초록 ▼

Systems are provided that may be used to diffuse and deflect the flows of gas into a plurality of gas flows. A gas flow, for example, exhaust gas, may be diffused, that is, spread out by the diffuser. A flow deflector may be coupled to the diffuser so that the gas flow may result in a plurality of g

Systems are provided that may be used to diffuse and deflect the flows of gas into a plurality of gas flows. A gas flow, for example, exhaust gas, may be diffused, that is, spread out by the diffuser. A flow deflector may be coupled to the diffuser so that the gas flow may result in a plurality of gas flows. By diffusing and allowing a plurality of gas flows, improved gas flows may be achieved.

대표청구항 ▼

1. A system comprising: a gas turbine engine having a longitudinal axis;an axial exhaust diffuser coupled to the gas turbine engine;a radial flow deflector coupled to the axial exhaust diffuser by using a plurality of rods, wherein the radial flow deflector comprises a first annular wall having a ci

1. A system comprising: a gas turbine engine having a longitudinal axis;an axial exhaust diffuser coupled to the gas turbine engine;a radial flow deflector coupled to the axial exhaust diffuser by using a plurality of rods, wherein the radial flow deflector comprises a first annular wall having a circular opening disposed concentrically with respect to the axial exhaust diffuser, wherein the radial flow deflector splits an exhaust path into an axial flow portion and a radial flow portion; and,a radial exhaust collector disposed about the axial exhaust diffuser and the radial flow deflector, wherein the radial exhaust collector is configured to route exhaust gas along a radial path away from the longitudinal axis, wherein each of the plurality of rods does not extend past a wide end of the first annular wall. 2. The system of claim 1, wherein the first annular wall comprises a diameter that gradually expands in a downstream direction along the longitudinal axis. 3. The system of claim 2, wherein the first annular wall comprises a bell-shaped wall that curves from a first angle to a second angle relative to the longitudinal axis, wherein a difference between the first and second angles is at least approximately 45 degrees. 4. The system of claim 1, wherein the wide end of the first annular wall is disposed to bisect a chamber of the radial exhaust collector into two approximately equal sections. 5. The system of claim 1, comprising a thermally-insulated bore coupled to the axial exhaust diffuser, wherein the axial exhaust diffuser is disposed about the thermally-insulated bore. 6. The system of claim 5, wherein the axial exhaust diffuser is coupled to the thermally-insulated bore via a plurality of airfoil-shaped ribs. 7. The system of claim 1, wherein the exhaust gas comprises a flow rate of between 0 and 450 lbs/sec. 8. The system of claim 1, wherein the axial exhaust diffuser comprises a second annular wall with a diameter that gradually expands in a downstream direction along the longitudinal axis. 9. The system of claim 1, wherein the radial exhaust deflector is disposed concentrically between the axial exhaust diffuser and a central bore. 10. The system of claim 1, comprising only one of the annular wall. 11. The system of claim 10, wherein the radial exhaust collector comprises a chamber having a cone disposed on a downstream wall of the chamber, and wherein a wide end of the annular wall is disposed to evenly bisect the chamber. 12. The system of claim 11, wherein a narrow end of the annular wall is approximately between 0 inches to 5 inches from a rear rim of the axial exhaust diffuser. 13. The system of claim 10, wherein the axial exhaust diffuser is coupled to the chamber by using a collector flange, a diffuser flange, and an o-ring. 14. The system of claim 13, wherein the axial exhaust diffuser is coupled to the chamber by using only the collector flange, the diffuser flange, and the o-ring. 15. A system comprising: a turbine exhaust diffuser configured to diffuse a turbine exhaust gas flow in an axial direction; and,a radial flow deflector coupled to the turbine exhaust diffuser, wherein the radial flow deflector comprises an annular wall having a circular opening disposed concentrically with respect to the turbine exhaust diffuser, and coupled to the turbine exhaust diffuser by using a plurality of support arms, wherein the radial flow deflector splits the turbine exhaust gas flow into a radial exhaust flow portion and an axial exhaust flow portion, and wherein the annular wall comprises a first diameter greater than a second diameter of the turbine exhaust diffuser, and wherein each of the plurality of support arms does not extend past a wide end of the annular wall. 16. The system of claim 15, comprising a gas turbine engine coupled to the turbine exhaust diffuser. 17. The system of claim 15, wherein the radial flow deflector comprises a bell-shaped wall. 18. The system of claim 17, wherein the bell-shaped wall curves from a first angle to a second angle relative to the axial direction, wherein a difference between the first and second angles is at least approximately 60 degrees. 19. The system of claim 15, wherein the turbine exhaust diffuser comprises a first annular wall with a first diameter that gradually expands in the axial direction, the radial flow deflector comprises a second annular wall with a second diameter that gradually expands in the axial direction, the first and second annular walls are coaxial with one another, and the second annular wall is disposed radially between the first annular wall and a third annular wall of a central bore. 20. The system of claim 19, wherein the radial flow deflector is coupled to the turbine exhaust diffuser via a plurality of circumferentially placed rods. 21. The system of claim 20, wherein the turbine exhaust diffuser is coupled to the central bore via a plurality of airfoil-shaped ribs. 22. A system comprising: a turbine diffuser retrofit kit, comprising: a radial flow deflector comprising a first annular wall with a first diameter that gradually expands in an axial direction along a central axis of the radial flow deflector; anda plurality of rods configured to couple the radial flow deflector to an axial exhaust diffuser of a gas turbine engine, wherein the first annular wall comprises a circular opening and wherein the radial flow deflector is configured to be disposed downstream of the exhaust diffuser so that the circular opening is concentric with respect to the axial exhaust diffuser and so that a wide end of the first annular wall bisects a chamber of the axial exhaust diffuser into a first section having a first axial distance and a second section having a second axial distance, and wherein a ratio between the first axial distance to the second axial distance is approximately 0.9 to 1.1, and wherein each of the plurality of rods does not extend past a wide end of the first annular wall. 23. The system of claim 22, wherein the first annular wall comprises a bell-shaped wall that curves from a first angle to a second angle relative to the axial direction, wherein a difference between the first and second angles is at least approximately 75 degrees. 24. The system of claim 22, comprising the axial exhaust diffuser retrofitted into a turbine system by using the turbine diffuser retrofit kit, wherein the axial exhaust diffuser comprises a second annular wall with a second diameter that gradually expands in the axial direction along the central axis, and the first and second annular walls are coaxial with one another. 25. The system of claim 24, comprising a radial exhaust collector disposed about the axial exhaust diffuser with the radial flow deflector, wherein the radial exhaust collector comprises a conical wall downstream from the axial exhaust diffuser.