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CN114459392A - System and method for measuring exhaust area of turbine guider of aircraft engine - Google Patents

System and method for measuring exhaust area of turbine guider of aircraft engine Download PDF

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Publication number
CN114459392A
CN114459392A CN202210125061.5A CN202210125061A CN114459392A CN 114459392 A CN114459392 A CN 114459392A CN 202210125061 A CN202210125061 A CN 202210125061A CN 114459392 A CN114459392 A CN 114459392A
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CN
China
Prior art keywords
aircraft engine
exhaust area
turbine guider
engine turbine
guider
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Pending
Application number
CN202210125061.5A
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Chinese (zh)
Inventor
高继昆
闫峰
李季
王晓艳
张涛
王荣誉
权伊明
赵海
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AECC Shenyang Engine Research Institute
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AECC Shenyang Engine Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN202210125061.5A priority Critical patent/CN114459392A/en
Publication of CN114459392A publication Critical patent/CN114459392A/en
Pending legal-status Critical Current

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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01BMEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00Measuring arrangements characterised by the use of optical techniques
    • G01B11/28Measuring arrangements characterised by the use of optical techniques for measuring areas

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Length Measuring Devices By Optical Means (AREA)

Abstract

The application relates to an aeroengine turbine director exhaust area measurement system includes: the single-shaft rotary table is connected with the turbine guider of the aero-engine and can drive the turbine guider of the aero-engine to rotate; an optical scanner; the six-degree-of-freedom mechanical arm is connected with the optical scanner and can drive the optical scanner to move relative to the single-shaft turntable; the controller is connected with the single-shaft turntable, the six-degree-of-freedom mechanical arm and the optical scanner, can control the single-shaft turntable and the six-degree-of-freedom mechanical arm to cooperatively act, and can control the optical scanner to acquire three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine; and the computer is connected with the optical scanner and can calculate the exhaust area of the turbine guider of the aircraft engine according to the three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine. Furthermore, the invention relates to a method for measuring the exhaust area of a turbine guide of an aircraft engine.

