WO2018117799A1 - Method and system for manufacturing a stage-transition structure for an aerospace turbine using in-line multisensor metrology - Google Patents
Method and system for manufacturing a stage-transition structure for an aerospace turbine using in-line multisensor metrology Download PDFInfo
- Publication number
- WO2018117799A1 WO2018117799A1 PCT/MX2016/000186 MX2016000186W WO2018117799A1 WO 2018117799 A1 WO2018117799 A1 WO 2018117799A1 MX 2016000186 W MX2016000186 W MX 2016000186W WO 2018117799 A1 WO2018117799 A1 WO 2018117799A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- analysis
- intelligent
- information
- cell
- manufacturing process
- Prior art date
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000013461 design Methods 0.000 claims abstract description 9
- 238000003754 machining Methods 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims abstract description 4
- 230000006854 communication Effects 0.000 claims abstract 3
- 238000004891 communication Methods 0.000 claims abstract 3
- 238000012417 linear regression Methods 0.000 claims abstract 3
- 238000013481 data capture Methods 0.000 claims abstract 2
- 238000004088 simulation Methods 0.000 claims abstract 2
- 238000005457 optimization Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 2
- 239000002253 acid Substances 0.000 claims 1
- 150000007513 acids Chemical class 0.000 claims 1
- 230000007175 bidirectional communication Effects 0.000 claims 1
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 238000005259 measurement Methods 0.000 claims 1
- 238000003801 milling Methods 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q15/00—Automatic control or regulation of feed movement, cutting velocity or position of tool or work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/20—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring workpiece characteristics, e.g. contour, dimension, hardness
Definitions
- the present invention has its preponderant field of application in turbine manufacturing processes for the Aerospace Industry by implementing online metrology.
- Patent No. US2009027700 describes a method for manufacturing and / or machining components, in particular gas turbine components, such as blades, blade segments or integral blade rotors for an aircraft engine.
- the method includes at least the following steps: a) provide a work piece; b) milling the workpiece to provide a component to be manufactured; C) round the edges of the component and / or smooth the surface of the component and / or harden the surface of the component by a hydraulic method using a lubricant and / or coolant required for milling.
- the invention No. US20070017817 describes a method for manufacturing components of a gas turbine in which it includes at least one metal injection molding stage (MIM process) and a precise electrochemical machining process stage (PECM process).
- MIM process metal injection molding stage
- PECM process precise electrochemical machining process stage
- Patent procedure No. WO / 2007/082504 claims a process for machining components by milling to produce recesses with one or more walls lateral, in particular for the manufacture of integrated vane rotors for gas turbines, forming flow channels and the side walls forming fully flattened rotor blade surfaces for gas turbines, in which the milling component is held in a device of location for the mechanized of milling.
- patent No. US20160319834 describes a method for manufacturing a gas turbine engine component where a nickel-based alloy workpiece is provided and material is removed from the workpiece surface using an abrasive machining operation to form an axisymmetric surface on the workpiece dond.
- patent No. US20070169913 refers to a method for manufacturing semi-finished components or parts for gas turbines, in particular for aircraft engines, preferably by casting.
- Figure 1 is a schematic diagram of the components for implementing the manufacturing method for aerospace turbine of the present invention.
- the element [A] is the CNC manufacturing module of structural components, which has at least 5 axes and implements a critical precision transmission system to the next workstation [B].
- Element [B] is the multisensor metrology cell for the geometry sizing of machined components in the previous stage [A], and is characterized by its ability to intelligently capture data in at least six degrees of freedom, as well as registration and deployment of them in mathematical form by multifactor modeling.
- Element [C] represents the metrological analysis server that executes intelligent and regression algorithms to send results and projection reports to the engineering and design cell [D] to optimize quality and efficiency in the manufacturing process.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laser Beam Processing (AREA)
Abstract
Technical description: method for manufacturing structural components of an aerospace turbine, which combines processes, materials, tools and machining techniques and is characterised by: a numerically controlled manufacturing cell with tool capacity of at least five critical shafts for machining pieces with special shapes, geometries and dimensions; a multisensor metrology cell for the dimensional capture of the geometry of machined components, which is characterised by intelligent data capture in at least six degrees of freedom, multifactorial modelling and communication with an intelligent analysis server; intelligent analysis of metrological information, characterised by the use of intelligent algorithms and linear regression algorithms in real time for the optimisation of the quality and efficiency of the manufacturing process; and an engineering and design cell characterised by the capacity for design optimisation by means of simulations coordinated with said information analysis devices, generating multistage simulation–analysis cycles in the manufacturing process.
