Patent ID: 8317456
Filing Date: 2012-11-27
Classification: F01D,F02K,F04D,F05D,Y02T,Y10T

Abstract:
1. A method, comprising: encircling an outer circumferential surface of one of a closed, solid containment ring and a fan blade containment region of fan case of a gas turbine jet engine having a turbine case having a turbine adapted to rotate along an axis of rotation within said fan case, and a fan having fan blades coupled to said turbine and adapted to rotate along an axis of rotation within said fan case, each fan blade having a leading edge and a trailing edge, using an inner circumferential surface of the other of the containment ring and the fan blade containment region of the fan case of a gas turbine jet engine; and applying radially compressive forces to said outer circumferential surface along the length of the circumference of said inner circumferential surface and along the width of the fan blade containment region extending at least forward of the leading edge of each fan blade and at least aft of the trailing edge of each fan blade, using said encircling inner circumferential surface.