阅读说明：本技术 一种基于固体耦合的界面刚度检测装置 (Interface rigidity detection device based on solid coupling ) 是由 穆晓凯 袁博 王英全 孙泽宇 王新煦 汪云龙 孙清超 孙伟 于 2021-08-13 设计创作，主要内容包括：本发明属于界面刚度检测技术领域,公开了一种基于固体耦合的界面刚度检测装置,目的是为航空发动机典型部位的螺栓连接结构提供一种界面刚度的在位检测装置。该界面刚度检测装置以装置基体为基础,根据超声透射检测的要求,整个装置以上下结构的形式构成。伸缩杆基体分别与二级伸缩杆、一级伸缩杆联合实现二级伸缩功能,在一级伸缩杆的末端设有超声探头。吸附圆柱与电磁铁相互吸附为超声探头提供了夹紧力。本发明的特点在于能够在航空发动机狭小空间开展界面刚度检测,能够利用弹簧杆提供压力实现较好的重复性,利用固体耦合方式避免了液体耦合剂所带来的污染。(The invention belongs to the technical field of interface rigidity detection, discloses an interface rigidity detection device based on solid coupling, and aims to provide an in-situ detection device for interface rigidity for a bolt connection structure of a typical part of an aircraft engine. The interface rigidity detection device is based on a device substrate, and the whole device is formed in a vertical structure mode according to the requirement of ultrasonic transmission detection. The telescopic link base member jointly realizes the flexible function of second grade with second grade telescopic link, one-level telescopic link respectively, is equipped with ultrasonic probe at the end of one-level telescopic link. The adsorption cylinder and the electromagnet are mutually adsorbed to provide clamping force for the ultrasonic probe. The method has the characteristics that the method can be used for carrying out interface rigidity detection in a narrow space of an aeroengine, can realize better repeatability by utilizing pressure provided by a spring rod, and avoids pollution caused by a liquid coupling agent by utilizing a solid coupling mode.)

1. The interface rigidity detection device based on solid coupling is characterized by comprising a device base body (22), a linear sliding block, an adsorption cylinder (2), a rotating disk, an electromagnet (14), a telescopic rod base body, a two-stage telescopic rod, a first-stage telescopic rod, an ultrasonic probe clamping block, a linear bearing, a spring rod, an ultrasonic probe, a positioning telescopic rod (4), a linear guide rail base, a linear guide rail and an end cover (28) with a limiting bearing; the device base body (22) is of a hollow cylindrical structure, the three positioning telescopic rods (4) are uniformly distributed in the device base body (22), and the three positioning telescopic rods (4) are used for positioning and clamping a circular ring in an aircraft engine; the upper end and the lower end of the device base body (22) are connected with the rotating disc through bearings, and an inner ring with a limiting bearing end cover (28) pressing the bearings is connected with the device base body (22); a convex plate at the top end of the adsorption cylinder (2) is matched with a groove of the end cover (28) with a limiting bearing; the connecting rod (27) is respectively connected with the upper rotating disk (3) and the lower rotating disk (5) in a positioning manner, so that the rotating synchronization function of the upper rotating disk and the lower rotating disk is realized; the rotating disc is connected with the linear guide rail base, and the linear guide rail base is connected with the linear guide rail; the adsorption cylinder (2) is connected with an upper telescopic rod base body (21), and the electromagnet (14) is connected with a lower telescopic rod base body (7); the adsorption column (2) and the electromagnet (14) are mutually adsorbed to provide clamping displacement for the ultrasonic probe; the telescopic rod base body, the secondary telescopic rod and the primary telescopic rod form a secondary telescopic mechanism together, and the two groups of secondary telescopic mechanisms are formed; the secondary telescopic mechanism is fixedly connected with the linear sliding block, and the linear sliding block moves to drive the secondary telescopic mechanism and the ultrasonic probe to do linear motion; the tail end of the primary telescopic rod is provided with a linear bearing and an ultrasonic probe clamping block, the ultrasonic probe clamping block is used for clamping an ultrasonic probe, and the linear bearing is provided with a spring rod.

2. The interface rigidity detection device based on solid coupling is characterized in that the adsorption cylinder (2) and the electromagnet (14) are mutually adsorbed to provide clamping force for the ultrasonic probe; the ultrasonic probe mainly comprises an ultrasonic transducer (29) and a solid coupling layer (30).

