Auxiliary tool, device and method for three-coordinate detection of aero-engine diffuser

Abstract

The invention discloses an auxiliary tool, device and method for three-coordinate detection of an aero-engine diffuser, and belongs to the field of aero-engine detection.The auxiliary tool comprises a bottom plate, a tool positioning unit used for fixing the position of the bottom plate, a diffuser center shaft positioning unit, a diffuser axial locking unit and a datum plane construction unit; the diffuser center axis positioning unit can coincide the diffuser with the center axis of the bottom plate so as to achieve initial positioning of the diffuser, aiming at the problem that the diffuser is poor in appearance consistency, the tool adopts the reference plane construction unit, the reference plane construction unit is arranged at the front edge of a blade and is tangent to the blade, flexible positioning of the diffuser can be achieved, and the appearance consistency of the diffuser is improved. The problem that the positioning block is not flatly cushioned due to the fact that the state of the casting diffuser part is unstable is solved; the diffuser is locked after being positioned through the diffuser axial locking unit, so that the accuracy and the efficiency of three-coordinate detection are ensured; the tool is simple in structure and principle, and the detection precision and the detection efficiency are improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine detection, and in particular relates to an auxiliary tool, a device and a method for three-coordinate detection of an aero-engine diffuser. Background Art

[0002] The diffuser of an aircraft engine is an annular, rotating integral casting component. Currently, the casting state uses three-coordinate measurement to detect its dimensional characteristics. According to the measurement requirements, it is necessary to detect the inner and outer channel diameters of one end face of the diffuser, and the axial and radial position of the diffuser blades; the other end face needs to detect the contour of the inner and outer flow channel surfaces of the diffuser.

[0003] The existing detection method of aircraft engine diffusers has the following disadvantages: First, the detection process has a low degree of automation: the existing aircraft engine diffuser detection process adopts a three-coordinate detection method. Due to the unstable state of the casting and the uncertainty of the detection position, the operator needs to manually collect points to establish a basic coordinate system each time, and the detection efficiency is low; Second, the method of establishing the reference plane has a large deviation: according to the design requirements, the reference plane of the aircraft engine diffuser is at the leading edge of the blade. Since it cannot be directly collected manually, the operator uses the method of placing pads to convert the coordinate data to the reference plane. Compared with the direct collection method, the method of establishing the reference plane by data conversion has a large deviation.

[0004] It can be seen that the existing inspection measures for aircraft engine diffusers, due to the unstable casting state and uncertain inspection position, require operators to manually collect points to establish a basic coordinate system each time, resulting in low inspection efficiency and low inspection accuracy. Summary of the invention

[0005] The present invention provides an auxiliary tooling, device and method for three-coordinate detection of an aircraft engine diffuser, so as to solve the technical problems that in existing detection measures, due to the unstable state of the casting and the uncertainty of the detection position, the operator needs to manually collect points to establish a basic coordinate system each time, resulting in low detection efficiency and low detection accuracy.

[0006] In order to achieve the above object, the present invention adopts the following technical contents:

[0007] An auxiliary tool for three-coordinate detection of an aircraft engine diffuser, comprising a base plate and a tool positioning unit arranged on a three-coordinate measuring machine table;

[0008] The tooling positioning unit is used to fix the position of the base plate;

[0009] The bottom plate is provided with a diffuser central axis positioning unit, a diffuser axial locking unit and a reference plane construction unit; when the diffuser is located on the auxiliary tooling:

[0010] The diffuser central axis positioning unit is used to make the diffuser coincide with the central axis of the base plate;

[0011] The diffuser axial locking unit is used to lock the axial movement of the diffuser;

[0012] The reference plane construction unit is located at the leading edge of the blade of the diffuser and is vertically tangent to the blade, and is used to construct a reference plane.

[0013] Furthermore, the tool positioning unit includes a first tool positioning pin and a second tool positioning pin inserted on the table of the three-dimensional coordinate measuring machine. The first tool positioning pin and the second tool positioning pin are arranged along the outer circle of the base plate and are tangent to the outer circle of the base plate.

[0014] Furthermore, the diffuser central axis positioning unit includes a first diffuser positioning pin and a second diffuser positioning pin inserted in the circumferential direction of the base plate. When the diffuser is tangent to the first diffuser positioning pin and the second diffuser positioning pin at the same time, the diffuser coincides with the central axis of the base plate.

[0015] Furthermore, the reference plane construction unit includes a plurality of slide grooves evenly distributed between the outer circle and the center of the base plate, and a slider is provided in each slide groove; when the diffuser is located on the auxiliary tooling, each slider is located at the leading edge of the blade and is vertically tangent to the blade; and the reference plane is constructed according to the vertical plane of each slider.

[0016] Furthermore, the diffuser axial locking unit adopts a positioning block. When the blades of the diffuser are determined, the positioning block is inserted between the two blades and inserted into the sliding groove of the bottom plate.

[0017] A three-coordinate detection device for an aircraft engine diffuser comprises a three-coordinate measuring machine and the above-mentioned auxiliary tooling.

