A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

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.

A bearing assembly for a turbo-engine with a bearing and parts of a bearing temperature detecting device. The bearing includes a main body having a thermoplastic bearing layer. A space is defined in the interior of the main body and of the thermoplastic bearing layer for accommodating parts of the bearing temperature detecting device. The space has a through hole having a first opening in the thermoplastic bearing layer and a second opening located in the main body. The parts include a temperature conducting element, a temperature sensor, and a securing fixture that attaches the temperature conducting element. The first opening of the through hole has a chamfer and the first end of temperature conducting element has a head which is correspondingly shaped to the chamfer in a form fitting manner. The center-axis of the temperature sensor extends transversely to the center-axis of the temperature conducting element.

Disclosed is a method of reducing play in a vane arc segment. The vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the radial flange, and a thermal insulation element is located adjacent the radial flange. The method includes performing a light scan of the radial flange to produce a digital three-dimensional model of the radial flange, and then machining the thermal insulation element in accordance with the digital three-dimensional model to provide a low-tolerance fit between the radial flange and the thermal insulation element that limits play between the airfoil piece and the thermal insulation element.

An airtight seal configured to be mounted on a first turbomachine member, such as a door of a bleed valve, and to bear against a second member of the turbomachine, such as a hub of an intermediate casing, the airtight seal including a retaining device for mounting the seal on the first member; a sealing lip ensuring airtightness through contact and intended to bear against the second member; an anti-return device for the sealing lip reinforcing the rigidity of the airtight seal at the base of the sealing lip.

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 turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition −a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.

A method of joining first and second turbine vanes is provided. The method includes casting and machining each of the first and second turbine vanes, coating each of the first and second turbine vanes with thermal barrier coating (TBC) and executing field assisted sintering technology (FAST) processing to join the first and second turbine vanes.

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 tribological and creep resistant system configured to operate at temperatures in excess of 700° C. A seal body extends between a leading edge and a trailing edge. A first component contact surface is adjacent the leading edge and a second component contact surface is adjacent the trailing edge. The seal body is formed from a high entropy alloy.