Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
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Thuraganur V. Yogesh
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Laasya P. Nidamarty
Abstract
Drawing the inspiration from Full Engine Simulation performed by the scientific community, the methodology for performing an integration analysis of single stage turbine with convergent exhaust nozzle of a small gas turbine engine is developed in the present study. Initially, a numerical simulation on exhaust system supported with experimental validation has been discussed. A scope of improvement in the exhaust system study has been identified and these principles are applied to improve the accuracy of prediction of CFD analysis. By taking the confidence from the validation, a 3D steady pressure-based analysis is carried out to understand the flow patterns and aero-thermal properties of the single stage turbine with convergent type nozzle influenced by the integration. The integration resulted in increased specific work output of the turbine and increased the thrust coefficient of the nozzle. Further important outcomes of this study highlight the changes observed in the performance parameters with and without integration. The thermal pattern across the rotor blades from CFD analysis is observed to be in-line with the used blades of the gas turbine engine thereby reinforcing the accuracy of the methodology developed for the integration study.
Acknowledgments
Authors like to acknowledge Director, GTRE, DRDO for supporting to carry out the activities and permitting to publish the contents provided in the publication.
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Research ethics: I hereby declare that the contents of the publication are not published in any conferences, journals, and publications.
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Informed consent: Informed consent was obtained from all individuals included in this study, or their legal guardians or wards.
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Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Use of Large Language Models, AI and Machine Learning Tools: None declared.
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Conflict of interest: All authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
Nomenclature (SI units)
- ε
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rate of dissipation of turbulent kinetic energy (J/s)
- ω
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turbulence frequency (s)
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
Artikel in diesem Heft
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
