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

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The present disclosure relates generally to a gasket assembly for use in a gas turbine engine, the gasket assembly including a gasket component including an outer surface and end portions, and a seal component operably coupled to the outer surface of the gasket component for providing sealing contact.

Abstract: 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.

Abstract: A method of assembling a gas turbine engine includes locating a consumable assembly tool within the engine

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

Abstract: A gasket assembly for a gas turbine engine includes a seal portion defining outer surfaces for providing sealing contact and a bias portion defining inner structures that are spaced apart from the seal portion for biasing the outer surfaces into sealing contact. The gasket further includes end portions disposed at ends of the seal portion that including a material thickness greater than a thickness of the bias portion.

Abstract: A urine specimen collection receptacle is formed as a one-piece unit by vacuum forming a sheet resin and includes an outer rectangular trough forming a urine reservoir and a lid with a funnel formed therein. The lid is folded about a fold line into substantial covering relation to the trough with the funnel positioned within the reservoir and in fluidic communication therewith. Front corner areas of the trough have spout grooves formed therein, and corresponding areas at the front of the lid are beveled to facilitate pouring a collected sample into another container. The lid is provided with a bulged area to extend the volume of the reservoir to lessen the tendency of the sample to backflow through the funnel during pouring the sample to another container.