[0018] A three-coordinate detection method for an aircraft engine diffuser, based on the above auxiliary tooling or the above three-coordinate detection device, comprises:

[0019] Fixing the position of the bottom plate of the auxiliary tooling by using the tooling positioning unit;

[0020] Positioning the diffuser using a diffuser central axis positioning unit so that the diffuser coincides with the central axis of the base plate;

[0021] Adjusting the reference plane construction unit so that the reference plane construction unit is located at the leading edge of the blade of the diffuser and is vertically tangent to the blade;

[0022] The axial movement of the diffuser is locked by using the diffuser axial locking unit;

[0023] Acquire the current position of the reference plane construction unit, and construct the reference plane to determine the vertical direction of the coordinate system;

[0024] An external rough reference coordinate system is established according to the vertical direction of the coordinate system;

[0025] The external rough reference coordinate system is called to complete the detection of the outer flow channel surface, inner flow channel surface, blade position, and inner and outer channel diameters of the diffuser.

[0026] Furthermore, it specifically includes:

[0027] Place the base plate of the auxiliary tooling on the table of the three-dimensional coordinate measuring machine, and adjust the position of the base plate until the outer circle of the base plate is tangent to the first tooling locating pin and the second tooling locating pin at the same time;

[0028] Placing the diffuser to be inspected on the bottom plate of the auxiliary tooling, and adjusting the position of the diffuser until the diffuser is tangent to the first diffuser positioning pin and the second diffuser positioning pin at the same time;

[0029] Adjust the position of each slider on the slide slot so that each slider is located at the leading edge of the blade and is vertically tangent to the blade;

[0030] Insert the positioning block between the two blades and into the slide groove of the bottom plate;

[0031] Collect the current position of each slider and construct a reference plane to determine the vertical direction of the coordinate system;

[0032] An external rough reference coordinate system is established according to the vertical direction of the coordinate system;

[0033] The external rough reference coordinate system is called to complete the detection of the outer flow channel surface, inner flow channel surface, blade position, inner channel and outer channel of the diffuser.

[0034] Furthermore, the specific steps of establishing an external rough reference coordinate system according to the vertical direction of the coordinate system are as follows:

[0035] Taking the vertical direction of the coordinate system as the reference, construct a straight line between the center of the outer circle of the base plate and a point on the left end face of the positioning block as the reference axis direction;

[0036] The external reference coordinate system is established in the form of points, lines and surfaces according to the right-hand rule, thereby completing the establishment of the external rough reference coordinate system.

[0037] Furthermore, the stylus of the three-dimensional coordinate measuring machine is directed vertically downward to construct an automatic touch inner circle at a first preset cross-sectional height of the outer flow path surface of the diffuser, and the external rough reference coordinate system is called back, and the center of the constructed automatic touch inner circle is used as the center of the horizontal coordinate system to establish a first external fine reference coordinate system, and the outer flow path surface of the diffuser is detected according to the first external fine reference coordinate system;

[0038] The stylus of the three-dimensional coordinate measuring machine is pointed vertically downward to construct an automatic touch inner circle at the second preset cross-section height of the inner flow path surface of the diffuser, and the external rough reference coordinate system is called back. The center of the constructed automatic touch inner circle is used as the center of the horizontal coordinate system to establish a second external fine reference coordinate system, and the inner flow path surface of the diffuser is inspected according to the second external fine reference coordinate system;

[0039] The external coarse reference coordinate system is called back to make the first reference blade as the starting blade and the reference direction, and the high point command is called in the vertical direction of the first reference blade, the second reference blade, the third reference blade, and the fourth reference blade in the radial direction of the diffuser, respectively. The reference plane is constructed with the four high points of the first reference blade, the second reference blade, the third reference blade, and the fourth reference blade, and the external coarse reference coordinate system is called back to construct the third external fine reference coordinate system, and the automatic circle command is called to detect the diameters of the inner and outer channels of the diffuser respectively; the high point command is called, and the third external fine reference coordinate system is rotated to collect the high point of each blade in the vertical direction, and the three blades with the smallest deviation are evenly selected as the machining axial direction reference, and the rotation coordinate system command is called to realize the detection of the position of each blade.

[0040] Compared with the prior art, the present invention has the following beneficial effects:

[0041] The invention provides an auxiliary tool for three-coordinate detection of an aircraft engine diffuser. The tool comprises a base plate and a tool positioning unit for fixing the position of the base plate, a diffuser central axis positioning unit, a diffuser axial locking unit and a reference plane construction unit; the diffuser central axis positioning unit can make the diffuser coincide with the central axis of the base plate to achieve initial positioning of the diffuser. Aiming at the problem of poor consistency of the diffuser appearance, the tool adopts a reference plane construction unit, and the reference plane construction unit is placed on the leading edge of the blade and tangent to the blade, so as to achieve flexible positioning of the diffuser, and avoid the problem of uneven positioning block pad placement due to the unstable state of the casting diffuser parts; the diffuser is locked after positioning by the diffuser axial locking unit, so as to ensure the accuracy and efficiency of three-coordinate detection; the tool has a simple structure and principle, is easy to operate and implement, improves detection accuracy and detection efficiency, and has good popularization and application value.

[0042] Preferably, in the present invention, the first tooling locating pin and the second tooling locating pin are arranged along the outer circle of the base plate and are tangent to each other, thereby ensuring stable positioning of the base plate on the three-dimensional coordinate measuring machine and improving positioning accuracy.

