Patents by Inventor Wieslaw Chlus
Wieslaw Chlus 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: 10677070Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.Type: GrantFiled: October 19, 2015Date of Patent: June 9, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Joseph F. Englehart, Edward F. Pietraszkiewicz, Wieslaw A. Chlus, David M. Konopka, Luke A. Hmiel, Kenneth Boucher
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Patent number: 10626729Abstract: An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees.Type: GrantFiled: March 13, 2014Date of Patent: April 21, 2020Assignee: United Technologies CorporationInventors: Seth J. Thomen, Edward F. Pietraszkiewicz, Dominic J. Mongillo, Jr., Wieslaw A. Chlus, Erik R. Granstrand
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Patent number: 10408066Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.Type: GrantFiled: August 15, 2012Date of Patent: September 10, 2019Assignee: United Technologies CorporationInventors: Wieslaw A. Chlus, Seth J. Thomen
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Patent number: 10156150Abstract: An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces.Type: GrantFiled: March 10, 2014Date of Patent: December 18, 2018Assignee: United Technologies CorporationInventors: Wieslaw A. Chlus, Seth J. Thomen
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Patent number: 9982549Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.Type: GrantFiled: December 18, 2012Date of Patent: May 29, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Seth J. Thomen, Wieslaw A. Chlus
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Patent number: 9850761Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.Type: GrantFiled: January 24, 2014Date of Patent: December 26, 2017Assignee: United Technologies CorporationInventors: Seth J. Thomen, Wieslaw A. Chlus
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Publication number: 20170107830Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.Type: ApplicationFiled: October 19, 2015Publication date: April 20, 2017Inventors: Joseph F. Englehart, Edward F. Pietraszkiewicz, Wieslaw A. Chlus, David M. Konopka, Luke A. Hmiel, Kenneth Boucher
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Publication number: 20160169002Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body that includes a first wall and a second wall spaced apart and joined together at each of a leading edge and a trailing edge and extending between a root and a tip. An internal cooling circuit is disposed at least partially inside of the airfoil body. The internal cooling circuit has a first cooling passage disposed near a junction between the tip and the trailing edge and a fanned array of cooling holes that extend between the first cooling passage to at least the tip.Type: ApplicationFiled: July 24, 2014Publication date: June 16, 2016Inventors: Wieslaw A. CHLUS, Seth J. THOMEN
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Publication number: 20160032730Abstract: An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees.Type: ApplicationFiled: March 13, 2014Publication date: February 4, 2016Inventors: Seth J. Thomen, Edward F. Pietraszkiewicz, Dominic J. Mongillo, JR., Wieslaw A. Chlus, Erik R. Granstrand
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Publication number: 20160003074Abstract: An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces.Type: ApplicationFiled: March 10, 2014Publication date: January 7, 2016Inventors: Wieslaw A. Chlus, Seth J. Thomen
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Publication number: 20150369055Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.Type: ApplicationFiled: January 24, 2014Publication date: December 24, 2015Inventors: Seth J. Thomen, Wieslaw A. Chlus
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Publication number: 20150354369Abstract: An airfoil for a gas turbine engine includes an airfoil that extends from a platform that has first and second circumferential sides that respectively extend to first and second circumferential edges. The first circumferential side has a tapered surface at a first angle relative to a flow path surface. The second circumferential surface has a cooling hole that extends toward the second lateral edge at a second angle relative to the flow path surface. The tapered surface and the cooling hole are axially aligned with one another.Type: ApplicationFiled: June 2, 2015Publication date: December 10, 2015Inventors: Wieslaw A. Chlus, Seth J. Thomen
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Publication number: 20140165591Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.Type: ApplicationFiled: December 18, 2012Publication date: June 19, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Seth J. Thomen, Wieslaw A. Chlus
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Publication number: 20140047842Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.Type: ApplicationFiled: August 15, 2012Publication date: February 20, 2014Inventors: Wieslaw A. Chlus, Seth J. Thomen
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Publication number: 20130318787Abstract: A method of manufacturing a family of airfoils includes providing a plurality of airfoil blanks of identical geometry, selecting a first airfoil geometry from a family of airfoil geometries, selecting a second, different airfoil geometry from the family of airfoil geometries, machining a first one of the plurality of airfoil blanks to the first airfoil geometry to produce a first airfoil of the family of airfoil geometries, and machining a second, different one of the plurality of airfoil blanks to the second airfoil geometry to produce a second, different airfoil of the family of airfoil geometriesType: ApplicationFiled: June 5, 2012Publication date: December 5, 2013Inventors: Seth J. Thomen, Wieslaw A. Chlus
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Patent number: 7726944Abstract: A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.Type: GrantFiled: September 20, 2006Date of Patent: June 1, 2010Assignee: United Technologies CorporationInventors: Richard H. Page, Wieslaw A. Chlus
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Publication number: 20100080711Abstract: A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.Type: ApplicationFiled: September 20, 2006Publication date: April 1, 2010Inventors: Richard H. Page, Wieslaw A. Chlus
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Patent number: 7575416Abstract: A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In one detailed embodiment, a deformable seal member formed of a high temperature material is disposed between the root sections of adjacent rotor blades and engages the blades under operative conditions.Type: GrantFiled: May 18, 2006Date of Patent: August 18, 2009Assignee: United Technologies CorporationInventors: Stanley J. Funk, Wieslaw A. Chlus
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Publication number: 20070269315Abstract: A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In one detailed embodiment, a deformable seal member formed of a high temperature material is disposed between the root sections of adjacent rotor blades and engages the blades under operative conditions.Type: ApplicationFiled: May 18, 2006Publication date: November 22, 2007Inventors: Stanley J. Funk, Wieslaw A. Chlus
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Patent number: 7175386Abstract: A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.Type: GrantFiled: December 17, 2003Date of Patent: February 13, 2007Assignee: United Technologies CorporationInventors: Anthony Cherolis, Wieslaw A. Chlus