초록 ▼

A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an ou

A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust.

대표청구항 ▼

1. A system for cooling a generator mounted in a cavity of an engine tail-cone, the engine comprising a casing having the tail-cone coupled thereto, a core compartment within the casing, and an intake for drawing air into the casing, the system comprising: a bypass passage defined between the casing

1. A system for cooling a generator mounted in a cavity of an engine tail-cone, the engine comprising a casing having the tail-cone coupled thereto, a core compartment within the casing, and an intake for drawing air into the casing, the system comprising: a bypass passage defined between the casing and the core compartment, the bypass passage adapted to divert a bypass portion of the air therethrough;at least one fairing coupled to the tail-cone in fluid communication with the bypass passage and the tail-cone cavity, the at least one fairing configured to direct the bypass portion of the air towards the tail-cone cavity through an inlet positioned in a plane substantially orthogonal to a longitudinal plane of the engine; anda support strut coupled to the casing in fluid communication with the bypass passage and the tail-cone cavity and adapted to expel the bypass portion of the air from the tail-cone cavity towards the bypass passage via an outlet positioned in the plane substantially orthogonal to a longitudinal plane of the engine, thereby exposing the inlet of the at least one fairing and the outlet of the support strut to a same level of static pressure. 2. The system of claim 1, wherein the at least one fairing is adapted to accommodate therein a plurality of lines for servicing the engine and further wherein the bypass portion of the air routed through the at least one fairing enables cooling of the plurality of lines. 3. The system of claim 1, further comprising a lobe mixer coupled to the tail-cone in fluid communication with the bypass passage and the core compartment, the lobe mixer having a plurality of lobes for routing the bypass portion of the air towards a portion of the air routed through the core compartment and the at least one fairing being routed within a selected one of the lobes. 4. The system of claim 3, wherein the selected lobe comprises at least one shield for preventing impingement on the fairing of the portion of the air routed through the core compartment. 5. The system of claim 4, wherein the at least one shield comprises a first shield extending axially away from a first side edge of the selected lobe and a second shield extending axially away from a second side edge of the selected lobe opposite to the first side edge. 6. The system of claim 5, wherein the at least one shield comprises a third shield extending radially away from a middle edge of the selected lobe. 7. The system of claim 3, wherein the portion of the air routed through the core compartment impinges on the lobe mixer and an inner surface of the selected lobe is spaced from an outer surface of the at least one fairing for reducing heat transfer between the bypass portion of the air routed through the fairing and the portion of the air impinging on the lobe mixer. 8. The system of claim 1, wherein the tail-cone comprises an inner wall and an outer wall exposed to a portion of the air routed through the core compartment and further wherein the at least one fairing is coupled to the inner wall. 9. A method for cooling a generator mounted in a cavity of an engine tail-cone, the engine comprising a casing having the tail-cone coupled thereto, a core compartment within the casing, and an intake for drawing air into the casing, the method comprising: diverting a bypass portion of the air through a bypass passage defined between the casing and the core compartment;directing the bypass portion of the air through at least one fairing in fluid communication with the bypass passage and the tail-cone cavity and towards the tail-cone cavity through an inlet positioned in a plane substantially orthogonal to a longitudinal plane of the engine; andexpelling the bypass portion of the air from the tail-cone cavity and towards the bypass passage through a support strut in fluid communication with the bypass passage and the tail-cone cavity via an outlet positioned in the plane substantially orthogonal to a longitudinal plane of the engine, thereby exposing the inlet of the at least one fairing and the outlet of the support strut to a same level of static pressure. 10. The method of claim 9, further comprising accommodating in the at least one fairing a plurality of lines for servicing the engine, wherein routing the bypass portion of the air through the at least one fairing enables cooling of the plurality of lines. 11. The method of claim 9, further comprising routing the at least one fairing within a selected one of a plurality of lobes of a lobe mixer coupled to the tail-cone in fluid communication with the bypass passage and the core compartment, the plurality of lobes routing the bypass portion of the air towards a portion of the air routed through the core compartment. 12. The method of claim 11, further comprising providing at least one shield on the selected lobe for preventing impingement on the fairing of the portion of the air routed through the core compartment, said portion impinging on the lobe mixer. 13. The method of claim 11, wherein routing the at least one fairing within the selected lobe comprises spacing an inner surface of the selected lobe from an outer surface of the at least one fairing for preventing heat transfer between the bypass portion of the air routed through the fairing and the portion of the air routed through the core compartment. 14. The method of claim 9, further comprising coupling the at least one fairing to an inner wall of the tail-cone. 15. A system for cooling a generator mounted in a cavity of an engine tail-cone, the engine comprising a casing having the tail-cone coupled thereto, a core compartment within the casing, and an intake for drawing air into the casing, the method comprising: means for diverting a bypass portion of the air through a bypass passage defined between the casing and the core compartment;means for directing the bypass portion of the air through at least one fairing in fluid communication with the bypass passage and the tail-cone cavity and towards the tail-cone cavity through an inlet positioned in a plane substantially orthogonal to a longitudinal plane of the engine; andmeans for expelling the bypass portion of the air from the tail-cone cavity and towards the bypass passage through a support strut in fluid communication with the bypass passage and the tail-cone cavity via an outlet positioned in the plane substantially orthogonal to a longitudinal plane of the engine, thereby exposing the inlet of the at least one fairing and the outlet of the support strut to a same level of static pressure.