The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

A heat exchanger for cooling a component is coupled with a cowl at least partially surrounding the component. The cowl defines a cowl plenum and a peripheral gap for receiving the heat exchanger. The heat exchanger includes a housing defining a heat exchange plenum for receiving a cool fluid stream and a plurality of heat exchange tubes passing through the heat exchange plenum for receiving a hot fluid stream. A discharge manifold defines a discharge plenum that provides fluid communication between the heat exchange plenum and the cowl plenum through a fluid outlet. In addition, an impingement baffle at least partially defines the discharge manifold and defines a plurality of cooling holes for impinging cooling air on the component proximate the heat exchanger.

An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties based on a reduced order model for an IBR type to which the first IBR belongs. Shape data indicating an initial shape of a surface of a first blade is used, with repair data that indicates a candidate repair to form a restored shape, to determine a change in a value of an inherent blade section vibratory property of the set of inherent vibratory properties. A condition of the first IBR is determined based at least in part on the change in the value of the inherent blade section vibratory property. The first IBR is maintained based on the condition.

A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

A method of hyper-feed machining the bladed components of turbomachines, and more specifically their bladed components. Hyper-feed machining, by means of the physical process of controlled fracturing, is the fastest, most precise, and nearest net shape method of machining in existence. The practical effects of the invention are: (1) the production of new and useful small-scale gas turbine engines for a wide range of previously impossible or impractical applications, and (2) the production of existing larger-scale gas turbine engines with great improvements in material removal rates by orders of magnitude, greater precision and geometric complexity of the bladed components, faster overall rates of production of these engines, and significantly reduced costs in production. As a consequence, the best preferred embodiment of the invention is the small-scale turboshaft electric engine for automotive vehicles, which makes possible a turbo-electric vehicle that replaces both the electric battery vehicle and the piston-engine vehicle.

A case for a gas turbine engine includes a case wall and a boss that extends from the case wall. The boss includes a perimeter step.

A method of assembling a fan drive gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier defining a central axis and that includes spaced apart walls and circumferentially spaced mounts defining spaced apart apertures at an outer circumference of the carrier, gear pockets defined between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes the steps of inserting a plurality of intermediate gears through the central opening, moving the intermediate gears radially outwardly relative to the central axis into the gear pockets, inserting a sun gear through the central opening, moving the plurality of intermediate gears radially inwardly relative to the central axis to engage the sun gear, and coupling a fan shaft to the carrier such that the fan shaft and intermediate gears are rotatable about the central axis. A fan drive gear system is also disclosed.

An aft cascade ring includes a first ring portion having a first arc shape and defining a first portion first lug. The aft cascade ring further includes a second ring portion having a second arc shape and defining a second portion first lug, the second ring portion being coupled to the first ring portion such that the first portion first lug and the second portion first lug are aligned.