Open AccessExperimental Prediction of Lean Blowout Limits for 3kW Micro Gas Turbine Combustor fuelled with LPG
Author(s) -
V. Kirubakaran,
David Bhatt
Publication year - 2021
Publication title -
incas buletin
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.282
H-Index - 10
eISSN - 2247-4528
pISSN - 2066-8201
DOI - 10.13111/2066-8201.2021.13.1.9
Subject(s) - combustor , pressure drop , inlet , turbine , gas turbines , liquefied petroleum gas , nuclear engineering , materials science , mechanics , environmental science , combustion , aerospace engineering , engineering , mechanical engineering , waste management , chemistry , physics , organic chemistry
The Lean Blowout Limit of the combustor is one of the important performance parameters for a gas turbine combustor design. This study aims to predict the total pressure loss and Lean Blowout (LBO) limits of an in-house designed swirl stabilized 3kW can-type micro gas turbine combustor. The experimental prediction of total pressure loss and LBO limits was performed on a designed combustor fuelled with Liquefied Petroleum Gas (LPG) for the combustor inlet velocity ranging from 1.70 m/s to 11 m/s. The results show that the predicted total pressure drop increases with increasing combustor inlet velocity, whereas the LBO equivalence ratio decreases gradually with an increase in combustor inlet velocity. The combustor total pressure drop was found to be negligible; being in the range of 0.002 % to 0.065 % for the measured inlet velocity conditions. These LBO limits predictions will be used to fix the operating boundary conditions of the gas turbine combustor.