Heat exchange module for a turbine engine

Abstract

A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

What is claimed is: 
     
         1 . A heat exchange module for a turbine engine, comprising:
 a duct including a flowpath defined radially between a plurality of concentric duct walls, the flowpath extending along an axial centerline through the duct between a first duct end and a second duct end; and   a plurality of heat exchangers located within the flowpath, and arranged circumferentially around the centerline.   
     
     
         2 . The heat exchange module of  claim 1 , wherein a first of the heat exchangers has an arcuate geometry. 
     
     
         3 . The heat exchange module of  claim 1 , wherein a first of the heat exchangers has a rectangular geometry. 
     
     
         4 . The heat exchange module of  claim 3 , wherein at least a portion of a first of the duct walls has a polygonal cross-sectional geometry. 
     
     
         5 . The heat exchange module of  claim 4 , wherein
 the first of the duct walls includes a transition segment that extends axially from the first duct end to a heat exchanger segment;   the heat exchanger segment has the polygonal cross-sectional geometry; and   the transition segment has a cross-sectional geometry that transitions from a circular cross-section geometry at the first duct end to the polygonal cross-sectional geometry at the heat exchanger segment.   
     
     
         6 . The heat exchange module of  claim 5 , wherein
 the first of the duct walls further includes a second transition segment that extends axially from the second duct end to the heat exchanger segment; and   the second transition segment has a cross-sectional geometry that transitions from a circular cross-sectional geometry at the second duct end to the polygonal cross-sectional geometry at the heat exchanger segment.   
     
     
         7 . The heat exchange module of  claim 4 , wherein at least a portion of a second of the duct walls has a polygonal cross-sectional geometry. 
     
     
         8 . The heat exchange module of  claim 1 , further comprising an actuator that moves a first of the heat exchangers between a deployed position and a stowed position. 
     
     
         9 . The heat exchange module of  claim 8 , wherein the first of the heat exchangers is located within the flowpath in the deployed position, and is located adjacent to the flowpath in the stowed position. 
     
     
         10 . The heat exchange module of  claim 8 , wherein the first of the heat exchangers pivots within the flowpath about an axis between the deployed position and the stowed position. 
     
     
         11 . The heat exchange module of  claim 8 , further comprising:
 a baffle arranged circumferentially between the first and a second of the heat exchangers; and   a second actuator that moves a baffle between a deployed position and a stowed position.   
     
     
         12 . A turbine engine with an axial centerline, comprising:
 a core comprising a compressor section, a combustor section and a turbine section;   an annular engine flowpath defined radially between a plurality of turbine engine cases, the engine flowpath extending axially between an inlet and an outlet and circumferentially around the core; and   a heat exchange module connected to a first of the turbine engine cases, and comprising
 a duct including an annular duct flowpath defined radially between a plurality of duct walls, the duct flowpath extending axially through the duct and coupled with the engine flowpath; and 
 a plurality of heat exchangers located with the duct flowpath, and arranged circumferentially around the centerline. 
   
     
     
         13 . The turbine engine of  claim 12 , wherein
 a first of the heat exchangers has a rectangular geometry; and   at least a portion of a first of the duct walls has a polygonal cross-sectional geometry.   
     
     
         14 . The turbine engine of  claim 13 , wherein
 the first of the duct walls includes a transition segment that extends axially from a first duct end to a heat exchanger segment;   the heat exchanger segment has the polygonal cross-sectional geometry; and   the transition segment has a cross-sectional geometry that transitions from a circular cross-section geometry at the first duct end to the polygonal cross-sectional geometry at the heat exchanger segment.   
     
     
         15 . The turbine engine of  claim 14 , wherein
 the first of the duct walls further includes a second transition segment that extends axially from a second duct end to the heat exchanger segment; and   the second transition segment has a cross-sectional geometry that transitions from a circular cross-sectional geometry at the second duct end to the polygonal cross-sectional geometry at the heat exchanger segment.   
     
     
         16 . The turbine engine of  claim 12 , further comprising:
 an actuator that moves a first of the heat exchangers between a deployed position and a stowed position;   wherein the first of the heat exchangers is located within the duct flowpath in the deployed position, and is located adjacent to the duct flowpath in the stowed position.   
     
     
         17 . The turbine engine of  claim 12 , further comprising:
 an actuator that moves a first of the heat exchangers between a deployed position and a stowed position;   wherein the first of the heat exchangers pivots within the duct flowpath about an axis between the deployed position and the stowed position.   
     
     
         18 . The turbine engine of  claim 12 , wherein the first of the turbine engine cases includes a plurality of case segments, and a first of the duct walls is connected axially between the case segments. 
     
     
         19 . The turbine engine of  claim 12 , further comprising an annular second engine flowpath defined radially between one of the turbine engine cases and a third turbine engine case, the second engine flowpath extending axially between a second inlet and a second outlet, and circumferentially around the core and within the engine flowpath. 
     
     
         20 . A turbine engine with an axial centerline, comprising:
 a core comprising a compressor section, a combustor section and a turbine section;   an annular engine flowpath defined radially between a plurality of turbine engine cases, the engine flowpath extending axially between an inlet and an outlet and circumferentially around the core; and   a heat exchange module connected to a first of the turbine engine cases, and comprising
 a duct including a duct flowpath defined by a duct wall that extends circumferentially about the centerline, the duct flowpath extending axially through the duct and circumferentially about the centerline, wherein the duct flowpath is coupled inline with the engine flowpath; and 
   a plurality of heat exchangers located with the duct flowpath, and arranged circumferentially about the centerline.