CN111609826A - Method and device for measuring blade tip clearance of aircraft engine - Google Patents
Method and device for measuring blade tip clearance of aircraft engine Download PDFInfo
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- CN111609826A CN111609826A CN202010511497.9A CN202010511497A CN111609826A CN 111609826 A CN111609826 A CN 111609826A CN 202010511497 A CN202010511497 A CN 202010511497A CN 111609826 A CN111609826 A CN 111609826A
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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
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/16—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance of clearance between spaced objects
Abstract
The invention provides a method for measuring blade tip clearance of an aero-engine, which relates to the technical field of aero-engine assembly and comprises the following steps: and pre-assembling the parts to be assembled, and constructing a pre-assembled casing model. And acquiring the blade tip outline data of the blade, constructing a three-dimensional model of the blade tip outline, and acquiring a blade tip outline model. And formally assembling the pre-assembled casing to obtain a formally assembled casing model. Calculating positional offset data using a finite element analysis method based on the pre-assembled casing model and the formal assembled casing model. And obtaining the predicted data of the tip clearances of the plurality of blades according to the tip contour model and the position deviation data. The problem of prior art exist can't realize accurate apex clearance measurement at aeroengine assembling process is solved, guaranteed to be in the best running state after the aeroengine assembly, have the significance to aeroengine's performance and structure safety.
Description
Technical Field
The invention relates to the technical field of aero-engine assembly, in particular to a method and a device for measuring blade tip clearance of an aero-engine.
Background
The blade tip clearance is a basic parameter in the design process of the aero-engine, and the size of the blade tip clearance has great influence on the performance and the structural safety of the aero-engine. Generally, the smaller the blade tip clearance is, the lower the fuel consumption rate of the aircraft engine is, the longer the service life is, and meanwhile, the performance of the aircraft engine can be effectively improved. However, too small blade tip clearance also easily causes the collision and friction between the blade tip of the rotor of the aircraft engine and the casing, thereby causing certain potential safety hazard. Because the blade tip clearance of the aeroengine is small, the operation environment is severe, and the accurate measurement and analysis and evaluation of the blade tip clearance are difficult to realize in the operation process.
Therefore, the prior art has the problems that: how to provide a blade tip clearance measuring method in the assembly process of an aircraft engine so as to realize accurate blade tip clearance measurement to ensure that the aircraft engine is in an optimal operation state.
Disclosure of Invention
In view of the above, the present invention provides a method and a device for measuring a blade tip clearance of an aircraft engine, so as to solve the problems in the prior art.
In one aspect, the invention provides a blade tip clearance measurement method for an aircraft engine, which is applied to parts to be assembled of the aircraft engine, wherein the parts to be assembled comprise a plurality of blades and a brake, and the method comprises the following steps: and pre-assembling the parts to be assembled, and constructing a pre-assembled casing model. And acquiring the blade tip outline data of the blade, constructing a three-dimensional model of the blade tip outline, and acquiring a blade tip outline model. And formally assembling the pre-assembled casing to obtain a formally assembled casing model. Calculating positional offset data using a finite element analysis method based on the pre-assembled casing model and the formal assembled casing model. And obtaining the predicted data of the tip clearances of the plurality of blades according to the tip contour model and the position deviation data.
According to a specific implementation manner of the present disclosure, the to-be-assembled part includes a bearing and a casing, and the step of pre-assembling the to-be-assembled part and constructing a pre-assembled casing model includes: and pre-assembling the parts to be assembled to obtain a pre-assembled casing, wherein the pre-assembling is to stack the parts to be assembled. And acquiring the concentricity between the casing of the part to be assembled and the bearing. And constructing a three-dimensional model of the blade tip outline according to the concentricity to obtain the preassembled casing model.
According to a specific implementation manner of the present disclosure, the step of obtaining the predicted data of the tip clearance according to the tip contour model and the position offset data includes: and obtaining the prediction data of the tip clearance according to the concentricity, the tip contour model and the position deviation data.
