Methods and apparatus for operating gas turbine engines
A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.
1. A method for assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation, the gas turbine engine including a fan assembly, a booster downstream from the fan assembly, and a high pressure compressor downstream from the booster, the booster including an inlet guide vane assembly, at least one splitter, and an outlet guide vane assembly, said method comprising:
coupling at least one heat pipe to the engine such that a first closed end of the at least one heat pipe is coupled in thermal communication with a heat source; and
coupling a second closed end of the at least one heat pipe in thermal communication with and positioned within at least one of the inlet guide vane assembly and the outlet guide vane assembly that is prone to icing, such that fluid flows from the first end to the second end of the at least one heat pipe, and in an opposite flow direction from the second end to the first end of the at least one heat pipe through the at least one heat pipe to facilitate preventing ice accumulation on an outer surface of at least one of the inlet guide vane assembly and the outlet guide vane assembly that is prone to icing.
2. A method in accordance with claim 1 wherein coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source further comprises coupling the first end of the at least one heat pipe to at least one of an engine frame strut, an oil tank, a sump, and a compressor casing.
3. A method in accordance with claim 1 wherein coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source further comprises coupling the first end of the at least one heat pipe to at least one of an environmental bleed air manifold and a compressor discharge bleed air manifold.
4. A method in accordance with claim 1 wherein coupling a second end of the at least one heat pipe further comprises coupling the at least one heat pipe second end in thermal communication with at least a portion of an outer surface of an engine stator assembly.
5. A method in accordance with claim 1 wherein coupling a second end of the at least one heat pipe further comprises coupling the at least one heat pipe second end in thermal communication with at least a portion of an outer surface of an engine component such that heat transfer from the at least one heat pipe second end to the engine component outer surface facilitates preventing ice accretion across the outer surface of the engine component.
6. An ice protection system for a turbine engine, said ice protection system comprising at least one heat pipe coupled in thermal communication between a heat source and an outer surface of at least one engine component that is prone to icing, the turbine engine including a fan assembly, a booster downstream from the fan assembly, and a high pressure compressor downstream from the booster, the booster including an inlet guide vane assembly, at least one splitter, and an outlet guide vane assembly, said at least one heat pipe comprises a first closed end, a second closed end positioned within at least one of an inlet guide vane assembly and an outlet guide vane assembly, and a body extending therebetween, said body has a cross-sectional flow area that is sized to enable fluid to flow in a first direction from the first end to the second end therethrough and in a second direction from the second end to the first end therethrough during engine operation, said ice protection system facilitates at least one of preventing and mitigating ice accretion across an outer surface of at least one of the inlet guide vane assembly and the outlet guide vane assembly that is prone to icing.
7. An ice protection system in accordance with claim 6 wherein said heat source comprises at least one of an engine frame strut, an oil tank, a sump, and a compressor casing.
8. An ice protection system in accordance with claim 6 wherein said heat source comprises at least one of an environmental bleed air manifold and a compressor discharge bleed air manifold.
9. An ice protection system in accordance with claim 6 wherein said at least one heat pipe is coupled in thermal communication to an outer surface of at least one of an inlet guide vane assembly, a splitter, and an outlet guide vane assembly.
10. An ice protection system in accordance with claim 6 wherein said at least one heat pipe is coupled in thermal communication to an outer surface of at least a portion of an engine stator assembly.
11. An ice protection system in accordance with claim 6 wherein said at least one heat pipe comprises a plurality of heat pipes coupled together in thermal communication.
12. An ice protection system in accordance with claim 6 wherein said at least one heat pipe facilitates reducing at least one of engine stalls and engine flameouts.
13. A gas turbine engine comprising:
a fan assembly, a booster downstream from the fan assembly, and a high pressure compressor downstream from the booster, the booster including an inlet guide vane assembly, at least one splitter, and an outlet guide vane assembly,
a stator assembly comprising an external surface of at least one of the outlet guide vane assembly and inlet guide vane assembly that is prone to icing;
a heat source downstream from said stator assembly; and an ice protection system comprising at least one heat pipe coupled in thermal communication between said heat source and said stator assembly outer surface, said at least one heat pipe comprises a first closed end, a second closed end positioned within at least one of an inlet guide vane assembly and an outlet guide vane assembly, and a body extending therebetween, said body has a cross-sectional flow area that is sized to enable fluid to flow in a first direction from the first end to the second end therethrough and in a second direction from the second end to the first end therethrough during engine operation, said ice protection system facilitates at least one of preventing and mitigating ice accretion across the outer surface of at least one of the inlet guide vane assembly and the outlet guide vane assembly that is prone to icing.
14. A gas turbine engine in accordance with claim 13 wherein said stator assembly comprises at least one of an inlet guide vane assembly, a splitter, and an outlet guide vane assembly.
15. A gas turbine engine in accordance with claim 13 wherein said at least one ice protection system heat pipe comprises a plurality of heat pipes coupled together in thermal communication.
16. A gas turbine engine in accordance with claim 13 wherein said ice protection system facilitates reducing at least one of engine stalls and engine flameouts.
17. A gas turbine engine in accordance with claim 13 wherein said heat source comprises at least one of an engine frame strut, an oil tank, a sump, and a compressor casing.
18. An ice protection system in accordance with claim 13 wherein said heat source comprises at least one of an environmental bleed air manifold and a compressor discharge bleed air manifold.