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Title: Multi-component assembly casting

Abstract

Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat resistant material (18) each comprises an interlocking feature (24); preheating the mold; introducing molten structural material (46) into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component (12) with respect to the preformed shroud heat resistant material (18) and is effective to provide structural support for the shroud heat resistant material (18). Surfaces between the airfoil component (12) and the structural material (46), between the airfoil component (12) and the shroud heat resistant material (18), and between the shroud heat resistant material (18) and the structural material (46) are free of metallurgical bonds.

Inventors:
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1223118
Patent Number(s):
9,156,086
Application Number:
12/795,002
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2010 Jun 07
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

James, Allister W. Multi-component assembly casting. United States: N. p., 2015. Web.
James, Allister W. Multi-component assembly casting. United States.
James, Allister W. 2015. "Multi-component assembly casting". United States. https://www.osti.gov/servlets/purl/1223118.
@article{osti_1223118,
title = {Multi-component assembly casting},
author = {James, Allister W.},
abstractNote = {Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat resistant material (18) each comprises an interlocking feature (24); preheating the mold; introducing molten structural material (46) into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component (12) with respect to the preformed shroud heat resistant material (18) and is effective to provide structural support for the shroud heat resistant material (18). Surfaces between the airfoil component (12) and the structural material (46), between the airfoil component (12) and the shroud heat resistant material (18), and between the shroud heat resistant material (18) and the structural material (46) are free of metallurgical bonds.},
doi = {},
url = {https://www.osti.gov/biblio/1223118}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Oct 13 00:00:00 EDT 2015},
month = {Tue Oct 13 00:00:00 EDT 2015}
}

Works referenced in this record:

Aerofoil member for a gas turbine engine
patent, March 1982


Turbine nozzle
patent, December 1992


Turbine stator vane assembly
patent, September 1993


Bicast vane and shroud rings
patent, March 1994


Turbine engine vane segment
patent, September 1998


Multi-component hybrid turbine blade
patent, August 2003


Directly cooled thermal barrier coating system
patent, September 2003


Split flow turbine nozzle
patent, August 2005


Superalloy for single crystal turbine vanes
patent, March 2006


Lamellate CMC structure with interlock to metallic support structure
patent, July 2007


Countercooled turbine nozzle
patent, May 2008


Multi-piece turbine vane assembly
patent, November 2008


CMC vane assembly apparatus and method
patent, October 2012


Blade outer air seal
patent, November 2012