Device and method for testing fireproof performance of aero-engine installation joint

Abstract

The invention provides a performance testing device and method for an aero-engine installation joint, the device comprises a static force loading device, a test piece clamping device and a combustion device, the static force loading device is used for applying static force to the installation joint, the test piece clamping device is used for clamping the installation joint, and the combustion device is used for performing flame impact on the installation joint. According to the invention, the performance of the aero-engine installation joint can be tested.

Description

Technical Field

[0001] The invention relates to the field of installation joint performance testing, and in particular to a device and method for testing the fire resistance performance of an aircraft engine installation joint. Background Art

[0002] Fire is an important factor affecting aircraft flight safety. There are thousands of flight accidents caused by aircraft engine fires, which have caused huge losses of life and property. Most flight fires are accompanied by fire and explosion when they occur. Whether it is an aircraft accident caused by fire or a fire caused by an aircraft accident, it will bring unacceptable loss of life and property. Therefore, civil aviation fire safety has always been highly valued by the aviation industry.

[0003] The mounting node is the connecting part between the engine and the aircraft. It is responsible for transferring various external loads of the aircraft engine to the aircraft and is an important component of the engine. The mounting node not only fixes the engine to the aircraft, but also transfers various loads generated by the engine. It is a component that should have flame containment capability within the target area or range of the fire in the engine system. The Civil Aviation Administration of China CCAR-33-R2 "Aerospace Engine Certification" AC 33.17 Fire Protection Clause states that the acceptable conformity verification methods for components include: description, analysis, testing, and demonstration. The AP-21-AA-2022-11 "Type Certification Procedure" further clarifies the 10 types of conformity verification methods, namely, declaration of conformity / reference to model design documents / selection method coefficients, etc. / definition, design review, analysis / calculation, safety assessment, laboratory testing, ground testing on related products, flight testing, engineering conformity inspection, simulator testing, and equipment identification). Regarding the airworthiness compliance verification method of the fire protection design of the engine mounting node, since its fire protection performance is closely related to the installation environment, design dimensions, flight conditions, etc., the laboratory test verification method should be adopted, and it is recommended to carry out the compliance method verification in accordance with Article 33.17 (b, c, e) of CCAR-33-R2 and Article 25.1183 of CCAR-25-R4. The aircraft engine mounting node belongs to the power unit, which refers to the general term for the aircraft engine and the systems and accessories necessary to ensure the normal operation of the aircraft engine. Fire in the power unit or failure of the corresponding mounting node structure will pose a serious threat to flight safety. If the mounting node breaks in the fire, the flame will burst out of the engine nacelle and may spread to the wing fuel tank or fuselage, causing a major accident with the destruction of the aircraft and the death of people. Therefore, it is necessary to test the fire resistance of the engine mounting node to ensure that the performance of the mounting node installed on the aircraft is reliable. Summary of the invention

[0004] In view of the above technical problems, the technical solution adopted by the present invention is:

[0005] According to a first aspect of the present invention, a performance test device for an aircraft engine mounting section is provided, comprising: a static loading device, a test piece clamping device and a combustion device; wherein the static loading device comprises a first base, a second base and a support frame, one end of the support frame is arranged above the first base, and the other end is arranged above the second base, a slide rail is arranged on the support frame, a first loading mechanism connected to the slide rail is arranged on the first base, a second loading mechanism is arranged on the second base, and a placement space for placing the combustion device is formed between the first base and the second base; the test piece clamping device comprises a first connecting component, a second connecting component, an interface connecting component and a clamping component, one end of the first connecting component is connected to the first loading mechanism, and the other end is connected to one end of the interface connecting component, the clamping component is used to clamp the test piece, the other end of the interface connecting component is connected to the test piece, one end of the second connecting component is connected to the second loading structure, and the other end is connected to the clamping component, and the test piece is an aircraft engine mounting section.

[0006] According to a first aspect of the present invention, a performance testing method for an aircraft engine mounting node is provided, which is used to test the fire resistance performance of the engine mounting node, and the method comprises the following steps:

[0007] S100, according to the preset m test conditions, accurately test m test pieces, wherein the test piece is an aircraft engine mounting section; parameter information corresponding to the test conditions includes flame impact position, static loading method and test steps.

