Ribbed turbine blade tip

A gas turbine engine turbine blade squealer tip comprising:

• an airfoil tip cap having an airfoil shape,
• said tip cap including pressure and suction sides joined together at chordally spaced apart leading and trailing edges of said tip cap,
• a plurality of squealer ribs extending outward from said tip cap between said leading and trailing edges,
• substantially parallel channels between said squealer ribs, and
• ribs disposed between said squealer ribs and across said channels.

A gas turbine engine turbine blade comprising:

• an airfoil having an airfoil outer wall with pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending longitudinally from a blade root to a squealer tip;
• said sidewalls being spaced apart from each other between said leading and trailing edges and joined together by a plurality of internal ribs defining at least one cooling circuit;
• said squealer tip includes an airfoil tip cap having an airfoil share with pressure and suction sides coinciding with said pressure and suction sidewalls and a plurality of squealer ribs extending outward from said tip cap between said leading and trailing edges;
• substantially parallel channels between said squealer ribs;
• a trailing edge rib along a portion of said suction side including said trailing edge;
• and
• a leading edge rib curved around at least an axially extending portion of said leading edge.

A gas turbine engine turbine blade comprising:

• an airfoil having an airfoil outer wall with pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending longitudinally from a blade root to a squealer tip;
• said sidewalls being spaced apart from each other between said leading and trailing edges and joined together by a plurality of internal ribs defining at least one cooling circuit;
• said squealer tip includes an airfoil tip cap having an airfoil shape with pressure and suction sides coinciding with said pressure and suction sidewalls and a plurality of squealer ribs extending outward from said tip cap between said leading and trailing edges;
• substantially parallel channels between said squealer ribs;
• a trailing edge rib along a portion of said suction side including said trailing edge;
• a leading edge rib curved around at least an axially extending portion of said leading edge;
• said squealer ribs are angled in an axially aft direction from said leading edge on said suction side towards said trailing edge on said pressure side;
• and
• said squealer ribs and channels have rectangular cross-sections between said pressure and suction sides.

A gas turbine engine turbine blade comprising:

• an airfoil having an airfoil outer wall with pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending longitudinally from a blade root to a squealer tip;
• said sidewalls being spaced apart from each other between said leading and trailing edges and joined together by a plurality of internal ribs defining at least one cooling circuit;
• said squealer tip includes an airfoil tip cap having an airfoil shape with pressure and suction sides coinciding with said pressure and suction sidewalls and a plurality of squealer ribs extending outward from said tip cap between said leading and trailing edges;
• substantially parallel channels between said squealer ribs;
• and
• channel ribs disposed between said squealer ribs and across said channels.