Patents by Inventor Edward F. Pietraszkiewicz
Edward F. 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).
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Patent number: 7866947Abstract: A turbine component includes a coolant passage and a plurality of trip members that extend within the coolant passage. Each of the plurality of trip members includes an orientation relative to an expected flow direction through the coolant passage. At least three of the trip members have orientations that are different from each other. For example, the orientations of the trip members progressively transition along the length of the coolant passage.Type: GrantFiled: January 3, 2007Date of Patent: January 11, 2011Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, James P. Downs
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Patent number: 7857588Abstract: A reinforced airfoil includes an airfoil body including opposed walls that define a hollow interior space and a reinforcement member provided on at least one of the walls within the interior space, the reinforcement member increasing the thickness of the at least one wall so as to resist deformation of the at least one wall but not extending from one wall to the other.Type: GrantFiled: July 6, 2007Date of Patent: December 28, 2010Assignee: United Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Edward F. Pietraszkiewicz, Steven Bruce Gautschi
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Patent number: 7845907Abstract: A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion.Type: GrantFiled: July 23, 2007Date of Patent: December 7, 2010Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, Atul Kohli
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Patent number: 7845906Abstract: A cooling system for an airfoil portion of a turbine engine component is provided. The cooling system includes a first cavity dedicated to cooling a trailing edge portion of an airfoil portion and a second cavity dedicated to cooling an aft portion of a pressure side wall.Type: GrantFiled: January 24, 2007Date of Patent: December 7, 2010Assignee: United Technologies CorporationInventors: Brandon W. Spangler, Edward F. Pietraszkiewicz
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Patent number: 7827799Abstract: 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: GrantFiled: October 29, 2008Date of Patent: November 9, 2010Assignee: United Technologies CorporationInventors: Lisa O'Neill, Edward F. Pietraszkiewicz, Richard Silverman, Barry Beckwith
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Patent number: 7819169Abstract: 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 provide 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: GrantFiled: May 14, 2007Date of Patent: October 26, 2010Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, Christina Botnick, Todd Coons
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Patent number: 7731481Abstract: A turbine engine component has an airfoil portion with a pressure side wall and a suction side wall and a cooling system. The cooling system has at least one cooling circuit disposed longitudinally along the airfoil portion. Each cooling circuit has a plurality of staggered internal pedestals for increasing heat pick-up.Type: GrantFiled: December 18, 2006Date of Patent: June 8, 2010Assignee: United Technologies CorporationInventors: Francisco J. Cunha, Edward F. Pietraszkiewicz
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Publication number: 20090285683Abstract: A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil. The cooling channels include a leading edge channel, a trailing edge channel, a serpentine cooling circuit, and a dedicated up-pass channel. The serpentine cooling circuit includes a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil, a down-pass channel forward of and in flow communication with the first up-pass channel, and a second up-pass channel forward of and in flow communication with the down-pass channel.Type: ApplicationFiled: May 14, 2008Publication date: November 19, 2009Applicant: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, Sandra S. Pinero
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Publication number: 20090285684Abstract: A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.Type: ApplicationFiled: May 14, 2008Publication date: November 19, 2009Applicant: United Technologies CorporationInventors: Sandra S. Pinero, Edward F. Pietraszkiewicz, Bryan P. Dube, Stephen J. Yee, Ryan Shepard Levy, Mohamed Hassan, Domenico Valerio, Scott D. Hartmann
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Patent number: 7534085Abstract: A gas turbine engine is provided with a turbine rotor disk having a plurality of disk slots which each receive a turbine blade. Cooling air is delivered into the disk slots, and flows into cooling air passages at a radially inner surface of the turbine blades. As known, the cooling air flows through the turbine blades to cool internal and external surfaces of the turbine blade. The disk slots are formed to have a greater cross-sectional area adjacent at the inlet end than at downstream locations. In this manner, the velocity of the air at the inlet end is reduced compared to the prior art, and pressure losses are minimized compared to the prior art.Type: GrantFiled: June 21, 2006Date of Patent: May 19, 2009Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, James P. Downs
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Publication number: 20090116956Abstract: 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: ApplicationFiled: January 7, 2009Publication date: May 7, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Frank Cunha, Om Parkash Sharma, Edward F. Pietraszkiewicz
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Patent number: 7513040Abstract: 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: GrantFiled: August 31, 2005Date of Patent: April 7, 2009Assignee: United Technologies CorporationInventors: Frank Cunha, Om Parkash Sharma, Edward F. Pietraszkiewicz
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Patent number: 7507075Abstract: 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.Type: GrantFiled: August 15, 2005Date of Patent: March 24, 2009Assignee: United Technologies CorporationInventors: Moon-Kyoo Brian Kang, Kenneth A. Lonczak, Edward F. Pietraszkiewicz
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Publication number: 20090067994Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.Type: ApplicationFiled: March 1, 2007Publication date: March 12, 2009Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
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Publication number: 20090060741Abstract: A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.Type: ApplicationFiled: August 27, 2007Publication date: March 5, 2009Inventors: Scott W. Gayman, Justin D. Piggush, Edward F. Pietraszkiewicz, William A. Agli, III
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Publication number: 20090044512Abstract: 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: ApplicationFiled: October 29, 2008Publication date: February 19, 2009Inventors: Lisa O'Neill, Edward F. Pietraszkiewicz, Richard Silverman, Barry Beckwith
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Publication number: 20090028702Abstract: A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion.Type: ApplicationFiled: July 23, 2007Publication date: January 29, 2009Inventors: Edward F. Pietraszkiewicz, Atul Kohli
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Patent number: 7478994Abstract: An airfoil, and in a disclosed embodiment a rotor blade, has film cooling holes formed at a leading edge. A supplemental film cooling channel is positioned near the leading edge, but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel directs film cooling air onto a suction wall. The supplemental film cooling channel air is generally directed to a location on the suction wall that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.Type: GrantFiled: November 23, 2004Date of Patent: January 20, 2009Assignee: United Technologies CorporationInventors: Frank J. Cunha, Edward F. Pietraszkiewicz, David M. Kontrovitz, Jeffrey R. Levine, Young Chon, Dominic Mongillo, Bret Teller
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Publication number: 20090010765Abstract: A reinforced airfoil includes an airfoil body including opposed walls that define a hollow interior space and a reinforcement member provided on at least one of the walls within the interior space, the reinforcement member increasing the thickness of the at least one wall so as to resist deformation of the at least one wall but not extending from one wall to the other.Type: ApplicationFiled: July 6, 2007Publication date: January 8, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Tracy A. Propheter-Hinckley, Edward F. Pietraszkiewicz, Steven Bruce Gautschi
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Patent number: 7422771Abstract: A method for applying a hybrid thermal barrier coating, comprising masking at least a portion of a first surface of a component with a first maskant; applying a first coating material to at least a portion of a second surface of said component; removing said first maskant; optionally masking at least a portion of said second surface of said component with a second maskant; applying a second coating material to at least a portion of said first surface of said component; and removing said second maskant.Type: GrantFiled: September 1, 2005Date of Patent: September 9, 2008Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, Kevin W. Schlichting, David A. Litton, Heather A. Terry