According to a specific implementation manner of the present disclosure, the gate includes features such as a flange, a spigot, an inner wall, and an outer wall, and the step of pre-assembling the part to be assembled and constructing a pre-assembled casing model includes: and pre-assembling the parts to be assembled to obtain a pre-assembled casing. And acquiring the size characteristic data of the flange, the spigot, the inner wall and the outer wall of the pre-assembled casing. And obtaining a pre-assembly casing model according to the size characteristic data.
According to a specific implementation manner of the present disclosure, the to-be-assembled part further includes a rotor, and the step of obtaining the tip contour data of the blade, constructing a three-dimensional model of the tip contour, and obtaining the tip contour model includes: and measuring tip profile data of the blade by taking the end face of the rotor matched with the bearing as a reference. And constructing a three-dimensional model of the tip profile according to the tip profile data to obtain a tip profile model.
According to a specific implementation manner of the present disclosure, the step of calculating the position offset data according to the pre-assembly casing model and the formal assembly casing model by using a finite element analysis method includes: and establishing a finite element model of the part to be assembled. Setting an analysis boundary condition of the finite element model. Calculating the positional offset data using a finite element analysis method based on the finite element model, the analytical boundary conditions, the pre-assembled casing model, and the formal assembled casing model.
According to a specific implementation manner of the present disclosure, the step of setting the analysis boundary condition of the finite element model includes: and acquiring position data of the parts to be assembled of the pre-assembled casing model and the formal assembled casing model as the analysis boundary conditions.
According to a specific implementation manner of the present disclosure, the obtaining, according to the tip profile model and the position deviation data, prediction data of tip clearances of the plurality of blades further includes: and acquiring deformation data of the annular characteristic surface matched with the blade tip of the rotor blade in the machine brake by using a finite element analysis method. And obtaining the predicted data of the tip clearances of the plurality of blades according to the deformation data, the tip contour model and the position deviation data.
In another aspect, the present invention provides a tip clearance measuring apparatus applied to the above method, the apparatus including: and the first assembling module is used for pre-assembling the parts to be assembled and constructing a pre-assembled casing model. And the building module is used for obtaining the blade tip outline data of the blade, building a three-dimensional model of the blade tip outline and obtaining a blade tip outline model. And the second assembling module is used for carrying out formal assembly on the pre-assembled casing to obtain a formal assembled casing model. A first calculation module for calculating positional offset data using a finite element analysis method based on the pre-assembled casing model and the formal assembled casing model. And the second calculation module is used for obtaining the predicted data of the tip clearances of the plurality of blades according to the tip contour model and the position deviation data.
According to a specific implementation of the present disclosure, the first assembling module includes: the assembling submodule is used for pre-assembling the parts to be assembled to obtain a pre-assembled casing, and the pre-assembling is to stack the parts to be assembled. And the acquisition submodule is used for acquiring the concentricity between the casing of the part to be assembled and the bearing. And the construction submodule is used for constructing a three-dimensional model of the blade tip outline according to the concentricity to obtain the pre-assembled casing model.
According to the method and the device for measuring the blade tip clearance of the aero-engine, provided by the embodiment of the invention, in the assembling process of the aero-engine, the prediction data of the blade tip clearance is obtained according to the blade tip contour model, the position offset data and the like. The problem of prior art exist can't realize accurate apex clearance measurement at aeroengine assembling process is solved, guaranteed to be in the best running state after the aeroengine assembly, have the significance to aeroengine's performance and structure safety.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a first prior art structure of a casing of an aircraft engine;
FIG. 2 is a schematic view of a second prior art configuration of a casing of an aircraft engine;
FIG. 3 is a flow chart of a method for measuring the blade tip clearance of an aircraft engine according to the present invention;
fig. 4 is a block diagram of a blade tip clearance measuring device provided by the present invention.
Reference numerals:
1-a flange; 2-outer wall; 3-outer wall holes; 4-inner wall; 5-rotor.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to or other than one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present disclosure, and the drawings only show the components related to the present disclosure rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic diagram of an external mechanism of a prior art aero-engine casing, and fig. 2 is a schematic diagram of an internal structure of the prior art aero-engine casing. The parts to be assembled of the existing aircraft engine comprise a blade, a bearing, a casing, an inner wall 4, an outer wall 2, a flange 1, a rotor 5, an outer wall hole 3 and other mechanisms, and the parts need to be assembled as shown in fig. 1 and 2 in actual operation.