[0008] S200, using a test piece clamping device to install the i-th test piece corresponding to the i-th test condition onto a static loading device, where i ranges from 1 to m.

[0009] S300, performing a corresponding test operation on the i-th test piece according to the parameter information corresponding to the i-th test condition, and obtaining a corresponding test result R i , wherein, if an abnormal phenomenon occurs in the test piece during the test operation, the corresponding test result includes the occurrence time of the abnormal phenomenon.

[0010] The present invention has at least the following beneficial effects:

[0011] The invention can test the fireproof performance of the aero-engine mounting joint and can ensure the reliable performance of the mounting joint installed on the aircraft.

[0012] It should be understood that the contents described in this section are not intended to identify the key or important features of the embodiments of the present invention, nor are they intended to limit the scope of the present invention. Other features of the present invention will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0014] Figure 1 A top view of the key structure of a performance testing device for an aero-engine mounting section provided by an embodiment of the present invention;

[0015] Figure 2 for Figure 1 Side view of

[0016] Figure 3 and Figure 4 It is a structural schematic diagram of the aircraft engine installation section;

[0017] Figure 5 A schematic diagram of the structure of a static force applying device provided in an embodiment of the present invention;

[0018] Figure 6 A schematic diagram of the structure of a test piece clamping device provided in an embodiment of the present invention;

[0019] Figure 7 It is a structural schematic diagram of a concave connecting block;

[0020] Figure 8 It is a schematic diagram of the structure of the fuel oil device;

[0021] Fig. 9 A schematic diagram of a performance testing method for an aircraft engine mounting node provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0023] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0024] It should be noted that some exemplary embodiments are described as processes or methods depicted as flow charts. Although the flow charts describe the steps as sequential processes, many of the steps can be implemented in parallel, concurrently or simultaneously. In addition, the order of the steps can be rearranged. The process can be terminated when its operation is completed, but it can also have additional steps not included in the accompanying drawings. The process can correspond to a method, function, procedure, subroutine, subprogram, etc.

[0025] The embodiment of the present invention provides a performance testing device for an aircraft engine mounting section, such as Figures 1 to 4 As shown, the device is used to test the performance of the aircraft engine installation node 1, and the device may include: a static loading device 2, a test piece clamping device 3 and a combustion device 4. Among them, the static loading device is used to apply a static loading value to the installation node, the test piece clamping device is used to clamp the installation node, and the combustion device is used to perform flame impact on the installation node.

[0026] In the embodiment of the present invention, the aircraft engine mounting section 1 may be an existing structure. In an exemplary embodiment, Figure 3 and Figure 4 As shown, it may include a mounting node base 101, a first side connection end 102 and a second side connection end 103 arranged on both sides of the mounting node base 101, and a middle connection end 104 arranged in the middle of the mounting node base 101. The side connection end and the middle connection end are respectively formed with two connection interfaces arranged at intervals. In the embodiment of the present invention, the side connection end and the middle connection end are weak points of the aircraft engine mounting node.

[0027] Furthermore, in the embodiment of the present invention, the maximum test force of the static loading device 2 can be 2000 kN, and the accuracy level is 0.5. Figure 2 and Figure 5 As shown, the static loading device 2 may include a first base 202, a second base 203 and a support frame 201, one end of the support frame 201 is arranged above the first base 202, and the other end is arranged above the second base 203, a slide rail 204 is arranged on the support frame 201, a first loading mechanism connected to the slide rail is arranged on the first base, a second loading mechanism is arranged on the second base, and a placement space for placing the combustion device 4 is formed between the first base and the second base.

[0028] Further, the first loading mechanism may include a first driving part 206, a first telescopic rod 205, a second driving part (not shown), the second telescopic rod 206 and a first clamp 207. The first driving part 206 is fixed to one end of the support frame 201, one end of the first telescopic rod 205 is connected to the first driving part 206, and the other end is connected to the first clamp 207. The first clamp 207 is slidably connected to the slide rail 204 through a connecting rod, and the first clamp 207 is formed with a first wedge-shaped jaw 208. The second telescopic rod and the second driving part are arranged in the first telescopic rod, one end of the second telescopic rod 206 is connected to the second driving part, and the other end extends into the first wedge-shaped jaw 208.

[0029] Further, the second loading mechanism includes a fixed rod 209, a second clamp 210, a third driving unit (not shown) and a third telescopic rod 211. One end of the fixed rod 209 is fixedly connected to the other end of the support frame 201, and the other end is connected to the second clamp 210. The second clamp 210 is also connected to the support frame through a support rod to be fixed on the support frame. The second clamp 210 is formed with a second wedge-shaped jaw 212. The third telescopic rod and the third driving unit are arranged in the fixed rod, one end of the third telescopic rod is connected to the third driving unit, and the other end extends into the second wedge-shaped jaw 212.

[0030] In an embodiment of the present invention, the first drive unit, the second drive unit and the third drive unit may all be hydraulic drive devices. The first telescopic rod moves forward and backward along the length direction of the support frame under the driving action of the first drive unit to drive the first clamp to move forward or backward. The second telescopic rod moves forward and backward along the length direction of the support frame under the driving action of the second drive unit. The third telescopic rod moves forward and backward along the length direction of the support frame under the driving action of the third drive unit.

[0031] In addition, a displacement detection sensor (not shown) is provided on the first telescopic rod for detecting the displacement of the first fixture. A pressure detection sensor is provided on the fixed rod for detecting the force applied by the first driving part. A first cooling interface 213 is also formed on the first fixture for allowing coolant to flow in to cool the first fixture. A second cooling interface 214 is also formed on the second fixture for allowing coolant to flow in to cool the first fixture. The coolant may be water. The function of the coolant is to prevent the fixture from deforming during the test.

[0032] Furthermore, a first heat insulation baffle is provided on the first base, and a second heat insulation baffle is provided on the second base. Both the first heat insulation baffle and the second heat insulation baffle are located above the placement space and are used to insulate the fixture during the test.

[0033] In the embodiment of the present invention, the driving part, the displacement detection sensor and the force detection sensor of the static loading device may be communicatively connected with a controller (not shown).

[0034] In the embodiment of the present invention, the test piece clamping device needs to be determined in combination with the structure of the test piece, and the test piece fixture design and structural strength verification need to be performed before the test piece clamping device is designed. During the manufacturing process of the test piece for installation, the weak points of the test piece force analysis should be evaluated accordingly, and the test piece clamping device should be matched with the weak force area of ​​the test piece. The test piece clamping device should match the weak force area of ​​the test piece to avoid the defects of the test piece force design.

[0035] Furthermore, if Figure 1 , Figure 2 and Figure 6 As shown, the test piece clamping device 3 may include a first connection component, a second connection component, an interface connection component and a clamping component. One end of the first connection component is connected to the first loading mechanism, and the other end is connected to one end of the interface connection component. The clamping component is used to clamp the test piece, and the other end of the interface connection component is connected to the test piece. One end of the second connection component is connected to the second loading structure, and the other end is connected to the clamped component. The test piece is an aircraft engine mounting joint.

[0036] Further, the first connection assembly may include a first wedge-shaped locking block 301, a first concave connection block 302 and a first connection block 303, wherein the first wedge-shaped locking block 301 is connected to the first concave connection block and fixed in the first wedge-shaped jaw through the second telescopic rod. Specifically, the first wedge-shaped locking block 301 may be fixedly connected to the first concave connection block 302 by bolts. Afterwards, the first wedge-shaped locking block 301 is placed in the first wedge-shaped jaw, and the second driving unit is controlled to drive, so as to push the second telescopic rod forward and push the locking block to move toward the narrower end of the first wedge-shaped jaw. Due to the wedge-shaped structure, the wedge-shaped locking block will be stuck in the first wedge-shaped jaw and then fixed in the first wedge-shaped jaw.

[0037] like Figure 7 As shown, the first concave connection block 302 is formed with a first groove 304, one end of the first connection block 302 is inserted and fixed in the first groove 304, and the other end is connected to the interface connection assembly. The first concave connection block and the first connection block can be fixedly connected by multiple, for example, three bolts.

[0038] Furthermore, the clamping assembly may include a first clamping member 306 and a second clamping member 307, the front end of the first clamping member 306 is formed with a first front groove, the rear end of the first clamping member is formed with a first rear groove, the front end of the second clamping member 307 is formed with a second front groove, the rear end of the second clamping member is formed with a second rear groove, the first front groove and the second front groove cooperate to form a wrapping space that wraps around the mounting section base, and the mounting section base refers to the portion of the mounting section other than the weak point. In the embodiment of the present invention, during the test, the clamping assembly wraps around the mounting section body, so that the tension on the clamping device can be evenly distributed, which can prevent the clamping device from being damaged during the test, thereby ensuring the effective conduct of the test.

