CN111368472A - Model correction method for additive manufacturing of gas turbine parts - Google Patents
Model correction method for additive manufacturing of gas turbine parts Download PDFInfo
- Publication number
- CN111368472A CN111368472A CN202010135501.6A CN202010135501A CN111368472A CN 111368472 A CN111368472 A CN 111368472A CN 202010135501 A CN202010135501 A CN 202010135501A CN 111368472 A CN111368472 A CN 111368472A
- Authority
- CN
- China
- Prior art keywords
- model
- deformation
- gas turbine
- additive manufacturing
- state model
- 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.)
- Withdrawn
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
- B29C64/30—Auxiliary operations or equipment
- B29C64/386—Data acquisition or data processing for additive manufacturing
- B29C64/393—Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
Abstract
The invention relates to the field of gas turbine design and manufacture, and discloses a model correction method for additive manufacturing of gas turbine parts, which is used for correcting a hot-state model to obtain a cold-state model based on the deformation factors of the gas turbine parts caused by the working conditions of high temperature, high pressure and high rotating speed in the working process of the gas turbine parts; based on the factor that the gas turbine part deforms due to the fact that internal stress is formed by temperature gradient in the additive manufacturing process, the cold state model is corrected, and the transition state model is obtained, so that the gas turbine part obtained through additive manufacturing according to the transition state model meets the size requirement and the appearance requirement, and the gas turbine part obtained through additive manufacturing meets various working requirements when in use.
Description
Technical Field
The invention relates to the field of design and manufacture of gas turbines, in particular to a model correction method for additive manufacturing of gas turbine parts.
Background
Most parts of the gas turbine, especially rotating parts, operate in extreme operating environments such as high temperature, high pressure, high rotational speed, and the like. The shapes of the above parts are affected by temperature, pressure and rotation speed, and may take on completely different geometric forms during operation than during non-operation. In addition, in the prior art, the 3D printing technology is generally adopted to perform additive manufacturing on the parts of the gas turbine, and when the additive manufacturing is performed according to the model to be manufactured, the deformation between the manufactured model and the model to be manufactured is large due to the influence of various factors in the additive manufacturing process, so that the production and manufacturing requirements are difficult to meet.
Due to the above two factors, it is difficult to meet production design requirements for gas turbine components obtained by additive manufacturing.
Disclosure of Invention
The invention aims to provide a model correction method for an additive manufacturing gas turbine part, which can correct a model of the additive manufacturing gas turbine part to obtain the gas turbine part meeting the working requirement.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method of model modification for additive manufacturing of a gas turbine component, comprising the steps of:
step 1, designing the pneumatic appearance of the gas turbine part under a preset working condition according to a load requirement;
step 2, the pneumatic appearance is materialized through three-dimensional modeling to obtain a solid model under a preset working condition, and the structure of the solid model is optimized under the preset working condition by utilizing finite element analysis to obtain a thermal state model;
step 3, correcting the hot model to obtain a cold model;
and 4, correcting the cold state model to obtain a transition state model.
As a preferred technical solution of the model modification method for manufacturing the gas turbine component by the additive manufacturing method, modifying the hot-state model to obtain the cold-state model includes:
step 31, carrying out finite element analysis on the thermal state model under a preset working condition, and calculating the analysis deformation of the same position before and after the finite element analysis;
step 32: selecting a first deformation area with the analysis deformation exceeding a first preset deformation, and carrying out area division on the first deformation area on the basis of points, lines and surfaces;
step 33, moving the point, line and surface elements of the first deformation area along the opposite direction of deformation according to the analysis deformation amount to obtain updated entity elements;
step 34: and stitching the updated entity elements based on the point, line and plane elements to obtain a materialized first new entity model, and taking the first new entity model as a cold state model.
As a preferred technical solution of the model modification method for manufacturing the gas turbine component by the additive manufacturing method, before the first new solid model is used as the cold state model, the method further includes:
step 35, performing finite element analysis on the first new solid model under a preset working condition, and calculating a first correction deformation amount of deformation at the same position before performing the finite element analysis on the thermal state model and after performing the finite element analysis on the first new solid model;
and step 36, when the first correction deformation is within the first allowable error range, stitching the first new entity model based on the point, line and surface elements to obtain an materialized cold state model.
