Aero-engine test bed

Abstract

The invention provides an aero-engine test bed which comprises a support and an elastic part, one end of the support is connected with a main frame, a containing cavity is formed in the support, and the containing cavity is provided with a first port and a second port which are oppositely arranged; one end of the elastic piece penetrates into the containing cavity and is connected with the support at the first port, a connecting rod is arranged on the peripheral side of the elastic piece, and one end of the connecting rod penetrates out of the containing cavity and is used for being connected with a test piece; the other end of the elastic piece is installed at the second port, and a gap adjusting ring is arranged between the elastic piece and the support. And the elastic piece is in clearance fit with the clearance adjusting ring. According to the aero-engine test bed, the limitation of a single force transmission path is broken through, multi-path load transmission is achieved, the load is transmitted through the elastic piece under a conventional load, the requirement for low rigidity of the bed is met, and the resonant frequency of a system is reduced; under a large load, a transmission path, namely a force transmission path from the elastic piece to the gap adjusting ring to the support, is added, so that the bearing capacity is increased, and the rigidity of the rack is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine complete machine testing, and in particular to an aircraft engine test bench. Background Art

[0002] In order to overcome the loads transmitted by engines of different models, aircraft engine test benches are usually designed with sturdy steel structures. The steel structures have great strength and rigidity to meet the support requirements of the benches.

[0003] The critical speed of the rotor is fully considered when designing aircraft engines. Either the critical speed is kept out of the normal operating speed range, or damping and vibration reduction structures such as squeeze film dampers are designed to keep the rotor vibration level low, thereby reducing the impact of resonance on the rotor system.

[0004] When an aircraft engine is installed on a test bench, the aircraft engine and the test bench form a larger dynamic system, which is also called the "aircraft engine-test bench system". This system also has a resonant frequency, which is generally low and outside the engine's operating speed range. However, when the test bench has a large stiffness and the engine mass is relatively small, the resonant frequency of the aircraft engine-test bench system may be high, close to or even within the aircraft engine's operating speed range, thereby generating resonance during the test and affecting test safety.

[0005] Based on this, the inventor of the present application proposes an aircraft engine test bench in order to solve the above technical problems. Summary of the invention

[0006] The technical problem to be solved by the present invention is to overcome the defect of resonance between an aircraft engine and a test bench in the prior art and to provide an aircraft engine test bench.

[0007] The present invention solves the above technical problems through the following technical solutions:

[0008] The present invention provides an aero-engine test bench, which is characterized in that it comprises:

[0009] A support, one end of which is connected to the main frame, wherein a receiving chamber is provided in the support, and the receiving chamber has a first port and a second port which are arranged opposite to each other;

[0010] An elastic member, one end of which is passed through the accommodating chamber and connected to the support at the first port, a connecting rod is provided on the outer peripheral side of the elastic member, one end of which is passed through the outside of the accommodating chamber and is used to connect the test piece; the other end of the elastic member is installed at the second port, and a gap adjustment ring is provided between the elastic member and the support; wherein,

[0011] The elastic member and the clearance adjustment ring are clearance-matched.

[0012] According to an embodiment of the present invention, the elastic member is hollow in design, and at least a portion of the elastic member along its axial direction is a cage bar structure.

[0013] According to an embodiment of the present invention, the support is provided with an avoidance hole along the direction from the first port to the second port, and the elastic member is slidably matched with the avoidance hole through the connecting rod to be assembled with the support.

[0014] According to an embodiment of the present invention, the support is provided with a limiting protrusion on the inner side of the avoidance hole, and the limiting protrusion is designed as an arc and is rotatably matched with the connecting rod.

[0015] According to one embodiment of the present invention, the elastic member is detachably connected to the support at the first port via a threaded connection member;

[0016] The support is provided with a baffle at the side of the second port away from the first port. The baffle is sleeved on the outside of the elastic member and connected to the support by a threaded connector.

[0017] According to an embodiment of the present invention, the support is further provided with a slot on the inner side of the second port, and the gap adjustment ring is clamped in the slot.

