Bidirectional axial force loading device of aero-engine rotor tester

Abstract

The invention discloses a bidirectional axial force loading device for an aero-engine rotor tester. The bidirectional axial force loading device comprises an electronic propeller, a first force applying assembly and a second force applying assembly, the first stress application assembly comprises a first loading cylinder, a fixing bolt, a locking nut and a stress application circular ring; the second stress application assembly comprises a second loading cylinder, a first angular contact ball bearing, a second angular contact ball bearing and an inner fixing cylinder. According to the invention, bidirectional axial force loading with different amplitudes and frequencies can be completed, the rub-impact force can be measured and controlled in real time in the loading process, additional bending moment loading is avoided, the operation is simple, and the measurement is accurate.

Description

Technical Field

[0001] The invention relates to the field of bidirectional axial force loading of an aero-engine rotor tester, in particular to a bidirectional axial force loading device of an aero-engine rotor tester. Background Art

[0002] Aircraft engines are subject to complex axial loads during operation, including aerodynamic thrust, thermal expansion, and inertial forces. Aircraft engine simulators accurately replicate these load environments through axial force application devices to verify the dynamic response and structural strength of rotors under extreme conditions. This represents a key technological upgrade, providing comprehensive data support for rotor system design verification, performance optimization, and reliability assessment. The axial force application and measurement device dynamically replicates the mechanical effects of axial loads on the rotor system. For example, by precisely controlling the magnitude and variation of the axial force, the axial displacement, bearing load distribution, seal clearance changes, and component vibration response under load can be monitored in real time. This helps engineers optimize bearing selection and support structure design (such as thrust and radial bearing matching parameters and bearing lubrication methods), avoiding the risk of bearing overheating, wear, lifespan reduction, or blade-casing friction caused by axial movement due to axial load miscalculation. Furthermore, by combining axial displacement and seal leakage testing, the sealing efficiency and reliability of key structures such as tip clearance and labyrinth seals can be accurately assessed under varying loads, balancing aerodynamic performance and structural safety. Through coupled monitoring of axial force and vibration signals, potential risks such as critical speed offset and bending-axial vibration coupling can be effectively identified, thereby improving the vibration stability of the entire machine. From the perspective of safety and durability, the device can simulate extreme working conditions caused by excessive or unbalanced axial force, and expose design problems such as insufficient thrust bearing capacity and axial positioning structure stiffness defects in advance. It also evaluates the stress cycle characteristics of components such as shafts and bearing seats through dynamic load fatigue testing, providing a basis for material selection and structural reinforcement, and ensuring that the engine meets long-life design requirements. Therefore, it is of great significance to study the axial force loading of aircraft engine rotor testers. However, existing axial force loading devices generally have one or more of the following deficiencies: bidirectional axial force loading is impossible, large axial load loading is impossible, additional bending moment loading cannot be avoided during axial force loading, and the magnitude of the loaded axial force cannot be accurately controlled.

[0003] Therefore, how to construct an axial force loading device that can load large axial forces in both directions, avoid additional bending moment loading and accurately control the magnitude of the axial force has become a technical problem that technical personnel in this field urgently need to solve. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a bidirectional axial force loading device for an aero-engine rotor tester in view of the defects involved in the background technology.

