the axial direction of the engine: when the rocker arm is parallel to the axis B of the engine, the rocker arm is positioned at a position of 0 degrees along the direction of the axis B of the engine, and the dial indicator is zeroed; when the rectifying blade rotates to an angle to be checked, reading out and recording the displacement value H from the dial indicator; s4, converting the displacement value into an angle value according to the functional relation. According to the invention, the measured angle value is converted into the measured jump value by utilizing the geometric relationship, and the measurement can be performed by adopting the dial indicator, so that the operability, the working efficiency and the measurement accuracy are greatly improved.

Description

Method for measuring rotation angle of adjustable flow blade of aero-engine compressor
Technical Field
The invention relates to the technical field of aero-engine assembly, in particular to a method for measuring the rotation angle of adjustable flow blades of an aero-engine compressor.
Background
In order to adapt to the demands of various working conditions, the working stability margin of the air compressor is enlarged, and the front stages of rectifiers of the air compressor of the aeroengine are generally designed into a structure with blades capable of being rotationally adjusted along the axis of the front stages of rectifiers, so that the air demand of a main combustion chamber under different working conditions is matched. In general, a single-stage adjustable rectifier mainly comprises a stator casing, rectifying blades with rocker arms, an actuating ring, a connecting pin and other parts. The rectifying vane with the rocker arm is fixedly connected with the rocker arm with the knuckle bearing by the rectifying vane, as shown in figure 1. The rectifying vane with the rocker arm is movably connected with the actuating ring of the rectifier through a joint bearing on the rocker arm, as shown in figure 2. The rectifier blades are uniformly distributed on the stator casing along the circumference, and when the stator casing works, all the rectifier blades simultaneously rotate along the respective axes of the blades under the cooperation of the actuating rings, so that the flow area formed by the rectifier blades of each stage is changed, and the air flow of the inlet of the compressor is controlled.
When the aeroengine works, the opening and closing angle of the rectifying blade influences the air flow of the main combustion chamber, so that the working performance of the engine is influenced. Therefore, when the aeroengine is assembled, the design gives clear numerical requirements on the rotation angle of the rectifying blade of the aeroengine, and when the aeroengine is assembled, the rotation angle of the rectifying blade needs to be measured and checked, and the rotation angle of the rectifying blade is the same as the rotation angle of the rocker arm because the rectifying blade is fixedly connected with the rocker arm.
However, due to the design requirement of the aero-engine and the structural limitation of the compressor rectifier, the vertex of the rotation angle of the rectifying blade and two edges of the angle are difficult to capture when the rotation angle of the rectifying blade is actually measured, so that the measurement is difficult to conveniently and accurately carry out. Currently, when measuring the rotation angle of an adjustable flow blade of an aero-engine compressor, a protractor or a special angle measurement tool is generally adopted. However, because the adjustable rectifier of the aero-engine compressor is limited in structure and small in operation space, the angle vertex and the angle edge are difficult to determine during angle measurement, so that the method for directly measuring the angle is extremely poor in operability, the special tool is difficult to design, the tool structure is complex, the use is inconvenient, and the measurement error is larger. And the measured value is greatly influenced by human factors.
In the prior art, as disclosed in patent application publication No. CN111272132a, an adjustable flow vane rotation angle detection device and detection method are disclosed, and the rotation angle of a single adjustable flow vane is measured by adopting a digital display angle measuring instrument and other structures, but the following disadvantages are included:
1) The measuring device is more complicated, and structural parts are many, and the installation is dismantled comparatively consuming time during the measurement, and the operability is not enough.
2) The measuring device is limited by the structure of the engine and has a narrow application range, threads extending from the long shaft of the rectifying blade are required to be connected with the measuring device, but most types of engine rectifying blades have no extending thread structure, especially for the design of the medium and small aeroengine for reducing weight, the rocker arm and the blade are of a pin locking and non-outcropping structure, and under the condition, the measuring device mentioned in the patent cannot be used.
