Abstract: A combustor for an industrial turbine includes a single transition piece transitioning directly from a combustor head-end to a turbine inlet. The transition piece includes an inner surface and an outer surface. The inner surface bounds an interior space for combusted gas flow from the combustor head-end to the turbine inlet. The outer surface at least partially defines an area for compressor discharge air flow. The transition piece includes a plurality of apertures configured to allow compressor discharge air flow into the interior space. Each of the plurality of apertures extends from an entry portion on the outer surface to an exit portion on the inner surface.

Abstract: A method, system, and apparatus is provided for transferring heat from a can combustor associated with a gas turbine by providing a one-piece can combustor body having surface features that facilitate the transfer of heat away from the can combustor body, and by directing air flow to the surface features so that heat from the can combustor body is transferred from the surface features to the air flow.

Abstract: Disclosed is an apparatus for cooling a single-piece duct includes at least one metal wrapper disposed at the transition piece located outboard of the transition piece. At least one support boss is located between the metal wrapper and the transition piece. The support boss, the metal wrapper and transition piece define at least one cooling flow channel for directing flow for cooling the transition piece. A related method of cooling a single-piece duct extending between a forward end of a combustor and a first stage of a turbine includes providing a plurality of flow direction devices radially between the single-piece duct and a metal wrapper extending at least partially around the single-piece duct; flowing cooling air into a space between the single-piece duct and the metal wrapper such that the plurality of flow direction devices guide the cooling air about a surface of the single-piece duct enclosed by the metal wrapper.

Abstract: An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

Abstract: A combustor cap is cooperable with an impingement plate in a turbine fuel nozzle and includes a plurality of cap segments independently securable to the impingement plate. The plurality of cap segments are radially and tangentially movable relative to the impingement plate.

Abstract: A turbine includes a static member, a moveable member fluidly connected to the static member, and a flexible seal. The flexible seal includes a spring component having a base section mounted to one of the static member and the moveable member of the turbine and a plurality of biasing members. Each of the plurality of biasing members includes a first portion extending from the base section and a cantilevered portion. The flexible seal further includes a seal component provided on the cantilevered portion of each of the plurality of biasing members. The seal component is biased into contact with the other of the static member and the moveable member.

Abstract: A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless.

Abstract: A hybrid structure that combines characteristics of the DACRS and Swozzle burners to provide the high mixing ability of an axial flowing counter rotating vane swirler with good dynamic flame stability characteristics of a bluff center body.