[0039] Furthermore, if Figure 1 and Figure 2 As shown, the second connection assembly includes a second wedge-shaped locking block 308, a second concave connection block 309 and a second connection block 310, and the second wedge-shaped locking block is connected to the second concave connection block and fixed in the second wedge-shaped jaw through the third telescopic rod. Specifically, the second wedge-shaped locking block 308 can be fixedly connected to the second concave connection block 309 by bolts. Afterwards, the second wedge-shaped locking block 308 is placed in the second wedge-shaped jaw, and the second driving unit is controlled to drive, push the second telescopic rod forward, and push the locking block to move toward the narrower end of the second wedge-shaped jaw. Due to the wedge-shaped structure, the wedge-shaped locking block will be stuck in the second wedge-shaped jaw, and then fixed in the second wedge-shaped jaw.

[0040] Furthermore, the second concave connection block has the same structure as the first concave connection block, that is, a second groove is formed. A clamping block is formed at the first end of the second connection block 310, and the clamping block is clamped in the groove space formed by the first rear groove and the second rear groove, and the second end of the second connection block is inserted into and fixed in the second groove by bolts.

[0041] Furthermore, the interface connection component may include a first interface connection component and a second interface connection component, such as Figure 1 and Figure 3 As shown, the first interface connection assembly includes three first connection members 311 of the same structure, which are respectively used to connect with the middle connection interface and two side connection interfaces of the installation section. The second interface connection assembly includes three second connection members 305 of the same structure, which are respectively used to connect with the three first connection members.

[0042] In the embodiment of the present invention, the first connecting member is an elliptical structure with fixing holes at both ends. Each second connecting member 306 may include an upper connecting block 3051, an intermediate block 3052 and a lower connecting block 3053, the upper connecting block 3051 and the lower connecting block 3053 are both elliptical structures with fixing holes at both ends, the upper connecting block 3051 and the lower connecting block 3053 are connected through the intermediate block 3052 to form a first connecting space A1 and a second connecting space A2, the first connecting member is inserted into the first connecting space and connected to the second connecting member by bolts, the first connecting block is inserted into the second connecting space and connected to the second connecting member by bolts.

[0043] Furthermore, if Figure 8 As shown, the combustion device 4 in the embodiment of the present invention may include a burner 41, a positioning bracket 42, a first fixed bracket 43 and a second fixed bracket 44, the burner 41 may be fixed on the first fixed bracket, the first fixed bracket 43 is connected to the positioning bracket 42, a movable slide rail 45 is provided on the second fixed bracket 44, and the positioning bracket 42 is also connected to the movable slide rail 45 through a movable plate 46 to drive the burner 41 to move along the movable slide rail.

[0044] In the embodiment of the present invention, the functions of the positioning bracket include: on the one hand, it can ensure that the standard distance of 100cm from the standard flame of the burner to the impact position of the test piece can be guaranteed; on the other hand, it can prevent the test piece from falling and damaging the burner after being broken. The oil burner in the embodiment of the present invention can be an existing oil burner. During the test operation, the distance between the outlet end face of the burner cone and the surface of the flame impact position of the test piece is 102mm±3mm, and the flame area is at least 10in×10in (254mm×254mm), meeting the AC20-135 requirements.

[0045] In an embodiment of the present invention, the movable plate may be driven by a driving mechanism (not shown). The driving mechanism may be in communication with a controller, and drive the movable plate to move along the movable slide rail based on a control instruction sent by the controller.

[0046] In view of the current situation that it is impossible to effectively test the thermal damage performance of aircraft engine mounting nodes in simulated fire situations, the present invention combines static loading equipment with a standard fuel burner used to simulate fire scenes, which can highly accurately reproduce the stress and strain conditions of aircraft engine mounting nodes in simulated fire environments, and can also accurately present its ultimate tensile strength and fracture deformation. The static loading equipment is specially customized to adapt to the complex test environment in the presence of large flames. In complex and dangerous situations with the presence of flames, it can still maintain normal operation and provide a stable static loading function for the test. In addition, this loading function is adjustable and can be flexibly adjusted according to different test requirements, greatly improving the accuracy and operability of the test.

