US2013276451A1
|
|
Combustion system including a transition piece and method of forming using a cast superalloy
|
US2013167543A1
|
|
Methods and systems for cooling a transition nozzle
|
US2013086914A1
|
|
Turbine system
|
US2012324898A1
|
|
Combustor assembly for use in a turbine engine and methods of assembling same
|
US2012328421A1
|
|
Methods and systems for cooling a transition nozzle
|
US2012324897A1
|
|
Methods and systems for transferring heat from a transition nozzle
|
US2011304104A1
|
|
Spring loaded seal assembly for turbines
|
US2011247341A1
|
|
Combustor liner helical cooling apparatus
|
US2011239652A1
|
|
Segmented annular ring-manifold quaternary fuel distributor
|
US2011217159A1
|
|
Preferential cooling of gas turbine nozzles
|
US2010287943A1
|
|
Methods and systems for inducing combustion dynamics
|
US2010236249A1
|
|
Systems and methods for reintroducing gas turbine combustion bypass flow
|
US2010058766A1
|
|
Segmented combustor cap
|