Rtx Corporation

Jaime G Ghigliotty Rosado

Brandon W Spangler

Tracy A Propheter-Hinckley

Dominic J Mongillo, Jr

David R Pack

A turbine vane includes a vane body, a baffle, and a plurality of axial divider ribs. The vane body includes a first side wall, a second side wall, and a trailing edge rib forming a cooling passage. The baffle includes a baffle body disposed within the cooling passage. The baffle body includes a first baffle side and a second baffle side. The baffle body forms an internal baffle cavity. The baffle body further forms a plurality of baffle apertures. Each axial divider rib extends between and to the second side wall and the second baffle side. The vane body, the baffle body, and the axial divider ribs form a feed cavity and one or more axial flow channels. The feed cavity is disposed between the vane body and the baffle body at least between the first side wall and the first baffle side. The axial flow channels are formed by the axial divider ribs. Each axial flow channel o is connected in fluid communication with the internal baffle cavity by one or more of the baffle apertures.

Turbine vane for a gas turbine engine

A turbine component includes a body having a pair of spaced walls, with at least one of the walls for facing a fluid flow when mounted in a gas turbine engine. There are a plurality of wall cooling passages having a generally boomerang shape such that a peak apex is spaced from the wall and an indent apex is adjacent to the wall, with the plurality of wall cooling passages having interior sides extending from the peak apex toward the wall to define a corner. Outer sides extend from the corners with a component away from the wall and to the indent apex. A gas turbine engine is also disclosed.

Turbine blade with boomerang shaped wall cooling passages

A turbine blade for a gas turbine engine, including: an airfoil, the having a leading edge, a pressure side, a suction side and a trailing edge; a plurality of internal cooling cavities including a leading edge cavity, a leading edge feed passage, pressure side cooling passages, suction side cooling passages and main body cavities; the leading edge cavity extending towards the suction side; a first crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage; and a second crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage, a centerline of the first crossover row of cooling passages is located closer to the pressure side than a centerline of the second crossover row of cooling passages and the centerline of the second crossover row of cooling passages is located closer to the suction side than the centerline of the first crossover row of cooling passages, and wherein the second crossover row of cooling passages are radially staggered relative to the first crossover row of cooling passages.

Air foil with staggered cooling hole configuration

A turbine engine airfoil element has: a plurality of spanwise main body passageways along a camber line; and a plurality of spanwise skin passageways along the pressure side. The spanwise skin passageways include: first skin passageways each having a plurality of film cooling outlets to the pressure side; and second skin passageways each lacking film cooling outlets to the pressure side. Linking passageways extend between the first skin passageways and the second skin passageways. The first skin passageways and second skin passageways are directly fed from one or more inlets of the airfoil element.

Growing community of inventors

Cabo Rojo, Puerto Rico

Jaime G Ghigliotty Rosado