[0047] In an embodiment of the present invention, the test piece is first fixed on the test piece clamping device to form a clamping unit, and then the two wedge-shaped locking blocks of the clamping unit are respectively placed in the corresponding two jaws, and then the jaws are controlled to contract and press the wedge-shaped locking blocks to fix the wedge-shaped locking blocks in the jaws. Next, the oil burner is placed in the placement space of the static loading device and aligned with the position where the flame impact of the test piece is required. During the test, the static loading device will control the hydraulic device to drive the first telescopic rod to move forward along the length direction of the support frame according to the instructions preset in the control system to apply a static loading value to the clamping device, and then apply a corresponding tensile force to the test piece. The static loading value and the stretching distance can be obtained by the force detection sensor and the displacement detection sensor respectively.

[0048] Based on the same inventive concept, an embodiment of the present invention provides a performance testing method for an aircraft engine mounting node, which is used to simulate the engine under harsh or extreme working conditions, and under the action of a standard flame generated by a standard burner, measure the influence of changes in parameters such as material thickness, structure, and load of the aircraft engine mounting node structural parts on temperature distribution and strain distribution within 15 minutes.

[0049] Furthermore, a performance test method for an aircraft engine mounting joint provided in an embodiment of the present invention is implemented based on the aforementioned device, such as Fig. 9 As shown, the method may include the following steps:

[0050] S100, according to the preset m test conditions, accurately test m test pieces.

[0051] In the embodiment of the present invention, the test piece may be an aircraft engine mounting section, and the specific structure may be as shown in 3 and Figure 4 As shown, it includes a mounting node base 101 , a first side connection end 102 and a second side connection end 103 arranged at both sides of the mounting node base 101 , and a middle connection end 104 arranged in the middle of the mounting node base 101 .

[0052] In an embodiment of the present invention, parameter information corresponding to the test condition may include flame impact position, static loading method and test steps.

[0053] In the embodiment of the present invention, the parameter information corresponding to the test condition includes the flame impact position, the static loading method and the test steps. The test condition can be determined according to the simulation experiment of the engine installation section.

[0054] In the embodiment of the present invention, four test conditions are included, that is, m=4. Among them, the flame impact position corresponding to the first test condition is the side connection interface, the corresponding static loading method is to apply tension to each side connection interface, and the corresponding test steps include a flame impact stage, a stretching stage, and an unloading force stage, wherein, in the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the stretching stage, F1 is increased to a second set tension F2, and the duration of F2 is a second set duration t2; F2=k×F1, k is a coefficient greater than 1, and t2<t1.

[0055] In the embodiment of the present invention, the first test condition is used to simulate the normal load of the actual installation section of the engine and the fire protection capability of the main structure. F1 and F2 can be determined based on the corresponding engine design parameters. In an exemplary embodiment, 150000N≤F1≤200000N, preferably, F1=175000N, 20000N≤F2≤300000N, preferably, F2=250000N.

[0056] In the embodiment of the present invention, t1 = 900 s, t2 = 30 s.

[0057] In the first test condition, in the flame impact stage, the force control rate is 500N / s≤V1≤1500N / s, preferably 1000N / s, and in the stretching stage, the force control rate is 1500N / s≤V2≤2500N / s, preferably 2000N / s.

[0058] The flame impact position corresponding to the second test condition is the middle connection interface, and the corresponding static loading method is to apply tension to each side connection interface. The corresponding test steps include a flame impact stage, a stretching stage, and an unloading force stage. In the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the stretching stage, F1 is first increased to F2 and maintained for t2, and then the test piece is broken or F2 is increased to the third set tension F3 and maintained for t2.

[0059] In the embodiment of the present invention, the second test condition is used to simulate the normal load of the actual installation section of the engine and the fire protection capability of the lifting ring (weak area).

[0060] In the embodiment of the present invention, F3 is the limit load that the installation joint can withstand. In an exemplary embodiment, 450000 N ≤ F3 ≤ 500000 N, preferably, F3 = 475000 N. In the second test condition, in the flame impact stage, the force control rate is 500 N / s ≤ V1 ≤ 1500 N / s, preferably, 1000 N / s, and in the stretching stage, the force control rate is 1500 N / s ≤ V2 ≤ 2500 N / s, preferably, 2000 N / s.

