CN113865458A - Device and method for measuring runout of inner profile surface and outer circle of aero-engine part - Google Patents
Device and method for measuring runout of inner profile surface and outer circle of aero-engine part Download PDFInfo
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- CN113865458A CN113865458A CN202111241809.XA CN202111241809A CN113865458A CN 113865458 A CN113865458 A CN 113865458A CN 202111241809 A CN202111241809 A CN 202111241809A CN 113865458 A CN113865458 A CN 113865458A
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000005259 measurement Methods 0.000 claims description 10
- 239000000203 mixture Substances 0.000 claims 1
- 239000002994 raw material Substances 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000001514 detection method Methods 0.000 description 8
- 230000009191 jumping Effects 0.000 description 4
- 230000004075 alteration Effects 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011897 real-time detection Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/003—Measuring of motor parts
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- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses a device and a method for measuring the run-out of the inner profile surface and the outer circle of an aircraft engine part. When the method is used for measuring, the part is uniformly rotated by hands for one circle, and the read swing numerical values of the two dial indicators are the runout of the inner profile surface to the end surface and the outer circle, so that the labor intensity of workers for detecting the part is reduced, the production efficiency of the part is improved, the production cost of the part is reduced, and the benefit of enterprises is improved.
Description
Technical Field
The invention belongs to the field of machining, and particularly relates to a device and a method for detecting the size of an aircraft engine part.
Background
The runout requirements of inner holes on end faces and outer circles on the end faces are often required to be controlled in parts such as shells of aircraft engines. For example, see FIG. 1, it is desirable to detect a 0.03 run-out of the inner bore surface (#D) from end surface datum B and a 0.04 run-out of the outer circle (#C) from end surface datum B.
The existing detection method generally adopts three-coordinate detection, but the detection consumes long time, can not realize real-time detection on a processing site, also needs turnover and long waiting time, is not beneficial to batch production detection, and in conclusion, a special measuring device and a special measuring method need to be designed to carry out detection quickly and conveniently.
Disclosure of Invention
In order to solve the technical problems, the invention aims to provide a device and a method for measuring the run-out of the inner profile surface to the end surface and the outer circle of an aircraft engine part.
In order to realize the purpose, the invention adopts the following technical scheme:
a device for measuring the run-out of the inner profile surface and the outer circle of an aeroengine part comprises,
a flat plate;
the positioning support sleeve is connected to the upper end face of the flat plate, is of a circular structure, and is provided with a positioning groove and a supporting face for aeroengine parts;
the sleeve penetrates through the upper end face and the lower end face of the flat plate and is connected with the flat plate, the sleeve is positioned in the annular inner hole of the positioning supporting sleeve, a through groove is formed in the sleeve along the axial direction of the sleeve, and a spring placing hole and a first through hole are formed in the upper end and the lower end of the bottom face of the barrel groove respectively;
the measuring rod is arranged in the through groove of the sleeve and is rotatably connected with the sleeve through a fixing pin;
the spring is arranged in the spring placing hole, and one end of the spring is in contact with the measuring rod;
the supporting screw is arranged in the first hole, and one end of the supporting screw is in contact with the measuring rod;
the first dial indicator is connected to the lower end face of the flat plate, and a measuring head of the first dial indicator is in contact with the measuring rod;
and the second dial indicator is connected to the upper end face of the flat plate.
Furthermore, the measuring device also comprises supporting legs, and a plurality of supporting legs are connected to the lower end face of the flat plate.
Furthermore, the positioning support sleeve is fixedly connected to the upper end face of the flat plate through a first fixing screw and a positioning pin.
Further, the sleeve is connected to the flat plate through a second fixing screw.
Furthermore, the two ends of the measuring rod in the length direction are respectively provided with a contact in contact with the inner profile of the aircraft engine part and a flat end face in contact with the first dial indicator, and the distance from the fixing pin to the contact is equal to the distance from the fixing pin to the contact position of the first dial indicator and the flat end face.
