A durable light weight, high temperature acoustic CMC liner system. A thin ceramic matrix composite skin, also referred to as a facesheet, forms an outer layer of a cell in the CMC liner system, forming the boundary with the flow of hot gases in the exhaust. A backplate forms the opposite boundary for the cell. The truss structure is formed between the backplate and the facesheet and provides the cell with strength. When the CMC system replaces the metal liner, the backplate thickness is increased so that it is about the thickness of the liner system that it replaces. The truss structure extends between the backplate and the facesheet, forming channels or volumetric spaces. These channels or volumetric spaces are filled with high temperature air permeable acoustic materials that attenuate sound propagated by cooling air in the acoustic range.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver is coupled to a closed form refrigeration system having an evaporator, a compressor, a condenser, an expansion valve, and a refrigerant contained therein. The thermal driver is cooled by the refrigeration system, and the rate of cooling causes expansion and contraction of the thermal driver that is translated by linkages into axially forward and aft motion of the shroud.

An assembly in a turbine engine having a dynamically moveable flowpath boundary member for encasing a rotatable bladed disc and maintaining a clearance gap between the flowpath boundary member and the blade tips of the bladed disc. The assembly comprises a static casing, a flowpath boundary member carried by the casing, and a refrigeration system configured to remove heat from the flowpath boundary member to thereby thermally expand and contract the flowpath boundary member to control blade tip clearance.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, 35% nickel, 12.0-20.0% cobalt, 5.0-15.0% aluminum, and 5.0-15.0% chromium.

A turbine engine cleaning system includes a foaming nozzle. The foaming nozzle includes a wall having a thickness between an outer surface of the wall and an inner surface of the wall. The outer surface of the wall is configured to contact a detergent in which the foaming nozzle is configured to be disposed. The inner surface of the wall surrounds an inner plenum of the foaming nozzle, and the inner plenum is configured to receive an aerating gas. The foaming nozzle also includes a first row of first through holes fluidly coupled to, and extending between, a first row of first through hole inlets at the inner surface of the wall and a first row of first through hole outlets at the outer surface of the wall. The foaming nozzle also includes a second row of second through holes disposed axially adjacent to the first row of second through holes with respect to a longitudinal axis of the inner plenum, where the second row of second through holes is fluidly coupled to, and extending between, a second row of second through hole inlets at the inner surface of the wall and a second row of second through hole outlets at the outer surface of the wall. The foaming nozzle also includes cross-sections of the first through holes and the second through holes having regular shapes.

This composite-material blade formed by using a fiber-reinforced resin containing a resin and reinforcing fibers is provided with: a base material part provided on the inner surface of the composite-material blade; and a first cover part for covering the outer surface of the base material part. The base material part is formed by using a carbon fiber-reinforced resin containing a first resin and carbon fibers. The first cover part is formed from an elastic polymer fiber-reinforced resin containing a second resin and elastic polymer fibers, and has more resistance to impact than the base material part.

An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator. The locator includes a fusible guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. The fusible guide pin is configured to fracture to absorb energy while the catcher pin limits system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing). The locator can further include an anti-rotation pin extending from the plate member and configured to be received by the auxiliary component. The anti-rotation pin prevents rotation of the locator, about a third pin of the locator, with respect to the auxiliary component when the fusible guide pin is broken.

A surface treatment device for applying a surface treatment to an inner surface of a hollow engine shaft extending longitudinally along a shaft axis and having an axial shaft length to be treated. The device includes a supply of a surface treatment agent and an elongated rod extending from a proximal end to a distal end with an applicator disposed at the distal end. The elongated rod is insertable inside the hollow engine shaft. An applicator is disposed at the distal end of the elongated rod and wetted with the surface treatment agent. The applicator is engageable with the inner surface of the hollow engine shaft for applying the surface treatment agent to the inner surface of the hollow engine shaft. A pair of markers are disposed on the elongated rod and axially spaced apart from one another at a first axial distance corresponding to the axial shaft length.

The invention relates to a casing (3) of an aircraft turbomachine, said casing comprising: an annular shell (9) extending around an axis A and made of a composite material comprising fibres which are woven and embedded in a resin, an annular layer (4) made of abradable material extending inside the shell, around axis A, and obtained by spreading and polymerising a paste, andsupport panels (10) which extend around axis A and are interposed between the shell and the abradable layer.

The invention relates to a composite blade (5) for a turbine engine rotor, for example, an unducted propeller, comprising a skin (6) made of woven fibres forming the outer profile of the blade and an attachment (11) with cylindrical geometry in the direction of the span emerging from the blade root (9), which attachment is intended to retain the blade (5) on a hub of the rotor, characterised in that it further comprises a spar (16) having a hollow tube structure made of braided carbon fibres, fixed to the attachment (11) and extending inside the skin (6) over at least part of the span of the blade (5). The invention also relates to a propeller comprising said blade and to a method for manufacturing said blade.