초록 ▼

An exhaust system for gas turbine engine is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine. In various embodiments, the system includes an exhaust plenum that provides a gradual expansion of the exhaust gases. The exh

An exhaust system for gas turbine engine is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine. In various embodiments, the system includes an exhaust plenum that provides a gradual expansion of the exhaust gases. The exhaust plenum may also include one or more flow splitters that further reduce turbulence in the plenum and provide a more uniform gas flow in the plenum and other downstream exhaust components.

대표청구항 ▼

1. A system, comprising: a turbine engine comprising a radial diffuser disposed about a first axis downstream in an exhaust flow path from a turbine section; andan exhaust plenum, comprising: an inlet, wherein the radial diffuser is disposed through the inlet into the exhaust plenum, and the exhaust

1. A system, comprising: a turbine engine comprising a radial diffuser disposed about a first axis downstream in an exhaust flow path from a turbine section; andan exhaust plenum, comprising: an inlet, wherein the radial diffuser is disposed through the inlet into the exhaust plenum, and the exhaust plenum extends along a second axis crosswise relative to the first axis of the turbine engine;a flow splitter extending completely across the exhaust plenum along the first axis, wherein the flow splitter extends in a first direction radially outward from the radial diffuser relative to the first axis, and the flow splitter bends from the first direction to a second direction downstream along the second axis; anda set of first and second aerodynamic surfaces facing one another about the radial diffuser, wherein the first and second aerodynamic surfaces are axially offset from one another by an axial offset along the first axis, and the first and second aerodynamic surfaces gradually expand the axial offset with increasing radial distance away from the first axis. 2. The system of claim 1, wherein the radial diffuser comprises a plurality of circular vanes disposed about the first axis, and the flow splitter extends in the first direction radially outward from the vanes. 3. The system of claim 1, wherein the flow splitter bends at least approximately 90 degrees from the first direction to the second direction. 4. The system of claim 1, wherein the flow splitter extends in the first direction at an angle of approximately 90 degrees relative to the second axis. 5. The system of claim 1, wherein the flow splitter extends downstream along the second axis to an axial offset away from the radial diffuser. 6. The system of claim 1, wherein the flow splitter extends from the first direction to the second direction with a length of at least greater than a radius of the radial diffuser. 7. The system of claim 1, comprising another flow splitter extending completely across the exhaust plenum along the first axis, wherein the other flow splitter extends in a third direction radially outward from the radial diffuser relative to the first axis, the other flow splitter bends from the third direction to a fourth direction downstream along the second axis. 8. The system of claim 1, wherein the first and second aerodynamic surfaces comprise conical surfaces diverging away from one another in an outward radial direction away from the first axis. 9. The system of claim 1, wherein the first and second aerodynamic surfaces comprise diverging surfaces that diverge away from one another in an outward radial direction away from the first axis at a rate of less than about 115 percent of a change in axial offset versus a change in radial distance. 10. A system, comprising: a turbine exhaust plenum, comprising: an inlet coupled to a diffuser region configured to receive a radial diffuser of a turbine engine along a first axis, wherein the turbine exhaust plenum extends along a second axis crosswise relative to the first axis; anda flow splitter extending completely across the turbine exhaust plenum along the first axis adjacent the diffuser region, wherein the flow splitter extends from an upstream end to a downstream end with a length of at least greater than a radius of the radial diffuser, and the flow splitter bends from the upstream end to the downstream end over an angle of at least approximately 90 degrees. 11. The system of claim 10, wherein the flow splitter is configured to split and route exhaust flow to provide a substantially uniform flow distribution. 12. The system of claim 10, wherein the diffuser region is positioned in the turbine exhaust plenum at an off-center position relative to the first axis, and wherein the diffuser region is closer to a first side and farther from a second side opposite from the first side about the first axis, and the flow splitter is disposed on the second side. 13. The system of claim 10, wherein the flow splitter comprises first and second flow splitters disposed on opposite first and second sides of the diffuser region about the first axis, each of the first and second flow splitters has the length of at least greater than the radius of the radial diffuser, and each of the first and second flow splitters bends from the upstream end to the downstream end over the angle of at least approximately 90 degrees. 14. The system of claim 10, wherein the diffuser region is centered within the turbine exhaust plenum relative to a width of the turbine exhaust plenum along the first axis, and the diffuser region is centered within the turbine exhaust plenum relative to a height of the turbine exhaust plenum along a third axis crosswise to both the first and second axes. 15. The system of claim 10, comprising a second flow splitter extending completely across the turbine exhaust plenum along the first axis adjacent the diffuser region, wherein the second flow splitter extends from an second upstream end to a second downstream end, and the first downstream end and the second downstream end lie in a plane orthogonal to the second axis. 16. The system of claim 10, comprising aerodynamic surfaces positioned about the first axis and surrounding the inlet, wherein the aerodynamic surfaces provide an initial plenum width at the inlet and gradually slope outward to a full plenum width at a location radially away from the inlet relative to the first axis. 17. A system, comprising: a turbine exhaust plenum, comprising: an inlet coupled to a diffuser region configured to receive a radial diffuser of a turbine engine along a first axis, wherein the turbine exhaust plenum extends along a second axis crosswise relative to the first axis; anda set of first and second aerodynamic surfaces disposed opposite from one another relative to the diffuser region, wherein the first and second aerodynamic surfaces diverge away from one another in an outward radial direction away from the first axis. 18. The system of claim 17, wherein the first and second aerodynamic surfaces comprise conical surfaces diverging away from one another in the outward radial direction away from the first axis. 19. The system of claim 18, wherein the conical surfaces are axially offset from one another by an axial offset along the first axis. 20. The system of claim 19, wherein the conical surfaces diverge away from one another in the outward radial direction away from the first axis at a rate of less than about 115 percent of a change in the axial offset versus a change in radial distance.