Patent ID: 9097139
Filing Date: 2015-08-04
Classification: F01D,F02K,Y02T

Abstract:
1. A containment casing for containing a blade or a blade fragment of a gas turbine engine, the containment casing comprising: a radially outer layer; a radially inner layer; an intermediate energy absorbing layer disposed between the radially outer layer and the radially inner layer; and a retention framework disposed axially and circumferentially along the containment casing and extending substantially radially inwardly through the intermediate energy absorbing layer, the retention framework terminating in a plurality of radially inwardly facing engagement features, the inwardly facing engagement features are located immediately adjacent to the inner layer and taper radially inwardly in a direction oriented towards a surface of the radially inner layer; and at least one engagement feature penetrates through the entire thickness of the radially inner layer in response to the blade or the blade fragment impacting the containment casing.