3) The measuring device is large in appearance, needs to be fixed on an engine, is special in fixing mode, and is difficult to use in a narrow space.
Disclosure of Invention
The invention mainly aims to provide a method for measuring the rotation angle of adjustable flow blades of an aero-engine compressor, and aims to solve the technical problems.
In order to achieve the above purpose, the present invention provides a method for measuring the rotation angle of adjustable flow blades of an aero-engine compressor, comprising the following steps:
s1, determining a measuring surface: selecting the right end face A of the actuating ring as a measuring surface;
s2, setting a measuring tool: selecting a dial indicator as a measuring tool, so that a measuring head of the dial indicator abuts against the right end face A of the actuating ring; the axis of the dial indicator measuring head is vertical to the right end face A of the actuating ring;
s3, measuring displacement of a measuring surface in the axial direction of the engine: when the rocker arm is parallel to the axis B of the engine, the rocker arm is positioned at a position of 0 degrees along the direction of the axis B of the engine, and the dial indicator is zeroed; when the rectifying blade rotates to an angle to be checked, reading out and recording the displacement value H from the dial indicator;
s4, converting the displacement value into an angle value according to the functional relation.
Preferably, in step S4, the functional relationship is:
wherein: alpha is the rotation angle of the rocker arm; h measuring the displacement of the surface on the engine axis; and R is the length from the center of a hole on the rocker arm, which is connected with the rectifying blade, to the center of a joint bearing hole on the rocker arm, which is connected with the actuating ring.
Preferably, in step S2, a dial gauge or a lever gauge may be selected as the measuring tool.
Preferably, in step S1, the measuring surface may also be a right end surface C of an extension plate fixed to the actuation ring; the right end face C is perpendicular to the engine axis B.
Preferably, in step S3, when the dial indicator is zeroed, the actuating ring is rocked to rotate the rectifying blade, and the readings of the percentage are observed, and when the dial indicator measuring head is compressed to cause the extreme value of the dial indicator, the position of the actuating ring of the rectifier is maintained, and the dial indicator is zeroed.
Due to the adoption of the technical scheme, the invention has the following beneficial effects:
according to the invention, the measured angle value is converted into the measured runout value by utilizing the geometric relation, and the adjustable flow blade rotation angle measurement during the assembly of the aero-engine is realized by utilizing only a conventional assembly tool, so that the operability, the working efficiency and the measurement accuracy are greatly improved, and the problems of inaccurate measurement of the adjustable flow blade rotation angle of the aero-engine and high design difficulty of a special tool are solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a single stage adjustable rectifier with rocker arms in the rectifier blades;
FIG. 2 is a diagram of the connection of the rectifying blades, rocker arms, and actuating rings in a single-stage adjustable rectifier;
FIG. 3 is a schematic diagram of the measuring method of the present invention;
FIG. 4 is a schematic diagram of an angle-displacement relationship geometric model in the measurement method of the present invention.
Reference numerals illustrate: 1. a dial indicator; 2. actuating the ring; 3. a pin; 4. a rocker arm; 5. a rectifying vane; 6. a stator case; 7. a knuckle bearing; 8. an extension plate.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Referring to fig. 1 and 2, in the conventional engine structure, the single-stage adjustable flow device mainly includes a stator casing 6, a rectifying vane 5 with a rocker arm 4, an actuating ring 2, a pin 3, and other parts. The rectifying vane 5 is provided with an outer journal and an inner journal, the rectifying vane 5 is uniformly distributed on the stator casing 6 along the circumference, the outer journal of the rectifying vane 5 is in running fit with the stator casing 6, one end of the rocker arm 4 is sleeved on the outer journal of the rectifying vane 5 and is inserted with an anti-rotation pin 9, namely, the outer journal of the rectifying vane 5 and the rocker arm 4 form fixed connection, and the position of the outer journal cannot rotate. The end of the rocker arm 4 remote from the outer journal is provided with a knuckle bearing 7 and this end is inserted into the actuating ring 2 and connected by means of a pin 3. By utilizing the cooperation structure of the knuckle bearing 7 and the pin 3, a rotational connection is formed between the rocker arm 4 and the actuating ring 2. The actuating ring 2 rotates about the engine axis B and simultaneously drives the fairing blades 5 about their axis D. When the single-stage adjustable rectifier works, all the rectifying blades 5 simultaneously rotate along the respective axes D of the blades under the cooperation of the actuating ring 2, and the flow area formed by the rectifying blades 5 of each stage is changed so as to control the air flow of the inlet of the compressor.
