Multi-element propeller blade deicer scheme for balanced three-phase electrical loads
AssigneeHamilton Sundstrand Corporation
InventorDavid R. Danielson
Life of this patent
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Abstract
Provided are embodiments for deicing an aircraft propeller having a plurality of blades of an aircraft. An example method includes performing a first heating, by a first plurality of heating elements connected to a first portion of each of the plurality of blades, for a first period of time, the first portion of each of the plurality of blades of the propeller defining a first deicing zone. The method further includes, subsequent to expiration of the first period of time, performing a second heating, by a second plurality of heating elements connected to a second portion of each of the plurality of blades, for a second period of time, the second portion of each of the plurality of blades of the propeller defining a second deicing zone.
Claims20
A method for deicing an aircraft propeller having a plurality of blades of an aircraft, the method comprising:
- performing a first heating, with current from a three phase generator by a first plurality of heating elements connected to a first portion of each of the plurality of blades, for a first period of time, the first portion of each of the plurality of blades of the propeller defining a first deicing zone, the first deicing zone being formed radially about a center point of the propeller;
- and
- subsequent to expiration of the first period of time, performing a second heating, by a second plurality of heating elements connected to a second portion of each of the plurality of blades, for a second period of time, the second portion of each of the plurality of blades of the propeller defining a second deicing zone, the second deicing zone being formed radially about the center point of the propeller, the second deicing zone differing from the first deicing zone,
- wherein while performing the first heating current from one phase of the three phase generator is applied to a first of the first plurality of heating elements on a first of the plurality of blades and current from another phase of the three phase generator is applied to a second of the first plurality of heating elements on a second of the plurality of blades;
- wherein, while performing the second heating, a current is supplied to the respective first plurality of heating elements and the second plurality of heating elements from each of three phases of the three-phase power generation device associated with the aircraft, a load on each of the three phases being balanced.
An aircraft comprising:
- a propeller comprising a first plurality of heating elements disposed in a plurality of blades of the propeller and a second plurality of heating elements disposed in the plurality of blades of the propeller, wherein each of the plurality of first heating elements is disposed between a center point of the propeller and the respective each of the second heating elements;
- a three-phase power generation device selectively providing a current to the first plurality of heating elements and the second plurality of heating elements;
- and
- a processing device for executing computer readable instructions stored in a memory, the computer readable instructions controlling the processing device to perform operations comprising:
- causing heating, by the first plurality of heating elements connected to a first portion of each of the plurality of blades, for a first period of time, the first portion of each of the plurality of blades of the propeller defining a first deicing zone, the first deicing zone being formed radially about a center point of the propeller;
- and
- subsequent to expiration of the first period of time, causing heating, by the second plurality of heating elements connected to a second portion of each of the plurality of blades, for a second period of time, the second portion of each of the plurality of blades of the propeller defining a second deicing zone, the second deicing zone being formed radially about the center point of the propeller, the second deicing zone differing from the first deicing zone,
- wherein, while performing the first heating current from one phase is applied to a first of the first plurality of heating elements on a first of the plurality of blades and current from another phase is applied to a second of the first plurality of heating elements on a second of the plurality of blades;
- wherein, while performing the second heating, the current is supplied to the respective first plurality of heating elements and the second plurality of heating elements from each of three phases of the three-phase power generation device, a load on each of the three phases being balanced.
Dependencies are inferred from the claim text.