However, the problems in the prior art are that the blade tip clearance of the aeroengine is small, the operation environment is severe, and the accurate measurement and analysis and evaluation of the blade tip clearance are difficult to realize in the operation process.
In view of the above, the inventor has conducted long-term research and continuous research to provide a method and an apparatus 600 for measuring blade tip clearance of an aircraft engine according to the embodiment of the present invention.
Example 1
As shown in fig. 3, the invention provided for the embodiment of the invention provides a method for measuring a blade tip clearance of an aircraft engine, which includes:
and S10, pre-assembling the parts to be assembled and constructing a pre-assembled casing model.
Pre-assembling the parts to be assembled of the two sections of aeroengine casings to be assembled, wherein the pre-assembling is to simply stack the parts to be assembled together. And after the preassembly is finished, precisely measuring the stacked casings, and reversely reconstructing a three-dimensional digital model of the assembly body. In one embodiment, the steps specifically include:
and pre-assembling the parts to be assembled to obtain a pre-assembled casing, wherein the pre-assembling is to stack the parts to be assembled.
Specifically, the parts of two sections of aircraft engines assembled are stacked from bottom to top (preassembled).
And acquiring the size characteristic data of the flange, the spigot, the inner wall and the outer wall of the pre-assembled casing. And obtaining a pre-assembly casing model according to the size characteristic data.
Specifically, after the stack installation is completed, three-dimensional coordinate measurement is performed on key features of each part in the pre-assembled casing, such as a flange, an outer wall, an inner wall 8 matched with the rotor, and the like, so as to obtain size feature data of the pre-assembled casing.
And acquiring the concentricity between the casing of the part to be assembled and the bearing.
And constructing a three-dimensional model of the blade tip outline according to the concentricity and the size characteristic data to obtain the pre-assembled casing model.
And (3) performing three-dimensional reconstruction on the pre-assembled casing by using the measured data, namely concentricity, dimensional characteristic data and the like, and determining an exact digital model of the pre-assembled casing and each part after the stacking assembly is completed, namely a pre-assembled casing model.
And S20, obtaining the tip outline data of the blade, constructing a three-dimensional model of the tip outline, and obtaining a tip outline model.
And measuring tip profile data of the blade by taking the end face of the rotor matched with the bearing as a reference. And constructing a three-dimensional model of the tip profile according to the tip profile data to obtain a tip profile model.
And S30, carrying out formal assembly on the pre-assembled casing to obtain a formal assembly casing model.
According to the actual assembly process of the aircraft engine, the stacking process of the parts to be assembled in the step S10 belongs to a pre-assembly link, and the parts to be assembled are disassembled after the specific installation process parameters of the parts to be assembled are determined through pre-assembly. And then, according to the installation process parameters of the parts to be assembled determined in the pre-assembly process, completing the formal assembly of the parts to be assembled in the rotor formal assembly process of the aircraft engine. In the process, parts such as a rotor of the engine, a combustion chamber and the like are installed inside the casing of the aircraft engine.
In practice, after the assembly of the rotor of the aircraft engine is completed, parts with thin-wall structural features are usually deformed to some extent. At this time, the three-dimensional coordinate measurement is performed again on the pre-assembled casing according to the same reference as the step S10 — the key features such as holes and the like on the flange of the pre-assembled casing and the external profile of the pre-assembled casing are measured with emphasis, and the three-dimensional reconstruction of the measured features is completed.
And S40, calculating position deviation data according to the pre-assembly casing model and the formal assembly casing model by using a finite element analysis method.
And establishing a finite element model of the part to be assembled.
And introducing a pre-assembled casing model, and establishing a structural deformation finite element analysis model of the aircraft engine casing assembly.
Setting an analysis boundary condition of the finite element model.
