Gas turbine bleed ecs cooling

Abstract

A method for managing heat in an airplane includes extracting hot bleed air from a gas turbine engine, and cooling the hot bleed air in a first heat exchanger thereby forming warm bleed air. The method further includes expanding the warm bleed air with a turbine thereby forming cool bleed air, and using the cool bleed air as a heat sink in a second heat exchanger associated with an environmental control system and thereby forming used bleed air.

1 . A method for managing heat in an airplane, the method comprising:
 extracting hot bleed air from a gas turbine engine;   cooling the hot bleed air in a first heat exchanger thereby forming warm bleed air;   expanding the warm bleed air with a turbine thereby forming cool bleed air; and   using the cool bleed air as a heat sink in a second heat exchanger associated with an environmental control system and thereby forming used bleed air.   
     
     
         2 . The method of  claim 1 , further comprising:
 exhausting the used bleed air out of the airplane.   
     
     
         3 . The method of  claim 1 , wherein the hot bleed air is extracted from one of a fan bleed port, an intermediate compressor bleed port, and a high compressor bleed port of the gas turbine engine. 
     
     
         4 . The method of  claim 1 , wherein the hot bleed air is cooled in the first heat exchanger by one of ram air, lower stage bleed air, or fuel. 
     
     
         5 . The method of  claim 1 , further comprising:
 operating one of a pump, a compressor, a generator, or a gearbox with energy generated by expanding the warm bleed air with the turbine.   
     
     
         6 . The method of  claim 1 , wherein the cool bleed air cools a working fluid in the second heat exchanger for one of an air cycle system, a vapor cycle system, or a hybrid cooling system. 
     
     
         7 . A heat management system for an airplane, the system comprising:
 a first heat exchanger for cooling the hot bleed air produced by a gas turbine engine, thereby forming warm bleed air;   a turbine for expanding the warm bleed air thereby forming cool bleed air; and   a second heat exchanger using the cool bleed air as a heat sink for a fluid in an environmental control system.   
     
     
         8 . The system of  claim 7 , wherein the hot bleed air is tapped from the gas turbine engine at one of a fan section, an intermediate compressor section, and a high compressor section. 
     
     
         9 . The system of  claim 7 , wherein one of ram air, lower stage bleed air, or fuel enter the first heat exchanger to provide the heat sink for cooling the hot bleed air. 
     
     
         10 . The system of  claim 7 , further comprising:
 a pump attached to the turbine, the pump for using work generated by the turbine expanding the warm bleed air.   
     
     
         11 . The system of  claim 7 , further comprising:
 a compressor attached to the turbine, the compressor for using work generated by the turbine expanding the warm bleed air.   
     
     
         12 . The system of  claim 7 , further comprising:
 a generator attached to the turbine, the generator for using work generated by the turbine expanding the warm bleed air.   
     
     
         13 . The system of  claim 7 , further comprising:
 a gearbox attached to the turbine, the gearbox for using work generated by the turbine expanding the warm bleed air.   
     
     
         14 . The system of  claim 7 , wherein the environmental control system is one of an air cycle system, a vapor cycle system, or a hybrid cooling system. 
     
     
         15 . A heat management system for an airplane, the system comprising:
 a gas turbine engine having a bleed port for extracting hot bleed air;   a first heat exchanger fluidly connected to the bleed port, the heat first heat exchanger configured to cool the hot bleed air into warm bleed air;   a turbine fluidly connected to the first heat exchanger, the turbine configured to expand the warm bleed air into cool bleed air; and   a second heat exchanger fluidly connected to the turbine, the second heat exchanger configured to cool a fluid for an environmental control system with the cool bleed air.   
     
     
         16 . The system of  claim 15 , wherein the bleed port is located at one of a fan section, an intermediate compressor section, and a high compressor section. 
     
     
         17 . The system of  claim 15 , wherein one of ram air, lower stage bleed air, or fuel enter the first heat exchanger to cool the hot bleed air into warm bleed air. 
     
     
         18 . The system of  claim 15 , wherein one of a pump, a compressor, a generator, or a gearbox is attached to the turbine for using work generated by expanding the warm bleed air. 
     
     
         19 . The system of  claim 15 , wherein the environmental control system is one of an air cycle system, a vapor cycle system, or a hybrid cooling system.