Furthermore, the first dial indicator is detachably connected with the lower end face of the flat plate through a first dial indicator clamp, and a clamping screw for adjusting the clamping force is arranged on the first dial indicator clamp;
the second dial indicator is detachably connected with the upper end face of the flat plate through a second indicator clamp, and a clamping screw for adjusting the clamping force is arranged on the second indicator clamp.
Furthermore, first table presss from both sides and the second table presss from both sides and all includes first centre gripping section and second centre gripping section, and first centre gripping section and second centre gripping section interval arrangement, first centre gripping section and second centre gripping section all are provided with a screw and a recess, and clamping screw passes the screw on first centre gripping section and the second centre gripping section simultaneously.
Further, the first dial indicator and the second dial indicator are perpendicular to each other.
The measuring method for the run-out of the inner profile surface and the outer circle of the aeroengine part adopts the measuring device and comprises the following steps,
the method comprises the following steps: moving the support screw along the first through hole such that the metering rod rotates about the fixed pin and is substantially perpendicular to the flat plate;
step two: placing the detected aircraft engine part on a positioning bearing sleeve, contacting and positioning the aircraft engine part with an inner hole of the aircraft engine part through a positioning groove, and supporting the end surface of the aircraft engine part through a supporting surface;
step three: adjusting the supporting screw to enable the upper end of the measuring rod to abut against the inner molded surface of the aero-engine part under the driving of the spring, adjusting the first dial indicator to press the lower end of the measuring rod tightly, and adjusting the second dial indicator to abut against the outer circular surface of the aero-engine part;
step four: adjusting the pointers of the first dial indicator and the second dial indicator to zero scale positions;
step five: and rotating the aeroengine part for a circle, reading the swing numerical values of the first dial indicator and the second dial indicator, wherein the maximum scale numerical value of the swing of the first dial indicator is the run-out value of the inner profile facing to the end face reference, and the maximum scale numerical value of the swing of the second dial indicator is the run-out value of the outer circle facing to the end face reference.
Furthermore, in the second step, the fit clearance between the inner hole of the aircraft engine part and the positioning groove of the positioning support sleeve is smaller than the runout value of the inner profile facing end surface and the outer circle facing end surface.
Compared with the prior art, the measuring device adopted by the invention can measure the run-out of the inner profile surface and the outer circle of the aero-engine part at one time, solves the problems that three-coordinate measurement is time-consuming and labor-consuming, the on-site detection cannot be carried out in real time and the efficiency is low, improves the detection efficiency of the run-out of the inner profile surface and the outer circle to the end surface reference, reduces the labor intensity of workers for detecting the part, improves the production efficiency of the part, reduces the production cost of the part and improves the benefits of enterprises.
Drawings
FIG. 1 is a schematic view of a part structure;
FIG. 2 is a schematic view of a measuring apparatus;
FIG. 3 is a schematic sectional view taken along line A-A of FIG. 2;
FIG. 4 is a left side view of FIG. 2;
FIG. 5 is a perspective view of the measuring device;
FIG. 6 is a schematic cross-sectional view of the assembled measuring device and aircraft engine components;
FIG. 7 is a perspective view of FIG. 6;
in the figure, 1, a supporting foot, 2, a flat plate, 3, a sleeve, 4, a measuring rod, 5, a positioning supporting sleeve, 6, a supporting screw, 7, a first fixing screw, 8, a second fixing screw, 9, a first dial indicator, 10, a first dial indicator clamp, 11, a second dial indicator clamp, 12, a dial indicator clamp screw, 13, a fixing pin, 14, a positioning pin, 15, a spring and 16, and a second dial indicator are arranged.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
As shown in fig. 2 to 4, in the present embodiment, a set of measuring device for measuring the run-out of the inner profile of an aircraft engine part from the end face to the end face and the outer circle is designed, and the device mainly comprises a support leg 1, a flat plate 2, a sleeve 3, a measuring rod 4, a positioning support sleeve 5, a support screw 6, a first fixing screw 7, a second fixing screw 8, a first dial indicator 9, a first dial indicator clamp 10, a second dial indicator clamp 11, a dial indicator clamp screw 12, a fixing pin 13, a positioning pin 14, a spring 15, and a second dial indicator 16.
Referring to fig. 2 and 3, the sleeve 3 is cylindrical, a through groove is formed on the surface of the sleeve 3 and parallel to the axis direction of the cylinder, a spring 15 is placed in a spring placing hole on the bottom surface of the through groove of the sleeve 3 (the spring placing hole is a blind hole, namely a blind hole on the bottom surface of the barrel groove), the measuring rod 4 is fixed in the through groove of the sleeve 3 through a fixing pin 13, the measuring rod 4 can rotate around the fixing pin 13, then the supporting screw 6 is screwed into the first through hole, the tail end of the supporting screw 6 is pressed against the measuring rod 4, and the measuring rod 4 is ensured to be basically vertical to the flat plate 2. The assembled sleeve 3 is fixedly assembled on the flat plate 2 through a second fixing screw 8, positioning pins 14 (2) are assembled on the flat plate 2, the positioning support sleeve 5 is positioned on the flat plate 2 through the positioning pins 14 and then fixed on the flat plate 2 through screwing in first fixing screws 7, and support feet 1 are arranged at 4 corners of the lower end face of the flat plate 2 to support the whole measuring device. The first dial gauge 10 is assembled and fixed with screws under the plate 2 and the first dial gauge 9 is assembled to the first dial gauge 10 by means of the gauge clamp screws 12, and the second dial gauge 16 is assembled to the second dial gauge 11 and fixed above the plate 2 in the same assembly sequence, and the assembly of the measuring device is completed. First table presss from both sides 10 and second table and presss from both sides 11 the structure the same, all is including the base of being connected with dull and stereotyped 2, has two grip blocks on the base, has the interval in the middle of two grip blocks, and the end of two grip blocks is connected through table clamp screw 12 to interval and clamping-force between two grip blocks are adjusted, it has the recess to open on the grip block, and first percentage table 9 and second percentage table 16 are held by the centre gripping in the groove of two grip blocks. The measuring rod 4 is linear, the cross-sectional areas of two ends are smaller, the upper end is a contact in contact with the inner profile, and the lower end is a flat end surface in contact with the first dial indicator 9. The first and second dial indicators 9, 16 are disposed in a 90 degree perpendicular relationship with respect to the plate 2.
During measurement, the support screw 6 is moved to ensure that the measuring rod 4 is basically vertical to the flat plate 2, the detected aeroengine part is placed on the upper end surface of the positioning support sleeve 5, as shown in fig. 6 and 7, the positioning support sleeve 5 is of a circular ring structure, an annular groove is arranged on the upper end surface of the circular ring structure and serves as a positioning groove, an annular end surface serves as a support surface, the inner hole phi E surface of the aeroengine part is positioned with the inner ring surface of the positioning groove, the reference end surface B of the aeroengine part is contacted with the support surface to form support, the support screw 6 is adjusted, and the contact head (round head, namely the contact part of the contact head and the inner profile surface is chamfered on the contact head through the elasticity of the spring 15, so that the contact head is smoothly contacted with the inner profile phi D surface of the D hole, and the whole contact head can be processed into a sphere without being tightly close to the inner profile phi D of the aeroengine; adjusting a first dial indicator 9 to be tightly pressed on a flat end face at the lower end of a measuring rod 4, then screwing a dial clamp screw 12, adjusting a second dial indicator 16 on a second dial clamp 11 in the same operation mode to enable the second dial indicator 16 to be tightly pressed on an outer circle face phi C of a part, then screwing another dial clamp screw 12, adjusting 2 dial indicator pointers to a 0 scale position, uniformly rotating the part for a circle by hands, reading swing values of the first dial indicator 9 and the second dial indicator 16, a swing maximum scale value of the first dial indicator 9 below a flat plate 2, namely a run-out value of an inner profile phi D to a reference of an end face B, and a swing maximum scale value of the second dial indicator 16 above the flat plate 2, namely a run-out value of the outer circle phi C to the reference of the end face B.
