CN115711565A - Device and method for measuring blade tip diameter of aeroengine rotor - Google Patents
Device and method for measuring blade tip diameter of aeroengine rotor Download PDFInfo
- Publication number
- CN115711565A CN115711565A CN202211436096.7A CN202211436096A CN115711565A CN 115711565 A CN115711565 A CN 115711565A CN 202211436096 A CN202211436096 A CN 202211436096A CN 115711565 A CN115711565 A CN 115711565A
- Authority
- CN
- China
- Prior art keywords
- rotor
- measuring
- machine tool
- blade tip
- arc
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses a device and a method for measuring the diameter of a rotor blade tip of an aircraft engine, which belong to the technical field of measurement and comprise the following steps: the measuring device is suitable for a rotor with odd blades at the whole stage, and can measure the runout of the blades at all stages of the rotor. The measuring method can be finished by utilizing a set of standard parts and measuring tools, the measurement is simple and efficient, can be finished by one person, the problems that a large micrometer or a riding gauge is inconvenient and inaccurate in measurement are solved, the measuring method is also suitable for rotors with odd-numbered whole-stage blades, and meanwhile, the runout of all-stage blades of the rotors can be measured.
Description
Technical Field
The invention belongs to the technical field of measurement, and particularly relates to a device and a method for measuring the diameter of a rotor blade tip of an aircraft engine.
Background
The clearance between the blade tip and the casing of the rotor of the aero-engine is one of important control indexes of the engine, the performance of the engine is reduced when the clearance is too large, and the safety of the engine is affected because the blade tip and the casing are abraded due to too small clearance. The rotor tip diameter size directly affects the tip to casing clearance.
In order to ensure the diameter size of the blade tip of the engine rotor, the blade tip size needs to be accurately measured besides process control, so as to ensure the requirement of the clearance between the blade tip of the rotor and the casing. At present, the commonly used measuring method of the diameter of the rotor blade tip is measuring by a micrometer or a riding horse gauge, and the defects are as follows:
first, the micrometer measurement is inaccurate. Because the micrometer gauge head is a plane, the contact positions of the two gauge heads and the blade tip are different during measurement, so that measurement errors can be caused, especially for odd blades, the measurement errors are easy to generate, and numerical value conversion is needed. Secondly, when the blade tip diameter is measured by using a riding gauge, the blade tip diameter measurement of a fixed axial position can be only carried out, and the diameter size on the whole length of the blade tip cannot be reflected. Thirdly, to the great rotor of diameter, micrometer and riding the horse gauge measure and all need two people's cooperation to accomplish and measure, comparatively loaded down with trivial details.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a device and a method for measuring the diameter of the blade tip of an aeroengine rotor, so as to solve the problems of large error and complicated measuring process of the existing measuring method.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
the invention discloses a device for measuring the diameter of a rotor blade tip of an aircraft engine, which comprises: a measuring tool, a standard part and a dial indicator; the standard part is hung on a rear shaft neck of a rotor on a machine tool, the measuring tool is arranged on a guide rail of the machine tool, is positioned under the standard part and is in contact with the standard part, and the dial indicator is arranged on the measuring tool.
Preferably, the measuring tool comprises: the base is arranged on the machine tool guide rail, the gauge stand is arranged on the base, the dial indicator is arranged on the gauge stand, and the gauge stand is in contact with the standard part.
Preferably, the distance from the top end of the gauge stand to the bottom end of the base is the distance from a machine tool guide rail to the center line of the rotor, namely the radius of the tip of the rotor.
Preferably, the distance between the axial center line of the watch frame and the side surface of the base is the distance between the side surface of the machine tool guide rail and a vertical plane passing through the center line of the rotor.
Preferably, the standard comprises: the angle bracket, the support plate and the arc-shaped meter aligning plate; one end of the support plate is connected with the angle bracket, the other end of the support plate is connected with the arc-shaped meter aligning plate, the angle bracket is hung on a rear shaft neck of a rotor on a machine tool, and the arc-shaped meter aligning plate is contacted with the measuring tool.
Preferably, the angle frame and the arc-shaped surface aligning plate are fixedly connected with the support plate through screws and pins.
Preferably, the angle frame is of a V-shaped structure, and the diameter of an inscribed circle of the V-shaped groove is the same as the diameter of the rear journal of the rotor.
Preferably, the arc-shaped counter plate is provided with a screw hole and a pin hole at one end, the other end is of an arc structure, and the radius of the arc is half of the diameter of the rotor blade tip.
