Abstract: A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20) with inner and outer endwalls (14, 16) that are coupled together with a first radially outer tie bar (22). In at least one embodiment, first and second radially outer tie bars (22, 24) may form first and second stator vane segments (26, 28) that together form the circumferentially extending stator assembly (10). The inner and outer endwalls (14, 16) may be coupled together with one or more circumferentially extending alignment pins (30) that limit deflection. The stator assembly (10) may include one more deformable seals (52) extending radially inward from the inner endwall (14).

Abstract: A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered.

Abstract: A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20) with inner and outer endwalls (14, 16) that are coupled together with a first radially outer tie bar (22). In at least one embodiment, first and second radially outer tie bars (22, 24) may form first and second stator vane segments (26, 28) that together form the circumferentially extending stator assembly (10). The inner and outer endwalls (14, 16) may be coupled together with one or more circumferentially extending alignment pins (30) that limit deflection. The stator assembly (10) may include one more deformable seals (52) extending radially inward from the inner endwall (14).

Abstract: A stator vane segment (10) including a connection system (12) that enables stator vane (14) alignment while enabling an individual stator vane (14) to be replaced is disclosed. The stator vane connection system (12) may include a radially extending inner support (26) extending from a stator vane (14), whereby the inner support (26) is secured to forward and aft inner rings via a removable, inner axial bolt (22). The stator vane connection system (12) may include one or more first inner pins (24) that aligns the stator vane (14) and is positioned within the portion of the inner support (26) of the stator vane (14) to which one or more inner axial bolts (22) are attached. The stator vane connection system (12) may include one or more first outer alignment pins (28) that aligns the stator vane (14) and is positioned within a portion of the outer diameter platform (48) of the stator vane (14), whereby the first outer alignment pin (28) aligns the stator vane (14).

Abstract: A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered.

Abstract: Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.