Abstract
In the present work, LBO limits for methane-air combustion stabilized by a V-Gutter have been predicted by a hybrid method using numerical simulation and empirical relations. The numerical simulations have been carried out to study the stable methane-air combustion and temperature gradients at exit and recirculation region in a model gas turbine afterburner with a planar V-Gutter as a bluff body for four inlet air pressure conditions and three V-Gutter angles. The calculated average exit gas temperature (AEGT) and the average gas temperature in recirculation region have been used for predicting the blowout conditions. An empirical method based on Feature Section Criterion has been used to determine Fuel-Air Ratio (FAR) at blowout conditions very accurately from the numerically calculated average temperature in the central recirculation zone (CRZ).The predicted Fuel-Air Ratio (FAR) at lean blowout conditions has been compared with the experimental results obtained for the same conditions and are found to be in good agreement.
Nomenclature
| (A/F)ST | Stoichiometric air fuel ratio |
| mair | Mass flow rate of air (kg) |
| mfuel | Mass flow rate of fuel (kg) |
| MWair | Molecular Weight of air |
| MWfuel | Molecular Weight of fuel |
| Γ | Feature parameter |
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Articles in the same Issue
- Frontmatter
- Estimation of Characteristic Data of Aircraft Engine Compressor based on Developed Modeling Method
- Conjugate Heat Transfer Analysis on the Interior Surface of Nozzle Guide Vane with Combined Impingement and Film Cooling
- Prediction of Lean Blowout Limits for Methane-Air Bluff Body Stabilized Combustion using a Temperature Gradient Method in a Model Gas-Turbine Afterburner
- Investigation of Film Cooling Effectiveness of Dual-fanned Hole with Various Exit Widths
- Performance Seeking Control of Propfan Engines Based on Modified Cuckoo Search
- A New Scheduling Method for TTCAN-Based Turbofan Distributed Control System
- Numerical Investigation of Three-dimensional Separation Control on a High-speed Compressor Stator Vane with Tailored Synthetic Jet
- Aerodynamic Optimization of Winglet-Cavity Tip in an Axial High Pressure Turbine Stage
- Estimation of Gas Turbine Unmeasured Variables for an Online Monitoring System
Articles in the same Issue
- Frontmatter
- Estimation of Characteristic Data of Aircraft Engine Compressor based on Developed Modeling Method
- Conjugate Heat Transfer Analysis on the Interior Surface of Nozzle Guide Vane with Combined Impingement and Film Cooling
- Prediction of Lean Blowout Limits for Methane-Air Bluff Body Stabilized Combustion using a Temperature Gradient Method in a Model Gas-Turbine Afterburner
- Investigation of Film Cooling Effectiveness of Dual-fanned Hole with Various Exit Widths
- Performance Seeking Control of Propfan Engines Based on Modified Cuckoo Search
- A New Scheduling Method for TTCAN-Based Turbofan Distributed Control System
- Numerical Investigation of Three-dimensional Separation Control on a High-speed Compressor Stator Vane with Tailored Synthetic Jet
- Aerodynamic Optimization of Winglet-Cavity Tip in an Axial High Pressure Turbine Stage
- Estimation of Gas Turbine Unmeasured Variables for an Online Monitoring System