A component and a system for mitigating coke formation during delivery of a hydrocarbon fluid. The component includes a contact surface configured to be in contact with the hydrocarbon fluid. Tuning the zeta potential of the contact surface allows selective attraction and/or repulsion of coke-catalyzing materials, metal ions, heteroatomic hydrocarbons, and/or coke precursors present in the hydrocarbon fluid. A method of mitigating coke formation during delivery of a hydrocarbon fluid includes tuning a zeta potential of the contact surface of the component and injecting or circulating the hydrocarbon fluid through the system such that the contact surface selectively attracts and/or repels coke-catalyzing materials, metal ions, heteroatomic hydrocarbons, and/or coke precursors present in the hydrocarbon fluid.

A component and a system for mitigating coke formation during delivery of a hydrocarbon fluid. The component includes a contact surface configured to be in contact with the hydrocarbon fluid. Tuning the zeta potential of the contact surface allows selective attraction and/or repulsion of coke-catalyzing materials, metal ions, heteroatomic hydrocarbons, and/or coke precursors present in the hydrocarbon fluid. A method of mitigating coke formation during delivery of a hydrocarbon fluid includes tuning a zeta potential of the contact surface of the component and injecting or circulating the hydrocarbon fluid through the system such that the contact surface selectively attracts and/or repels coke-catalyzing materials, metal ions, heteroatomic hydrocarbons, and/or coke precursors present in the hydrocarbon fluid.

Method for optimizing the limitation of dust emissions from a gas turbine or combustion plant comprising a line for supplying liquid fuel oil, a line for generating fuel oil atomizing air, and a central controller, wherein: a first definition step, starting from a nominal temperature of the fuel oil and a nominal pressure ratio of the atomizing air of the fuel oil, and by controlling the injection of the soot inhibitor, of a nominal operating point corresponding to the maximum permissible level of emitted dust; a second step of controlling a first parameter, taken from the group of the fuel oil temperature and the pressure ratio of the fuel oil atomizing air, in order to reach another operating point; and a third step of controlling the soot inhibitor injection to achieve the maximum permissible level of emitted dust.

Method for optimizing the limitation of dust emissions from a gas turbine or combustion plant comprising a line for supplying liquid fuel oil, a line for generating fuel oil atomizing air, and a central controller, wherein: a first definition step, starting from a nominal temperature of the fuel oil and a nominal pressure ratio of the atomizing air of the fuel oil, and by controlling the injection of the soot inhibitor, of a nominal operating point corresponding to the maximum permissible level of emitted dust; a second step of controlling a first parameter, taken from the group of the fuel oil temperature and the pressure ratio of the fuel oil atomizing air, in order to reach another operating point; and a third step of controlling the soot inhibitor injection to achieve the maximum permissible level of emitted dust.

A combustion device burns fuel ammonia with combustion air in a combustion chamber, and includes: a combustor liner which forms the combustion chamber; a burner which is installed at one end of the combustor liner; a deflection member which is provided on a downstream side of the combustor liner in a flow direction of a combustion gas, and is configured to deflect the flow direction of the combustion gas; and at least one ammonia injection hole which is provided between the burner and an outlet of the deflection member and is configured to supply the fuel ammonia into the combustion chamber.

A combustion device burns fuel ammonia with combustion air in a combustion chamber, and includes: a combustor liner which forms the combustion chamber; a burner which is installed at one end of the combustor liner; a deflection member which is provided on a downstream side of the combustor liner in a flow direction of a combustion gas, and is configured to deflect the flow direction of the combustion gas; and at least one ammonia injection hole which is provided between the burner and an outlet of the deflection member and is configured to supply the fuel ammonia into the combustion chamber.

A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.

A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.

A fuel system can include a first fuel circuit, a second fuel circuit, and an inert gas purge system operatively connected to both the first fuel circuit and the second fuel circuit to purge at least a portion of either or both of the first and/or second fuel circuit. The first fuel can be a liquid fuel and the second fuel can be a gaseous fuel. The first fuel circuit can include a first fuel manifold configured to fluidly communicate a first fuel supply with at least one dual fuel nozzles downstream of the first fuel manifold.

A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.