In order to prevent the part from generating radial movement when the aircraft engine part is rotated, the fit clearance between the positioning outer circle (namely the surface of the inner ring of the positioning groove) of the positioning support sleeve 5 and the positioning inner hole phi E of the aircraft engine part is required to be 0.005-0.015.
In order to ensure that the ratio of the swing value of the first dial indicator 9 to the contact runout of the measuring rod 4 below the flat plate 2 is 1:1 (namely the swing value of the first dial indicator 9 is equal to the runout value, and equal scaling is not needed), the rotation center of the measuring rod 4 (the position fixed with the sleeve 3 through the fixing pin 13) is ensured to be symmetrical or equal to the measuring positions at two ends (the contact position phi D of the measuring rod 4 is in contact with the inner profile of the part and the position where the flat end surface of the measuring rod 4 is in contact with the first dial indicator 9), namely two distances L in FIG. 6 are equal.
Taking the phi D and outer circle phi C of the inner profile surface measured in FIG. 1 as examples, the phi C is jumped by 0.03 and 0.04 to the end surface datum B, the detection method of the aero-engine part is as follows:
the method comprises the following steps: as shown in fig. 6 and 7, the support screw 6 is moved inside the first through hole of the sleeve 3, ensuring that the measuring rod 4 is substantially perpendicular to the plate 2;
step two: as shown in fig. 6, the detected aircraft engine part is placed on the upper end surface of the positioning bearing sleeve 5, the inner hole phi E of the part is used as a positioning surface and is in contact positioning with the surface of the inner ring of the positioning groove on the upper end surface of the positioning bearing sleeve 5, and the reference end surface B of the part is supported by the annular supporting surface on the upper end surface of the positioning bearing sleeve 5;
step three: adjusting the support screw 6 to enable the measuring rod 4 to rotate around the fixing pin 13, enabling a contact (round head) of the measuring rod 4 to be close to the inner profile surface phi D of the part through the elastic force of the spring 15, adjusting the first dial indicator 9 to be tightly pressed on the flat end surface of the lower end of the measuring rod 4, then screwing the dial indicator clamp screw 12 to fasten the first dial indicator 9, adjusting the second dial indicator 16 on the second dial indicator clamp 11 to enable the second dial indicator to push the outer circumferential surface phi C of the part, and then screwing the other dial indicator clamp screw 12 to fasten the second dial indicator;
step four: adjusting the pointers of the first dial indicator 9 and the second dial indicator 16 to the position of scale "0";
step five: uniformly rotating the parts of the aero-engine by hand for one circle, reading the swing numerical values of the first dial indicator 9 and the second dial indicator 16, wherein the maximum swing scale numerical value of the first dial indicator 9 below the flat plate 2 is the jumping value of the inner profile phi D to the end surface B reference, and the maximum swing scale numerical value of the second dial indicator 16 above the flat plate 2 is the jumping value of the outer circle phi C to the end surface B reference.
Through the steps, the purpose that two jumping values can be measured by one-time rotation of the part is achieved, the measurement efficiency is greatly improved, and the jumping values are accurately measured.
