Methods and apparatus for operating gas turbine engines
AssigneeGeneral Electric Company
InventorsKattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching-Pang Lee
Life of this patent
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Abstract
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.
Claims18
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.
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.
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.
Dependencies are inferred from the claim text.