CN-116412958-B - Calibrating device of aeroengine axial force measurement structure

CN116412958BCN 116412958 BCN116412958 BCN 116412958BCN-116412958-B

Abstract

The invention belongs to the field of axial force measurement of thrust bearings of aeroengines, and particularly relates to a calibration device of an axial force measurement structure of an aeroengine, which comprises a supporting frame, a supporting platform, a pressurizing device, a pressure head, a pressure plate and a bearing platform; the invention can directly connect the axial force measuring structure component through the flange edge, and has the adjusting function of the position and the gesture of the test piece, thereby simplifying the operation steps of test personnel.

Inventors

Wei Songhan
Yang Feibing
GAO WEIQIANG
SHI XIAOJIANG
TENG GUANGRONG
TAN QINGJIANG
WEI JINGLAN

Assignees

中国航发四川燃气涡轮研究院

Dates

Publication Date: 20260505
Application Date: 20230208

Claims (4)

1. The utility model provides a calibration device of aeroengine axial force measurement structure which characterized in that includes: -a fixed frame (1), the fixed frame (1) comprising a supporting frame (1-1) and a supporting platform (1-2), the supporting platform (1-2) being mounted on the supporting frame (1-1) for carrying an axial force measuring structural assembly (5); The pressure device (2) is arranged on the supporting frame (1-1) and is opposite to the supporting platform (1-2) and used for generating a measuring load towards the supporting platform (1-2), the pressure device (2) is provided with a pressure head (2-3) and a pressure plate (2-4), the pressure head (2-3) is used for transmitting the measuring load, one end of the pressure head (2-3) towards the supporting platform (1-2) is a conical head, the axial direction of the conical head is parallel to or coincides with the load center shaft of an axial force measuring structure component (5) borne on the supporting platform (1-2), one end of the pressure plate (2-4) towards the pressure head (2-3) is provided with a conical hole, the outer diameter of the pressure plate (2-4) is the same as the upper end straight hole of the axial force measuring structure component (5), and when the axial force measuring structure component (5) is borne on the supporting platform (1-2) and the pressure plate (2-4) is coaxial with the axial force measuring structure component (5) at the axial force limiting end of the axial force measuring structure component (5); The bearing platform (4) is arranged on the supporting platform (1-2), the axial force measuring structure component (5) is arranged on the bearing platform (4) in an adjustable position, a plurality of adjusting jacking columns (3) are arranged between the bearing platform (4) and the supporting platform (1-2), one end, connected with the bearing platform (4), of each adjusting jacking column (3) is used for adjusting the position of the supporting platform (1-2) based on the expansion and contraction of the adjusting jacking columns, each adjusting jacking column (3) comprises a supporting sleeve (3-1), a ball stud (3-2), a spherical jacking block (3-3) and a compression nut (3-4), the supporting sleeve (3-1) is fixedly connected with the supporting platform (1-2), the ball stud (3-2) is connected with the supporting sleeve (3-1) based on the compression nut (3-4), the bottom surface of the spherical jacking block (3-3) is matched with the top surface (3-2) of the supporting platform (4) through the spherical surface of the supporting bolt (4); the pressure sensor is characterized in that the shape of the conical head is the same as that of the conical hole, the tail of the conical hole faces to the end part of the conical head, and a force sensor (2-2) is arranged between the pressure device (2) and the pressure head (2-3).
2. The calibration device of an aeroengine axial force measurement structure according to claim 1, wherein the bearing platform (4) comprises a tray (4-1), a flange mounting plate (4-2) and a plurality of screw slider assemblies (4-3), the bottom surface of the tray (4-1) is supported by each adjusting top column (3), a plurality of mounting holes for mounting the screw slider assemblies (4-3) are uniformly distributed on the circumference of the tray (4-1), the flange mounting plate (4-2) is used for fixing an axial force measurement structure assembly (5), the flange mounting plate (4-2) is slidably mounted on the tray (4-1), and planar sliding on the tray (4-1) is realized based on each screw slider assembly (4-3).
3. Calibration device for an aeroengine axial force measurement structure according to claim 2, wherein the screw slider assembly (4-3) comprises a screw (4-4), a slider (4-5), a rotary handle (4-6) and a spring (4-7), wherein the screw (4-4) is threadedly mounted in the mounting hole, the rotary handle (4-6) drives the screw (4-4) to rotate, the slider (4-5) is arranged at one end of the screw (4-4) close to the flange mounting plate (4-2), the slider (4-5) contacts the flange mounting plate (4-2), and the spring (4-7) is arranged between the screw (4-4) and the slider (4-5) for maintaining contact of the screw (4-4) with the slider (4-5).
4. Calibration device for an aeroengine axial force measurement structure according to claim 1, characterized in that the support frame (1-1) is further provided with a beam guide rail, the pressurizing device (2) is provided with a movable beam (2-1), the pressurizing device (2) is mounted on the beam guide rail based on the movable beam (2-1), and the beam guide rail is used for providing movement guidance of the movable beam (2-1).

