System For Reducing Combustion Noise And Improving Cooling

A cooling system for a gas turbine comprising:

• a flow sleeve comprising:
• a tubular portion having a tubular inlet and a tubular outlet;
• a conical portion having a conical inlet and a conical outlet, the conical portion connected to the tubular portion at the tubular outlet;
• a plurality of rows of cooling holes, each row extending about the perimeter of the flow sleeve;
• an aft ring located about the conical outlet and having a receptacle;
• and
• a piston ring positioned within the receptacle;
• a combustion liner comprising a generally tubular body and extending through the flow sleeve thereby forming a cooling passage therebetween, the combustion liner having a liner inlet and a liner outlet;
• and
• a transition duct coupled to the liner outlet, the transition duct receiving hot combustion gases from the combustion liner, the transition duct having an outer wall transitioning from a generally circular duct inlet to a generally rectangular duct outlet;
• wherein the piston ring of the flow sleeve creates a seal between the flow sleeve and the transition duct, thereby preventing compressor air from entering a passageway formed between the flow sleeve and the combustion liner, and instead directing the compressed air to enter the passageway through the plurality of rows of cooling holes.

A sealing device for an aft end of a gas turbine combustor comprising:

• an axially-extending sleeve having a conical portion;
• an aft ring with a U-shaped receptacle at an outlet end of the conical portion;
• and
• a piston ring located in the U-shaped receptacle, the piston ring capable of expanding or contracting in diameter upon placement of an inlet end of a transition duct into the outlet end of the conical portion;
• wherein a seal is formed between the piston ring and the transition duct, thereby preventing air from entering a combustor through a gap between the sleeve and the transition duct.