Patents by Inventor Edward Pietraszkiewicz

Edward Pietraszkiewicz has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 10215051
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a non-gas path surface and a gas path surface, a cover plate positioned relative to the non-gas path surface and a cooling passage that extends between the cover plate and the non-gas path surface. At least one cooling entrance is formed through the cover plate and configured to bias the flow of a cooling fluid toward a prioritized location of the non-gas path surface.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: February 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Seth J. Thomen, Edward Pietraszkiewicz
  • Publication number: 20160194980
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a non-gas path surface and a gas path surface, a cover plate positioned relative to the non-gas path surface and a cooling passage that extends between the cover plate and the non-gas path surface. At least one cooling entrance is formed through the cover plate and configured to bias the flow of a cooling fluid toward a prioritized location of the non-gas path surface.
    Type: Application
    Filed: August 13, 2014
    Publication date: July 7, 2016
    Inventors: Seth J. THOMEN, Edward PIETRASZKIEWICZ
  • Patent number: 8534122
    Abstract: A system for airflow testing a turbine engine component having multiple cavities has a test fixture with a module for supporting a turbine engine component to be tested and a sliding element for sequentially allowing a pressurized fluid to flow through each of the multiple cavities in the turbine engine component. A method for performing the airflow testing is also described.
    Type: Grant
    Filed: December 27, 2011
    Date of Patent: September 17, 2013
    Assignee: United Technologies Corporation
    Inventors: Sergey Mironets, Thomas R. Davis, Richard Varsell, Edward Pietraszkiewicz
  • Publication number: 20130160535
    Abstract: A system for airflow testing a turbine engine component having multiple cavities has a test fixture with a module for supporting a turbine engine component to be tested and a sliding element for sequentially allowing a pressurized fluid to flow through each of the multiple cavities in the turbine engine component. A method for performing the airflow testing is also described.
    Type: Application
    Filed: December 27, 2011
    Publication date: June 27, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergey Mironets, Thomas R. Davis, Richard Varsell, Edward Pietraszkiewicz
  • Patent number: 7871245
    Abstract: Two pairs of ribs define three intermediate cooling chambers. Each rib in each pair extends parallel to the other rib in the pair. The ribs in a first pair are non-parallel to the ribs in a second pair. A first rib from the first pair is positioned spaced toward the leading edge. A first rib of the second pair is then serially positioned spaced toward the trailing edge. A second rib of the first pair is then positioned toward the trailing edge relative to the first rib in the second pair. A second rib in the second pair is then positioned toward the trailing edge relative to the second rib in the first pair.
    Type: Grant
    Filed: June 24, 2009
    Date of Patent: January 18, 2011
    Assignee: United Technologies Corporation
    Inventors: Edward Pietraszkiewicz, Irwin D. Singer, James P. Downs
  • Patent number: 7862325
    Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.
    Type: Grant
    Filed: June 24, 2009
    Date of Patent: January 4, 2011
    Assignee: United Technologies Corporation
    Inventors: Edward Pietraszkiewicz, Irwin D. Singer, James P. Downs
  • Patent number: 7665968
    Abstract: A rotor blade is provided that includes a root and a hollow airfoil. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a passage disposed adjacent the leading edge, and an axially extending passage disposed adjacent the tip. The first passage is connected to the second passage. The second passage includes an opening disposed at the trailing edge of the airfoil. A conduit is disposed within the root that is operable to permit airflow through the root and into the leading edge passage, wherein the conduit provides the primary path into the leading edge passage.
    Type: Grant
    Filed: May 27, 2004
    Date of Patent: February 23, 2010
    Assignee: United Technologies Corporation
    Inventors: Dominic J. Mongillo, Jr., Shawn J. Gregg, Jeffrey R. Levine, Edward Pietraszkiewicz
  • Publication number: 20090269210
    Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.
    Type: Application
    Filed: June 24, 2009
    Publication date: October 29, 2009
    Inventors: Edward Pietraszkiewicz, Irwin D. Singer, James P. Downs
  • Publication number: 20090258102
    Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.
    Type: Application
    Filed: June 24, 2009
    Publication date: October 15, 2009
    Inventors: Edward Pietraszkiewicz, Irwin D. Singer, James P. Downs
  • Patent number: 7569172
    Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.
    Type: Grant
    Filed: June 23, 2005
    Date of Patent: August 4, 2009
    Assignee: United Technologies Corporation
    Inventors: Edward Pietraszkiewicz, Irwin D. Singer, James P. Downs
  • Patent number: 7467924
    Abstract: 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.
    Type: Grant
    Filed: August 16, 2005
    Date of Patent: December 23, 2008
    Assignee: United Technologies Corporation
    Inventors: Robert A. Charbonneau, Kenneth P. Botticello, Shawn J. Gregg, Kirk David Hlavaty, Jeffrey R. Levine, Kenneth A. Lonczak, Craig R. McGarrah, Dominic J. Mongillo, Lisa P. O'Neill, Edward Pietraszkiewicz, Richard M. Salzillo, Heather Ann Terry
  • Patent number: 7452186
    Abstract: 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.
