초록 ▼

In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-pressure turbine spool to have a r

In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-pressure turbine spool to have a relatively larger diameter than the high-pressure turbine spool. One or more unobstructed fluid flow paths between one or more boundary layer suction ports disposed within the upstream end of the outer-body surface of the inter-turbine duct and the suction side of the associated low-pressure turbine nozzle are provided. Advantageously, the natural static pressure difference between these points results in a self-aspirating assembly. The fluid flow control provided by the respective suction and blowing forces generated allows for a relatively larger diameter low-pressure turbine spool and/or relatively fewer low-pressure turbine nozzles to be used than is possible with conventional systems, assemblies, and methods. Thus, a gas turbine engine weight savings and optimized performance may be achieved.

대표청구항 ▼

1. An inter-turbine duct assembly for use in a gas turbine engine or the like, the inter-turbine duct assembly comprising:a duct configured to receive flow from a turbine, the duct having an upstream end and a downstream end, wherein the duct comprises an inner-body surface and an outer-body surface

1. An inter-turbine duct assembly for use in a gas turbine engine or the like, the inter-turbine duct assembly comprising:a duct configured to receive flow from a turbine, the duct having an upstream end and a downstream end, wherein the duct comprises an inner-body surface and an outer-body surface, and wherein the duct forms a primary fluid flow path; a port disposed within the outer-body surface of the duct; a nozzle coupled with the duct; and a channel having an upstream end and a downstream end, wherein the upstream end of the channel is coupled with the port and the downstream end of the channel is disposed within the nozzle, and wherein the channel forms a bypass fluid flow path between the duct and the nozzle. 2. The inter-turbine duct assembly of claim 1, wherein the duct comprises a first annular structure.3. The inter-turbine duct assembly of claim 1, wherein the port comprises a region of porous material.4. The inter-turbine duct assembly of claim 2, wherein the nozzle comprises a second annular structure.5. The inter-turbine duct assembly of claim 1, wherein the channel comprises a tube.6. The inter-turbine duct assembly of claim 1, wherein the channel comprises a third annular structure.7. The inter-turbine duct assembly of claim 1, further comprising an exhaust piece coupled with the downstream end of the channel.8. The inter-turbine duct assembly of claim 1, wherein the port is disposed adjacent to a fluid flow boundary layer present within the duct adjacent to the outer-body surface of the duct.9. The inter-turbine duct assembly of claim 1, wherein the port is disposed between the upstream end of the duct and a fluid flow boundary layer separation point present within the duct along the outer-body surface of the duct.10. The inter-turbine duct assembly of claim 1, where the port is disposed upstream or downstream of and in close proximity to fluid flow boundary layer separation point present within the duct along the outer-body surface of the duct.11. The inter-turbine duct assembly of claim 1, wherein a first region defined by the duct comprises a region of relatively high pressure.12. The inter-turbine duct assembly of claim 11, wherein a second region defined by the nozzle comprises a region of relatively low pressure.13. The inter-turbine duct assembly of claim 12, wherein the channel forms a bypass fluid flow path between the first region of relatively high pressure of the duct and the second region of relatively low pressure of the nozzle.14. The inter-turbine duct assembly of claim 1, wherein the fluid comprises a gas.15. An inter-turbine duct assembly for use in a gas turbine engine or the like, the inter-turbine duct assembly comprising:an inter-turbine duct having an upstream end and a downstream end, wherein the inter-turbine duct comprises an inner-body surface and an outer-body surface, and wherein the inter-turbine duct forms a primary fluid flow path; a boundary layer suction port disposed within the outer-body surface of the inter-turbine duct; a low-pressure turbine nozzle coupled with the inter-turbine duct; and a bypass channel having an upstream end and a downstream end, wherein the upstream end of the bypass channel is coupled with the boundary layer suction port and the downstream end of the bypass channel is disposed within the low-pressure turbine nozzle, and wherein the bypass channel forms a bypass fluid flow path between the inter-turbine duct and the low-pressure turbine nozzle. 16. The inter-turbine duct assembly of claim 15, wherein the inter-turbine duct comprises a first annular structure disposed about an axis of the inter-turbine duct assembly.17. The inter-turbine duct assembly of claim 15, wherein the boundary layer suction port comprises a region of porous material.18. The inter-turbine duct assembly of claim 16, wherein the low-pressure turbine nozzle comprises a second annular structure disposed about an axis of the inter-turbine duct assembly.19. The inter-turbine duct assembly of claim 15, wherein the bypass channel comprises a tube.20. The inter-turbine duct assembly of claim 18, wherein the bypass channel comprises a third annular structure disposed about an axis of the inter-turbine duct assembly.21. The inter-turbine duct assembly of claim 15, further comprising an exhaust piece coupled with the downstream end of the bypass channel.22. The inter-turbine duct assembly of claim 15, wherein the boundary layer suction port is disposed adjacent to a fluid flow boundary layer present within the inter-turbine duct adjacent to the outer-body surface of the inter-turbine duct.23. The inter-turbine duct assembly of claim 15, wherein the boundary layer suction port is disposed between the upstream end of the inter-turbine duct and a fluid flow boundary layer separation point present within the inter-turbine duct along the outer-body surface of the inter-turbine duct.24. The inter-turbine duct assembly of claim 15, wherein a first region defined by the