As a preferred embodiment of the model modification method for the additive manufacturing of the gas turbine component, when the first corrected deformation amount is not within the first allowable error range, the step 32 is performed with the first corrected deformation amount as the analysis deformation amount.
As a preferable technical solution of the model correction method for manufacturing the gas turbine component by the additive manufacturing method, the gas turbine includes a compressor and a turbine blade, and the first preset deformation amount corresponding to the compressor and/or the turbine blade is not greater than 0.05 mm.
As a preferred technical solution of the model modification method for manufacturing a gas turbine component by additive manufacturing, modifying a cold state model to obtain a transition state model includes:
step 41, performing additive manufacturing process simulation based on a cold-state model, and predicting the predicted deformation amount of the same position before and after additive manufacturing;
step 42, selecting a second deformation area with the predicted deformation exceeding a second preset deformation, and carrying out area division on the second deformation area based on the point, the line and the surface;
step 43, moving the point, line and surface elements of the second deformation area along the opposite direction of deformation according to the preset deformation amount to obtain updated entity elements;
and step 44, stitching the updated entity elements based on the point, line and plane elements to obtain a second materialized new entity model, and taking the second new entity model as a cold state model.
As a preferred embodiment of the method for model modification of an additive manufactured gas turbine component, before the second new solid model is used as a cold state model, the method further includes:
step 45, performing additive manufacturing process simulation based on the second new solid model, and calculating a second correction deformation amount of deformation at the same position before the additive manufacturing simulation based on the cold state model and after the additive manufacturing simulation is performed on the second new solid model;
and step 46, when the second correction deformation is within the second allowable error range, stitching the second new entity model based on the point, line and surface elements to obtain the materialized cold state model.
As a preferred embodiment of the model correction method for the additive manufacturing of the gas turbine component, when the second corrected deformation amount is not within the second allowable error range, the step 42 is executed again with the second corrected deformation amount as the predicted deformation amount.
As a preferable technical solution of the model correction method for manufacturing the gas turbine component by the additive manufacturing method, the gas turbine includes a compressor and a turbine blade, and a second preset deformation amount corresponding to the compressor and/or the turbine blade is not greater than 0.05 mm.
As a preferred technical solution of the model modification method for manufacturing the gas turbine component by the additive manufacturing method, the preset working conditions include that the working temperature is greater than 800 ℃, and the working pressure is greater than 3.03 × 105KPa, and the working speed is not lower than 1 × 105r/min。
The invention has the beneficial effects that: the method is based on the deformation factors of the gas turbine parts caused by the working conditions of high temperature, high pressure and high rotation speed in the working process of the gas turbine parts, and corrects the hot state model to obtain the cold state model; based on the factor that the gas turbine part deforms due to the fact that internal stress is formed by temperature gradient in the additive manufacturing process, correcting the cold state model to obtain a transition state model, so that the gas turbine part obtained by additive manufacturing according to the transition state model meets the size requirement and the appearance requirement, and the gas turbine part obtained by additive manufacturing meets various working requirements when in use; the yield of processing the gas turbine parts through the additive manufacturing mode is guaranteed, the manufacturing cost is reduced, the feasibility of the additive manufacturing technology is improved, and the popularization and the application of the additive manufacturing technology are facilitated.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the contents of the embodiments of the present invention and the drawings without creative efforts.
FIG. 1 is a flow chart of a model modification method for additive manufacturing of a gas turbine component provided by an embodiment of the invention;
FIG. 2 is a flowchart of modifying a hot model to obtain a cold model according to an embodiment of the present invention;
fig. 3 is a flowchart of modifying a cold state model to obtain a transition state model according to an embodiment of the present invention.
Detailed Description
In order to make the technical problems solved, the technical solutions adopted and the technical effects achieved by the present invention clearer, the technical solutions of the present invention are further described below by way of specific embodiments with reference to the accompanying drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the elements associated with the present invention are shown in the drawings.
As shown in fig. 1, the present embodiment provides a model modification method for additive manufacturing of a gas turbine component, including the following steps:
step 1, designing the pneumatic appearance of the gas turbine part under a preset working condition according to a load requirement;
the load requirements generally refer to working pressure, working temperature and working speed, and correspondingly, the preset working conditions in the embodiment include that the working temperature is greater than 800 ℃, and the working pressure is greater than 3.03 × 105KPa, and the working speed is not lower than 1 × 105r/min. In other embodiments, the limitation of the operating temperature, the operating pressure and the operating speed in the preset operating condition is not limited to the specific values, but may be other values, which are determined according to the specific components of the gas turbine of the selected engine, and the operating temperature, the operating pressure and the operating speed may be different in different models of engines corresponding to the preset operating condition.
Step 2, the pneumatic appearance is materialized through three-dimensional modeling to obtain a solid model under a preset working condition, and the structure of the solid model is optimized under the preset working condition by utilizing finite element analysis to obtain a thermal state model;
the three-dimensional modeling tools may be Solidworks, Catia, ProE, etc., and the finite element analysis is typically performed using ANSIS to optimize the structure based on structural strength and manufacturing process requirements.
The thermal state model of a gas turbine component generally refers to the state of the gas turbine component when operating under preset operating conditions, i.e., at high temperature, high pressure, and high rotational speed.
Step 3, correcting the hot model to obtain a cold model;
the cold model of a gas turbine component generally refers to the state of the gas turbine component when it is not operating, such as normal temperature, normal pressure, and zero rotational speed.
And 4, correcting the cold state model to obtain a transition state model.
The transition state model of a gas turbine component is generally referred to as a design drawing for manufacturing the gas turbine component.
In the embodiment, based on the deformation factors of the gas turbine parts caused by the working conditions of high temperature, high pressure and high rotation speed in the working process of the gas turbine parts, the hot-state model is corrected to obtain the cold-state model; based on the factor that the gas turbine part deforms due to the fact that internal stress is formed by temperature gradient in the additive manufacturing process, correcting the cold state model to obtain a transition state model, so that the gas turbine part obtained by additive manufacturing according to the transition state model meets the size requirement and the appearance requirement, and the gas turbine part obtained by additive manufacturing meets various working requirements when in use; the yield of processing the gas turbine parts through the additive manufacturing mode is guaranteed, the manufacturing cost is reduced, the feasibility of the additive manufacturing technology is improved, and the popularization and the application of the additive manufacturing technology are facilitated.
As shown in fig. 2, the modifying the hot state model to obtain the cold state model includes:
step 31, carrying out finite element analysis on the thermal state model under a preset working condition, and calculating the analysis deformation of the same position before and after the finite element analysis;
step 32: selecting a first deformation area with the analysis deformation exceeding a first preset deformation, and carrying out area division on the first deformation area on the basis of points, lines and surfaces;
gas turbines include compressors and turbine blades and the like, and for gas turbines, analyzing the deformation beyond a first predetermined deformation is often referred to as a region of significant deformation, typically at the location of a sealing engagement of a rotating component, such as the tip of a turbine blade, a high temperature component, and the like.
Taking the compressor and the turbine blade as examples, the first preset deformation corresponding to the compressor and the turbine blade is not more than 0.05 mm.
Step 33, moving the point, line and surface elements of the first deformation area along the opposite direction of deformation according to the analysis deformation amount to obtain updated entity elements;
step 34: stitching the updated entity elements based on the point, line and plane elements to obtain a materialized first new entity model;
step 35, performing finite element analysis on the first new solid model under a preset working condition, and calculating a first correction deformation amount of deformation at the same position before performing the finite element analysis on the thermal state model and after performing the finite element analysis on the first new solid model;
step 36, judging whether the first correction deformation is in a first allowable error range, if so, stitching the first new entity model based on the point, line and surface elements to obtain an materialized cold state model; if not, the first corrected deformation amount is used as the analysis deformation amount, and step 32 is executed again.