Based on the single-stage adjustable flow device, the rotation angle of the rectifying vane 5 is the rotation angle of the rocker arm 4, for a point with a certain radius on the rocker arm 4, when the rocker arm 4 rotates, the rotation angle of the point corresponds to the displacement generated by the projection of the point on the axis B of the engine on two sides of the axis one by one respectively, and a certain functional relation exists. Using this functional relationship, the rotation angle measurement can be converted into a displacement measurement that is projected onto the axis. The method and the device greatly avoid the adverse factors brought by the measurement of the rotation angle of the rectifying blade of the aero-engine, thereby conveniently, rapidly and accurately measuring the rotation angle of the rectifying blade of the aero-engine.
Referring to fig. 3 and 4, the present embodiment provides a method for measuring the rotation angle of an adjustable flow vane of an aero-engine compressor, which includes the following steps:
s1, determining a measuring surface: the right end face a of the actuation ring 2 is selected as the measurement face. The measurement surface has certain requirements on flatness and perpendicularity with the axis B of the engine, the specific requirements are determined according to measurement accuracy, and for a common aeroengine, the right end face A of the actuating ring 2 can meet the requirements on flatness and perpendicularity;
s2, setting a measuring tool: selecting the dial indicator 1 as a measuring tool, so that a measuring head of the dial indicator 1 abuts against the right end face A of the actuating ring 2; the axis of the measuring head of the dial indicator 1 is vertical to the right end face A of the actuating ring 2;
s3, measuring displacement of a measuring surface in the axial direction of the engine: when the rocker arm 4 is parallel to the engine axis B, the rocker arm is positioned at a position of 0 degrees along the direction of the engine axis B, and the dial indicator 1 is zeroed; when the rectifying vane 5 rotates to an angle to be inspected, the actuating ring 2 moves under the drive of the rocker arm 4, displacement is generated in the direction of the axis B of the engine, and the displacement value H is read and recorded from the dial indicator 1;
s4, converting the displacement value into an angle value according to the functional relation.
Referring to fig. 4, a schematic diagram of an angle-displacement relation geometric model in the measuring method is shown, and specific functional relations are as follows:
wherein: alpha is the rotation angle of the rocker arm 4; h measuring the displacement of the surface on the engine axis; r is the length from the center of a hole on the rocker arm 4 for connecting the rectifying vane 5 to the center of a knuckle bearing hole 7 on the rocker arm 4 for connecting the actuating ring 2; the O point represents a point where projections of the axis D of the rectifying vane 5 are converged. The vertical direction of R can be used for searching the design drawing of the rocker arm 4 on a specific engine to obtain an accurate value, so that measurement errors are avoided.
The shape and size of the rectifying blades 5, the length and structure of the rocker arms 4, the shape of the actuating ring 2 and the like of different aeroengines may be different, but the mechanical transmission structure and the geometric elements formed by the same can be simplified and abstracted into the geometric model of fig. 4.
In this embodiment, according to the measurement accuracy requirement, in step S2, a dial gauge or lever gauge with appropriate accuracy may be selected as the measuring tool.
As shown in fig. 3, in the present embodiment, in step S1, the measurement surface may also be the right end surface C of the extension plate 8 fixed to the actuation ring 2; the right end face C is perpendicular to the engine axis B. The extension plate 8 can be processed independently, so that the flatness and roughness of the right end face C of the extension plate can be guaranteed.
In step S3, when the dial indicator 1 is zeroed, the actuating ring 2 is rocked to rotate the rectifying blade 5, and the readings of the dial indicator 1 are observed, and when the dial indicator 1 measuring head is compressed to cause the extreme value of the dial indicator 1, the position of the actuating ring 2 of the rectifier is maintained, and the dial indicator 1 is zeroed.
In step S4, the rotation angle of the rectifying vane 5 is converted. The rotation angle α is converted from the geometric relationship between the rotation angle α of the rectifying vane 5 and the axial displacement H of the actuation ring 2. For the determined model, a conversion table may be prepared to improve the working efficiency.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather, the equivalent structural changes made by the description of the present invention and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the invention.

