Coriolis turbulator blade
AssigneeGeneral Electric Company
InventorChing-Pang Lee
Life of this patent
Estimating the term…
Abstract
A method of placing turbulators in a turbine rotor blade includes placing slant turbulators in a radial flow channel offset circumferentially from the blade leading edge. The slant turbulators are all inclined radially inward toward the blade trailing edge for directing coolant along the turbulators co-directionally with Coriolis flow inside the offset channel. In a specific embodiment, turbulator chevrons are also placed in a radial flow channel axially aligned with the blade leading edge consistent with the Coriolis flow therein.
Claims20
A turbine rotor blade comprising:
- pressure and suction sidewalls extending longitudinally in span from root to tip, and extending in chord between leading and trailing edges;
- said sidewalls being spaced laterally apart between said leading and trailing edges, and joined together by chordally spaced apart partitions extending longitudinally between said root and tip to define a flow channel for channeling a coolant therethrough;
- and
- said blade having twist to offset laterally said channel from said leading edge toward said trailing edge, and said channel having a row of slant turbulators spaced apart longitudinally and all inclined inward toward said root and trailing edge for directing said coolant along said turbulators co-directionally with Coriolis flow inside said channel.
A method of placing turbulators in a turbine rotor blade having internal radial flow channels bounded circumferentially by pressure and suction sidewalls and axially by partitions extending therebetween, with said blade having twist to circumferentially offset a trailing edge of said blade from a leading edge thereof, said method comprising:
- placing turbulator chevrons in one of said channels axially aligned with said leading edge for directing coolant flow along said chevrons co-directionally with Coriolis flow inside said aligned channel;
- and
- placing slant turbulators in one of said channels offset circumferentially from said leading edge toward said trailing edge, and all inclined radially inward toward said trailing edge for directing said coolant along said turbulators co-directionally with Coriolis flow inside said offset channel.
A turbine rotor blade comprising:
- internal radial flow channels bounded circumferentially by pressure and suction sidewalls and axially by partitions extending therebetween, with said blade having twist to circumferentially offset a trailing edge of said blade from a leading edge thereof;
- a row of turbulator chevrons disposed in one of said channels axially aligned with said leading edge for directing coolant flow along said chevrons co-directionally with Coriolis flow inside said aligned channel;
- and
- a row of slant turbulators disposed in one of said channels offset circumferentially from said leading edge toward said trailing edge, and all inclined radially inward toward said trailing edge for directing said coolant along said turbulators co-directionally with Coriolis flow inside said offset channel.
Dependencies are inferred from the claim text.