[0061] The flame impact position corresponding to the third test condition is the two side connection interfaces, and the corresponding static loading method is to apply tension to the middle connection interface. The corresponding test steps include a flame impact stage, a first stretching stage, a second stretching stage and an unloading force stage. In the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the first stretching stage, F1 is increased to F2 and maintained for t2; in the second stretching stage, F2 is increased to F3 and maintained for the third set duration t3.

[0062] In the embodiment of the present invention, the third test condition is used to simulate the fire protection capability of the main body and the weak area of ​​the engine mounting node under the extreme load.

[0063] The flame impact position corresponding to the fourth test condition is the two side connection interfaces, the corresponding static loading method is to apply tension to the two side connection interfaces, and the corresponding test steps include a flame impact stage, a first stretching stage, a second stretching stage and an unloading force stage, wherein, in the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the first stretching stage, F1 is increased to F3 and maintained for t2; in the second stretching stage, F3 is increased to a fourth set tension F4 and maintained for t3;

[0064] In the embodiment of the present invention, the fourth test condition is used to simulate the fireproof capability of the actual engine installation section body and the weak area under a strong load. In an exemplary embodiment, 800000N≤F4≤850000N, preferably, F4=825000N.

[0065] In the embodiment of the present invention, the unloading force stage is a stage of unloading the current pulling force to 0. In the embodiment of the present invention, an oil burner may be used for flame impact.

[0066] S200, using a test piece clamping device to install the i-th test piece corresponding to the i-th test condition onto a static loading device, where i ranges from 1 to m.

[0067] S300, performing a corresponding test operation on the ith test piece according to the parameter information corresponding to the ith test condition, and obtaining a corresponding test result, wherein, if an abnormal phenomenon occurs in the test piece during the test operation, the test result includes the occurrence time corresponding to the abnormal phenomenon.

[0068] In the embodiment of the present invention, the abnormal phenomenon includes deformation and fracture. The deformation phenomenon can be obtained by a displacement detection sensor. When the displacement detection sensor detects a displacement value, it indicates that the first fixture has moved, that is, the test piece has deformed. The fracture phenomenon can be determined when the reading of the force detection sensor is zero, which indicates that the test piece has fractured.

[0069] In the embodiment of the present invention, the occurrence time may be recorded by a timer.

[0070] In the embodiment of the present invention, the test result may include a first result indicating that the test piece meets the relevant fire protection performance requirements and a second result indicating that the test piece does not meet the relevant fire protection performance requirements.

[0071] Furthermore, in the embodiment of the present invention, S300 also includes: recording the test operation process, for example, by recording a video.

[0072] Further, in the embodiment of the present invention, a strain sensor and a temperature sensor are provided on the test piece. In the embodiment of the present invention, the strain sensor is attached to the side connector and the middle connector of the test piece. The temperature sensor is provided on the entire test piece and can be attached to a position of interest based on actual needs.

[0073] In the embodiment of the present invention, the strain sensor may be a high-precision high-temperature strain gauge resistant to 800°C, for example, a high-temperature strain gauge of model TG120-2AA800-YF50 may be used. Before pasting, the strain sensor needs to be cured, and the curing method may adopt the existing method.

[0074] Since the temperature test point is at the critical surface between the fire zone and the metal surface of the test piece, it is known from the preliminary research of the project that the welding technology of the thermocouple (such as the selection of the thermocouple, the welding method, the welding depth, the depth of the welding surface covering the weld point, etc.) directly affects the accuracy of the wall temperature measurement. Therefore, the present invention adopts a K-type thermocouple with a specification of Φ1×1000×L500 to monitor the temperature of the installation section test piece under flame conditions. The thermocouple is carried out by laser welding, and the thermocouple extension wire is reinforced as necessary to ensure the accuracy of the test piece wall temperature test.

[0075] Furthermore, the method provided by the embodiment of the present invention also includes the following steps:

[0076] S400: Analyze actual stress conditions and thermal response characteristics of the test piece under flame impact based on stress data acquired by the strain sensor and temperature data acquired by the temperature sensor.