Description

System and method for measuring exhaust area of turbine guider of aircraft engine
Technical Field
The application belongs to the technical field of measuring the exhaust area of an aircraft engine turbine guider, and particularly relates to a system and a method for measuring the exhaust area of the aircraft engine turbine guider.
Background
The total exhaust area of the turbine guider and the exhaust areas of the windows of the turbine guider in the aircraft engine have important influence on the performance of the aircraft engine, the total exhaust area of the turbine guider of the aircraft engine and the exhaust areas of the windows of the turbine guider are accurately obtained, and guidance can be provided for machining, manufacturing and performance prediction of the turbine guider.
Currently, the total exhaust area of an aircraft engine turbine nozzle and the exhaust area of each window thereof are mainly measured by the following three methods:
1) the method comprises the steps of measuring relevant geometric parameters of the turbine guider of the aero-engine by using a special measuring tool calibrated by a standard sample, and calculating to obtain the total exhaust area and each window exhaust area of the turbine guider of the aero-engine according to the measured geometric parameters, wherein the method is complex in operation and low in measurement efficiency, multiple geometric parameter supports are needed for calculation to obtain the total exhaust area and each window exhaust area of the turbine guider of the aero-engine, data accumulation errors are transmitted, and the errors are large;
2) the method comprises the following steps of (1) acquiring three-dimensional point coordinates on an aircraft engine turbine guider by using a three-dimensional measuring machine, and calculating to obtain the total exhaust area and the exhaust area of each window of the aircraft engine turbine guider according to the measured three-dimensional point coordinates;
3) according to the acoustic resonance frequency method, a Helmholtz resonance cavity is in sealing contact with guide blades of the turbine guider of the aircraft engine, the resonance frequency with the largest acoustic wave transmission loss is identified by using an acoustic principle, the volume of the resonance cavity is calculated according to the frequency, and the exhaust area of each window of the turbine guider of the aircraft engine is calculated.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine turbine nozzle exhaust area measurement system and method thereof to overcome or mitigate at least one aspect of the known prior art deficiencies.
The technical scheme of the application is as follows:
one aspect provides an aircraft engine turbine vane exhaust area measurement system comprising:
the single-shaft rotary table is connected with the turbine guider of the aero-engine and can drive the turbine guider of the aero-engine to rotate;
an optical scanner;
the six-degree-of-freedom mechanical arm is connected with the optical scanner and can drive the optical scanner to move relative to the single-shaft turntable;
the controller is connected with the single-shaft turntable, the six-degree-of-freedom mechanical arm and the optical scanner, can control the single-shaft turntable and the six-degree-of-freedom mechanical arm to cooperatively act, and can control the optical scanner to acquire three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine;
and the computer is connected with the optical scanner and can calculate the exhaust area of the turbine guider of the aircraft engine according to the three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine.
According to at least one embodiment of the application, in the system for measuring the exhaust area of the turbine guider of the aircraft engine, the computer calculates the exhaust area of the turbine guider of the aircraft engine according to the three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine, and the calculation includes the calculation of the total exhaust area of the turbine guider of the aircraft engine and the exhaust areas of all windows of the turbine guider of the aircraft engine.
According to at least one embodiment of the application, in the aircraft engine turbine guider exhaust area measuring system, the system further comprises:
and one end of the positioning shaft is connected to the single-shaft turntable, and the other end of the positioning shaft is connected to the turbine guider of the aircraft engine.
According to at least one embodiment of the application, in the aircraft engine turbine guider exhaust area measuring system, the positioning shaft is made of carbon fiber materials.
According to at least one embodiment of the application, in the aircraft engine turbine guider exhaust area measuring system, the positioning shaft is provided with a positioning mark point;
the optical scanner can collect the space coordinates of the positioning mark points, and the space coordinates of the positioning mark points are used as a positioning reference to splice the three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine.
In another aspect, a method for measuring an exhaust area of an aircraft engine turbine nozzle guide comprises the following steps:
powder is sprayed on a turbine guider of the aircraft engine;
connecting an aircraft engine turbine guider to one end, back to the single-shaft rotary table, of the positioning shaft;
the controller is used for controlling the single-shaft rotary table and the six-degree-of-freedom mechanical arm to cooperatively act, the position of the optical scanner relative to the single-shaft rotary table is adjusted, the aircraft engine turbine guider is made to rotate, the optical scanner is controlled to acquire three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider and acquire space coordinates of positioning mark points on the positioning shaft;
