Back to results
US 9,175,568 B2Granted
Methods for manufacturing turbine components
AssigneeHoneywell International Inc.
InventorsDaniel Ryan, Mark C. Morris, Donald G. Godfrey, Steve Starr
Life of this patent
Estimating the term…
Abstract
A method is provided for manufacturing a turbine component. The method includes forming a first intermediate turbine article with an additive manufacturing process; encapsulating the first intermediate turbine article with an encapsulation layer to form a second intermediate turbine article; and consolidating the second intermediate turbine article to produce the turbine component.
Claims14
A method for manufacturing a turbine component, comprising the steps of:
- forming a first intermediate turbine article with an additive manufacturing process, the first intermediate turbine article including internal surfaces forming internal cooling passages;
- encapsulating the first intermediate turbine article with an encapsulation layer to form a second intermediate turbine article, the encapsulating step including depositing a portion of the encapsulation layer on the internal surfaces within the internal cooling passages;
- consolidating the second intermediate turbine article to produce the turbine component, wherein the consolidating step includes consolidating the second intermediate turbine article to form a third intermediate turbine article, the consolidating step further including consolidating the portion of the encapsulation layer on the internal surfaces within the internal cooling passages;
- and
- finishing the third intermediate turbine article to produce the turbine component, wherein the finishing step includes removing the encapsulation layer.
2 more elements
A method for manufacturing a turbine component, comprising the steps of:
- forming a first intermediate turbine article with an additive manufacturing process with a nickel-based superalloy, the first intermediate turbine article including internal surfaces forming internal cooling passages;
- encapsulating the first intermediate turbine article with an encapsulation layer to form a second intermediate turbine article, the encapsulating step including converting surface porosity and cracks of the first intermediate turbine article to internal porosity and cracks in the second intermediate turbine article, the encapsulating step including depositing a portion of the encapsulation layer on the internal surfaces within the internal cooling passages;
- hot isostatic pressing the second intermediate turbine article to produce a third intermediate turbine article;
- and
- removing the encapsulation layer from the third intermediate turbine article to produce the turbine component.
2 more elements
Dependencies are inferred from the claim text.