Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Christopher Perron

Shawn M McMahon

Justin M Aniello

Brett Alan Bartling

Steven Bruce Gautschi

Ricardo Trindade

Mohamed Hassan

Ryan Lundgreen

Robin Prenter

David Barger

Nicholas J Madonna

Christopher Cosher

Dominic J Mongillo, Jr

Dana K Bondarevsky

Yuta Yoshimura

David D Chapdelaine

Bryan P Dube

Christopher Whitfield

Christopher Corcoran

Kristopher K Anderson

Jason B Moran

Stephanie Tanner

Jr Dominic J Mongillo

An airfoil for a gas turbine engine includes a first wall disposed in an interior cavity, the first wall extending in the spanwise direction from a base region to a tip wall and adjoining a pressure side wall and a suction side wall to form a first cooling channel; a second wall disposed in the interior cavity and extending in a chordwise direction from the first wall toward a trailing edge, the second wall adjoining the pressure side wall and the suction side wall to form a second cooling channel; a first hole through the first wall, the first hole connecting the first cooling channel to the second cooling channel; and a second hole though the second wall connecting the second cooling channel to a third cooling channel.

Airfoil cooling circuit

An airfoil for a gas turbine engine is configured to extend in a radial direction relative to an engine axis from an inner diameter to an outer diameter. The airfoil comprises a body having a base disposed at the inner diameter, a tip disposed at the outer diameter, a leading edge, a trailing edge, and pressure and suction side walls extending between the leading edge and the trailing edge and between the base and the tip. The body defines an interior cavity. A first wall is disposed in the interior cavity, extends radially, and adjoins the pressure side wall and the suction side wall to form a first cooling channel. A first hole through the first wall connects the first cooling channel to a second cooling channel. The first hole has a profile that tapers inward toward the base.

Non-circular stress reducing crossover

A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.

Redundant entry cooling air feed hole blockage preventer for a gas turbine engine

A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

Shape recessed surface cooling air feed hole blockage preventer for a gas turbine engine

A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

Extension air feed hole blockage preventer for a gas turbine engine

A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

Turbine vane cluster including enhanced vane cooling

Growing community of inventors

Tolland, CT, United States of America

Christopher Perron