[0077] Those skilled in the art know that any method for analyzing the actual stress conditions and thermal response characteristics of the test piece under flame impact based on the stress data obtained by the strain sensor and the temperature data obtained by the temperature sensor falls within the scope of protection of the present invention.

[0078] Furthermore, the method provided by the embodiment of the present invention also includes the following steps:

[0079] S500: If deformation of the test piece is detected, the movement of the oil burner is controlled based on the currently detected deformation amount so that the oil burner is aligned with the flame impact position.

[0080] In an embodiment of the present invention, during the flame impact process, if deformation of the test piece is detected, the moving distance of the oil burner can be determined based on the detection value of the displacement detection sensor to control the oil burner to move a corresponding distance to align with the flame impact position of the test piece, thereby making the test result more accurate.

[0081] The method provided by the embodiment of the present invention can perform performance tests on the aircraft engine installation section under multiple test conditions.

[0082] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps described in the present invention can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solution disclosed in the present invention can be achieved, and this document does not limit this.

[0083] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A performance testing device for an aircraft engine mounting section, characterized in that: include: Static loading equipment, test piece clamping device and combustion device; wherein the static loading equipment comprises a first base, a second base and a support frame, one end of the support frame is arranged above the first base, and the other end is arranged above the second base, a slide rail is arranged on the support frame, a first loading mechanism connected to the slide rail is arranged on the first base, a second loading mechanism is arranged on the second base, and a placement space for placing the combustion device is formed between the first base and the second base; The test piece clamping device includes a first connecting component, a second connecting component, an interface connecting component and a clamping component, one end of the first connecting component is connected to the first loading mechanism, and the other end is connected to one end of the interface connecting component, the clamping component is used to clamp the test piece, the other end of the interface connecting component is connected to the test piece, one end of the second connecting component is connected to the second loading structure, and the other end is connected to the clamped component, and the test piece is an aircraft engine mounting node.

2. The device according to claim 1, characterized in that The first loading mechanism comprises a first driving part, a first telescopic rod, a second driving part, a second telescopic rod and a first clamp, wherein the first driving part is fixed to one end of the support frame, one end of the first telescopic rod is connected to the first driving part, and the other end is connected to the first clamp, the first clamp is slidably connected to the slide rail through a connecting rod, the first clamp is formed with a first wedge-shaped jaw, the second telescopic rod and the second driving part are arranged in the first telescopic rod, one end of the second telescopic rod is connected to the second driving part, and the other end extends into the first wedge-shaped jaw; The second loading mechanism includes a fixed rod, a second clamp, a third driving part and a third telescopic rod, one end of the fixed rod is fixedly connected to the other end of the support frame, the other end of the fixed rod is connected to the second clamp, the second clamp is also connected to the support frame through the support rod to be fixed on the support frame, the second clamp is formed with a second wedge-shaped jaw, the third telescopic rod and the third driving part are arranged in the fixed rod, one end of the third telescopic rod is connected to the third driving part, and the other end extends into the second wedge-shaped jaw; Among them, a displacement detection sensor is arranged on the first telescopic rod for detecting the displacement of the first clamp, and a pressure detection sensor is arranged on the fixed rod for detecting the force applied by the first driving part; a first cooling interface is also formed on the first clamp for supplying coolant to flow in to cool the first clamp, and a second cooling interface is also formed on the second clamp for supplying coolant to flow in to cool the first clamp.

3. The device according to claim 2, characterized in that The first connection assembly comprises a first wedge-shaped locking block, a first concave connection block and a first connection block, the first wedge-shaped locking block is connected to the first concave connection block and fixed in the first wedge-shaped jaw through the second telescopic rod, the first concave connection block is formed with a first groove, one end of the first connection block is inserted and fixed in the first groove, and the other end is connected to the interface connection assembly; The clamping assembly includes a first clamping member and a second clamping member, the front end of the first clamping member is formed with a first front groove, the rear end of the first clamping member is formed with a first rear groove, the front end of the second clamping member is formed with a second front groove, and the rear end of the second clamping member is formed with a second rear groove, the first front groove and the second front groove cooperate to form a wrapping space that wraps around the mounting joint base, the mounting joint base refers to the part of the mounting joint except the weak point, the weak point includes the middle connecting end and two side connecting ends of the mounting joint; the second connecting assembly includes a second wedge-shaped locking block, a second concave connecting block and a second connecting block, the second wedge-shaped locking block is connected to the second concave connecting block and is fixed in the second wedge-shaped jaw through the third telescopic rod, the second concave connecting block is formed with a second groove, the first end of the second connecting block is formed with a clamping block, the clamping block is clamped in the groove space formed by the cooperation of the first rear groove and the second rear groove, and the second end of the second connecting block is inserted and fixed in the second groove.