Claims (5)

1. A method of measuring the rotational angle of an adjustable flow vane of an aircraft engine compressor, comprising the steps of:
s1, determining a measuring surface: selecting the right end face A of the actuating ring (2) as a measuring surface;
s2, setting a measuring tool: selecting a dial indicator (1) as a measuring tool, so that a measuring head of the dial indicator (1) is abutted against the right end face A of the actuating ring (2); the axis of the measuring head of the dial indicator (1) is vertical to the right end face A of the actuating ring (2);
s3, measuring displacement of a measuring surface in the axial direction of the engine: when the rocker arm (4) is parallel to the axis B of the engine, the rocker arm is positioned at a position of 0 degrees along the direction of the axis B of the engine, and the dial indicator (1) is zeroed; when the rectifying blade (5) rotates to an angle to be checked, reading and recording the displacement value H from the dial indicator (1);
s4, converting the displacement value into an angle value according to the functional relation.
2. The method for measuring the rotational angle of an adjustable flow vane of an aircraft engine compressor as set forth in claim 1, wherein in step S4, the functional relationship is:
wherein: alpha is the rotation angle of the rocker arm (4); h measuring the displacement of the surface on the engine axis; r is the length from the center of a hole on the rocker arm (4) for connecting the rectifying blade (5) to the center of a knuckle bearing hole (7) on the rocker arm (4) for connecting the actuating ring (2).
3. The method of claim 1, wherein in step S2, a dial gauge or a lever gauge is selected as the measuring tool.
4. A method for measuring the rotation angle of adjustable flow blades of an aero-engine compressor according to claim 1, wherein in step S1 the measuring surface is also the right end face C of an extension plate (8) fixed to the actuation ring (2); the right end face C is perpendicular to the engine axis B.
5. A method of measuring the rotation angle of adjustable flow vanes of an aeroengine compressor according to claim 1, wherein in step S3, the actuating ring (2) is rocked to rotate the commutating vanes (5) and observe the readings of the percentage table (1), and when the measuring head of the percentage table (1) is compressed to cause the extreme value of the percentage table (1), the position of the actuating ring (2) of the commutator is maintained and the percentage table (1) is zeroed.
CN202311408807.4A 2023-10-27 2023-10-27 Method for measuring rotation angle of adjustable flow blade of aero-engine compressor Pending CN117450095A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202311408807.4A CN117450095A (en) 2023-10-27 2023-10-27 Method for measuring rotation angle of adjustable flow blade of aero-engine compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202311408807.4A CN117450095A (en) 2023-10-27 2023-10-27 Method for measuring rotation angle of adjustable flow blade of aero-engine compressor

Publications (1)

Publication Number Publication Date
CN117450095A true CN117450095A (en) 2024-01-26

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ID=89579376

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202311408807.4A Pending CN117450095A (en) 2023-10-27 2023-10-27 Method for measuring rotation angle of adjustable flow blade of aero-engine compressor

Country Status (1)

Country Link
CN (1) CN117450095A (en)

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