About this Special Issue
The combustion chamber and high-pressure turbine (HPT) are the two most critical hot components of the core engine in aero-engines. The flow conditions and temperature profiles at the combustor-turbine interface play a significant role in the advancement of modern aero-engines. At this interface, essential flow information is transferred from the combustor to the turbine, and the high-pressure turbine, particularly its first stage, is strongly influenced by the complex upstream flows exiting the combustor.
Consequently, the presence of downstream turbines, along with their inherent unsteady flow characteristics, significantly impacts the combustion chamber. Therefore, a comprehensive understanding of the combustor-turbine interaction (CTI) phenomenon is essential, encompassing, but not limited to, flow distribution with swirling, the migration of hot streaks, total pressure distortion, noise generation, and thermoacoustic instability. These elements are crucial for elucidating the interaction mechanisms between the combustor and the HPT, particularly in the design and optimization of both components, including their integrated design. This special issue aims to highlight the latest research and developments concerning CTI mechanisms in aero-engines, thereby providing a platform for researchers and practitioners to share insights and innovations.
Scope
This Special Issue invites contributions related to the applications of combustor-turbine interactions in aeroengine research and engineering implications, including but not limited to the following areas:
1. Numerical modelling and simulation methods
2. Experiment test and flow diagnostics
3. Hot streaks and other non-uniformities migrations and dilutions
4. HPT aerothermal performance analysis and cooling design
5. Acoustic impedance and combustion stabilities
6. Noise generation (direct and indirect noise)
7. Combustor-turbine integrated design and analysis
Prospective contributors are invited to submit original research articles, review articles, and case studies that address the topics outlined above. All submissions will undergo a rigorous peer-review process to ensure the quality, relevance, and originality of the published content.
Any questions? Please email the Editorial Office.
All article processing charges are being waived until the end of 2025 for submissions to Aerospace Research Communications.
Consequently, the presence of downstream turbines, along with their inherent unsteady flow characteristics, significantly impacts the combustion chamber. Therefore, a comprehensive understanding of the combustor-turbine interaction (CTI) phenomenon is essential, encompassing, but not limited to, flow distribution with swirling, the migration of hot streaks, total pressure distortion, noise generation, and thermoacoustic instability. These elements are crucial for elucidating the interaction mechanisms between the combustor and the HPT, particularly in the design and optimization of both components, including their integrated design. This special issue aims to highlight the latest research and developments concerning CTI mechanisms in aero-engines, thereby providing a platform for researchers and practitioners to share insights and innovations.
Scope
This Special Issue invites contributions related to the applications of combustor-turbine interactions in aeroengine research and engineering implications, including but not limited to the following areas:
1. Numerical modelling and simulation methods
2. Experiment test and flow diagnostics
3. Hot streaks and other non-uniformities migrations and dilutions
4. HPT aerothermal performance analysis and cooling design
5. Acoustic impedance and combustion stabilities
6. Noise generation (direct and indirect noise)
7. Combustor-turbine integrated design and analysis
Prospective contributors are invited to submit original research articles, review articles, and case studies that address the topics outlined above. All submissions will undergo a rigorous peer-review process to ensure the quality, relevance, and originality of the published content.
Any questions? Please email the Editorial Office.
All article processing charges are being waived until the end of 2025 for submissions to Aerospace Research Communications.
Keywords: Combustor-turbine interactions, Reactive flows, Swirling flows, HP turbine, aerothermal modelling and test, Direct/indirect noise, Combustion instabilities, High fidelity simulation, Combustor-turbine integrated design