Claims (10)
1. The utility model provides a measuring device that aeroengine part inner mould face is beated to terminal surface and excircle which characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
a plate (2);
the positioning and supporting sleeve (5) is connected to the upper end face of the flat plate (2), the positioning and supporting sleeve (5) is of a circular structure, and a positioning groove and a supporting face for aero-engine parts are arranged on the annular upper end face of the positioning and supporting sleeve (5);
the sleeve (3) penetrates through the upper end face and the lower end face of the flat plate (2) and is connected with the flat plate (2), the sleeve (3) is located in an annular inner hole of the positioning supporting sleeve (5), a through groove is formed in the sleeve (3) along the axial direction of the sleeve (3), and a spring placing hole and a first through hole are formed in the upper end and the lower end of the bottom face of the barrel groove respectively;
the measuring rod (4) is arranged in the through groove of the sleeve (3), and is rotatably connected with the sleeve (3) through a fixing pin (13);
the spring (15) is arranged in the spring placing hole, and one end of the spring (15) is in contact with the measuring rod (4);
the supporting screw (6) is arranged in the first through hole, and one end of the supporting screw (6) is in contact with the measuring rod (4);
the first dial indicator (9), the first dial indicator (9) is connected to the lower end face of the flat plate (2), and a measuring head of the first dial indicator (9) is in contact with the measuring rod (4);
and the second dial indicator (16), wherein the second dial indicator (16) is connected to the upper end face of the flat plate (2).
2. The aero-engine part inside profile facing end face and outside circular run-out measurement device according to claim 1, wherein: the support device is characterized by further comprising support legs (1), wherein the support legs (1) are connected to the lower end face of the flat plate (2).
3. The aero-engine part inside profile facing end face and outside circular run-out measurement device according to claim 1, wherein: the positioning support sleeve (5) is fixedly connected to the upper end face of the flat plate (2) through a first fixing screw (7) and a positioning pin (14).
4. The aero-engine part inside profile facing end face and outside circular run-out measurement device according to claim 1, wherein: the sleeve (3) is connected to the flat plate (2) through a second fixing screw (8).
5. The aero-engine part inside profile facing end face and outside circular run-out measurement device according to claim 1, wherein: the two ends of the length direction of the measuring rod (4) are respectively provided with a contact in contact with the inner profile of an aircraft engine part and a flat end face in contact with the first dial indicator (9), and the distance between the fixing pin (13) and the contact is equal to the distance between the fixing pin (13) and the contact between the first dial indicator (9) and the flat end face.
6. The aero-engine part inside profile facing end face and outside circular run-out measurement device according to claim 1, wherein:
the first dial indicator (9) is detachably connected with the lower end face of the flat plate (2) through a first dial clamp (10), and a clamping screw (12) for adjusting the clamping force is arranged on the first dial clamp (10);
the second dial indicator (16) is detachably connected with the upper end face of the flat plate (2) through a second indicator clamp (11), and a clamping screw (12) for adjusting the clamping force is arranged on the second indicator clamp (11).
7. The aero-engine part inside profile facing end face and outside circular run-out measurement device as claimed in claim 6, wherein: the first meter clamp (10) and the second meter clamp (11) comprise a first clamping section and a second clamping section which are arranged at intervals, a screw hole and a groove are formed in the first clamping section and the second clamping section, and a clamping screw (12) penetrates through the screw hole in the first clamping section and the screw hole in the second clamping section simultaneously.
8. The aero-engine part inside profile facing end face and outside circular run-out measurement device according to claim 1, wherein: the first dial indicator (9) and the second dial indicator (16) are perpendicular to each other.
9. A method for measuring the run-out of the inner profile surface and the outer circle of an aircraft engine part is characterized in that: the use of the measuring device of claim 1, comprising the steps of,
the method comprises the following steps: moving the support screw (6) along the first through hole such that the metering rod (4) rotates about the fixing pin (13) and is substantially perpendicular to the plate (2);
step two: the part to be detected of the aircraft engine is placed on a positioning bearing sleeve (5), is in contact positioning with an inner hole of the part of the aircraft engine through a positioning groove, and supports the end face of the part of the aircraft engine through a supporting surface;
step three: adjusting the supporting screw (6) to enable the upper end of the measuring rod (4) to abut against the inner molded surface of the aeroengine part under the driving of the spring (15), adjusting the first dial indicator (9) to press the lower end of the measuring rod (4), and adjusting the second dial indicator (16) to abut against the outer circular surface of the aeroengine part;
step four: adjusting the pointers of the first dial indicator (9) and the second dial indicator (16) to zero scale positions;
step five: rotating the aeroengine part for a circle, reading the swing numerical values of the first dial indicator (9) and the second dial indicator (16), wherein the swing maximum scale numerical value of the first dial indicator (9) is the run-out value of the inner profile to the end surface reference, and the swing maximum scale numerical value of the second dial indicator (16) is the run-out value of the outer profile to the end surface reference.
