Abstract: A connection piece for the articulate connection of a first and a second tube, in particular a first and a second tube of a hot air supply system fed from the power unit of an aircraft, with the possibility of compensating for tolerances, wherein an interval between a tube end of the first tube and a tube end of the second tube is enclosed by a sealing mechanism. The tube ends each have a support ring, wherein the support rings are connected to each other by at least two connection elements arranged outside the sealing mechanism. At least two metal bellows are preferably used as the sealing mechanism, which enable almost maintenance-free operation. Steel ropes are preferably used as connection elements. In particular, tubes with a diameter of up to 160 mm, which are intended, depending on the material used, to conduct media with temperatures of up to 8500 C and pressures of up to 20 bars, can be connected in an articulate manner to each other by means of the connection piece.

Abstract: A connector with an additional tolerance compensation capacity for articulately connecting a first and second pipeline of an engine-powered hot air supply system in an aircraft. One pipe end of the first pipeline is articulately connected by a tie rod with a pipe end of the second pipeline with the formation of a gap. The pipe ends each include a bearing ring incorporating an essentially centrically arranged receptacle for attaching the tie rod. The receptacle is connected with a bearing ring inner surface by at least two braces pointing radially outward. The opposing pipe ends are enveloped by a sealing unit for sealing the gap. A first end of the tie rod includes an adjusting unit in the form of a screw-on ball head for length adjustment while the second end includes a fixed ball head.

Abstract: The invention relates to a connection piece (1) for the articulate connection of a first and a second tube (3, 5), in particular a first and a second tube (3,5) of a hot air supply system fed from the power unit of an aircraft, with the possibility of compensating for tolerances, wherein an interval (40) between a tube end (2) of the first tube (3) and a tube end (4) of the second tube (5) is enclosed by a sealing mechanism (6). According to the invention both tube ends (2, 4) each have a support ring (14, 15), wherein the support rings (14, 15) are connected to each other by at least two connection means arranged outside the sealing mechanism (6). At least two metal bellows (7, 8) are preferably used as the sealing mechanism (6), which enable almost maintenance-free operation. Steel ropes (22, 23) are preferably used as connection means.

Abstract: The invention relates to a connector (1) for hinging a first and second pipeline (3, 5), in particular a first and second pipeline (3, 5) of an engine-powered hot air supply system in an aircraft, with an additional tolerance compensation capacity, wherein one pipe end (2) of the first pipeline (3) is hinged by a tie rod (32) with a pipe end (4) of the second pipeline (5) with the formation of a gap (39). According to the invention, the opposing pipe ends (2, 4) are enveloped by a sealing unit, in particular a metal bellows (11), for sealing the gap (39), and the first end (33) of the tie rod (32) has an adjusting unit (35) for length adjustment. Because the adjusting unit 35 is arranged on the edge, the connector 1 according to the invention is easy to assemble, wherein a separable V-flange joint is provided in the area of the pipe end (2) of the first pipeline (3).

Abstract: An insulation arrangement for pipes, especially for pipes of a pneumatic system in a passenger transport aircraft, essentially includes at least one insulation layer (6) as well as an outer sheath (3) consisting of titanium foil (31). The outer sheath (3) is connected, in a first end section (32) and in a second end section (33), respectively with a termination profile (7), and thereby a shell (9) with at least one longitudinal seam (13) is formed, into which the insulation layer (6) is insertable.

Abstract: An insulation arrangement for pipes, especially for pipes of a pneumatic system in a passenger transport aircraft, essentially comprises at least one insulation layer (6) as well as an outer sheath (3) consisting of titanium foil (31). The invention consists in that the outer sheath (3) is connected, in a first end section (32) and in a second end section (33), respectively with a termination profile (7), and thereby a shell (9) with at least one longitudinal seam (13) is formed, into which the insulation layer (6) is insertable.