[0043] Preferably, in the present invention, the first diffuser positioning pin and the second diffuser positioning pin are simultaneously tangent to the diffuser to ensure that the diffuser and the center axis of the base plate coincide with each other, thus providing a basis for subsequent accurate detection.

[0044] Preferably, in the present invention, a flexible reference plane construction unit is constructed by means of the slide groove and slider structure on the bottom plate, which can be accurately positioned on the leading edge of the diffuser blade and vertically tangent to the blade, thereby ensuring flexible positioning of the diffuser and providing a reliable basis for constructing the reference plane.

[0045] Preferably, in the present invention, a positioning block is inserted between the two blades and in the slide groove of the bottom plate, thereby effectively locking the axial movement of the diffuser and ensuring stability during the detection process.

[0046] The present invention also provides a three-coordinate detection device for an aircraft engine diffuser, including the above-mentioned auxiliary tooling; the device integrates high-precision measuring equipment and special tooling, meets the three-coordinate detection requirements for diffuser castings, has strong versatility, and realizes comprehensive and efficient detection of aircraft engine diffusers.

[0047] The present invention also provides a three-coordinate detection method for an aircraft engine diffuser. Based on the above-mentioned auxiliary tooling or three-coordinate detection device, in the method, a tooling positioning unit is used to fix the position of a base plate of the auxiliary tooling; a diffuser central axis positioning unit is used to position the diffuser so that the diffuser coincides with the central axis of the base plate; a reference plane construction unit is adjusted so that the reference plane construction unit is located at the leading edge of the diffuser blade and is vertically tangent to the blade; an axial locking unit of the diffuser is used to lock the axial movement of the diffuser; the current position of the reference plane construction unit is collected, and a reference plane is constructed to determine the vertical direction of the coordinate system; an external rough reference coordinate system is established according to the vertical direction of the coordinate system; finally, the external rough reference coordinate system is called to complete the detection of the outer flow channel surface, inner flow channel surface, blade position, and inner and outer channel diameters of the diffuser; a systematic method is provided for the accurate detection of the diffuser. The method is reasonable and perfect, and can realize the three-coordinate full-size detection process of the diffuser.

[0048] Preferably, in the present invention, the processes of precise placement of the tooling and diffuser, slider adjustment, positioning block insertion, reference plane acquisition, etc. are specifically introduced, so that the detection method is more operable and practical.

[0049] Preferably, the present invention specifically describes how to establish an external rough reference coordinate system according to the vertical direction of the coordinate system. By constructing the reference axis direction and following the right-hand rule, the accuracy and reliability of the coordinate system are ensured, providing an important basis for subsequent precise detection.

[0050] Preferably, in the present invention, an external fine reference coordinate system is established by calling back the external coarse reference coordinate system, thereby realizing the detection of the outer flow channel surface, the inner flow channel surface, the inner channel and the outer channel diameters and the blade position; the external fine reference coordinate system ensures higher precision detection and meets the requirements of high precision detection. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Attached Figure 1 It is a structural schematic diagram of a three-coordinate detection device for an aircraft engine diffuser provided by an embodiment of the present invention;

[0052] Attached Figure 2 is a top view of the position detection of the connection between the diffuser and the auxiliary tooling provided by an embodiment of the present invention;

[0053] Attached Figure 3 It is a side view of position detection of the connection between the diffuser and the auxiliary tooling provided by an embodiment of the present invention;

[0054] Attached Figure 4 It is an overall schematic diagram of the position detection of the connection between the diffuser and the auxiliary tooling provided by the embodiment of the present invention;

[0055] Attached Figure 5 is a top view of the contour detection of the connection between the diffuser and the auxiliary tooling provided by the embodiment of the present invention;

[0056] Attached Figure 6 is a structural schematic diagram of contour detection of a diffuser connected to an auxiliary tooling provided by an embodiment of the present invention;

[0057] Attached Figure 7 It is a top view of an auxiliary tooling for three-coordinate detection of an aircraft engine diffuser provided by an embodiment of the present invention;

[0058] Attached Figure 8 It is a structural schematic diagram of an auxiliary tooling for three-coordinate detection of an aircraft engine diffuser provided by an embodiment of the present invention;

[0059] Attached Fig. 9 is a top view of a diffuser provided by an embodiment of the present invention;

[0060] Attached Fig.10 is a schematic structural diagram of a diffuser provided by an embodiment of the present invention;

[0061] Attached Fig.11 Schematic diagram of the bottom plate of the tooling provided in the embodiment of the present invention

[0062] Attached Fig.12 is a schematic diagram of a slider provided by an embodiment of the present invention;

[0063] Attached Fig.13 is a schematic diagram of a tooling positioning pin provided in an embodiment of the present invention;

[0064] Attached Fig.14 is a schematic diagram of a diffuser positioning pin provided in an embodiment of the present invention;

[0065] Attached Fig.15 is a schematic diagram of a positioning block provided in an embodiment of the present invention;

[0066] Attached Fig.16 The present invention is a flow chart of a three-coordinate detection method for an aircraft engine diffuser.

