Interlocking material transition zone with integrated film cooling
US-9914172-B2 · Mar 13, 2018 · US
Additively manufactured bladed disk
US10180072B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10180072-B2 |
| Application number | US-201514887531-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 20, 2015 |
| Priority date | Oct 20, 2015 |
| Publication date | Jan 15, 2019 |
| Grant date | Jan 15, 2019 |
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- Title
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Abstract
Official abstract text for this publication.
A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone. The rotor disk includes a plurality of fused layers of a first material formed via additive manufacturing and defines an outer rim. The plurality of rotor blades includes a plurality of fused layers of a second material formed via additive manufacturing. The interlocking transition zone includes a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades.
First claim
Opening claim text (preview).
What is claimed: 1. A bladed disk for a gas turbine engine, comprising: a rotor disk comprising a plurality of fused layers of a first material formed via additive manufacturing, wherein the rotor disk defines an outer rim; a plurality of rotor blades comprising a plurality of fused layers of a second material formed via additive manufacturing; and an interlocking transition zone comprising a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades, wherein each of the plurality of projections allows for variations in the relative motion between the rotor disk and the plurality of rotor blades. 2. The bladed disk of claim 1 , wherein at least a portion of adjacent projections between the rotor disk and the plurality of rotor blades prevents or limits the relative motion between the rotor disk and the plurality of rotor blades. 3. The bladed disk of claim 1 , wherein the interlocking transition zone defines a fluid channel, the fluid channel being configured to provide fluid communication between the rotor disk and the plurality of rotor blades. 4. The bladed disk of claim 1 , wherein the first material is a first metal alloy and the second material is a second metal alloy. 5. The bladed disk of claim 1 , wherein a brazed joint is located between the rotor disk and the plurality of rotor blades to act as adhesive.
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Frequently asked questions
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- What does patent US10180072B2 cover?
- A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone. The rotor disk includes a plurality of fused layers of a first material formed via additive manufacturing and defines an outer rim. The plurality of rotor blades includes a plurality of fused layers of a second material formed via additive …
- Who is the assignee on this patent?
- Gen Electric
- What technology area does this patent fall under?
- Primary CPC classification F01D5/30. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jan 15 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 5 related publications on this page (citations in our corpus or others sharing the same primary CPC).