In step 36, if the first corrected deformation amount is not within the first allowable error range, the process returns to step 32, and a first deformation region in which the analysis deformation amount exceeds a first preset deformation amount is selected on the first new solid model.
The hot state model of the gas turbine part is corrected at least once by adopting the mode to obtain the cold state model.
As shown in fig. 3, the modifying the cold state model to obtain the transition state model includes:
step 41, performing additive manufacturing process simulation based on a cold-state model, and predicting the predicted deformation amount of the same position before and after additive manufacturing;
the method for simulating the additive manufacturing process of the cold-state model is to introduce the cold-state model into an additive manufacturing analysis tool such as a simulfact tool.
Step 42, selecting a second deformation area with the predicted deformation exceeding a second preset deformation, and carrying out area division on the second deformation area based on the point, the line and the surface;
step 43, moving the point, line and surface elements of the second deformation area along the opposite direction of deformation according to the preset deformation amount to obtain updated entity elements;
and step 44, stitching the updated entity elements based on the point, line and plane elements to obtain a second new entity model for materialization.
Step 45, performing additive manufacturing process simulation based on the second new solid model, and calculating a second correction deformation amount of deformation at the same position before the additive manufacturing simulation based on the cold state model and after the additive manufacturing simulation is performed on the second new solid model;
step 46, judging whether the second correction deformation is within a second allowable error range, if so, stitching a second new entity model based on point, line and surface elements to obtain an materialized transition state model; if not, the second corrected deformation amount is used as the predicted deformation amount, and step 42 is executed again.
In step 46, if the second corrected deformation amount is not within the second allowable error range, the process returns to step 32, and a second deformation region in which the analysis deformation amount exceeds a second preset deformation amount is selected on the second new solid model.
Taking the compressor and the turbine blade as examples, the second preset deformation corresponding to the compressor and/or the turbine blade is not more than 0.05 mm.
The gas turbine types selected by the engines of different models are different, so that the structures or the sizes of the gas turbine parts may be different, and therefore, the first preset deformation and the second preset deformation are not limited to the specific values defined in the embodiment, and the specific values may be determined according to the models of the engines. Wherein the specific values of the first allowable error range and the second allowable error range can also be determined according to specific requirements, and are not limited herein.
In the model modification method for the gas turbine component manufactured by the additive manufacturing method provided by the embodiment, the finite element analysis tool and the additive manufacturing process simulation tool are used, and the relationships between points, lines and lines, lines and surfaces, surfaces and bodies, and bodies are established through the design process from points to surfaces and then to bodies, so that the conversion between the hot-state model and the cold-state model is realized in a simulation working state, and the conversion between the cold-state model and the transition-state model is realized in a simulation additive manufacturing process.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Wherein the terms "first position" and "second position" are two different positions.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Claims (10)
1. A method of model modification for additive manufacturing of a gas turbine component, comprising the steps of:
step 1, designing the pneumatic appearance of the gas turbine part under a preset working condition according to a load requirement;
step 2, the pneumatic appearance is materialized through three-dimensional modeling to obtain a solid model under a preset working condition, and the structure of the solid model is optimized under the preset working condition by utilizing finite element analysis to obtain a thermal state model;
step 3, correcting the hot model to obtain a cold model;
and 4, correcting the cold state model to obtain a transition state model.
2. The method of model modification of an additively manufactured gas turbine component part as claimed in claim 1, wherein modifying the hot state model to obtain the cold state model comprises:
step 31, carrying out finite element analysis on the thermal state model under a preset working condition, and calculating the analysis deformation of the same position before and after the finite element analysis;
step 32: selecting a first deformation area with the analysis deformation exceeding a first preset deformation, and carrying out area division on the first deformation area on the basis of points, lines and surfaces;
step 33, moving the point, line and surface elements of the first deformation area along the opposite direction of deformation according to the analysis deformation amount to obtain updated entity elements;
step 34: and stitching the updated entity elements based on the point, line and plane elements to obtain a materialized first new entity model, and taking the first new entity model as a cold state model.