3. The device for detecting the interfacial rigidity based on solid coupling according to claim 1 or 2, wherein the upper spring bar (19) and the lower spring bar (10) generate constant pressure to ensure that the coupling state of the ultrasonic transducer (29) and the solid coupling layer (30) is the same as the contact stress state.

4. The interface rigidity detection device based on solid coupling according to claim 1 or 2, characterized in that in the non-detection stage, the electromagnet (14) is not electrified and has no magnetism, and the upper linear slide block (1) and the lower linear slide block (6) are separated from each other, and the ultrasonic probe has no clamping force; in the detection stage, the upper linear sliding block (1) and the lower linear sliding block (6) are close to each other, the electrified electromagnet (14) and the adsorption cylinder (2) are adsorbed to each other, and the ultrasonic probe has clamping force and performs interface rigidity detection work.

5. The interface rigidity detection device based on solid coupling of claim 1 or 2, characterized in that the primary telescopic rod, the secondary telescopic rod and the telescopic rod base body are all in a laminated state at an initial stage, after the positioning telescopic rod completes the positioning and clamping function, the secondary telescopic mechanism is opened in sequence, and the ultrasonic probe moves to a specific extension area.

Technical Field

The invention belongs to the technical field of interface rigidity detection, and particularly relates to an interface rigidity detection device based on solid coupling.

Background

The components of the aircraft engine are connected through bolts and limited by factors such as processing, assembly and the like, so that a plurality of connecting structures exist in an engine rotor system, and the rotor system generates additional unbalance due to the change of a local contact state of the connecting structures, so that the problem of vibration of the whole engine is caused. Therefore, the method has important significance for detecting the interface rigidity of the inner cavity part of the aircraft engine.

In the interface rigidity detection, the ultrasonic detection method has unique detection advantages, and is a better detection method for the interface rigidity detection under the conditions of not damaging the connection structure form and on-line in place. Particularly, in order to enable the ultrasonic signals to be transmitted into the to-be-detected piece better, the couplant is used for removing air between the transducer and the to-be-detected piece and enhancing the transmission performance of sound waves. However, the pressure sensitivity of different couplants is different, and the repeatability and accuracy of detection are affected when the force applied to the transducer is not kept the same.

The existing interface rigidity detection device has the following problems:

1) the accessibility is poor, the inner structure of the position of the air compressor drum disc is narrow, the operation space is limited, the detection equipment is difficult to enter, and the existing device is difficult to carry out the related interface rigidity detection work.

2) The repeatability is poor, the coupling force of the probe is difficult to ensure to be constant, and the repeatability of detection is difficult to ensure.

3) The conventional liquid coupling agent (such as water, glycerol and the like) is used as a coupling layer in the conventional interface rigidity detection, which increases the difficulty and cost of cleaning an aeroengine with a narrow inner cavity.

Disclosure of Invention

The invention aims to solve the problem that the interface rigidity of the aero-engine is difficult to detect, and provides a device for detecting the interface rigidity of an inner cavity part of the aero-engine. The method can be used for carrying out interface rigidity detection in a narrow space of the aeroengine, realizes better repeatability by utilizing the pressure provided by the spring rod, and realizes pollution-free in-situ detection by utilizing a solid coupling mode.

The technical scheme of the invention is as follows:

the utility model provides an interface rigidity detection device based on solid coupling includes device base member 22, linear slide block, adsorbs cylinder 2, rotary disk, electro-magnet 14, the telescopic link base member, the second grade telescopic link, the one-level telescopic link, the ultrasonic probe clamp splice, linear bearing, the spring beam, ultrasonic probe, location telescopic link 4, the linear guide base, linear guide and take spacing bearing end cover 28.

The device base body 22 is of a hollow cylindrical structure, the three positioning telescopic rods 4 are uniformly distributed in the device base body 22, and the three positioning telescopic rods 4 are used for positioning and clamping a circular ring in an aircraft engine; the upper end and the lower end of the device base body 22 are connected with the rotating disc through bearings, and the inner ring with a limiting bearing end cover 28 pressing the bearings is connected with the device base body 22; the convex plate at the top end of the adsorption cylinder 2 is matched with the groove of the end cover 28 with the limit bearing; the connecting rod 27 is respectively connected with the upper rotating disk 3 and the lower rotating disk 5 in a positioning way, so that the rotating synchronization function of the upper rotating disk and the lower rotating disk is realized; the rotating disc is connected with the linear guide rail base, and the linear guide rail base is connected with the linear guide rail; the adsorption cylinder 2 is connected with an upper telescopic rod base body 21, and the electromagnet 14 is connected with a lower telescopic rod base body 7; the adsorption column 2 and the electromagnet 14 are mutually adsorbed to provide clamping displacement for the ultrasonic probe; the telescopic rod base body, the secondary telescopic rod and the primary telescopic rod form a secondary telescopic mechanism together, and the two groups of secondary telescopic mechanisms are formed; the secondary telescopic mechanism is fixedly connected with the linear sliding block, and the linear sliding block moves to drive the secondary telescopic mechanism and the ultrasonic probe to do linear motion; the tail end of the primary telescopic rod is provided with a linear bearing and an ultrasonic probe clamping block, the ultrasonic probe clamping block is used for clamping an ultrasonic probe, and the linear bearing is provided with a spring rod.

