Turbine airfoil to shroud attachment method
Abstract
Bi-casting a platform (50) onto an end portion (42) of a turbine airfoil (31) after forming a coating of a fugitive material (56) on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (76A, 76B) onto the end portion in opposite directions parallel to a chord line (41) of the airfoil or parallel to a mid-platform length (80) of the platform to form respective layers tapering in thickness from the leading (32) and trailing (34) edges along the suction side (36) of the airfoil.
- Inventors:
- Issue Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1166020
- Patent Number(s):
- 8,914,976
- Application Number:
- 13/195,959
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2011 Aug 02
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 36 MATERIALS SCIENCE; 17 WIND ENERGY
Citation Formats
Campbell, Christian X, Kulkarni, Anand A, James, Allister W, Wessell, Brian J, and Gear, Paul J. Turbine airfoil to shroud attachment method. United States: N. p., 2014.
Web.
Campbell, Christian X, Kulkarni, Anand A, James, Allister W, Wessell, Brian J, & Gear, Paul J. Turbine airfoil to shroud attachment method. United States.
Campbell, Christian X, Kulkarni, Anand A, James, Allister W, Wessell, Brian J, and Gear, Paul J. Tue .
"Turbine airfoil to shroud attachment method". United States. https://www.osti.gov/servlets/purl/1166020.
@article{osti_1166020,
title = {Turbine airfoil to shroud attachment method},
author = {Campbell, Christian X and Kulkarni, Anand A and James, Allister W and Wessell, Brian J and Gear, Paul J},
abstractNote = {Bi-casting a platform (50) onto an end portion (42) of a turbine airfoil (31) after forming a coating of a fugitive material (56) on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (76A, 76B) onto the end portion in opposite directions parallel to a chord line (41) of the airfoil or parallel to a mid-platform length (80) of the platform to form respective layers tapering in thickness from the leading (32) and trailing (34) edges along the suction side (36) of the airfoil.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2014},
month = {12}
}
Works referenced in this record:
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- US Patent Document 5,797,725
Bi-cast blade ring for multi-alloy turbine rotor
patent-application, October 2006
- Rice, Derek A.; Baker, William C.; Perron, James S.
- US Patent Application 11/111530; 20060239825
Metal injection joining
patent-application, August 2009
- James, Allister
- US Patent Application 12/024326; 20090196761
Turbine Airfoil to Shroud Attachment
patent-application, October 2011
- Campbell, Christian X.; Morrison, Jay. A.; James, Allister W.
- US Patent Application 12/752460; 20110243724