[0005] The present invention adopts the following technical solutions to solve the above technical problems: A bidirectional axial force loading device for an aero-engine rotor tester, comprising an electronic pusher, a first force-adding assembly, and a second force-adding assembly; The first force-adding assembly comprises a first loading cylinder, a fixing bolt, a locking nut and a force-adding ring; The fixing bolt comprises a nut and a stud; one end of the stud is coaxially and vertically fixed to the nut, and the other end of the stud is provided with an external thread for matching with the locking nut on the side wall, and the outer wall of the stud between the external thread and the nut is smooth; The force-adding ring is a hollow cylinder with openings at both ends; The first loading cylinder is a hollow cylinder with one end open and the other end closed, and a first through hole and a second through hole are symmetrically provided on its side wall for matching with the stud of the fixing bolt, and a first through groove and a second through groove are symmetrically provided on its side wall and parallel to its axis; The fixing bolt passes through the first through hole, the force ring, and the second through hole in sequence and is threadedly connected to the fixing bolt, so that the first loading cylinder, the fixing bolt, and the lock nut are fixed to each other, and the force ring and the stud of the fixing bolt are loosely matched; the two sides of the force ring extend out of the first loading cylinder through the first through slot and the second through slot respectively; The electronic pusher is fixed to the outside, and its output shaft is connected to the outer wall of the force ring. The output shaft of the electronic pusher is coaxial with the first loading cylinder, and the axis of the output shaft of the electronic pusher passes through the center of the force ring. The second force-applying assembly comprises a second loading cylinder, a first angular contact ball bearing, a second angular contact ball bearing, and an inner fixing cylinder; The second loading cylinder is a hollow cylinder with one end open and the other end closed, and the closed end is coaxially fixedly connected to the closed end of the first loading cylinder; The inner fixing cylinder is a hollow cylinder with one end open and the other end provided with a through hole. The inner fixing cylinder is sleeved on the end of the aircraft engine rotor tester and is coaxially fixedly connected to the end of the aircraft engine rotor tester. The first and second angular contact ball bearings have the same structure and are arranged back-to-back, i.e., their wide end faces abut each other. The inner rings of the first and second angular contact ball bearings are coaxially fixedly connected to the inner fixed cylinder, and the outer rings are coaxially fixedly connected to the second loading cylinder, so that the second loading cylinder and the end of the aircraft engine rotor tester can rotate freely in the circumferential direction and are fixed in the radial direction. The electronic pusher is used to apply radial pressure or tension to the aircraft engine rotor tester through the first force-adding component and the second force-adding component.

[0006] As a further optimization solution of the bidirectional axial force loading device of the aircraft engine rotor tester of the present invention, the electronic pusher adopts an electronic pusher provided with a force sensor.

[0007] As a further optimized solution of the bidirectional axial force loading device of the aircraft engine rotor tester of the present invention, the second loading cylinder includes a base, a connecting cylinder and a retaining ring; The base is a hollow cylinder with one end open and the other end closed; The connecting tube is a hollow cylinder with two ends open, the outer diameter of which is equal to the outer diameter of the base and the inner diameter of which is larger than the inner diameter of the base; The retaining ring is annular and is arranged at one end of the connecting tube. The outer wall is coaxially fixed to the inner wall of the connecting tube, and the inner diameter of the retaining ring is equal to the inner diameter of the base. The end of the connecting tube away from the retaining ring and the open end of the base are coaxially fixedly connected by bolts, so that the outer ring of the first angular contact ball bearing and the retaining ring abut against each other, and the outer ring of the second angular contact ball bearing and the open end of the base abut against each other; The inner ring of the first angular contact ball bearing abuts against the step at the end of the aircraft engine rotor tester, and the inner ring of the second angular contact ball bearing abuts against the open end of the inner fixed cylinder.

[0008] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects: 1. The output shaft of the electronic actuator can rotate horizontally around the fixing bolt, avoiding the loading of additional bending moment; 2. The electronic actuator is equipped with a force sensor, which can provide feedback on the axial force being loaded at any time, facilitating quantitative loading to control the degree of axial force loading; 3. It can carry out bidirectional large-load axial force loading and complete bidirectional axial force loading of different amplitudes and frequencies. The device is easy to operate and has accurate measurement. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention; Figure 2 It is a schematic cross-sectional structural diagram of the present invention.

