Abstract: A turbine assembly having an outer casing (36), an inner structural ring (38), and an annular gas path (42) defined between outer and inner flow path walls (44, 46) for conducting a gas flow through the turbine assembly. A plurality of structural struts (52) are spaced apart in a circumferential direction, each strut (52) including a strut body (52a) extending in a radial direction for supporting the inner structural ring (38) to the outer casing (36). A first strut end (64) at a radially outer end of the strut body (52a) is detachably attached to the outer casing (36) with a first fastener structure (68) engaging the outer casing (36), and a second strut end (66) at a radially inner end of the strut body (52a) is detachably attached to the inner structural ring (38) with a second fastener structure (70) engaging the inner structural ring (38).

Abstract: A transition exit frame (10) for supporting a transition (12) extending downstream from a combustor (14) to a turbine assembly (16) in a turbine engine (18) and including one or more transition exit frame inserts (20) configured to reduce thermal distortion created during operation of the turbine engine (18) is disclosed. The transition exit frame (10) may be formed from one or more transition exit frame bodies (22). The transition exit frame body (22) may be formed from a first material (24) having a first coefficient of thermal expansion. The transition exit frame insert (20) may form at least a portion of the transition exit frame body (22). The transition exit frame insert (20) may be formed from a second material (26) having a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion of the first material (24) to reduce distortion within the transition exit frame body (22) during operation of the turbine engine (18).

Abstract: A turbine assembly having an outer casing (36), an inner structural ring (38), and an annular gas path (42) defined between outer and inner flow path walls (44, 46) for conducting a gas flow through the turbine assembly. A plurality of structural struts (52) are spaced apart in a circumferential direction, each strut (52) including a strut body (52a) extending in a radial direction for supporting the inner structural ring (38) to the outer casing (36). A first strut end (64) at a radially outer end of the strut body (52a) is detachably attached to the outer casing (36) with a first fastener structure (68) engaging the outer casing (36), and a second strut end (66) at a radially inner end of the strut body (52a) is detachably attached to the inner structural ring (38) with a second fastener structure (70) engaging the inner structural ring (38).

Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.

Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.

Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.

Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.