Abstract: A system for feature recognition of design geometry may include one or more processors coupled to memory, which may be collectively operable to execute a mapping environment. The mapping environment may be operable to access one or more input images of geometric features of at least one component design. The mapping environment may be operable to determine, using a machine learning classifier model, a geometry of the respective geometric features of the at least one component design from the one or more input images. The mapping environment may be operable to assign, using the classifier model, predefined names to the respective geometric features based on the determined geometry. The classifier model may be trained with training data, which may include training images of geometric features and the predefined names assigned to the respective geometric features in the training images. A method for feature recognition of design geometry is also disclosed.

Abstract: A system for feature recognition of design geometry according to an implementation of the present disclosure may include one or more processors coupled to memory. The one or more processors may be collectively operable to execute a mapping environment. The mapping environment may be operable to access at least one component design including a plurality of geometric features. The mapping environment may be operable to determine values for geometric attributes associated with the respective geometric features of the component design. The mapping environment may be operable to assign, using a machine learning classifier model, predefined names to the respective geometric features based on the values of the geometric attributes. The mapping environment may be operable to assign values for one or more parameters to the respective geometric features according to the assigned predefined names. A method for feature recognition of design geometry is also disclosed.

Abstract: A heat exchanger includes a hollow fairing, a heat exchanger core disposed in the hollow fairing and comprising a plurality of fluid conduits, at least one external manifold disposed external to the hollow fairing and fluidly coupled to the plurality of fluid conduits, and at least one compliant support structure connected to the at least one external manifold. The at least one compliant support structure includes a first support leg, a second support leg, and a compliant member. The first support leg extends from the at least one external manifold. The second support leg extends from the hollow fairing or an external structure of the heat exchanger toward the first support leg and is separated from the first support leg by a first gap. The compliant member is connected to one or both of the first support leg and the second support leg.

Abstract: An assembly for an aircraft includes an airframe, an aircraft propulsion system mounted to the airframe, and a thermal management system. The aircraft propulsion system includes an open propulsor rotor and a turbine engine core configured to drive rotation of the open propulsor rotor. The thermal management system includes a fluid circuit and a fluid circuit working fluid within the fluid circuit. The fluid circuit includes a propulsion system heat exchanger and an airframe heat exchanger. The propulsion system heat exchanger is arranged with the aircraft propulsion system and configured to transfer heat energy out of a propulsion system working fluid within the aircraft propulsion system into the fluid circuit working fluid. The airframe heat exchanger is arranged with the aircraft airframe and configured to transfer at least some of the heat energy out of the fluid circuit working fluid into an airframe working fluid within the aircraft airframe.

Abstract: In one aspect, a panel for lining a combustor shell of a combustor of a gas turbine engine includes a front surface configured to face a combustion chamber and a back surface configured to face the combustor shell, a plurality of cooling holes extending from the back surface to the front surface, a rail extending from the back surface and defining a perimeter of the panel, and a plurality of studs disposed adjacent to and connected to the rail. The rail is configured to contact the combustor shell. The plurality of studs are configured to be received in a plurality of holes of the combustor shell. The plurality of studs is asymmetrically arranged around the perimeter of the panel.