Aerospace engine power turbine rotor sleeve tooth connection structure torsional moment load loading device

Abstract

The application discloses a torsional moment load loading device for a toothed sleeve connecting structure of an aero-engine power turbine rotor, which comprises a test-bed base, a power turbine rotor test piece, a front supporting seat, a rear supporting seat, a torsional moment load loading structure, an L-shaped support, a torsional load loading threaded support, an angular limiting spline shaft adapter plate and an angular limiting spline, wherein the front supporting seat and the rear supporting seat are used for supporting the power turbine rotor test piece; the torsional moment load loading device is installed between a compressor and a turbine of the power turbine rotor test piece, the L-shaped support is used for restraining the torsional moment load loading structure; and the angular limiting spline shaft adapter plate and the angular limiting spline exert circumferential restraint on a power output shaft of the power turbine rotor. The application can exert torsional moment load on the toothed sleeve connecting structure rotor test piece, and simulate the aerodynamic torque effect of the power turbine on the rotor in a working state.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, specifically relating to a torsional moment load loading device for a geared connection structure of an aero-engine power turbine rotor. Background Technology

[0002] Aero engines are typical high-speed rotating complex machines. Due to the large temperature gradients in compressor and turbine components, as well as the strength requirements of individual parts and the structural design of assembly, their rotors are often composed of multiple components with different geometries and materials, connected by various forms of connection structures. For rotor systems with connection interfaces, under external loads, the interface will inevitably experience changes in contact characteristic parameters or even local separation. This leads to mechanical property degradation phenomena such as constraint failure and bending stiffness loss in the connection structure, causing the rotor dynamic characteristics to deviate from the design values.

[0003] For power turbine rotors, the front end often uses a toothed spline connection structure to connect with the power output shaft. For ease of assembly and to reduce interference and contact damage from the toothed spline, a toothed spline connection structure design without axial positioning or centering cylindrical surface constraints is adopted. The bending stiffness of the connection structure mainly depends on the tooth surface contact of the spline under torsional load. However, because the torque load received by the toothed spline connection structure varies under different operating conditions, the stress distribution at the spline spline interface changes, leading to alterations in the mechanical properties of the connection structure. Therefore, it is necessary to establish an easy-to-use torsional moment load testing device for toothed spline connections to assist in the design of rotors and toothed spline connection structures. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention discloses a torsional moment load loading device for a geared rotor rotor of an aero-engine, which can apply a torsional moment load to the rotor test piece of the geared rotor structure to simulate the aerodynamic torque effect generated by the power turbine on the rotor under working conditions.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] A torsional moment load loading device for a geared connection structure of an aero-engine power turbine rotor includes a test bench base, a power turbine rotor test piece, a front support, a rear support, a torsional moment load loading structure, an L-shaped support, a torsional load loading threaded support, an angular limiting spline shaft adapter plate, and an angular limiting spline. The front and rear support supports the power turbine rotor test piece and are both fixedly mounted on the test bench base. The torsional moment load loading device is installed between the compressor and turbine of the power turbine rotor test piece. The L-shaped support supports the torsional moment load loading structure. The torsional load loading threaded support is mounted on the L-shaped support and applies a torsional moment load through bolts A and B. The angular limiting spline shaft adapter plate and the angular limiting spline apply circumferential constraints to the power output shaft of the power turbine rotor.

[0007] The aforementioned power turbine rotor test specimen includes a power output shaft, a power turbine shaft, a first-stage power turbine, and a second-stage power turbine. Firstly, to facilitate the application of test loads and constraint boundary conditions, all blades of the first-stage power turbine must be disassembled before the test torque load is applied by the torsional moment load loading device of the power turbine rotor gear connection structure. Then, the bladed disk of the second-stage power turbine is removed, and the torsional moment load loading structure is installed at the original bladed disk location of the second-stage power turbine.

