Importance

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Abstract

A ceramic shroud ring is located within a gas turbine engine in abutment with the inner surface of the metal engine case. The ring is characterized in that it is divided by a split extending between the radially inner and outer surfaces. The natural resilience of the ring is such that it tends to open out when unconstrained, the ring thereby following the contour of the engine case as its diameter changes according to temperature. The engine case is provided with a pair of circumferential flanges directed inwardly and abutting respectively against high pressure upstream and low pressure downstream portions of the ring to define an annular cavity about the ring, and the ring is provided on its downstream face with at least one radial slot giving low pressure air access to the annular cavity. Within the thickness of the ring a slot extends from the upstream face to the downstream face and intersects the split in the ring. A seal strip occupies the slot.

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First Claim