Abstract: A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.

Abstract: A seal assembly includes a cloth seal for sealing a cavity between a first mating body and a second mating body, the seal dividing the cavity into a high pressure region and a low pressure region. The cloth seal has a shim assemblage and a cloth assemblage. A first peripheral portion of the cloth seal may include a portion of the cloth assemblage and/or the shim assemblage which contacts the high pressure region and a second peripheral portion including a portion of the cloth assemblage adapted to contact the low pressure region. Knowing the flow conditions and pressure differential through the seal, the density of the cloth seal may be calibrated to control leakage and the shim and cloth assemblages may be designed to minimize contact loads on a mating body.

Abstract: Metallic cloth seals backed by stiff high temperature-resistant shims depend from a bracket for engagement in a slot of a transition piece for sealing between the transition piece and a first-stage nozzle. The high pressure acting on the shim forces the metallic cloth into engagement with the sealing surface in the slot. The lower edge of the shim is bent about, and overlies, the edge of the metallic cloth in a direction toward the sealing surface of the slot to choke any flow from the high pressure region past the seal. Elongated spline seals are also inserted into opposed registering slots of adjacent transition pieces. The spline seals comprise metallic cloth folded onto itself backed by elongated stiff high temperature-resistant shims having lateral edges overlying the lateral edges of the cloth material. The overlying edges prevent leakage flow about the spline seals from the high pressure to the low pressure regions.

Abstract: A burner for use in a combustion system of a heavy-duty industrial gas turbine includes a fuel/air premixer having an air inlet, a fuel inlet, and an annular mixing passage. The fuel/air premixer mixes fuel and air into a uniform mixture for injection into a combustor reaction zone. The burner also includes an inlet flow conditioner disposed at the air inlet of the fuel/air premixer for controlling a radial and circumferential distribution of incoming air. The pattern of perforations in the inlet flow conditioner is designed such that a uniform air flow distribution is produced at the swirler inlet annulus in both the radial and circumference directions. The premixer includes a swozzle assembly having a series of preferably air foil shaped turning vanes that impart swirl to the airflow entering via the inlet flow conditioner.

Abstract: A seal assembly includes a cloth seal for sealing a cavity between a first mating body and a second mating body, the seal dividing the cavity into a high pressure region and a low pressure region. The cloth seal has a shim assemblage and a cloth assemblage. A first peripheral portion of the cloth seal may include a portion of the cloth assemblage and/or the shim assemblage which contacts the high pressure region and a second peripheral portion including a portion of the cloth assemblage adapted to contact the low pressure region. Knowing the flow conditions and pressure differential through the seal, the density of the cloth seal may be calibrated to control leakage and the shim and cloth assemblages may be designed to minimize contact loads on a mating body.

Abstract: A burner for use in a combustion system of a heavy-duty industrial gas turbine includes a fuel/air premixer having an air inlet, a fuel inlet, and an annular mixing passage. The fuel/air premixer mixes fuel and air into a uniform mixture for injection into a combustor reaction zone. The burner also includes an inlet flow conditioner disposed at the air inlet of the fuel/air premixer for controlling a radial and circumferential distribution of incoming air. The pattern of perforations in the inlet flow conditioner is designed such that a uniform air flow distribution is produced at the swirler inlet annulus in both the radial and circumference directions. The premixer includes a swozzle assembly having a series of preferably air foil shaped turning vanes that impart swirl to the airflow entering via the inlet flow conditioner.