Turbine blade shroud assembly

Claim 1

In a gas turbine engine having an annular stage of rotatable turbine blades in a hot gas flow path of said engine wherein a gas temperature varies in a range from ambient to a maximum in said engine, a turbine blade shroud assembly comprising: a continuous ceramic barrier ring around said turbine blades having a plurality of operating temperatures increasing from ambient with increasing temperature in said hot gas flow path temperature range, a continuous metal substrate ring on a case of said gas turbine engine around said barrier ring having a plurality of operating temperatures increasing from ambient with increasing temperature in said hot gas flow path temperature range at a rate less than a rate of increase of temperature of said barrier ring for corresponding increases in temperature in said hot gas flow path temperature range and having a coefficient of thermal expansion selected with respect to a coefficient of thermal expansion of said barrier ring such that said barrier ring expands relative to said substrate ring with increasing temperature in said hot gas flow path temperature range from ambient to said maximum hot gas temperature, and a compliant ring between said barrier ring and said substrate ring having an inside surface attached to said barrier ring and an outside surface connected to said substrate ring whereby said barrier ring is connected to said substrate ring.