Gas turbine compressor with adaptive blade tip seal assembly

A gas turbine engine having a compressor section optimized to provide enhanced efficiency during several operating conditions, said compressor section comprising:

• a vane carrier;
• a ring segment assembly disposed within said vane carrier, said ring segment assembly characterized by a radially-outward backing element, a radially-inward tip-facing element, and at last one biasing element adapted and arranged to dynamically position said tip-facing element with respect to said backing element;
• wherein said backing element is characterized by a first coefficient of thermal expansion and said tip-facing element is characterized by a second coefficient of thermal expansion, said first coefficient of thermal expansion being higher than said second coefficient of thermal expansion;
• wherein said backing element includes a first mating surface and said tip-facing element includes a second mating surface, said mating surfaces adapted and arranged to provide positive engagement of said engage said first engagement notch;
• wherein said at least one biasing element is positioned and adapted to cooperatively urge said tip-facing element against said backing element;
• and
• whereby said tip-facing element and said backing element, are alternately in contact along an interface disposed therebetween during a first operating condition and spaced apart along an interface an interface gap disposed therebetween during a second operating condition, and whereby said at least biasing element maintains contact between said first and second mating surfaces during both operating conditions.