The adsorption cylinder 2 and the electromagnet 14 are mutually adsorbed to provide clamping force for the ultrasonic probe; the ultrasonic probe mainly consists of an ultrasonic transducer 29 and a solid coupling layer 30.

The upper spring rods 19 and the lower spring rods 10 generate constant pressure, and ensure that the coupling state and the contact stress state of the ultrasonic transducer 29 and the solid coupling layer 30 are the same.

In the non-detection stage, the electromagnet 14 is not electrified and does not have magnetism, the upper linear slide block 1 and the lower linear slide block 6 are separated from each other, and the ultrasonic probe does not have clamping force; in the detection stage, the upper linear sliding block 1 and the lower linear sliding block 6 are close to each other, the electrified electromagnet 14 and the adsorption cylinder 2 are adsorbed to each other, and at the moment, the ultrasonic probe has clamping force to perform interface rigidity detection work.

The first-stage telescopic rod, the second-stage telescopic rod and the telescopic rod base body are all in a laminated state at the initial stage, after the positioning telescopic rod completes the positioning and clamping functions, the second-stage telescopic mechanism is opened in sequence, and the ultrasonic probe moves to a specific extension area.

The three evenly distributed positioning telescopic rods ensure the concentric positioning effect of the device base body 22 and the inner circular ring of the aero-engine under the action of the same spring force.

The bearing end cap 28 with the limit functions to prevent the bearing from falling off and to provide a rotational limit function.

The invention has the beneficial effects that: the method has the characteristics that the method can be used for carrying out interface rigidity detection in a narrow space of an aeroengine, can realize better repeatability by utilizing pressure provided by a spring rod, and avoids pollution caused by a liquid coupling agent by utilizing a solid coupling mode.

Drawings

FIG. 1 is a front view of an interface rigidity detection device based on solid coupling according to the present invention;

FIG. 2 is a side view of an interface stiffness detection apparatus based on solid coupling according to the present invention;

FIG. 3 is a top view of an interface stiffness detection apparatus based on solid coupling according to the present invention;

FIG. 4 is a partial view of an interface stiffness detection apparatus based on solid coupling according to the present invention;

in the figure: 1, a linear sliding block is arranged above the base; 2, adsorbing the cylinder; 3, rotating the disc above; 4, positioning the telescopic rod; 5, rotating the disc below; 6, a linear sliding block is arranged below the sliding block; 7, a telescopic rod base body is arranged below the lower part; 8, a secondary telescopic rod is arranged below the lower part; 9, a first-stage telescopic rod is arranged below the lower part of the lower part; 10 a lower spring rod; 11 lower linear bearing; 12 below the ultrasonic probe clamping block; 13 a lower ultrasonic probe; 14 an electromagnet; 15 an upper ultrasonic probe; 16 upper ultrasonic probe clamping blocks; 17, a first-stage telescopic rod is arranged above the upper part; a linear bearing above 18; 19 an upper spring rod; 20, a two-stage telescopic rod above; 21, an upper telescopic rod base body; 22 a device substrate; 23 linear guide rail base above; 24 upper linear guide rails; a linear guide rail base below 25; 26 a lower linear guide rail; 27 connecting rods; 28 bearing end covers with limit; 29 an ultrasonic transducer; 30 solid coupling layer

Detailed Description

The following is a specific embodiment of the present invention, and the technical solution of the present invention is further described with reference to the accompanying drawings.

To facilitate an understanding of the invention, the invention will now be described more fully with reference to the accompanying drawings. It is to be understood that such description is merely illustrative of the features and advantages of the present invention, and is not intended to limit the scope of the claims.

