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, said ring segment assembly being characterized by an arcuate ring segment angle;
• 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 characterized by an interface angle and said tip-facing element includes a second mating surface, said mating surfaces adapted and arranged to provide positive engagement;
• wherein said backing element and said tip-facing element cooperate with said at least one biasing element to urge said tip-facing element and said backing element into said positive engagement;
• wherein said at least one biasing element and said interface angle are selected to provide a biasing force sufficient to overcome a friction force generated along the first and second mating surfaces;
• 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 gap disposed therebetween during a second operating condition, and whereby said at least one biasing element maintains contact between said first and second mating surfaces during both operating conditions.