Method and apparatus for aircraft anti-icing
First Claim
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1. An aircraft anti-icing system comprising:
- a source of high temperature gas;
a housing;
at least one conduit configured to carry the high temperature gas from the source to the housing;
at least one nozzle coupled to said at least one conduit, said at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing; and
a port for exhausting air from the housing;
wherein said at least one nozzle comprises a longitudinal axis and a plurality of tubes wrapped around the longitudinal axis of the at least one nozzle to form a helix; and
wherein the housing comprises one of a nose cowl and a wing.
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Abstract
An aircraft anti-icing system includes a source of high temperature gas, a housing, at least one conduit to carry the high temperature gas from the source to the housing, the at least one conduit coupled to the housing and the source, at least one nozzle coupled to the at least one conduit, at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing, and a port for exhausting air from the housing.
68 Citations
12 Claims
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1. An aircraft anti-icing system comprising:
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a source of high temperature gas; a housing; at least one conduit configured to carry the high temperature gas from the source to the housing; at least one nozzle coupled to said at least one conduit, said at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing; and a port for exhausting air from the housing; wherein said at least one nozzle comprises a longitudinal axis and a plurality of tubes wrapped around the longitudinal axis of the at least one nozzle to form a helix; and wherein the housing comprises one of a nose cowl and a wing. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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Specification