Description
MÉTODO Y SISTEMA DE MANUFACTURA DE ESTRUCTURA DE METHOD AND SYSTEM OF MANUFACTURE OF STRUCTURE OF
TRANSICIÓN DE ETAPA PARA TURBINA AEROESPACIAL UTILIZANDO METROLOGÍA MULTISENSOR EN LÍNEA TRANSITION OF STAGE FOR Aerospace TURBINE USING MULTISENSOR METROLOGY ONLINE
CAMPO TÉCNICO DE LA INVENCIÓN TECHNICAL FIELD OF THE INVENTION
La presente invención tiene su campo de aplicación preponderante en procesos de manufactura de turbinas para la Andustria Aeroespacial implementando metrología en línea. The present invention has its preponderant field of application in turbine manufacturing processes for the Aerospace Industry by implementing online metrology.
ANTECEDENTES DE LA INVENCIÓN BACKGROUND OF THE INVENTION
Las turbinas de gas modernas, en particular los motores de aeronaves, exigen las más altas exigencias en cuanto a fiabilidad, potencia, peso, eficiencia económica y vida útil. La selección o desarrollo de nuevos materiales, así como procesos de fabricación o métodos de fabricación adecuados desempeña un papel crucial en la optimización de turbinas de gas, en particular los motores de aeronaves. A continuación se presenta una breve recopilación de invenciones registradas en el tema de manufactura de dichas turbinas. Modern gas turbines, particularly aircraft engines, demand the highest demands in terms of reliability, power, weight, economic efficiency and useful life. The selection or development of new materials, as well as manufacturing processes or suitable manufacturing methods plays a crucial role in the optimization of gas turbines, in particular aircraft engines. Below is a brief compilation of inventions registered in the subject of manufacture of said turbines.
La patente No. US2009027700 describe un método para fabricar y / o mecanizar componentes, en particular componentes de turbina de gas, tales como cuchillas, segmentos de cuchillas o rotores de hojas integrales para un motor de avión. En una de sus aplicaciones, el método incluye al menos las siguientes etapas: a) proporcionar una pieza de trabajo; b) fresar la pieza de trabajo para proporcionar un componente a fabricar; C) redondear los bordes del componente y / o alisar la superficie del componente y / o endurecer la superficie del componente por un método hidráulico utilizando un lubricante y / o refrigerante requerido para el fresado. La invención No. US20070017817 describe un método para fabricar componentes de una turbina de gas en la que incluye al menos una etapa de moldeo por inyección de metal (proceso MIM) y una etapa de proceso de mecanizado electroquímico preciso (proceso PECM). Patent No. US2009027700 describes a method for manufacturing and / or machining components, in particular gas turbine components, such as blades, blade segments or integral blade rotors for an aircraft engine. In one of its applications, the method includes at least the following steps: a) provide a work piece; b) milling the workpiece to provide a component to be manufactured; C) round the edges of the component and / or smooth the surface of the component and / or harden the surface of the component by a hydraulic method using a lubricant and / or coolant required for milling. The invention No. US20070017817 describes a method for manufacturing components of a gas turbine in which it includes at least one metal injection molding stage (MIM process) and a precise electrochemical machining process stage (PECM process).
En el registro de patente No. WO/2007/082504 se reclama un procedimiento para el mecanizado por fresado de componentes para producir rebajes con una o más paredes
laterales, en particular para la fabricación de rotores de paletas integradas para turbinas de gas, formando canales de flujo y las paredes laterales formando superficies de lámina de rotores totalmente aplanados para turbinas de gas, en el que el componente para fresado se sujeta en un dispositivo de localización para el mecanizado de fresado. Patent procedure No. WO / 2007/082504 claims a process for machining components by milling to produce recesses with one or more walls lateral, in particular for the manufacture of integrated vane rotors for gas turbines, forming flow channels and the side walls forming fully flattened rotor blade surfaces for gas turbines, in which the milling component is held in a device of location for the mechanized of milling.
