Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study

Degradation of compressors is a common concern for operators gas turbine engines (GTEs). Surface roughness, due to erosion or fouling, considered one the major factors degradation phenomenon in that can negatively affect designed pressure rise, efficiency, and, therefore, engine aero/thermodynamic performance. The understanding aerodynamic implications varying blade surface roughness plays significant role establishing magnitude performance degradation. present work investigates compressor caused by operation eroding environments on cycle linking, thereby, aerodynamics with thermodynamic cycle. At core study numerical assessment effect employing Computational Fluid Dynamics (CFD) tools. research test case employed comprised fan, bypass, and two stages low (booster). Three operating conditions 100% speed-line, including design point, were investigated. Five cases, addition smooth case, equivalent sand-grain (ks) 15, 30, 45, 60, 150 µm simulated. Turbomatch Cranfield in-house simulation software, was model degraded showed increase uniform associated sizable drops booster ratio (PR), non-dimensional mass flow (NDMF), overall (EPR) together rises entry temperature (TET) specific fuel consumption (SFC). evaluation variables such as isentropic efficiency (ηis), (LPC) PR, NDMF, TET, SFC, andEPR. variation these quantities showed, maximum 7.68%, 2.62% 3.53%, 1.14% 0.69%, drop 0.86%, respectively.