3. The method of model modification of an additively manufactured gas turbine component part as claimed in claim 2, further comprising, before applying the first new solid model as a cold state model:
step 35, performing finite element analysis on the first new solid model under a preset working condition, and calculating a first correction deformation amount of deformation at the same position before performing the finite element analysis on the thermal state model and after performing the finite element analysis on the first new solid model;
and step 36, when the first correction deformation is within the first allowable error range, stitching the first new entity model based on the point, line and surface elements to obtain an materialized cold state model.
4. The model modification method for additive manufacturing of a gas turbine component according to claim 3, wherein the step 32 is performed again using the first corrected distortion amount as the analysis distortion amount when the first corrected distortion amount is not within the first allowable error range.
5. The model modification method for additive manufacturing of a gas turbine component according to any one of claims 1 to 4, wherein the gas turbine includes a compressor and a turbine blade, and the compressor and/or the turbine blade have a corresponding first predetermined deformation amount of not more than 0.05 mm.
6. The method of model modification of an additively manufactured gas turbine component part of claim 1, wherein modifying the cold state model to obtain the transition state model comprises:
step 41, performing additive manufacturing process simulation based on a cold-state model, and predicting the predicted deformation amount of the same position before and after additive manufacturing;
step 42, selecting a second deformation area with the predicted deformation exceeding a second preset deformation, and carrying out area division on the second deformation area based on the point, the line and the surface;
step 43, moving the point, line and surface elements of the second deformation area along the opposite direction of deformation according to the preset deformation amount to obtain updated entity elements;
and step 44, stitching the updated entity elements based on the point, line and plane elements to obtain a second materialized new entity model, and taking the second new entity model as a cold state model.
7. The method of model modification of an additively manufactured gas turbine component part as claimed in claim 6, further comprising, before applying the second new solid model as a cold state model:
step 45, performing additive manufacturing process simulation based on the second new solid model, and calculating a second correction deformation amount of deformation at the same position before the additive manufacturing simulation based on the cold state model and after the additive manufacturing simulation is performed on the second new solid model;
and step 46, when the second correction deformation is within the second allowable error range, stitching the second new entity model based on the point, line and surface elements to obtain the materialized cold state model.
8. The model modification method for additive manufacturing of a gas turbine component according to claim 7, wherein when the second corrected distortion amount is not within the second allowable error range, the step 42 is performed again using the second corrected distortion amount as the predicted distortion amount.
9. The model modification method for additive manufacturing of a gas turbine component according to any one of claims 6 to 8, wherein the gas turbine includes a compressor and a turbine blade, and the second preset deformation amount corresponding to the compressor and/or the turbine blade is not more than 0.05 mm.
10. The method of model modification of an additively manufactured gas turbine component part as claimed in claim 1, wherein the predetermined operating conditions include an operating temperature of greater than 800 ℃ and an operating pressure of greater than 3.03 × 105KPa, and the working speed is not lower than 1 × 105r/min。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010135501.6A CN111368472A (en) | 2020-03-02 | 2020-03-02 | Model correction method for additive manufacturing of gas turbine parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010135501.6A CN111368472A (en) | 2020-03-02 | 2020-03-02 | Model correction method for additive manufacturing of gas turbine parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111368472A true CN111368472A (en) | 2020-07-03 |
Family
