Aero-engine turbine rear casing strength test device with auxiliary mounting section

Abstract

The application belongs to the field of aerospace technology, and particularly relates to a turbine rear casing strength test device of an aero-engine with an auxiliary mounting joint, a turbine rear casing strength test device of an aero-engine with an auxiliary mounting joint, and the test device can realize static strength and fatigue test of the turbine rear casing with the auxiliary mounting joint of the same type. The loading device can simultaneously apply loads of different positions and different directions of the auxiliary mounting joint, the mounting edge and the fulcrum generated in the working of the turbine rear casing. The application adopts a fulcrum squirrel cage structure, and several simple pull rods are used to simultaneously apply two-directional loads in the same position in the effective space. The structure is simple, convenient to install, and the processing cost of the test tool is reduced without complex structure.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, and specifically relates to a strength testing device for the rear casing of an aero-engine turbine with an auxiliary mounting section. Background Technology

[0002] The turbine rear casing of a certain type of aircraft engine is mounted on the aircraft via a rear mounting section on the outer ring of the casing. The main loads borne by the turbine rear casing are: 1) The engine auxiliary mounting section system is connected to the outer ring of the load-bearing frame, and part of the engine's vertical and lateral loads, as well as torque, are transmitted to the aircraft through the auxiliary mounting section system on the turbine rear frame; 2) A five-point bearing seat is fixed to the front mounting edge of the inner ring of the load-bearing frame, bearing the maneuvering loads generated by the engine's low-pressure turbine rotor during various maneuvers of the aircraft. Figures 1-2 The turbine rear casing of a certain type of aero-engine mainly bears three types of loads: first, the axial load M and lateral load P at the mounting edge; second, the axial load N and lateral load R5 at five supports; and third, the loads F4, F5, and F6 from the auxiliary installation section of the aircraft being hoisted. To analyze and determine whether the casing meets engineering requirements, a strength test of the full-size turbine rear casing is necessary. The more complex structure and load-bearing conditions increase the difficulty of designing the test plan.

[0003] Based on the structural and load characteristics of the turbine rear casing, the main disadvantages of existing loading schemes are:

[0004] 1. The loading space of the auxiliary installation section load of the turbine rear casing is interfered with, and it is impossible to directly load it using a general method.

[0005] In strength tests, a basic loading unit consisting of a hydraulic actuator, a force gauge, a load-bearing foundation, and a transition section is typically used to load the test specimen. Its structure is as follows: Figure 3-4 As shown. Figures 1-2 As shown, the auxiliary mounting sections F4, F5, and F6 of the turbine rear casing intersect in the load directions. Due to the limited loading space, using a basic loading unit will inevitably cause spatial interference, such as... Figure 3 As shown, and due to the characteristics of the test specimen, the basic loading unit cannot be changed to the opposite direction of the test specimen load to achieve load application, such as... Figure 4 As shown, it is therefore impossible to directly apply the auxiliary installation section load using a general basic loading unit.

[0006] 2. The axial load at the installation edge and the axial load at the 5-point support interfere with each other in terms of loading space, making it impossible to directly load them using a common method.

[0007] Both the axial load at the mounting edge and the axial load at the five supports need to be applied by the loading cell through the center of the test specimen, which will cause spatial interference. To solve the spatial interference problem of the loading cell, the following methods are generally adopted: Figure 5The loading method shown is as follows: the axial load at the 5-point support is changed from being applied in tension to being applied in compression by the axial loading unit at the 5-point support. Due to the size limitation of the axial loading unit at the 5-point support, the height of the foundation transition tube will be significantly increased, resulting in a higher loading section of the auxiliary installation section and the loading section of the rear installation edge of the test specimen. This places higher demands on the load-bearing capacity of the test foundation platform, the foundation transition tube, and the bearing foundation, and also increases the risk of damage to the test fixtures and consequently the test specimen.

[0008] The lateral and axial loads at the 3rd and 5th supports interfere with each other in terms of loading space, making it impossible to apply them directly using a general method.

