Turbine engine and method of assembling thereof

Abstract

A turbine engine is provided. The turbine engine includes a compressor configured to discharge a flow of air at a first flow angle and a combustor coupled downstream from the compressor. The combustor is configured to combust the flow of air with fuel to form a flow of combustion gas discharged from the combustor at a second flow angle. The turbine engine also includes a turbine coupled downstream from the combustor. The turbine includes an inlet configured to receive the flow of combustion gas having a flow angle within a predetermined range, wherein the combustor is oriented such that the second flow angle is within the predetermined range.

What is claimed is: 
     
         1 . A turbine engine comprising:
 a compressor configured to discharge a flow of air at a first flow angle;   a combustor coupled downstream from said compressor, said combustor configured to combust the flow of air with fuel to form a flow of combustion gas discharged from said combustor at a second flow angle; and   a turbine coupled downstream from said combustor, said turbine comprising an inlet configured to receive the flow of combustion gas having a flow angle within a predetermined range,
 wherein said combustor is oriented such that the second flow angle is within the predetermined range. 
   
     
     
         2 . The turbine engine in accordance with  claim 1  further comprising a variable guide vane positioned between said compressor and said combustor, wherein an orientation of said variable guide vane is selected such that the second flow angle is within the predetermined range. 
     
     
         3 . The turbine engine in accordance with  claim 2 , wherein said variable guide vane is selectively actuated to modify the first flow angle of the flow of air channeled towards said combustor. 
     
     
         4 . The turbine engine in accordance with  claim 2 , wherein said variable guide vane is positioned between a last stage rotor of said compressor and said combustor. 
     
     
         5 . The turbine engine in accordance with  claim 2 , wherein said combustor comprises a bulk swirl combustor. 
     
     
         6 . The turbine engine in accordance with  claim 1  further comprising a flow path extending between said compressor and said turbine in a substantially axial direction, said flow path comprising a variable cross-sectional area along the substantially axial direction, the variable cross-sectional area selected such that the second flow angle is within the predetermined range. 
     
     
         7 . The turbine engine in accordance with  claim 6 , wherein said flow path comprises:
 a first section extending between said compressor and said combustor, wherein a cross-sectional area of said first section progressively increases in size from said compressor to said combustor; and   a second section extending between said combustor and said turbine, wherein a cross-sectional area of said second section progressively decreases in size from said combustor to said turbine.   
     
     
         8 . The turbine engine in accordance with  claim 1 , wherein said combustor is configured to discharge the flow of combustion gas at a greater velocity than a velocity of the flow of air discharged from said compressor. 
     
     
         9 . The turbine engine in accordance with  claim 8 , wherein said combustor is oriented such that the second flow angle is within the predetermined range, an orientation of said combustor selected as a function of a velocity gradient between the flow of air entering said combustor and the flow of combustion gas discharged from said combustor. 
     
     
         10 . The turbine engine in accordance with  claim 1 , wherein said turbine engine does not comprise a nozzle positioned between said combustor and said turbine. 
     
     
         11 . A method of assembling a turbine engine, said method comprising:
 coupling a combustor downstream from a compressor configured to discharge a flow of air at a first flow angle, wherein the combustor is configured to combust the flow of air with fuel to form a flow of combustion gas configured to discharge from the combustor at a second flow angle;   coupling a turbine downstream from the combustor, the turbine comprising an inlet configured to receive the flow of combustion gas from the combustor having a flow angle within a predetermined range; and   orienting the combustor such that the second flow angle is within the predetermined range.   
     
     
         12 . The method in accordance with  claim 11  further comprising positioning a variable guide vane between the compressor and the combustor, wherein an orientation of the variable guide vane is selected such that the second flow angle is within the predetermined range. 
     
     
         13 . The method in accordance with  claim 12  further comprising configuring the variable guide vane to be selectively actuated to modify the first flow angle of the flow of air channeled towards the combustor. 
     
     
         14 . The method in accordance with  claim 12 , wherein positioning a variable guide vane comprises positioning the variable guide vane between a last stage rotor of the compressor and the combustor. 
     
     
         15 . The method in accordance with  claim 12 , wherein coupling the combustor comprises orienting the combustor in a second fixed orientation relative to a centerline of the turbine engine. 
     
     
         16 . The method in accordance with  claim 11  further comprising defining a flow path that extends between the compressor and the turbine in a substantially axial direction, the flow path comprising a variable cross-sectional area along the substantially axial direction, the variable cross-sectional area selected such that the second flow angle is within the predetermined range. 
     
     
         17 . The method in accordance with  claim 16  further comprising:
 extending a first section of the flow path between the compressor and the combustor, wherein a cross-sectional area of the flow path progressively increases in size from the compressor to the combustor; and 
 extending a second section of the flow path between the combustor and the turbine, wherein a cross-sectional area of the flow path progressively decreases in size from the combustor to the turbine. 
 
     
     
         18 . The method in accordance with  claim 11  further comprising configuring the combustor to discharge the flow of combustion gas at a greater velocity than a velocity of the flow of air discharged from the compressor. 
     
     
         19 . The method in accordance with  claim 18 , wherein configuring the combustor comprises orienting the combustor such that the second flow angle is within the predetermined range, an orientation of said combustor selected as a function of a velocity gradient between the flow of air entering the combustor and the flow of combustion gas discharged from the combustor. 
     
     
         20 . The method in accordance with  claim 11 , wherein coupling a turbine comprises coupling the turbine downstream from the combustor such that the flow of combustion gas is channeled directly towards the inlet of the turbine.