High temperature anti-ice systems for aircraft engines
AssigneeGeneral Electric Company
InventorsArthur W. Sibbach, Brandon W. Miller, Jeffrey D. Clements, Daniel A. Niergarth
Life of this patent
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Abstract
Aircraft engines and high temperature anti-ice systems for aircraft engines are disclosed herein. An example aircraft engine includes: a fan including a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section; a supply duct to accept bleed air from the compressor section; and a heat exchange system to capture waste heat from the turbine section and convey the waste heat to the bleed air, the bleed air with the waste heat to be conveyed to at least one of an environmental control system or a wing of an aircraft.
Claims20
An aircraft engine comprising:
- a fan including a plurality of fan blades;
- a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section;
- a supply duct to accept bleed air from the compressor section;
- and
- a heat exchange system to capture waste heat from the turbine section and convey the waste heat to the bleed air, the bleed air with the waste heat to be conveyed to at least one of an environmental control system or a wing of an aircraft, wherein a portion of the heat exchange system is wrapped about at least a portion of the turbine section.
An aircraft engine comprising:
- a fan including a plurality of fan blades;
- a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section;
- a supply duct to accept post-combustion bleed air from the turbine section;
- and
- a heat exchange system that is wrapped about at least a portion of the turbine section, the heat exchange system to capture waste heat from the turbine section.
An aircraft engine comprising:
- a fan including a plurality of fan blades;
- a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section;
- and
- a heat exchange system including:
- a closed flowpath;
- a fluid in the closed flowpath;
- and
- a pump to circulate the fluid in the closed flowpath, wherein a portion of the closed flowpath is at least one of (1) adjacent the turbine section or (2) in a post-combustion exhaust path in the turbine section, the heat exchange system to convey waste heat to the fluid, wherein a portion of the heat exchange system is wrapped about at least a portion of the turbine section.
Dependencies are inferred from the claim text.