Patent ID: 9097209
Filing Date: 2015-08-04
Classification: F02K,Y02T

Abstract:
1. A gas turbine engine thrust reverser system comprising: a fan nacelle having a fixed portion and a movable portion configured to move relative to the fixed portion between opened and closed positions in response to a command to selectively provide an opening between the fixed and movable portions; a fan case arranged within the fan nacelle, the fan case including a wall that has an integral bull nose, the fan case adjacent to the opening in the open position and to the movable portion in the closed position, the bull nose provided by a curved portion at a terminal end of the wall, the curved portion sloping radially outward; a core supported by the fan case by struts; and circumferentially spaced flow exit guide vanes mounted to the wall, wherein the flow exit guide vanes are secured to the fan case between the struts and the fan section and extend radially inward to the core.