The invention also discloses a method for measuring the diameter of the blade tip of the rotor of the aircraft engine, which comprises the following steps:
hanging a standard part on a rear shaft neck of a rotor on a machine tool, arranging a measuring tool on a guide rail of the machine tool, locating right below the standard part and contacting with the standard part, and arranging a dial indicator on the measuring tool;
swinging the standard component to return the dial indicator on the measuring tool to zero, thereby finishing the meter setting;
translating the measuring tool to the blade tip part of the measured blade to measure the blade tip of the rotor, rotating the rotor and measuring the blade tips of other blades;
and swinging the standard component to determine whether the meter calibration is twice zeroed, and repeating the steps if the meter calibration is not zeroed.
Preferably, during measurement, a measuring tool for aligning the meter is placed on a machine tool guide rail, the bottom surface and one side surface of the measuring tool are attached to the machine tool guide rail, the measuring tool is translated to the tip part of the measured blade, namely the measurement of the first blade is completed, and then the rotor is slowly rotated along the axis of the rotor, so that the tip measurement of other blades at the level is completed;
rotor tip diameter D =2 × (actual value of standard R + value of table L)
The actual value R of the standard component is a rated value of the standard component which is periodically checked, and the table value L is a deflection value of the standard component when the blade is measured after the table is checked.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a device for measuring the diameter of a rotor blade tip of an aircraft engine, which comprises: the measuring device is suitable for a rotor with odd blades at the whole stage, and can measure the runout of the blades at all stages of the rotor.
The invention also discloses a method for measuring the diameter of the blade tip of the rotor of the aero-engine, which can be finished by utilizing a set of standard parts and measuring tools, has simple and efficient measurement and can be finished by one person, and avoids the problems of inconvenience and inaccuracy in measurement of a large micrometer or a horse riding gauge, and the measuring method is also suitable for the rotor with odd-numbered whole blades and can measure the runout of all the stages of the blades of the rotor.
Drawings
FIG. 1 is a schematic view of a rotor of a high pressure machine;
FIG. 2 is a schematic diagram of a test tool and standard pair of tables;
FIG. 3 is a schematic diagram of a standard construction;
FIG. 4 is a schematic view of the measuring tool.
Wherein: 1-a corner bracket; 2-a support plate; 3-arc surface aligning plate; 4-screws; 5-a pin; 6-a watch frame; 7-a base; 8-dial indicator; 9-rear journal; 10-front journal; 11-blade tip; 12-machine tool guide rail.
Detailed Description
In order to make those skilled in the art better understand the technical solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention is described in further detail below with reference to the accompanying drawings:
referring to fig. 1 to 4, the invention discloses a device for measuring the diameter of a rotor blade tip of an aircraft engine, which comprises: a measuring tool, a standard part and a dial indicator 8; the standard part is hung on a rotor rear shaft neck 9 on a machine tool, the measuring tool is arranged on a machine tool guide rail 12 and is positioned right below the standard part and is in contact with the standard part, and the dial indicator 8 is arranged on the measuring tool. The measuring tool comprises: the base 7 is arranged on a machine tool guide rail 12, the gauge stand 6 is arranged on the base 7, the dial indicator 8 is arranged on the gauge stand 6, and the gauge stand 6 is in contact with a standard part; the distance from the top end of the gauge stand 6 to the bottom end of the base 7 is the distance from the machine tool guide rail 12 to the center line of the rotor-the radius of the tip of the rotor; the distance between the axial central line of the gauge stand 6 and the side surface of the base 7 is the distance between the side surface of the machine tool guide rail 12 and a vertical plane passing through the central line of the rotor; the standard component comprises: the device comprises an angle bracket 1, a support plate 2 and an arc-shaped surface aligning plate 3; one end of the support plate 2 is connected with the angle bracket 1, the other end is connected with the arc-shaped meter aligning plate 3, the angle bracket 1 is hung on a rotor rear shaft neck 9 on a machine tool, and the arc-shaped meter aligning plate 3 is contacted with a measuring tool; the angle frame 1 is of a V-shaped structure, the diameter of an inscribed circle of the V-shaped groove is the same as the diameter of the rear shaft neck 9 of the rotor, the arc is provided with a screw hole and a pin hole for one end of the dial plate 3, the other end of the arc is of an arc structure, and the radius of the arc is half of the diameter of the tip of the rotor.
The angle frame 1 and the arc-shaped meter aligning plate 3 are fixedly connected with the support plate 2 through screws 4 and pins 5.
The technical scheme of the invention is as follows:
(1) Installing a detection device: a detection device is prepared according to the structure of the machine tool guide rail 12 and the rotor, and comprises a standard part and a measuring tool.
