Honeywell International Inc.

Alliedsignal Inc.

Steve Halfmann

Mark C Morris

Ardeshir Riahi

Daniel Cregg Crites

Michael Kahrs

Jude Miller

Jason Smoke

David K Jan

Bob Mitlin

Craig A Wilson

Thomas E Strangman

Milton Ortiz

Dave Narasimhan

Morris G Anderson

Malak Fouad Malak

Luis A Tapia

Yong Weon Kim

David Chou

Rajiv Rana

Christopher Zollars

Kin Poon

Alexander S Kozlov

George E Zurmehly

Brandan Wakefield

Stuart Andrew Harman

George W Wolfmeyer

Frank A Mignano

Shawn J Pollock

Carl A Larson

David R Pack

Mitlin Bob

Luis Tapia

A turbine engine includes a turbine wheel including a rotor disk and turbine blades connected to the rotor disk through blade mounts. The blade mounts and the rotor disk have fore and aft surfaces. The blade mount includes a blade attachment surface connecting the fore and aft surfaces with the turbine blade extending from the blade attachment surface. A gap is defined between and separating adjacent blade mounts and extends into the rotor disk. The gap includes a pocket having a fore opening and a rotor relief hole. The turbine wheel further includes a plug disposed in a rotor relief opening and a pocket seal disposed in the pocket. The turbine engine further includes a fore seal plate having an edge abutting the blade mounts about a circumference of the turbine wheel and a finger extending toward and contacting the plug to maintain the plug in the rotor relief opening.

Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing

Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.

Turbine wheels, turbine engines including the same, and methods of fabricating turbine wheels with improved bond line geometry

A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.

Turbine blade with integral flow meter

An airfoil for a gas turbine engine includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; and an internal cooling system arranged within the first and second side walls configured to direct cooling air through and out of the airfoil. The internal cooling system has a first cooling circuit that includes an acceleration channel generally extending in a radial outward direction. A first section of the acceleration channel decreases in cross-sectional area along the radial outward direction such that the cooling air is accelerated through the first section of the acceleration channel. The first cooling circuit further includes a trailing edge chamber fluidly coupled to receive at least a portion of the cooling air from the acceleration channel and extending generally in a chordwise aft direction from the acceleration channel to the trailing edge.

Gas turbine engines with airfoils having improved dust tolerance

The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.

Turbine rotor assemblies with improved slot cavities

A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.

Gas turbine engines with turbine rotor blades having improved platform edges

A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.

Gas turbine engine components with blade tip cooling

A turbine blade includes a blade portion, the blade portion comprising a tip outer wall and a trailing edge, an internal cooling circuit, the internal cooling circuit being configured for directing cooling air within the blade portion, and a tip trailing edge slot positioned adjacent to the tip outer wall and the trailing edge, the tip trailing edge slot being fluidly connected to the internal cooling circuit. The tip outer wall is recessed at the tip trailing edge slot such that the tip outer wall is not provided over the trailing edge slot, thereby allowing cooling air to flow from the cooling circuit, into the trailing edge slot, and radially over the tip outer wall.

Turbine blade tip cooling

A turbine blade includes an airfoil defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the interior including an airfoil cooling circuit for directing airflow through the blade, and a platform supporting the airfoil and having a leading side edge, a trailing side edge, suction side edge, a pressure side edge, an airfoil-facing wall, and a root-facing wall, the platform including a platform cooling circuit having an inlet on the leading side edge and an outlet. The turbine blade may be included in a turbine rotor assembly.

Turbine blades and turbine rotor assemblies

Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.

Turbine blades and methods of forming modified turbine blades and turbine rotors

A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

Turbine blade assemblies and methods of manufacturing the same

A support and air mixer includes an inner annular member, an outer annular member shaped and positioned such that an annular air gap is formed between the inner annular member and the outer annular member, and a plurality of air mixing members, each air mixing member having a mixing passageway therethrough and each air mixing member having an inner portion connected to the inner annular member, an outer portion connected to the outer annular member, and first and second opposing side portions interconnecting the inner and outer portions and the inner and outer annular members such that the mixing passageway is in fluid communication with the annular air gap.

Integrated support and mixer for turbo machinery

A core assembly including two cores is used to manufacture a blade. The first core has an outer surface shaped to complement the tip wall bottom surface. The second core has a tip surface, a side surface, and a protrusion or a depression. The tip surface is shaped to complement at least a portion of the tip wall top surface and is configured to be disposed proximate the first core. The side surface is shaped to complement at least a portion of the side wall, and the protrusion extends from the second core side surface to contact at least a portion of the ceramic mold inner surface. In embodiments employing a depression, the depression is formed in the side surface.

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Chandler, AZ, United States of America

Steve Halfmann