splicing three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine by using the spatial coordinates of the positioning mark points as a positioning reference through an optical scanner;
and calculating the exhaust area of the turbine guider of the aircraft engine by using a computer according to the three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine.
According to at least one embodiment of the application, in the method for measuring the exhaust area of the turbine guider of the aircraft engine, the calculation of the exhaust area of the turbine guider of the aircraft engine by the computer according to the three-dimensional point cloud coordinates of all parts of the turbine guider of the aircraft engine comprises the calculation of the total exhaust area of the turbine guider of the aircraft engine and the exhaust areas of all windows of the turbine guider of the aircraft engine.
Drawings
FIG. 1 is a schematic view of an aircraft engine turbine nozzle exhaust area measurement system provided by an embodiment of the present application;
wherein:
1-single axis turntable; 2-an aircraft engine turbine guide; 3-an optical scanner; 4-six degree of freedom mechanical arm; 5-a controller; 6-a computer; 7-positioning the shaft.
For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
One aspect provides an aircraft engine turbine vane exhaust area measurement system comprising:
the single-shaft rotary table 1 is connected with an aircraft engine turbine guider 2 and can drive the aircraft engine turbine guider 2 to rotate;
an optical scanner 3;
the six-degree-of-freedom mechanical arm 4 is connected with the optical scanner 3 and can drive the optical scanner 3 to move relative to the single-axis turntable 1;
the controller 5 is connected with the single-axis turntable 1, the six-degree-of-freedom mechanical arm 4 and the optical scanner 3, can control the single-axis turntable 1 and the six-degree-of-freedom mechanical arm 4 to act cooperatively, and can control the optical scanner 3 to acquire three-dimensional point cloud coordinates;
and the computer 6 is connected with the optical scanner 3 and can calculate the exhaust area of the aircraft engine turbine guider 2 according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider 2.
With the system for measuring the exhaust area of the turbine guider of the aircraft engine, the measurement of the exhaust area of the turbine guider 2 of the aircraft engine can be carried out by referring to the following steps:
attaching an aircraft engine turbine guide 2 to a single-shaft turret 1;
the controller 5 is used for controlling the single-shaft turntable 1 and the six-degree-of-freedom mechanical arm 4 to act cooperatively, the position of the optical scanner 3 relative to the single-shaft turntable 1 is adjusted, the aircraft engine turbine guider 2 is made to rotate, and the optical scanner 3 is controlled to acquire three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider 2;
splicing three-dimensional point cloud coordinates of all parts of the turbine guider 2 of the aircraft engine by using an optical scanner 3;
and calculating the exhaust area of the aircraft engine turbine guider 2 by using the computer 6 according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider 2.
In order to prevent reflections from occurring, which could affect the accuracy of the measurement of the exhaust area of the aircraft engine turbine guide 2, powder may be sprayed on the aircraft engine turbine guide 2 before the aircraft engine turbine guide 2 is attached to the single-shaft turntable 1.
For the system for measuring the exhaust area of the turbine guider of the aircraft engine disclosed in the above embodiment, as can be understood by those skilled in the art, the three-dimensional point cloud coordinates of each part of the turbine guider 2 of the aircraft engine are acquired by the optical scanner 3, so that the accuracy and the density are high, the contour of the turbine guider 2 of the aircraft engine can be better reproduced after splicing, and based on the contour, the exhaust area of the turbine guider 2 of the aircraft engine can be more accurately obtained according to the three-dimensional point cloud coordinates of each part of the turbine guider 2 of the aircraft engine.
For the system for measuring the exhaust area of the turbine guider of the aircraft engine disclosed in the above embodiment, those skilled in the art can understand that the controller 5 is designed to control the single-shaft turntable 1 and the six-degree-of-freedom mechanical arm 4 to cooperatively act, adjust the position of the optical scanner 3 relative to the single-shaft turntable 1, rotate the turbine guider 2 of the aircraft engine, and control the optical scanner 3 to acquire the three-dimensional point cloud coordinates of each part of the turbine guider 2 of the aircraft engine, so that the degree of automation is high, and the exhaust area of the turbine guider 2 of the aircraft engine can be accurately and efficiently obtained.
For the system for measuring the exhaust area of the turbine guider of the aircraft engine disclosed in the above embodiment, those skilled in the art can understand that the single-shaft turntable 1 is designed to drive the turbine guider 2 of the aircraft engine to rotate, the angular rotation precision is high, and the system can be regarded as the seventh degree of freedom out of six degrees of freedom by cooperating with the six-degree-of-freedom mechanical arm 4 under the control of the controller 5, so that the relative position and angle between the optical scanner 3 and the turbine guider 2 of the aircraft engine can be accurately positioned, and the collection of the three-dimensional point cloud coordinates of each part of the turbine guider 2 of the aircraft engine can be efficiently realized.
