Patents by Inventor Honza Stastny
Honza Stastny 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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Publication number: 20160109130Abstract: Turbine engine components having heat-extracting features and methods for manufacturing such components using additive manufacturing are disclosed. An exemplary method comprises providing a base portion of the engine component manufactured by a first manufacturing process and adding one or more heat-extracting features to the engine component using a second manufacturing process different from the first manufacturing process where the second manufacturing process comprises an additive manufacturing process.Type: ApplicationFiled: March 27, 2015Publication date: April 21, 2016Inventors: Honza STASTNY, Francois RICHARD, Marjolaine COTE
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Publication number: 20160054000Abstract: A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.Type: ApplicationFiled: September 14, 2015Publication date: February 25, 2016Inventors: Honza STASTNY, Jeffrey VERHIEL, Parthasarathy SAMPATH
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Publication number: 20160040543Abstract: A sliding joint in a gas turbine engine between a large exit duct of a combustor and a turbine vane assembly having a leading edge lug. The sliding joint has an elongated flexible arm extending between a first end joined to the outer surface of the large entry duct, and an opposed free second end disposed radially inward of the outer surface of the large entry duct. A spacer is joined to the second end of the arm and projects radially away therefrom toward the outer surface of the large entry duct. The spacer is spaced apart from the outer surface and defines a gap therebetween. The spacer, the arm, and the sliding joint axially displace with respect to the lug upon thermal expansion of the large entry duct.Type: ApplicationFiled: August 7, 2014Publication date: February 11, 2016Inventors: Honza Stastny, Robert Sze
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Patent number: 9134028Abstract: A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.Type: GrantFiled: January 18, 2012Date of Patent: September 15, 2015Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Honza Stastny, Jeffrey Richard Verhiel, Parthasarathy Sampath
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Publication number: 20150211420Abstract: A gas turbine engine comprising a combustor having a combustor liner assembly and a mounting bracket provided on the combustor liner assembly, a floating collar being slidingly received on the mounting bracket for relative sliding movement in a plane normal to an axis of an igniter opening in the liner assembly. The floating collar includes an annular surface defining a collar opening, and an igniter having an axis concentric with the axis of the collar opening is sealingly engages the annular surface. A plurality of purge openings defined in at least one of the igniter and the floating collar form cooling airflow passages communicating from the plenum to the cavity.Type: ApplicationFiled: January 28, 2014Publication date: July 30, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Robert Sze, Kian McCaldon, Honza Stastny
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Publication number: 20150040568Abstract: A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss.Type: ApplicationFiled: August 12, 2013Publication date: February 12, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Honza STASTNY, Bhawan B. PATEL, Ram KULATHU, Sudhakara Reddy ANNEM, Balakrishna GAJA, Bharath Mandya NAGARAJ
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Publication number: 20140250896Abstract: The build-up of carbon deposition on the front face of a combustor heat shield is discouraged by jetting air out from the front face of the heat shield with sufficient momentum to push approaching fuel droplets or rich fuel-air mixture way from the heat shield.Type: ApplicationFiled: March 8, 2013Publication date: September 11, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Tin Cheung John HU, Robert SZE, Honza STASTNY
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Patent number: 8745988Abstract: A heat shield unit for a gas turbine engine combustor comprises a panel body secured to a combustor liner. A first surface of the body is oriented toward a combustion zone of a combustor. A second surface is oriented toward the liner. The body is separated into upstream and downstream portions. Pin fins project from the second surface of the body. The pin fins are arranged in arrays of at least two different densities of volume of pin fins per unit volume. One density, lower than the second density, is in the upstream portion and another in the downstream portion of the body. Connectors connect the body to the liner with a line between the upstream and downstream portions of the body aligned with fluid-coolant injection apertures in the liner. A gas turbine engine combustor and a method for cooling a heat shield unit in a combustor liner of a gas turbine engine are also provided.Type: GrantFiled: September 6, 2011Date of Patent: June 10, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Jeffrey Verhiel, Honza Stastny, Robert Sze