10. The method for measuring the run-out of the inner profile facing end surface and the outer circle of the aircraft engine part as claimed in claim 9, wherein: in the second step, the fit clearance between the inner hole of the aircraft engine part and the positioning groove of the positioning support sleeve (5) is smaller than the runout value of the inner profile facing end surface and the outer circle facing end surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111241809.XA CN113865458A (en) | 2021-10-25 | 2021-10-25 | Device and method for measuring runout of inner profile surface and outer circle of aero-engine part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111241809.XA CN113865458A (en) | 2021-10-25 | 2021-10-25 | Device and method for measuring runout of inner profile surface and outer circle of aero-engine part |
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| Publication Number | Publication Date |
|---|---|
| CN113865458A true CN113865458A (en) | 2021-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111241809.XA Pending CN113865458A (en) | 2021-10-25 | 2021-10-25 | Device and method for measuring runout of inner profile surface and outer circle of aero-engine part |
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| CN (1) | CN113865458A (en) |
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| CN204007399U (en) * | 2014-07-30 | 2014-12-10 | 三江瓦力特特种车辆有限公司 | A kind of jitter detection apparatus of the axial workpiece with axial bore |
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| CN208419819U (en) * | 2018-06-26 | 2019-01-22 | 江门市力泰科技有限公司 | A kind of detection revolving body internal-and external diameter beating degree device |
| US20200003541A1 (en) * | 2018-07-02 | 2020-01-02 | Citic Dicastal Co., Ltd | Runout detection device |
| CN210321491U (en) * | 2019-07-24 | 2020-04-14 | 南京华测达精密机械有限公司 | Quick detection device for inner diameter circle run-out |
| CN210426371U (en) * | 2019-10-22 | 2020-04-28 | 中国工程物理研究院化工材料研究所 | On-machine measuring device suitable for energy-containing rotary part |
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- 2021-10-25 CN CN202111241809.XA patent/CN113865458A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202393334U (en) * | 2011-12-09 | 2012-08-22 | 昆山恒源机械制造有限公司 | Axiality and verticality detecting tool |
| CN203024681U (en) * | 2012-12-15 | 2013-06-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Inner positioning mounting seat run-out inspection device |
| CN203572358U (en) * | 2013-11-01 | 2014-04-30 | 成都豪能科技股份有限公司 | Multifunctional comprehensive detecting tool |
| CN103900437A (en) * | 2014-04-10 | 2014-07-02 | 西安航空动力股份有限公司 | Inner conical surface bouncing detection device of aircraft engine fuel nozzle |
| CN204007399U (en) * | 2014-07-30 | 2014-12-10 | 三江瓦力特特种车辆有限公司 | A kind of jitter detection apparatus of the axial workpiece with axial bore |
| CN107421414A (en) * | 2017-06-30 | 2017-12-01 | 天津天海同步科技有限公司 | A kind of axial workpiece internal spline bounce gauge |
| CN208419819U (en) * | 2018-06-26 | 2019-01-22 | 江门市力泰科技有限公司 | A kind of detection revolving body internal-and external diameter beating degree device |
| US20200003541A1 (en) * | 2018-07-02 | 2020-01-02 | Citic Dicastal Co., Ltd | Runout detection device |
| CN210321491U (en) * | 2019-07-24 | 2020-04-14 | 南京华测达精密机械有限公司 | Quick detection device for inner diameter circle run-out |
| CN210426371U (en) * | 2019-10-22 | 2020-04-28 | 中国工程物理研究院化工材料研究所 | On-machine measuring device suitable for energy-containing rotary part |
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Application publication date: 20211231 |