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

1. An air inlet duct for a compressor of a gas or fuel oil turbine, comprising:

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.

2. The inlet duct according to claim 1 , in which one section of the sections is disposed upstream of the other section of the sections relative to the direction of said flow of air inside the inlet duct.

3. The inlet duct according to claim 1 , in which the structure and said sections are configured to form a completely empty space between said sections when the structure is disposed outside the air passage duct.

4. The inlet duct according to claim 1 , in which the first element is able, after the spacer is positioned outside the air passage duct, to be moved in a first movement direction and then a second movement direction to detach the first element from the first section to which it is fixed.

5. The air inlet duct according to claim 4 , in which the air passage duct defines the direction of said flow of air through the inlet duct, the first movement direction extending substantially along the direction of said flow of air and the second movement direction extending substantially transversely relative to the direction of said flow of air.

6. The air inlet duct according to claim 4 , further comprising removable guide means adapted to be inserted in the at least partly empty space formed by the second element to guide the first element in the first movement direction and/or the second movement direction.

7. The inlet duct according to claim 1 , in which one of said sections comprises:

a hollow body enabling the flow of air to pass through it;

retaining means forming a projection extending out of the hollow body;

a support configured to cooperate with the retaining means to transmit a load from the one of said sections to the ground.

8. The inlet duct according to claim 7 , in which the support is a gas turbine protection thermo-acoustic enclosure, or a portion of a structure of a building in which the gas turbine and the inlet duct are placed, or a framework.

9. 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.

10. The maintenance method according to claim 9 , further comprising, before the step of moving the first element, a step including installing guide means in the at least partly empty space left by the spacer, the frame being moved in the second movement direction in contact with the guide means.

11. The maintenance method according to claim 9 , further comprising a step of replacing the at least one nozzle when the frame is positioned outside the air passage duct.

12. 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.