Low noise turbine for geared gas turbine engine
US-10605172-B2 · Mar 31, 2020 · US
Low noise turbine for geared gas turbine engine
US11560849B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11560849-B2 |
| Application number | US-202117503814-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 18, 2021 |
| Priority date | Mar 14, 2013 |
| Publication date | Jan 24, 2023 |
| Grant date | Jan 24, 2023 |
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 according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first turbine. The propulsor is driven by the first turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.
First claim
Opening claim text (preview).
What is claimed is: 1. A gas turbine engine comprising: a propulsor section including a propulsor having a plurality of propulsor blades; a turbine section including a first turbine and a second turbine; a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor; a geared architecture driven by the first turbine; a first shaft that connects an input of the geared architecture to the first turbine; a sec…
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 US11560849B2 cover?
- A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first tur…
- Who is the assignee on this patent?
- Raytheon Tech Corp, Mtu Aero Engines Gmbh
- What technology area does this patent fall under?
- Primary CPC classification F02C7/24. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jan 24 2023 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).