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US 10,539,037 B2Granted
Device for controlling clearance at the tops of turbine rotating blades
AssigneeSafran Aircraft Engines
InventorsGuillaume Michael Maurice Giliberti, Joël Creti, Gabrijel Radeljak
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Abstract
A device for controlling clearance at the tops of turbine rotating blades. The device comprises shroud supporting rings, abradable ring sectors, elastic centering elements, and a shroud supporting ring sectors inserted radially to the supporting shroud, between the elastic elements and the abradable ring sectors, which are attached to said supporting shroud, which has a volume varying according to temperature, due to the action of fluid supply elements.
Claims15
An assembly comprising:
- a gas turbine comprising an external annular case having a longitudinal axis, and comprising rotating blades, and
- a clearance controlling device positioned topfacing a top of the rotating blades, with said clearance controlling device comprising:
- a shroud supporting rings extending along the longitudinal axis and coaxially integral with the external annular case,
- abradable ring sectors positioned coaxially to the shroud supporting rings so as to locally define a gas jet surrounded by the external annular case,
- elastic means attached to the shroud supporting rings so as to center the abradable ring sectors radially to the shroud supporting rings and hold same thereon,
- a shroud supporting abradable ring sectors inserted radially to the shroud supporting rings, between the elastic means and the abradable ring sectors which are attached to said shroud supporting abradable ring sectors, which has a volume varying according to temperature, and
- means for varying the temperature of the shroud supporting abradable ring sectors and thus for varying the clearance at the tops of the rotating blades, radially to the shroud supporting rings,
- wherein said clearance controlling device comprises, successively, in the outward direction and radially to the longitudinal axis:
- the abradable ring sectors, the shroud supporting abradable ring sectors, the elastic means and said shroud supporting rings, so that the elastic means are radially inserted between the shroud supporting rings and the shroud supporting abradable ring sectors, and
- wherein the means for varying the temperature of the shroud supporting abradable ring sectors are thermally insulated in their expansions out of the shroud supporting abradable ring sectors or exclusively positioned in said supporting shroud so as to focus onto said shroud supporting abradable ring sectors the thermal expansion they impart thereon.
7 more elements
An assembly comprising:
- a gas turbine comprising an external annular case having a longitudinal axis, and comprising rotating blades, and
- a clearance controlling device positioned top acing a top of the rotating blades, with said clearance controlling device comprising:
- a shroud supporting rings extending along the longitudinal axis and coaxially integral with the external annular case,
- abradable ring sectors positioned coaxially to the shroud supporting rings so as to locally define a gas jet surrounded by the external annular case,
- elastic elements attached to the shroud supporting rings so as to center the abradable ring sectors radially to the shroud supporting rings and hold same thereon,
- a shroud supporting abradable ring sectors inserted radially to the shroud supporting rings, between the elastic elements and the abradable ring sectors which are attached to said shroud supporting abradable ring sectors, which has a volume varying according to temperature, and
- elements for varying the temperature of the shroud supporting abradable ring sectors and thus for varying the clearance at the tops of the rotating blades, radially to the shroud supporting rings,
- wherein said clearance controlling device comprises, successively, in the outward direction and radially to the longitudinal axis:
- the abradable ring sectors, the shroud supporting abradable ring sectors, the elastic elements and said shroud supporting rings, so that the elastic elements are radially inserted between the shroud supporting rings and the shroud supporting abradable ring sectors, and
- wherein the shroud supporting abradable ring sectors is aluminium-based.
7 more elements
An assembly comprising:
- a gas turbine comprising an external aim case having a longitudinal axis, and comprising rotating blades, and
- a clearance controlling device positioned topfacing a top of the rotating blades, with said clearance controlling device comprising:
- a shroud supporting rings extending along the longitudinal axis and coa y integral with the external annular case,
- abradable ring sectors positioned coaxially to the shroud supporting rings so as to locally define a gas jet surrounded by the external annular case,
- elastic elements attached to the shroud supporting rings so as to center the abradable ring sectors radially to the shroud supporting rings and hold same thereon,
- a shroud supporting abradable ring sectors inserted radially to the shroud supporting rings, between the elastic elements and the abradable ring sectors which are attached to said shroud supporting abradable ring sectors, which has a volume varying according to temperature, and
- elements for varying the temperature of the shroud supporting abradable ring sectors and thus for varying the clearance at the tops of the rotating blades, radially to the shroud supporting rings, wherein the elements for varying the temperature of the shroud supporting abradable ring sectors comprise ducts supplying the shroud supporting abradable ring sectors with a coolant fluid or a refrigerant fluid,
- wherein said clearance controlling device comprises, successively, in the outward direction and radially to the longitudinal axis:
- the abradable ring sectors, the shroud supporting abradable ring sectors, the elastic elements and said shroud supporting rings, so that the elastic elements are radially inserted between the shroud supporting rings and the shroud supporting abradable ring sectors, and
- wherein the supply ducts are heat-insulated up to the shroud supporting abradable ring sectors so as to focus the variation in temperature onto said shroud supporting abradable ring sectors.
7 more elements
Dependencies are inferred from the claim text.