Curved heat exchanger

Abstract

A heat exchanger system is disclosed herein that extends between a first component and a second component. The heat exchanger system includes a hot flow path configured to convey hot fluid between the first component and the second component, a cool flow path configured to convey cool fluid, and a heat exchanger located between the first component and the second component along the hot flow path and the cool flow path. The heat exchanger includes at least one curve to accommodate the hot flow path and is configured to reduce the temperature of the hot fluid by allowing the transfer of thermal energy from the hot fluid to the cool fluid.

1 . A heat exchanger system that extends between a first component and a second component, the heat exchanger system comprising:
 a hot flow path configured to convey hot fluid between the first component and the second component;   a cool flow path configured to convey cool fluid;   a heat exchanger located between the first component and the second component along the hot flow path and the cool flow path, the heat exchanger having at least one curve to accommodate the hot flow path and configured to reduce the temperature of the hot fluid by allowing the transfer of thermal energy from the hot fluid to the cool fluid.   
     
     
         2 . The heat exchanger system of  claim 1 , wherein the heat exchanger has a circular cross section. 
     
     
         3 . The heat exchanger system of  claim 1 , wherein the heat exchanger extends an entire distance of the hot flow path between the first component and the second component. 
     
     
         4 . The heat exchanger system of  claim 1 , wherein the heat exchanger extends only a portion of a distance of the hot flow path between the first component and the second component. 
     
     
         5 . The heat exchanger system of  claim 4 , wherein the hot flow path comprises:
 a first hot flow duct extending from the first component to a first end of the heat exchanger; and   a second hot flow duct extending from a second end of the heat exchanger to the second component.   
     
     
         6 . The heat exchanger system of  claim 5 , further comprising:
 a first header adjacent a first end of the heat exchanger, the first header configured to guide the hot fluid from the first hot flow duct into the heat exchanger; and   a second header adjacent the second end of the heat exchanger, the second header configured to guide the hot fluid from the heat exchanger into the hot flow duct.   
     
     
         7 . The heat exchanger system of  claim 1 , wherein the heat exchanger includes multiple curves to accommodate the route of the hot flow path. 
     
     
         8 . The heat exchanger system of  claim 1 , wherein the hot flow path extends a shortest practical distance between the first component and the second component. 
     
     
         9 . The heat exchanger system of  claim 1 , wherein the cool flow path extends in an opposite direction of the hot flow path through the heat exchanger. 
     
     
         10 . The heat exchanger system of  claim 1 , wherein the cool flow path comprises:
 a first cool flow duct extending between a cool fluid source and the heat exchanger; and   a second cool flow duct extending between the heat exchanger and the cool fluid source.   
     
     
         11 . A gas turbine engine comprising:
 the heat exchanger system of  claim 1 .   
     
     
         12 . The gas turbine engine of  claim 11 , wherein the first component is in a first stage of a turbine section and the second component is in a second stage of the turbine section. 
     
     
         13 . The heat exchanger system of  claim 1 , wherein the heat exchanger is constructed utilizing additive manufacturing. 
     
     
         14 . The heat exchanger system of  claim 1 , wherein the heat exchanger includes at least one S-shaped configuration to accommodate the route of the hot flow path. 
     
     
         15 . An airplane system comprising:
 a first component in need of thermal energy management;   a second component in need of thermal energy management;   a hot flow path extending from the first component to the second component and configured to convey a first fluid to aid in thermal energy management of the first component and the second component;   a cool flow path configured to convey a second fluid; and   a heat exchanger located along the hot flow path and the cool flow path, the heat exchanger having at least one bend to accommodate the hot flow path and configured to provide thermal energy transfer between the first fluid and the second fluid.   
     
     
         16 . The airplane system of  claim 15 , wherein the heat exchanger has a circular cross-sectional shape. 
     
     
         17 . The airplane system of  claim 15 , wherein the first component is in a first turbine stage and the second component is in a second turbine stage of a gas turbine engine. 
     
     
         18 . The airplane system of  claim 15 , wherein the heat exchanger extends only a portion of a distance of the hot flow path between the first component and the second component. 
     
     
         19 . The airplane system of  claim 15 , wherein the hot flow path includes a first hot flow duct that conveys the first fluid to the heat exchanger and a second hot flow duct that conveys the first fluid from the heat exchanger to the second component. 
     
     
         20 . The airplane system of  claim 15 , wherein the heat exchanger includes multiple bends to curve around a third component in the airplane system that is at least partially located between the first component and the second component.