TY - JOUR

T1 - Numerical Study of Stage Roughness Variations in a High Pressure Compressor

AU - Seehausen, Hendrik

AU - Gilge, Philipp

AU - Kellersmann, Andreas

AU - Friedrichs, Jens

AU - Herbst, Florian

N1 - Funding Information: The present work has been carried out in the subproject B3 within the Collaborative Research Center (CRC) 871 "Regenera-tion of Complex Capital Goods" which is funded by the DFG (Deutsche Forschungsgemeinschaft) under grant SFB 871. The au-thors would like to thank the DFG for the support. Moreover, the authors would like to acknowledge the substantial contribution of the DLR Institute of Propulsion Technology and MTU Aero En-gines AG for providing TRACE. The results presented here were partially carried out on the cluster system at the Leibniz University IT Service (LUIS). Thus, the authors acknowledge the support of the cluster system team in the production of this work.

PY - 2020/6

Y1 - 2020/6

N2 - The objective of this study is to quantify the sensitivity of blade roughness on the overall performance of a 10-stage high-pressure compressor of the jet engine type V2500-A1. The Reynolds-Aver-aged Navier-Stokes flow solver TRACE is used to study the multi-stage compressor. The three-dimensional numerical setup contains all geometric and aerodynamic features such as bleed ports and the variable stator vanes system. In order to estimate the effect of stage roughness on overall compressor performance, compressor maps of the CFD-model are created by modeling the surface rough- ness sep-arately for a single stage and combinations of stages. The surface roughness values are applied to the blade's suction side of the first, center and last stage in the CFD-model by setting an equivalent sand-grain value. This equivalent sand-grain roughness is deter-mined from non-intrusive measurements of blade surfaces from an equivalent real aircraft engine for the first, center and last stage. In addition, further simulations are conducted to analyze the perfor-mance drop of a fully rough HPC due to surface roughness. The studies are performed at the operating conditions 'cruise' and 'take-off' to cover two different Reynolds number regimes. The re-sults show that the models with roughness in a single stage already lead to significantly lower mass flow rates because of higher block-age compared to the smooth compressor. In fact, roughness at the first stage has the biggest effect on the overall performance with a drop in performance of about 0.1% while the effect of the last stage is the smallest. This behavior is mainly caused by enhanced insta-bilities through the compressor changing the stage-by-stage match-ing of the stages downstream. In addition to the displacement of the compressor maps to a lower mass flow, a reduction of stall and choke margins is noticeable.

AB - The objective of this study is to quantify the sensitivity of blade roughness on the overall performance of a 10-stage high-pressure compressor of the jet engine type V2500-A1. The Reynolds-Aver-aged Navier-Stokes flow solver TRACE is used to study the multi-stage compressor. The three-dimensional numerical setup contains all geometric and aerodynamic features such as bleed ports and the variable stator vanes system. In order to estimate the effect of stage roughness on overall compressor performance, compressor maps of the CFD-model are created by modeling the surface rough- ness sep-arately for a single stage and combinations of stages. The surface roughness values are applied to the blade's suction side of the first, center and last stage in the CFD-model by setting an equivalent sand-grain value. This equivalent sand-grain roughness is deter-mined from non-intrusive measurements of blade surfaces from an equivalent real aircraft engine for the first, center and last stage. In addition, further simulations are conducted to analyze the perfor-mance drop of a fully rough HPC due to surface roughness. The studies are performed at the operating conditions 'cruise' and 'take-off' to cover two different Reynolds number regimes. The re-sults show that the models with roughness in a single stage already lead to significantly lower mass flow rates because of higher block-age compared to the smooth compressor. In fact, roughness at the first stage has the biggest effect on the overall performance with a drop in performance of about 0.1% while the effect of the last stage is the smallest. This behavior is mainly caused by enhanced insta-bilities through the compressor changing the stage-by-stage match-ing of the stages downstream. In addition to the displacement of the compressor maps to a lower mass flow, a reduction of stall and choke margins is noticeable.

UR - http://www.scopus.com/inward/record.url?scp=85097782006&partnerID=8YFLogxK

U2 - 10.38036/jgpp.11.3_16

DO - 10.38036/jgpp.11.3_16

M3 - Article

AN - SCOPUS:85097782006

VL - 11

SP - 16

EP - 25

JO - International Journal of Gas Turbine, Propulsion and Power Systems

JF - International Journal of Gas Turbine, Propulsion and Power Systems

IS - 3

T2 - International Gas Turbine Congress (IGTC) 2019

Y2 - 17 November 2019 through 22 November 2019

ER -