Abstract: Aspects of the invention relate to a system for attaching a fuel swirler assembly in a turbine engine combustor. According to embodiments of the invention, at least an axial upstream end of the fuel swirler assembly can be attached to a combustor support frame using one or more fasteners, such as bolts. The fuel swirler assembly can include a radial bracket provided on the swirler body to facilitate attachment. The axial downstream end of the fuel swirler assembly can be positioned within an opening defined in a swirler base plate or within an opening in a swirler support plate. Aspects of the invention can reduce the time and cost associated with installation and replacement of fuel swirlers in a combustor while avoiding concerns associated with known welded pin attachment systems.

Abstract: A barrier structure (302) blocks exit of spring clip fragments (317) that may break off from a spring clip assembly disposed between a gas turbine engine combustor (300) and a transition piece component (360). The barrier structure (302) may additionally comprise an aspect (326) effective to restrict a spring clip's (310, 311) radially inward compression, thereby reducing or eliminating damage to the spring clip (310, 311) during shipping and handling. The barrier structure (302) additionally may comprise an aspect (330) to restrict access by a human hand to the free ends (318) of the spring clips (310, 311). This aspect (330) reduces or eliminates the undesired lifting of the compressor by grabbing the spring clips (310, 311) during combustor transport, installation or removal. Accordingly, barrier structure embodiments are provided that reduce stress on spring clips, and that prevent the exit of spring clips from a containment space partly formed by the barrier structure.

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal is composed of inner and outer housings and a center sealing member disposed between the inner and outer housings. The center sealing member is flexible and prevents a fluid, such as air, from leaking through the seal. In operation, the center sealing member flexes and is sealed against the outer housing by a pressure differential that is created by the relatively higher pressure on the inner housing side and the relatively lower pressure on the outer housing side.

Abstract: A support member for removably supporting a swirler on a basket frame of a combustion gas turbine engine includes a plug removably mounted on the basket frame and a pin fixedly mounted on the swirler. A mechanical lock detachably connects the plug and the pin with one another, and the mechanical lock may include cooperating threads or other appropriate structures. The swirler is removed from the basket frame by detaching the plug from the basket frame, disconnecting the plug from the pin, and sliding the swirler longitudinally along its own axis whereby the pin clears the mounting hole within which the plug was mounted.

Abstract: A fuel filtering apparatus for use in a gas turbine fuel system is provided. The fuel filtering apparatus includes a removable filter housing which receives and maintains a filter element therein to filter a fuel flow when the filter housing is positioned on the apparatus. The fuel filtering apparatus is also provided with a casing which is installed in-line in a portion of the fuel system. The removable filter housing alleviates the need for removal of the casing when a filter element is inserted and removed for cleaning and other routine maintenance. The fuel filtering apparatus also reduces pressure disruption within the fuel system.

Abstract: A combustion system has a diffusion flame pilot assembly and a steam delivery assembly. The diffusion flame pilot assembly has a fuel line with a downstream end terminating at a pilot nozzle. The steam delivery assembly has a steam line terminating at a steam outlet proximate to said fuel line and upstream of said pilot nozzle for directing steam to the pilot nozzle. An aspect of the invention has a steam throttle valve for adjusting the steam flow to the pilot nozzle based on the combustion system's NO.sub.X emissions and/or characteristics of said pilot fuel stream.

Abstract: A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle.