A gas turbine nozzle segment (10) has outer and inner bands (12, 14) and vanes (16) therebetween. Each band includes a side wall (40), a cover (20) and an impingement plate (22) between the cover and nozzle wall defining two cavities (24, 26) on opposite s...

A transition duct assembly (26, 28) for a gas turbine includes a transition duct (28) having opposite ends, one of the ends adapted to communicate with an inlet (14) to a first turbine stage; an impingement cooling sleeve surrounding the transition duct (2...

A nozzle vane segment includes outer (12) and inner band portions with a vane extending therebetween and defining first and second cavities (26, 28) separated by an impingement plate (22) for flowing cooling medium for impingement cooling of nozzle side wa...

A system and method are provided for controlling cooling air flow for pressure modulation of turbine components, such as the turbine outer sidewall cavities. The pressure at which cooling and purge air is supplied to the turbine outer side wall cavities is...

A double wall bearing cone closes an opening between a bearing housing and an exhaust frame in a gas turbine. The bearing cone includes a conical forward plate (14) having an inner diameter and an outer diameter and a conical aft plate (12) nested with and...