Abstract: An outer crossfire tube for attachment between adjacent combustors in a land-based gas turbine includes a substantially cylindrical bellows portion and a pair of uniform diameter free ends on opposite sides of the bellows portion, the uniform diameter free ends adapted to seat within apertures provided in the adjacent combustors. The outer crossfire tube is surrounded by a telescoping sleeve assembly, with remote ends of a pair of telescoping sleeve members fixed to respective combustor flanges.

Abstract: An outer crossfire tube for attachment between adjacent combustors in a land-based gas turbine includes a substantially cylindrical bellows portion and a pair of uniform diameter free ends on opposite sides of the bellows portion, the uniform diameter free ends adapted to seat within apertures provided in the adjacent combustors. The outer crossfire tube is surrounded by a telescoping sleeve assembly, with remote ends of a pair of telescoping sleeve members fixed to respective combustor flanges.

Abstract: A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

Abstract: A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

Abstract: A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

Abstract: A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

Abstract: Dilution sleeves are provided in radially aligned openings in the combustion liner and flow sleeve of a combustor for a gas turbine. The sleeves have a flange for seating on a collar of the flow sleeve about the opening therethrough enabling the dilution sleeve to extend through the aligned openings. A cover is removably mounted on the outer casing and a spring bears between the cover and the dilution sleeve flange to maintain the dilution sleeve in the openings. Dilution sleeves having different cross-sectional flow areas may be provided in lieu of initially installed dilution sleeves upon comparing measured emission levels with desired emission levels and ascertaining the desired increase or decrease in cross-sectional flow area through the dilution sleeves.