La invención No. US20160319834 describe un método para fabricar un componente de motor de turbina de gas donde se proporciona una pieza de trabajo de aleación basada en níquel y se elimina material de la superficie de pieza de trabajo usando una operación de mecanizado abrasivo para formar una superficie axisimétrica sobre la pieza de trabajo dond. Por otro lado, la patente No. US20070169913 se refiere a un método para fabricar componentes o piezas semielaboradas para turbinas de gas, en particular para motores de aeronaves, preferentemente por colada. The invention No. US20160319834 describes a method for manufacturing a gas turbine engine component where a nickel-based alloy workpiece is provided and material is removed from the workpiece surface using an abrasive machining operation to form an axisymmetric surface on the workpiece dond. On the other hand, patent No. US20070169913 refers to a method for manufacturing semi-finished components or parts for gas turbines, in particular for aircraft engines, preferably by casting.
DESCRIPCION DETALLADA DE LA INVENCIÓN Los detalles característicos de la presente invención se muestran en la siguiente descripción y en la figura que se acompaña, la cual se menciona a manera de ejemplo por lo que no deben considerarse como una limitante para dicha invención. DETAILED DESCRIPTION OF THE INVENTION The characteristic details of the present invention are shown in the following description and in the accompanying figure, which is mentioned by way of example and should not be considered as a limitation on said invention.
La figura 1 es un diagrama esquemático de los componentes para implementar el método de manufactura para turbina aeroestpacial de la presente invención. El ele- elemento [A] es el módulo de manufactura por CNC de componentes estructurales, el cual cuenta con al menos 5 ejes e implementa un sistema de transmisión de precisión críticos hacia la siguiente estación de trabajo [B]. El elemento [B] es la celda de metrología multisensor para el dimensionamiento de geometría de componentes maquina- dos en la etapa anterior [A], y se caracteriza por su capacidad de captura inteligente de datos en al menos seis grados de libertad, así como registro y despliegue de los mismos en forma matemática por modelación multifactorial. El elemento [C] representa el servidor de análisis metrológico que ejecuta algoritmos inteligentes y de regresión para enviar resultados y reportes de proyección a la celda de ingeniería y diseño [D] para optimizar calidad y eficiencia en el proceso de manufactura.
Figure 1 is a schematic diagram of the components for implementing the manufacturing method for aerospace turbine of the present invention. The element [A] is the CNC manufacturing module of structural components, which has at least 5 axes and implements a critical precision transmission system to the next workstation [B]. Element [B] is the multisensor metrology cell for the geometry sizing of machined components in the previous stage [A], and is characterized by its ability to intelligently capture data in at least six degrees of freedom, as well as registration and deployment of them in mathematical form by multifactor modeling. Element [C] represents the metrological analysis server that executes intelligent and regression algorithms to send results and projection reports to the engineering and design cell [D] to optimize quality and efficiency in the manufacturing process.
Claims
1. Método de manufactura de componentes estructurales de turbina aeroespacial conformado por la combinación de procesos, materiales, herramentales, y técnicas de maquinado caracterizado por: 1. Method of manufacture of structural components of aerospace turbine formed by the combination of processes, materials, tools, and machining techniques characterized by:
a.-Manufactura por control numérico avanzado de componentes estructurales de turbina aeroespacial caracterizado por su capacidad herramental de mínimo cinco ejes críticos para el maquinado de piezas con formas, geometrías y dimensiones especiales, así como el acoplamiento de sistemas de transmisión de precisión críticos para asegurar la tolerancia de diseño requerida por el proceso de manufactura. a.-Manufacture by advanced numerical control of structural components of aerospace turbine characterized by its tooling capacity of at least five critical axes for the machining of parts with special shapes, geometries and dimensions, as well as the coupling of critical precision transmission systems to ensure the design tolerance required by the manufacturing process.
b.- Celda de metrología multi sensor para la captura dimensional de geometría de componentes maquinados, caracterizada por la captura inteligente de datos en por lo menos seis grados de libertad, así como el registro y despliegue de datos en forma matemática por modelación multifactorial, con comunicación con el servidor de análisis inteligente. b.- Multi sensor metrology cell for dimensional capture of machined component geometry, characterized by intelligent data capture in at least six degrees of freedom, as well as the registration and deployment of data in mathematical form by multifactor modeling, with communication with the intelligent analysis server.