[0010] In the figure, 1-first loading cylinder, 2-fixing bolt, 3-force ring, 4-locking nut, 5-electronic pusher, 6-second force assembly, 7-base of second loading cylinder, 8-connecting cylinder of second loading cylinder, 9-retaining ring of second loading cylinder, 10-first angular contact ball bearing, 11-second angular contact ball bearing, 12-inner fixing cylinder. DETAILED DESCRIPTION

[0011] The technical solution of the present invention is further described in detail below with reference to the accompanying drawings: The present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0012] like Figure 1 、 Figure 2 As shown, the present invention discloses a bidirectional axial force loading device for an aero-engine rotor tester, comprising an electronic pusher, a first force-adding assembly and a second force-adding assembly; The first force-adding assembly comprises a first loading cylinder, a fixing bolt, a locking nut and a force-adding ring; The fixing bolt comprises a nut and a stud; one end of the stud is coaxially and vertically fixed to the nut, and the other end of the stud is provided with an external thread for matching with the locking nut on the side wall, and the outer wall of the stud between the external thread and the nut is smooth; The force-adding ring is a hollow cylinder with openings at both ends; The first loading cylinder is a hollow cylinder with one end open and the other end closed, and a first through hole and a second through hole are symmetrically provided on its side wall for matching with the stud of the fixing bolt, and a first through groove and a second through groove are symmetrically provided on its side wall and parallel to its axis; The fixing bolt passes through the first through hole, the force ring, and the second through hole in sequence and is threadedly connected to the fixing bolt, so that the first loading cylinder, the fixing bolt, and the lock nut are fixed to each other, and the force ring and the stud of the fixing bolt are loosely matched; the two sides of the force ring extend out of the first loading cylinder through the first through slot and the second through slot respectively; The electronic pusher is fixed to the outside, and its output shaft is connected to the outer wall of the force ring. The output shaft of the electronic pusher is coaxial with the first loading cylinder, and the axis of the output shaft of the electronic pusher passes through the center of the force ring. The second force-applying assembly comprises a second loading cylinder, a first angular contact ball bearing, a second angular contact ball bearing, and an inner fixing cylinder; The second loading cylinder is a hollow cylinder with one end open and the other end closed, and the closed end is coaxially fixedly connected to the closed end of the first loading cylinder; The inner fixing cylinder is a hollow cylinder with one end open and the other end provided with a through hole. The inner fixing cylinder is sleeved on the end of the aircraft engine rotor tester and is coaxially fixedly connected to the end of the aircraft engine rotor tester. The first and second angular contact ball bearings have the same structure and are arranged back-to-back, i.e., their wide end faces abut each other. The inner rings of the first and second angular contact ball bearings are coaxially fixedly connected to the inner fixed cylinder, and the outer rings are coaxially fixedly connected to the second loading cylinder, so that the second loading cylinder and the end of the aircraft engine rotor tester can rotate freely in the circumferential direction and are fixed in the radial direction. The electronic pusher is used to apply radial pressure or tension to the aircraft engine rotor tester through the first force-adding component and the second force-adding component.

[0013] The electronic pusher is preferably an electronic pusher provided with a force sensor.

[0014] The second loading cylinder comprises a base, a connecting cylinder and a retaining ring; The base is a hollow cylinder with one end open and the other end closed; The connecting tube is a hollow cylinder with two ends open, the outer diameter of which is equal to the outer diameter of the base and the inner diameter of which is larger than the inner diameter of the base; The retaining ring is annular and is arranged at one end of the connecting tube. The outer wall is coaxially fixed to the inner wall of the connecting tube, and the inner diameter of the retaining ring is equal to the inner diameter of the base. The end of the connecting tube away from the retaining ring and the open end of the base are coaxially fixedly connected by bolts, so that the outer ring of the first angular contact ball bearing and the retaining ring abut against each other, and the outer ring of the second angular contact ball bearing and the open end of the base abut against each other; The inner ring of the first angular contact ball bearing abuts against the step at the end of the aircraft engine rotor tester, and the inner ring of the second angular contact ball bearing abuts against the open end of the inner fixed cylinder.

[0015] The output shaft of the electronic actuator in the present invention can rotate horizontally around the fixing bolt, avoiding the loading of additional bending moment; and the electronic actuator adopts an electronic actuator equipped with a force sensor, which can feedback the size of the loaded axial force at any time, facilitating quantitative loading to control the degree of axial force loading; thereby enabling the present invention to perform bidirectional large-load axial force loading, and complete bidirectional axial force loading of different amplitudes and frequencies. The device is simple to operate and the measurement is accurate.

