Aero-derivative gas turbine engine with an advanced transition duct combustion assembly

Abstract

An aero-derivative can annular gas turbine engine having: an aero gas turbine engine core including an aero high pressure compressor ( 65 ) interconnected with an aero high pressure turbine ( 73 ) by an aero high pressure shaft ( 142 ) in a geometric arrangement appropriate for association with an aero annular combustor ( 84 ), but with the aero annular combustor ( 84 ) and a first row of turbine vanes ( 38 ) of the aero high pressure turbine ( 73 ) absent; and a can annular combustor assembly ( 122 ) assembled with the aero gas turbine engine core and configured to receive compressed air from the aero high pressure compressor ( 65 ) and to accelerate and orient combustion gasses directly onto a first row of blades of the aero high pressure turbine ( 73 ).

The invention claimed is: 
     
         1 . An aero-derivative can annular gas turbine engine, comprising:
 an aero gas turbine engine core comprising an aero high pressure compressor interconnected with an aero high pressure turbine by an aero high pressure shaft in a geometric arrangement appropriate for association with an aero annular combustor, but with the aero annular combustor and a first row of vanes of the aero turbine absent; and   a can annular combustor assembly assembled with the aero gas turbine engine core and configured to receive compressed air from the aero high pressure compressor and to accelerate and orient combustion gasses directly onto a first row of blades of the aero high pressure turbine.   
     
     
         2 . The aero-derivative can annular gas turbine engine of  claim 1 , wherein the can annular combustor assembly comprises a plurality of combustors and associated advanced transition ducts, the aero-derivative can annular gas turbine engine comprising an advanced combustor aero-derivative outer casing configured to permit removal of an individual combustor and associated advanced transition duct there through. 
     
     
         3 . The aero-derivative can annular gas turbine engine of  claim 1 , comprising an advanced combustor aero-derivative inner casing that encloses a greater volume than an aero combustor inner casing associated with the aero annular combustor. 
     
     
         4 . The aero-derivative can annular gas turbine engine of  claim 1 , further comprising a power turbine. 
     
     
         5 . A power generation assembly comprising the aero-derivative can annular gas turbine engine of  claim 4  and an electrical generator associated with the power turbine. 
     
     
         6 . An aero-derivative can annular gas turbine engine, comprising:
 an aero high pressure compressor;   an aero high pressure turbine comprising a first row of rotating turbine blades at an upstream-most end;   an aero high pressure shaft assembly interconnecting the high pressure aero compressor and the aero high pressure turbine;   a can annular combustor assembly assembled between the aero high pressure compressor and the aero high pressure turbine;   wherein can annular combustors of the can annular combustor assembly receive compressed air from the aero high pressure compressor and accelerate and orient combustion gasses directly onto the first row of rotating blades.   
     
     
         7 . The aero-derivative can annular gas turbine engine of  claim 6 , further comprising a power turbine. 
     
     
         8 . A power generation assembly comprising the aero-derivative can annular gas turbine engine of  claim 7  and an electrical generator associated with the power turbine. 
     
     
         9 . The aero-derivative can annular gas turbine engine of  claim 6 , comprising a combustor outer casing configured to enclose the can annular combustor assembly, wherein the can annular combustor assembly comprises a plurality of combustors and associated advanced transition ducts, and wherein the combustor outer casing comprises an access port sufficient to permit removal of a combustor and associated advanced transition duct there through. 
     
     
         10 . A method of upgrading an aero-derivative gas turbine engine, the method comprising:
 removing an existing aero combustor outer casing;   removing an existing aero annular combustor;   removing an existing first row of aero turbine vanes;   installing a can annular combustor assembly within an axial span of the aero-derivative gas turbine engine vacated by the existing aero annular combustor and the existing first row of aero turbine vanes, the can annular combustor assembly configured to accelerate and orient combustion gassed directly onto a first row of aero turbine blades; and   installing an aero-derivative can annular combustor assembly outer casing.   
     
     
         11 . The method of  claim 10 , comprising installing the can annular combustor assembly without changing a model of at least one component selected from a group consisting of the aero high pressure shaft, and the aero high pressure shaft bearings. 
     
     
         12 . The method of  claim 10 , comprising installing the can annular combustor assembly without changing at least one component selected from a group consisting of the aero high pressure shaft, and the aero high pressure shaft bearings. 
     
     
         13 . The method of  claim 10 , comprising using existing aero compressor outer casing mounts and existing aero turbine outer casing mounts to secure the aero-derivative can annular combustor assembly outer casing to the aero compressor outer casing and the aero turbine outer casing. 
     
     
         14 . The method of  claim 10 , comprising replacing an existing aero combustor inner casing with an aero-derivative can annular combustor assembly inner casing effective to improve access to a volume enclosed thereby. 
     
     
         15 . The method of  claim 10 , comprising converting an adjustable compressor vane to a fixed compressor vane.