Patents by Inventor Robert C. Dolan
Robert C. Dolan 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: 20240123238Abstract: A system comprising processing circuitry configured to receive a wirelessly-transmitted message from a medical device, the message indicating that the medical device detected an acute health event of the patient. In response to the message, the processing circuitry is configured to determine a location of the patient, determine an alert area based on the location of the patient, and control transmission of an alert of the acute heath event of the patient to any one or more computing devices of one or more potential responders within the alert area.Type: ApplicationFiled: February 16, 2022Publication date: April 18, 2024Inventors: Robert W. Stadler, Becky L. Dolan, Yong K. Cho, Paul G. Krause, Shantanu Sarkar, Robert C. Kowal
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Patent number: 11781436Abstract: An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.Type: GrantFiled: January 7, 2022Date of Patent: October 10, 2023Assignee: RTX CorporationInventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Eric W. Malmborg, Steven T. Gordon
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Patent number: 11389900Abstract: A method of forming an airfoil includes the steps of (a) providing an airfoil body with a hollow having at least one rib extending to an outer surface, and forming the outer surface of the rib to have at least one groove connecting a hollow pocket within a boundary defined by the rib to a location outwardly of the rib, (b) placing a cover over the hollow, and (c) welding the cover to the airfoil body, and such that the rib is welded to the blade cover. An intermediate airfoil body is also disclosed.Type: GrantFiled: April 13, 2020Date of Patent: July 19, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Robert C. Dolan
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Publication number: 20220127966Abstract: An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.Type: ApplicationFiled: January 7, 2022Publication date: April 28, 2022Inventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Eric W. Malmborg, Steven T. Gordon
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Patent number: 11248477Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.Type: GrantFiled: August 2, 2019Date of Patent: February 15, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Eric W. Malmborg, Steven T. Gordon
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Patent number: 11174737Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.Type: GrantFiled: March 24, 2020Date of Patent: November 16, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Robert C. Dolan, Michael A. Weisse, Daniel A. Bales, Steven T. Gordon, Dmitri Novikov, Eric W. Malmborg, Francis B. Parisi
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Patent number: 11148221Abstract: A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to establish pressure and suction sides of an airfoil, positioning the airfoil between first and second dies of a deforming station, heating the airfoil body to a first predefined temperature threshold between the first and second dies, and moving the first die relative to the second die to hold the airfoil between the first and second dies subsequent to the heating step, and then deforming the airfoil between the first and second dies.Type: GrantFiled: August 29, 2019Date of Patent: October 19, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel A. Bales, Thomas DeMichael, Robert C. Dolan, Francis B. Parisi
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Publication number: 20210060692Abstract: A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to establish pressure and suction sides of an airfoil, positioning the airfoil between first and second dies of a deforming station, heating the airfoil body to a first predefined temperature threshold between the first and second dies, and moving the first die relative to the second die to hold the airfoil between the first and second dies subsequent to the heating step, and then deforming the airfoil between the first and second dies.Type: ApplicationFiled: August 29, 2019Publication date: March 4, 2021Inventors: Daniel A. Bales, Thomas DeMichael, Robert C. Dolan, Francis B. Parisi
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Publication number: 20210032997Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.Type: ApplicationFiled: August 2, 2019Publication date: February 4, 2021Inventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Eric W. Malmborg, Steven T. Gordon
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Publication number: 20200392854Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.Type: ApplicationFiled: March 24, 2020Publication date: December 17, 2020Inventors: Robert C. Dolan, Michael A. Weisse, Daniel A. Bales, Steven T. Gordon, Dmitri Novikov, Eric W. Malmborg, Francis B. Parisi
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Patent number: 10830064Abstract: An airfoil surface includes a first titanium portion, a second titanium portion, an aluminum alloy braze disposed there between, and a titanium coating covering the aluminum alloy braze, at least part of the first titanium portion and at least part of the second titanium portion.Type: GrantFiled: June 12, 2017Date of Patent: November 10, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Robert C. Dolan
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Publication number: 20200346302Abstract: A method of forming an airfoil includes the steps of (a) providing an airfoil body with a hollow having at least one rib extending to an outer surface, and forming the outer surface of the rib to have at least one groove connecting a hollow pocket within a boundary defined by the rib to a location outwardly of the rib, (b) placing a cover over the hollow, and (c) welding the cover to the airfoil body, and such that the rib is welded to the blade cover. An intermediate airfoil body is also disclosed.Type: ApplicationFiled: April 13, 2020Publication date: November 5, 2020Inventor: Robert C. Dolan
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Patent number: 10502064Abstract: An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.Type: GrantFiled: August 7, 2017Date of Patent: December 10, 2019Assignee: United Technologies CorporationInventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Kenneth A. Frisk, Steven T. Gordon, William R. Graves, Eric W. Malmborg, Francis B. Parisi, Randy P. Salva, Michael A. Weisse, Russell A. Beers, Xuedong Zhou, Christopher Treese, Tri Nguyen
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Publication number: 20190040744Abstract: An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.Type: ApplicationFiled: August 7, 2017Publication date: February 7, 2019Inventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Kenneth A. Frisk, Steven T. Gordon, William R. Graves, Eric W. Malmborg, Francis B. Parisi, Randy P. Salva, Michael A. Weisse, Russell A. Beers, Xuedong Zhou, Christopher Treese, Tri Nguyen
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Publication number: 20180355733Abstract: An airfoil surface includes a first titanium portion, a second titanium portion, an aluminum alloy braze disposed there between, and a titanium coating covering the aluminum alloy braze, at least part of the first titanium portion and at least part of the second titanium portion.Type: ApplicationFiled: June 12, 2017Publication date: December 13, 2018Inventor: Robert C. Dolan