Turbine blade with cooling channels

A turbine engine rotor blade, comprising:

• a root;
• and
• an airfoil that extends spanwise between a tip and a base, the airfoil including a side wall with a side wall exterior surface and a side wall interior surface, wherein the side wall exterior surface extends between a leading edge of the airfoil and a trailing edge and spanwise between the tip and the base;
• wherein the airfoil includes at least one first wall channel, and the first wall channel is defined by a base surface that is a portion of the side wall interior surface, a first interior wall surface, and a second interior wall surface, wherein a first interface surface extends between the base surface and the first interior wall surface, a second interface surface extends between the base surface and the second interior wall surface, and a third interface surface extends between the first interior wall surface and the second interior wall surface;
• and
• wherein the base surface includes a base surface first segment, a base surface second segment, and a peak interface surface extending between the base surface first segment and the base surface second segment, and wherein the base surface first segment and the base surface second segment are disposed at an oblique angle;
• wherein the third interface surface is spaced apart from the peak interface surface;
• wherein the first interface surface is disposed from the sidewall exterior surface a first interface separation distance, the peak interface surface is disposed from the sidewall exterior surface a peak interface separation distance, the first interface separation distance less than the peak interface separation distance, the second interface surface is disposed from the exterior sidewall a second interface separation distance, and the first interface separation distance is less than the second interface separation distance;
• and
• a cooling aperture extending between the base surface and the side wall exterior surface, wherein the cooling aperture has a central axis that intersects with the third interface surface.

A turbine engine rotor blade, comprising:

• a root;
• and
• an airfoil that extends spanwise between a tip and a base, the airfoil including a side wall with a side wall exterior surface and a side wall interior surface, wherein the side wall exterior surface extends between a leading edge of the airfoil and a trailing edge and spanwise between the tip and the base;
• wherein the airfoil includes at least one first wall channel, and the first wall channel is defined by a base surface that is a portion of the side wall interior surface, a first interior wall surface, and a second interior wall surface, wherein a first interface surface extends between the base surface and the first interior wall surface, a second interface surface extends between the base surface and the second interior wall surface, and a third interface surface extends between the first interior wall surface and the second interior wall surface;
• and
• wherein the base surface includes a base surface first segment, a base surface second segment, and a peak interface surface extending between the base surface first segment and the base surface second segment, and wherein the base surface first segment and the base surface second segment are disposed at an oblique angle;
• wherein the third interface surface is spaced apart from the peak interface surface;
• and
• wherein the second interface surface and the peak interface surface are equidistant from the side wall exterior surface and the first interface surface is disposed closer to the side wall exterior surface than the second interface surface and the peak interface surface;
• and
• a cooling aperture extending between the base surface and the side wall exterior surface, wherein the cooling aperture has a central axis that intersects with the base surface second segment.