A sealing assembly and a turbomachine including the sealing assembly are provided. The sealing assembly includes a sealing body configured to be inserted into an insertion hole of a second component adjacent to a first component, and a sealing protrusion, formed on one circumferential side of the sealing body, protruding toward one circumferential direction from the sealing body and configured to be inserted into a sealing groove formed on the other circumferential side of a sealing body of the first adjacent sealing assembly, the sealing body of the first adjacent sealing assembly being adjacent to the sealing body in a circumferential direction.

In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.

A combustor includes a liner having an outlet end to pass combustion gas and a liner flange protruding outward from the outlet end; a transition piece to discharge combustion gas from the liner to a turbine, the transition piece having an inlet end for coupling to the outlet end of the liner and a transition piece flange protruding outward from the inlet end to face the liner flange; and a first elastic support installed on the liner flange to protrude toward the transition piece flange. A force applied from the transition piece elastically deforms an elastic arch of the first elastic support, which includes a movable support that is spaced apart from the liner flange if the force applied from the transition piece does not primarily deform the elastic arch. An auxiliary elastic support installed inside the first elastic support elastically deforms if the force secondarily deforms the elastic arch.

A seal structure may comprise a cavity defined at least partially by an axial surface and a radial surface. A brush seal may be disposed in the cavity. The brush seal may comprise a bristle pack and a backing plate coupled to the bristle pack. A first surface of the backing plate may contact the axial surface, and a second surface of the backing plate may contact the radial surface.

A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

A support assembly for a turbocharger defining a system axis, the support assembly comprising a housing assembly and a bearing assembly. The housing assembly comprises a housing defining at least one support groove and a seal plate. The bearing assembly comprises an outer sleeve defining at least one support tab. The at least one support tab is sized and dimensioned such that, when the outer sleeve is supported by the housing member in a desired orientation, the support tab is within the support groove such that movement of the outer sleeve along the system axis relative to the housing member is inhibited. The seal plate may be configured to define at least one anti-rotation projection arranged relative to the support tab to inhibit rotation of the outer sleeve about the system axis relative to the housing member.

A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.

A variable guide vane assembly has: variable guide vanes having airfoils extending from inner ends to outer ends, the variable guide vanes pivotable about respective spanwise axes between one or more open positions and a closed position, in the closed position, trailing edge regions of the airfoils sealingly engage leading edge regions of adjacent ones of the airfoils to block an air flow; an outer wall extending around the central axis, the outer ends of the variable guide vanes pivotably engaged to the outer wall; and an inner wall extending around the central axis, the inner ends of the variable guide vanes pivotably engaged to the inner wall, the inner wall defining inner faces distributed about the central axis, a shape of the inner faces complementary to a shape of the inner ends of the airfoils to form a seal when the variable guide vanes are in the closed position.

A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate and a backing plate that extend circumferentially about an assembly axis. The backing plate includes a main body and a first set of abutments that extend outwardly from the main body to abut the first side plate. A first set of pockets are established between adjacent abutments of the first set of abutments. A first brush seal is between the first side plate and the backing plate. Sections of the first brush seal received in respective pockets of the first set of pockets are dimensioned to join together to establish a first sealing relationship with a first gas turbine engine component. A method of assembly is also disclosed.