Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures
As turbine entry temperatures of modern jet engines continue to increase, additional thermal stresses are introduced onto the high-pressure turbine rotors, which are already burdened by substantial levels of centrifugal and gas loads. Usually, for modern turbofan engines, the temperature distributio...
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MDPI AG
2024-09-01
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| author | Mario Carta Shahrokh Shahpar Tiziano Ghisu Fabio Licheri |
| author_facet | Mario Carta Shahrokh Shahpar Tiziano Ghisu Fabio Licheri |
| author_sort | Mario Carta |
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| description | As turbine entry temperatures of modern jet engines continue to increase, additional thermal stresses are introduced onto the high-pressure turbine rotors, which are already burdened by substantial levels of centrifugal and gas loads. Usually, for modern turbofan engines, the temperature distribution upstream of the high-pressure stator is characterized by a series of high-temperature regions, determined by the circumferential arrangement of the combustor burners. The position of these high-temperature regions, both radially and circumferentially in relation to the high-pressure stator arrangement, can have a strong impact on their subsequent migration through the high-pressure stage. Therefore, for a given amount of thermal power entering the turbine, a significant reduction in maximum rotor temperatures can be achieved by adjusting the inlet temperature distribution. This paper is aimed at mitigating the maximum surface temperatures on a high-pressure turbine rotor from a modern commercial turbofan engine by conducting a parametric analysis and optimization of the inlet temperature field. The parameters considered for this study are the circumferential position of the high-temperature spots, and the overall bias of the temperature distribution in the radial direction. High-fidelity unsteady (phase-lag) and conjugate heat transfer simulations are performed to evaluate the effects of inlet clocking and radial bias on rotor metal temperatures. The optimized inlet distribution achieved a 100 K reduction in peak high-pressure rotor temperatures and 7.5% lower peak temperatures on the high-pressure stator vanes. Furthermore, the optimized temperature distribution is also characterized by a significantly more uniform heat load allocation on the stator vanes, when compared to the baseline one. |
| format | Article |
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| institution | OA Journals |
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| language | English |
| publishDate | 2024-09-01 |
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| spelling | doaj-art-0a45e9aa7cf34bf78ffee33f585156292025-08-20T01:56:09ZengMDPI AGAerospace2226-43102024-09-0111975010.3390/aerospace11090750Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine TemperaturesMario Carta0Shahrokh Shahpar1Tiziano Ghisu2Fabio Licheri3Department of Mechanical, Chemical and Materials Engineering, University of Cagliari, 09123 Cagliari, ItalyRolls-Royce Plc, Fluid Mechanics, Derby DE24 8BJ, UKDepartment of Mechanical, Chemical and Materials Engineering, University of Cagliari, 09123 Cagliari, ItalyDepartment of Mechanical, Chemical and Materials Engineering, University of Cagliari, 09123 Cagliari, ItalyAs turbine entry temperatures of modern jet engines continue to increase, additional thermal stresses are introduced onto the high-pressure turbine rotors, which are already burdened by substantial levels of centrifugal and gas loads. Usually, for modern turbofan engines, the temperature distribution upstream of the high-pressure stator is characterized by a series of high-temperature regions, determined by the circumferential arrangement of the combustor burners. The position of these high-temperature regions, both radially and circumferentially in relation to the high-pressure stator arrangement, can have a strong impact on their subsequent migration through the high-pressure stage. Therefore, for a given amount of thermal power entering the turbine, a significant reduction in maximum rotor temperatures can be achieved by adjusting the inlet temperature distribution. This paper is aimed at mitigating the maximum surface temperatures on a high-pressure turbine rotor from a modern commercial turbofan engine by conducting a parametric analysis and optimization of the inlet temperature field. The parameters considered for this study are the circumferential position of the high-temperature spots, and the overall bias of the temperature distribution in the radial direction. High-fidelity unsteady (phase-lag) and conjugate heat transfer simulations are performed to evaluate the effects of inlet clocking and radial bias on rotor metal temperatures. The optimized inlet distribution achieved a 100 K reduction in peak high-pressure rotor temperatures and 7.5% lower peak temperatures on the high-pressure stator vanes. Furthermore, the optimized temperature distribution is also characterized by a significantly more uniform heat load allocation on the stator vanes, when compared to the baseline one.https://www.mdpi.com/2226-4310/11/9/750jet enginehot streak migrationconjugate heat transferphase-lag simulation |
| spellingShingle | Mario Carta Shahrokh Shahpar Tiziano Ghisu Fabio Licheri Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures Aerospace jet engine hot streak migration conjugate heat transfer phase-lag simulation |
| title | Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures |
| title_full | Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures |
| title_fullStr | Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures |
| title_full_unstemmed | Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures |
| title_short | Multi-Fidelity Modelling of the Effect of Combustor Traverse on High-Pressure Turbine Temperatures |
| title_sort | multi fidelity modelling of the effect of combustor traverse on high pressure turbine temperatures |
| topic | jet engine hot streak migration conjugate heat transfer phase-lag simulation |
| url | https://www.mdpi.com/2226-4310/11/9/750 |
| work_keys_str_mv | AT mariocarta multifidelitymodellingoftheeffectofcombustortraverseonhighpressureturbinetemperatures AT shahrokhshahpar multifidelitymodellingoftheeffectofcombustortraverseonhighpressureturbinetemperatures AT tizianoghisu multifidelitymodellingoftheeffectofcombustortraverseonhighpressureturbinetemperatures AT fabiolicheri multifidelitymodellingoftheeffectofcombustortraverseonhighpressureturbinetemperatures |