Patents by Inventor David R. Pack
David R. Pack 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: 20210148235Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.Type: ApplicationFiled: November 14, 2019Publication date: May 20, 2021Inventors: Brandon W. Spangler, David R. Pack, JinQuan Xu
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Publication number: 20210140323Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.Type: ApplicationFiled: November 13, 2019Publication date: May 13, 2021Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 10954799Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.Type: GrantFiled: April 29, 2019Date of Patent: March 23, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
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Publication number: 20210054747Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.Type: ApplicationFiled: August 20, 2019Publication date: February 25, 2021Inventors: Brandon W. Spangler, David R. Pack
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Publication number: 20210054746Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides joining the leading end and the trailing end. First and second ribs each connect the first and second sides of the airfoil wall. Each of the first and second ribs define a tube portion that circumscribes a rib passage and includes cooling apertures, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall. The airfoil wall and the first and second ribs bound a cooling channel there between.Type: ApplicationFiled: August 20, 2019Publication date: February 25, 2021Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 10871074Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.Type: GrantFiled: February 28, 2019Date of Patent: December 22, 2020Assignee: Raytheon Technologies CorporationInventors: Brandon W Spangler, David R Pack
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Publication number: 20200277858Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.Type: ApplicationFiled: February 28, 2019Publication date: September 3, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, David R. Pack
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Publication number: 20200256194Abstract: A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.Type: ApplicationFiled: February 7, 2019Publication date: August 13, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: BRANDON W. SPANGLER, DAVID R. PACK
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Publication number: 20200024962Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.Type: ApplicationFiled: April 29, 2019Publication date: January 23, 2020Inventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
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Patent number: 10378364Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.Type: GrantFiled: November 7, 2017Date of Patent: August 13, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Edwin Otero, David R. Pack
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Patent number: 10378453Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.Type: GrantFiled: September 3, 2015Date of Patent: August 13, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Gabriel L. Suciu, Julian Partyka, David R. Pack, James D. Hill
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Patent number: 10316671Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.Type: GrantFiled: July 17, 2015Date of Patent: June 11, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
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Publication number: 20190136699Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.Type: ApplicationFiled: November 7, 2017Publication date: May 9, 2019Applicant: United Technologies CorporationInventors: Brandon W. Spangler, Edwin Otero, David R. Pack
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Patent number: 9719363Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.Type: GrantFiled: June 4, 2015Date of Patent: August 1, 2017Assignee: United Technologies CorporationInventors: David R Pack, Julian Partyka, James D. Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
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Publication number: 20160186666Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.Type: ApplicationFiled: September 3, 2015Publication date: June 30, 2016Inventors: Gabriel L. Suciu, Julian Partyka, David R. Pack, James D. Hill
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Publication number: 20160024935Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.Type: ApplicationFiled: July 17, 2015Publication date: January 28, 2016Inventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
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Publication number: 20150354389Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.Type: ApplicationFiled: June 4, 2015Publication date: December 10, 2015Inventors: David R Pack, Julian Partyka, James D Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
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Patent number: 6974308Abstract: A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors. The vane or blade design allows the turbine inlet temperature to increase over current technology levels while simultaneously reducing turbine cooling to low levels. A multi-wall cooling system is described, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade's pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to specific heat load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the suction surface is an independent rearward flowing serpentine). The cooling air for the independent circuits is supplied through separate passages at the base of the vane or blade.Type: GrantFiled: November 14, 2001Date of Patent: December 13, 2005Assignee: Honeywell International, Inc.Inventors: Steve H. Halfmann, Yong W. Kim, Mark C. Morris, Milton Ortiz, David R. Pack, Craig A. Wilson
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Publication number: 20040076519Abstract: A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors. The inventive vane or blade design allows the turbine inlet temperature to increase over current technology levels while simultaneously reducing turbine cooling to low levels. The invention comprises a complex multi-wall cooling system, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade's pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to specific head load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the suction surface is an independent rearward flowing serpentine).Type: ApplicationFiled: November 14, 2001Publication date: April 22, 2004Applicant: Honeywell International, Inc.Inventors: Steve H. Halfmann, Yong W. Kim, Mark C. Morris, Milton Ortiz, David R. Pack, Craig A. Wilson