Direct drive electrically-geared turbofan
US-2024218837-A1 · Jul 4, 2024 · US
Geared turbofan architecture for regional jet aircraft
US2016195022A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016195022-A1 |
| Application number | US-201615015198-A |
| Country | US |
| Kind code | A1 |
| Filing date | Feb 4, 2016 |
| Priority date | Sep 30, 2013 |
| Publication date | Jul 7, 2016 |
| Grant date | — |
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- Title
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Abstract
Official abstract text for this publication.
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section. The fan has a fan diameter, Dfan, and the high pressure compressor section has a compressor diameter, Dcomp. The fan diameter Dfan and the compressor diameter Dcomp have an interdependence represented by a scalable ratio Dfan/Dcomp that is greater than about 4.5.
First claim
Opening claim text (preview).
What is claimed is: 1 . A gas turbine engine comprising: a fan situated at an inlet of a bypass passage; a core engine configured to drive the fan, the core engine including: a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section; and wherein the gas turbine engine has a bypass ratio greater than about 10, the fan has a fan diameter, Dfan, the high pressure compressor s…
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Classifications
- F02C7/36Primary
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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Frequently asked questions
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- What does patent US2016195022A1 cover?
- A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section. The fan has a fan …
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F02C7/36. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Jul 07 2016 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).