c- Análisis inteligente de información metrológica, caracterizado por el análisis de información con algoritmos inteligentes y de regresión lineal en tiempo real, enviando resultados y reportes de proyección a la celda de ingeniería y diseño para la optimización de la calidad y eficiencia del proceso de manufactura, c- Intelligent analysis of metrological information, characterized by the analysis of information with intelligent algorithms and linear regression in real time, sending results and projection reports to the engineering and design cell for the optimization of the quality and efficiency of the manufacturing process ,
d.- Celda de ingeniería y diseño, caracterizado por su comunicación nativa con los dispositivos de análisis de información metrológica, obteniendo información analizada en relación a desviaciones criticas al diseño, con capacidad para optimización de diseños mediante simulaciones coordinadas con los mismos dispositivos de análisis de información, generando cidos de simulación-análisis multi etapa en el proceso de manufactura. d.- Engineering and design cell, characterized by its native communication with the metrological information analysis devices, obtaining information analyzed in relation to critical deviations to the design, with capacity for optimization of designs through coordinated simulations with the same analysis devices. information, generating multi-stage simulation-analysis acids in the manufacturing process.
2. Celda de metrología avanzada multi sensor para la captura dimensional de geometría estructural de componentes maquinados, caracterizada por la captura— - inteligente de datos en por lo menos seis grados de libertad, integrando dispositivos de medición mecánico, láser, por ultrasonido y captura de imágenes, así como el registro y despliegue de datos en forma matemática por modelación
multifactorial, con capacidad de comunicación con el servidor de análisis inteligente. 2. Advanced multi sensor metrology cell for dimensional capture of structural geometry of machined components, characterized by capture— intelligent data in at least six degrees of freedom, integrating mechanical, laser, ultrasonic and ultrasonic measurement devices. images, as well as the registration and display of data in mathematical form by modeling Multifactorial, capable of communicating with the intelligent analysis server.
3. Análisis inteligente de información metrológica y comparación con modelo CAD, caracterizado por el registro y análisis de información utilizando algoritmos inteligentes y de regresión lineal generando proyecciones de puntos de falla en el proceso de manufactura, con comunicación bi direccional con la celda de metrología avanzada, caracterizado además por el análisis de información en tiempo real enviando resultados y reportes de proyección a la celda de ingeniería y diseño para la optimización de la calidad y eficiencia del proceso de manufactura.
3. Intelligent analysis of metrological information and comparison with CAD model, characterized by the registration and analysis of information using intelligent algorithms and linear regression generating projections of points of failure in the manufacturing process, with bi-directional communication with the advanced metrology cell , also characterized by the analysis of information in real time by sending results and projection reports to the engineering and design cell for the optimization of the quality and efficiency of the manufacturing process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/MX2016/000186 WO2018117799A1 (en) | 2016-12-20 | 2016-12-20 | Method and system for manufacturing a stage-transition structure for an aerospace turbine using in-line multisensor metrology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/MX2016/000186 WO2018117799A1 (en) | 2016-12-20 | 2016-12-20 | Method and system for manufacturing a stage-transition structure for an aerospace turbine using in-line multisensor metrology |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2018117799A1 true WO2018117799A1 (en) | 2018-06-28 |
Family
ID=62627798
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/MX2016/000186 WO2018117799A1 (en) | 2016-12-20 | 2016-12-20 | Method and system for manufacturing a stage-transition structure for an aerospace turbine using in-line multisensor metrology |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2018117799A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109189035A (en) * | 2018-11-13 | 2019-01-11 | 重庆佰节成测控技术有限公司 | The U-shaped assembly line of automotive electronics intelligence manufacture |
| CN110712770A (en) * | 2019-08-15 | 2020-01-21 | 燕山大学 | A 9-DOF Hybrid Attitude Adjustment Platform for Solar Wing Horizontal Docking Assembly in Low Space |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005319531A (en) * | 2004-05-07 | 2005-11-17 | Toru Nishikazu | Numerical control machine tool and method for checking machining program |
