Composite retention feature
US-9506356-B2 · Nov 29, 2016 · US
Fan blade attachment root with improved strain response
US11002285B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11002285-B2 |
| Application number | US-202017012940-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 4, 2020 |
| Priority date | May 27, 2015 |
| Publication date | May 11, 2021 |
| Grant date | May 11, 2021 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.
First claim
Opening claim text (preview).
What is claimed is: 1. A fan blade, comprising: a leading edge; an attachment root extending aft of the leading edge; and a first spherical recess formed in a bottom surface of the attachment root and offset from the leading edge, wherein the height of the first spherical recess equals the width of the first spherical recess; and a second spherical recess formed in the bottom surface of the attachment root and offset in an aft direction from the first spherical recess. 2. An attachment root, comprising: a leading edge; a dovetail extending aft of the leading edge; and a first spherical recess formed in a bottom surface of the dovetail and offset from the leading edge, wherein the height of the first spherical recess equals the width of the first spherical recess; and a second spherical recess formed in the bottom surface of the attachment root and offset in an aft direction from the first spherical recess. 3. A gas turbine engine, comprising: a compressor section configured to rotate about an axis; a combustor aft of the compressor section; a turbine section aft of the combustor and configured to rotate about the axis; and a fan forward of the turbine section comprising a blade, wherein: a first spherical recess is formed in a bottom surface of an attachment root of the blade and offset from a leading edge of the blade, wherein the height of the first spherical recess equals the width of the first spherical recess; and a second spherical recess formed in the bottom surface of the attachment root and offset in an aft direction from the first spherical recess.
Assignees
Inventors
Classifications
- F04D29/322Primary
Blade mountings · CPC title
spherical · CPC title
- F04D29/34Primary
Blade mountings {(for axial flow compressors F04D29/322)} · CPC title
by removing material · CPC title
hollowed · CPC title
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Frequently asked questions
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- What does patent US11002285B2 cover?
- A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbin…
- Who is the assignee on this patent?
- Raytheon Tech Corp
- What technology area does this patent fall under?
- Primary CPC classification F04D29/322. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue May 11 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 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).