skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Casting core for a cooling arrangement for a gas turbine component

Patent ·
OSTI ID:1167465
;

A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) defining an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each including interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).

Research Organization:
Siemens Aktiengesellschaft, Munchen, DE (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
SC0001359
Assignee:
Siemens Aktiengesellschaft (Munchen, DE)
Patent Number(s):
8,936,067
Application Number:
13/658,045
OSTI ID:
1167465
Country of Publication:
United States
Language:
English

References (32)

Radial wafer airfoil construction patent May 1980
Cooled turbine blade patent August 1987
Turbine blade trailing edge cooling construction patent September 1993
Investment casting using core with integral wall thickness control means patent March 1994
Film cooling of turbine airfoil wall using mesh cooling hole arrangement patent December 1994
Internally cooled gas turbine vane patent February 1997
Internal cooling of turbine airfoil wall using mesh cooling hole arrangement patent November 1997
Shear jet cooling passages for internally cooled machine elements patent January 1998
Apparatus for cooling a gas turbine airfoil and method of making same patent May 1998
Reduction of turbomachinery noise patent December 1999
Axial serpentine cooled airfoil patent August 2000
Method and apparatus for cooling a wall within a gas turbine engine patent July 2001
Method and apparatus for cooling a wall within a gas turbine engine patent June 2002
Triple circuit turbine blade patent January 2006
Hot gas path component with mesh and impingement cooling patent February 2007
Drillable super blades patent June 2007
Microcircuit cooling for blades patent December 2007
Turbine blade cooling system having multiple serpentine trailing edge cooling channels patent October 2008
Airfoil with supplemental cooling channel adjacent leading edge patent January 2009
Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels patent June 2009
Component comprising a multiplicity of cooling passages patent August 2009
High effectiveness cooled turbine blade patent December 2009
Turbine airfoil with serpentine trailing edge cooling circuit patent March 2010
Turbine bladed with tip cooling patent May 2010
Thin turbine rotor blade with sinusoidal flow cooling channels patent July 2010
Turbine blade with multiple metering trailing edge cooling holes patent August 2010
Turbine airfoil with spiral trailing edge cooling passages patent August 2010
Film-cooling augmentation device and turbine airfoil incorporating the same patent November 2011
Turbine blade patent January 2012
Rotor blades for turbine engines patent April 2012
Turbine airfoil ceramic core with strain relief slot patent September 2012
Crossflow Turbine Airfoil patent-application December 2009

Similar Records

Related Subjects

42 ENGINEERING