And acquiring position data of the parts to be assembled of the pre-assembled casing model and the formal assembled casing model as the analysis boundary conditions.
Specifically, position deviation data obtained by two measurements performed according to the same key features of the preassembled casing are taken as displacement boundary conditions of the structural deformation analysis process and are brought into the finite element model.
Calculating the positional offset data using a finite element analysis method based on the finite element model, the analytical boundary conditions, the pre-assembled casing model, and the formal assembled casing model.
On the basis of the finite element model and the boundary conditions, carrying out structural deformation finite element analysis work of the pre-assembled case of the aircraft engine, and acquiring detailed structural deformation data of the pre-assembled case and each part of the pre-assembled case.
And S50, obtaining the predicted data of the tip clearances of the plurality of blades according to the tip contour model and the position deviation data.
After the assembly work of the aero-engine is completed, the three-dimensional numerical reconstruction is carried out on the casing by using the deformation data, the concentricity data and the blade tip profile data through the connection relation between the rotor, the bearing and the casing in the assembly of the aero-engine.
In one embodiment, the predicted data for the tip clearance is obtained based on the concentricity, the tip profile model, and the positional offset data.
Specifically, deformation data of the annular feature surfaces of the rotor and the blade tip of the blade are obtained by using a finite element analysis method. And obtaining the predicted data of the tip clearances of the plurality of blades according to the deformation data, the tip contour model and the position deviation data, and completing the measurement of the tip clearances.
Example 2
Referring to fig. 4, in order to provide a tip clearance measuring apparatus 600 according to an embodiment of the present invention, the apparatus 600 is applied to the above method, and includes:
and the first assembling module 610 is used for pre-assembling the parts to be assembled and constructing a pre-assembled casing model.
And the constructing module 620 is configured to obtain the tip contour data of the blade, construct a three-dimensional model of the tip contour, and obtain a tip contour model.
A second assembling module 630, configured to perform formal assembly on the pre-assembled casing, so as to obtain a formal assembled casing model.
A first calculation module 640 for calculating positional offset data using a finite element analysis method based on the pre-assembled casing model and the formal assembled casing model.
A second calculating module 650, configured to obtain predicted data of tip clearances of the plurality of blades according to the tip contour model and the position deviation data.
In one embodiment, the first assembly module 610 includes:
the assembling submodule is used for pre-assembling the parts to be assembled to obtain a pre-assembled casing, and the pre-assembling is to stack the parts to be assembled.
And the acquisition submodule is used for acquiring the concentricity between the casing of the part to be assembled and the bearing. And the construction submodule is used for constructing a three-dimensional model of the blade tip outline according to the concentricity to obtain the pre-assembled casing model.
According to the method and the device for measuring the blade tip clearance of the aero-engine, provided by the embodiment of the invention, in the assembling process of the aero-engine, the prediction data of the blade tip clearance is obtained according to the blade tip contour model, the position offset data and the like. The problem of prior art exist can't realize accurate apex clearance measurement at aeroengine assembling process is solved, guaranteed to be in the best running state after the aeroengine assembly, no matter in result degree of accuracy, simple operation nature, aassessment efficiency and working cost, all have the significance to aeroengine's assembly engineering.
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (10)
1. The method for measuring the blade tip clearance of the aircraft engine is characterized by being applied to parts to be assembled of the aircraft engine, wherein the parts to be assembled comprise a plurality of blades and a brake, and the method comprises the following steps:
pre-assembling the parts to be assembled, and constructing a pre-assembled casing model;
acquiring tip outline data of the blade, constructing a three-dimensional model of the tip outline, and acquiring a tip outline model;
formally assembling the pre-assembled casing to obtain a formally assembled casing model;
calculating position deviation data by using a finite element analysis method according to the preassembly casing model and the formal assembly casing model;
and obtaining the predicted data of the tip clearances of the plurality of blades according to the tip contour model and the position deviation data.
