Abstract Aero engine performance analysis is very important for engines under development as well as for engines in service for condition monitoring. Predictions of aero engine performance and ability of building the simulation model is an invaluable asset for designers, manufacturer and end-use operator. This paper presents the methodology in establishing the baseline performance of a twin spool mixed flow low bypass turbofan engine through extensive testing at engine test bench. The baseline data is used to validate a GasTurb model which is subsequently used for assessment of off-design performance and component degradation responsible for performance deterioration at various service hours. The estimated exhaust gas temperatures by the model for degraded engines are in good agreement with the measured data. The model further assesses the drop in HP compressor efficiency and shift in operating line which will be very useful for taking judicious decision for withdrawal of engines and is expected to reduce or delay withdrawals and increase the availability of engines at operating base.
{"title":"Assessment of performance degradation of a mixed flow low bypass turbofan engine through GasTurb simulation","authors":"Narahari Rath, Mishra R. K., A. Kushari","doi":"10.1515/tjj-2023-0064","DOIUrl":"https://doi.org/10.1515/tjj-2023-0064","url":null,"abstract":"Abstract Aero engine performance analysis is very important for engines under development as well as for engines in service for condition monitoring. Predictions of aero engine performance and ability of building the simulation model is an invaluable asset for designers, manufacturer and end-use operator. This paper presents the methodology in establishing the baseline performance of a twin spool mixed flow low bypass turbofan engine through extensive testing at engine test bench. The baseline data is used to validate a GasTurb model which is subsequently used for assessment of off-design performance and component degradation responsible for performance deterioration at various service hours. The estimated exhaust gas temperatures by the model for degraded engines are in good agreement with the measured data. The model further assesses the drop in HP compressor efficiency and shift in operating line which will be very useful for taking judicious decision for withdrawal of engines and is expected to reduce or delay withdrawals and increase the availability of engines at operating base.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-08-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46638670","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Abstract In this study, the authors propose an optimization process to design the baseline rotor of a supersonic through-flow fan (STFF) at an inlet Mach number of 2.0 based on Genetic Algorithm. Unlike the improvement in performance brought about by the pre-compression of conventional supersonic profiles in the presence of axial pressure flow, pre-compression did not help improve the performance of the rotor of the STFF. The efficiency of elements of the blade at spanwise heights of 10 %, 50 %, and 90 % increased by 2.47 %, 1.95 %, and 2.49 %, respectively. The performance of the rotor of the STFF that was reconstructed by stacking the optimized elements of the blade was improved at the design point as well as in off-design conditions by using three-dimensional computational fluid dynamics (CFD) simulations. The performance of the blade also improved considerably, with increases of by 2.46 % and 9.59 % in its isentropic efficiency and the overall pressure ratio, respectively.
{"title":"Design optimization of a supersonic through-flow fan rotor based on the blade profiles","authors":"Jutao Yang, L. Ji, Yuxin Shen, Lingchen Zhou","doi":"10.1515/tjj-2022-0082","DOIUrl":"https://doi.org/10.1515/tjj-2022-0082","url":null,"abstract":"Abstract In this study, the authors propose an optimization process to design the baseline rotor of a supersonic through-flow fan (STFF) at an inlet Mach number of 2.0 based on Genetic Algorithm. Unlike the improvement in performance brought about by the pre-compression of conventional supersonic profiles in the presence of axial pressure flow, pre-compression did not help improve the performance of the rotor of the STFF. The efficiency of elements of the blade at spanwise heights of 10 %, 50 %, and 90 % increased by 2.47 %, 1.95 %, and 2.49 %, respectively. The performance of the rotor of the STFF that was reconstructed by stacking the optimized elements of the blade was improved at the design point as well as in off-design conditions by using three-dimensional computational fluid dynamics (CFD) simulations. The performance of the blade also improved considerably, with increases of by 2.46 % and 9.59 % in its isentropic efficiency and the overall pressure ratio, respectively.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-07-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46558494","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Jutao Yang, Yuxin Shen, L. Ji, Jiabin Li, Lingchen Zhou
Abstract This article delves into the intricate relationship between the modeling parameters of an axial supersonic through-flow fan (STFF) rotor and its performance based on an active subspace method. It considers the influence of the STFF rotor key parameters on its performance. Implementing the active subspace method generates cloud maps to visualize the performance of the STFF rotor. Moreover, this study investigates the correlation between Bezier curve variables for constructing blade angles and critical performance metrics, such as the total pressure ratio and isentropic efficiency. After a 50 % chord length, the Bezier control point parameters dominate the effect on the total pressure ratio with a linear relationship. This article provides comparative flow field analyses on the blade elements with different performances under three working conditions. Under the constraint of the blade chamber turning angle, there is a linear relationship between the upper and lower limits of the isentropic efficiency distribution and total pressure ratio. This study shows that the total pressure ratio, installation angle, and maximum deflection value are positively associated. Further analysis provides an empirical formula.
