A gas turbine engine has: an annular gaspath extending around a central axis and defined between a first casing and a second casing; and a variable guide vane (VGV) assembly having: variable guide vanes, the variable guide vanes having airfoils extending between first and second stems at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes; a unison ring rotatable about the central axis, the unison ring operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, and a segmented bushing having bushing segments circumferentially distributed around the central axis, the bushing segments radially supported and axially constrained by the first casing, the unison ring rollingly engaged to the first casing via the bushing segments, the unison ring axially and radially constrained to the first casing via the bushing segments.

A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

This exit seal is for connecting an exit flange of a combustor and a shroud in a stator blade of a turbine. The exit seal is equipped with: a seal body that extends in a circumferential direction; and a lid member disposed at a circumferential end of the seal body. The seal body comprises one or more recessed sections that are recessed in a radial direction or in an axial direction and extend in the circumferential direction. At a position of the circumferential end of at least one recessed section among the one or more recessed sections, the lid member is disposed so as to overlap, in the axial direction and the radial direction, with a recessed space formed by the one recessed section.

A centering device (10) for centering a turbine housing (40) with respect to a central axis (33) of a radial turbine of a turbo system is described. The centering device (10) includes a ring-shaped body (11) having an outer diameter D1 and an inner diameter D2, wherein a ratio of D1/D2 is ≤2. Additionally, the centering device (10) includes two or more centering elements (16) provided on a side surface (12) of the ring-shaped body (11) for engaging with respective complementary centering elements (21) provided on a bearing housing (20). The two or more centering elements (16) are configured for allowing a radial thermal expansion of the ring-shaped body (11) during engagement of the two or more centering elements (16) with the respective complementary centering elements (21). Further, a turbo system, including such a centering device as well as a method of centering a turbine housing are described.

A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

A turbocharger includes a turbine housing. The turbine housing includes a turbine inlet wall defining an inlet passage, an exducer shroud wall defining an exducer interior, a turbine outlet wall defining an outlet passage, a wastegate port wall defining a wastegate channel, and a bushing wall coupled to the wastegate port wall and defining a bushing boss extending along a bushing axis, and a valve seat disposed about the wastegate channel. The turbocharger also includes a wastegate assembly. The wastegate assembly includes a valve element engageable with the valve seat. The wastegate port wall is disposed outside of the exducer interior such that the wastegate port wall and the bushing wall are configured to be thermally decoupled from the turbine inlet wall and such that relative displacement between the valve seat and the bushing axis is reduced during operation of the turbocharger.

In order to alleviate a mismatch problem of thermal deformation, in all directions, of a connecting and installing structure between a CMC turbine outer annular component and a metal intermediate casing, a connector and an anti thermal mismatch connecting device are provided. The rod part of the connector comprises a subtractive hollow section and a cylindrical section. The subtractive hollow section is composed of a central shaft, a plurality of supporting rib plates extending outwards from a peripheral surface of the central shaft and inclined radially relative to the central shaft, and a plurality of outer annular plates arranged around the central shaft, with a circumferential gap between adjacent outer annular plates. The supporting rib plate is connected with the central shaft and the outer annular plate, and the central shaft is connected with the cylindrical section. The anti thermal mismatch connecting device the connector.

A gas turbine engine having a fluid transfer connection is provided. The gas turbine engine includes a first component configured to channel a flow of air from a portion of the gas turbine engine; a second component configured to receive the flow of air from the first component, wherein the first component and the second component are movable relative to one another; a sleeve portion disposed between the first component and the second component; and a spoolie device disposed within the sleeve portion, the spoolie device having elliptical shaped opposing ends, wherein the spoolie device bridges the first component and the second component to channel the flow of air from the first component to the second component.

A seal device is configured so that seal properties can be held over a long period of time. A seal device 1 inserted into and disposed between grooves each formed at first and second components which are adjacent to each other and collectively form a housing structure includes a first seal member inserted into the groove of the first component, a second seal member inserted into the groove of the second component, and a partitioning member extending between the first and second seal members to partition a space between the grooves of the first and second components and arranged movably relative to the first and second seal members.