Core positioning
US-2015377038-A1 · Dec 31, 2015 · US
Additive manufactured fuel nozzle core for a gas turbine engine
US9975169B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9975169-B2 |
| Application number | US-201415026409-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 1, 2014 |
| Priority date | Oct 4, 2013 |
| Publication date | May 22, 2018 |
| Grant date | May 22, 2018 |
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- Title
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Abstract
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A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.
First claim
Opening claim text (preview).
What is claimed is: 1. A method of manufacturing a fuel component for a gas turbine engine combustor, the method comprising: additive manufacturing a sacrificial core; manufacturing a fuel component body at least partially around the sacrificial core; at least partially removing the sacrificial core to at least partially define an internal geometry of the fuel component body of the fuel component; additive manufacturing a first structure and a second structure, the first structure at least partially defining a first passage of the internal geometry and the second structure at least partially defining a second passage of the internal geometry; and additive manufacturing an interface structure between the first structure and the second structure that is outside the internal geometry of the fuel component body during the manufacturing of the fuel component body. 2. The method as recited in claim 1 , further comprising additive manufacturing the sacrificial core of a refractory metal alloy. 3. The method as recited in claim 1 , further comprising additive manufacturing the sacrificial core of a ceramic material. 4. The method as recited in claim 1 , further comprising additive manufacturing the sacrificial core of a hybrid material. 5. The method as recited in claim 1 , further comprising additive manufacturing an interface structure that at least partially surrounds the sacrificial core. 6. The method as recited in claim 1 , further comprising additive manufacturing an interface structure of the sacrificial core that is outside the internal geometry of the fuel component body during the manufacturing of the fuel component body. 7. The method as recited in claim 1 , further comprising additive manufacturing a connection of the sacrificial core that is inside the internal geometry of the fuel component body during the manufacturing of the fuel component body. 8. The method as recited in claim 1 , further comprising additive manufacturing a connection between the first structure and the second structure that is within the internal geometry of the fuel component body during the manufacturing of the fuel component body.
Assignees
Inventors
Classifications
having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title
Accessories: Details · CPC title
Nozzles; Cleaning devices therefor · CPC title
for hollow articles · CPC title
comprising an air supply system for the atomisation of fuel · CPC title
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- What does patent US9975169B2 cover?
- A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel c…
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification B22C9/10. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue May 22 2018 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).