In some optional embodiments, in the system for measuring the exhaust area of the turbine nozzle of the aircraft engine, the computer 6 calculates the exhaust area of the turbine nozzle 2 of the aircraft engine according to the three-dimensional point cloud coordinates of the various parts of the turbine nozzle 2 of the aircraft engine, including calculating the total exhaust area of the turbine nozzle 2 of the aircraft engine and the exhaust areas of the windows thereof.
In some optional embodiments, in the aircraft engine turbine guider exhaust area measurement system, the system further comprises:
location axle 7, one end is connected on unipolar revolving stage 1, aeroengine turbine director 2 is connected to the other end, aeroengine turbine director 2 passes through location axle 7 promptly and connects on unipolar revolving stage 1, 7 one end of unipolar revolving stage 1 dorsad at location axle, the special anchor clamps of accessible design carry out the centre gripping to aeroengine turbine director 2, specifically can be by relevant technical personnel when using the technical scheme that this application discloses, design according to specific reality, or refer to and adopt existing anchor clamps, no longer carry out more detailed explanation here.
In some alternative embodiments, in the aircraft engine turbine guider exhaust area measurement system, the positioning shaft 7 is made of a carbon fiber material, has sufficient strength and rigidity, and has an extremely low thermal expansion coefficient, so that the reliability of the optical scanner 3 for acquiring three-dimensional point cloud coordinates is ensured.
In some alternative embodiments, in the aircraft engine turbine guider exhaust area measuring system, the positioning shaft 7 is provided with positioning mark points;
the optical scanner 3 can collect the space coordinates of the positioning mark points, and the space coordinates of the positioning mark points are used as a positioning reference to splice the three-dimensional point cloud coordinates of all parts of the turbine guider 2 of the aircraft engine.
For the system for measuring the exhaust area of the turbine guide of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the system is designed to collect the three-dimensional point cloud coordinates of each part of the turbine guide 2 of the aircraft engine by using the optical scanner 3, simultaneously collect the spatial coordinates of the positioning mark points on the positioning shaft 7, further collect the spatial coordinates of the positioning mark points as the positioning reference, and splice the three-dimensional point cloud coordinates of each part of the turbine guide 2 of the aircraft engine, so that the system is fast and efficient, the positioning mark points can be specifically marks which are easily identified and are pasted on the positioning shaft 7, and specifically distributed positions and the number thereof can be designed according to specific practice by related technical personnel when applying the technical scheme disclosed in the application, and no further limitation is performed here.
In some optional embodiments, in the system for measuring the exhaust area of the turbine vane of the aircraft engine, an existing dedicated measurement tool for the turbine vane of the aircraft engine may be selected, one end of the measurement tool is connected to the single-shaft turntable, and the other end of the measurement tool clamps the turbine vane of the aircraft engine to replace the positioning shaft 7.
In another aspect, a method for measuring an exhaust area of an aircraft engine turbine nozzle guide comprises the following steps:
calibrating the single-axis turntable 1, the optical scanner 3 and the six-degree-of-freedom mechanical arm 4 to realize the unification of coordinate systems;
powder is sprayed on the turbine guider 2 of the aircraft engine;
connecting the turbine guider 2 of the aircraft engine to one end, back to the single-shaft rotary table 1, of the positioning shaft 7;
the controller 5 is used for controlling the single-shaft turntable 1 and the six-degree-of-freedom mechanical arm 4 to act cooperatively, the position of the optical scanner 3 relative to the single-shaft turntable 1 is adjusted, the aircraft engine turbine guider 2 is made to rotate, the optical scanner 3 is controlled to acquire three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider 2, and spatial coordinates of positioning mark points on the positioning shaft 7 are acquired;
splicing three-dimensional point cloud coordinates of all parts of the turbine guider 2 of the aircraft engine by taking the space coordinates of the positioning mark points as a positioning reference through the optical scanner 3;
and calculating the exhaust area of the aircraft engine turbine guider 2 by using the computer 6 according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider 2.
In some alternative embodiments, in the method for measuring the exhaust area of the turbine nozzle of the aircraft engine, the computer 6 calculates the exhaust area of the turbine nozzle 2 of the aircraft engine according to the three-dimensional point cloud coordinates of the various parts of the turbine nozzle 2 of the aircraft engine, including calculating the total exhaust area of the turbine nozzle 2 of the aircraft engine and the exhaust areas of the windows thereof.
For the aircraft engine turbine guider exhaust area measurement method disclosed in the above embodiment, the description is simpler based on the aircraft engine turbine guider exhaust area measurement system disclosed in the above embodiment, specific relevant points can be referred to the relevant description of the aircraft engine turbine guider exhaust area measurement system part, and the technical effects can also refer to the technical effects of the relevant parts of the aircraft engine turbine guider exhaust area measurement system, and are not repeated herein.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.

