A seal assembly configured to seal against a surface of a seal depressor is disclosed. The seal assembly includes a body member configured to elastically expand from an original state into an expanded state. The body member exerts a sealing pressure against the surface of the seal depressor when in the expanded state. The seal assembly also includes one or more actuation members constructed from a shape memory material having a high energy state and a low energy state. The one or more actuation members are configured to urge the body member of the seal assembly from the original state into the expanded state when the shape memory material transitions from the low energy state to the high energy state.

An adsorption device for compressed gas, is provided with a vessel with an inlet for the supply of a compressed gas to be treated, and an outlet for treated gas and an adsorption element is affixed in the vessel. The adsorption element extends along the flow direction of the compressed gas to be treated, between the inlet and the outlet. The adsorption element has a monolithic supporting structure that is at least partially provided with a coating that contains an adsorbent.

A shaft mounting assembly includes an elongate shaft with an outer surface having a substantially circular cross-section and a cylinder having an inner surface defining a bore housing the shaft. A spring having a substantially circular discontinuous band with correspondingly shaped axially arcuate inner and outer surfaces. One of the surfaces comprises a groove, and the spring is positioned in the groove with both axial edges of the band located therein. In a de-energised state of the spring, the height of the band is greater than the depth of the groove, a portion of the band between the axial edges protruding out of the groove, the axial width of the band being less than the width of the groove; and, an energised state with the spring compressed within the bore to reduce the height of the band and increase the axial width compared to the de-energised state.

A radially flexible connection joint for a gas turbine engine includes an exhaust manifold flange operatively coupling an exhaust cylinder to an exhaust manifold of the gas turbine engine. The exhaust cylinder includes a cylindrical flange that extends radially outwardly from a rotation axis of the gas turbine. The cylindrical flange defines a downstream axial face. The exhaust manifold is positioned downstream from the exhaust cylinder. The exhaust manifold includes an upstream edge. The exhaust cylinder and the exhaust manifold are substantially coaxial with the rotation axis of the gas turbine. The exhaust manifold flange has a bellows portion that extends radially between the cylindrical flange of the exhaust cylinder and the upstream edge of the exhaust manifold. The bellows portion permits relative radial motion of the exhaust cylinder and the exhaust manifold.

A sealing apparatus for a gas turbine engine includes: a first component; a second component positioned in proximity to the first component such that cavity is defined between the first and second components; a resilient seal disposed in the cavity so as to block gas flow between the first and second components, the resilient seal having a first contact surface contacting the first component and a second contact surface contacting the second component; and wherein the resilient seal is configured so as to produce a rolling movement in response to relative movement of the first and second components.

Flexible seal assemblies having a relatively low torsional rigidity and high longitudinal flexure to thereby allow the flexible seal assembly to flex between adjacent components and maintain a seal, even when movement between adjacent components occurs, is described. In some embodiments, the flexible seal assembly includes one or more layers of metal matrix material, the metal matrix material being comprised of a plurality of short segments of thin wire arranged randomly and sintered together to form a semi-rigid sheet. The one or more layers of metal matrix material can be sandwiched between an upper casing and a lower casing of a metal alloy casing. In various embodiments, additional features are provided for helping to make sure the seal assembly stays together, such as spot welds formed through the seal assembly, an S-shaped casing, and a recess/protrusion feature provided on adjacent layers of metal matrix material.

A compressor may include a shell, first and second scroll members, a floating seal, a muffler plate, and a wear ring. The shell defines a discharge chamber and a suction chamber. The floating seal may sealingly engage the second scroll member. The muffler plate defines the discharge chamber and the suction chamber. The wear ring may sealingly engage the muffler plate and the floating seal such that the wear ring, the muffler plate, and the floating seal fluidly isolate the discharge chamber from the suction chamber. The muffler plate may include an axially facing surface that contacts the wear ring. The axially facing surface may include an annular recess. The wear ring may at least partially cover the annular recess. The annular recess may provide clearance between the muffler plate and the wear ring to allow the wear ring to deflect relative to the muffler plate during compressor operation.

An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.

A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.

A seal assembly that may be for turbine engine includes a first wall defining in-part a first flowpath and a second wall defining in-part a second flowpath having a pressure that is greater than the first flowpath. The second wall has a plurality of metering apertures in fluid communication between the second flowpath and a cavity defined by and between the first and second walls. The walls may be convoluted and generally, resiliently compressed between two substantially opposing surfaces for providing a seal between the two flowpaths.