Structural frame integrated with variable-vectoring flow control for use in turbine systems

Abstract

The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.

What is claimed is: 
     
         1 . An apparatus for directing a compressed air flow comprising:
 an annular outer structural casing;   an annular central hub disposed within the annular outer structural casing;   a plurality of structural support elements extending radially between the annular central hub and the annular outer structural casing; and   a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the annular central hub and the annular outer structural casing and positioned circumferentially along the annular central hub between ones of the plurality of structural support elements, wherein the plurality of positionally-fixed, variable-vectoring flow control bodies are capable of actively directing the compressed air flow at variable angles but do not rotate, translate, or otherwise move with respect to the annular central hub to accomplish such variable-angle directing of the compressed air flow.   
     
     
         2 . The apparatus of  claim 1 , wherein the plurality of positionally-fixed, variable-vectoring flow control bodies comprise plasma control-type bodies, wherein the plasma control-type bodies are configured to provide an electric potential to the compressed air flow to ionize the compressed air flow and to generate an electric field that exerts a force on the ionized compressed air flow. 
     
     
         3 . The apparatus of  claim 1 , wherein the plurality of positionally-fixed, variable-vectoring flow control bodies comprise fluidic control-type bodies, wherein the fluidic control-type bodies are configured to inject and/or remove air from the compressed air flow. 
     
     
         4 . The apparatus of  claim 1 , wherein a point of maximum circumferential width of the structural support elements is positioned axially further upstream with respect to the compressed air flow as compared to a point of maximum circumferential width of the plurality of positionally-fixed, variable-vectoring flow control bodies. 
     
     
         5 . The apparatus of  claim 4 , wherein each flow control body of the plurality of positionally-fixed, variable-vectoring flow control bodies has a downstream axial end with respect to the compressed air flow that is at a first axial position with respect to the annular central hub, wherein each of the structural support elements has a downstream axial end with respect to the compressed air flow that is at a second axial position with respect to the annular central hub, and wherein the first axial position and the second axial position are substantially equal. 
     
     
         6 . The apparatus of  claim 5 , wherein a degree of curvature of the downstream axial end of the plurality of positionally-fixed, variable-vectoring flow control bodies and of the structural support elements is substantially equal. 
     
     
         7 . The apparatus of  claim 6 , wherein an axial length of the plurality of positionally-fixed, variable-vectoring flow control bodies is less than an axial length of the structural support elements. 
     
     
         8 . The apparatus of  claim 1 , wherein a maximum circumferential width of the plurality of positionally-fixed, variable-vectoring flow control bodies is less than a maximum circumferential width of the structural support elements. 
     
     
         9 . The apparatus of  claim 8 , wherein the structural support elements have a generally oblong configuration and the plurality of positionally-fixed, variable-vectoring flow control bodies have a generally circular configuration. 
     
     
         10 . The apparatus of  claim 8 , wherein both the structural support elements and the plurality of positionally-fixed, variable-vectoring flow control bodies have generally oblong configurations. 
     
     
         11 . The apparatus of  claim 1 , wherein a downstream axial end with respect to the compressed air flow of the structural support elements comprises a positionally-fixed, variable-vectoring flow control functionality, such that the downstream end of the structural support elements are configured to provide an electric potential to the compressed air flow to ionize the compressed air flow and to generate an electric field that exerts a force on the ionized compressed air flow, or are configured to inject and/or remove air from the compressed air flow. 
     
     
         12 . A turbine engine system comprising:
 a fan section that directs a flow of air along an axial path into the turbine engine system;   a compressor section, axially downstream with respect to the flow of air from the fan section, that compresses the flow of to generate a compressed air flow; and   a combustion section, axially downstream with respect to the compressed air flow from the compressor section, that combusts the compressed air flow,   wherein the compressor section comprises:
 an annular outer structural casing; 
 an annular central hub disposed within the annular outer structural casing; 
 a plurality of structural support elements extending radially between the annular central hub and the annular outer structural casing; and 
 a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the annular central hub and the annular outer structural casing and positioned circumferentially along the annular central hub between ones of the plurality of structural support elements, wherein the plurality of positionally-fixed, variable-vectoring flow control bodies are capable of actively directing the compressed air flow at variable angles but do not rotate, translate, or otherwise move with respect to the central hub to accomplish such variable-angle directing of the compressed air flow. 
   
     
     
         13 . The turbine engine system of  claim 12 , wherein the plurality of positionally-fixed, variable-vectoring flow control bodies comprise plasma control-type bodies or fluidic control-type bodies, wherein the plasma control-type bodies are configured to provide an electric potential to the compressed air flow to ionize the compressed air flow and to generate an electric field that exerts a force on the ionized compressed air flow, and wherein the fluidic control-type bodies are configured to inject and/or remove air from the compressed air flow. 
     
     
         14 . The turbine engine system of  claim 13 , wherein the compressor section comprises a low-pressure compressor and a high-pressure compressor axially downstream from the low-pressure compressor with respect to the compressed air flow, and wherein the plurality of structural support elements and the plurality of positionally-fixed, variable-vectoring flow control bodies are positioned within the high-pressure compressor. 
     
     
         15 . The turbine engine system of  claim 14 , wherein a downstream axial end with respect to the compressed air flow of the structural support elements comprises a positionally-fixed, variable-vectoring flow control functionality, such that the downstream end of the structural support elements are configured to provide an electric potential to the compressed air flow to ionize the compressed air flow and to generate an electric field that exerts a force on the ionized compressed air flow, or are configured to inject and/or remove air from the compressed air flow. 
     
     
         16 . The turbine engine system of  claim 15 , wherein a point of maximum circumferential width of the structural support elements is positioned axially further upstream with respect to the compressed air flow as compared to a point of maximum circumferential width of the plurality of positionally-fixed, variable-vectoring flow control bodies. 
     
     
         17 . The turbine engine system of  claim 16 , wherein a maximum circumferential width of the plurality of positionally-fixed, variable-vectoring flow control bodies is less than a maximum circumferential width of the structural support elements. 
     
     
         18 . The turbine engine system of  claim 12 , wherein the turbine engine system comprises a gas turbine engine. 
     
     
         19 . The turbine engine system of  claim 12 , wherein the turbine engine system comprises an auxiliary power unit (APU). 
     
     
         20 . An apparatus for directing a gas flow comprising:
 an annular outer structural casing;   an annular central hub disposed within the outer structural casing;   a plurality of structural support elements extending radially between the central hub and the outer structural casing; and   
       a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.