United Technologies Corporation

Raytheon Technologies Corporation

Jesse R Christophel

Mark F Zelesky

Bryan P Dube

Matthew E Bintz

William Abdel-Messeh

Anthony P Cherolis

Ricardo Trindade

Justin D Piggush

Wieslaw A Chlus

Richard H Page

Karl A Mentz

Nelson DaCunha

William Abdel-Messah

An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

Airfoil assembly formed of high temperature-resistant material

A method for assembling a section of a gas turbine engine is disclosed. The method involves aligning a vane ring with a first rotor hub such that a row of vanes on the vane ring is adjacent a first row of blades of the first rotor hub, and aligning a second rotor hub with the vane ring such that a second row of blades of the second rotor hub is adjacent the row of vanes and the row of vanes is axially between the first row of blades and the second row of blades. The first hub and the second hub are then non-mechanically bonded together.

Method of assembling gas turbine engine section

A method for assembling a section of a gas turbine engine is disclosed. The method involves a plurality of vane arc segments that together form a full vane ring, and a multi-row rotor drum that is formed of a single-piece body that has at least two rows of blades about a central axis. The method includes inserting the plurality of vane arc segments in a radial direction into an assembled position that is axially between the two rows of blades.

An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.

Investment casting cores and methods

A gas turbine blade assembly includes a neck defining a neck cavity, and has a first end and a second end at an opposite side relative to the first end. A platform has first and second sides. The first side is disposed on and faces the second end of the neck. An airfoil is supported on the second side of the platform. The neck, platform and airfoil define an inner cooling passage extending through the neck, platform and into the airfoil. The neck defines at least one core channel extending between the cooling passage and the neck cavity. The platform defines at least one film cooling channel extending from the first side facing the neck cavity to the second side disposed exterior to the airfoil to permit cooling air to flow through the inner cooling passage into the neck cavity and through the platform exterior to the airfoil.

Industrial gas turbine blade assembly

A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the heat transfer at the area. In addition, a second pedestal array replaces the metering holes which has been positioned radially inwardly of the tip strip. The two pedestal arrays provide improved heat transfer at an area which has been subject to burning and spallation in the prior art.

Turbine component with tip flagged pedestal cooling

A blade outer air seal (BOAS) has a body having an inner (ID) face and an outer (OD) face, first and second circumferential ends, and fore and aft longitudinal ends. The BOAS has one or more mounting hooks extending from the body. The OD face comprises a plurality of transversely elongate protuberances. The protuberances include rearwardly divergent first protuberances and forwardly divergent second protuberances.

Blade outer air seals

A blade has an airfoil body having an internal cooling passageway network and a body tip pocket. At least one plate is secured within the body tip pocket and has inboard and outboard surfaces. A recess is in the outboard surface and an associated protrusion is on the inboard surface.

Growing community of inventors

Manchester, CT, United States of America

Jesse R Christophel