{"title":"Active subspace-based performance analysis of supersonic through-flow fan rotor","authors":"Jutao Yang, Yuxin Shen, L. Ji, Jiabin Li, Lingchen Zhou","doi":"10.1515/tjj-2023-0044","DOIUrl":"https://doi.org/10.1515/tjj-2023-0044","url":null,"abstract":"Abstract This article delves into the intricate relationship between the modeling parameters of an axial supersonic through-flow fan (STFF) rotor and its performance based on an active subspace method. It considers the influence of the STFF rotor key parameters on its performance. Implementing the active subspace method generates cloud maps to visualize the performance of the STFF rotor. Moreover, this study investigates the correlation between Bezier curve variables for constructing blade angles and critical performance metrics, such as the total pressure ratio and isentropic efficiency. After a 50 % chord length, the Bezier control point parameters dominate the effect on the total pressure ratio with a linear relationship. This article provides comparative flow field analyses on the blade elements with different performances under three working conditions. Under the constraint of the blade chamber turning angle, there is a linear relationship between the upper and lower limits of the isentropic efficiency distribution and total pressure ratio. This study shows that the total pressure ratio, installation angle, and maximum deflection value are positively associated. Further analysis provides an empirical formula.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-07-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48299292","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Abstract Hydrogen-blended fuel is a promising resource for future generations of gas turbine engines, due to its capability of reducing carbon-based emissions. This paper presents a numerical study to assess hydrogen-enriched combustion in a laboratory-scale burner operating at a high turbulence level and under lean and stoichiometric burning conditions. Moreover, a wide range of H2 (up to 90 %) is used for enriching CH4-air combustion in combination with two different swirl levels. The results show that a high swirl intensity results in shorter flames, due to the increased turbulent intensity, which reduces the flame surface area and uniformness the reacting zone. Besides, increasing swirl intensity further increase flame temperature for a given H2-blended fuel. Overall, the results suggest that high swirl intensity in combination to lean mixtures is favorable when using H2-blended fuel with high H2 concentrations. The simulation results also demonstrate that considering radiation heat loss is influential, as it yields a reduction of the outlet temperature by not less than 100 K, bringing down NO x emissions by half.
{"title":"Numerical study of the impact of hydrogen addition, swirl intensity and equivalence ratio on methane-air combustion","authors":"M. Elbayoumi, F. Garnier, P. Seers","doi":"10.1515/tjj-2021-0048","DOIUrl":"https://doi.org/10.1515/tjj-2021-0048","url":null,"abstract":"Abstract Hydrogen-blended fuel is a promising resource for future generations of gas turbine engines, due to its capability of reducing carbon-based emissions. This paper presents a numerical study to assess hydrogen-enriched combustion in a laboratory-scale burner operating at a high turbulence level and under lean and stoichiometric burning conditions. Moreover, a wide range of H2 (up to 90 %) is used for enriching CH4-air combustion in combination with two different swirl levels. The results show that a high swirl intensity results in shorter flames, due to the increased turbulent intensity, which reduces the flame surface area and uniformness the reacting zone. Besides, increasing swirl intensity further increase flame temperature for a given H2-blended fuel. Overall, the results suggest that high swirl intensity in combination to lean mixtures is favorable when using H2-blended fuel with high H2 concentrations. The simulation results also demonstrate that considering radiation heat loss is influential, as it yields a reduction of the outlet temperature by not less than 100 K, bringing down NO x emissions by half.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42320245","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Abstract The ingestion of ice crystals in aero-engine will cause engine surge, flameout, thrust loss, and even in-flight shutdown in the extreme cases, which seriously endanger the flight safety. In order to quantitatively investigate the ice crystal melting characteristic in the compressor, a method based on the compressor mean line flow was developed and validated. Results showed that the wet-bulb temperature increases as the temperature offset increases. The increase in temperature offset or decrease in particle size result in earlier or faster melting of the ice crystals in the low-pressure compressor. The rate of increase in melting ratio decreases with the increase of ice water content at the descent condition. The ambient temperature and ice crystal property are both the important factors affecting the icing risk in the compressor. Higher ambient temperature, smaller particle size or higher ice water content can increase the icing risk in the low-pressure compressor.
