A method of making a rub strip includes resin transfer molding an arcuate composite structure. The resin transfer molding step includes inserting a honeycomb core into a mold cavity having an arcuate base so that the honeycomb core assumes an arcuate shape. The resin transfer molding step further includes directing liquid resin into the mold cavity to form the composite structure comprising the liquid resin and the honeycomb core, and curing the liquid resin for a sufficient period of time. The resin transfer molding step further includes removing the composite structure from the mold. The method further includes repeating the resin transfer molding step until a sufficient number of arcuate composite structures are produced. The method further includes coupling a plurality of the arcuate composite structures together to form the rub strip.

A seal arrangement of a gas turbine engine includes a seal carrier, and at least one seal element secured at the seal carrier. The at least one seal element is formed from a moldable silicone rubber material configured for operation in temperature conditions equal to or greater than 500 degrees Fahrenheit. The at least one seal element is positioned and configured to minimize airflow leakage between a first component and a second component while preventing wear of the first component and the second component.

A repair process includes providing a gas turbine engine article that has an elastomeric coating that has an eroded region, plasma etching the elastomeric coating in the eroded region, and applying an elastomeric repair coating on the eroded region.

Provided is an air-conditioning indoor unit. The air-conditioning indoor unit includes a plurality of centrifugal wind wheels, a motor drivingly connected to the plurality of centrifugal wind wheels, an electric control box disposed in an axial direction of the plurality of centrifugal wind wheels, and an evaporator disposed in a radial direction of the plurality of centrifugal wind wheels and obliquely disposed relative to a height direction of the air-conditioning indoor unit. By providing the plurality of centrifugal wind wheels and driving the plurality of centrifugal wind wheels by a same motor, when a size of the air-conditioning indoor unit is large, a constant air volume may be outputted. The electric control box is located in the axial direction of the centrifugal wind wheel and far away from the evaporator, to prevent the electric control box from being splashed by condensed water. In addition, since there is a large space when the centrifugal wind wheel is provided, the electric control box is located in the axial direction of the centrifugal wind wheel to more facilitate an arrangement of the electric control box. The evaporator is disposed obliquely relative to the air-conditioning indoor unit. In this way, a thickness of the air-conditioning indoor unit can be reduced, and heat exchange efficiency can be improved.

An assembly is provided for an aircraft propulsion system. This assembly includes a flowpath wall and an actuation system. The flowpath wall includes an inflatable bladder with a deformable face skin and an interior volume. The deformable face skin includes an exterior surface that forms a peripheral boundary of a flowpath along the flowpath wall. The interior volume extends within the inflatable bladder to the deformable face skin. The actuation system includes an air system and an actuator. The air system is fluidly coupled to the interior volume. The air system is configured to inflate or deflate the inflatable bladder to change a geometry of the exterior surface. The actuator is disposed in the interior volume. The actuator is configured to mechanically apply a force to the deformable face skin to further change the geometry of the exterior surface.

An assembly is provided for an aircraft propulsion system. This assembly includes a propulsor rotor and a flowpath wall. The propulsor rotor is rotatable about an axis. The propulsor rotor includes a plurality of propulsor blades and an inner platform. The propulsor blades are arranged circumferentially about the axis and project radially out from the inner platform. The flowpath wall is next to and downstream of the inner platform. The flowpath wall includes an inflatable bladder and a radial outer surface. The inflatable bladder is configured to change a geometry of the radial outer surface.

An assembly is provided for an aircraft propulsion system. This assembly includes a bladed rotor, an inner flowpath, an outer flowpath, a splitter and a flowpath wall. The bladed rotor is rotatable about an axis. The inner flowpath includes an inner flowpath inlet downstream of the bladed rotor. The outer flowpath includes an outer flowpath inlet downstream of the bladed rotor. The outer flowpath inlet is radially outboard of the inner flowpath inlet. The splitter is disposed radially between and partially forms the inner flowpath inlet and the outer flowpath inlet. The flowpath wall is arranged with the splitter and forms a radial inner peripheral boundary of the outer flowpath. The flowpath wall includes an inflatable bladder and a radial outer surface. The inflatable bladder is configured to change a geometry of the radial outer surface.

An assembly is provided for an aircraft propulsion system. This assembly includes a propulsor rotor and a flowpath wall. The propulsor rotor is rotatable about an axis. The propulsor rotor includes a plurality of propulsor blades and an inner platform. The propulsor blades are arranged circumferentially about the axis and project radially out from the inner platform. The flowpath wall is next to and downstream of the inner platform. The flowpath wall includes an inflatable bladder and a radial outer surface. The inflatable bladder is configured to change a geometry of the radial outer surface.

A fan includes a rotor hub comprising a slot and a blade comprising an airfoil extending from a blade root in a first direction. The blade root is configured to be received in the slot. The fan also includes a deformable spacer situated between the rotor hub and the blade root in the slot, a first blade lock situated at a first side of the slot, and a second blade lock situated at a second side of the slot opposite the first side. At least one of the first and second blade locks includes a tab configured to extend between the blade root and the rotor hub and to compress the spacer such that the spacer exerts a force on the blade in the first direction. A method of assembling a fan and another example fan are also disclosed.

A gas turbine engine includes a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, and defining an engine centerline extending between a forward direction and an aft direction. A disk includes a slot for mounting a composite airfoil to the disk. An axial retainer couples to the disk and secures the composite airfoil to the disk. A compliant portion positioned at the composite airfoil abuts the composite airfoil during operation of the gas turbine engine to secure the composite airfoil to the disk.