|
WO2020092896A1
|
|
System and method for providing compressed air to a gas turbine combustor
|
|
WO2020092916A1
|
|
Turbulator geometry for a combustion liner
|
|
WO2020106431A2
|
|
Diffuser guide vane
|
|
WO2020092234A1
|
|
Method and apparatus for improving cooling of a turbine shroud
|
|
US2020003654A1
|
|
Systems and methods for modal testing of turbine blades
|
|
US2020360985A1
|
|
Core pattern reformer tool
|
|
US2020216932A1
|
|
Nickel-base alloy for gas turbine components
|
|
US2020198180A1
|
|
Method and apparatus for improving core manufacturing for gas turbine components
|
|
US2020141250A1
|
|
Diffuser guide vane
|
|
US2020141584A1
|
|
Cross fire tube retention system
|
|
US2020141585A1
|
|
Axial stop configuration for a combustion liner
|
|
US2020141251A1
|
|
Method and apparatus for mounting a transition duct in a gas turbine engine
|
|
US2020141576A1
|
|
Turbulator geometry for a combustion liner
|
|
US2020141252A1
|
|
System and method for providing compressed air to a gas turbine combustor
|
|
US2020131915A1
|
|
Method and apparatus for improving turbine blade sealing in a gas turbine engine
|
|
US2020131913A1
|
|
Method and apparatus for improving cooling of a turbine shroud
|
|
US2020063565A1
|
|
First stage turbine blade
|
|
US2020063570A1
|
|
Second stage turbine blade
|
|
US2020063579A1
|
|
First stage turbine nozzle
|
|
US2020063580A1
|
|
Second stage turbine nozzle
|