[0018] According to an embodiment of the present invention, one end of the card slot is connected to the first port, and the support has a stop surface at the other end of the card slot;

[0019] One end of the gap adjustment ring abuts against the baffle, and the other end abuts against the stop surface.

[0020] According to an embodiment of the present invention, the support is provided with an internal flange between the first port and the second port and close to the first port, and one end of the elastic member is detachably connected to the internal flange via a threaded connector.

[0021] According to an embodiment of the present invention, a damping mechanism is provided between the baffle and the elastic member, and one end of the damping mechanism abuts against an outer end surface of the elastic member.

[0022] According to an embodiment of the present invention, the damping mechanism is a solid damper, a placement groove is opened on the inner side of the baffle, and the solid damper is placed in the placement groove.

[0023] According to an embodiment of the present invention, the damping mechanism is liquid damping, a damping groove is provided on the inner side of the baffle, and the damping groove is filled with hydraulic oil.

[0024] The positive and progressive effects of the present invention are:

[0025] The aero-engine test bench of the present invention breaks through the limitation of a single force transmission path and realizes multi-path load transmission. Under conventional loads, the load is transmitted through elastic parts, thereby achieving low stiffness requirements for the bench and reducing the resonant frequency of the system. Under large loads, an additional transmission path is added, namely, the force transmission path from the elastic part to the gap adjustment ring to the support, thereby increasing its load-bearing capacity and thus improving the stiffness of the bench. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0027] Figure 1 This is a schematic diagram of the normal installation of the test piece and the test stand of the present invention;

[0028] Figure 2 It is the vibration shape diagram of the test piece and the test bench of the present invention;

[0029] Figure 3 is a cross-sectional view of a test bench according to an embodiment of the present invention;

[0030] Figure 4 for Figure 3 Schematic diagram of the structure of the middle bracket;

[0031] Figure 5 for Figure 3 Partial view of the fit between the middle connecting rod and the support;

[0032] Figure 6 for Figure 3 A schematic diagram of the structure of the elastic member;

[0033] Figure 7 for Figure 3 Schematic diagram of the structure of the center gap adjustment ring;

[0034] Figure 8 This is a schematic diagram of the force transmission path between the test piece and the support under a small load according to an embodiment of the present invention;

[0035] Fig. 9 It is a schematic diagram of the force transmission path between the test piece and the support under a large load according to an embodiment of the present invention;

[0036] Fig.10 It is a schematic structural diagram of a test bench according to another embodiment of the present invention;

[0037] Fig.11 for Fig.10 A cross-sectional view at one angle;

[0038] Fig.12 for Fig.10 Schematic diagram of force transmission path using solid damping under small and medium loads;

[0039] Fig.13 for Fig.10 Schematic diagram of force transmission path using solid damping under medium and large loads;

[0040] Fig.14 It is a structural schematic diagram of a test bench according to another embodiment of the present invention;

[0041] Fig.15 for Fig.14 Schematic diagram of force transfer paths using liquid damping under medium to heavy loads.

[0042] 10. Support; 110. Accommodating chamber; 111. First port; 112. Second port; 120. Avoidance hole; 130. Baffle; 131. Placement groove; 132. Damping groove; 140. Card groove; 141. Stop surface; 150. Internal flange;

[0043] 20. Main frame;

[0044] 30. elastic member; 310. connecting rod;

[0045] 40. Test piece;

[0046] 50. Clearance adjustment ring;

[0047] 60. Damping mechanism; 610. Liquid damping. DETAILED DESCRIPTION

[0048] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0049] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0050] Reference Figures 1 to 15 The present invention proposes an aircraft engine test bench, including a support 10 and an elastic member 30. One end of the support 10 is connected to the main frame 20. A receiving chamber 110 is opened in the support 10. The receiving chamber 110 has a first port 111 and a second port 112 that are arranged opposite to each other.

[0051] That is, the support 10 is a hollow structure along its axial direction, corresponding to the accommodating chamber 110 , and the support 10 is opened at two opposite ends along its axial direction, corresponding to the first port 111 and the second port 112 .