2. The method of claim 1, wherein the parts to be assembled include a bearing and a casing, and the step of pre-assembling the parts to be assembled and building a pre-assembled casing model comprises:
pre-assembling the parts to be assembled to obtain a pre-assembled casing, wherein the pre-assembling is to stack the parts to be assembled;
acquiring the concentricity between the casing and the bearing of the part to be assembled;
and constructing a three-dimensional model of the blade tip outline according to the concentricity to obtain the preassembled casing model.
3. The method of claim 2, wherein said step of obtaining predicted data of said tip clearance based on said tip profile model and said position offset data comprises:
and obtaining the prediction data of the tip clearance according to the concentricity, the tip contour model and the position deviation data.
4. The method of claim 1, wherein the gate includes features of a flange, a spigot, an inner wall, and an outer wall, and wherein the pre-assembling the part to be assembled and building a pre-assembled casing model comprises:
pre-assembling the part to be assembled to obtain a pre-assembled casing;
acquiring size characteristic data of a flange, a spigot, an inner wall and an outer wall of the pre-assembled casing;
and obtaining a pre-assembly casing model according to the size characteristic data.
5. The method according to claim 3, wherein the part to be assembled further comprises a rotor, and the step of obtaining tip profile data of the blade, constructing a three-dimensional model of the tip profile, and obtaining a tip profile model comprises:
measuring tip profile data of the blade by taking the end face of the rotor matched with the bearing as a reference;
and constructing a three-dimensional model of the tip profile according to the tip profile data to obtain a tip profile model.
6. The method of claim 5, wherein said step of calculating positional offset data from said pre-assembled casing model and said formal assembled casing model using a finite element analysis method comprises:
establishing a finite element model of the part to be assembled;
setting an analysis boundary condition of the finite element model;
calculating the positional offset data using a finite element analysis method based on the finite element model, the analytical boundary conditions, the pre-assembled casing model, and the formal assembled casing model.
7. The method of claim 6, wherein the step of setting analytical boundary conditions for the finite element model comprises:
and acquiring position data of the parts to be assembled of the pre-assembled casing model and the formal assembled casing model as the analysis boundary conditions.
8. The method of claim 7, wherein said step of obtaining tip clearance prediction data for a plurality of said blades based on said tip profile model and said position offset data comprises:
obtaining deformation data of an annular characteristic surface matched with the blade tip of the rotor blade in the machine brake by using a finite element analysis method;
and obtaining the predicted data of the tip clearances of the plurality of blades according to the deformation data, the tip contour model and the position deviation data.
9. An aeroengine tip clearance measurement device, characterized in that, when applied to the method of any one of claims 1-8, the device comprises:
the first assembling module is used for pre-assembling the parts to be assembled and constructing a pre-assembled casing model;
the construction module is used for acquiring the blade tip outline data of the blade, constructing a three-dimensional model of the blade tip outline and acquiring a blade tip outline model;
the second assembly module is used for carrying out formal assembly on the pre-assembled casing to obtain a formal assembly casing model;
a first calculation module, configured to calculate position offset data using a finite element analysis method according to the pre-assembly casing model and the formal assembly casing model;
and the second calculation module is used for obtaining the predicted data of the tip clearances of the plurality of blades according to the tip contour model and the position deviation data.
10. The apparatus of claim 9, wherein the first assembly module comprises:
the assembling submodule is used for pre-assembling the parts to be assembled to obtain a pre-assembled casing, and the pre-assembling is to stack the parts to be assembled;
the acquisition submodule is used for acquiring the concentricity between the casing and the bearing of the part to be assembled;
and the construction submodule is used for constructing a three-dimensional model of the blade tip outline according to the concentricity to obtain the pre-assembled casing model.
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| CN115235404A (en) * | 2022-09-22 | 2022-10-25 | 中国航发燃气轮机有限公司 | Rotor and stator clearance correction method for heavy gas turbine |
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| CN111609826B (en) | 2021-09-14 |
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Effective date of registration: 20220822 Address after: 100089 Qinghua garden, Haidian District, Beijing Patentee after: TSINGHUA University Patentee after: AECC SHENYANG ENGINE Research Institute Address before: 100084 No. 1 Tsinghua Yuan, Beijing, Haidian District Patentee before: TSINGHUA University |