United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

James M Koonankeil

Dominic J Mongillo, Jr

Brian T Hazel

Brian Richard Craig

Paul E Denney

Edward F Pietraszkiewicz

Paul Edward Denney

Gordon Miller Reed

Richard William Varsell

Kevin J Klinefelter

Markus W Fritch

Sergey Mironets

Jesse R Boyer

Jeffrey S Beattie

Dean N Marszal

Thomas R Davis

Rodney H Warner

Kirk David Hlavaty

James Romanelli

Dorel M Moisei

Jason Daley

Lukas A Rubino

Karl A Schachtner

Kenneth J Hollman

Francis M Tamiso

Dominic J Mongillo

A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.

Forming and/or inspecting cooling aperture(s) in a turbine engine component

A process of determining a location of a core cavity in a cast part including determining a nominal location of the cavity within the part; determining a nominal location of at least one locator hole in at least one external surface of the part; determining an actual location of the at least one locator hole in the at least one external surface of the part; comparing the nominal location of the at least one locator hole in the at least one external surface of the part to the actual location of the at least one locator hole in the at least one external surface of the part; and determining an actual location of the core cavity within the part.

Method of determining location and orientation of an internal core cavity

A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate and a locating feature at an exterior surface of the substrate. An outer coating is applied over the substrate. The outer coating covers the locating feature. At least a portion of the preform component and the outer coating are scanned with an imaging system to provide scan data indicative of a location of the locating feature. A cooling aperture is formed in the substrate and the outer coating based on the scan data.

Forming cooling aperture(s) in a turbine engine component

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

Forming lined cooling aperture(s) in a turbine engine component

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.

A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate. An outer coating is applied over the substrate. A characteristic of the outer coating is determined. Instructions for forming a cooling aperture are revised based on the characteristic of the outer coating to provide revised instructions. The cooling aperture is formed in the outer coating and the substrate based on the revised instructions.

Methods for forming cooling apertures in a turbine engine component

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

Transition section for accommodating mismatch between other sections of a cooling aperture in a turbine engine component

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate comprising electrically conductive material having an outer coating comprising non-electrically conductive material applied over a surface of the substrate. A preform aperture is formed in the preform component using an electrical discharge machining electrode. The preform aperture includes a meter section of a cooling aperture in the substrate. The preform aperture also includes a pilot hole in the outer coating. A diffuser section of the cooling aperture is formed in at least the outer coating using a second machining process.

Forming cooling aperture(s) using electrical discharge machining

A manufacturing method is provided during which a preform component for a turbine engine is provided. A cooling aperture is formed in the preform component. The cooling aperture includes a centerline, an inlet and an outlet. The cooling aperture extends longitudinally along the centerline through a wall of the preform component from the inlet to the outlet. The forming of the cooling aperture includes forming a first portion of the cooling aperture using a machining tool implement with a first toolpath that is angularly offset from the centerline by a first angle between thirty-five degrees and ninety degrees.

Energy beam positioning during formation of a cooling aperture

One exemplary embodiment of this disclosure relates to a method of inspecting a component of a gas turbine engine. The method includes performing a through-hole inspection, and determining a location of the plurality of holes from results of the through-hole inspection.

Method and assembly for inspecting engine component

A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed.

Method of reducing manufacturing variation related to blocked cooling holes

A method for disposing blocking material within an interior of a component for blocking a beam of radiation from a laser during a laser drilling operation, the method including forming one of a multiple of apertures formed via a first process and forming the remainder of the multiple of apertures formed via a laser drilling process. A component for a gas turbine engine includes a surface with at least one of a multiple of apertures formed via a first process, the at least one of the multiple of apertures formed via the first process in communication with a cavity, a remainder of the multiple of apertures formed via a laser drilling process, the remainder of the multiple of apertures in communication with the cavity.

Method for disposing a blocking material

A method is provided for inspecting at least one aperture of a component with curable material and an inspection system. At least a portion of the curable material is injected into the aperture. The curable material conforms to at least a portion the aperture and subsequently cures and forms a mold of at least a portion of the aperture. The mold is removed from the aperture. At least a portion of a geometry of the mold is compared to at least a portion of a geometry of a reference model for the aperture using the inspection system.

Inspecting one or more apertures of a component using moldable material

An airfoil body includes an airfoil wall defined between an internal cavity surface and an external airfoil surface. A pad extends from the internal cavity surface. A cooling hole extends from the external airfoil surface, through the airfoil wall and through the pad for fluid communication through the airfoil wall.

Growing community of inventors

Marlborough, CT, United States of America

James M Koonankeil