[0067] Reference numerals:

[0068] 1- auxiliary tooling, 2- three-dimensional measuring machine, 3- first diffuser locating pin, 4- first slider, 5- diffuser, 6- bottom plate, 7- first tooling locating pin, 8- second diffuser locating pin, 9- second slider, 10- second tooling locating pin, 11- third slider, 12- positioning block, 13- blade, 14- outer flow channel surface, 15- inner flow channel surface, 16- first reference blade, 17- second reference blade, 18- third reference blade, 19- fourth reference blade, 20- slide groove. DETAILED DESCRIPTION

[0069] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail in the following specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0070] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0071] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0072] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0073] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0074] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0075] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0076] Example 1

[0077] In combination with what was mentioned in the background technology, the existing detection method of aircraft engine diffusers has the following disadvantages: First, the detection process has a low degree of automation: the existing aircraft engine diffuser detection process adopts a three-coordinate detection method. Due to the unstable state of the casting and the uncertainty of the detection position, the operator needs to manually collect points each time to establish a basic coordinate system, and the detection efficiency is low; Second, the method of establishing the reference plane has a large deviation: According to the design requirements, the reference plane of the aircraft engine diffuser is at the leading edge of the blade. Since it cannot be directly collected manually, the operator uses the method of placing pads to convert the coordinate data to the reference plane. Compared with the direct collection method, the method of establishing the reference plane by data conversion has a large deviation; that is, a reasonable, accurate and efficient three-coordinate measurement method is proposed to improve the detection efficiency of aircraft engine diffusers.

[0078] In order to solve the above problems, the present invention provides an auxiliary tooling, a detection device and a detection method for three-coordinate detection of an aircraft engine diffuser. The use of the tooling, the device and the method can realize high-precision detection of the aircraft engine diffuser and achieve the following purposes:

[0079] First, design auxiliary tooling to improve the degree of automation of the detection process; design standardized auxiliary tooling to reduce manual operation and improve the automation level of diffuser three-coordinate detection; second, propose a three-coordinate detection method for aircraft engine diffusers, optimize the program design process, solidify the measurement path, and improve detection accuracy.

[0080] The present invention is further described in detail below with reference to the accompanying drawings and embodiments:

[0081] The present embodiment provides an auxiliary tooling for three-coordinate detection of an aircraft engine diffuser, comprising a base plate 6, a tooling positioning unit, and a diffuser central axis positioning unit, a diffuser axial locking unit and a reference surface construction unit arranged on the base plate 6, wherein the tooling positioning unit is arranged on the table of a three-coordinate measuring machine 2.

[0082] Among them, the tooling positioning unit is used to fix the position of the base plate 6; when the diffuser 5 is located on the auxiliary tooling 1: the diffuser central axis positioning unit is used to make the diffuser 5 coincide with the central axis of the base plate 6; the diffuser axial locking unit is used to lock the axial movement of the diffuser 5; the reference plane construction unit is located at the leading edge of the blade 13 of the diffuser 5 and is vertically tangent to the blade 13, and is used to construct a reference plane.

[0083] Combination Fig. 9 and Fig.10 As shown, the diffuser 5 is a circular casting having a plurality of blades 13 in the circumferential direction.

[0084] like Figures 2 to 8 As shown, combined Fig.13 As shown, in this embodiment, the tooling positioning unit includes a first tooling positioning pin 7 and a second tooling positioning pin 10 inserted on the table of the three-dimensional coordinate measuring machine 2. The first tooling positioning pin 7 and the second tooling positioning pin 10 are arranged along the outer circle of the base plate 6 and are tangent to the outer circle of the base plate 6.

[0085] like Fig.14 As shown, in this embodiment, the diffuser central axis positioning unit includes a first diffuser positioning pin 3 and a second diffuser positioning pin 8 inserted in the circumferential direction of the base plate 6. When the diffuser 5 is tangent to the first diffuser positioning pin 3 and the second diffuser positioning pin 8 at the same time, the diffuser 5 coincides with the central axis of the base plate 6.

[0086] like Fig.12 As shown, in this embodiment, the reference plane construction unit includes a plurality of slide grooves 20 evenly distributed between the outer circle and the center of the base plate 6, and each slide groove 20 is provided with a slider, specifically a first slider 4, a second slider 9 and a third slider 11, and a sliding pad can be used to meet the flexibility requirements and prevent damage to the casting; when the diffuser 5 is located on the auxiliary tooling 1, each slider is located at the leading edge of the blade 13 and is vertically tangent to the blade 13; the reference plane is constructed according to the vertical plane of each slider.

[0087] like Fig.15 As shown, in this embodiment, the diffuser axial locking unit adopts a positioning block 12 . When the blades 13 of the diffuser 5 are determined, the positioning block 12 is inserted between the two blades 13 and inserted into the slide groove 20 of the bottom plate 6 .

[0088] More specifically, Figure 1 As shown, this embodiment provides a three-coordinate detection device for an aircraft engine diffuser, comprising the above-mentioned auxiliary tooling for three-coordinate detection of an aircraft engine diffuser and a three-coordinate measuring machine 2, namely, the auxiliary tooling 1.

[0089] In auxiliary tooling 1, combined Figure 2 , 7 , 8, 9 and 10, wherein the first tooling locating pin 7 and the second tooling locating pin 10 are fixed in the locating holes of the marble table top of the three-dimensional coordinate measuring machine 2, and the tooling base plate 6, as the tooling body, is placed on the marble table top of the three-dimensional coordinate measuring machine 2 and is tangent to the first tooling locating pin 7 and the second tooling locating pin 10, thereby fixing the specific position of the tooling base plate 6.