[0008] The angular limiting spline shaft needs to extend from the front side of the power output shaft and constrain the angular displacement of the spline shaft through the angular limiting spline shaft adapter plate, so that the angular rotation of the power output shaft is constrained. At the same time, a torsional torque load is applied to the first-stage power turbine. This torsional torque will be transmitted to the sleeve gear connection structure through the rotor shaft, causing the splines to mesh.

[0009] The L-shaped support is used to support the structure loaded with torsional moment load. Two symmetrical threaded supports for torsional load loading are installed on the L-shaped support. By screwing bolts into the threaded holes, the bolts generate equal and opposite clamping forces to form a couple, thereby realizing the loading of torsional moment load.

[0010] In addition, since the misalignment of the supports on both sides of the power turbine may cause initial angular deformation at the position of the sleeve connection structure, it will also change the spline contact state and the mechanical properties of the connection structure. Therefore, the loading device leaves a 0.5mm gap on one side of the mounting surface of the support seat on both sides. By installing feeler gauges of different thicknesses between the front and rear cylindrical surfaces, the misalignment of the supports on both sides of the power turbine can be adjusted.

[0011] The present invention has the following beneficial effects:

[0012] (1) The present invention can change the torsional moment load on the power turbine rotor test piece of the sleeve tooth connection structure by adjusting the tightness of the bolts on the threaded support under torsional load, thereby simulating the torsional process of the power turbine rotor sleeve tooth connection structure during actual operation.

[0013] (2) Since the bending stiffness of the above-mentioned connection structure mainly depends on the tooth surface contact of the spline under torsional load, once the torque amplitude of the sleeve connection structure changes and causes a change in the spline contact state, the bending stiffness of the connection structure will deviate from the design value. This invention is of great significance for further exploring the bending stiffness loss state and dispersion of the sleeve connection structure of the power turbine rotor, as well as its impact on the dynamic characteristics of the power turbine. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a torsional moment load loading device for a turbine rotor sleeve connection of an aero-engine according to an embodiment of the present invention.

[0015] Figure 2 This is a cross-sectional view of the structural composition of the power turbine rotor test piece in this invention;

[0016] Figure 3 This is a schematic diagram of the torsional torque load loading method for the power turbine rotor test piece in this invention.

[0017] In the figure: 101-front support, 102-power turbine rotor test piece, 103-rear support, 104-torsional moment load loading structure, 105-L-type support, 106-torsional load loading threaded support, 107-angular limiting spline shaft adapter plate, 108-angular limiting spline, 109-test bench base;

[0018] 201 - Power output shaft, 202 - Power turbine shaft, 203 - First stage power turbine, 204 - Second stage power turbine;

[0019] 301 - Bolt A, 302 - Bolt B. Detailed Implementation

[0020] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Unless otherwise specified, the technical means used in the embodiments are conventional means well known to those skilled in the art.

[0021] like Figure 1As shown, this embodiment of the invention relates to a torsional moment load loading device for aero-engine power turbine rotor geared connection, comprising a front support 101, a power turbine rotor test piece 102, a rear support 103, a torsional moment load loading structure 104, an L-shaped support 105, a torsional load loading threaded support 106, an angular limiting spline shaft adapter plate 107, an angular limiting spline 108, and a test bench base 109. The front and rear support pieces support the power turbine rotor test piece and are both fixedly mounted on the test bench base. The torsional moment load loading device is installed between the compressor and turbine of the power turbine rotor test piece. The L-shaped support supports the torsional moment load loading device. The torsional load loading threaded support is mounted on the L-shaped support and applies the torsional moment load through bolts A and B. The angular limiting spline shaft adapter plate and the angular limiting spline apply circumferential constraints to the power output shaft of the power turbine rotor.

[0022] like Figure 2 As shown, the power turbine rotor test piece 102 in this embodiment of the invention includes a power output shaft 201, a power turbine shaft 202, a first-stage power turbine 203, and a second-stage power turbine 204; wherein, the connection position relationship of the power output shaft, the power turbine shaft, the first-stage power turbine, and the second-stage power turbine is the same as the connection position of the actual aero-engine power turbine rotor.

