Turbomachine rotor blade
AssigneeGeneral Electric Company
InventorRobert Alan Brittingham
Life of this patent
Estimating the term…
Abstract
The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a first cooling channel and a second cooling channel. The first cooling channel is radially spaced apart from the second cooling channel. Coolant flows in a first direction through the first cooling channel and in a second direction through the second cooling channel. The first direction is different than the second direction.
Claims18
A rotor blade for a turbomachine, the rotor blade comprising:
- an airfoil defining a cooling passage;
- and
- a tip shroud coupled to the airfoil, the tip shroud including a radially outer wall, the tip shroud and the airfoil defining a cooling core in fluid communication with the cooling passage, the cooling core including a first cooling channel and a second cooling channel, the first cooling channel being radially spaced apart from the second cooling channel, the tip shroud further including a first interior wall positioned within the cooling core and extending radially inward from the radially outer wall and a second interior wall positioned within the cooling core and coupled to the first interior wall such that the radially outer wall, the first interior wall, and the second interior wall at least partially define the second cooling channel,
- wherein coolant flows in a first direction through the first cooling channel before flowing in a second direction through the second cooling channel, the first direction being different than the second direction.
A turbomachine, comprising:
- a turbine section including one or more rotor blades, each rotor blade including:
- an airfoil defining a cooling passage;
- and
- a tip shroud coupled to the airfoil, the tip shroud including a radially outer wall, the tip shroud and the airfoil defining a cooling core in fluid communication with the cooling passage, the cooling core including a first cooling channel and a second cooling channel, the first cooling channel being radially spaced apart from the second cooling channel, the tip shroud further including a first interior wall positioned within the cooling core and extending radially inward from the radially outer wall and a second interior wall positioned within the cooling core and coupled to the first interior wall such that the radially outer wall, the first interior wall, and the second interior wall at least partially define the second cooling channel,
- wherein coolant flows in a first direction through the first cooling channel before flowing in a second direction through the second cooling channel, the first direction being different than the second direction.
Dependencies are inferred from the claim text.