Abstract: A tool kit for decoupling a telescoping tube from a first liner of a gas turbine engine is disclosed. The tool kit includes a base plate coupled to a combustor casing. A post extends outward from the base plate into a combustion chamber defined by the liner. A plunger slidably mounts to the post and is slidable between an extended position and a retracted position. A lever arm pivotably couples to the post and the plunger. Pivoting the lever arm in a first direction slides the plunger to the extended position to decouple the telescoping tube from the liner. A retaining clip couples to the combustor casing and extends into an annular plenum at least partially defined between the liner and the combustor casing. The retaining clip defines a notch that receives the telescoping tube after the plunger assembly decouples the telescoping tube from the liner.

Abstract: A tool kit for decoupling a telescoping tube from a first liner of a gas turbine engine is disclosed. The tool kit includes a base plate coupled to a combustor casing. A post extends outward from the base plate into a combustion chamber defined by the liner. A plunger slidably mounts to the post and is slidable between an extended position and a retracted position. A lever arm pivotably couples to the post and the plunger. Pivoting the lever arm in a first direction slides the plunger to the extended position to decouple the telescoping tube from the liner. A retaining clip couples to the combustor casing and extends into an annular plenum at least partially defined between the liner and the combustor casing. The retaining clip defines a notch that receives the telescoping tube after the plunger assembly decouples the telescoping tube from the liner.

Abstract: The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover. The fuel nozzle may include a pilot system in communication with the end cover passage.

Abstract: A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as O2 and O2 mixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor. The aerodynamic peg includes a first passage configured to convey a first fluid into the gas turbine combustor and a second passage configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.

Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.

Abstract: The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover. The fuel nozzle may include a pilot system in communication with the end cover passage.

Abstract: A system for vibration damping a fuel nozzle within a combustor includes a support plate, a fuel nozzle passage that extends through the support plate and a cylindrical damping insert that is coaxially aligned within the fuel nozzle passage and at least partially defines the fuel nozzle passage. The damping insert may include a metallic-mesh liner.

Abstract: A seal test fixture for a gas turbine fuel nozzle including an enclosed container for receiving a body of the gas turbine fuel nozzle including a seal; a test chamber coupled to the enclosed container for sealingly enclosing a flange of the gas turbine fuel nozzle and fluidly communicating with a leak path of the gas turbine fuel nozzle; an air injector opening through which pressurized air is injected into a main fuel chamber of the gas turbine fuel nozzle; and a pressure gauge for measuring an air pressure within the test chamber.

Abstract: A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber.

Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.

Abstract: A fuel nozzle assembly for use with a combustor is provided. The fuel nozzle assembly includes a fuel nozzle including a discharge end. A cap is coupled adjacent to the nozzle discharge end, wherein the cap includes an outer surface. At least one dampener mechanism is coupled to the cap outer surface to facilitate reducing vibrations induced to the fuel nozzle.

Abstract: A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casing includes an extruded fluid manifold mounted to the outer surface. The extruded fluid manifold includes first and second walls integrally formed with a third, connecting, wall. The first wall includes a first mounting element and the second wall includes a second mounting element. The first mounting element extends axially along the combustor casing away from the first wall and the second mounting element extends axially along the combustor casing away from the second wall and the first mounting element. The extruded fluid manifold is joined to the outer surface of the combustor casing through the first and second mounting elements.

Abstract: A forward casing used in a combustor assembly for a turbine engine includes a circumferential sloped surface which reduces the total interior volume within the forward casing. The circumferential sloped surface can be flat or concave shaped.

Abstract: A combustor includes an end cover and a casing adjacent to the end cover, wherein the end cover and casing at least partially define a volume inside the combustor. The combustor further includes an end cap that extends radially across at least a portion of the combustor, at least one nozzle arranged in the end cap to provide fluid communication through the end cap, and means for conditioning flow through the volume. A method for conditioning flow through a combustor includes flowing a working fluid through a volume at least partially defined by an end cover, a casing, and an end cap that extends radially across at least a portion of the combustor and flowing the working fluid across an annular insert adjacent to the end cover.

Abstract: A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casing includes an extruded fluid manifold mounted to the outer surface. The extruded fluid manifold includes first and second walls integrally formed with a third, connecting, wall. The first wall includes a first mounting element and the second wall includes a second mounting element. The first mounting element extends axially along the combustor casing away from the first wall and the second mounting element extends axially along the combustor casing away from the second wall and the first mounting element. The extruded fluid manifold is joined to the outer surface of the combustor casing through the first and second mounting elements.