[0052] One end of the elastic member 30 is passed through the accommodating chamber 110 and is connected to the support 10 at the first port 111. A connecting rod 310 is provided on the outer peripheral side of the elastic member 30. One end of the connecting rod 310 is passed through the outside of the accommodating chamber 110 and is used to connect the test piece 40. The other end of the elastic member 30 is installed at the second port 112, and a gap adjustment ring 50 is provided between the elastic member 30 and the support 10, and the gap between the elastic member 30 and the gap adjustment ring 50 is matched.

[0053] The elastic member 30 is used to connect the test piece 40 and the support 10. The elastic member 30 is inserted into the accommodating chamber 110 and connected to the support 10, so that the vibration load on the test piece 40 can be transmitted to the support 10 through the elastic member 30, and then transmitted to the main frame 20.

[0054] The gap adjustment ring 50 is sleeved on the outside of the elastic member 30 and is gap-matched with the elastic member 30 . Therefore, when the test piece 40 operates normally, a gap-matched relationship is maintained between the elastic member 30 and the gap adjustment ring 50 , and the load received by the elastic member 30 is transmitted to the main frame 20 via the support 10 .

[0055] When the vibration intensity of the test piece 40 is too high, abutment will be formed between the elastic member 30 and the gap adjustment ring 50, so that part of the load will be transmitted to the support 10 through the gap adjustment ring 50, and then transmitted to the main frame 20. Therefore, under large load vibration, a force transmission path is added, thereby achieving low stiffness requirements for the test bench.

[0056] Figure 1 This is a schematic diagram of the normal installation of the test piece and the test stand of the present invention. Figure 2 The vibration mode diagram of the test piece and the test bench of the present invention. In order to avoid the occurrence of resonance, the present invention breaks through the limitation of the traditional single force transmission path and uses different force transmission schemes according to different loads. Under normal loads, force is transmitted through the elastic member 30 to achieve low stiffness requirements for the test bench and reduce the resonant frequency of the system. When the load is large, an additional force transmission path is added to increase the load-bearing capacity of the test bench, thereby improving the strength of the test bench.

[0057] Moreover, as for the elastic member 30 , the elastic member 30 can be replaced according to the stiffness requirement of the system.

[0058] By using the test bench of the present invention, the gap associated with the elastic member 30 can be measured, for example, by using a feeler gauge from the second port 112 . Under normal load, the gap will not be squeezed out, so there is only one force transmission path from the test piece 40 to the support 10 .

[0059] When the load is too large, the deformation of the elastic part 30 becomes larger, and the gap between the gap adjustment ring 50 and the elastic part 30 is squeezed out, thereby forming two force transmission paths. The two force transmission paths can prevent the elastic part 30 from being excessively deformed, ensuring that the elastic part 30 itself will not have strength problems. The wall thickness of the support 10 is relatively thick and can withstand large loads, so that the stand meets the strength test requirements.

[0060] Please refer to Figures 3 to 7 In one embodiment, the elastic member 30 is hollow in design, and at least a portion of the elastic member 30 along its axial direction is a cage bar structure.

[0061] The hollow design of the elastic member 30 and the cage bar structure design of at least a portion of the elastic member 30 along its axial direction are used to reduce the connection stiffness between the elastic member 30 and the support 10 .

[0062] In one embodiment, the support 10 is provided with an avoidance hole 120 along the direction from the first port 111 to the second port 112 , and the elastic member 30 is slidably matched with the avoidance hole 120 via a connecting rod 310 to be assembled with the support 10 .

[0063] Because the connecting rod 310 needs to extend to the outside of the support 10 to connect with the test piece 40, the support 10 has an avoidance hole 120 along its axial direction, so that the elastic member 30 can be inserted into the accommodating cavity along the direction from the first port 111 to the second port 112 of the support 10. At the same time, the avoidance hole 120 plays the role of avoiding the connecting rod 310 and guiding the installation.

[0064] Please refer to Figure 6 Furthermore, the support 10 is provided with a limiting protrusion on the inner side of the avoidance hole 120 , and the limiting protrusion is designed as an arc and is rotatably matched with the connecting rod 310 .

[0065] That is, the rotational cooperation between the elastic member 30 and the support 10 can play a damping role and suppress the resonance generated during the swinging process of the connecting rod 310.

