Patents by Inventor Maria C. Kirejczyk
Maria C. Kirejczyk 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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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: 10487843Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.Type: GrantFiled: August 4, 2014Date of Patent: November 26, 2019Assignee: United Technologies CorporationInventors: Lee M. Drozdenko, James O. Hansen, Maria C. Kirejczyk, Scot A. Webb, Jesse C. Meyer, Brandon A. Gates, Richard B. Bergethon, Michael A. Morden
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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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Publication number: 20180202299Abstract: A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.Type: ApplicationFiled: January 18, 2017Publication date: July 19, 2018Inventors: James R. Murdock, James H. Moffitt, Scot A. Webb, Jay Thomas Abraham, Maria C. Kirejczyk
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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: 20160215784Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.Type: ApplicationFiled: August 4, 2014Publication date: July 28, 2016Applicant: United Technologies CorporationInventors: Lee M. Drozdenko, James O. Hansen, Maria C. Kirejczyk, Scot A. Webb, Jesse C. Meyer, Brandon A. Gates, Richard B. Bergethon, Michael A. Morden