Standard parts: the overall structure is of a barb type and mainly comprises a support plate 2, an angle bracket 1 and an arc-shaped surface aligning plate 3. The support plate 2 is a main body part of the measuring tool, and the angle bracket 1 and the arc-shaped surface alignment plate 3 are connected to the support plate 2 through a positioning pin 5 and a screw 4; the angle frame 1 is of a V-shaped structure, the diameter of an inscribed circle of the V-shaped groove is designed according to the diameter of a rear shaft neck of the rotor, the tolerance is +/-0.01, and the side surface of the angle frame 1 is provided with 2 threaded holes and 1 precise pin hole; one end of the arc-shaped counter plate 3 is provided with 1 screw hole and 1 precision pin hole, the other end of the arc-shaped counter plate is of an arc structure, the radius of an arc is half of the diameter of the tip of the rotor, and the tolerance is +/-0.005.
The measuring tool comprises: mainly comprises a base 7 and a watch frame 6. The verticality of the side surface and the bottom surface of the base 7 is 0.1, and the roughness is Ra0.4; the watch holder 6 is connected to the base 7. The distance from the top end of the gauge stand 6 to the bottom end of the base 7 is designed according to the distance from the machine tool guide rail to the center line of the rotor-the radius of the tip of the rotor, and the range of +/-4 moving ranges is ensured, the distance from the axial center line of the gauge stand 6 to the side face of the base 7 is designed according to the distance from the side face of the machine tool guide rail to the vertical plane passing through the center line of the rotor, and the tolerance is +/-0.3.
Before measurement, a measuring tool and a standard part with corresponding sizes are selected according to the rotor for installation.
(2) And (4) tabulating: the method comprises the steps of inversely hanging a standard part on a precise excircle of a rear shaft neck 9 of a rotor on a machine tool, arranging a measuring tool on a machine tool guide rail 12, attaching the machine tool guide rail 12 to the bottom surface and one side surface of the measuring tool, horizontally moving the measuring tool to a position right below the standard part to ensure that a gauge stand 6 on the measuring tool is in contact with an arc-shaped gauge plate 3 of the standard part, mounting a dial indicator 8 on the gauge stand 6, swinging the standard part in a small range in the circumferential direction, returning the dial indicator 8 to zero, and finishing gauge setting.
(3) Measurement: and (3) placing the measuring tool aligned with the meter on a machine tool guide rail 12, attaching the bottom surface and one side surface of the measuring tool to the machine tool guide rail 12, translating the measuring tool to the tip part of the measured blade, namely completing the measurement of the first blade, and then slowly rotating the rotor along the axis of the rotor to complete the measurement of the tips of other blades at the level.
And the rotor tip diameter D =2 x (the actual value R of the standard component + the table value L), wherein the actual value R of the standard component is a rated value of the standard component which is periodically checked, the table value L is a deflection value when the blades are measured after the table is checked, the deflection value is far from positive, and otherwise, the deflection value is negative.
(4) Calibration: and (3) performing the surface calibration of the measuring tool according to the step (2) to determine whether the surface calibration is twice zeroed, and repeating the steps (2) to (4) if the surface calibration is not zeroed.
And (4) for other grades of blades, only selecting corresponding standard parts and measuring tools, and executing according to the steps (2) to (4).
[ examples ] A method for producing a compound
Taking the blade tip diameter of a 3 rd stage blade of a certain compressor rotor as an example, the blade tip diameter of the 3 rd stage blade of the rotor is phi M0-0.010, and the precise excircle diameter of a rear shaft neck is phi N0-0.014.
1) Preparing a detection device: a detection device is prepared according to the structure of a machine tool guide rail and a rotor, and comprises a standard part and a measuring tool.
Standard parts: the overall structure is of a barb type and mainly comprises a support plate 2, an angle bracket 1 and an arc-shaped surface aligning plate 3. The support plate 2 is a main body part of the measuring tool, and the angle bracket 1 and the arc-shaped surface alignment plate 3 are connected to the support plate 2 through a positioning pin 5 and a screw 4; the angle frame 1 is of a V-shaped structure, the nominal diameter value of an inscribed circle of the V-shaped groove is designed according to the diameter median difference of a rear journal 9 of the rotor, namely phi (N-0.007), the tolerance is designed to be +/-0.01, and 2M 6 multiplied by 1.5 threaded holes and 1 phi 6+0.012 precision pin hole are formed in the side surface of the angle frame 1; one end of the arc-shaped dial plate 3 is provided with 1M 6 multiplied by 1.5 screw hole and 1 phi 6+0.012 precision pin hole, the other end is in an arc structure, the nominal value of the arc radius is designed according to the diameter upper difference of the rotor blade tip, namely phi M, and the tolerance is designed to be +/-0.005.