[0023] First, in order to facilitate the application of test loads and the application of constraint boundary conditions, some rotor components of the original power turbine rotor structure need to be replaced and removed. The first step is to remove all the blades of the first-stage power turbine 203, and the second step is to remove the blade disk of the second-stage power turbine 204 and replace it with the torsional moment load loading structure 104.

[0024] The front support 101 and the rear support 103 are fixedly installed on the test bench base 109. The power turbine rotor test piece 102 is located between the front support 101 and the rear support 103. The angular limiting spline 108 needs to extend from the front side of the power output shaft 201 and constrain the angular displacement of the spline shaft through the angular limiting spline shaft adapter plate 107, so that the angular rotation of the power output shaft 201 is constrained. At the same time, a torsional moment load is applied to the first-stage power turbine 203. This torsional moment will be transmitted to the gear connection structure through the rotor shaft, causing the splines to mesh.

[0025] like Figure 3 As shown, the L-shaped support 105 is used to constrain the torsional moment load loading structure 104. Two symmetrical torsional load loading threaded supports 106 are installed on the L-shaped support 105. By screwing bolts A301 and B302 into the threaded holes, the bolts generate equal and opposite clamping forces to form a couple, thereby realizing the loading of the torsional moment load.

[0026] It should be noted that since the front support 101 and the rear support 103 on both sides of the power turbine rotor test piece 102 are not concentric, the initial angular deformation of the sleeve tooth connection structure may occur, which will also change the spline contact state and the mechanical properties of the connection structure. Therefore, the loading device leaves a 0.5mm gap on one side of the mounting column surface of the support on both sides. By installing feeler gauges of different thicknesses between the front and rear columns, the concentricity of the two supports on both sides of the power turbine is adjusted.

[0027] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Any modifications, alterations, substitutions, or variations made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A torsional moment load loading device for a geared connection structure of an aero-engine power turbine rotor, characterized in that: The system includes a front support, a power turbine rotor test piece, a rear support, a torsional moment load loading structure, an L-shaped support, a torsional load loading threaded support, an angular limiting spline shaft adapter plate, an angular limiting spline, and a test bench base. The front and rear support are used to support the power turbine rotor test piece and are both fixedly mounted on the test bench base. The torsional moment load loading structure is installed between the compressor and turbine of the power turbine rotor test piece. The L-shaped support is used to support the torsional moment load loading structure. The torsional load loading threaded support is installed on the L-shaped support and applies the torsional moment load through bolts A and B. The angular limiting spline shaft adapter plate and the angular limiting spline apply circumferential constraints to the power output shaft of the power turbine rotor. The L-shaped support is used to constrain the structure loading torsional moment load. Two symmetrical torsional load loading threaded supports are installed on the L-shaped support. By screwing bolts A and B into the threaded holes, the bolts generate equal and opposite clamping forces to form a couple, thereby realizing the loading of torsional moment load. The front support and rear support are fixedly installed on the test bench base. The power turbine rotor test piece is located between the front support and the rear support. The angular limiting spline extends from the front side of the power output shaft and constrains the angular displacement of the spline shaft through the angular limiting spline shaft adapter plate, thereby constraining the angular rotation of the power output shaft. At the same time, a torsional moment load is applied to the first-stage power turbine. This torsional moment load is transmitted to the gear connection structure through the rotor shaft, causing the splines to mesh.

2. The torsional moment load loading device for the geared connection structure of an aero-engine power turbine rotor according to claim 1, characterized in that: The power turbine rotor test piece includes a power output shaft, a power turbine shaft, a first-stage power turbine, and a second-stage power turbine.

3. The torsional moment load loading device for the geared connection structure of an aero-engine power turbine rotor according to claim 1, characterized in that: Before applying the test torque load to the torsional moment load loading structure of the power turbine rotor sleeve tooth connection structure, all blades of the first-stage power turbine are removed, then the blade disk of the second-stage power turbine is removed, and the torsional moment load loading structure is installed at the original blade disk position of the second-stage power turbine.

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