    Type: Grant
    Filed: August 16, 2005
    Date of Patent: November 18, 2008
    Assignee: United Technologies Corporation
    Inventors: Robert A. Charbonneau, Kenneth P. Botticello, Shawn J. Gregg, Kirk David Hlavaty, Jeffrey R. Levine, Kenneth A. Lonczak, Craig R. McGarrah, Dominic J. Mongillo, Lisa P. O'Neill, Edward Pietraszkiewicz, Richard M. Salzillo, Heather Ann Terry
  • Patent number: 7371048
    Abstract: A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge. The trailing edge region includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.
    Type: Grant
    Filed: May 27, 2005
    Date of Patent: May 13, 2008
    Assignee: United Technologies Corporation
    Inventors: James P. Downs, Norman F. Roeloffs, Edward Pietraszkiewicz, David Michael Kontrovitz, Takao Fukuda
  • Publication number: 20080044282
    Abstract: A turbine blade airfoil assembly includes a cooling air passage. The cooling air passage includes a plurality of impingement openings that are isolated from at least one adjacent impingement opening. The cooling air passage is formed and cast within a turbine blade assembly through the use of a single core. The single core forms the features required to fabricate the various separate and isolated impingement openings. The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.
    Type: Application
    Filed: May 14, 2007
    Publication date: February 21, 2008
    Inventors: Edward Pietraszkiewicz, Christina Botnick, Todd Coons
  • Publication number: 20070237638
    Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.
    Type: Application
    Filed: August 31, 2005
    Publication date: October 11, 2007
    Inventors: Om Sharma, Frank Cunha, Edward Pietraszkiewicz
  • Publication number: 20070189897
    Abstract: A turbine blade is cooled by cooling air that flows through a radial cooling channel. The turbine blade includes a root and an airfoil. The flow of cooling air into the cooling channel is limited by a pre-meter orifice to provide a reduced pressure within the cooling channel. The pressure drop results from the cross-sectional area of the pre-meter orifice being less than the cross-sectional area of the adjacent cooling channel. After flowing through the cooling channel, the cooling air exits the cooling channel through a film hole to form a film layer over the airfoil to cool and insulate the turbine blade.
    Type: Application
    Filed: February 15, 2006
    Publication date: August 16, 2007
    Applicant: United Technologies Corporation
    Inventors: Edward Pietraszkiewicz, Om Sharma, Kar Chin
  • Publication number: 20070140848
    Abstract: A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.
    Type: Application
    Filed: December 15, 2005
    Publication date: June 21, 2007
    Inventors: Robert Charbonneau, James Downs, Shawn Gregg, Wesley Harris, Natalia Khandros, Jeffrey Levine, Paul Orndoff, Steve Palmer, Edward Pietraszkiewicz, Norman Roeloffs, Richard Stockton, Wanda Widmer, Dagny Williams
  • Publication number: 20070119145
    Abstract: A compressor diffuser for a gas turbine engine is provided with a dirt separator. The dirt separator ensures the air having moved downstream of the compressor section, and moving toward the combustion section, is separated into a dirtier air flow path directly radially outwardly, and a cleaner airflow path directed radially inwardly. In this manner, the air reaching a combustion section, and the air being utilized for radially inner cooling air is relatively cleaner air. Further, the dirt separator provides a convenient surface for mounting a pressure sensor. In one embodiment, the dirt separator is mounted within the diffuser housing, and in a second embodiment, it is mounted immediately downstream.
    Type: Application
    Filed: November 29, 2005
    Publication date: May 31, 2007
    Inventors: Lisa O'Neill, Edward Pietraszkiewicz, Richard Silverman, Barry Beckwith
  • Patent number: 7195448
    Abstract: A rotor blade is provided that includes a root, a hollow airfoil, and a conduit disposed within the root. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a first radial passage, a second radial passage, a rib disposed between and separating the first radial passage and second radial passage, a plurality of crossover apertures disposed within the rib, and a plurality of trip strips disposed within the second radial passage. The trip strips are attached to an interior surface of one or both of the pressure side wall and the suction side wall. The trip strips are disposed within the first radial passage at an angle ? that is skewed relative to a cooling airflow direction within the first radial passage, and positioned such that each of the plurality of trip strips converges toward the rib.
    Type: Grant
    Filed: May 27, 2004
    Date of Patent: March 27, 2007
    Assignee: United Technologies Corporation
    Inventors: Jeffrey R. Levine, Edward Pietraszkiewicz, John Calderbank, Dominic J. Mongillo, Jr.
  • Publication number: 20070048128
    Abstract: A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.
    Type: Application
    Filed: August 31, 2005
    Publication date: March 1, 2007
    Inventors: Frank Cunha, Om Sharma, Edward Pietraszkiewicz