inter-turbine duct comprises a region of relatively high pressure.25. The inter-turbine duct assembly of claim 24, wherein a second region defined by the low-pressure turbine nozzle comprises a region of relatively low pressure.26. The inter-turbine duct assembly of claim 25, wherein the bypass channel forms a bypass fluid flow path between the first region of relatively high pressure of the inter-turbine duct and the second region of relatively low pressure of the low-pressure turbine nozzle.27. The inter-turbine duct assembly of claim 15, wherein the fluid comprises a combustion gas.28. A gas turbine engine system, comprising:a high-pressure turbine rotor, wherein the high-pressure turbine rotor comprises a first plurality of airfoils; a low-pressure turbine nozzle, wherein the low-pressure turbine nozzle comprises a second plurality of airfoils; an inter-turbine duct having an upstream end and a downstream end, the inter-turbine duct disposed between the high-pressure turbine rotor and the low-pressure turbine nozzle, wherein the inter-turbine duct comprises an inner-body surface and an outer-body surface, and wherein the inter-turbine duct forms a primary fluid flow path; a boundary layer suction port disposed within the outer-body surface of the inter-turbine duct; a bypass channel having an upstream end and a downstream end, wherein the upstream end of the bypass channel is coupled with the boundary layer suction port and the downstream end of the bypass channel is disposed within the low-pressure turbine nozzle, and wherein the bypass channel forms a bypass fluid flow path between the inter-turbine duct and the low-pressure turbine nozzle. 29. The gas turbine engine system of claim 28, wherein the inter-turbine duct comprises a first annular structure disposed about an axis of the gas turbine engine system.30. The gas turbine engine system of claim 28, wherein the boundary layer suction port comprises a region of porous material.31. The gas turbine engine system of claim 29, wherein the low-pressure turbine nozzle comprises a second annular structure disposed about an axis of the gas turbine engine system.32. The gas turbine engine system of claim 28, wherein the bypass channel comprises a tube.33. The gas turbine engine system of claim 31, wherein the bypass channel comprises a third annular structure disposed about an axis of the gas turbine engine system.34. The gas turbine engine system of claim 28, further comprising an exhaust piece coupled with the downstream end of the bypass channel.35. The gas turbine engine system of claim 28, wherein the boundary layer suction port is disposed adjacent to a fluid flow boundary layer present within the inter-turbine duct adjacent to the outer-body surface of the inter-turbine duct.36. The gas turbine engine system of claim 28, wherein the boundary layer suction port is disposed between the upstream end of the inter-turbine duct and a fluid flow boundary layer separation point present within the inter-turbine duct along the outer-body surface of the inter-turbine duct.37. The gas turbine engine system of claim 28, wherein a first region defined by the inter-turbine duct comprises a region of relatively high pressure.38. The gas turbine engine system of claim 37, wherein a second region defined by the low-pressure turbine nozzle comprises a region of relatively low pressure.39. The gas turbine engine system of claim 38, wherein the bypass channel forms a bypass fluid flow path between the first region of relatively high pressure of the inter-turbine duct and the second region of relatively low pressure of the low-pressure turbine nozzle.40. The gas turbine engine system of claim 28, wherein the fluid comprises a combustion gas.41. A method for optimizing the performance of a gas turbine engine or the like, the method comprising:given a primary fluid flow through an inter-turbine duct of the gas turbine engine, diverting a predetermined portion of the primary fluid flow into a bypass channel; transmitting the predetermined portion of the primary fluid flow to a low-pressure turbine nozzle of the gas turbine engine; and expelling the predetermined portion of the primary fluid flow into the interior of the low-pressure turbine nozzle. 42. The method of claim 41, wherein the predetermined portion of the primary fluid flow comprises a bypass fluid flow.43. The method of claim 41, wherein diverting the predetermined portion of the primary fluid flow into the bypass channel comprises diverting a predetermined portion of a boundary layer fluid flow from along an outer-body surface of the inter-turbine duct.44. The method of claim 43, wherein diverting the predetermined portion of the primary fluid flow into the bypass channel comprises diverting the predetermined portion of the boundary layer fluid flow from a predetermined point prior to a boundary layer separation point along the outer-body surface of the inter-turbine duct.45. The method of claim 41, further comprising providing an inter-turbine duct comprising an outer-body surface having a predetermined slope.46. The method of claim 45, wherein the slope of the inter-turbine duct is about 40 degrees.47. The method of claim 41, further comprising providing an inter-turbine duct comprising an outer-body surface having a predetermined length.48. The method of claim 47, wherein the length of the inter-turbine duct is less than about twice the height of the high-pressure turbine rotor.49. An inter-turbine duct assembly for use in a gas turbine engine or the like, the inter-turbine duct assembly comprising:a duct having an upstream end and a downstream end, wherein the duct comprises an inner-body surface and an outer-body surface, and wherein the duct forms a primary fluid flow path; a port disposed within the outer-body surface of the duct between the upstream end of the duct and a fluid flow boundary layer separation point present within the duct along the outer-body surface of the duct; a nozzle coupled with the duct; and a channel having an upstream end and a downstream end, wherein the upstream end of the channel is coupled with the port and the downstream end of the channel is disposed within the nozzle, and wherein the channel forms a bypass fluid flow path between the duct and the nozzle.