Nacelle anti-icing system
AssigneeQuiet Nacelle Corporation
InventorFernando Birbragher
Life of this patent
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Abstract
A nacelle anti-icing system for a jet engine and a method for preventing icing of the nacelle. The nacelle anti-icing system includes a nose cowling assembly having a nose ring and an inlet duct connected to the nose ring, the nose ring including a plurality of openings formed therein; a nose cowling conduit positioned in the nose ring for communicating a heated gas to the plurality of openings formed in the nose ring and for creating a heated gas boundary layer on the inlet duct, and a mechanism connected to the nose cowling conduit for generating the heated gas. The method includes the steps of feeding a heated gas through the nose cowling conduit and through a plurality of openings formed in the nose ring and generating a heated gas boundary layer on the inlet duct so as to heat the inlet duct.
Claims10
A nacelle anti-icing system for a jet engine, comprising:
- a nose cowling assembly which includes a nose ring and an inlet duct connected to said nose ring and having an inner and outer circumferential surface portion, said nose ring including a plurality of openings formed therein;
- nose cowling conduit means positioned in said nose ring for communicating a heated gas to said plurality of openings formed in said nose ring and for creating a heated gas boundary layer on said inner circumferential surface of said inlet duct and for communicating said heated gas internally of said outer circumferential surface portion of said inlet duct;
- and
- duct means positioned between said inner and outer circumferential surface portions of said inlet duct and connected to said nose cowling conduit means for communicating said heated gas to said conduit means wherein said nose cowling assembly comprises a first bulkhead member positioned within said nose ring and a plurality of first spacer members interconnecting said first bulkhead member and an inner surface portion of said nose ring and wherein said first spacer members are circumferentially spaced about said first bulkhead member so as to form first passages between said first spacer members and which communicate directly with said inner circumferential surface of said inlet duct.
A method for preventing icing of a nacelle for a jet engine having a nose cowling assembly which includes a nose ring, an inlet duct having an inner and outer circumferential surface and connected to said nose ring, said nose ring including a plurality of openings formed therein, and nose cowling conduit means positioned in said nose ring and connected to said plurality of openings and duct means positioned between said inner and outer circumferential surface of said inlet duct and connected to said nose cowling conduit means for communicating said heated gas to said conduit means wherein said nose cowling assembly comprises a first bulkhead member positioned within said nose ring and a plurality of first spacer members interconnecting said first bulkhead member and an inner surface portion of said nose ring and wherein said first spacer members are circumferentially spaced about said first bulkhead member so as to form first passages between said first spacer members and which communicate directly with said inner circumferential surface of said inlet duct, which comprises:
- feeding a heated gas to said nose cowling conduit means and through said first passages directly to said inner circumferential surface of said inlet duct;
- generating a heated gas boundary layer on said inlet duct so as to heat said inlet duct;
- feeding said heated gas internally to an outer circumferential surface portion of said nose ring and said nose cowling assembly so as to heat said outer circumferential surface portion of said nose ring and said cowling assembly.
Dependencies are inferred from the claim text.