Turbine blade with counter flowing near wall cooling channels
View Patent ↗A turbine rotor blade with counter flowing near wall cooling channels that includes an outer spanwise flowing near wall cooling channel and an inner chordwise flowing near wall cooling channel connected in series and with an arrangement of pedestals to produce turbulent flow. Cooling air form the spanwise flow channels flows through a blade tip floor cooling channel and then into a collection cavity, and then through impingement cooling holes in the leading edge region and into the chordwise channels before discharging out exit holes on both sides of the blade. An arrangement of pedestals forms 90 degree flow paths through the near wall cooling channels.
1. An air cooled turbine rotor blade comprising:
an inner wall forming a cooling air collection cavity;
an outer wall forming an airfoil surface;
a middle wall forming an outer near wall cooling channel and an inner near wall cooling channel;
a plurality of pedestals extending in the outer near wall cooling channel and the inner near wall cooling channel to form a criss-cross flow path;
a cooling air supply cavity formed in a blade root and connected to the outer near wall cooling channel;
a blade tip floor cooling channel to connected the outer near wall cooling channel to the cooling air collection cavity; and,
a row of exit holes on a pressure side and a suction side connected to the inner near wall cooling channel to discharge cooling air from the blade.
2. The air cooled turbine rotor blade of claim 1 , and further comprising:
the outer near wall cooling channel is a spanwise direction flowing near wall cooling channel; and,
the inner near wall cooling channel is a chordwise direction flowing near wall cooling channel.
3. The air cooled turbine rotor blade of claim 1 , and further comprising:
the outer and inner near wall cooling channels are connected in a series flow through the blade.
4. The air cooled turbine rotor blade of claim 1 , and further comprising:
a thickness of the outer wall is in a range from 0.010 inches to 0.020 inches.
5. The air cooled turbine rotor blade of claim 1 , and further comprising:
a row of impingement cooling holes connecting the cooling air collection cavity to the inner near wall cooling channel to produce impingement cooling for the leading edge of the blade.
6. The air cooled turbine rotor blade of claim 1 , and further comprising:
the pedestals are square shaped pedestals and form 90 degree flow paths within the channel.
7. The air cooled turbine rotor blade of claim 4 , and further comprising:
the inner wall is twice a thickness of the outer wall.
8. A process for near wall cooling of a turbine rotor blade, comprising the steps of:
supplying cooling air to a root section of the blade;
passing cooling air in a spanwise direction of the blade to produce near wall cooling of outer surfaces of the blade on the pressure side wall and the suction side wall;
passing the cooling air from the outer surfaces of the blade along a blade tip floor to cool the blade tip floor of the blade;
discharging the cooling air from the blade tip floor into a collection cavity formed within an inner wall of the blade;
impinging the cooling air from the collection cavity against a backside surface of the leading edge of the airfoil to produce impingement cooling;
passing the impingement cooling air along an inner channel of the blade in a chordwise direction to heat up the inner wall of the blade; and,
discharging the chordwise flowing cooling air out from the blade on the pressure side and the suction side in the trailing edge region of the blade.
9. The process for near wall cooling of a turbine rotor blade of claim 8 , and further comprising the steps of:
producing a turbulent flow of the cooling air within the spanwise cooling air flow; and,
producing a turbulent flow of the cooling air within the chordwise cooling air flow.