United Technologies Corporation

Raytheon Technologies Corporation

Jason Shenny

San Quach

Jeffrey T Morton

Alberto A Mateo

Gregory Anselmi

James B Hoke

Robert M Sonntag

John J Rup, Jr

Richard G Ullrich

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

Impingement cooling arrangement for airfoils

An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

Directional cooling arrangement for airfoils

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

Combustor panels including panel bodies with first and second sides, a pin array extending from the first side, wherein each pin extends a first height, has a pin diameter, and is separated from adjacent pins by a pin array separation distance. A structural protrusion extends from the first side. No pins of the pin array are located within a flashing distance that is equal to a protrusion separation distance plus half of the pin diameter, wherein a location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. At least one pin array extension is integrally formed with the structural protrusion, the pin array extension extending along the first side to a position that replaces a pin of the pin array that would be within the flashing distance.

Float wall combustor panels having airflow distribution features

Combustor panel bodies with first and second sides, a pin array of cooling pins extending from the first side, with each pin extending a first height from the first side and having a pin diameter, each pin separated from adjacent pins by a pin array separation distance. A structural protrusion extending from the first side with no pins located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter. A location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. A pin array scallop is integrally formed with the structural protrusion forming a reduction in material such that each pin of the array that is closest to the structural protrusion is positioned the pin array separation distance from the structural protrusion.

Growing community of inventors

West Hartford, CT, United States of America

Jason Shenny