Abstract: A hose connection system for connecting a hose to a gas turbine engine. The hose connection system may include a connection fitting and a connection tool. The connection fitting may include a first member to be attached to the gas turbine engine, a mating component to be attached to the hose, and a splined second member to be torqued onto the first member. The connection tool may include a drive wheel with a number of drive wheel splines such that the drive wheel splines torque the splined second member onto the first member.

Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.

Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first portion that is axially offset from the first inner seal and the second inner seal and a second portion abutting the first inner seal and the second inner seal. Also disclosed is an aft frame having a forward face and an aft face. The aft frame includes at least one side seal slot that extends along a side portion. A first portion of the side seal slot is axially offset from the aft face. A second portion of the side seal slot is axially and radially offset from the first portion.

Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.

Abstract: The present application thus provides a hose connection system for connecting a hose to a gas turbine engine. The hose connection system may include a connection fitting and a connection tool. The connection fitting may include a first member to be attached to the gas turbine engine, a mating component to be attached to the hose, and a splined second member to be torqued onto the first member. The connection tool may include a drive wheel with a number of drive wheel splines such that the drive wheel splines torque the splined second member onto the first member.

Abstract: A crossfire tube assembly is positioned between adjacent combustors, the crossfire tube assembly having a primary body made up of a first telescoping sleeve slidably engaged with a second telescoping sleeve. An interlocking raceway is configured to limit axial travel length of the telescoping sleeves and lock the telescoping sleeves to each other. A bias is positioned between the first telescoping sleeve and the second telescoping sleeve. First and second floating collars are removably disposed to the first and second telescoping sleeves at a first and second floating collar annulus. First and second liner collars are disposed between the first and second floating collars on the first and second combustors. The crossfire tube assembly is adapted to provide fluid communication from the first combustor to the second combustor serving a gas turbine.

Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.

Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.

Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.

Abstract: A crossfire tube assembly is positioned between adjacent combustors, the crossfire tube assembly having a primary body made up of a first telescoping sleeve slidably engaged with a second telescoping sleeve. An interlocking raceway is configured to limit axial travel length of the telescoping sleeves and lock the telescoping sleeves to each other. A bias is positioned between the first telescoping sleeve and the second telescoping sleeve. First and second floating collars are removably disposed to the first and second telescoping sleeves at a first and second floating collar annulus. First and second liner collars are disposed between the first and second floating collars on the first and second combustors. The crossfire tube assembly is adapted to provide fluid communication from the first combustor to the second combustor serving a gas turbine.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first portion that is axially offset from the first inner seal and the second inner seal and a second portion abutting the first inner seal and the second inner seal. Also disclosed is an aft frame having a forward face and an aft face. The aft frame includes at least one side seal slot that extends along a side portion. A first portion of the side seal slot is axially offset from the aft face. A second portion of the side seal slot is axially and radially offset from the first portion.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. At least one shroud is secured to the baffle plate and includes at least one piston ring disposed at the shroud. The at least one piston ring is configured to meter a flow of diluent between the at least one shroud and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a piston ring gap defined by at least one piston ring disposed at a baffle plate and a fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the piston ring gap toward at least one airflow hole in the fuel nozzle.

Abstract: A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A plurality of injection holes extend through the at least one fuel nozzle and are configured to meter a flow of diluent into the combustor. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings located at at least one fuel nozzle extending through a through hole in a baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle.

Abstract: A gas turbine includes a combustor liner having at least one hole formed therein. The gas turbine also includes a flow sleeve that at least partially surrounds the liner thereby forming a plenum between the flow sleeve and the liner, the plenum having an airflow therethrough, a portion of the airflow passing through the at least one hole in the liner and into the liner thereby reducing the mass of the airflow in the plenum. The flow sleeve has an axial profile that is reduced in cross section dimension at a predetermined axial location of the flow sleeve, thereby reducing a width of the plenum at the predetermined axial location. The reduction at the cross section dimension in the flow sleeve increases a velocity of the airflow in the plenum at the predetermined axial location, the increased velocity airflow increasing transfer of heat away from the liner.

Abstract: A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone.

Abstract: A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone.