Abstract: A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Abstract: An outlet guide vane assembly in a gas turbine engine is presented. The outlet guide vane assembly includes an inner shroud and an outlet guide vane having an inner platform. The inner shroud has a flange arranged at aft side that is bolted to a flange of the inner platform arranged at forward side. The inner shroud flange has a protrusion that engages a recess of the inner platform flange forming a form fit connection interface between the inner shroud and the outlet guide vane. The inner platform has shiplaps arranged at two circumferential sides that overlap shiplaps of an adjacent inner platform forming a form fit connection interface between adjacent outlet guide vanes. The outlet guide vane assembly includes a plurality of segments circumferentially arranged. Each segment includes a plurality of outlet guide vanes assembled to an inner shroud.

Abstract: An outlet guide vane assembly in a gas turbine engine is presented. The outlet guide vane assembly includes an inner shroud and an outlet guide vane having an inner platform. The inner shroud has a flange arranged at aft side that is bolted to a flange of the inner platform arranged at forward side. The inner shroud flange has a protrusion that engages a recess of the inner platform flange forming a form fit connection interface between the inner shroud and the outlet guide vane. The inner platform has shiplaps arranged at two circumferential sides that overlap shiplaps of an adjacent inner platform forming a form fit connection interface between adjacent outlet guide vanes. The outlet guide vane assembly includes a plurality of segments circumferentially arranged. Each segment includes a plurality of outlet guide vanes assembled to an inner shroud.

Abstract: A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Abstract: A closing assembly for closing a blade ring inserted into a circumferential T-groove of a blade support of a turbomachine, having two insertion elements, each has a C-shaped basic form having a resting leg, retention leg, and connection leg connecting the resting leg and the retention leg and is designed to reach around a ridge of the T-groove. The resting leg reaches over the ridge and the retention leg reaches under the ridge, and an intermediate element, is positioned between the insertion elements to prevent the insertion elements from moving to the center of the T-groove. The intermediate element reaches below the retention legs of the insertion elements in the assembled state, and a positioning element is associated with the intermediate element, which is supported between the groove base of the T-groove and the intermediate element and to position the intermediate element at a desired distance from the groove base.

Abstract: A rotor blade arrangement for a turbomachine having a blade carrier, on whose outer circumferential surface there is formed a circumferential T-shaped slot, having a blade ring which has a plurality of blades and spacers, that are inserted in alternation into the T-shaped slot, and having support elements that are braced between the blades and spacers on one hand and a base of the T-shaped slot on the other hand such that the blades and spacers are pressed radially outward, a separate support element being assigned to each spacer and being releasably held thereon, in particular secured in a clamping manner. A method includes assembling a rotor blade arrangement.

Abstract: A rotor blade arrangement for a turbomachine having a blade carrier, on whose outer circumferential surface there is formed a circumferential T-shaped slot, having a blade ring which has a plurality of blades and spacers, that are inserted in alternation into the T-shaped slot, and having support elements that are braced between the blades and spacers on one hand and a base of the T-shaped slot on the other hand such that the blades and spacers are pressed radially outward, a separate support element being assigned to each spacer and being releasably held thereon, in particular secured in a clamping manner. A method includes assembling a rotor blade arrangement.

Abstract: A closing assembly for closing a blade ring inserted into a circumferential T-groove of a blade support of a turbomachine, having two insertion elements, each has a C-shaped basic form having a resting leg, retention leg, and connection leg connecting the resting leg and the retention leg and is designed to reach around a ridge of the T-groove. The resting leg reaches over the ridge and the retention leg reaches under the ridge, and an intermediate element, is positioned between the insertion elements to prevent the insertion elements from moving to the center of the T-groove. The intermediate element reaches below the retention legs of the insertion elements in the assembled state, and a positioning element is associated with the intermediate element, which is supported between the groove base of the T-groove and the intermediate element and to position the intermediate element at a desired distance from the groove base.

Abstract: A blade ring for an axial turbomachine is provided, having a blade carrier with a number of retaining grooves and corresponding blades, the blade roots of which are inserted into the retaining grooves, wherein the blades, on the underside facing toward a groove base of the retaining groove, have a recess, the base of which is at least partially obliquely inclined relative to the groove base and in which recess is arranged one wedge-shaped clamping element for pressing the blade root against the support flanks. A spring element is provided in each recess, the spring force of which acts on the respective wedge-shaped clamping element along the retaining groove. Means are provided with which the wedge-shaped clamping element can be displaced temporarily into a position in which the blade root is seated in the retaining groove with play.