Anterior part of a nacelle of an aircraft propulsion unit having a shock absorbing element
US-2019195085-A1 · Jun 27, 2019 · US
Air inlet lip of an aircraft engine comprising a de-icing system
US11073081B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11073081-B2 |
| Application number | US-201816145367-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 28, 2018 |
| Priority date | Oct 18, 2017 |
| Publication date | Jul 27, 2021 |
| Grant date | Jul 27, 2021 |
How to read this patent
A practical reading order for non-experts. Skip the full description unless you need deep technical detail.
- Title
What the patent document calls the invention.
- Abstract
A short plain-language summary of the technical disclosure.
- Assignees and inventors
Who owns or filed the patent and who is credited as inventor.
- Key dates
Filing, priority, publication, and grant dates set the timeline.
- First independent claim
The legal scope of protection — read this for what is actually claimed.
- CPC / IPC classifications
Technology tags used to group this patent with similar filings.
- Citations and related patents
Prior art links and similar publications in this corpus.
Abstract
Official abstract text for this publication.
An aircraft engine air inlet lip takes an annular form about a longitudinal axis and delimits an air inlet stream, and includes: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards interior of the air inlet lip, an inner wall extending inside the wall between two zones of the inner face, so as to close an inner chamber delimited between the wall and the inner wall and filled with a gas, the inner wall having an upstream face oriented towards and a downstream face oriented away from the inner chamber, a fan configured to move the gas contained in the inner chamber, and at least one pipeline fixed to the upstream face and extending all around the air inlet lip and configured to be fed with a heat transfer fluid heated by a heat source.
First claim
Opening claim text (preview).
The invention claimed is: 1. An aircraft engine comprising a core, a heat source, a nacelle surrounding the core and at the front of which is arranged an air inlet lip taking an annular form about a longitudinal axis X and delimiting an air inlet stream, said air inlet lip comprising: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards an interior of the air inlet lip; an inner wall extending inside the wall between two zones of the inner face, so as to close an inner chamber delimited between the wall and the inner wall and filled with a gas, the inner wall having an upstream face oriented towards the inner chamber and a downstream face oriented away from the inner chamber; a fan configured to move the gas contained in the inner chamber; and at least one pipeline fixed to the upstream face and extending all around the air inlet lip and configured to be fed with a heat transfer fluid heated by a heat source of the aircraft, an intake pipeline connected between an end of the at least one pipeline and the heat source; and a return pipeline connected between another end of the at least one pipeline and the heat source. 2. An aircraft comprising at least one engine according to claim 1 . 3. The aircraft engine according to claim 1 , wherein at least one or each of the at least one pipeline is equipped with fins oriented towards the outside of the pipeline and dipping into the inner chamber. 4. The aircraft engine according to claim 3 , wherein the inner wall has a part having an upstream face oriented towards the air inlet stream, and wherein the free ends of the fins are oriented towards the air inlet stream. 5. The aircraft engine according to claim 3 , wherein the fins are made in one piece with the pipeline. 6. The aircraft engine according to claim 3 , wherein the fins are elements added and fixed to the pipeline. 7. The aircraft engine according to claim 3 , wherein the fins are made of a material ensuring a transfer of heat.
Assignees
Inventors
Classifications
- F02C7/047Primary
Heating to prevent icing · CPC title
comprising de-icing means · CPC title
using fins or ribs · CPC title
Efficient propulsion technologies, e.g. for aircraft · CPC title
by the provision of a heat exchanger within the cooling circuit · CPC title
Patent family
Related publications grouped by family.
External sources
Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US11073081B2 cover?
- An aircraft engine air inlet lip takes an annular form about a longitudinal axis and delimits an air inlet stream, and includes: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards interior of the air inlet lip, an inner wall extending inside the wall between two zones of the inner face, so as to close an inner c…
- Who is the assignee on this patent?
- Airbus Operations Sas
- What technology area does this patent fall under?
- Primary CPC classification F02C7/047. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jul 27 2021 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 4 related publications on this page (citations in our corpus or others sharing the same primary CPC).