| 摘要 |
A combustion turbine subsystem that includes a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, said circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction, and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, the combustion turbine subsystem including an annular array of transition ducts each for routing gas flow from a combustor to the first stage blade array, a first transition duct (94) of the annular array of transition ducts comprising a transition duct body (96) having an internal passage (102) extending between an inlet (98) and an outlet (100), the outlet (100) being offset from the inlet (98) in the longitudinal direction and the tangential direction, the transition duct body (96) having a throat (134) positioned therein having a cross-sectional area that is less than other aspects of the transition duct body (96), wherein an axis (130) of the transition duct body (96) downstream of the throat (134) is generally linear, wherein the outlet (100) is formed from a radially outer side (108) generally opposite to a radially inner side (110), the radially outer and inner sides (108, 110) being coupled together with opposed first and second outlet side walls (112, 114), wherein the first transition duct (94) has an axis (130) that is generally linear, wherein the inlet (98) is generally cylindrical and is adjacent to a conical midsection (132), wherein the conical midsection (132) is positioned between the inlet (98) and the throat (134), wherein the conical midsection (132) includes an ever decreasing cross-sectional area until the conical midsection (132) joins the adjacent throat (134). |
