Turbine engine assembly including a rotating detonation combustor

Abstract

A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.

What is claimed is: 
     
         1 . A turbine engine assembly comprising:
 a rotating detonation combustor configured to combust a fuel-air mixture, wherein said rotating detonation combustor comprises:
 a radially inner side wall; 
 a radially outer side wall extending about said radially inner side wall such that an annular combustion chamber is at least partially defined therebetween; and 
 a cooling conduit extending along at least one of said radially inner side wall or said radially outer side wall; and 
   a first compressor configured to discharge a flow of cooling air towards said rotating detonation combustor and configured to channel the flow of cooling air through said cooling conduit.   
     
     
         2 . The turbine engine assembly in accordance with  claim 1 , wherein said rotating detonation combustor further comprises an annular jacket radially spaced from at least one of said radially inner side wall or said radially outer side wall, said annular jacket at least partially defining said cooling conduit. 
     
     
         3 . The turbine engine assembly in accordance with  claim 1 , wherein said rotating detonation combustor is configured to channel the fuel-air mixture in a first direction within said annular combustion chamber, said first compressor coupled in flow communication with said rotating detonation combustor such that the flow of cooling air is channeled in a second direction, opposite from the first direction, within said cooling conduit. 
     
     
         4 . The turbine engine assembly in accordance with  claim 1 , wherein said cooling conduit extends along said radially inner side wall, wherein said rotating detonation combustor is configured to channel the fuel-air mixture in a first direction within said annular combustion chamber, and wherein said first compressor is coupled in flow communication with said rotating detonation combustor such that the flow of cooling air is channeled in the first direction within said cooling conduit. 
     
     
         5 . The turbine engine assembly in accordance with  claim 1 , wherein said rotating detonation combustor further comprises a fuel-air mixer configured to receive fuel and air to form the fuel-air mixture, said cooling conduit oriented such that the flow of cooling air channeled therethrough is further channeled towards said fuel-air mixer such that the fuel-air mixture is formed from the cooling air. 
     
     
         6 . The turbine engine assembly in accordance with  claim 5 , wherein said cooling conduit and said fuel-air mixer are coupled in flow communication such that the air in the fuel-air mixture is derived entirely from the flow of cooling air. 
     
     
         7 . The turbine engine assembly in accordance with  claim 1  further comprising a second compressor configured to receive a flow of bleed air from said first compressor, and configured to discharge a flow of boosted cooling air towards said rotating detonation combustor such that the fuel-air mixture is formed from a mixed flow of cooling air and boosted cooling air. 
     
     
         8 . The turbine engine assembly in accordance with  claim 7  further comprising a cooling device positioned between said first compressor and said second compressor, said cooling device configured to cool the flow of bleed air before being channeled towards said second compressor. 
     
     
         9 . A rotating detonation combustor comprising:
 a radially inner side wall;   a radially outer side wall extending about said radially inner side wall such that an annular combustion chamber is at least partially defined therebetween; and   a cooling conduit configured to channel cooling air therethrough, said cooling conduit extending along at least one of said radially inner side wall or said radially outer side wall.   
     
     
         10 . The rotating detonation combustor in accordance with  claim 9  further comprising a plurality of thermally conductive projection members extending into an interior of said cooling conduit from at least one of said radially inner side wall or said radially outer side wall. 
     
     
         11 . The rotating detonation combustor in accordance with  claim 9  further comprising:
 a first end plate coupled to said radially inner side wall and said radially outer side wall, said first end plate at least partially defining said annular combustion chamber, wherein said first end plate comprises an air inlet defined therein; and 
 a second end plate spaced from said first end plate and at least partially defining said cooling conduit such that the cooling air channeled therethrough is further channeled towards said air inlet. 
 
     
     
         12 . The rotating detonation combustor in accordance with  claim 9  further comprising a first annular jacket radially spaced from said radially outer side wall such that said cooling conduit is defined between said radially outer side wall and said first annular jacket. 
     
     
         13 . The rotating detonation combustor in accordance with  claim 9  further comprising a second annular jacket radially spaced from said radially inner side wall such that said cooling conduit is defined between said radially inner side wall and said second annular jacket. 
     
     
         14 . The rotating detonation combustor in accordance with  claim 9 , wherein said cooling conduit extends within a portion of at least one of said radially inner side wall or said radially outer side wall. 
     
     
         15 . The rotating detonation combustor in accordance with  claim 14 , wherein at least a portion of said at least one of said radially inner side wall or said radially outer side wall is recessed relative to an interior of said annular combustion chamber such that a stepped side wall portion is formed, said stepped side wall portion defining an air pocket within said annular combustion chamber, and said stepped side wall portion comprising an opening defined therein that couples said cooling conduit in flow communication with said air pocket. 
     
     
         16 . A turbine engine assembly comprising:
 a rotating detonation combustor configured to combust a fuel-air mixture, wherein said rotating detonation combustor comprises:
 a radially inner side wall; 
 a radially outer side wall extending about said radially inner side wall such that an annular combustion chamber is at least partially defined therebetween; and 
 a cooling conduit extending along at least one of said radially inner side wall or said radially outer side wall; and 
   a source of cooling fluid coupled in flow communication with said rotating detonation combustor, said source of cooling fluid configured to discharge a flow of cooling fluid towards said rotating detonation combustor, and configured to channel the flow of cooling fluid through said cooling conduit, wherein the cooling fluid includes at least one of steam, water, or fuel.   
     
     
         17 . The turbine engine assembly in accordance with  claim 16 , wherein said source of cooling fluid is configured to channel steam or water through said cooling conduit such that heated steam or heated water is formed, said turbine engine assembly further comprising a steam turbine configured to receive a flow of heated steam or heated water from said cooling conduit. 
     
     
         18 . The turbine engine assembly in accordance with  claim 16 , wherein said source of cooling fluid is configured to channel fuel through said cooling conduit, wherein at least one of said radially inner side wall or said radially outer side wall comprises at least one fuel inlet defined therein, said at least one fuel inlet configured to inject the fuel into said annular combustion chamber. 
     
     
         19 . The turbine engine assembly in accordance with  claim 18 , wherein said at least one fuel inlet comprises a plurality of fuel inlets spaced axially from each other relative to a centerline of said rotating detonation combustor. 
     
     
         20 . The turbine engine assembly in accordance with  claim 18 , wherein said rotating detonation combustor further comprises a fuel-air mixer positioned within said annular combustion chamber upstream from said at least one fuel inlet relative to a flow direction of the fuel-air mixture.