[0066] In one embodiment, the elastic member 30 is detachably connected to the support 10 at the first port 111 via a threaded connection.

[0067] Specifically, the support 10 is provided with an internal flange 150 between the first port 111 and the second port 112 and close to the first port 111 , and one end of the elastic member 30 is detachably connected to the internal flange 150 via a threaded connector.

[0068] The support 10 and the elastic member 30 are detachably connected, so that different elastic members 30 can be installed according to different test pieces 40 to meet different test requirements.

[0069] Please continue to refer to Figure 3 and Figure 7 In one embodiment, the support 10 is further provided with a slot 140 on the inner side of the second port 112 , and the gap adjustment ring 50 is clamped in the slot 140 .

[0070] Furthermore, the support 10 is provided with a baffle 130 on the side of the second port 112 away from the first port 111 . The baffle 130 is sleeved on the outside of the elastic member 30 and connected to the support 10 by a threaded connector.

[0071] One end of the slot 140 is connected to the first port 111 , and the support 10 has a stop surface 141 at the other end of the slot 140 ; ​​one end of the gap adjustment ring 50 abuts against the baffle 130 , and the other end abuts against the stop surface 141 .

[0072] That is, the holder 10 is provided with a clamping groove 140 for limiting the axial position of the clearance adjustment ring 50 to prevent the clearance adjustment ring 50 from sliding along the axial direction of the holder 10 and affecting the force transmission.

[0073] One end of the gap adjustment ring 50 is in contact with the baffle 130 , so that the baffle 130 can cooperate with the slot 140 to limit the gap adjustment ring 50 .

[0074] Specifically, the gap adjustment ring 50 is a sleeve structure with a hollow design. Meanwhile, a hole for avoiding the connecting rod 310 is provided on the gap adjustment ring 50 to avoid interference with the installation of the connecting rod 310 .

[0075] Please refer to Figure 8 and Fig. 9 It should be noted that the above two force transmission paths can adjust the resonance between the test piece 40 and the support 10 to below the working speed of the test piece 40, so as to keep it away from the working speed of the test piece 40. However, the test piece 40 still needs to repeatedly pass through the resonance frequency each time it is pneumatically operated and stopped. Therefore, a damping mechanism 60 can be further provided between the baffle 130 and the elastic member 30 to reduce the amplitude during resonance. The damping mechanism 60 can be, but is not limited to, solid damping and liquid damping 610.

[0076] Please refer to Figures 10 to 15 In one embodiment, the damping mechanism 60 is a solid damper, a placement groove 131 is opened on the inner side of the baffle 130, and the solid damper is placed in the placement groove 131.

[0077] The solid damping may be arranged in a complete ring around the baffle 130 axially, or may be arranged in a single direction, which is not limited here.

[0078] Please refer to Figures 10 to 13The solid damping can be rubber. After the damping mechanism 60 is added between the baffle 130 and the elastic member 30, under the action of a small load, there are two force transmission paths between the test piece 40 and the main frame 20. One path is transmitted to the support 10 through the elastic body, and then transmitted to the main frame 20; the other path is transmitted to the solid damping through the elastic body, and then transmitted to the support 10 through the damping mechanism 60, and then transmitted to the main frame 20.

[0079] Under the action of large load, an additional force transmission path is added, that is, on the basis of the above two paths, the force is transmitted from the elastic member 30 to the gap adjustment ring 50, then transmitted to the support 10 through the gap adjustment ring 50, and finally transmitted to the main frame 20 through the support 10.

[0080] Please refer to Fig.14 and Fig.15 In another embodiment, the damping mechanism 60 is a liquid damper 610 , and a damping groove 132 is provided on the inner side of the baffle 130 , and the damping groove 132 is filled with hydraulic oil.

[0081] Specifically, an extrusion oil film area is formed between the elastic member 30 and the baffle 130 , an oil supply hole is opened on the outer side of the baffle 130 , the inner side of the oil supply hole is connected to an oil supply groove, and the oil supply groove has multiple oil supply channels evenly distributed along the circumference, and the oil supply channels are connected to the extrusion oil film area.

