Turbine overspeed protection
US-2024368999-A1 · Nov 7, 2024 · US
Gas turbine engine blade containment system
US10167727B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10167727-B2 |
| Application number | US-201514794576-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 8, 2015 |
| Priority date | Aug 13, 2014 |
| Publication date | Jan 1, 2019 |
| Grant date | Jan 1, 2019 |
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- Title
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- Abstract
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- Assignees and inventors
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- First independent claim
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- CPC / IPC classifications
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- Citations and related patents
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Abstract
Official abstract text for this publication.
A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.
First claim
Opening claim text (preview).
What is claimed is: 1. A method for manufacturing a gas turbine engine blade containment system, comprising: providing a cylindrical casing being made of a first material; and depositing a second material onto the casing that coaxially surrounds the casing to form a ring, at least a portion of the ring metallurgically bonded to the casing and a gap positioned between the casing and the ring, wherein a sheet metal core is positioned between the casing and the ring and a rib is connected to at least some portion of the sheet metal core and extending through the ring. 2. The method of claim 1 , wherein the depositing is step is one of; electron beam melting, electron beam wire deposition, direct metal laser sintering, selective laser sintering, laser beam powder deposition, selective laser melting, cold metal transfer, gas dynamic cold spraying, high velocity oxy-fuel coating spraying (HVOF) and combinations thereof. 3. The method of claim 1 , wherein the first material is selected one of; titanium, titanium alloy, nickel, nickel alloy, steel, aluminum, aluminum alloy and combinations thereof. 4. The method of claim 1 , wherein the second material is one of; titanium, titanium alloy, nickel, nickel alloy, steel, aluminum, aluminum alloy and combinations thereof.
Assignees
Inventors
Classifications
- F01D21/045Primary
special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title
by thermal means (control of energy beam parameters for post heating B22F10/364) · CPC title
Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title
- F01D5/3061Primary
by welding, brazing · CPC title
Build-up welding · CPC title
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Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US10167727B2 cover?
- A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F01D21/045. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jan 01 2019 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).