TY - JOUR

T1 - Surface roughness of real operationally used compressor blade and blisk

AU - Gilge, Philipp

AU - Kellersmann, Andreas

AU - Friedrichs, Jens

AU - Seume, Jörg R.

N1 - Funding Information: The author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: The present work has been carried out in the subprojects B3 and D4 within the Collaborative Research Center (CRC) 871 ‘Regeneration of Complex Capital Goods’, which is funded by the DFG (Deutsche Forschungsgemeinschaft) under grant of CRC871. The authors would like to thank the DFG for their support.

PY - 2019/11

Y1 - 2019/11

N2 - 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.

AB - 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.

KW - aircraft engine

KW - blisk blades

KW - compressor blades

KW - operationally stressed surfaces

KW - Surface roughness

UR - http://www.scopus.com/inward/record.url?scp=85065746251&partnerID=8YFLogxK

U2 - 10.1177/0954410019843438

DO - 10.1177/0954410019843438

M3 - Article

AN - SCOPUS:85065746251

VL - 233

SP - 5321

EP - 5330

JO - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

JF - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

SN - 0954-4100

IS - 14

ER -