[0016] It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by those skilled in the art in the art to which this invention belongs. It should also be understood that terms such as those defined in common dictionaries should be understood to have meanings consistent with their meanings in the context of the prior art and, unless defined as such, will not be interpreted in an idealized or overly formal sense.

[0017] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A bidirectional axial force loading device for an aircraft engine rotor tester, characterized in that: It includes an electronic propulsion device, a first force-added component, and a second force-added component; The first force-adding assembly comprises a first loading cylinder, a fixing bolt, a locking nut and a force-adding ring; The fixing bolt comprises a nut and a stud; one end of the stud is coaxially and vertically fixed to the nut, and the other end of the stud is provided with an external thread for matching with the locking nut on the side wall, and the outer wall of the stud between the external thread and the nut is smooth; The force-adding ring is a hollow cylinder with openings at both ends; The first loading cylinder is a hollow cylinder with one end open and the other end closed, and a first through hole and a second through hole are symmetrically provided on its side wall for matching with the stud of the fixing bolt, and a first through groove and a second through groove are symmetrically provided on its side wall and parallel to its axis; The fixing bolt passes through the first through hole, the force ring, and the second through hole in sequence and is threadedly connected to the fixing bolt, so that the first loading cylinder, the fixing bolt, and the lock nut are fixed to each other, and the force ring and the stud of the fixing bolt are loosely matched; the two sides of the force ring extend out of the first loading cylinder through the first through slot and the second through slot respectively; The electronic pusher is fixed to the outside, and its output shaft is connected to the outer wall of the force ring. The output shaft of the electronic pusher is coaxial with the first loading cylinder, and the axis of the output shaft of the electronic pusher passes through the center of the force ring. The second force-applying assembly comprises a second loading cylinder, a first angular contact ball bearing, a second angular contact ball bearing, and an inner fixing cylinder; The second loading cylinder is a hollow cylinder with one end open and the other end closed, and the closed end is coaxially fixedly connected to the closed end of the first loading cylinder; The inner fixing cylinder is a hollow cylinder with one end open and the other end provided with a through hole. The inner fixing cylinder is sleeved on the end of the aircraft engine rotor tester and is coaxially fixedly connected to the end of the aircraft engine rotor tester. The first and second angular contact ball bearings have the same structure and are arranged back-to-back, i.e., their wide end faces abut each other. The inner rings of the first and second angular contact ball bearings are coaxially fixedly connected to the inner fixed cylinder, and the outer rings are coaxially fixedly connected to the second loading cylinder, so that the second loading cylinder and the end of the aircraft engine rotor tester can rotate freely in the circumferential direction and are fixed in the radial direction. The electronic pusher is used to apply radial pressure or tension to the aircraft engine rotor tester through the first force-adding component and the second force-adding component.

2. The bidirectional axial force loading device for an aircraft engine rotor tester according to claim 1, characterized in that: The electronic pusher is an electronic pusher provided with a force sensor.

3. The bidirectional axial force loading device for an aircraft engine rotor tester according to claim 1, characterized in that: The second loading cylinder comprises a base, a connecting cylinder and a retaining ring; The base is a hollow cylinder with one end open and the other end closed; The connecting tube is a hollow cylinder with two ends open, the outer diameter of which is equal to the outer diameter of the base and the inner diameter of which is larger than the inner diameter of the base; The retaining ring is annular and is arranged at one end of the connecting tube. The outer wall is coaxially fixed to the inner wall of the connecting tube, and the inner diameter of the retaining ring is equal to the inner diameter of the base. The end of the connecting tube away from the retaining ring and the open end of the base are coaxially fixedly connected by bolts, so that the outer ring of the first angular contact ball bearing and the retaining ring abut against each other, and the outer ring of the second angular contact ball bearing and the open end of the base abut against each other; The inner ring of the first angular contact ball bearing abuts against the step at the end of the aircraft engine rotor tester, and the inner ring of the second angular contact ball bearing abuts against the open end of the inner fixed cylinder.

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