| US20070017817A1 (en) * | 2004-06-19 | 2007-01-25 | Claus Mueller | Method for manufacturing components of a gas turbine and a component of a gas turbine |
| KR20080079849A (en) * | 2007-02-28 | 2008-09-02 | 부산대학교 산학협력단 | 5-axis milling time prediction method |
| EP2127804A1 (en) * | 2007-01-15 | 2009-12-02 | Tsudakoma Kogyo Kabushikikaisha | Indexing device for machine tools |
| CN102615435A (en) * | 2012-04-13 | 2012-08-01 | 中国航空工业集团公司北京航空制造工程研究所 | Method for directly machining turbine blade air film irregular holes through laser |
| CN204487320U (en) * | 2015-02-13 | 2015-07-22 | 华中科技大学 | Numerical control abrasive belt grinding machine with six-axis linkage |
-
2016
- 2016-12-20 WO PCT/MX2016/000186 patent/WO2018117799A1/en active Application Filing
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005319531A (en) * | 2004-05-07 | 2005-11-17 | Toru Nishikazu | Numerical control machine tool and method for checking machining program |
| US20070017817A1 (en) * | 2004-06-19 | 2007-01-25 | Claus Mueller | Method for manufacturing components of a gas turbine and a component of a gas turbine |
| EP2127804A1 (en) * | 2007-01-15 | 2009-12-02 | Tsudakoma Kogyo Kabushikikaisha | Indexing device for machine tools |
| KR20080079849A (en) * | 2007-02-28 | 2008-09-02 | 부산대학교 산학협력단 | 5-axis milling time prediction method |
| CN102615435A (en) * | 2012-04-13 | 2012-08-01 | 中国航空工业集团公司北京航空制造工程研究所 | Method for directly machining turbine blade air film irregular holes through laser |
| CN204487320U (en) * | 2015-02-13 | 2015-07-22 | 华中科技大学 | Numerical control abrasive belt grinding machine with six-axis linkage |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109189035A (en) * | 2018-11-13 | 2019-01-11 | 重庆佰节成测控技术有限公司 | The U-shaped assembly line of automotive electronics intelligence manufacture |
| CN110712770A (en) * | 2019-08-15 | 2020-01-21 | 燕山大学 | A 9-DOF Hybrid Attitude Adjustment Platform for Solar Wing Horizontal Docking Assembly in Low Space |
| CN110712770B (en) * | 2019-08-15 | 2021-06-11 | 燕山大学 | 9-freedom hybrid attitude adjusting platform for horizontal butt joint assembly of solar wings in low space |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104597838B (en) | A kind of deep narrow slot turning processing method of high temperature alloy integral wheel annular | |
| US20130302103A1 (en) | Automatic method for milling complex channel-shaped cavities | |
| EP3346093B1 (en) | Additively manufactured blade extension with internal cooling features | |
| JP6822822B2 (en) | How to monitor components | |
| US10682704B2 (en) | Material extraction tool | |
| CN107249813A (en) | A kind of method and system of the complicated metal parts of lamella superposed addicting manufacture | |
| US11162432B2 (en) | Integrated nozzle and diaphragm with optimized internal vane thickness | |
| CN103971019A (en) | Method for predicting workpiece machining energy consumption based on geometrical characteristics | |
| Burghardt et al. | Robotic automation of the turbo-propeller engine blade grinding process | |
| CN106378478B (en) | A kind of micro- milling method of rule pyramid micro-structure | |
| WO2018117799A1 (en) | Method and system for manufacturing a stage-transition structure for an aerospace turbine using in-line multisensor metrology | |
| Ameta et al. | Tolerance specification and related issues for additively manufactured products | |
| Tao et al. | Recent repair technology for aero-engine blades | |
| CN103658520B (en) | A kind of metalwork casting mold subdivision method | |
| CN102398093A (en) | Machining system and method | |
| Zhang et al. | Intelligent machining of complex aviation components | |
| US10376958B2 (en) | Removable support for additive manufacture | |
| 谭建荣 et al. | Digital intelligent forward design method and its application in manufacturing equipment and process | |
| Im et al. | Development of a computer-aided manufacturing system for profiled edge lamination tooling | |
| Isnaini et al. | Development of a CAD-CAM interaction system to generate a flexible machining process plan | |
| Bergs et al. | Simulation assisted cathode design for the manufacturing of complex geometries by electrochemical machining (ECM) | |
| Yan et al. | Advanced design and manufacture to gain a competitive edge | |
| US10503148B2 (en) | System and method for diffuser hole creation | |
| Wang | Discussion on advanced manufacturing | |
| Lu et al. | STUDY ON ROUGH MACHINING STRATEGY AND VERICUT SIMULATION OF INTEGRAL IMPELLER BASED ON UG |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 16924760 Country of ref document: EP Kind code of ref document: A1 |
|
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 16924760 Country of ref document: EP Kind code of ref document: A1 |