4. The device according to claim 3, characterized in that The interface connection component includes a first interface connection component and a second interface connection component. The first interface connection component includes three first connection members with the same structure, which are respectively used to connect with the middle connection interface and two side connection interfaces of the mounting section; the second interface connection component includes three second connection members with the same structure, which are respectively used to connect with the three first connection members.

5. The device according to claim 2, characterized in that The combustion device includes a burner, a positioning bracket, a first fixed bracket and a second fixed bracket, the burner is fixed on the first fixed bracket, the first fixed bracket is connected to the positioning bracket, a movable slide rail is arranged on the second fixed bracket, and the positioning bracket is also connected to the movable slide rail through a movable plate to drive the burner to move along the movable slide rail.

6. A performance testing method for an aircraft engine mounting node, characterized in that: Based on the device implementation of claim 1, the method comprises the following steps: S100, according to the preset m test conditions, accurately test m test pieces, the test piece is an aircraft engine installation section, and the parameter information corresponding to the test conditions includes flame impact position, static loading method and test steps; S200, using a test piece clamping device to install the i-th test piece corresponding to the i-th test condition onto a static loading device, where i ranges from 1 to m; S300, performing a corresponding test operation on the ith test piece according to the parameter information corresponding to the ith test condition, and obtaining a corresponding test result, wherein, if an abnormal phenomenon occurs in the test piece during the test operation, the corresponding test result includes the occurrence time of the abnormal phenomenon.

7. The method according to claim 6, characterized in that Includes four test conditions; The flame impact position corresponding to the first test condition is the side connection interface of the installation section, the corresponding static loading method is to apply tension to each side connection interface, and the corresponding test steps include a flame impact stage, a stretching stage, and an unloading force stage, wherein in the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the stretching stage, F1 is increased to a second set tension F2, and the duration of F2 is a second set duration t2; F2 = k × F1, k is a coefficient greater than 1, and t2 < t1; The flame impact position corresponding to the second test condition is the middle connection interface of the installation section, and the corresponding static loading method is to apply tension to each side connection interface. The corresponding test steps include a flame impact stage, a stretching stage, and an unloading force stage. In the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the stretching stage, F1 is first increased to F2 and maintained for t2, and then the test piece is broken or F2 is increased to a third set tension F3 and maintained for t2; The flame impact position corresponding to the third test condition is the two side connection interfaces of the installation section, and the corresponding static loading method is to apply tension to the middle connection interface. The corresponding test steps include a flame impact stage, a first stretching stage, a second stretching stage, and an unloading force stage, wherein, in the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the first stretching stage, F1 is increased to F2 and maintained for t2; in the second stretching stage, F2 is increased to F3 and maintained for a third set duration t3; The flame impact position corresponding to the fourth test condition is the two side connection interfaces of the installation section, and the corresponding static loading method is to apply tension to the two side connection interfaces. The corresponding test steps include a flame impact stage, a first stretching stage, a second stretching stage, and an unloading force stage, wherein, in the flame impact stage, the tension applied to each side connection interface is a first set tension F1, and the duration of F1 is a first set duration t1; in the first stretching stage, F1 is increased to F3 and maintained for t2; in the second stretching stage, F3 is increased to a fourth set tension F4 and maintained for t3; The unloading force stage is a stage of unloading the current tension to 0.

8. The method according to claim 6, characterized in that The test piece is provided with a strain sensor and a temperature sensor, and the method further comprises the following steps: S400: Analyze actual stress conditions and thermal response characteristics of the test piece under flame impact based on stress data acquired by the strain sensor and temperature data acquired by the temperature sensor.

9. The method according to claim 6, characterized in that 150000N≤F1≤200000N, 20000N≤F2≤300000N, 450000N≤F3≤500000N 800000N≤F4≤850000N.

10. The method according to claim 6, characterized in that 500N / s≤V1≤1500N / s,1500N / s≤V2≤2500N / s。

Images