[0090] The first diffuser locating pin 3 and the second diffuser locating pin 8 are connected to the tooling base plate 6. When the diffuser 5 is placed for inspection, the first diffuser locating pin 3 and the second diffuser locating pin 8 are tangent to the maximum outer circle of the diffuser 5. According to the manufacturing requirements of the auxiliary tooling 1, when the first diffuser locating pin 3 and the second diffuser locating pin 8 are tangent to the maximum outer circle of the diffuser 5, the theoretical central axes of the tooling base plate 6 and the diffuser 5 coincide, thereby determining the relative position of the diffuser 5 and the tooling base plate 6.

[0091] The first slider 4, the second slider 9, and the third slider 11 are placed in the three slide grooves of the tooling bottom plate 6 respectively. When the outer flow path surface 14 and the inner flow path surface 15 of the diffuser 5 are detected, the three sliders are placed at the leading edge of the blade 13 and are tangent to the leading edge of the blade 13 of the diffuser 5 in the vertical direction, thereby determining the reference plane. When detecting the position of the blade 13 of the diffuser 5, the positioning block 12 is placed between the two blades 13 and inserted into the vertical slide groove 20 of the tooling bottom plate 6, thereby controlling the axial rotation of the diffuser 5.

[0092] This embodiment provides an auxiliary tool or detection device for three-coordinate detection of an aircraft engine diffuser, such as Fig.16 As shown, the specific working principle is as follows:

[0093] Place the bottom plate 6 of the auxiliary tooling 1 on the table of the three-dimensional coordinate measuring machine 2, and adjust the position of the bottom plate 6 until the outer circle of the bottom plate 6 is tangent to the first tooling positioning pin 7 and the second tooling positioning pin 10 at the same time; place the diffuser 5 to be tested on the bottom plate 6 of the auxiliary tooling 1, and adjust the position of the diffuser 5 until the diffuser 5 is tangent to the first diffuser positioning pin 3 and the second diffuser positioning pin 8 at the same time; adjust the position of each slider on the slide 20 so that each slider is located at the leading edge of the blade 13 and is vertically tangent to the blade 13; insert the positioning block 12 between the two The blades 13 are inserted into the slide groove 20 of the bottom plate 6; the current position of each slider is collected, and a reference plane is constructed to determine the vertical direction of the coordinate system; an external rough reference coordinate system is established according to the vertical direction of the coordinate system; the external rough reference coordinate system is called to complete the detection of the outer flow path surface 14, the inner flow path surface 15, the blade 13 position, and the inner channel and the outer channel of the diffuser 5; the detection process is specifically shown in 16, including: manually collecting feature points of components such as tooling sliders and tooling bottom plates, and constructing an external rough reference coordinate system in the form of points, lines, and surfaces;

[0094] Call the external rough reference coordinate system to automatically build a precise reference coordinate system for dimensional characteristics to detect the inner and outer flow path surfaces of the diffuser; call the external rough reference coordinate system to automatically build a precise reference coordinate system for dimensional characteristics to detect the inner and outer channel diameters and blade position of the diffuser.

[0095] It can be seen that the above-mentioned tools and devices not only meet the production needs on site but also meet economic benefits. Considering the problem of poor appearance consistency of diffuser castings on site, a positioning method using a slider is specially designed to replace the positioning method of the fixed block. The flexible positioning method of the casting avoids the problem of uneven positioning block pads due to the unstable state of the casting diffuser parts. According to the operating principle of the three-coordinate detection device, a three-coordinate full-size detection method of the diffuser that conforms to the detection device is proposed.

[0096] The above detection method is characterized by novel structural design of the detection device, complete and reliable functions, and can assist in completing the full-size automated detection of aircraft engine diffusers; the three-coordinate detection method of aircraft engine diffusers is reasonable and perfect, realizing the three-coordinate full-size detection process of diffusers.

[0097] Example 2

[0098] This embodiment also provides a three-coordinate detection method for an aircraft engine diffuser, which specifically includes:

[0099] Combined with Figure 1 , 7As shown in Figures 1 and 8, the method for establishing the external rough reference coordinate system is as follows: according to the detection principle of the three-dimensional coordinate measuring machine, manually collect the vertical planes of the first slider 4, the second slider 9, and the third slider 11 to construct a reference plane and determine the vertical direction; collect the outer cylindrical surface of the tooling base plate 6 to determine the center position; place the positioning block 12 in the slide groove 20 of the tooling base plate 6, collect a point on the left end surface of the positioning block 12, and construct a straight line with the center of the outer circle of the tooling base plate 6 and a point on the left end surface of the positioning block 12 as one of the reference axis directions; establish the external reference coordinate system according to the right-hand rule in the form of points, lines, and surfaces and save it, thereby completing the establishment of the external rough reference coordinate system.

