Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Allan N Arisi

Tracy A Propheter-Hinckley

Dominic J Mongillo, Jr

Bret M Teller

Brandon W Spangler

San Quach

Bryan P Dube

Howard J Liles

James Tilsley Auxier

Ricardo Trindade

Adam P Generale

Corneil S Paauwe

Lucas Dvorozniak

Christopher Cosher

Karl A Mentz

Tracy A Propheter-hinckley

Dominic Mongillo

Tracy A Protheter-Hinckley

Dominic J Mongillo

An airfoil includes a platform and an airfoil section that extends from the platform. The airfoil defines leading and trailing ends and suction and pressure sides. The airfoil section has a transition region through which the airfoil section blends into the platform. The trailing end of the airfoil section has an axial cooling slot opening through the transition region and defines a circumferentially diverging ramp in the transition region.

Airfoil with axial cooling slot having diverging ramp

An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

Airfoil with cooling passage network having arced leading edge

An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.

Airfoil with arced pedestal row

An airfoil section has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.

Airfoil with wall that tapers in thickness

An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. An arced rib extends from the first side to the second side and divides the internal core cavity into a forward cavity and an aft cavity. A cooling passage network is embedded in the airfoil wall aft of the rib and between inner and outer portions of the airfoil wall. The network includes a cooling passage leading edge and a cooling passage trailing edge. The aft core cavity has a central cavity section and a cavity lobe. The cavity lobe projects between the rib and the cooling passage leading edge.

Airfoil with cavity lobe adjacent cooling passage network

A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.

Cooling passage configuration

A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.

Cooling arrangement including overlapping diffusers

A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network.

Minicore cooling passage network having trip strips

A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.

Article having cooling passage network with inter-row sub-passages

An airfoil has a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib extends from the first side to the second side and partitions an internal core cavity into a forward cavity and an aft cavity. A baffle is disposed in the forward cavity and has a showerhead array of impingement orifices adjacent the leading end of the airfoil wall. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall, an array of pedestals, and at least one outlet orifice through the outer portion. The inlet orifice opens to the forward cavity at a location aft of the showerhead array of impingement orifices.

Airfoil with baffle showerhead and cooling passage network having aft inlet

An airfoil includes an airfoil section that has an airfoil wall that define leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. The airfoil section extends form a platform. The platform defines a shelf that extends forward from the first end at the leading end of the airfoil section to a platform leading edge, aft from the first end at the trailing end of the airfoil section to a platform trailing edge, laterally from the first end at the first side of the airfoil section to a first platform side edge, and laterally from the first end at the second side of the airfoil section to a second platform side edge. The internal core cavity extends from the airfoil section into the shelf.

Airfoil with core cavity that extends into platform shelf

Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a pressure and suction side walls and an internal rib and defining a cavity between, at least, the pressure side wall, the suction side wall, and the internal rib. A baffle insert is arranged within the cavity and includes a sealing portion arranged adjacent to the internal rib of the airfoil body with a gap therebetween. A seal element is arranged within the cavity and located in the gap. The seal element is free to move relative to each of the baffle insert and the airfoil body within the gap. When a pressure differential exists across the seal element, the seal element will sealingly engage between sealing portion of the baffle insert and the internal rib of the airfoil body to block a flow through the gap.

Baffle systems for airfoils

An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. First and second platforms are attached, respectively, with the first and second ends. A cooling passage circuit extends at least in the first platform and the airfoil section. The cooling passage circuit includes a first plenum in the first platform adjacent at least the first side of the airfoil wall, a hybrid skin core passage embedded in the first side of the airfoil wall and that extends longitudinally, and a resupply passage that connects the first plenum with the hybrid skin core passage.

Airfoil with skincore passage resupply

A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.

Growing community of inventors

Manchester, CT, United States of America

Allan N Arisi