The measuring tool comprises: mainly comprises a base 7 and a watch frame 6. The verticality of the side surface and the bottom surface of the base 7 is 0.1, and the roughness is Ra0.4; the watch holder 6 is connected to the base 7. The distance from the top end of the meter frame 6 to the bottom end of the base 7 is designed according to the distance from the machine tool guide rail to the center line of the rotor-the nominal value of the radius of the blade tip of the rotor, namely, the design is carried out, and the moving range (can be +/-4) is ensured, the distance from the axial center line of the meter frame 6 to the side surface of the base 7 is designed according to the distance from the side surface of the machine tool guide rail to the vertical plane passing through the center line of the rotor, and the tolerance is +/-0.3.
2) And (4) tabulating: the method comprises the steps of inversely hanging a standard part on a phi M precision excircle of a rear shaft neck 9 of a rotor on a machine tool, placing a measuring tool on a machine tool guide rail 12, attaching the machine tool guide rail 12 to the bottom surface and one side surface of the measuring tool, horizontally moving the measuring tool to the position right below the standard part to ensure that a gauge stand of an upper measuring tool 6 is in contact with an arc-shaped counter plate 3 of the standard part, mounting a dial indicator 8 on the gauge stand 6, swinging the standard part in a small range in the circumferential direction, returning the dial indicator 8 to zero, and finishing the counter.
3) Measurement: and (3) placing the measuring tool with the aligned surface on a machine tool guide rail 12, attaching the bottom surface and one side surface of the measuring tool, translating the measuring tool to the tip part of the 3 rd-level blade, namely completing the measurement of the first blade, and then slowly rotating the rotor along the axis of the rotor to complete the tip measurement of other blades at the level.
And D =2 x (standard component actual value R + table value L) of the 3 rd-stage rotor blade tip diameter, wherein the standard component actual value R is a rated value of the standard component which is periodically checked, the table value L is a deflection value when the blade is measured after the table is checked, the deflection value is far from positive, and otherwise, the deflection value is negative.
4) Calibration: and (3) performing the surface alignment of the measuring tool according to the step 2), and returning to zero for the second time, and repeating the steps 2) to 4) if the surface alignment is not returned to zero.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (10)
1. An aeroengine rotor apex diameter measuring device which characterized in that includes: the measuring tool, the standard part and the dial indicator (8); the standard part is hung on a rotor rear shaft neck (9) on a machine tool, the measuring tool is arranged on a machine tool guide rail (12) and is positioned right below the standard part and is in contact with the standard part, and the dial indicator (8) is arranged on the measuring tool.
2. The aircraft engine rotor blade tip diameter measuring device according to claim 1, wherein the measuring tool comprises: the base (7) is arranged on a machine tool guide rail (12), the gauge stand (6) is arranged on the base (7), the dial indicator (8) is arranged on the gauge stand (6), and the gauge stand (6) is in contact with a standard part.
3. The aircraft engine rotor tip diameter measuring device according to claim 2, wherein the distance from the top end of the gauge stand (6) to the bottom end of the base (7) is the distance from the machine tool guide rail (12) to the rotor center line-the rotor tip radius.
4. The aircraft engine rotor blade tip diameter measuring device according to claim 2, characterized in that the distance between the axial center line of the gauge stand (6) and the side surface of the base (7) is the distance between the side surface of the machine tool guide rail (12) and a vertical plane passing through the center line of the rotor.
5. An aircraft engine rotor tip diameter measuring device according to claim 1, wherein the standard component comprises: the angle bracket (1), the support plate (2) and the arc-shaped meter aligning plate (3); one end of the support plate (2) is connected with the angle bracket (1), the other end of the support plate is connected with the arc-shaped meter aligning plate (3), the angle bracket (1) is hung on a rotor rear shaft neck (9) on a machine tool, and the arc-shaped meter aligning plate (3) is contacted with the measuring tool.
6. The aircraft engine rotor blade tip diameter measuring device of claim 5, wherein the angle bracket (1) and the arc-shaped surface aligning plate (3) are fixedly connected with the support plate (2) through screws (4) and pins (5).
7. The aircraft engine rotor tip diameter measuring device of claim 5, characterized in that the angle bracket (1) is of a V-shaped structure, and the diameter of an inscribed circle of the V-shaped groove is the same as the diameter of the rear journal (9) of the rotor.