[0100] Combined with Figure 1 , 5 As shown in , 6, 9, and 10, the detection method of the outer flow passage surface 14 and the inner flow passage surface 15 of the diffuser 5 is as follows:

[0101] According to the design requirements, the measurement reference plane of the diffuser 5 is the leading edge position of the blade 13. The first slider 4, the second slider 9, and the third slider 11 are slid, and the diffuser 5 is placed so that the leading edges of every two blades 13 are vertically tangent to the first slider 4, the second slider 9, and the third slider 11 respectively; the position of the diffuser 5 is adjusted so that it is tangent to the first diffuser locating pin 3 and the second diffuser locating pin 8, and the starting position of the blade 13 of the diffuser 5 corresponds to the horizontal axis direction of the base plate 6.

[0102] Recall the external rough reference coordinate system, point the measuring needle of the coordinate measuring machine 2 vertically downward, and construct an automatic touch inner circle at a certain section height of the outer flow channel surface 14 of the diffuser 5. Recall the external rough reference coordinate system, and use the constructed center of the automatic touch inner circle as the center of the horizontal coordinate system, thereby establishing a coordinate system with higher accuracy, i.e., the first external fine reference coordinate system. Call the loop and rotate coordinate command, rotate the coordinate system around the vertical axis to the detection direction of the relative orientation, measure the detection points of different sections, and complete the measurement of the outer flow channel surface 14. Recall the external rough reference coordinate system, assign values ​​and call the loop command, so that the measuring needle rotates different measuring needle angles in different orientations, and construct an automatic touch inner circle at a certain section height of the inner flow channel surface 15 of the diffuser 5. Recall the external rough reference coordinate system, and use the constructed center of the automatic touch outer circle as the center of the horizontal coordinate system, thereby establishing a coordinate system with higher accuracy, i.e., the second external fine reference coordinate system. The loop and coordinate rotation commands are called to rotate the coordinate system around the vertical axis to the detection direction of the corresponding orientation, and the detection points of different cross sections are measured to complete the measurement of the inner flow channel surface 15.

[0103] Combined with Figure 1 , 2 As shown in , 3, 4, and 9, the method for detecting the position of the blade 13 and the inner and outer channels is as follows:

[0104] Slide the first slider 4, the second slider 9, and the third slider 11 to the inner side of the tooling base plate 6, so that the leading edge position of the blade 13 of the diffuser 5 is vertically upward, place the diffuser 5 on the tooling base plate 6, so that it is tangent to the first diffuser positioning pin 3 and the second diffuser positioning pin 8, and make the starting position of the diffuser blade 13 correspond to the horizontal direction of the tooling base plate 6, insert the positioning block 12 in the empty position between the two blades, and make the first reference blade 16 tangent to the positioning block 12, call back the external rough reference coordinate system, and use the first reference blade 16 as the starting blade and the reference direction, and call the high point command in the vertical direction of the first reference blade 16, the second reference blade 17, the third reference blade 18, and the fourth reference blade 19 of the radial measurement distance of the diffuser 5 respectively, and construct a reference plane with the four high points of the first reference blade 16, the second reference blade 17, the third reference blade 18, and the fourth reference blade 19, and call back the coordinate system to construct a coordinate system with higher accuracy, that is, the third external fine reference coordinate system. The automatic circle command is called to detect the inner and outer channel diameters of the diffuser 5 respectively, the high point command is called, and the coordinate system is rotated to collect the vertical high point of each blade 13, and the three blades with the smallest deviation are evenly selected as the axial direction reference of the machining. The rotating coordinate system command is called to specify the measurement distance in the radial direction of the diffuser 5 to detect the position of each blade 13.

[0105] More specific implementation steps include:

[0106] Step S110 , manually collect the feature points of the tooling slider, tooling base plate 6 and other components, and construct an external rough reference coordinate system in the form of points, lines and surfaces.

[0107] Specifically, according to the detection principle of the three-coordinate measuring machine, in the manual mode of the PC-DMIS program editing window, the horizontal end faces of the three sliders are touched to construct plane features; four points on the outer cylindrical surface of the tooling base plate are evenly touched to construct circle features; the positioning block 12 is placed in the slide groove 20, and a point on the left end face of the positioning block 12 is touched to construct a point feature; a straight line feature is constructed with the center of the outer circle of the tooling base plate 6 and a point on the left end face of the positioning block 12, the start coordinate system is called back, the positive coordinate Z direction is found to the constructed plane feature, the X and Y axes are translated to the center position of the constructed circle feature, the Y negative direction is rotated to the constructed straight line feature, and the Z axis is translated to the constructed plane feature, thereby establishing an external reference coordinate system and saving it.

[0108] Step S120 , calling an external rough reference coordinate system, automatically constructing a precise reference coordinate system for dimensional characteristics, and detecting the outer flow path surface 14 and the inner flow path surface 15 of the diffuser 5 .

[0109] Specifically, the outer flow channel surface 14 and the inner flow channel surface 15 are inspected, and 16 characteristic points are evenly distributed in the circumferential direction of each section at 5 cross-sectional distances between the inner and outer flow channel surfaces, and the distance from the characteristic point to the rotation center is inspected and evaluated.

[0110] Among them, according to the detection principle of the three-dimensional coordinate measuring machine, the established external reference coordinate system is called in the automatic mode of the PC-DMIS program editing window, and the automatic circle feature is constructed at the middle distance between the outer flow channel surface 14 and the reference plane, and the external reference coordinate system is called back, and the X and Y axes are translated to the center position of the constructed automatic circle feature, so as to establish a more accurate reference coordinate system. The WHILE loop statement is called, the coordinate system rotation angle is assigned to 360 / 16 degrees, and the rotation offset coordinate system is called back in the loop statement. The point features of the 5 cross sections in each orientation are touched in the loop statement, and the position of the 5 point features is evaluated and the loop command is ended, thereby completing the detection of the outer flow channel surface 14.