[0009] The space at the 5-support point is confined, and the lateral load at the 5-support point cannot be directly applied using the loading unit. A common approach is to... Figure 6 The load is applied using a lever configuration as shown. In addition to the lateral load at the five fulcrums, an axial load also needs to be applied. Since the levers occupy the space required for the axial load, a method is employed as follows... Figure 6 The conventional loading method shown can apply axial load while applying lateral load to the fulcrum. However, this loading method will cause the lateral load and axial load to affect each other during the loading process, resulting in an unavoidable interference phenomenon, which seriously affects the loading accuracy. Summary of the Invention

[0010] To address the aforementioned issues, this application provides: 1. A strength testing device for the rear turbine casing of an aero-engine with an auxiliary mounting section, which performs a loading test on the turbine rear casing test piece. The turbine rear casing test piece is vertically fixed on the base platform via the axis of the base adapter cylinder connected to the front mounting edge. The rear mounting edge of the turbine rear casing test piece is connected to a simulated cylinder. The simulated cylinder is connected to the axial load loading unit of the mounting edge fixed at the top via the axial load bearing plate of the mounting edge.

[0011] The turbine rear casing test piece has a 5-point fulcrum fitted with a fulcrum lateral load loading lever. The two ends of the fulcrum lateral load loading lever are respectively connected to two lateral tie rods. The two lateral tie rods are connected to the fulcrum lateral load loading unit through the same connecting rod.

[0012] The turbine rear casing test piece has a 5-point connection between the axial load cage and the lower end face of the axial load cage. The axial load cage is fitted outside the lateral load lever. The lateral tie rod is placed in the gap between the axial tie rods of the axial load cage. The upper end of the axial load cage is connected to the axial load unit. The axial load unit applies axial force to the 5 points through the axial load cage.

[0013] The fifth auxiliary mounting section of the turbine rear casing test piece is loaded with load through the auxiliary mounting section F5 load loading unit; the sixth auxiliary mounting section is loaded with load through the auxiliary mounting section F6 load loading unit; the fourth auxiliary mounting section is loaded with load through the combined force of the auxiliary mounting section F4″ load loading unit and the auxiliary mounting section F4′ load loading unit.

[0014] Preferably, the five support points of the turbine rear casing test piece are sleeved outside the lateral load loading lever of the support points through spherical bearings.

[0015] Preferably, the auxiliary mounting section F4″ load loading unit and the auxiliary mounting section F4′ load loading unit are connected to the fourth auxiliary mounting section through the irregular F4 load loading ears. The irregular F4 load loading ears include a first end connected to the fourth auxiliary mounting section, a second end connected to the auxiliary mounting section F4″ load loading unit, and a third end connected to the auxiliary mounting section F4′ load loading unit.

[0016] Preferably, the angle between the axes of the second end and the third end is 60°.

[0017] Preferably, the axial load loading unit is mounted on the axial load bearing plate, and the axial load bearing plate is connected to the foundation platform through multiple circumferentially distributed axial load bearing brackets.

[0018] Preferably, the reaction forces of the mounting side axial load loading unit, the auxiliary mounting section F5 load loading unit, the auxiliary mounting section F6 load loading unit, the auxiliary mounting section F4″ load loading unit, the auxiliary mounting section F4′ load loading unit, the fulcrum axial load loading unit, and the fulcrum transverse load loading unit act on the bearing foundation respectively.

[0019] Preferably, the load-bearing foundation includes load-bearing columns and beams.

[0020] Preferably,

[0021] F4 is the load that needs to be applied to the fourth auxiliary installation section, F4′ is the load applied by the load loading unit of the auxiliary installation section F4′, and F4″ is the load applied by the load loading unit of the auxiliary installation section F4″.

[0022] The advantages of this application include: This invention proposes a strength testing device for the rear turbine casing of an aero-engine with an auxiliary mounting section. The device can be used to perform static strength and fatigue tests on the same type of rear turbine casing with an auxiliary mounting section. The loading device can simultaneously apply loads at different positions and in different directions of the auxiliary mounting section, mounting edge, and support point generated during the operation of the rear turbine casing.

[0023] This application adopts a fulcrum cage structure, which uses a few simple tie rods to achieve simultaneous application of loads in two directions at the same position within the effective space. Its structure is simple and easy to install, and the absence of complex structures reduces the processing cost of experimental tooling.

[0024] This application adopts an axial force loading scheme in the same direction, which effectively reduces the height of the test specimen, reduces the load-bearing capacity requirement of the test foundation, reduces the difficulty of test design and the processing cost of test tooling, and reduces the risk of damage to the test specimen due to failure of test tooling. Attached Figure Description

[0025] Figure 1 This is a top view of the test specimen at the loading position;

[0026] Figure 2 This is a sectional view of the test specimen at the loading position;

[0027] Figure 3 This is a schematic diagram of the mutual interference of the general loading units in the auxiliary installation section;

[0028] Figure 4 This is a schematic diagram of the interference between the auxiliary installation section's universal loading unit and the casing;

[0029] Figure 5 It is a general loading scheme for axial loads;

[0030] Figure 6 This is a schematic diagram of a universal lever loading system with 5 fulcrums for lateral loads;

[0031] Figure 7 This is a schematic diagram of the experimental loading device of this application;

[0032] Figure 8 yes Figure 7 Schematic diagram of the test loading device (AA view);

[0033] Figure 9 This is a schematic diagram of the implementation of axial load at 5 support points;

[0034] Figure 10 yes Figure 9 A schematic diagram of the axial load implementation at 5 support points (AA view);

[0035] Figure 11 This is a schematic diagram of a 5-point mouse cage loading structure;

[0036] Figure 12 yes Figure 11 5-point mouse cage loading structure BB view;

[0037] Figure 13 Force analysis diagram of the two ears of the irregular F4 under load;

[0038] Figure 14Calculation diagram of force analysis on the two ears of the irregular F4 under load. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0040] like Figures 7-12 The front mounting edge of the turbine rear casing test piece 4 is fixed to the base platform 1 via the base adapter sleeve 2, and the rear mounting edge is connected to the simulated cylinder 10. The lateral load R5 at the 5th support point is applied by the lateral load loading unit 11 through the lateral load loading lever 5; the axial load N at the 5th support point is applied to the 5th support point by the axial load loading unit 9 through the axial load loading cage 6, and its reaction force acts on the base platform through the axial load bearing plate 8 and the axial load bearing bracket 7; the lateral load P at the rear mounting edge is applied by the lateral load loading unit 3; the axial load M at the rear mounting edge is applied by the axial load loading unit 13 through the axial load bearing plate 12. The load F4 of the auxiliary installation section is applied by the auxiliary installation section F4′ load loading unit 15 and the auxiliary installation section F4″ load loading unit 17 through the irregular F4 load loading lugs 16. The resultant force of the two loads is the F4 load. The load F5 of the auxiliary installation section is applied by the auxiliary installation section F5 load loading unit 18. The load F6 of the auxiliary installation section is applied by the auxiliary installation section F6 load loading unit 19. The reaction forces of all loading units act on the bearing foundation 14, which includes bearing columns, beams, etc.

[0041] a) such as Figures 3-4 As shown, the auxiliary mounting section F4 of the turbine rear casing spatially intersects with the load directions of F5 and F6, making it impossible to directly apply load using a general-purpose loading unit. If the F4 load is applied in the opposite direction, the loading unit will interfere with the test piece, preventing the application of the auxiliary mounting section F4 load. Therefore, the following method is used... Figures 7-8 The loading method shown decomposes the F4 load into two loads, F4′ and F4″, which are applied using a non-standard F4 load on both ears. The magnitude and direction of their resultant force are the same as those of F4. Figures 13-14As shown, the F4 load was applied. The actual applied values ​​of F4′ and F4″ can be calculated using the formula.

[0042] F4 is the load that needs to be applied to the fourth auxiliary installation section, F4′ is the load applied by the load loading unit of the auxiliary installation section F4′, F4″ is the load applied by the load loading unit of the auxiliary installation section F4″, F5 is the load that needs to be applied to the fifth auxiliary installation section, and F6 is the load that needs to be applied to the sixth auxiliary installation section.

[0043] b) such as Figure 9-12 As shown, utilizing the gap between the support plates of the turbine rear casing test piece, four axial load bearing brackets are fixed to the foundation platform through the test piece, forming a load-bearing foundation with the axial load bearing plates to withstand the reaction force of the axial load loading unit. This achieves the application of the axial load at the support points and the axial load at the mounting edge in the same direction, minimizing the height of the turbine rear casing test piece and solving the problem of... Figure 5 The general axial load loading scheme, due to the increased height of the test specimen, requires higher load-bearing capacity for the test base platform, bearing unit, and base adapter cylinder. This effectively reduces the difficulty of test design and the processing cost of test adapters, and reduces the risk of test specimen damage due to the failure of test tooling.

