Abstract: The invention concerns a system for controlling heat expansion and thermal stress in a gas turbine disk. The system includes perforated plates mounted close to and facing at least one surface of the disk, particularly opposite its rim and around its thick inner bored section. Conduits are provided for bleeding cold air and hot air from various stages of the compressor or from the turbine and for injecting cold air toward the rim of the disk and hot air toward its thick inner bored section through the corresponding perforated plates at the beginning of each acceleration, and, preferentially, during deceleration, for injecting hot air toward the said rim and cold air toward said inner bored section. The invention applies particularly to gas turbines used to propel aircraft.

Abstract: An improved guide vane shroud sealing device is disclosed wherein the shroud is formed from a plurality of segments, each segment having interengaging, "Z" shaped edges. The "Z" edges each have a mid-portion extending parallel to the rotational plane of a rotor blade wheel, and leading and trailing edge portions extending from this mid-portion to the leading and trailing edges of the shroud segments. A honeycomb packing structure seals the inner surface of the guide vane shroud in conjunction with labyrinth sealing fins on the rotor wheel. The honeycomb structure is oriented such that opposite sides of each cell which are joined to adjacent cells extend at an angle of approximately 60.degree. to the rotational plane of the rotor blade wheel.

Abstract: A turbojet turbine stage having air cooling of the turbine wheel disc is disclosed which has, on the one hand, devices for blowing in a flow of air A in the direction of the upstream surface of the disc (20) intended in particular to flow into the several passages delimited by the periphery (22) of the disc and by the shanks (14) and platforms (12) of the blade feet (11) of the wheel, and, on the other hand, a number of trough-shaped dampers (30) each of which is inserted in a passage and supported by its edges against the periphery of the disc while its back pushes against the platforms delimiting the passage. The upstream edge of each damper forms a peak (33) which extends beyond the upstream side of the disc.

Abstract: A sealing device disposed between two turbomachine elements traversed by gases, particularly between a combustion chamber and a high pressure turbine nozzle support. The device includes an independent collar supported by first and second bearing surfaces on the elements which are to be connected in leaktight manner, the collar being constructed of a material having a thermal expansion coefficient which is different from that of the elements which it interconnects so as to ensure a leaktight connection between the elements.

Abstract: A device for adjusting the clearance between moving blades and the ring of a turbine wherein the ring includes a cylindrical sleeve, a perforated partition, and a wall, which together form an enclosure. Boreholes receive tubular elements which fit together with coaxial boreholes provided in opposite walls of a distribution chamber. The chamber communicates with pipes which admit heat regulating air. Alternating tubular elements traverse the perforated wall and the chamber to evacuate exhaust gas through pipes.