Kenneth A Lonczak

7467924, Dec 23, 2008

Aug 16, 2005

11/205274

Robert A. Charbonneau - Meriden CT, US
Kenneth P. Botticello - West Suffield CT, US
Shawn J. Gregg - Wethersfield CT, US
Kirk David Hlavaty - East Hartford CT, US
Jeffrey R. Levine - Wallingford CT, US
Kenneth A. Lonczak - Meriden CT, US
Craig R. McGarrah - Southington CT, US
Dominic J. Mongillo - West Hartford CT, US
Lisa P. O'Neill - Manchester CT, US
Edward Pietraszkiewicz - Southington CT, US
Richard M. Salzillo - Plantsville CT, US
Heather Ann Terry - Middletown CT, US

United Technologies Corporation - Hartford CT

F01D 5/10

416193A, 416248

The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.

7507075, Mar 24, 2009

Aug 15, 2005

11/204257

Kenneth A. Lonczak - Meriden CT, US
Edward F. Pietraszkiewicz - Southington CT, US

United Technologies Corporation - Hartford CT

F01D 5/30

416248

An identification feature is used to unmistakably identify internal features present in different generations of turbine blade designs. The identification feature is located on a root portion of the turbine blade and protrudes to provide a visually identifiable feature that is also readable by a coordinate measuring machine, but does not interfere with installation or operation of the turbine blade. The weight of the identification feature is in a specific proportion to the weight of the turbine blade in order to prevent interfere with operation of the turbine blade during high-speed rotation in a gas turbine engine.

20070041835, Feb 22, 2007

Aug 16, 2005

11/205299

Robert Charbonneau - Meriden CT, US
Kenneth Botticello - West Suffield CT, US
Shawn Gregg - Wethersfield CT, US
Kirk Hlavaty - East Hartford CT, US
Jeffrey Levine - Wallingford CT, US
Kenneth Lonczak - Meriden CT, US
Craig McGarrah - Southington CT, US
Dominic Mongillo - West Hartford CT, US
Lisa O'Neill - Manchester CT, US
Edward Pietraszkiewicz - Southington CT, US
Richard Salzillo - Plantsville CT, US
Heather Terry - Middletown CT, US

F01D 5/18

41609700R

The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.