Acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor
US-2024200493-A1 · Jun 20, 2024 · US
Aircraft power system
US9915201B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9915201-B2 |
| Application number | US-201314140959-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 26, 2013 |
| Priority date | Mar 4, 2013 |
| Publication date | Mar 13, 2018 |
| Grant date | Mar 13, 2018 |
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.
A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
First claim
Opening claim text (preview).
What is claimed is: 1. A method comprising: operating a first aircraft engine and a second aircraft engine to produce propulsive thrust to power a multi-engine aircraft to a flight condition, the second aircraft engine being a gas turbine engine having a compressor, combustor, and turbine; actuating a valve to open a flow path from a source of compressed working fluid on board the multi-engine aircraft to permit passage of a compressed working fluid from the source of compressed…
Assignees
Inventors
Classifications
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Patent family
Related publications grouped by family.
External sources
Next steps
Free tools are coming soon. Tell us what you want to track and we'll notify you.
Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US9915201B2 cover?
- A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configuratio…
- Who is the assignee on this patent?
- Rolls Royce Corp
- What technology area does this patent fall under?
- Primary CPC classification F02C7/045. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Mar 13 2018 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).