Inline Cross Flow Heat Exchangers

Abstract

Apparatus and methods provide for the exchange of heat in a cross flow heat exchanger having heat exchanger sub-chambers in an inline configuration. According to embodiments described herein, the heat exchanger sub-chambers may be arranged in an inline configuration, where two or more of the sub-chambers are positioned generally along a linear axis. In further configurations, to accommodate the linear configuration of two or more sub-chambers, inlet fluid flows to subsequent or downstream sub-chambers are directed to the sub-chambers using bypasses around the upstream or prior sub-chambers. Various configurations may reduce or minimize pressure losses of one or more of the fluids moving through the heat exchanger.

1 . An aircraft heat exchanger, comprising:
 a cold fluid input;   a first partition that splits the cold fluid input into a first cold fluid input and a second cold fluid input;   a hot fluid input;   a second partition that splits the hot fluid input into a first hot fluid input and a second hot fluid input;   a first heat exchanger sub-chamber that exchanges heat energy in a cross flow configuration between the first cold fluid input and the first hot fluid input;   a second heat exchanger sub-chamber inline to the first heat exchanger sub-chamber such that a first central axis of the first heat exchanger sub-chamber along a direction of the first cold fluid input and a second central axis of the second heat exchanger sub-chamber along a direction of the second cold fluid input lie generally in a straight line along a common axis, the second heat exchanger sub-chamber exchanges heat energy in a cross flow configuration between the second cold fluid input and the second hot fluid input; and   a bypass that directs the second cold fluid input around the first heat exchanger sub-chamber and into the second heat exchanger sub-chamber.   
     
     
         2 . The aircraft heat exchanger of  claim 1 , wherein the cold fluid input comprises precooler fan air from an engine. 
     
     
         3 . The aircraft heat exchanger of  claim 1 , wherein the hot fluid input comprises bleed air from an engine. 
     
     
         4 . The aircraft heat exchanger of  claim 1 , wherein the first partition comprises a valve having a plurality of outputs that split the cold fluid input into the first cold fluid input and the second cold fluid input. 
     
     
         5 . The aircraft heat exchanger of  claim 1 , wherein the first partition comprises a barrier that splits the cold fluid input into the first cold fluid input and the second cold fluid input. 
     
     
         6 . The aircraft heat exchanger of  claim 1 , wherein the second partition comprises a valve having a plurality of outputs or a barrier that splits the hot fluid input into the first hot fluid input and the second hot fluid input. 
     
     
         7 . A method for exchanging heat between aircraft components, the method comprising:
 receiving a cold fluid input;   partitioning the cold fluid input into a first cold fluid input and a second cold fluid input;   receiving a hot fluid input;   partitioning the hot fluid input into a first hot fluid input and a second hot fluid input;   exchanging heat energy in a first heat exchanger sub-chamber in a cross flow configuration between the first cold fluid input and the first hot fluid input;   exchanging heat energy in a second heat exchanger sub-chamber inline to the first heat exchanger sub-chamber in a cross flow configuration between the second cold fluid input and the second hot fluid input; and   directing the second cold fluid input around the first heat exchanger sub-chamber in a bypass that is offset to a side of the first heat exchanger sub-chamber, extends along a length of the first heat exchanger sub-chamber, and enters the second heat exchanger sub-chamber positioned such that a first central axis of the first heat exchanger sub-chamber and a second central axis of the second heat exchanger sub-chamber lie generally in a straight line along a common axis.   
     
     
         8 . The method of  claim 7 , wherein the cold fluid input comprises precooler fan air from an engine. 
     
     
         9 . The method of  claim 7 , wherein the hot fluid input comprises precooler bleed air from an engine. 
     
     
         10 . The method of  claim 7 , wherein partitioning the cold fluid input into the first cold fluid input and the second cold fluid input comprises directing the cold fluid input into a valve having a plurality of outputs. 
     
     
         11 . The method of  claim 7 , wherein partitioning the cold fluid input into the first cold fluid input and the second cold fluid input comprises directing the cold fluid input through a barrier configured to split the cold fluid input into the first cold fluid input and the second cold fluid input. 
     
     
         12 . The method of  claim 7 , further comprising combining a hot output of the first heat exchanger sub-chamber and a hot output of the second heat exchanger sub-chamber. 
     
     
         13 . The method of  claim 7 , further comprising combining a cold output of the first heat exchanger sub-chamber and a cold output of the second heat exchanger sub-chamber. 
     
     
         14 . The method of  claim 7 , further comprising combining the first hot fluid input and the second hot fluid input upon exiting the first heat exchanger sub-chamber and the second heat exchanger sub-chamber, respectively. 
     
     
         15 . An aircraft, comprising:
 an engine having a precooler fan air supply; and   a cross flow heat exchanger comprising
 a cold fluid input for receiving the precooler fan air supply; 
 a first partition for splitting the cold fluid input into a first cold fluid input and a second cold fluid input; 
 a hot fluid input; 
 a second partition for splitting the hot fluid input into a first hot fluid input and a second hot fluid input; 
 a first heat exchanger sub-chamber for exchanging heat energy in a cross flow configuration between the first cold fluid input and the first hot fluid input; 
 a second heat exchanger sub-chamber inline to the first heat exchanger sub-chamber for exchanging heat energy in a cross flow configuration between the second cold fluid input and the second hot fluid input; and 
 a bypass for directing the second cold fluid input around the first heat exchanger sub-chamber, the bypass having a wall in contact with the second cold fluid input of a height equivalent to a height of the first heat exchanger sub-chamber and configured to divide the second cold fluid input within the bypass on a first side of the wall from the first cold fluid input and the first hot fluid input within the first heat exchanger sub-chamber on a second side of the wall. 
   
     
     
         16 . The aircraft of  claim 15 , wherein the hot fluid input comprises bleed air from an engine. 
     
     
         17 . The aircraft of  claim 15 , wherein the first partition comprises a valve having a plurality of outputs that split the cold fluid input into the first cold fluid input and the second cold fluid input. 
     
     
         18 . The aircraft of  claim 15 , wherein the first partition comprises a barrier that splits the cold fluid input into the first cold fluid input and the second cold fluid input. 
     
     
         19 . The aircraft of  claim 15 , wherein the second partition comprises a valve having a plurality of outputs or a barrier that splits the hot fluid input into the first hot fluid input and the second hot fluid input. 
     
     
         20 . The aircraft of  claim 15 , wherein a cross flow heat exchanger is mounted proximate to an engine strut.