Patents by Inventor Daniel S. Rogers
Daniel S. Rogers 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: 20240110488Abstract: A gas turbine engine includes a turbine section that has a ceramic matrix composite body that defines a core gaspath side that a row of blades, a forward end, an aft end, and circumferential sides. The forward end abuts at least one vane of a first row of vanes, and the aft end including a seal channel. A compliant seal is disposed in the seal channel and seals against at least one vane of a second row of vanes.Type: ApplicationFiled: August 28, 2023Publication date: April 4, 2024Inventors: Paul M. Lutjen, Daniel S. Rogers, Timothy J. Harding, James E. Weisheit, Morely S. Sherman, Mikayla M. Rogers, Marshall F. Thayer, Joseph Micucci
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Publication number: 20240110487Abstract: A gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.Type: ApplicationFiled: September 29, 2023Publication date: April 4, 2024Inventors: Daniel S. Rogers, James E. Weisheit, Morely S. Sherman, Mikayla M. Rogers, Timothy J. Harding, Marshall F. Thayer, Joseph Micucci
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Patent number: 11879340Abstract: There is a blade outer air seal positioned to be radially outward of blades in the rotating blade row relative to the rotational axis. There is at least one brush seal having bristles extending from a mount location radially inward to contact a sealing surface on the blade outer air seal. An angle is defined between the bristles and relative to the sealing surface having a radially inward extending component, and with an axial component in a direction toward a leading edge attachment feature and a trailing edge attachment feature, and the angle is less than 90° on a side of the brush seal opposite the leading edge and trailing edge mount hooks. A gas turbine engine component is also disclosed.Type: GrantFiled: September 30, 2022Date of Patent: January 23, 2024Assignee: RTX CorporationInventors: Daniel S. Rogers, Timothy J. Harding, Joseph Micucci, Paul M. Lutjen
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Patent number: 11352979Abstract: A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.Type: GrantFiled: April 24, 2020Date of Patent: June 7, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Yuk-Kwan Brian Yuen, Christopher T. Anglin, Matthew Nickerson, Daniel S. Rogers
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Publication number: 20210332775Abstract: A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.Type: ApplicationFiled: April 24, 2020Publication date: October 28, 2021Inventors: Yuk-Kwan Brian Yuen, Christopher T. Anglin, Matthew Nickerson, Daniel S. Rogers
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Patent number: 10794223Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.Type: GrantFiled: December 13, 2017Date of Patent: October 6, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson
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Patent number: 10767560Abstract: A bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.Type: GrantFiled: September 11, 2018Date of Patent: September 8, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Taryn Narrow, Gregory E. Reinhardt, Collin P. Fitzgerald, Christopher M. Valva, Leonard Kolshak
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Publication number: 20200080478Abstract: A bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.Type: ApplicationFiled: September 11, 2018Publication date: March 12, 2020Inventors: Daniel S. Rogers, Taryn Narrow, Gregory E. Reinhardt, Collin P. Fitzgerald, Christopher M. Valva, Leonard Kolshak
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Patent number: 10436071Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.Type: GrantFiled: April 15, 2016Date of Patent: October 8, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Jeremy Drake, Brian C. McLaughlin
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Patent number: 10352184Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.Type: GrantFiled: October 31, 2016Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jose R. Paulino, Ken F. Blaney, Terence P. Tyler, Jr., Daniel S. Rogers, Anthony B. Swift, Thomas E. Clark
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Patent number: 10316749Abstract: Conduits for guiding the motion of an inner diameter shroud of a low pressure compressor of a gas turbine engine are disclosed. The inner diameter shroud has at least three slots formed in one or more radially inwardly extending flanges. Each of the conduits are configured to assemble with a respective one of the at least three slots. Each conduit comprises a bushing having a first panel, and the first panel is capable of being inserted in a respective one of the slots of the inner diameter shroud. The conduit further comprises a bracket capable of being attached to a bearing support of a fan intermediate case of the gas turbine engine. The bushing is capable of being attached to the bracket.Type: GrantFiled: September 16, 2015Date of Patent: June 11, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson
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Publication number: 20180119560Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.Type: ApplicationFiled: October 31, 2016Publication date: May 3, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jose R. Paulino, Ken F. Blaney, Terence P. Tyler, JR., Daniel S. Rogers, Anthony B. Swift, Thomas E. Clark
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Publication number: 20180112558Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.Type: ApplicationFiled: December 13, 2017Publication date: April 26, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: DANIEL S. ROGERS, STEPHEN W. MILKS, STEVEN J. FEIGLESON
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Patent number: 9879565Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.Type: GrantFiled: January 20, 2015Date of Patent: January 30, 2018Assignee: United Technologies CorporationInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson
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Publication number: 20170298776Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.Type: ApplicationFiled: April 15, 2016Publication date: October 19, 2017Inventors: Daniel S. Rogers, Jeremy Drake, Brian C. McLaughlin
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Publication number: 20160208652Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.Type: ApplicationFiled: January 20, 2015Publication date: July 21, 2016Applicant: United Technologies CorporationInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson
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Publication number: 20160108812Abstract: Conduits for guiding the motion of an inner diameter shroud of a low pressure compressor of a gas turbine engine are disclosed. The inner diameter shroud has at least three slots formed in one or more radially inwardly extending flanges. Each of the conduits are configured to assemble with a respective one of the at least three slots. Each conduit comprises a bushing having a first panel, and the first panel is capable of being inserted in a respective one of the slots of the inner diameter shroud. The conduit further comprises a bracket capable of being attached to a bearing support of a fan intermediate case of the gas turbine engine. The bushing is capable of being attached to the bracket.Type: ApplicationFiled: September 16, 2015Publication date: April 21, 2016Applicant: United Technologies CorporationInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson