Abstract: A device for varying the section of the throat of a turbine nozzle, the nozzle being formed by a plurality of stationary vanes extending radially between outer and inner annular platforms and spaced apart from one another in order to define a throat presenting a minimum flow section. The device comprises an annular element having a coefficient of expansion that is less than that of the platforms of the nozzle, the annular element being secured to the outer platform and being capable of taking up two positions: one position corresponding to no expansion of the platforms, in which the element provides continuity for the profile of the flow passage; and another position corresponding to the platforms having expanded, in which position the element projects into the flow passage so as to reduce its section.

Abstract: A gas turbine, in particular a high pressure turbine for an airplane engine, the turbine comprising moving blades (10) with tips that are fitted with radially slidable stubs (26) for being pressed in operation by centrifugal forces against the inside surface of the casing (16) of the turbine in order to eliminate radial clearance between said surface and the tips of the blades (10).

Abstract: A diffuser for a gas turbine engine, said diffuser being disposed between a last stage of a turbine and an exhaust casing, and comprising an outer annular wall and an inner annular wall together defining an annular passage for fluid that diverges in the flow direction of said fluid, at least one of the annular walls including a plurality of orifices leading from said annular passage to at least one collecting box leading to means for exhausting a fraction of said fluid so as to reduce the flow speed of said fluid in said annular passage.

Abstract: A gas turbine, in particular a high pressure turbine for an airplane engine, the turbine comprising moving blades (10) with tips that are fitted with radially slidable stubs (26) for being pressed in operation by centrifugal forces against the inside surface of the casing (16) of the turbine in order to eliminate radial clearance between said surface and the tips of the blades (10).

Abstract: A diffuser for a gas turbine engine, said diffuser being disposed between a last stage of a turbine and an exhaust casing, and comprising an outer annular wall and an inner annular wall together defining an annular passage for fluid that diverges in the flow direction of said fluid, at least one of the annular walls including a plurality of orifices leading from said annular passage to at least one collecting box leading to means for exhausting a fraction of said fluid so as to reduce the flow speed of said fluid in said annular passage.