Internal cooling system for a turbine blade
View Patent ↗A turbine blade for a turbine engine having a cooling system with at least one serpentine cooling channel in internal aspects of the turbine blade. The serpentine cooling channel includes at least one root turn proximate to a root of the turbine blade. The root turn may have a generally rectangular shape and may account for reduced pressure losses relative to conventional curved root turns. One or more refresh holes may be positioned in a rib proximate to the root turn to provide the root turn with cooling fluids that have bypassed the first and second legs of the serpentine cooling channel.
1. A turbine blade, comprising:
a generally elongated blade having a leading edge, a trailing edge, and a tip at a first end, a root coupled to the blade at an end generally opposite the first end for supporting the blade and for coupling the blade to a disc, at least one cavity forming a cooling system in the blade, and at least one outer wall defining the at least one cavity forming at least a portion of the cooling system;
wherein the cooling system comprises at least one serpentine cooling channel formed from a first leg extending generally from the root towards the tip, a second leg in communication with the first leg and extending towards the root, and a third leg in communication with the second leg through a root turn and extending generally towards the tip; and
at least one refresh hole extending between the first leg and the second leg and positioned proximate to the root turn to direct cooling fluid into the upstream portion of the root turn;
wherein the at least one refresh hole is positioned between about 15 degrees and about 75 degrees relative to a direction of flow of the cooling fluid through the second leg and positioned immediately downstream of a mouth of an upstream portion of the turn.
2. The turbine blade of claim 1 , wherein the at least one refresh hole is positioned at about 45 degrees relative to a direction of flow of the cooling fluid through the second leg.
3. The turbine blade of claim 1 , wherein a cross-sectional area of the second leg proximate to the root turn is greater than the cross-sectional area of the third leg proximate to the root turn.
4. The turbine blade of claim 1 , wherein a cross-sectional area of the second leg proximate to the root turn is equal to the cross-sectional area of the third leg proximate to the root turn.
5. The turbine blade of claim 1 , wherein the at least one refresh hole is located on an upstream side of the root turn.
6. The turbine blade of claim 1 , wherein the at least one refresh hole has a bell mouth inlet section and a straight exit region.
7. The turbine blade of claim 1 , wherein the root turn is formed from a first rib extending from the root spanwise towards the tip and separating the first and second legs, a second rib extending from the root towards the tip and forming a portion of the third leg, and a third rib extending between the first and second ribs.
8. The turbine blade of claim 7 , wherein the third rib is substantially straight.
9. The turbine blade of claim 7 , wherein the third rib extends generally orthogonally to the first and second ribs such that the root turn is generally rectangular in shape.
10. The turbine blade of claim 7 , wherein a spanwise length of the root turn is at least as long as about half of a length of the second leg of the serpentine cooling channel.
11. A turbine blade, comprising:
a generally elongated blade having a leading edge, a trailing edge, and a tip at a first end, a root coupled to the blade at an end generally opposite the first end for supporting the blade and for coupling the blade to a disc, at least one cavity forming a cooling system in the blade, and at least one outer wall defining the at least one cavity forming at least a portion of the cooling system;
wherein the cooling system comprises at least two serpentine cooling channels, each formed from a first leg extending generally from the root towards the tip, a second leg in communication with the first leg and extending towards the root, and a third leg in communication with the second leg through a root turn and extending generally towards the tip;
wherein the root turn is formed from a first rib extending from the root spanwise towards the tip and separating the first and second legs, a second rib extending from the root towards the tip and forming a portion of the third leg, and a substantially straight third rib extending between the first and second ribs; and
at least one refresh hole in each of the at least two serpentine cooling channels extending between the first leg and the second leg and positioned proximate to the root turn to direct cooling fluid into the upstream portion of the root turn;
wherein the at least one refresh hole is positioned between about 15 degrees and about 75 degrees relative to a direction of flow of the cooling fluid through the second leg and positioned immediately downstream of a mouth of an upstream portion of the turn.
12. The turbine blade of claim 11 , wherein the at least one refresh hole is positioned at about 45 degrees relative to a direction of flow of the cooling fluid through the second leg.
13. The turbine blade of claim 11 , wherein a cross-sectional area of the second leg proximate to the root turn is greater than the cross-sectional area of the third leg proximate to the root turn.
14. The turbine blade of claim 11 , wherein a cross-sectional area of the second leg proximate to the root turn is equal to the cross-sectional area of the third leg proximate to the root turn.
15. The turbine blade of claim 11 , wherein the at least one refresh hole is located on an upstream side of the root turn.
16. The turbine blade of claim 11 , wherein the at least one refresh hole has a bell mouth inlet section and a straight exit region.