ID=71211652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010135501.6A Withdrawn CN111368472A (en) | 2020-03-02 | 2020-03-02 | Model correction method for additive manufacturing of gas turbine parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111368472A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112131681A (en) * | 2020-09-15 | 2020-12-25 | 中国航发沈阳发动机研究所 | Cold and hot state structure transformation method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102799730A (en) * | 2012-07-13 | 2012-11-28 | 北京航空航天大学 | Method for estimating reverse twisting process of fan blade of gas turbine |
| CN107340788A (en) * | 2016-12-12 | 2017-11-10 | 易思维（天津）科技有限公司 | Industrial robot field real-time temperature compensation method based on visual sensor |
| US20180099360A1 (en) * | 2016-10-06 | 2018-04-12 | Xiamen University | Method for producing drilled cooling holes in a gas turbine engine component |
| CN108710746A (en) * | 2018-02-08 | 2018-10-26 | 哈尔滨广瀚燃气轮机有限公司 | Take into account the anti-twisted design method that naval vessel combustion engine compressor blade and blade predeformation influences |
-
2020
- 2020-03-02 CN CN202010135501.6A patent/CN111368472A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102799730A (en) * | 2012-07-13 | 2012-11-28 | 北京航空航天大学 | Method for estimating reverse twisting process of fan blade of gas turbine |
| US20180099360A1 (en) * | 2016-10-06 | 2018-04-12 | Xiamen University | Method for producing drilled cooling holes in a gas turbine engine component |
| CN107340788A (en) * | 2016-12-12 | 2017-11-10 | 易思维（天津）科技有限公司 | Industrial robot field real-time temperature compensation method based on visual sensor |
| CN108710746A (en) * | 2018-02-08 | 2018-10-26 | 哈尔滨广瀚燃气轮机有限公司 | Take into account the anti-twisted design method that naval vessel combustion engine compressor blade and blade predeformation influences |
Non-Patent Citations (1)
| Title |
|---|
| 郑;王彪;杨慧;: "跨声速风扇叶片的反扭设计研究" * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112131681A (en) * | 2020-09-15 | 2020-12-25 | 中国航发沈阳发动机研究所 | Cold and hot state structure transformation method |
| CN112131681B (en) * | 2020-09-15 | 2024-02-02 | 中国航发沈阳发动机研究所 | Cold and hot state structure transformation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106557612B (en) | Method for simulating and calculating pneumatic performance of automobile air protection cover | |
| US8881392B2 (en) | Method of repairing machined components such as turbomachine blades or blades of blisks | |
| CN107944143B (en) | Assembly error obtaining method facing actual working condition | |
| CN111368472A (en) | Model correction method for additive manufacturing of gas turbine parts | |
| CN105290327A (en) | Method for controlling wave pattern deformation of large complex integral casting cartridge receiver | |
| CN114004039A (en) | Prediction method for air film hole shape and position parameters and hole depth of aero-engine hollow turbine blade | |
| CN112817271A (en) | Method for optimizing machining allowance of casting case blank based on-machine measurement | |
| CN114082988A (en) | Method for repairing aero-engine cold and hot end blade | |
| CN107527385B (en) | Automatic grid projection method | |
| CN112696258B (en) | Control method for thermal deformation design of exhaust manifold | |
| CN114186513A (en) | Modeling design method for axial flow compressor blade with reverse S-shaped front edge | |
| CN113468788B (en) | Deformation coordination design method for engine blisk | |
| CN108664742B (en) | Multi-objective optimization method for nacelle parametric design | |
| JP2017187032A (en) | Turbomachine alignment key and related turbomachine | |
| CN115994991A (en) | Method for rapidly converting cold state and hot state of turbine blade model | |
| CN112943699B (en) | Compressor stator blade vibration reduction optimization design method based on corner design | |
| US9358645B2 (en) | Adaptive machining method for smelted blades | |
| CN116011089A (en) | Turbine guide vane laminate cooling structure design method and device, terminal and storage medium | |
| CN110909420B (en) | Ship propulsion shafting alignment iterative calculation method considering bearing factors | |
| CN112528406B (en) | Geometric parameterization modeling method and device for aircraft fuselage frame structure | |
| CN113239466A (en) | Engine compartment thermal management simulation method | |
| CN114398731A (en) | Aircraft engine model correction method | |
| CN112035981B (en) | Modeling method for turbine blade laminate cooling structure | |
| CN117010093B (en) | Automobile modeling design method and equipment | |
| CN115008137A (en) | Method for manufacturing blade tip and tail edge reinforcing edge of aircraft engine fan blade |
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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20200703 |
|
| WW01 | Invention patent application withdrawn after publication |