Abstract:
A method for detecting malfunctions in a combustion chamber of a gas turbine plant includes providing dynamic pressure signals (P1 I , P2,...., P N ), each indicative of a dynamic pressure at the outlet of a respective burner of a combustion chamber of the plant. Frequency spectra (S 1 (f), S 2 (f),..., S N (f), S 1 *(f), S 2 * (f),..., S N *(f)) of the dynamic pressure signals (P 1 , P 2 ,..., P N ) are calculated, the malfunctions of the burners are recognized according to these spectra. Each burner subject to malfunctioning is identified according to a bijective correlation between the burners and the respective dynamic pressure signals (P 1 , P 2 ,..., P N ).
Abstract:
A gas turbine plant (1) for electric energy production is equipped with; a gas turbine (5); a compressor (3); a combustion chamber (4); a plurality of heat-sensitive elements (34) configured to detect a plurality of temperature values (T(1), T(2)... Tn) inside the combustion chamber (4); a control unit (12) configured to regulate at least a first parameter (PILOTpos; IGVpos; COOLpos; SPpower) of the plant (1) on the basis of the temperature values (T1, T2... Tn) detected by the plurality of heat- sensitive elements (34).
Abstract:
A burner assembly for a gas turbine includes a main burner (20), extending about an axis (B), and a Helmholtz resonator (22) having a resonant chamber (35) and passages (36, 37) for fluidic connection of the resonant chamber (35) to the outside. The main burner (20) further includes an inner body (25) and an outer body (26), which extend about the axis (B), and a swirler (23), arranged between the inner body (25) and the outer body (26) and defining mixing channels (30). The resonant chamber (35) is arranged about the outer body (26) adjacent to an inlet (31) of the swirler (23). The outer body (26) delimits a portion of the resonant chamber (35) and is shaped so as to prevent direct fluidic connections between the Helmholtz resonator (22) and the mixing channels (30).
Abstract:
A method for supplying fuel to a combustion chamber (4) of a gas turbine plant (1) envisaging supplying lean gas to the combustion chamber' (4) through a lean gas supply line (12) of the plant (1) and supplying natural gas to the combustion chamber (4) through a natural gas supply line (13) of the plant (1), which includes a pilot delivery line (23). In particular, the step of supplying natural gas envisages the measuring of a lean gas calorific value (HV SG ), calculating at least a first natural gas flow rate (Q NGp) to be supplied to the combustion chamber (4) through the pilot delivery line (23) on the basis of the measured lean gas calorific value (HV SG ), and supplying at least the first natural gas flow rate (Q NGp ) to the combustion chamber (4) through the pilot delivery line (23).