As shown in fig. 1 to 4, the present invention is based on a device substrate 22, and the whole device is constructed in the form of a top-bottom structure according to the requirements of ultrasonic transmission detection. The device base body 22 is respectively connected with the upper rotating disk 3 and the lower rotating disk 5 through bearings; the bearing end cap 28 also provides a rotational limit function while preventing the bearing from falling off. The upper rotating disk 3, the upper linear guide rail base 23 and the upper linear guide rail 24 are connected in sequence by bolts, and the lower rotating disk 5, the lower linear guide rail base 25 and the lower linear guide rail 26 are connected in sequence by bolts. The lower telescopic rod base body 7 is respectively combined with a lower two-stage telescopic rod 8 and a lower one-stage telescopic rod 9 to realize a two-stage telescopic function; the upper telescopic rod base body 21 is respectively combined with the upper two-stage telescopic rod 20 and the upper one-stage telescopic rod 17 to realize a two-stage telescopic function. The upper telescopic rod base body 21 is fixedly connected with the upper linear sliding block 1, and the lower telescopic rod base body 7 is fixedly connected with the lower linear sliding block 6. The tail end of the upper first-stage telescopic rod 17 is provided with an upper linear bearing 18 and an upper ultrasonic probe clamping block 16, the upper ultrasonic probe clamping block 16 clamps the upper ultrasonic probe 15, and the upper linear bearing 18 is connected with an upper spring rod 19; the tail end of the lower primary telescopic rod 9 is provided with a lower linear bearing 11 and a lower ultrasonic probe clamping block 12, the lower ultrasonic probe clamping block 12 clamps a lower ultrasonic probe 13, and the lower linear bearing 11 is connected with a lower spring rod 10.

The middle part 22 of the device matrix is of a hollow structure, and the adsorption cylinder 2 and the electromagnet 14 are mutually adsorbed to provide clamping displacement for the ultrasonic probe.

The implementation steps of the invention are as follows:

1) an initial stage; the three uniformly distributed positioning telescopic rods 4 are controlled by electromagnetic force to keep a tightening state, the lower two-stage telescopic rod 8 and the lower one-stage telescopic rod 9 are contracted and folded in the lower telescopic rod base body 7, and the upper two-stage telescopic rod 20 and the upper one-stage telescopic rod 17 are contracted and folded in the upper telescopic rod base body 21. At the moment, the whole detection device is in a contraction state and enters a narrow cavity structure of the aircraft engine.

2) A detection preparation stage; when the aircraft engine reaches a designated position, the electromagnetic force of the positioning telescopic rod 4 is disconnected, and the positioning telescopic rod is ejected out by spring force and is clamped with an inner circular ring of the aircraft engine. The three uniformly-distributed positioning telescopic rods 4 ensure the concentric positioning effect of the device base body 22 and the inner circular ring of the aircraft engine under the action of the same spring force. After the positioning telescopic rod 4 completes the positioning and clamping functions, the two-stage telescopic function of the two-stage telescopic mechanism is sequentially opened, so that the ultrasonic probe moves to a specific extension area. The rotating disc rotates for a specific angle, and the convex plate at the top end of the adsorption cylinder 2 is matched with the groove of the bearing end cover 28, so that the ultrasonic probe is just positioned between the two bolts.

3) A detection proceeding stage; the upper linear slide block 1 and the lower linear slide block 6 are close to each other, so that the electromagnet 14 and the adsorption cylinder 2 are adsorbed to each other. Due to the extension of the positioning telescopic rod 4, the central position of the device base body 22 is already in a hollow state. A10N clamping force is formed between the upper ultrasonic probe 15 and the lower ultrasonic probe 13 and the measured structure of the aircraft engine, so that the coupling state and the contact stress state of the ultrasonic transducer 29 and the solid coupling layer 30 are the same. After the interface rigidity detection of a local position is finished, the electromagnet 14 cuts off the electromagnetic force, the upper rotating disk 3 and the lower rotating disk 5 rotate for a specific angle, the upper ultrasonic probe 15 and the lower ultrasonic probe 13 are positioned at the next detection position according to the limit of the groove at the bearing end cover 28, and the steps are repeated.

4) At the end of the detection phase, the electromagnet 14 turns off the electromagnetic force, which separates from the adsorption cylinder 2 as the linear slide separates. The first-stage telescopic rod and the second-stage telescopic rod are mutually contracted and folded in the telescopic rod base body. The three uniformly distributed positioning telescopic rods are controlled by electromagnetic force to be converted into a tightening state, and the whole device is moved out of an inner cavity structure of the aero-engine.