Claims (7)

1. An aircraft engine turbine nozzle exhaust area measurement system, comprising:
the single-shaft rotary table (1) is connected with an aircraft engine turbine guider (2) and can drive the aircraft engine turbine guider (2) to rotate;
an optical scanner (3);
the six-degree-of-freedom mechanical arm (4) is connected with the optical scanner (3) and can drive the optical scanner (3) to move relative to the single-shaft turntable (1);
the controller (5) is connected with the single-shaft rotary table (1), the six-degree-of-freedom mechanical arm (4) and the optical scanner (3), can control the single-shaft rotary table (1) and the six-degree-of-freedom mechanical arm (4) to act in a coordinated mode, and can control the optical scanner (3) to collect three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2);
and the computer (6) is connected with the optical scanner (3) and can calculate the exhaust area of the aircraft engine turbine guider (2) according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2).
2. The aircraft engine turbine nozzle exhaust area measurement system of claim 1,
and the computer (6) calculates the exhaust area of the aircraft engine turbine guider (2) according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2), and the calculation comprises the calculation of the total exhaust area of the aircraft engine turbine guider (2) and the exhaust area of all windows of the aircraft engine turbine guider.
3. The aircraft engine turbine nozzle exhaust area measurement system of claim 1,
further comprising:
and one end of the positioning shaft (7) is connected to the single-shaft turntable (1), and the other end of the positioning shaft is connected to the aircraft engine turbine guider (2).
4. The aircraft engine turbine nozzle exhaust area measurement system of claim 3,
the positioning shaft (7) is made of carbon fiber materials.
5. The aircraft engine turbine nozzle exhaust area measurement system of claim 3,
the positioning shaft (7) is provided with a positioning mark point;
the optical scanner (3) can collect the space coordinates of the positioning mark points, and the space coordinates of the positioning mark points are used as a positioning reference to splice the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2).
6. A method for measuring an exhaust area of an aircraft engine turbine nozzle, comprising:
powder is sprayed on the turbine guider (2) of the aircraft engine;
connecting the turbine guider (2) of the aircraft engine to one end, back to the single-shaft rotary table (1), of the positioning shaft (7);
the controller (5) is used for controlling the single-shaft rotary table (1) and the six-degree-of-freedom mechanical arm (4) to act cooperatively, the position of the optical scanner (3) relative to the single-shaft rotary table (1) is adjusted, the aircraft engine turbine guider (2) is made to rotate, the optical scanner (3) is controlled to acquire three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2), and spatial coordinates of positioning mark points on the positioning shaft (7) are acquired;
splicing three-dimensional point cloud coordinates of all parts of the turbine guider (2) of the aircraft engine by taking the space coordinates of the positioning mark points as a positioning reference through the optical scanner (3);
and calculating the exhaust area of the aircraft engine turbine guider (2) by using a computer (6) according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2).
7. The aircraft engine turbine nozzle exhaust area measurement method according to claim 6,
and the computer (6) is used for calculating the exhaust area of the aircraft engine turbine guider (2) according to the three-dimensional point cloud coordinates of all parts of the aircraft engine turbine guider (2), and the calculation comprises the calculation of the total exhaust area of the aircraft engine turbine guider (2) and the exhaust area of all windows of the aircraft engine turbine guider.
CN202210125061.5A 2022-02-10 2022-02-10 System and method for measuring exhaust area of turbine guider of aircraft engine Pending CN114459392A (en)

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CN202210125061.5A CN114459392A (en) 2022-02-10 2022-02-10 System and method for measuring exhaust area of turbine guider of aircraft engine

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117906967A (en) * 2024-03-07 2024-04-19 江西中发天信航空发动机科技有限公司 Turbine guide exhaust area measurement equipment and measurement method

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113686268A (en) * 2021-07-13 2021-11-23 北京航天计量测试技术研究所 Automatic measuring system and method for exhaust area of turbine guider
CN113834450A (en) * 2021-08-12 2021-12-24 北京航天计量测试技术研究所 Automatic measuring system and method for exhaust area of turbine guider

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113686268A (en) * 2021-07-13 2021-11-23 北京航天计量测试技术研究所 Automatic measuring system and method for exhaust area of turbine guider
CN113834450A (en) * 2021-08-12 2021-12-24 北京航天计量测试技术研究所 Automatic measuring system and method for exhaust area of turbine guider

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117906967A (en) * 2024-03-07 2024-04-19 江西中发天信航空发动机科技有限公司 Turbine guide exhaust area measurement equipment and measurement method
CN117906967B (en) * 2024-03-07 2024-05-31 江西中发天信航空发动机科技有限公司 Turbine guide exhaust area measurement equipment and measurement method

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