Intake duct for a gas-fuelled or diesel-fuelled turbine equipped with a water saturation structure

A method of maintaining a structure of an inlet duct, the inlet duct including:

• two separate transition sections in fluid communication with one another for communication of a flow of air through said sections, each of said sections being self-supporting,
• a structure for injecting a mist of liquid particles, configured to be disposed between said sections and in contact with said sections, the structure being removable by sliding perpendicularly from between said sections relative to a direction of said flow of air, independently of demounting said sections,
• wherein said sections define an air passage duct of the inlet duct, the structure and said sections being configured to form an at least partly empty space between said sections when at least a part of the structure is disposed outside the air passage duct,
• wherein said structure comprises first and second elements disposed transversely relative to the air passage duct, the first element comprising means for injecting the mist of liquid particles and being configured to be fixed to a first of said sections, the second element being configured to be fixed on the one hand to the first element and on the other hand to a second of said sections, and in which the first and second elements are configured to form said at least partly empty space between the first element and said second of said sections when the second element is disposed outside the air passage duct,
• wherein said means for injecting the mist of liquid particles of the first element includes a frame, at least one injection nozzle fixed to the frame to generate the mist of liquid particles in the inlet duct and at least one pressurized liquid feed pipe each connected to the at least one injection nozzle, and
• wherein the second element is a removable spacer,
• wherein said method comprises the steps of:
• removing the second element so as to leave the at least partly empty space between the first element and said second section,
• moving the first element in a first movement direction so as to detach the first element from said first section,
• moving the first element in a second movement direction so as to position the first element at least partly outside the air passage duct.

A gas or fuel oil turbine assembly comprising:

• an air inlet duct including:
• two separate transition sections in fluid communication with one another for communication of a flow of air through said sections, each of said sections being self-supporting,
• a structure for injecting a mist of liquid particles, configured to be disposed between said sections and in contact with said sections, the structure being removable by sliding perpendicularly from between said sections relative to a direction of said flow of air, independently of demounting said sections,
• wherein said sections define an air passage duct of the inlet duct, the structure and said sections being configured to form an at least partly empty space between said sections when at least a part of the structure is disposed outside the air passage duct,
• wherein said structure comprises first and second elements disposed transversely relative to the air passage duct, the first element comprising means for injecting the mist of liquid particles and being configured to be fixed to a first of said sections, the second element being configured to be fixed on the one hand to the first element and on the other hand to a second of said sections, and in which the first and second elements are configured to form said at least partly empty space between the first element and said second of said sections when the second element is disposed outside the air passage duct,
• wherein said means for injecting the mist of liquid particles of the first element includes a frame, at least one injection nozzle fixed to the frame to generate the mist of liquid particles in the inlet duct and at least one pressurized liquid feed pipe each connected to the at least one injection nozzle, and
• wherein the second element is a removable spacer,
• said gas or fuel oil turbine assembly further comprises:
• a compressor connected to the air inlet duct to receive the flow of air therefrom,
• a combustion chamber for mixing and burning a fuel and air compressed by the compressor,
• an expansion turbine adapted to be driven in rotation by hot gases from the combustion chamber, and
• an alternator coupled to the expansion turbine to generate electricity.