Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module
An approach for preliminary aero-engine design, incorporating a mean-line code for the design of axial-flow, multi-stage compressors, is presented. The compressor mean-line code is developed and integrated within a framework for the preliminary design and assessment of aero-engine concepts. It is th...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2023-08-01
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| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/10/8/726 |
| _version_ | 1797585882987888640 |
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| author | Alexios Alexiou Ioannis Kolias Nikolaos Aretakis Konstantinos Mathioudakis |
| author_facet | Alexios Alexiou Ioannis Kolias Nikolaos Aretakis Konstantinos Mathioudakis |
| author_sort | Alexios Alexiou |
| collection | DOAJ |
| description | An approach for preliminary aero-engine design, incorporating a mean-line code for the design of axial-flow, multi-stage compressors, is presented. The compressor mean-line code is developed and integrated within a framework for the preliminary design and assessment of aero-engine concepts. It is then combined with modules for compressor map generation, multi-point engine design, steady-state and transient engine off-design performance and aircraft mission analysis. Implementation examples are presented, demonstrating the determination of the optimal combination of compressor and engine design parameters for achieving minimum fuel burn over a specific aircraft mission, while obeying constraints that guarantee operability over the entire flight envelope. Constraints related to compressor stability during transient maneuvers between idle and static take-off conditions and engine temperature limits at maximum take-off are respected by the final design. The results demonstrate the potential for design trade-offs between engine performance at the aircraft mission level and compressor aerodynamic stability. |
| first_indexed | 2024-03-11T00:13:28Z |
| format | Article |
| id | doaj.art-68227a4b40ef4dc78cbf926ac2669427 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-11T00:13:28Z |
| publishDate | 2023-08-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-68227a4b40ef4dc78cbf926ac26694272023-11-18T23:50:23ZengMDPI AGAerospace2226-43102023-08-0110872610.3390/aerospace10080726Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design ModuleAlexios Alexiou0Ioannis Kolias1Nikolaos Aretakis2Konstantinos Mathioudakis3Laboratory of Thermal Turbomachines, School of Mechanical Engineering, National Technical University of Athens, 15780 Athens, GreeceLaboratory of Thermal Turbomachines, School of Mechanical Engineering, National Technical University of Athens, 15780 Athens, GreeceLaboratory of Thermal Turbomachines, School of Mechanical Engineering, National Technical University of Athens, 15780 Athens, GreeceLaboratory of Thermal Turbomachines, School of Mechanical Engineering, National Technical University of Athens, 15780 Athens, GreeceAn approach for preliminary aero-engine design, incorporating a mean-line code for the design of axial-flow, multi-stage compressors, is presented. The compressor mean-line code is developed and integrated within a framework for the preliminary design and assessment of aero-engine concepts. It is then combined with modules for compressor map generation, multi-point engine design, steady-state and transient engine off-design performance and aircraft mission analysis. Implementation examples are presented, demonstrating the determination of the optimal combination of compressor and engine design parameters for achieving minimum fuel burn over a specific aircraft mission, while obeying constraints that guarantee operability over the entire flight envelope. Constraints related to compressor stability during transient maneuvers between idle and static take-off conditions and engine temperature limits at maximum take-off are respected by the final design. The results demonstrate the potential for design trade-offs between engine performance at the aircraft mission level and compressor aerodynamic stability.https://www.mdpi.com/2226-4310/10/8/726aero-enginespreliminary designaxial compressormean-line designengine optimizationoperability |
| spellingShingle | Alexios Alexiou Ioannis Kolias Nikolaos Aretakis Konstantinos Mathioudakis Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module Aerospace aero-engines preliminary design axial compressor mean-line design engine optimization operability |
| title | Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module |
| title_full | Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module |
| title_fullStr | Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module |
| title_full_unstemmed | Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module |
| title_short | Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module |
| title_sort | aero engine preliminary design optimization and operability studies supported by a compressor mean line design module |
| topic | aero-engines preliminary design axial compressor mean-line design engine optimization operability |
| url | https://www.mdpi.com/2226-4310/10/8/726 |
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