Method and apparatus for aircraft anti-icing
AssigneeRohr, Inc.
InventorsSteven M. Kestler, Sarah Lohman, Manuel Muñoz, Xiaolan Hu, Jay Francisco, Vijay V. Pujar
Life of this patent
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Abstract
An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.
Claims20
An apparatus for aircraft anti-icing, the apparatus comprising:
- a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle head, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall;
- and
- a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the neck is less than a maximum width of the through-hole.
An aircraft anti-icing system comprising:
- a source of a high temperature gas;
- a housing;
- a conduit configured to carry the high temperature gas from the source to the housing;
- a nozzle coupled to the conduit, the nozzle comprising:
- a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall;
- and
- a neck extending from the outer wall of the nozzle head, the neck configured to supply the high temperature gas to the plenum, and the high temperature gas exits the nozzle via the plenum, wherein a maximum width of the neck is less than a maximum width of the through-hole.
A method for preventing formation of ice, the method comprising:
- receiving, at a nozzle, a hot gas from a compression stage of an engine;
- and
- providing, via a nozzle head, the hot gas received from the compression stage to an internal volume of a leading edge housing, wherein the nozzle head provides the hot gas based on a flow pattern, wherein the flow pattern is determined based, at least in part, on a geometry of the nozzle head that has an inner wall and an outer wall, wherein the inner wall defines a through-hole that passes through the nozzle head, and wherein the hot gas passes between the inner wall and the outer wall, wherein a neck extends from the outer wall whereby the nozzle head receives the hot gas, a maximum width of the neck is less than a maximum width of the through-hole.
Dependencies are inferred from the claim text.