Shroud segment for a turbomachine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsDan Roth-Fagaraseanu, Thomas Wunderlich
Life of this patent
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Abstract
On an aircraft engine with a shroudless rotor wheel arranged in a flow duct, the flow duct includes a shroud segment (1) formed by a ceramic rubbing coating (3) which, while having good thermal conductivity, is highly-temperature resistant, attaches firmly to the metallic substrate (2) and is abradable by the tips of the rotor wheel to form a sealing gap as narrow as possible, this rubbing coating, owing to the lack of self-insulation, being coolable from a free side of the metallic substrate and, therefore, permitting for working gas temperatures occurring in high-pressure turbines and coating thicknesses sufficient for abrasion.
Claims24
A shroud segment for a turbomachine, the turbomachine having a flow duct, and a bladed rotor wheel arranged in the flow duct, which flow duct and bladed rotor wheel perform a relative rotary movement and which are flown by a hot working gas, the shroud segment comprising:
- a metallic substrate having an outer surface exposed to a cooling gas flow external of the flow duct of the turbomachine;
- and
- a ceramic rubbing coating having an inner surface and an outer surface, the ceramic rubbing coating outer surface bonded directly to at least one of an inner surface of the metallic substrate and a metallic bond layer attached directly to the metallic substrate, the ceramic rubbing coating inner surface being abradable by blade tips of the bladed rotor wheel for the formation of a narrow sealing gap, wherein the rubbing coating comprises a high-temperature resistant, thermally conductive ceramic material which is cooled through the metallic substrate by the exposure of the outer surface of the metallic substrate to the cooling gas flow, wherein the ceramic material is a spinel and the coefficient of thermal conductivity of the rubbing coating is ≧2.0 W/mK at an operating temperature;
- the thickness of the rubbing coating being more than 0.4 mm.
A shroud segment for a hot gas flow duct of a turbomachine, comprising:
- a metallic substrate having an outer surface exposed to a cooling gas flow external of the hot gas flow duct of the turbomachine, and
- a ceramic rubbing coating having an inner surface and an outer surface, the ceramic rubbing coating outer surface bonded directly to at least one of an inner surface of the metallic substrate and a metallic bond layer attached directly to the metallic substrate, the ceramic rubbing coating inner surface being abradable by blade tips of a bladed rotor wheel of the turbomachine for the formation of a narrow sealing gap,
- the rubbing coating comprising a high-temperature resistant, thermally conductive ceramic material which is cooled through the metallic substrate by the exposure of the outer surface of the metallic substrate to the cooling gas flow, wherein the ceramic material is a spinel and the coefficient of thermal conductivity of the rubbing coating is ≧2.0 W/mK at an operating temperature;
- the thickness of die rubbing coating being more than 0.4 mm.
Dependencies are inferred from the claim text.