8. The aircraft engine rotor blade tip diameter measuring device according to claim 5, wherein one end of the arc-shaped counter plate (3) is provided with a screw hole and a pin hole, the other end of the arc-shaped counter plate is of an arc structure, and the radius of the arc is half of the diameter of the blade tip of the rotor.
9. The measuring method of the aircraft engine rotor blade tip diameter measuring device based on any one of claims 1 to 8 is characterized by comprising the following steps:
hanging a standard part on a rotor rear shaft neck (9) on a machine tool, arranging a measuring tool on a machine tool guide rail (12), locating right below the standard part and contacting with the standard part, and arranging a dial indicator (8) on the measuring tool;
swinging the standard component to return a dial indicator (8) on the measuring tool to zero, thereby finishing the meter setting;
translating the measuring tool to the blade tip part of the measured blade to measure the blade tip of the rotor, rotating the rotor and measuring the blade tips of other blades;
and (5) swinging the standard component to determine whether the meter calibration is twice zeroed, and repeating the steps if the meter calibration is not zeroed.
10. The method for measuring the diameter of the blade tip of the aircraft engine rotor according to claim 9, wherein during measurement, a measuring tool for aligning a meter is placed on a machine tool guide rail (12), the bottom surface and one side surface of the measuring tool are attached to the machine tool guide rail (12), the measuring tool is translated to the blade tip part of the measured blade, so that the measurement of the first blade is completed, and then the rotor is slowly rotated along the axis of the rotor, so that the measurement of the blade tips of other blades at the level is completed;
rotor tip diameter D =2 × (actual value of standard R + value of table L)
The actual value R of the standard component is a rated value of the standard component which is periodically checked, and the table value L is a deflection value of the standard component when the blade is measured after the table is checked.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211436096.7A CN115711565A (en) | 2022-11-16 | 2022-11-16 | Device and method for measuring blade tip diameter of aeroengine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211436096.7A CN115711565A (en) | 2022-11-16 | 2022-11-16 | Device and method for measuring blade tip diameter of aeroengine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115711565A true CN115711565A (en) | 2023-02-24 |
Family
ID=85233465
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211436096.7A Pending CN115711565A (en) | 2022-11-16 | 2022-11-16 | Device and method for measuring blade tip diameter of aeroengine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115711565A (en) |
-
2022
- 2022-11-16 CN CN202211436096.7A patent/CN115711565A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105509595B (en) | Beating degree detection equipment | |
| CN108469238B (en) | Calibration control method of automatic camshaft measuring instrument | |
| CN201858953U (en) | Vertex angle detector of cutter | |
| CN106643576B (en) | Method and device for measuring non-concentricity | |
| CN211783158U (en) | Impeller, leaf disc class part rapid survey frock | |
| CN110732918A (en) | Complex multistage cone blade rotor and stator blade tip measuring method and grinding processing method | |
| CN113084706B (en) | Automatic measurement method for grinding blade tips of multistage stationary blades of gas compressor | |
| CN216745778U (en) | Six-point positioning measuring tool for turbine blade | |
| CN111043930A (en) | Measuring device for pitch diameter radial run-out of external thread of threaded sleeve | |
| CN214149110U (en) | Shaft centering tool | |
| CN112595281B (en) | Method and medium for rapidly measuring surface profile of workpiece | |
| CN115711565A (en) | Device and method for measuring blade tip diameter of aeroengine rotor | |
| CN209181664U (en) | A kind of radius of gyration measuring device of turbine blade bacterial type blade root | |
| CN201561747U (en) | Special fixture for measuring hobbing cutter of three-coordinate measuring system | |
| CN116481476A (en) | Aeroengine medium-pressure air compressor and turbine blade profile measuring method | |
| CN110779418A (en) | Method for measuring length of cone on line by double meters | |
| CN106903612B (en) | Tool detector and implementation method | |
| CN112254606B (en) | Measuring tool and measuring method for measuring radial size of rotor blade tip | |
| CN211042049U (en) | Utensil is examined to accurate measurement slot position | |
| CN112197671A (en) | Device and method for detecting distance from blade fixed point to casing end face | |
| CN220524805U (en) | Special measuring tool for measuring installation flat position of stator blade of aero-engine | |
| CN217465639U (en) | Measuring device for chamfer depth of hub spoke hole | |
| CN110926314A (en) | Synchronous detection method for eccentric surfaces of double-eccentric gear | |
| CN213238740U (en) | Beam leaf angular direction detection tool | |
| CN218511629U (en) | Bearing inner and outer ring height measuring device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |