Patent ID: 8662824
Filing Date: 2014-03-04
Classification: F01D

Abstract:
1. A rotor containment structure for gas turbine engine comprising: an inner containment layer having a single integral body with an outer surface radially oriented away from a rotor, an inner surface radially oriented toward the rotor to define an annular structure about the rotor forming a rotor volume, and a support on the inner surface of the inner containment layer for at least one shroud segment; an outer containment layer providing containment strength to contain blade fragments, the outer containment layer having an outer surface radially oriented away from the inner containment layer, and an inner surface radially oriented toward the inner containment layer to define an annular structure about the inner containment layer, and at least one air passage from the outer surface of the outer containment layer to the inner surface of the outer containment layer for air to pass from an exterior of the outer containment layer to an interior of the outer containment layer; and the inner containment layer being connected at a first end to the outer containment layer and a second free end, with a gap defined between the inner surface of the outer containment layer and the outer surface of the inner containment layer, the gap having an end away from the air passage open to the rotor volume within the inner surface of the inner containment layer, the gap being in direct fluid communication with the air passage such that air flows through the gap, beyond the free second end of the inner containment layer and into the rotor volume.