Abstract: A heat shield assembly for use in a turbine engine frame includes inner and outer flowpath liners for shielding the inner and outer turbine frame members from hot exhaust gasses flowing through the turbine engine. The flowpath liners are supported on the turbine frame members with a support structure which allows the flowpath liners to freely expand and contract under thermally induced forces. In this manner thermal stresses are minimized. The flowpath liner support structure also provides uniform support for the flowpath liners and allows for the even and unobstructed flow of cooling air through the flowpath liners.

Abstract: The invention comprises a mounting assembly for supporting the turbine outer casing duct adjacent to the turbine frame. Multiple support posts are mounted to the turbine frame and a roller means is rotatably attached to each support post. The roller means are aligned to rotate on a contact surface of the outer casing duct. Movement of the rollers on the contact surface is caused by the relative movement of the turbine frame and outer casing duct.

Abstract: A combustion liner for a gas turbine combustion apparatus has a wall of circular cross-section defining a primary air entrance at its upstream end, providing means for introduction of fuel near the upstream end, having a convergent-divergent fuel prevaporization zone, a reaction zone, and a dilution zone.The primary air entrance has two coaxial entrance portions separated by an annular intermediate wall disposed around a centerbody. Swirlers in the two entrance portions swirl the air with different degrees of swirl, which provides shear between the two layers downstream of the swirlers. Fuel is introduced onto the intermediate or outer wall, or both, upstream of the throat. Air is admitted through the centerbody and directed towards the throat at higher fuel flow rates, but is shut off by a valve plug at low fuel flow rates to promote recirculation and thus improve flame stability under such conditions. The valve responds to fuel and combustion air pressure.

Abstract: A combustion liner for a gas turbine combustion apparatus has a wall of circular cross-section defining a primary air entrance at its upstream end, providing means for introduction of fuel near the upstream end, having a convergent-divergent fuel prevaporization zone, a reaction zone, and a dilution zone.The primary air entrance has two coaxial entrance portions separated by an annular intermediate wall disposed around a centerbody. Swirlers in the two entrance portions swirl the air with different degrees of swirl, which provides shear between the two layers downstream of the swirlers. Fuel is introduced onto the intermediate or outer wall, or both, upstream of the throat. Air is admitted through the centerbody and directed towards the throat at higher fuel flow rates, but is shut off by a valve plug at low fuel flow rates to promote recirculation and thus improve flame stability under such conditions. The valve responds to fuel and combustion air pressure.