[0082] It should be noted that under the action of a small load, there are two force transmission paths between the test piece 40 and the main frame 20. One path is transmitted to the support 10 through the elastomer, and then transmitted to the main frame 20; the other path is transmitted to the damping mechanism 60 through the elastomer, and then transmitted to the support 10 through the liquid damping 610, and then transmitted to the main frame 20.

[0083] Under the action of large load, an additional force transmission path is added, that is, on the basis of the above two paths, the force is transmitted from the elastic member 30 to the gap adjustment ring 50, then transmitted to the support 10 through the gap adjustment ring 50, and finally transmitted to the main frame 20 through the support 10.

[0084] In summary, the aircraft engine test bench of the present invention breaks through the limitation of a single force transmission path and realizes multi-path load transmission. Under normal loads, the load is transmitted through the elastic member 30, thereby achieving low stiffness requirements for the bench and reducing the resonant frequency of the system. Under large loads, an additional transmission path is added, namely, the force transmission path from the elastic member 30 to the gap adjustment ring 50 to the support 10, which increases its load-bearing capacity, thereby improving the stiffness of the bench.

[0085] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installation", "connection", "attachment", "fixation" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral body; it can also be a mechanical connection. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0086] The present application uses specific terms to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the present application can be appropriately combined.

[0087] Although the present invention is disclosed above in preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modifications, equivalent changes, and decorations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention all fall within the protection scope defined by the claims of the present invention.

Claims

1. An aircraft engine test bench, It is characterized in that include: A support, one end of which is connected to the main frame, wherein a receiving chamber is provided in the support, and the receiving chamber has a first port and a second port which are arranged opposite to each other; An elastic member, one end of which is passed through the accommodating chamber and connected to the support at the first port, a connecting rod is provided on the outer peripheral side of the elastic member, one end of which is passed through the outside of the accommodating chamber and is used to connect the test piece; the other end of the elastic member is installed at the second port, and a gap adjustment ring is provided between the elastic member and the support; wherein, The elastic member and the clearance adjustment ring are clearance-matched.

2. The aircraft engine test bench according to claim 1, It is characterized in that The elastic member is hollow in design, and at least a portion of the elastic member along its axial direction is a cage bar structure.

3. The aircraft engine test bench according to claim 1, It is characterized in that The support is provided with an avoidance hole along the direction from the first port to the second port, and the elastic member is slidably matched with the avoidance hole through the connecting rod to be assembled with the support.

4. The aircraft engine test bench according to claim 3, It is characterized in that The support is provided with a limiting protrusion on the inner side of the avoidance hole, and the limiting protrusion is designed as an arc and is rotatably matched with the connecting rod.

5. The aircraft engine test bench according to claim 1, It is characterized in that The elastic member is detachably connected to the support at the first port via a threaded connection member; The support is provided with a baffle at the side of the second port away from the first port. The baffle is sleeved on the outside of the elastic member and connected to the support by a threaded connector.

6. The aircraft engine test bench according to claim 5, It is characterized in that The support is further provided with a clamping groove on the inner side of the second port, and the gap adjustment ring is clamped in the clamping groove.

7. The aircraft engine test bench according to claim 6, It is characterized in that One end of the card slot is communicated with the first port, and the support has a stop surface at the other end of the card slot; One end of the gap adjustment ring abuts against the baffle, and the other end abuts against the stop surface.

8. The aircraft engine test bench according to claim 5, It is characterized in that The support is provided with an internal flange between the first port and the second port and close to the first port, and one end of the elastic member is detachably connected to the internal flange through a threaded connector.

9. The aircraft engine test bench according to claim 5, It is characterized in that A damping mechanism is provided between the baffle and the elastic member, and one end of the damping mechanism abuts against the outer end surface of the elastic member.

10. The aircraft engine test bench according to claim 9, It is characterized in that The damping mechanism is a solid damper, a placement groove is provided on the inner side of the baffle, and the solid damper is placed in the placement groove.

11. The aircraft engine test bench according to claim 9, It is characterized in that The damping mechanism is liquid damping, a damping groove is provided on the inner side of the baffle, and the damping groove is filled with hydraulic oil.

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