[0111] Among them, the basic principle of the inner flow channel surface detection method is the same as that of the outer flow channel surface detection method. The WHILE loop statement is called at the middle distance between the inner flow channel surface 15 and the reference plane, the coordinate system rotation angle and the probe rotation angle are evenly assigned, the feature points are touched, and the feature circle is constructed with the touched feature points. The X and Y axes are translated to the center position of the constructed feature circle, thereby establishing a more accurate reference coordinate system. The WHILE loop statement is called, the coordinate system rotation angle is assigned to 360 / 16 degrees, the probe rotation angle is assigned to 360 / 16 degrees, and the rotation offset coordinate system is called back in the loop statement. The point features of the 5 cross sections in each orientation are touched in the loop statement, and the position of the 5 point features is evaluated before the loop command is ended, thereby completing the detection of the inner flow channel surface 15.

[0112] Step S130 , calling an external rough reference coordinate system, automatically constructing a precise reference coordinate system for dimensional characteristics, and detecting the inner and outer channel diameters of the diffuser 5 and the blade position.

[0113] Specifically, 44 detection points are evenly distributed around the inner and outer diameters of the channel to detect the inner and outer diameters of the channel and to detect the position deviation of the 88 blades at a certain distance from the rotation center.

[0114] Among them, in the automatic mode of the PC-DMIS program editing window, the established external reference coordinate system is called, the coordinate system is called back to construct an automatic circle feature in the outer channel of the diffuser, and the external reference coordinate system is called back, the X and Y axes are translated to the center position of the constructed automatic circle feature, the first reference blade 16 is touched, and a straight line feature is constructed with the center of the automatic circle feature and the feature point of the first reference blade 16 touched, the negative Y direction is rotated to the constructed straight line feature, the four blades of the first reference blade 16, the second reference blade 17, the third reference blade 18, and the fourth reference blade 19 are used to touch the high point features, and the plane feature is constructed with the four high point features, the coordinate system is called back, the positive coordinate Z direction is found to the constructed plane feature, and the Z axis is translated to the constructed plane feature, so as to establish a reference coordinate system with higher accuracy, and the automatic circle feature command is called to detect the inner and outer channel diameters respectively.

[0115] Among them, when detecting the position deviation of blade 88 at a certain distance from the rotation center, the WHILE loop statement is called, the coordinate system rotation angle of 360 / 88 degrees is assigned, and the rotation offset coordinate system is established by callback within the loop statement. The blade point features are touched within the loop statement, and the position of the blade point features is evaluated before the loop command is ended, thereby completing the detection of the blade position.

[0116] The above embodiment is only one of the implementation methods that can realize the technical solution of the present invention. The scope of protection claimed by the present invention is not limited only to this embodiment, but also includes changes, replacements and other implementation methods that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention.

Claims

1. An auxiliary tool for three-coordinate detection of an aircraft engine diffuser, characterized in that: It comprises a base plate (6) and a tool positioning unit arranged on the table of a three-dimensional coordinate measuring machine (2); The tool positioning unit is used to fix the position of the base plate (6); The base plate (6) is provided with a diffuser central axis positioning unit, a diffuser axial locking unit and a reference surface construction unit; when the diffuser (5) is located on the auxiliary tooling (1): The diffuser central axis positioning unit is used to make the central axis of the diffuser (5) coincide with the central axis of the base plate (6); The diffuser axial locking unit is used to lock the axial movement of the diffuser (5); The reference plane construction unit is located at the leading edge of the blade (13) of the diffuser (5) and is vertically tangent to the blade (13), and is used to construct a reference plane.

2. The auxiliary tooling for three-coordinate detection of an aircraft engine diffuser according to claim 1, characterized in that: The tool positioning unit comprises a first tool positioning pin (7) and a second tool positioning pin (10) inserted on a table of a three-dimensional coordinate measuring machine (2); the first tool positioning pin (7) and the second tool positioning pin (10) are arranged along the outer circle of the base plate (6) and are tangent to the outer circle of the base plate (6).

3. The auxiliary tooling for three-coordinate detection of an aircraft engine diffuser according to claim 1, characterized in that: The diffuser central axis positioning unit comprises a first diffuser positioning pin (3) and a second diffuser positioning pin (8) inserted in the circumferential direction of the base plate (6); when the diffuser (5) is tangent to the first diffuser positioning pin (3) and the second diffuser positioning pin (8) at the same time, the diffuser (5) coincides with the central axis of the base plate (6).

4. The auxiliary tooling for three-coordinate detection of an aircraft engine diffuser according to claim 1, characterized in that: The reference plane construction unit comprises a plurality of slide grooves (20) uniformly distributed between the outer circle and the center of the base plate (6), each slide groove (20) being provided with a slider; when the diffuser (5) is located on the auxiliary tooling (1), each slider is located at the leading edge of the blade (13) and is vertically tangent to the blade (13); and a reference plane is constructed according to the vertical planes of each slider.

