High speed propulsion system with inlet cooling

Abstract

A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.

1 . A turbine engine including a cooling system, the turbine engine comprising:
 a core engine configured to receive a first fluid stream and discharge an exhaust flow stream;   a bypass flow turbomachine disposed to receive a second fluid stream and the exhaust flow stream from the core engine and discharge a secondary exhaust flow stream, the bypass flow turbomachine including an augmentor; and   an inlet heat exchanger in fluid communication with the first fluid stream and disposed upstream and in fluid communication with the core engine, the inlet heat exchanger operative to cool the first fluid stream, the inlet heat exchanger comprising:
 a heat exchanger inlet for receiving a heat exchanging medium for exchange of heat from the first fluid stream to the heat exchanging medium; and 
 a heat exchanger outlet for discharging a heated output stream, wherein the heated output stream provides an additional flow into the bypass flow turbomachine. 
   
     
     
         2 . The turbine engine of  claim 1 , further comprising
 a core engine isolator; and   a bypass flow turbomachine isolator, wherein an incoming fluid stream is split into the first fluid stream flowing through the core engine isolator and the second fluid stream flowing through the bypass flow turbomachine isolator.   
     
     
         3 . The turbine engine of  claim 2 , wherein a boundary layer flow of the incoming fluid stream is drawn through the core engine isolator. 
     
     
         4 . The turbine engine of  claim 2 , wherein the inlet heat exchanger is positioned downstream of the core engine isolator and upstream of the core engine. 
     
     
         5 . The turbine engine of  claim 1 , further comprising:
 an isolator, wherein an incoming fluid stream flows through the isolator, and wherein a boundary layer flow of the incoming fluid stream is provided from the isolator to the core engine as the first fluid stream.   
     
     
         6 . The turbine engine of  claim 5 , wherein the isolator includes the inlet heat exchanger. 
     
     
         7 . The turbine engine of  claim 6 , wherein the inlet heat exchanger defines a leading end, and wherein the turbine engine includes flaps at the leading end to permit a flow into the core engine. 
     
     
         8 . The turbine engine of  claim 1 , further comprising a scramjet disposed about the core engine and the bypass flow turbomachine. 
     
     
         9 . The turbine engine of  claim 8 , wherein the scramjet is disposed in alignment with the inlet heat exchanger and configured to provide for passage therethrough of the second fluid stream. 
     
     
         10 . The turbine engine of  claim 9 , further comprising a diverter door between the bypass flow turbomachine and the scramjet configured to selectively divert the second fluid stream between the bypass flow turbomachine and the scramjet. 
     
     
         11 . The turbine engine of  claim 8 , wherein the bypass turbomachine is positioned aft of the core engine and wherein the bypass turbomachine and the core engine are aligned about a common centerline. 
     
     
         12 . The turbine engine of  claim 1 , wherein the bypass flow turbomachine is a first bypass flow turbomachine, and wherein the turbine engine further comprises a second bypass flow turbomachine, wherein the second bypass flow turbomachine is configured to receive a portion of the second fluid stream and a portion of the exhaust flow stream from the core engine, the second bypass flow turbomachine including a augmentor. 
     
     
         13 . A turbine engine including a cooling system, the turbine engine comprising:
 a core engine configured to receive a first fluid stream and discharge an exhaust flow stream;   a bypass flow turbomachine disposed to receive a second fluid stream and the exhaust flow stream from the core engine and discharge a secondary exhaust flow stream, the bypass flow turbomachine including an augmentor;   an inlet heat exchanger in fluid communication with the first fluid stream and disposed upstream and in fluid communication with the core engine, the inlet heat exchanger operative to cool the first fluid stream; and   an isolator, wherein an incoming fluid stream flows through the isolator, and wherein a boundary layer flow of the incoming fluid stream is provided from the isolator to the core engine as the first fluid stream.   
     
     
         14 . The turbine engine of  claim 13 , wherein the isolator includes the inlet heat exchanger. 
     
     
         15 . The turbine engine of  claim 14 , wherein the inlet heat exchanger defines a leading end, and wherein the turbine engine includes flaps at the leading end to permit a flow into the core engine. 
     
     
         16 . The turbine engine of  claim 13 , wherein the inlet heat exchanger is positioned downstream of the isolator. 
     
     
         17 . The turbine engine of  claim 13 , wherein the isolator is a bypass flow turbomachine isolator, and wherein the turbine engine further comprises:
 a core engine isolator, wherein an incoming fluid stream is split into the first fluid stream flowing through the core engine isolator and the second fluid stream flowing through the bypass flow turbomachine isolator.   
     
     
         18 . A turbine engine including a cooling system, the turbine engine comprising:
 a core engine configured to receive a first fluid stream and discharge an exhaust flow stream;   a bypass flow turbomachine disposed to receive a second fluid stream and the exhaust flow stream from the core engine and discharge a secondary exhaust flow stream, the bypass flow turbomachine including an augmentor;   an inlet heat exchanger in fluid communication with the first fluid stream and disposed upstream and in fluid communication with the core engine, the inlet heat exchanger operative to cool the first fluid stream; and   a scramjet disposed about the core engine and the bypass flow turbomachine.   
     
     
         19 . The turbine engine of  claim 18 , wherein the scramjet is disposed in alignment with the inlet heat exchanger and configured to provide for passage therethrough of the second fluid stream. 
     
     
         20 . The turbine engine of  claim 18 , wherein the bypass turbomachine is positioned aft of the core engine and wherein the bypass turbomachine and the core engine are aligned about a common centerline.