United Technologies Corporation

Raytheon Technologies Corporation

Michael S Stevens

Timothy M Davis

Ken Francis Blaney

Brian Duguay

David Richard Griffin

Brian C McLaughlin

Tomasz Pelic

Jeremy Drake

Jeffrey Vincent Anastas

Christine F McGinnis

Judith F Brooks

Dairus Deylan McDowell

Major D Jones

Ryan M Kohn

A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.

Duct with additive manufactured seal

The present disclosure relates generally to a seal between two components. The seal includes a plurality of seal sections including convolutions therein that are inter-engaged with one another to form flexible and resilient seals.

Multi-piece seal

A stator vane support with anti-rotation features is provided. The stator vane support may comprise an inner diameter surface opposite an outer diameter surface. The stator vane support may comprise an anti-rotation lug defining a protrusion extending inward from the inner diameter surface. The stator vane support may have a first recess defining a first void on the inner diameter surface proximate a first surface of the anti-rotation lug. The stator vane support may have a second recess defining a second void on the inner diameter surface proximate a second surface of the anti-rotation lug. The anti-rotation lug may be configured to interface with a stator vane to at least partially limit circumferential movement, and each recess may be configured to allow the stator vane to thermally expand during gas turbine engine operation.

Stator vane support with anti-rotation features

A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.

Support ring with thermal heat shield for case flange

A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.

Support ring with fluid flow metering

A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.

Necked debris separator for a gas turbine engine

A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.

Multi-air stream cooling system

A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages.

Gas turbine engine duct assembly

A seal assembly that may be for turbine engine includes first and second rings with a convoluted seal resiliently compressed there-between. The seal may define a gap for receipt of a thermally resistant shield that may also reduce wear of the seal. The seal may include a hole for the flow of cooling air and the shield may be porous so as not to obstruct the cooling air flow for cooling of the seal.

Thermally protected seal assembly

A method of assembling a gas turbine engine is provided that includes locating a consumable assembly tool within the engine. The consumable assembly tool is attached to another component of the gas turbine engine. The engine is run to vaporize the consumable assembly tool.

Consumable assembly tool for a gas turbine engine

A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint.

Low thermal mass joint

A method of assembling a gas turbine engine includes locating a consumable assembly tool clip within the engine.

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Alfred, ME, United States of America

Michael S Stevens