A method of manufacturing the aerofoil, and an aerofoil. The method includes: casting a first body portion having a passage passing there-through; casting a second body portion; and joining the first body portion and the second body portion to form the aerofoil. The passage extends from an opening at a first end at or near a leading edge to an opening at a second end at or near a trailing edge. The passage is formed during the casting process by a core; and the core is supported at the first and second ends through the respective openings of the passage.

A method of manufacturing the aerofoil, and an aerofoil. The method includes: casting a first body portion having a passage passing there-through; casting a second body portion; and joining the first body portion and the second body portion to form the aerofoil. The passage extends from an opening at a first end at or near a leading edge to an opening at a second end at or near a trailing edge. The passage is formed during the casting process by a core; and the core is supported at the first and second ends through the respective openings of the passage.

Airfoils having a leading edge, a trailing edge, a first end, and a second end with a leading edge hybrid skin core cavity formed within the airfoil extending from the first end to the second end proximate the leading edge, the cavity having a hot wall and a cold wall. The cavity has a variable height-to-width ratio in a direction from the first end to the second end, with a first aspect ratio proximate the first end and a second aspect ratio proximate the second end with the height defined as a maximum distance between the hot wall and the cold wall and the width is defined as an arc length of the cold wall.

Airfoils having a leading edge, a trailing edge, a first end, and a second end with a leading edge hybrid skin core cavity formed within the airfoil extending from the first end to the second end proximate the leading edge, the cavity having a hot wall and a cold wall. The cavity has a variable height-to-width ratio in a direction from the first end to the second end, with a first aspect ratio proximate the first end and a second aspect ratio proximate the second end with the height defined as a maximum distance between the hot wall and the cold wall and the width is defined as an arc length of the cold wall.

Airfoils having a leading edge and a trailing edge, with a plurality of cavities therein including a leading edge hybrid cavity extending in a radial direction between a first end and a second end of the airfoil body along the leading edge. An airfoil side hybrid cavity is located toward the trailing edge relative to the leading edge hybrid cavity and positioned adjacent a side wall of the airfoil body. The airfoil side hybrid cavity extends in a radial direction between the first end and the second end and a divider rib extends radially between the first end and the second end along the side wall of the airfoil between the airfoil side hybrid cavity and the leading edge hybrid cavity. At least one first cross-over hole is formed within the divider rib to fluidly connect the airfoil side hybrid cavity to the leading edge hybrid cavity.

Airfoils having a leading edge and a trailing edge, with a plurality of cavities therein including a leading edge hybrid cavity extending in a radial direction between a first end and a second end of the airfoil body along the leading edge. An airfoil side hybrid cavity is located toward the trailing edge relative to the leading edge hybrid cavity and positioned adjacent a side wall of the airfoil body. The airfoil side hybrid cavity extends in a radial direction between the first end and the second end and a divider rib extends radially between the first end and the second end along the side wall of the airfoil between the airfoil side hybrid cavity and the leading edge hybrid cavity. At least one first cross-over hole is formed within the divider rib to fluidly connect the airfoil side hybrid cavity to the leading edge hybrid cavity.

Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the first and second core cavities. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface. At least one circuit exit is located in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.

Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the first and second core cavities. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface. At least one circuit exit is located in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.

A method of manufacturing the aerofoil, and an aerofoil. The method includes: casting a first body portion having a passage passing there-through; casting a second body portion; and joining the first body portion and the second body portion to form the aerofoil. The passage extends from an opening at a first end at or near a leading edge to an opening at a second end at or near a trailing edge. The passage is formed during the casting process by a core; and the core is supported at the first and second ends through the respective openings of the passage.

Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the first and second core cavities. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface. At least one circuit exit is located in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.