{"title":"Numerical investigation of ice crystal melting characteristic and icing risk in an axial compressor","authors":"W. Jia, Bowen Yang, M. Zheng, Q. Kong","doi":"10.1515/tjj-2023-0053","DOIUrl":"https://doi.org/10.1515/tjj-2023-0053","url":null,"abstract":"Abstract The ingestion of ice crystals in aero-engine will cause engine surge, flameout, thrust loss, and even in-flight shutdown in the extreme cases, which seriously endanger the flight safety. In order to quantitatively investigate the ice crystal melting characteristic in the compressor, a method based on the compressor mean line flow was developed and validated. Results showed that the wet-bulb temperature increases as the temperature offset increases. The increase in temperature offset or decrease in particle size result in earlier or faster melting of the ice crystals in the low-pressure compressor. The rate of increase in melting ratio decreases with the increase of ice water content at the descent condition. The ambient temperature and ice crystal property are both the important factors affecting the icing risk in the compressor. Higher ambient temperature, smaller particle size or higher ice water content can increase the icing risk in the low-pressure compressor.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44922074","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Abstract This study measured the aerodynamic performance and dynamic pressure signals of a compressor cascade platform with high-speed rotating endwall. Instead of translational movement, the endwall features an innovative large rotating disk. Measurements were conducted on a controlled diffusion airfoil (CDA) under different conditions: tip clearances (3 mm and 2.5 mm), inlet incidences (+6° and −6°), and stationary or high-speed rotating states at 0.5 Ma inflow. The results reveal that endwall movement amplifies circumferential leakage losses, increases kinetic energy, deviates the leakage flow path, and reduces total pressure loss in the leakage core region. Dynamic pressure results reveal greater unsteadiness in the tip region under positive incidence conditions and with larger clearances. Characteristic frequency ranges (8000 Hz for system vibration and 150∼200 Hz for leakage flow development) are identified. Further experimental measurements and high-precision simulations are needed the determine the matching relationship between complex flow behaviour in the blade tip region and characteristic frequency.
{"title":"Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall","authors":"Kailong Xia, Hefang Deng, Shaopeng Lu, Jinfang Teng, X. Qiang, Mingmin Zhu","doi":"10.1515/tjj-2023-0025","DOIUrl":"https://doi.org/10.1515/tjj-2023-0025","url":null,"abstract":"Abstract This study measured the aerodynamic performance and dynamic pressure signals of a compressor cascade platform with high-speed rotating endwall. Instead of translational movement, the endwall features an innovative large rotating disk. Measurements were conducted on a controlled diffusion airfoil (CDA) under different conditions: tip clearances (3 mm and 2.5 mm), inlet incidences (+6° and −6°), and stationary or high-speed rotating states at 0.5 Ma inflow. The results reveal that endwall movement amplifies circumferential leakage losses, increases kinetic energy, deviates the leakage flow path, and reduces total pressure loss in the leakage core region. Dynamic pressure results reveal greater unsteadiness in the tip region under positive incidence conditions and with larger clearances. Characteristic frequency ranges (8000 Hz for system vibration and 150∼200 Hz for leakage flow development) are identified. Further experimental measurements and high-precision simulations are needed the determine the matching relationship between complex flow behaviour in the blade tip region and characteristic frequency.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45786714","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Dai Yuchen, Song Manxiang, Jin Donghai, G. Xingmin, Liu Xiaoheng
Abstract The significance of the volume effect on the compressor performance during acceleration and deceleration has received limited attention, despite its demonstrated importance in compressor flow instabilities. To better understand this effect, the in-house simulation program CAM (a modular transient simulator) is used to investigate the volume effect on the compressor transient performance. The modeling procedure is derived from Greziter’s lumped parameter approach and the accuracy of the simulation model is verified by experimental data. This study presents a comprehensive comparison and explanation of variations in compressor transient behavior observed under different conditions, including different shaft speed change rates, compressor volume sizes, and operating speeds. The relative difference between the compressor inlet and outlet mass flow is identified as the key factor contributing to these discrepancies. In addition, a simplified analytical model is developed to provide a basic description of the compressor operating line during acceleration and deceleration, which also provides additional support for the validity of the numerical results. This study systematically establishes the dynamic dependencies between shaft speed change, pressure and mass flow change, offering critical information for ensuring the safety of compressors during transient operation.
