Raytheon Technologies Corporation

General Electric Company

United Technologies Corporation

Scott Henry Lamson

Ching-Pang Lee

Kevin Richard Kirtley

Anna Tam

Ronald Scott Bunker

Scott Michael Carson

Andrew D Milliken

A gas turbine engine component assembly is provided. The gas turbine engine comprises: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate mitigation device extending from the first surface of the second component a selected distance wherein the particulate mitigation device has an opening therethrough in fluid connection with the cooling channel, and wherein the selected distance is selected to reduce the amount of particulate entering the cooling channel.

Apparatus and method for mitigating particulate accumulation on a component of a gas turbine engine

A gas turbine part with a cooling hole, is fabricated by first forming a model of a wall of a gas turbine part. The wall is defined by first and second surfaces, the first surface having an aperture indentation possessing a complex geometry and extending into but not all the way through the wall of the gas turbine part. A mold of the wall of the gas turbine part is formed using the model and is used to cast the wall of the gas turbine part by lost-material casting. A passage is drilled through the resulting casting. This passage extends from the aperture indentation in the first surface through to the second surface.

Method for forming cooling holes having separate complex and simple geometry sections

A gas turbine engine component assembly including: a first component having a first surface and second surface opposite the first surface, the first component includes a cooling hole extending from second surface to first surface; a second component having a first surface and second surface, the first surface of first component and second surface of second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling second surface of second component; and an aperture extension feature in the second component and extending into cooling channel, the aperture extension feature includes a passageway fluidly connecting cooling channel to an area located proximate to the first surface of second component, the aperture extension feature includes a face and inlet located in the first face to fluidly connect passageway to cooling channel, the first face being oriented between 0&#xb0; and 120&#xb0; relative to second surface of second component.

Hooded entrance to effusion holes

The present disclosure provides an airfoil assembly comprising a first segment comprising a first shroud and a second shroud radially outward of the first shroud, a second segment comprising a first shroud and a second shroud radially outward of the first shroud, and a first coupling coupled to at least one of the first shroud or the second shroud of the first segment and a second coupling coupled to at least one of the first shroud or the second shroud of the second segment, wherein the first segment and the second segment are coupled together by a first land of the first coupling and a second land of the second coupling.

Contact coupled singlets

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall, a first channel extending at least partially through the wall to a first outlet, and a second channel adjacent to the first channel and extending to a second outlet. The first channel is configured to communicate a cooling fluid along a first swirl flow path and the second channel is configured to communicate the cooling fluid along a second swirl flow path that is opposite the first swirl flow path.

Gas turbine engine component cooling channels

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.

Crescentic ramp turbine stage

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.

Growing community of inventors

Menands, NY, United States of America

Scott Henry Lamson