Airfoil with supplemental cooling channel adjacent leading edge

An airfoil comprising:

• an airfoil being curved with a pressure wall and a suction wall spaced from each other, said airfoil extending from a base to a tip, and having a leading edge and a trailing edge connecting said pressure and suction walls;
• cooling channels formed between said suction and pressure walls and within said airfoil, said cooling channels including a first main channel extending from said base outwardly and through said airfoil towards a tip, a leading edge channel communicating with said first main channel, said leading edge channel having film cooling parts extending from said leading edge channel and directing cooling air near said leading edge;
• a supplemental film cooling channel positioned at an area between said first main channel and said suction wall, said supplemental film cooling channel spaced toward said trailing edge from said leading edge channel, and said supplemental film cooling channel having film cooling ports for directing film cooling air onto said suction wall at a location spaced toward said trailing edge from said film cooling ports of said leading edge channel;
• a web defined between said first main channel and a second main channel spaced toward said trailing edge from said first main channel, said film cooling ports of said supplemental film cooling channel being located on said suction wall to be adjacent an extended location of said web, said extended location of said web being defined by identifying a leading edge side of said web and a trailing side edge of said web, and extending the two edges by lines to the suction wall, and said supplemental film cooling channel extending to said suction wall at a location between said extended edges;
• and
• a thermal barrier coating being applied to said airfoil.

A turbine blade comprising:

• an airfoil extending outwardly of a platform, said airfoil being curved with a pressure wall and a suction wall spaced from each other and having a leading edge and a trailing edge connecting said pressure and suction walls;
• cooling channels formed between said suction and pressure walls and within said airfoil, said cooling channels including a first main channel extending from said platform and towards a tip of said airfoil, a leading edge channel communicating with said first main channel and directing cooling air onto said leading edge through a plurality of film cooling ports;
• a microcircuit cooling circuit positioned between said suction wall and said first main channel, said microcircuit cooling circuit receiving cooling fluid from said first main channel to provide supplemental film cooling onto said suction wall through film cooling ports spaced towards said trailing edge relative to said film cooling ports of said leading edge channel, and said microcircuit cooling circuit having pedestals crossing said microcircuit cooling circuit, said microcircuit cooling circuit being smaller in cross-section than said first main channel;
• and
• a web defined between said first main channel and a second main channel spaced toward said trailing edge from said first main channel, said film cooling ports of said supplemental film cooling channel being located on said suction wall to be adjacent an extended location of said web, said extended location of said web being defined by identifying a leading edge side of said web and a trailing side edge of said web, and extending the two edges by lines to the suction wall, and said supplemental film cooling channel extending to said suction wall at a location between said extended edges.

A gas turbine engine comprising:

• a fan;
• a compressor;
• a combustion section;
• a turbine having rotor blades, and vanes, at least one of said rotor blades and said vanes having an airfoil with a base and a tip, and said airfoil extending between a suction wall and a pressure wall and having a leading edge and a trailing edge connecting said pressure and suction walls, cooling channels formed between said suction and pressure walls and within said airfoil, said cooling channels including a first main channel extending from said base outwardly and through said airfoil towards a tip, a leading edge channel communicating with said first main channel, said leading edge channel having film cooling ports extending from said leading edge channel and directing cooling air near said leading edge, a supplemental film cooling channel positioned at an area between said first main channel and said suction wall, said supplemental film cooling channel spaced toward said trailing edge from said leading edge channel, and said supplemental film cooling channel having film cooling ports for directing film cooling air onto said suction wall at a location spaced toward said trailing edge from said film cooling ports of said leading edge channel;
• a web defined between said first main channel and a second main channel spaced toward said trailing edge from said first main channel, said film cooling ports of said supplemental film cooling channel being located on said suction wall to be adjacent an extended location of said web, said extended location of said web being defined by identifying a leading edge side of said web and a trailing side edge of said web, and extending the two edges by lines to the suction wall, and said supplemental film cooling channel extending to said suction wall at a location between said extended edges;
• and
• said supplemental film cooling channel being a microcircuit cooling circuit embedded within said airfoil, said microcircuit cooling circuit receiving cooling fluid to provide additional cooling in said area.