5. The auxiliary tooling for three-coordinate detection of an aircraft engine diffuser according to claim 4, characterized in that: The diffuser axial locking unit adopts a positioning block (12). When the blades (13) of the diffuser (5) are positioned, the positioning block (12) is inserted between the two blades (13) and inserted into the slide groove (20) of the base plate (6).

6. A three-coordinate detection device for an aircraft engine diffuser, characterized in that: It comprises a three-dimensional coordinate measuring machine (2) and the auxiliary tooling (1) according to any one of claims 1 to 5.

7. A three-coordinate detection method for an aircraft engine diffuser, characterized in that: Based on the auxiliary tooling (1) according to any one of claims 1 to 5 or the three-coordinate detection device according to claim 6, comprising: Fixing the position of the bottom plate (6) of the auxiliary tool (1) by using a tool positioning unit; Using a diffuser central axis positioning unit to position the diffuser (5) so that the central axis of the diffuser (5) coincides with the central axis of the base plate (6); Adjusting the reference plane construction unit so that the reference plane construction unit is located at the leading edge of the blade (13) of the diffuser (5) and is vertically tangent to the blade (13); Using a diffuser axial locking unit to lock the axial movement of the diffuser (5); Acquire the current position of the reference plane construction unit, and construct the reference plane to determine the vertical direction of the coordinate system; An external rough reference coordinate system is established according to the vertical direction of the coordinate system; The external rough reference coordinate system is called to complete the detection of the outer flow channel surface (14), the inner flow channel surface (15), the position of the blade (13) and the inner channel and outer channel diameters of the diffuser (5).

8. The three-coordinate detection method for an aircraft engine diffuser according to claim 7, characterized in that: Specifically include: Placing the bottom plate (6) of the auxiliary tooling (1) on the table of the three-dimensional coordinate measuring machine (2), and adjusting the position of the bottom plate (6) until the outer circle of the bottom plate (6) is tangent to the first tooling positioning pin (7) and the second tooling positioning pin (10) at the same time; Placing the diffuser (5) to be tested on the bottom plate (6) of the auxiliary tooling (1), and adjusting the position of the diffuser (5) until the diffuser (5) is tangent to the first diffuser positioning pin (3) and the second diffuser positioning pin (8) at the same time; Adjusting the position of each slider on the slide groove (20) so that each slider is located at the front edge of the blade (13) and is vertically tangent to the blade (13); The positioning block (12) is inserted between the two blades (13) and inserted into the slide groove (20) of the bottom plate (6); Collect the current position of each slider and construct a reference plane to determine the vertical direction of the coordinate system; An external rough reference coordinate system is established according to the vertical direction of the coordinate system; The external rough reference coordinate system is called to complete the detection of the outer flow channel surface (14), the inner flow channel surface (15), the position of the blade (13) and the inner channel and the outer channel of the diffuser (5).

9. The three-coordinate detection method for an aircraft engine diffuser according to claim 8, characterized in that: The specific steps to establish an external rough reference coordinate system according to the vertical direction of the coordinate system are as follows: Taking the vertical direction of the coordinate system as a reference, a straight line is constructed between the center of the outer circle of the base plate (6) and a point on the left end surface of the positioning block (12) as the reference axis direction; The external reference coordinate system is established in the form of points, lines and surfaces according to the right-hand rule, thereby completing the establishment of the external rough reference coordinate system.

10. The three-coordinate detection method for an aircraft engine diffuser according to claim 8, characterized in that: in, The measuring needle of the three-dimensional coordinate measuring machine (2) is directed vertically downward to construct an automatic touch inner circle at a first preset cross-sectional height of the outer flow path surface (14) of the diffuser (5), call back the external rough reference coordinate system, use the center of the constructed automatic touch inner circle as the center of the horizontal coordinate system, establish a first external fine reference coordinate system, and implement detection of the outer flow path surface (14) of the diffuser (5) according to the first external fine reference coordinate system; The measuring needle of the three-dimensional coordinate measuring machine (2) is pointed vertically downward to construct an automatic touch inner circle at a second preset cross-sectional height of the inner flow path surface (15) of the diffuser (5), call back the external rough reference coordinate system, use the center of the constructed automatic touch inner circle as the center of the horizontal coordinate system, establish a second external fine reference coordinate system, and implement detection of the inner flow path surface (15) of the diffuser (5) according to the second external fine reference coordinate system; The external rough reference coordinate system is called back so that the first reference blade (16) is used as the starting blade and the reference direction, and the high point command is called in the vertical direction of the first reference blade (16), the second reference blade (17), the third reference blade (18), and the fourth reference blade (19) in the radial direction of the diffuser (5), respectively, and the reference plane is constructed with the four high points of the first reference blade (16), the second reference blade (17), the third reference blade (18), and the fourth reference blade (19), and the external rough reference coordinate system is called back to construct a third external fine reference coordinate system, and the automatic circle command is called to respectively detect the inner channel and outer channel diameters of the diffuser (5); The high point command is called, and the third external fine reference coordinate system is rotated to collect the vertical high point of each blade (13), and the three blades (13) with the smallest deviation are evenly selected as the machining axial direction reference, and the rotation coordinate system command is called to realize the detection of the position of each blade (13).

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