dc.identifier.uri |
http://dx.doi.org/10.15488/5070 |
|
dc.identifier.uri |
https://www.repo.uni-hannover.de/handle/123456789/5114 |
|
dc.contributor.author |
Gilge, Philipp
|
|
dc.contributor.author |
Kellersmann, Andreas
|
|
dc.contributor.author |
Friedrichs, Jens
|
|
dc.contributor.author |
Seume, Jörg R.
|
|
dc.date.accessioned |
2019-07-02T08:17:30Z |
|
dc.date.available |
2019-07-02T08:17:30Z |
|
dc.date.issued |
2019 |
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dc.identifier.citation |
Gilge, P.; Kellersmann, A.; Friedrichs, J.; Seume, J.R.: Surface roughness of real operationally used compressor blade and blisk. In: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233 (2019), Nr. 14, S. 5321-5330. DOI: https://doi.org/10.1177/0954410019843438 |
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dc.description.abstract |
Deterioration of axial compressors is in general a major concern in aircraft engine maintenance. Among other effects, roughness in high-pressure compressor reduces the pressure rise and thus efficiency, thereby increasing the specific fuel consumption of an engine. Therefore, it is important to improve the understanding of roughness on compressor blading and their impact on compressor performance. To investigate the surface roughness of rotor blades of a compressors, different stages of an axial high-pressure compressor and a first-stage blisk (BLade–Integrated–dISK) of a regional aircraft engine is measured by a three-dimensional laser scanning microscope. Fundamental types of roughness structures can be identified: impacts in different sizes, depositions as isotropically distributed single elements with steep flanks and anisotropic roughness structures direct approximately normal to the flow direction. To characterise and quantify the roughness structures in more detail, roughness parameters were determined from the measured surfaces. The quantification showed that the roughness height varies through the compressor depending on the stage, position and the blade side. Overall complex roughness structures of different shape, height and size are detected regardless of the type of the blades. |
eng |
dc.language.iso |
eng |
|
dc.publisher |
London : SAGE Publications Ltd. |
|
dc.relation.ispartofseries |
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233 (2019), Nr. 14 |
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dc.rights |
CC BY-NC 4.0 Unported |
|
dc.rights.uri |
https://creativecommons.org/licenses/by-nc/4.0/ |
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dc.subject |
aircraft engine |
eng |
dc.subject |
blisk blades |
eng |
dc.subject |
compressor blades |
eng |
dc.subject |
operationally stressed surfaces |
eng |
dc.subject |
Surface roughness |
eng |
dc.subject |
Aircraft |
eng |
dc.subject |
Aircraft engines |
eng |
dc.subject |
Compressors |
eng |
dc.subject |
Deterioration |
eng |
dc.subject |
Engines |
eng |
dc.subject |
High pressure effects |
eng |
dc.subject |
Aircraft engine maintenance |
eng |
dc.subject |
blisk blades |
eng |
dc.subject |
Compressor blades |
eng |
dc.subject |
Compressor performance |
eng |
dc.subject |
High pressure compressor |
eng |
dc.subject |
Roughness parameters |
eng |
dc.subject |
Specific fuel consumption |
eng |
dc.subject |
Three-dimensional laser scanning |
eng |
dc.subject |
Surface roughness |
eng |
dc.subject.ddc |
380 | Handel, Kommunikation, Verkehr
|
ger |
dc.subject.ddc |
620 | Ingenieurwissenschaften und Maschinenbau
|
ger |
dc.title |
Surface roughness of real operationally used compressor blade and blisk |
eng |
dc.type |
Article |
|
dc.type |
Text |
|
dc.relation.issn |
0954-4100 |
|
dc.relation.doi |
https://doi.org/10.1177/0954410019843438 |
|
dc.bibliographicCitation.firstPage |
1 |
|
dc.bibliographicCitation.lastPage |
10 |
|
dc.description.version |
publishedVersion |
|
tib.accessRights |
frei zug�nglich |
|