System and method for passive cooling of gas turbine engine control components

Abstract

A system for cooling a gas turbine engine control component comprises a control component, at least one duct in fluid communication with the component and the atmosphere, and a valve assembly located with the duct for modulating airflow to the component. A method for cooling a gas turbine engine control component comprises the steps of: a) providing a system for cooling the component, the system comprising at least one duct in fluid communication with the component and the atmosphere and a valve assembly located with the duct for modulating airflow to the component; b) exposing the system to a first condition where cooling of the component is required; c) opening the valve assembly in response to the first condition; d) exposing the system to a second condition where cooling of the component is not required; and e) closing the valve assembly in response to the second condition.

1 . A system for cooling a gas turbine engine control component, said system comprising:
 a control component;   at least one duct in fluid communication with said component and the atmosphere; and   a valve assembly located with said duct for modulating airflow to said component.   
   
   
       2 . The system of  claim 1 , wherein said valve assembly is normally biased to an open position. 
   
   
       3 . The system of  claim 1 , wherein said system comprises two ducts, a first duct leading from a first surface of an aircraft engine nacelle structure to said component and a second duct leading from said component to a second surface of an aircraft nacelle structure. 
   
   
       4 . The system of  claim 1 , wherein said component is located within an aircraft engine nacelle structure between a first surface of said structure and a second surface of said structure. 
   
   
       5 . The system of  claim 4 , wherein said first surface is an inner surface of said structure and a second surface is an outer surface of said structure. 
   
   
       6 . The system of  claim 5 , wherein said valve assembly is located in said second duct adjacent to said second surface. 
   
   
       7 . The system of  claim 1 , wherein said valve assembly comprises a pair of pivotally mounted valve flaps. 
   
   
       8 . The system of  claim 7 , wherein said valve flaps include at least one aperture extending therethrough. 
   
   
       9 . The system of  claim 7 , wherein said valve assembly includes at least one valve stop to limit travel of said valve flaps. 
   
   
       10 . The system of  claim 9 , wherein said valve assembly includes at least two valve stops to limit travel of said valve flaps. 
   
   
       11 . The system of  claim 9 , wherein said valve stop forms a continuous annular ring. 
   
   
       12 . The system of  claim 9 , wherein said valve assembly includes at least one seal in association with said valve stop. 
   
   
       13 . The system of  claim 12 , wherein said seal forms a continuous annular ring. 
   
   
       14 . The system of  claim 12 , wherein said seal forms one or more discontinuous annular segments. 
   
   
       15 . The system of  claim 1 , wherein said component is a FADEC unit. 
   
   
       16 . The system of  claim 1 , wherein said valve assembly is configured to operate in an open position when said component requires cooling and a closed position when said component does not require cooling. 
   
   
       17 . A system for cooling a gas turbine engine control component, said system comprising:
 a control component located within an aircraft engine nacelle structure between a first surface of said structure and a second surface of said structure;   two ducts in fluid communication with said component and the atmosphere, a first duct leading from a first surface of an aircraft engine nacelle structure to said component and a second duct leading from said component to a second surface of an aircraft nacelle structure; and   a valve assembly located with said duct for modulating airflow to said component, said valve assembly being located in said second duct adjacent to said second surface and being configured to operate in an open position when said component requires cooling and a closed position when said component does not require cooling.   
   
   
       18 . A method for cooling a gas turbine engine control component, said method comprising:
 providing a system for cooling said component, said system comprising at least one duct in fluid communication with said component and the atmosphere and a valve assembly located with said duct for modulating airflow to said component;   exposing said system to a first condition where cooling of said component is required;   opening said valve assembly in response to said first condition;   exposing said system to a second condition where cooling of said component is not required; and   closing said valve assembly in response to said second condition.   
   
   
       19 . The method of  claim 18 , wherein said closing step is accomplished by reversing airflow though said duct. 
   
   
       20 . The method of  claim 18 , wherein said opening and closing steps are accomplished passively.