Shrouds for gas turbine engines and methods for making the same

A gas turbine engine, comprising:

• a fan assembly having a rotatable disk and a plurality of blades for affecting a flow of air passing thereover during use, each blade having a blade root and a blade tip disposed opposite said blade root, each blade being attached to said rotatable disk adjacent said blade root, and each blade tip having a leading edge and a trailing edge;
• a self-supporting shroud ring extending from the leading edge to the trailing edge of each blade tip and in interfering contact with each blade tip when said rotatable disk is stationary, the shroud ring being formed of an organic matrix composite material containing a boron, graphite or carbide fiber component and being unconstrained by welding or mechanical connector in the axial tangential directions, and the interfering contact being between about 0.01 and about 0.1 inches;
• a core engine disposed downstream of said fan assembly, the core engine including a compressor, a first turbine assembly downstream of said compressor, a first shaft connecting said first turbine assembly to said compressor whereby said compressor is driven by said first turbine assembly, and a combuster disposed between said compressor and said first turbine assembly;
• and
• a second turbine assembly downstream of said core engine and rotatably connected to said fan assembly by a second shaft, said fan assembly being rotatably driven by said second turbine assembly.