Abstract: The seal arrangement for a mid turbine frame of a gas turbine, especially an aircraft gas turbine, includes a tubular fluid duct, especially an oil duct, which extends along an axial direction, a bearing sleeve surrounding the fluid duct radially outside and in the peripheral direction, and at least one seal ring arranged between fluid duct and bearing sleeve in the radial direction, this ring being arranged around the fluid duct. The seal ring is taken up at least partly in a groove provided in the bearing sleeve.

Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.

Abstract: The invention relates to a pipe arrangement with a fluid-carrying inner pipe and an outer pipe that surrounds the inner pipe, wherein spacers are arranged between the inner pipe and the outer pipe in such a way that a gap is formed between the inner pipe and the outer pipe, wherein the outer pipe is joined at its first axial end section in a material-bonded or cohesive manner to a first spacer, which is joined to the inner pipe in a material-bonded manner, and wherein the outer pipe is arranged at its second axial end section at least partially with a radial spacing to a second spacer, which is joined to the inner pipe in a material-bonded manner.

Abstract: The seal arrangement for a mid turbine frame of a gas turbine, especially an aircraft gas turbine, includes a tubular fluid duct, especially an oil duct, which extends along an axial direction, a bearing sleeve surrounding the fluid duct radially outside and in the peripheral direction, and at least one seal ring arranged between fluid duct and bearing sleeve in the radial direction, this ring being arranged around the fluid duct. The seal ring is taken up at least partly in a groove provided in the bearing sleeve.

Abstract: The invention relates to a pipe arrangement (10) with a fluid-carrying inner pipe (12) and an outer pipe (14) that surrounds the inner pipe (12), wherein spacers (20, 24) are arranged between the inner pipe (12) and the outer pipe (14) in such a way that a gap (16) is formed between the inner pipe (12) and the outer pipe (14), wherein the outer pipe (14) is joined at its first axial end section (18) in a material-bonded or cohesive manner to a first spacer (20), which is joined to the inner pipe (12) in a material-bonded manner, and wherein the outer pipe (14) is arranged at its second axial end section (22) at least partially with a radial spacing (26) to a second spacer (24), which is joined to the inner pipe (12) in a material-bonded manner.

Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.