Description

Calibrating device of aeroengine axial force measurement structure Technical Field The invention belongs to the field of axial force measurement of thrust bearings of aero-engines, and particularly relates to a calibration device of an axial force measurement structure of an aero-engine. Background In the development process of the aero-engine, axial force analysis of the thrust bearing is required to be completed, and reliable operation of the thrust bearing is ensured. The GJB 241-requires that "enough measurement devices be installed in place of the main bearings to measure the bearing load, and that the engine pressure balance system should provide enough unidirectional axial load to ensure that the bearings do not slip over all power conditions within the engine operating envelope". There are indirect and direct measurements of engine axial force. The traditional indirect measurement method is to indirectly judge the axial force by measuring the pressure of the unloading cavity of the compressor. This measurement method is simple but has poor accuracy. The common method for directly testing the axial force is to use an elastic ring type measuring structure (also called a force measuring ring) to be arranged in a bearing seat of an engine, and the bearing capacity of the elastic ring type measuring structure is reflected by the stress change of the measuring ring type structure. When the axial force of the engine is directly measured by using the force measuring ring structure, the measured physical quantity is the output of a strain gauge on the force to be measured, so that the corresponding relation between the strain and the force is required to be established before the test, namely the axial force measuring structure of the force measuring ring is calibrated. A typical calibration test is a compression test of an axial force measurement structure using a material tensile compression tester. As a general test device, the material tension-compression testing machine has a supporting surface which is mostly a plane, and the structure is easy to realize the calibration of single parts of the elastic force measuring ring. After the elastic force measuring ring is assembled to the engine axial force measuring structure, the mounting edge of the engine axial force measuring structure is a flange edge in the middle of the assembly, and the mounting edge cannot be directly placed on the supporting plane. Meanwhile, when the component (referred to as a test piece herein) of the axial force measuring structure is calibrated, the stress point is required to be positioned at the center of the component, and the force application direction is vertical to the stress plane, namely the position and the posture of the component need to be accurately positioned. The support plane of the material tension-compression testing machine is simple in structure, has no function of adjusting the position and the posture of a test piece, and can be manually adjusted by a tester, so that the operation experience of the tester has obvious influence on a test result. Disclosure of Invention In view of the above, the invention provides a calibration device of an aeroengine axial force measurement structure, which can be directly connected with an axial force measurement structure component through a flange edge, and has the function of adjusting the position and the posture of a test piece, thereby simplifying the operation steps of test personnel. In order to achieve the technical purpose, the invention adopts the following specific technical scheme: a calibration device for an aero-engine axial force measurement structure, comprising: A support frame; A support platform mounted on the support frame for carrying the axial force measurement structure; a pressurizing device mounted on the support frame, disposed opposite the support platform, for generating a measured load toward the support platform; The pressure head is arranged on the pressurizing device and used for transmitting the measuring load, and one end of the pressure head, which faces the supporting platform, is a conical head; When the axial force measuring structure is borne on the supporting platform and the pressing plate is limited in the straight hole at the upper end of the axial force measuring structure, the conical hole is coaxial with a load center shaft of the axial force measuring structure; the bearing platform is arranged on the supporting platform; the axial force measuring structure is arranged on the bearing platform in an adjustable pose; Wherein the shape of the conical head is the same as that of the conical hole; the tail part of the conical hole faces to the end part of the conical head, and a force sensor is arranged between the pressurizing device and the pressure head. Further, a plurality of adjusting jacking columns are arranged between the bearing platform and the supporting platform, and each adjusting jacking column is arranged at one en