Eductor driven anti-ice system
US-2019023405-A1 · Jan 24, 2019 · US
Ice protection system for a component of an aerodynamic system
US2022048637A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2022048637-A1 |
| Application number | US-202117462751-A |
| Country | US |
| Kind code | A1 |
| Filing date | Aug 31, 2021 |
| Priority date | Jul 11, 2018 |
| Publication date | Feb 17, 2022 |
| Grant date | — |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.
First claim
Opening claim text (preview).
What is claimed is: 1 . A method of preventing ice formation with an ice protection system on a surface of a component of an aerodynamic system, the surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the method comprising: heating the surface with a heating source of the ice protection system, and providing suction on an inwardly facing side of the heating source with a suction source to draw water melted by heating the surface through the heating source into a water collector. 2 . The method of claim 1 , wherein a flow facing side of the heating source comprises a perforated sheet. 3 . The method of claim 2 , wherein the heating source includes a drain hole extending between the perforated sheet and the suction source. 4 . The method of claim 3 , wherein the ice protection system comprises a honeycomb support structure on an inward side of the perforated sheet. 5 . The method of claim 4 , wherein the ice protection system comprises a water collector on an inwardly facing side of the honeycomb support structure. 6 . The method of claim 5 , wherein the suction source is a pump fluidly connected to the water collector. 7 . The method of claim 6 , wherein the ice protection system comprises a rigid shell on an inward facing side of the water collector. 8 . The method of claim 7 , wherein the ice protection system is coupled to a leading edge of the component. 9 . The method of claim 8 , wherein the component is a nacelle. 10 . The method of claim 8 , wherein the component is a wing.
Assignees
Inventors
Classifications
by ducted hot gas or liquid · CPC title
Heating to prevent icing · CPC title
De-icing or preventing icing on exterior surfaces of aircraft · CPC title
comprising de-icing means · CPC title
- B64D15/12Primary
by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title
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Frequently asked questions
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- What does patent US2022048637A1 cover?
- Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perf…
- Who is the assignee on this patent?
- Goodrich Corp
- What technology area does this patent fall under?
- Primary CPC classification B64D15/12. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Thu Feb 17 2022 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 2 related publications on this page (citations in our corpus or others sharing the same primary CPC).