Turbine airfoil to shroud attachment method

Title: 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:: Campbell, Christian X; Kulkarni, Anand A; James, Allister W; Wessell, Brian J; Gear, Paul J

Issue Date:: 2014-12-23

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) NETL

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.

Copy to clipboard


                    Campbell, Christian X, Kulkarni, Anand A, James, Allister W, Wessell, Brian J, & Gear, Paul J. Turbine airfoil to shroud attachment method.  United States.

Copy to clipboard


                    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.

Copy to clipboard


                    
@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}

}

Copy to clipboard

Patent:

View Patent

Save / Share:

Export Metadata

Save to My Library

Works referenced in this record:

Gas turbine engine vane and method of manufacture
patent, August 1998

Rhodes, Jeffrey
US Patent Document 5,797,725
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F5797725

Metal injection joining
patent-application, August 2009

James, Allister
US Patent Application 12/024326; 20090196761
URL: http://appft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PG01&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.html&r=1&f=G&l=50&s1=%2220090196761%22.PGNR.&OS=DN/20090196761&RS=DN/20090196761

Similar records in DOE Patents and OSTI.GOV collections:

Closed circuit steam cooled turbine shroud and method for steam cooling turbine shroud

Patent Burdgick, Steven Sebastian (Schenectady, NY); Sexton, Brendan Francis (Simpsonville, SC); Kellock, Iain Robertson (Simpsonville, SC)

A turbine shroud cooling cavity is partitioned to define a plurality of cooling chambers for sequentially receiving cooling steam and impingement cooling of the radially inner wall of the shoud. An impingement baffle is provided in each cooling chamber for receiving the cooling media from a cooling media inlet in the case of the first chamber or from the immediately upstream chamber in the case of the second through fourth chambers and includes a plurality of impingement holes for effecting the impingement cooling of the shroud inner wall.
Full Text Available
Turbine airfoil to shround attachment

Patent Campbell, Christian X; Morrison, Jay A; James, Allister W; ...

A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintainingmore »« less
Full Text Available
Method for forming a liquid cooled airfoil for a gas turbine

Patent Grondahl, Clayton M. (Clifton Park, NY); Willmott, Leo C. (Ballston Spa, NY); Muth, Myron C. (Amsterdam, NY)

A method for forming a liquid cooled airfoil for a gas turbine is disclosed. A plurality of holes are formed at spaced locations in an oversized airfoil blank. A pre-formed composite liquid coolant tube is bonded into each of the holes. The composite tube includes an inner member formed of an anti-corrosive material and an outer member formed of a material exhibiting a high degree of thermal conductivity. After the coolant tubes have been bonded to the airfoil blank, the airfoil blank is machined to a desired shape, such that a portion of the outer member of each of themore »« less
Full Text Available
Turbine inner shroud and turbine assembly containing such inner shroud

Patent Bagepalli, Bharat Sampathkumaran (Niskayuna, NY); Corman, Gregory Scot (Ballston Lake, NY); Dean, Anthony John (Scotia, NY); ...

A turbine inner shroud and a turbine assembly. The turbine assembly includes a turbine stator having a longitudinal axis and having an outer shroud block with opposing and longitudinally outward facing first and second sides having open slots. A ceramic inner shroud has longitudinally inward facing hook portions which can longitudinally and radially surround a portion of the sides of the outer shroud block. In one attachment, the hook portions are engageable with, and are positioned within, the open slots.
Full Text Available
Airfoil nozzle and shroud assembly

Patent Shaffer, James E. (Maitland, FL); Norton, Paul F. (San Diego, CA)

An airfoil and nozzle assembly including an outer shroud having a plurality of vane members attached to an inner surface and having a cantilevered end. The assembly further includes a inner shroud being formed by a plurality of segments. Each of the segments having a first end and a second end and having a recess positioned in each of the ends. The cantilevered end of the vane member being positioned in the recess. The airfoil and nozzle assembly being made from a material having a lower rate of thermal expansion than that of the components to which the airfoil andmore » nozzle assembly is attached.« less
Full Text Available

Similar Records

Title: Turbine airfoil to shroud attachment method

Abstract

Citation Formats

Gas turbine engine vane and method of manufacture patent, August 1998

Metal injection joining patent-application, August 2009

Gas turbine engine vane and method of manufacture
patent, August 1998

Metal injection joining
patent-application, August 2009