Patents by Inventor Lee Drozdenko
Lee Drozdenko 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: 11002285Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.Type: GrantFiled: September 4, 2020Date of Patent: May 11, 2021Assignee: Raytheon Technologies CorporationInventors: Lee Drozdenko, William R. Graves, Michael Li, Maria C. Kirejczyk
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Patent number: 10982683Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.Type: GrantFiled: November 25, 2014Date of Patent: April 20, 2021Assignee: Raytheon Technologies CorporationInventors: Lee Drozdenko, James O. Hansen, Jesse C. Meyer, Maria C. Kirejczyk, Scot A. Webb, Brandon A. Gates, Richard B. Bergethon
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Publication number: 20200400159Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.Type: ApplicationFiled: September 4, 2020Publication date: December 24, 2020Applicant: Raytheon Technologies CorporationInventors: Lee Drozdenko, William R. Graves, Michael LI, Maria C. Kirejczyk
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Patent number: 10801515Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.Type: GrantFiled: January 11, 2019Date of Patent: October 13, 2020Assignee: Raytheon Technologies CorporationInventors: Lee Drozdenko, William R. Graves, Michael Li, Maria C. Kirejczyk
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Patent number: 10760592Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 17.2-18.2 inches (436-462 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 10.0-11.0 inches (255-281 mm). The airfoil element includes at least two of a first mode with a frequency of 51±10% Hz, a second mode with a frequency of 147±10% Hz, a third mode with a frequency of 267±10% Hz, a fourth mode with a frequency of 350±10% Hz, a fifth mode with a frequency of 454±10% Hz and a sixth mode with a frequency of 619±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: September 1, 2020Assignee: Raytheon Technologies CorporationInventors: Xuedong Zhou, Jordan J. Franklin, Michael A. Weisse, Lee Drozdenko, Mouhamadou Diop, Daniel W. Yebo, Linda S. Li
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Publication number: 20200025211Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.Type: ApplicationFiled: January 11, 2019Publication date: January 23, 2020Applicant: United Technologies CorporationInventors: Lee Drozdenko, William R. Graves, Michael Li, Maria C. Kirejczyk
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Patent number: 10508556Abstract: An assembly includes a rotor disk, a rotor blade and a root spacer. The rotor disk includes a slot that extends longitudinally into the rotor disk. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged with the slot between the rotor disk and the blade root. The root spacer extends longitudinally to a spacer end, and includes a grip element and a plurality of notches. The grip element is arranged at the spacer end laterally between the notches. The grip element at least partially defines the notches. The notches extend radially and longitudinally into the root spacer.Type: GrantFiled: January 17, 2013Date of Patent: December 17, 2019Assignee: United Technologies CorporationInventors: Lee Drozdenko, James H. Moffitt
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Patent number: 10400784Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.Type: GrantFiled: March 21, 2016Date of Patent: September 3, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Lee Drozdenko, William R. Graves, Michael Li, Maria C. Kirejczyk
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Patent number: 10280771Abstract: A spacer for use in a hub and blade assembly of a gas turbine engine including a first layer of a first material forming the spacer body having an elongate shape. The first material has a first stiffness. A second layer of a second material is mechanically attached to the first layer. The second material has a second stiffness different from the first stiffness.Type: GrantFiled: September 19, 2014Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Lee Drozdenko, William R. Graves
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Patent number: 10087948Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.Type: GrantFiled: March 30, 2015Date of Patent: October 2, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Lee Drozdenko, James O. Hansen, Christopher J. Hertel, Steven T. Holland
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Patent number: 9828864Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.Type: GrantFiled: March 15, 2013Date of Patent: November 28, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sean A. Whitehurst, Patrick James McComb, Lee Drozdenko
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Patent number: 9650897Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.Type: GrantFiled: June 21, 2012Date of Patent: May 16, 2017Assignee: United Technologies CorporationInventors: James L. Deal, John J. Schirra, Lee Drozdenko, William R. Graves, James O. Hansen, Michael A. Weisse, Thomas J. Watson
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Publication number: 20170023010Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.Type: ApplicationFiled: November 25, 2014Publication date: January 26, 2017Inventors: Lee Drozdenko, James O. Hansen, Jesse C. Meyer, Maria C. Kirejczyk, Scot A. Webb, Brandon A. Gates, Richard B. Bergethon
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Publication number: 20160348689Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.Type: ApplicationFiled: March 21, 2016Publication date: December 1, 2016Applicant: United Technologies CorporationInventors: Lee Drozdenko, William R. Graves, Michael Ll, Maria C. Kirejczyk
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Publication number: 20160290356Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.Type: ApplicationFiled: March 30, 2015Publication date: October 6, 2016Inventors: Lee Drozdenko, James O. Hansen, Christopher J. Hertel, Steven T. Holland
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Patent number: 9422819Abstract: A rotor assembly is provided that includes a rotor blade, a root spacer, and a rotor disk with a slot. The rotor blade includes a blade root arranged within the slot. The blade root includes a root base segment and a pair of root side segments. The root base segment is laterally separated from the rotor disk by the root side segments. The root spacer is arranged within the slot, and includes a side surface that extends radially between an inner surface and an outer surface. The side surface is approximately laterally aligned with an intersection between the root base segment and a first of the root side segments. The outer surface engages the root base segment.Type: GrantFiled: December 18, 2012Date of Patent: August 23, 2016Assignee: United Technologies CorporationInventors: Lee Drozdenko, William R. Graves
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Publication number: 20160237835Abstract: A spacer for use in a hub and blade assembly of a gas turbine engine including a first layer of a first material forming the spacer body having an elongate shape. The first material has a first stiffness. A second layer of a second material is mechanically attached to the first layer. The second material has a second stiffness different from the first stiffness.Type: ApplicationFiled: September 19, 2014Publication date: August 18, 2016Inventors: Lee Drozdenko, William R. Graves
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Patent number: 9359906Abstract: A rotor assembly is provided that includes a rotor disk, a rotor blade and a root spacer. The rotor disk includes a slot. The rotor blade includes a blade root that is arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer includes a base segment, a side segment and a fracture feature. The base segment radially engages the rotor disk. The side segment is radially separated from the rotor disk by a gap. The fracture feature may radially fracture the root spacer at an intersection between the base segment and the side segment.Type: GrantFiled: December 18, 2012Date of Patent: June 7, 2016Assignee: United Technologies CorporationInventors: Lee Drozdenko, William R. Graves
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Patent number: 9297272Abstract: A fan rotor includes a rotor body with at least one slot receiving a fan blade. The fan blade has an outer surface, at least at some areas, formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A spacer is positioned radially inwardly of the dovetail biasing the fan blade against the slot. The spacer includes a grounding element, which is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor. The rotating element is formed of a third material. The first material is less electrically conductive than the third material. The grounding and rotating elements form a ground path from the portion of the dovetail into the rotor.Type: GrantFiled: October 24, 2012Date of Patent: March 29, 2016Assignee: United Technologies CorporationInventors: Lee Drozdenko, Allan R. Penda
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Publication number: 20150361805Abstract: An assembly includes a rotor disk, a rotor blade and a root spacer. The rotor disk includes a slot that extends longitudinally into the rotor disk. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged with the slot between the rotor disk and the blade root. The root spacer extends longitudinally to a spacer end, and includes a grip element and a plurality of notches. The grip element is arranged at the spacer end laterally between the notches. The grip element at least partially defines the notches. The notches extend radially and longitudinally into the root spacer.Type: ApplicationFiled: January 17, 2013Publication date: December 17, 2015Inventors: Lee Drozdenko, James H. Moffitt