A Robotic Polishing Trajectory Planning Method Combining Reverse Engineering and Finite Element Mesh Technology for Aero-Engine Turbine Blade TBCs

Yang, F; Cai, Z; Chen, Y; Dong, S; Deng, C; Niu, S; Zeng, W; Wen, S

A Robotic Polishing Trajectory Planning Method Combining Reverse Engineering and Finite Element Mesh Technology for Aero-Engine Turbine Blade TBCs

Yang, F Cai, Z Chen, Y Dong, S Deng, C Niu, S Zeng, W Wen, S

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Publisher:: Springer Nature
Publication Type:: Journal Article
Citation:: Journal of Thermal Spray Technology, 2022, 31, (7), pp. 2050-2067
Issue Date:: 2022-10-01

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Field	Value	Language
dc.contributor.author	Yang, F
dc.contributor.author	Cai, Z
dc.contributor.author	Chen, Y
dc.contributor.author	Dong, S
dc.contributor.author	Deng, C
dc.contributor.author	Niu, S
dc.contributor.author	Zeng, W
dc.contributor.author	Wen, S https://orcid.org/0000-0001-8077-7001
dc.date.accessioned	2023-06-28T00:43:00Z
dc.date.available	2023-06-28T00:43:00Z
dc.date.issued	2022-10-01
dc.identifier.citation	Journal of Thermal Spray Technology, 2022, 31, (7), pp. 2050-2067
dc.identifier.issn	1059-9630
dc.identifier.issn	1544-1016
dc.identifier.uri	http://hdl.handle.net/10453/170915
dc.description.abstract	The roughness of thermal barrier coatings (TBCs) prepared on the surface of aero-engine turbine blades affects the lifetime of the coating and the life cycle and aerodynamic performance of the blades. To reduce the TBC surface roughness, this study proposes a robot polishing trajectory planning method that combines reverse engineering and finite element mesh technology. First, a 3D model of the blade was reconstructed in reverse engineering by using the fast surface modeling method. Then, a dense mesh with controlled spacing was obtained by mapping the finite element mesh arbitrary quadrilateral elements on the surface of the blade model. Finally, a robot polishing path of the blade was generated by sorting the index of mesh nodes. Using this approach, polishing experiments of aero-engine turbine blades were systematically carried out, and the coordinate system conversion method from the robot off-line programming simulation environment to the actual work station was used to map the robot trajectory. Meanwhile, the point cloud registration method was introduced to improve the system calibration accuracy. The experiments showed that the technical solution proposed in this paper could reduce the overall surface roughness of the thermal barrier coating from above Ra 8 μm to about Ra 0.5 μm, which contributes to the performance improvement for the TBCs of aero-engine blades.
dc.language	en
dc.publisher	Springer Nature
dc.relation.ispartof	Journal of Thermal Spray Technology
dc.relation.isbasedon	10.1007/s11666-022-01434-9
dc.rights	info:eu-repo/semantics/closedAccess
dc.subject	0912 Materials Engineering, 0913 Mechanical Engineering
dc.subject.classification	Materials
dc.title	A Robotic Polishing Trajectory Planning Method Combining Reverse Engineering and Finite Element Mesh Technology for Aero-Engine Turbine Blade TBCs
dc.type	Journal Article
utslib.citation.volume	31
utslib.for	0912 Materials Engineering
utslib.for	0913 Mechanical Engineering
pubs.organisational-group	/University of Technology Sydney
pubs.organisational-group	/University of Technology Sydney/Faculty of Engineering and Information Technology
pubs.organisational-group	/University of Technology Sydney/Strength - AAII - Australian Artificial Intelligence Institute
utslib.copyright.status	closed_access	*
dc.date.updated	2023-06-28T00:42:58Z
pubs.issue	7
pubs.publication-status	Published
pubs.volume	31
utslib.citation.issue	7

Abstract:

The roughness of thermal barrier coatings (TBCs) prepared on the surface of aero-engine turbine blades affects the lifetime of the coating and the life cycle and aerodynamic performance of the blades. To reduce the TBC surface roughness, this study proposes a robot polishing trajectory planning method that combines reverse engineering and finite element mesh technology. First, a 3D model of the blade was reconstructed in reverse engineering by using the fast surface modeling method. Then, a dense mesh with controlled spacing was obtained by mapping the finite element mesh arbitrary quadrilateral elements on the surface of the blade model. Finally, a robot polishing path of the blade was generated by sorting the index of mesh nodes. Using this approach, polishing experiments of aero-engine turbine blades were systematically carried out, and the coordinate system conversion method from the robot off-line programming simulation environment to the actual work station was used to map the robot trajectory. Meanwhile, the point cloud registration method was introduced to improve the system calibration accuracy. The experiments showed that the technical solution proposed in this paper could reduce the overall surface roughness of the thermal barrier coating from above Ra 8 μm to about Ra 0.5 μm, which contributes to the performance improvement for the TBCs of aero-engine blades.

Please use this identifier to cite or link to this item:

http://hdl.handle.net/10453/170915