{"title":"The role of volume effect on the transient behavior of a transonic compressor","authors":"Dai Yuchen, Song Manxiang, Jin Donghai, G. Xingmin, Liu Xiaoheng","doi":"10.1515/tjj-2023-0013","DOIUrl":"https://doi.org/10.1515/tjj-2023-0013","url":null,"abstract":"Abstract The significance of the volume effect on the compressor performance during acceleration and deceleration has received limited attention, despite its demonstrated importance in compressor flow instabilities. To better understand this effect, the in-house simulation program CAM (a modular transient simulator) is used to investigate the volume effect on the compressor transient performance. The modeling procedure is derived from Greziter’s lumped parameter approach and the accuracy of the simulation model is verified by experimental data. This study presents a comprehensive comparison and explanation of variations in compressor transient behavior observed under different conditions, including different shaft speed change rates, compressor volume sizes, and operating speeds. The relative difference between the compressor inlet and outlet mass flow is identified as the key factor contributing to these discrepancies. In addition, a simplified analytical model is developed to provide a basic description of the compressor operating line during acceleration and deceleration, which also provides additional support for the validity of the numerical results. This study systematically establishes the dynamic dependencies between shaft speed change, pressure and mass flow change, offering critical information for ensuring the safety of compressors during transient operation.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-06-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45734714","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Abstract For an aero turbo-shaft engine, rain water enters the intake protection device and the morphology of water droplets after hitting the wall will affect the internal flow of the compressor. In this paper, Sommerfeld number was used to determine the shape of water droplets after they hit the wall. The flow field and characteristics of the compressor with inlet particle separator under different water ingestion conditions were studied with considering the impact of water film and droplets splashing near the wall. The results show that the entry of water droplets deteriorates the internal flow field of the compression component, and the water film affects the flow state of the airflow near the wall. Compared to the effect of the splashing factor, the viscous resistance effect of water film near the wall on the airflow and boundary layer can cause a significant reduction in the characteristics and stability of the compressor.
{"title":"Study on the water ingestion performance of compressor with inlet particle separator","authors":"Mingcong Luo, Yonghao Yu, Aocheng Liu, Shilin Yan","doi":"10.1515/tjj-2023-0006","DOIUrl":"https://doi.org/10.1515/tjj-2023-0006","url":null,"abstract":"Abstract For an aero turbo-shaft engine, rain water enters the intake protection device and the morphology of water droplets after hitting the wall will affect the internal flow of the compressor. In this paper, Sommerfeld number was used to determine the shape of water droplets after they hit the wall. The flow field and characteristics of the compressor with inlet particle separator under different water ingestion conditions were studied with considering the impact of water film and droplets splashing near the wall. The results show that the entry of water droplets deteriorates the internal flow field of the compression component, and the water film affects the flow state of the airflow near the wall. Compared to the effect of the splashing factor, the viscous resistance effect of water film near the wall on the airflow and boundary layer can cause a significant reduction in the characteristics and stability of the compressor.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-06-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49631996","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Wang Qing-ping, Wang Fei, Zhang Wen-chao, Zhang Wei-feng
Abstract To reduce excessive vibration of a turboprop engine with qualified balanced compressor and turbine rotor, the finite element model of the rotor system was established. The magnitude, axial distribution and especially the phase combinations of the residual unbalances were considered and optimized. Based on the numerical results, the whole engine tests were conducted for verification. The numerical and experimental results show that the vibration level of the rotor system can be significantly reduced by only changing the phase combination of the residual unbalances. The magnitude, axial distribution of residual unbalance and rotational speed of the rotor play a very important role in determining the optimal phase combination. The optimal phase combination under different rotational speeds might be conflicting, and reasonably designed optimization would be a feasible solution. The findings of the research can provide important reference for the design and troubleshooting for similar industrial turbine engines.
{"title":"Influences of unbalance phase combination on the dynamic characteristics for a turboprop engine","authors":"Wang Qing-ping, Wang Fei, Zhang Wen-chao, Zhang Wei-feng","doi":"10.1515/tjj-2023-0023","DOIUrl":"https://doi.org/10.1515/tjj-2023-0023","url":null,"abstract":"Abstract To reduce excessive vibration of a turboprop engine with qualified balanced compressor and turbine rotor, the finite element model of the rotor system was established. The magnitude, axial distribution and especially the phase combinations of the residual unbalances were considered and optimized. Based on the numerical results, the whole engine tests were conducted for verification. The numerical and experimental results show that the vibration level of the rotor system can be significantly reduced by only changing the phase combination of the residual unbalances. The magnitude, axial distribution of residual unbalance and rotational speed of the rotor play a very important role in determining the optimal phase combination. The optimal phase combination under different rotational speeds might be conflicting, and reasonably designed optimization would be a feasible solution. The findings of the research can provide important reference for the design and troubleshooting for similar industrial turbine engines.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":null,"pages":null},"PeriodicalIF":0.9,"publicationDate":"2023-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45347956","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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