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

Degradation of compressors is a common concern for operators of gas turbine engines (GTEs). Surface roughness, due to erosion or fouling, is considered one of the major factors of the degradation phenomenon in compressors that can negatively affect the designed pressure rise, efficiency, and, theref...

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Autores principales:	Jasem Alqallaf, Joao A. Teixeira
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	blade surface computational fluid dynamics gas turbine surface roughness turbomatch Motor vehicles. Aeronautics. Astronautics TL1-4050
Acceso en línea:	https://doaj.org/article/ac6995007d854243a815ec2eaacaf4a0
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id	oai:doaj.org-article:ac6995007d854243a815ec2eaacaf4a0
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spelling	oai:doaj.org-article:ac6995007d854243a815ec2eaacaf4a02021-11-25T15:57:26ZBlade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study10.3390/aerospace81103302226-4310https://doaj.org/article/ac6995007d854243a815ec2eaacaf4a02021-11-01T00:00:00Zhttps://www.mdpi.com/2226-4310/8/11/330https://doaj.org/toc/2226-4310Degradation of compressors is a common concern for operators of gas turbine engines (GTEs). Surface roughness, due to erosion or fouling, is considered one of the major factors of the degradation phenomenon in compressors that can negatively affect the designed pressure rise, efficiency, and, therefore, the engine aero/thermodynamic performance. The understanding of the aerodynamic implications of varying the blade surface roughness plays a significant role in establishing the magnitude of performance degradation. The present work investigates the implications due to the degradation of the compressor caused by the operation in eroding environments on the gas turbine cycle performance linking, thereby, the compressor aerodynamics with a thermodynamic cycle. At the core of the present study is the numerical assessment of the effect of surface roughness on compressor performance employing the Computational Fluid Dynamics (CFD) tools. The research engine test case employed in the study comprised a fan, bypass, and two stages of the low pressure compressor (booster). Three operating conditions on the 100% speed-line, including the design point, were investigated. Five roughness cases, in addition to the smooth case, with equivalent sand-grain roughness (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>k</mi><mi>s</mi></msub></mrow></semantics></math></inline-formula>) of 15, 30, 45, 60, and 150 µm were simulated. Turbomatch the Cranfield in-house gas turbine performance simulation software, was employed to model the degraded engine performance. The study showed that the increase in the uniform roughness is associated with sizable drops in efficiency, booster pressure ratio (PR), non-dimensional mass flow (NDMF), and overall engine pressure ratio (EPR) together with rises in turbine entry temperature (TET) and specific fuel consumption (SFC). The performance degradation evaluation employed variables such as isentropic efficiency (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>η</mi><mrow><mi>i</mi><mi>s</mi></mrow></msub></mrow></semantics></math></inline-formula>), low pressure compressor (LPC) PR, NDMF, TET, SFC, andEPR. The variation in these quantities showed, for the maximum blade surface degradation case, drops of 7.68%, 2.62% and 3.53%, rises of 1.14% and 0.69%, and a drop of 0.86%, respectively.Jasem AlqallafJoao A. TeixeiraMDPI AGarticleblade surfacecomputational fluid dynamicsgas turbinesurface roughnessturbomatchMotor vehicles. Aeronautics. AstronauticsTL1-4050ENAerospace, Vol 8, Iss 330, p 330 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	blade surface computational fluid dynamics gas turbine surface roughness turbomatch Motor vehicles. Aeronautics. Astronautics TL1-4050
spellingShingle	blade surface computational fluid dynamics gas turbine surface roughness turbomatch Motor vehicles. Aeronautics. Astronautics TL1-4050 Jasem Alqallaf Joao A. Teixeira Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study
description	Degradation of compressors is a common concern for operators of gas turbine engines (GTEs). Surface roughness, due to erosion or fouling, is considered one of the major factors of the degradation phenomenon in compressors that can negatively affect the designed pressure rise, efficiency, and, therefore, the engine aero/thermodynamic performance. The understanding of the aerodynamic implications of varying the blade surface roughness plays a significant role in establishing the magnitude of performance degradation. The present work investigates the implications due to the degradation of the compressor caused by the operation in eroding environments on the gas turbine cycle performance linking, thereby, the compressor aerodynamics with a thermodynamic cycle. At the core of the present study is the numerical assessment of the effect of surface roughness on compressor performance employing the Computational Fluid Dynamics (CFD) tools. The research engine test case employed in the study comprised a fan, bypass, and two stages of the low pressure compressor (booster). Three operating conditions on the 100% speed-line, including the design point, were investigated. Five roughness cases, in addition to the smooth case, with equivalent sand-grain roughness (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>k</mi><mi>s</mi></msub></mrow></semantics></math></inline-formula>) of 15, 30, 45, 60, and 150 µm were simulated. Turbomatch the Cranfield in-house gas turbine performance simulation software, was employed to model the degraded engine performance. The study showed that the increase in the uniform roughness is associated with sizable drops in efficiency, booster pressure ratio (PR), non-dimensional mass flow (NDMF), and overall engine pressure ratio (EPR) together with rises in turbine entry temperature (TET) and specific fuel consumption (SFC). The performance degradation evaluation employed variables such as isentropic efficiency (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>η</mi><mrow><mi>i</mi><mi>s</mi></mrow></msub></mrow></semantics></math></inline-formula>), low pressure compressor (LPC) PR, NDMF, TET, SFC, andEPR. The variation in these quantities showed, for the maximum blade surface degradation case, drops of 7.68%, 2.62% and 3.53%, rises of 1.14% and 0.69%, and a drop of 0.86%, respectively.
format	article
author	Jasem Alqallaf Joao A. Teixeira
author_facet	Jasem Alqallaf Joao A. Teixeira
author_sort	Jasem Alqallaf
title	Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study
title_short	Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study
title_full	Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study
title_fullStr	Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study
title_full_unstemmed	Blade Roughness Effects on Compressor and Engine Performance—A CFD and Thermodynamic Study
title_sort	blade roughness effects on compressor and engine performance—a cfd and thermodynamic study
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/ac6995007d854243a815ec2eaacaf4a0
work_keys_str_mv	AT jasemalqallaf bladeroughnesseffectsoncompressorandengineperformanceacfdandthermodynamicstudy AT joaoateixeira bladeroughnesseffectsoncompressorandengineperformanceacfdandthermodynamicstudy
_version_	1718413399328555008

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

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