Abstract: A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

Abstract: A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) including a pilot fuel nozzle is provided. A restraining element (30) is arranged in the base support structure (12) to support the pilot fuel nozzle. Restraining element (30) is integrally formed with the base support structure. The restraining element being integrally formed with the base support structure is effective to arrange for an incremental thickness (34) in a portion (39) of a wall (34) interposed between the inner diameter (36) of restraining element (30) and respective proximate edges (40) of a number of pilot bolt holes (32) disposed around the restraining element.

Abstract: A casting method and cast manifold are provided. The method allows configuring conduits, such as conduits in a fuel feed boss and/or a base rocket, which are part of the manifold for removing a ceramic core from the cast without forming extraneous holes in the body of the manifold. Absence of such extraneous holes in turn allows eliminating sealing plugs and welds, which otherwise would be needed for sealing the extraneous holes.

Abstract: A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) in a combustor of a gas turbine engine is provided. The fuel manifold includes stage fuel galleries (16, 18), and fuel feed bosses (20, 22) may be configured to connect to respective tubes arranged to deliver gas fuel to the stage fuel galleries (16. 18). Fuel feed bosses (20, 22) are integrally formed with base support structure (12) and this allows the body of fuel manifold (10) to be free of weld joints for affixing the fuel feed boss to the base support structure.

Abstract: Casting method and cast manifold are provided. The method allows configuring conduits, such as conduits (46, 48) in a fuel feed boss (20) and/or a base rocket (13), which are part of the manifold for removing a ceramic core (44) from the cast without forming extraneous holes in the body of the manifold. Absence of such extraneous holes in turn allows eliminating sealing plugs and welds, which otherwise would be needed for sealing the extraneous holes.

Abstract: A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) including a pilot fuel nozzle is provided. A restraining element (30) is arranged in the base support structure (12) to support the pilot fuel nozzle. Restraining element (30) is integrally formed with the base support structure. The restraining element being integrally formed with the base support structure is effective to arrange for an incremental thickness (34) in a portion (39) of a wall (34) interposed between the inner diameter (36) of restraining element (30) and respective proximate edges (40) of a number of pilot bolt holes (32) disposed around the restraining element.

Abstract: A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

Abstract: A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position. While in the first position, the second seal member is circumferentially spaced from the outlet portion of the second transition duct. While in the second position, the second seal member extends across the leakage gap and creates a seal with the outlet portion of the second transition duct to substantially prevent leakage through the leakage gap.

Abstract: An emissions control system (10) for a gas turbine engine (12) for reducing CO emissions at partial load of the gas turbine engine (12) is disclosed. In at least one embodiment, the emissions control system (10) may be formed from one or more compressed air exhausts (14) for exhausting compressed air into a hot gas pathway contained within a channel (18) formed by a transition (20) extending from a combustor (22) to a turbine assembly (24). In at least one embodiment, a plurality of seals (26) may extend circumferentially around the transition (20) providing a seal (26) between the transition (20) and a component of a downstream turbine assembly (24). One or more compressed air exhausts (14) may be positioned between adjacent seals (26). The compressed air exhausts (14) may be, but are not limited to being, channels (30), orifices (34) and metered spaces (32) having various shapes and configurations.

Abstract: A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position. While in the first position, the second seal member is circumferentially spaced from the outlet portion of the second transition duct. While in the second position, the second seal member extends across the leakage gap and creates a seal with the outlet portion of the second transition duct to substantially prevent leakage through the leakage gap.