Systems for thrust reverser with temperature and fluid management

Abstract

A thrust reverser system includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

What is claimed is: 
     
         1 . A thrust reverser system for a gas turbine engine, comprising:
 at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system;   at least one body coupled to the at least one hinge, the at least one body having a first body end and an opposing second body end, the body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end,   wherein the body is positioned within the at least one opening based on an operating condition of the gas turbine engine.   
     
     
         2 . The thrust reverser system of  claim 1 , further comprising:
 a transcowl movable between a first, stowed position and a second, deployed position, the transcowl having an outer surface and an opposing inner surface, the transcowl defining the at least one opening that extends through the transcowl from the outer surface to the inner surface.   
     
     
         3 . The thrust reverser system of  claim 2 , wherein the operating condition of the gas turbine engine is a pressure, and the body is positioned within the at least one opening based on the pressure as greater than atmospheric pressure, and the body is spaced apart from the opening to enable fluids to exit the gas turbine engine based on the pressure as equal to atmospheric pressure. 
     
     
         4 . The thrust reverser system of  claim 3 , wherein the body and the hinge cooperate to form a vent, and the at least one opening is defined in an upper surface of the transcowl, with the upper surface of the transcowl opposite a lower surface of the transcowl. 
     
     
         5 . The thrust reverser system of  claim 4 , wherein the counterweight is coupled to the second body end. 
     
     
         6 . The thrust reverser system of  claim 5 , wherein the hinge defines at least one first stop feature, and the first body end defines at least one second stop feature. 
     
     
         7 . A thrust reverser system for a gas turbine engine, comprising:
 at least one frame coupled to at least one opening defined in the thrust reverser system, the at least one frame defining at least one aperture; and   at least one sealing member coupled to the at least one frame, the at least one sealing member movable between a first, closed position in which the at least one sealing member covers the at least one aperture and a second, open position in which the at least one sealing member is spaced apart from the at least one aperture based on an operating condition of the gas turbine engine.   
     
     
         8 . The thrust reverser system of  claim 7 , further comprising:
 a transcowl movable between a first, stowed position and a second, deployed position, the transcowl having an outer surface and an opposing inner surface, the transcowl defining the at least one opening that extends through the transcowl from the outer surface to the inner surface.   
     
     
         9 . The thrust reverser system of  claim 8 , wherein the at least one sealing member includes at least one plug layer, which includes at least one finger that is received within the at least one aperture in the first, closed position. 
     
     
         10 . The thrust reverser system of  claim 9 , further comprising a compliant layer coupled to the at least one plug layer, the compliant layer responsive to the operating condition of the gas turbine engine to move the plug layer between the first, closed position and the second, open position. 
     
     
         11 . The thrust reverser system of  claim 10 , wherein the at least one frame defines a plurality of apertures, which are spaced apart from each other in a radial direction and extend in a longitudinal direction between a first frame end and a second frame end. 
     
     
         12 . The thrust reverser system of  claim 11 , wherein the compliant layer includes at least one compliant finger that extends from a first layer end to define a second layer end, and the at least one compliant finger is coupled to the at least one finger of the plug layer and is coupled to the at least one frame near the second frame end. 
     
     
         13 . The thrust reverser system of  claim 12 , wherein the first layer end is uncoupled from the inner surface of the transcowl, and overlaps the inner surface of the transcowl such that the first layer end extends beyond the at least one opening. 
     
     
         14 . A thrust reverser system for a gas turbine engine, comprising:
 a transcowl movable between a first, stowed position and a second, deployed position, the transcowl having an outer surface and an opposing inner surface, the transcowl defining the at least one opening that extends through the transcowl from the outer surface to the inner surface;   at least one frame coupled to the at least one opening defined in the transcowl, the at least one frame defining at least one aperture; and   at least one sealing member coupled to the at least one frame, the at least one sealing member movable between a first, closed position in which the at least one sealing member covers the at least one aperture and a second, open position in which the at least one sealing member is spaced apart from the at least one aperture based on an operating condition of the gas turbine engine.   
     
     
         15 . The thrust reverser system of  claim 14 , wherein the at least one sealing member includes at least one plug layer, which includes at least one finger that is received within the at least one aperture in the first, closed position. 
     
     
         16 . The thrust reverser system of  claim 15 , further comprising a compliant layer coupled to the at least one plug layer, the compliant layer responsive to the operating condition of the gas turbine engine to move the plug layer between the first, closed position and the second, open position. 
     
     
         17 . The thrust reverser system of  claim 14 , wherein the at least one frame defines a plurality of apertures, which are spaced apart from each other in a radial direction and extend in a longitudinal direction between a first frame end and a second frame end. 
     
     
         18 . The thrust reverser system of  claim 16 , wherein the compliant layer includes at least one compliant finger that extends from a first layer end to define a second layer end, and the at least one compliant finger is coupled to the at least one finger of the plug layer and is coupled to the at least one frame near the second frame end. 
     
     
         19 . The thrust reverser system of  claim 18 , wherein the first layer end is uncoupled from the inner surface of the transcowl, and overlaps the inner surface of the transcowl such that the first layer end extends beyond the at least one opening. 
     
     
         20 . The thrust reverser system of  claim 14  wherein the operating condition of the gas turbine engine is a pressure, and the at least one sealing member is in the first, closed position based on the pressure as greater than atmospheric pressure, and the at least one sealing member is in the second, open position based on the pressure as equal to atmospheric pressure.