[0044] c) A squirrel cage structure is used to solve the problem of interference between the lateral and axial loads at five supports, preventing proper loading. For example... Figure 11-12 As shown, a squirrel cage structure composed of eight axial tie rods encloses a loading lever, which can swing freely within the cage. One end of a transverse tie rod connects to the loading lever, passing through the gap between the axial tie rods, while the other end connects to the fulcrum transverse load loading unit to apply the fulcrum transverse load. The fulcrum axial load loading unit applies the axial load via the squirrel cage structure composed of eight axial tie rods. The two load paths do not interfere with each other, achieving simultaneous application of loads in two directions at the same fulcrum location.

[0045] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A strength testing device for the rear turbine casing of an aero-engine with an auxiliary mounting section, used for loading tests on a turbine rear casing test piece (4), characterized in that, The turbine rear casing test piece (4) is vertically fixed on the base platform (1) via the axis of the base adapter cylinder (2) connected to the front mounting edge. The rear mounting edge of the turbine rear casing test piece (4) is connected to the simulated cylinder (10). The simulated cylinder (10) is connected to the mounting edge axial load loading unit (13) fixed on the top via the mounting edge axial load bearing plate (12). The turbine rear casing test piece (4) has a 5-point lateral load loading lever (5) on its fulcrum. The two ends of the lateral load loading lever (5) are connected to two lateral tie rods (52). The two lateral tie rods (52) are connected to the lateral load loading unit (11) through the same connecting rod. The turbine rear casing test piece (4) has a 5-point connection to the lower end face of the axial load loading cage (6). The axial load loading cage (6) is fitted on the outside of the lateral load loading lever (5). The lateral tie rod (52) is placed in the gap between the axial tie rods (61) of the axial load loading cage (6). The upper end of the axial load loading cage (6) is connected to the axial load loading unit (9). The axial load loading unit (9) applies axial force to the 5 points through the axial load loading cage (6). The fifth auxiliary mounting section of the turbine rear casing test piece (4) is loaded by the auxiliary mounting section F5 load loading unit (18); the sixth auxiliary mounting section is loaded by the auxiliary mounting section F6 load loading unit (19); the fourth auxiliary mounting section is loaded by the combined force of the auxiliary mounting section F4″ load loading unit (17) and the auxiliary mounting section F4′ load loading unit (15); The auxiliary installation section F4″ load loading unit (17) and the auxiliary installation section F4′ load loading unit (15) are connected to the fourth auxiliary installation section through the irregular F4 load loading double ears (16). The irregular F4 load loading double ears (16) include a first end connected to the fourth auxiliary installation section, a second end connected to the auxiliary installation section F4″ load loading unit (17), and a third end connected to the auxiliary installation section F4′ load loading unit (15).

2. The aero-engine turbine rear casing strength testing device with auxiliary mounting section as described in claim 1, characterized in that, The five fulcrums of the turbine rear casing test piece (4) are fitted outside the fulcrum lateral load loading lever (5) via spherical bearings (51).

3. The aero-engine turbine rear casing strength testing device with auxiliary mounting section as described in claim 1, characterized in that, The angle between the axes of the second and third ends is 60°.

4. The aero-engine turbine rear casing strength testing device with auxiliary mounting section as described in claim 1, characterized in that, The axial load loading unit (9) is installed on the axial load bearing plate (8), and the axial load bearing plate (8) is connected to the foundation platform (1) through multiple circumferentially distributed axial load bearing brackets (7).

5. The aero-engine turbine rear casing strength testing device with auxiliary mounting section as described in claim 1, characterized in that, The reaction forces of the mounting side axial load loading unit (13), auxiliary mounting section F5 load loading unit (18), auxiliary mounting section F6 load loading unit (19), auxiliary mounting section F4″ load loading unit (17), auxiliary mounting section F4′ load loading unit (15), fulcrum axial load loading unit (9) and fulcrum transverse load loading unit (11) act on the bearing foundation (14) respectively.

6. The aero-engine turbine rear casing strength testing device with auxiliary mounting section as described in claim 1, characterized in that, The load-bearing foundation (14) includes load-bearing columns and beams.

7. The aero-engine turbine rear casing strength testing device with auxiliary mounting section as described in claim 3, characterized in that, F4 is the load that needs to be applied to the fourth auxiliary installation section, F4′ is the load applied by the load loading unit of the auxiliary installation section F4′, and F4″ is the load applied by the load loading unit of the auxiliary installation section F4″.

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