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Publication number: 20130251513Abstract: A multi-pieces gas turbine engine combustor heat shield is fabricated from sheet metal. The fabrication involves: sheet metal forming a base sheet having opposed hot and cold facing sides, providing cold side details separately from the base sheet, and mounting the cold side details to the cold facing side of the base sheet. The cold side details may be brazed to the base sheet.Type: ApplicationFiled: March 23, 2012Publication date: September 26, 2013Inventors: Honza Stastny, Parthasarathy Sampath
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Publication number: 20130180257Abstract: A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.Type: ApplicationFiled: January 18, 2012Publication date: July 18, 2013Inventors: Honza Stastny, Jeffrey Richard Verhiel, Parthasarathy Sampath
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Publication number: 20130055722Abstract: A heat shield unit for a gas turbine engine combustor comprises a panel body secured to a combustor liner. A first surface of the body is oriented toward a combustion zone of a combustor. A second surface is oriented toward the liner. The body is separated into upstream and downstream portions. Pin fins project from the second surface of the body. The pin fins are arranged in arrays of at least two different densities of volume of pin fins per unit volume. One density, lower than the second density, is in the upstream portion and another in the downstream portion of the body. Connectors connect the body to the liner with a line between the upstream and downstream portions of the body aligned with fluid-coolant injection apertures in the liner. A gas turbine engine combustor and a method for cooling a heat shield unit in a combustor liner of a gas turbine engine are also provided.Type: ApplicationFiled: September 6, 2011Publication date: March 7, 2013Inventors: Jeffrey VERHIEL, Honza Stastny, Robert Sze
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Patent number: 8375548Abstract: A method of repairing a modular gas turbine fuel nozzle tip, having a fuel-conveying body and an annular cap fastened to the body by at least two fasteners, includes removing the fasteners, replacing the annular cap with a replacement annular cap, and interconnecting the replacement annular cap and the body using new fasteners.Type: GrantFiled: October 7, 2009Date of Patent: February 19, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Honza Stastny, Bhawan B. Patel, John Greer, Parthasarathy Sampath
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Patent number: 8205336Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.Type: GrantFiled: September 28, 2010Date of Patent: June 26, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Honza Stastny, Parthasarathy Sampath, Carol Desjardins, Kenneth Parkman, John Greer, Stephen Phillips, Eduardo Hawie, Yvan Schraenen
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Publication number: 20110079667Abstract: A method of repairing a modular gas turbine fuel nozzle tip, having a fuel-conveying body and an annular cap fastened to the body by at least two fasteners, includes removing the fasteners, replacing the annular cap with a replacement annular cap, and interconnecting the replacement annular cap and the body using new fasteners.Type: ApplicationFiled: October 7, 2009Publication date: April 7, 2011Inventors: Honza Stastny, Bhawan B. Patel, John Greer, Parthasarathy Sampath
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Publication number: 20110010935Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.Type: ApplicationFiled: September 28, 2010Publication date: January 20, 2011Inventors: Honza Stastny, Parthasarathy Sampath, Carol Desjardins, Kenneth Parkman, John Greer, Stephen Phillips, Eduardo Hawie, Yvan Schraenen
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Patent number: 7827800Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.Type: GrantFiled: October 19, 2006Date of Patent: November 9, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Honza Stastny, Parthasarathy Sampath, Carol Desjardins, Kenneth Parkman, John Greer, Stephen Phillips, Eduardo Hawie, Yvan Schraenen
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Patent number: 7805948Abstract: An assembly for sealingly mounting a device in a hole in a pressure vessel casing, the assembly transferring a load produced by pressurized fluid to the casing and retaining the stem to the casing.Type: GrantFiled: December 15, 2005Date of Patent: October 5, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Lev Alexander Prociw, Aleksandar Kojovic, Honza Stastny
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Patent number: 7631503Abstract: A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.Type: GrantFiled: September 12, 2006Date of Patent: December 15, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Honza Stastny, Jeffrey Richard Verhiel
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Patent number: 7559203Abstract: The support boss is used in a combustor of a gas turbine engine. It comprises a side wall defining an internal space. The side wall has at least one air inlet orifice. It also comprises a bottom wall closing one end of the internal space. The bottom wall has at least one air outlet orifice.Type: GrantFiled: September 16, 2005Date of Patent: July 14, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Honza Stastny, Jeffrey Richard Verhiel
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Patent number: 7509813Abstract: A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield.Type: GrantFiled: September 7, 2007Date of Patent: March 31, 2009Assignee: Pratt & Whitney Canada Corp.Inventor: Honza Stastny