Cooling system for a platform of a turbine blade
View Patent ↗A turbine blade for a turbine engine having a platform cooling system formed from one or more platform cooling channels extending from an inner cooling cavity in a root of a turbine blade to an outer surface of a platform on the turbine blade. The platform cooling channels may be positioned in ribs protruding from a bottom surface of the platform. The ribs act as fins during operation of a turbine engine in which the turbine blade is installed by increasing surface area of the platform and thereby increasing convection on the bottom surface.
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 turbine blade;
at least one outer wall defining the at least one cavity forming the cooling system;
a platform generally orthogonal to the generally elongated blade and proximate to the root;
at least one rib protruding from a bottom surface of the platform, extending at an oblique angle to the platform contacting the root; and
at least one platform cooling channel in the at least one rib providing a pathway from the at least one cavity forming a cooling system in the root of the turbine blade to an outer side surface of the platform, wherein the at least one platform cooling channel terminates at the outer side surface of the platform to provide impingement cooling to a platform side surface on a platform of an adjacent turbine blade.
2. The turbine blade of claim 1 , wherein the at least one rib is positioned on an outer surface of the platform on a side of the platform extending proximate to a pressure side of the generally elongated blade.
3. The turbine blade of claim 1 , wherein the at least one rib is positioned on an outer surface of the platform on a side of the platform extending proximate to a suction side of the generally elongated blade.
4. The turbine blade of claim 1 , wherein the at least one platform cooling channel is positioned nonparallel relative to an outer surface of the platform and nonparallel relative to a longitudinal axis of the generally elongated blade.
5. The turbine blade of claim 1 , wherein the at least one rib comprises a plurality of ribs protruding from the bottom surface of the platform in a generally parallel configuration.
6. The turbine blade of claim 5 , wherein the plurality of ribs extend along the bottom surface of the platform only on a single side of the root.
7. The turbine blade of claim 1 , wherein the at least one rib protruding from the bottom surface of the platform tapers from a first thickness at a tip of the rib to a second thickness at an intersection between the at least one rib and the root, wherein the second thickness proximate the root is larger than the first thickness.
8. 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 turbine blade;
at least one outer wall defining the at least one cavity forming the cooling system;
a platform generally orthogonal to the generally elongated blade and proximate to the root;
at least one rib protruding from a bottom surface of the platform, extending at an oblique angle to the platform and contacting the root; and
at least one platform cooling channel in the at least one rib providing a pathway from the at least one cavity forming a cooling system in the root of the turbine blade to an outer side surface of the platform, wherein the at least one platform cooling channel terminates at the outer side surface of the platform to a provide impingement cooling to platform side surface on a platform of an adjacent turbine blade;
wherein the at least one platform cooling channel is positioned nonparallel relative to an outer surface of the platform and nonparallel relative to a longitudinal axis of the generally elongated blade.
9. The turbine blade of claim 8 , wherein the at least one rib is positioned on an outer surface of the platform on a side of the platform extending proximate to a pressure side of the generally elongated blade.
10. The turbine blade of claim 8 , wherein the at least one rib is positioned on an outer surface of the platform on a side of the platform extending proximate to a suction side of the generally elongated blade.
11. The turbine blade of claim 8 , wherein the at least one rib comprises a plurality of ribs protruding from the bottom surface of the platform in a generally parallel configuration.
12. The turbine blade of claim 11 , wherein the plurality of ribs extend along the bottom surface of the platform only on a single side of the root.
13. The turbine blade of claim 8 , wherein the at least one rib protruding from the bottom surface of the platform tapers from a first thickness at a rip of the rib to a second thickness at an intersection between the at least one rib and the root, wherein the second thickness proximate the root is larger than the first thickness.