18966893. Airfoils with Lobed Cooling Cavities (RTX Corporation)
Airfoils with Lobed Cooling Cavities
Organization Name
Inventor(s)
Brandon W. Spangler of Vernon CT US
David R. Pack of Gold Canyon AZ US
Airfoils with Lobed Cooling Cavities
This abstract first appeared for US patent application 18966893 titled 'Airfoils with Lobed Cooling Cavities
Original Abstract Submitted
A turbine engine airfoil element has a plurality of main body passageways along a camber line and having two or more camberwise/chordwise distributed protuberant portions with necks between the protuberant portions. A plurality of skin passageways include: at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and a plurality of second skin passageways each nested between first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway.