Patents by Inventor Michael Ray TUERTSCHER
Michael Ray TUERTSCHER 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: 11466580Abstract: A nozzle including a vane and a band, each having defined therein interlocking features. The vane and the band are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The vane and the band include one or more interlocking features. The nozzle further including an interlocking mechanical joint joining the vane and the band to one another. Methods are also provided for joining the vane and the band at the interlocking features to form an interlocking mechanical joint.Type: GrantFiled: May 2, 2018Date of Patent: October 11, 2022Assignee: General Electric CompanyInventors: Sara Saxton Underwood, Douglas Glenn Decesare, Michael Ray Tuertscher, Daniel Gene Dunn, Douglas Melton Carper
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Patent number: 11391171Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.Type: GrantFiled: April 23, 2019Date of Patent: July 19, 2022Assignee: General Electric CompanyInventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher, Aaron Michael Dziech, Brett Joseph Geiser
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Patent number: 11149569Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.Type: GrantFiled: April 22, 2019Date of Patent: October 19, 2021Assignee: General Electric CompanyInventors: Brandon ALIanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher
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Patent number: 11092023Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: GrantFiled: January 31, 2018Date of Patent: August 17, 2021Assignee: General Electric CompanyInventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps
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Patent number: 10738628Abstract: A ceramic matrix composite (CMC) component including a subcomponent, such as a band flowpath, a load bearing wall and a wall support, each comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The CMC component further including at least one mechanical joint joining the subcomponent, the load bearing wall and the wall support to form the CMC component. The reinforcing fibers of the load bearing wall are oriented substantially normal to the reinforcing fibers of the subcomponent and the wall support. Methods are also provided for joining the subcomponent, the load bearing wall and the wall support to form a mechanical joint.Type: GrantFiled: May 25, 2018Date of Patent: August 11, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Sara Saxton Underwood, Douglas Glenn Decesare, Michael Ray Tuertscher, Daniel Gene Dunn, Douglas Melton Carper, Brian Gregg Feie
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Publication number: 20200088051Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: ApplicationFiled: January 31, 2018Publication date: March 19, 2020Inventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps
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Publication number: 20200024999Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.Type: ApplicationFiled: April 22, 2019Publication date: January 23, 2020Inventors: Brandon ALIanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher
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Publication number: 20190360346Abstract: A ceramic matrix composite (CMC) component including a subcomponent, such as a band flowpath, a load bearing wall and a wall support, each comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The CMC component further including at least one mechanical joint joining the subcomponent, the load bearing wall and the wall support to form the CMC component. The reinforcing fibers of the load bearing wall are oriented substantially normal to the reinforcing fibers of the subcomponent and the wall support. Methods are also provided for joining the subcomponent, the load bearing wall and the wall support to form a mechanical joint.Type: ApplicationFiled: May 25, 2018Publication date: November 28, 2019Inventors: Sara Saxton Underwood, Douglas Glenn Decesare, Michael Ray Tuertscher, Daniel Gene Dunn, Douglas Melton Carper, Brian Gregg Feie
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Publication number: 20190338660Abstract: A nozzle including a vane and a band, each having defined therein interlocking features. The vane and the band are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The vane and the band include one or more interlocking features. The nozzle further including an interlocking mechanical joint joining the vane and the band to one another. Methods are also provided for joining the vane and the band at the interlocking features to form an interlocking mechanical joint.Type: ApplicationFiled: May 2, 2018Publication date: November 7, 2019Inventors: Sara Saxton Underwood, Douglas Glenn Decesare, Michael Ray Tuertscher, Daniel Gene Dunn, Douglas Melton Carper
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Patent number: 10400616Abstract: A turbine nozzle apparatus includes: a vane extending between inner and outer bands, the interior of the vane being open and communicating with an aperture in the outer band, wherein the vane and the bands are part of a monolithic whole of low-ductility material; a metallic baffle inside the vane, the baffle having upper and lower ends and a peripheral wall including a plurality of impingement holes defining an interior space, closed off by an end wall at the lower end; and a metallic retainer having a body with a shape generally matching the shape of the aperture, the body bearing against the upper end of the impingement baffle and being connected to the outer band by a plurality of mechanical fasteners.Type: GrantFiled: June 18, 2014Date of Patent: September 3, 2019Assignee: General Electric CompanyInventors: Michael Ray Tuertscher, Darell Glenn Senile, Greg Phelps
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Patent number: 10385709Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.Type: GrantFiled: February 23, 2017Date of Patent: August 20, 2019Assignee: General Electric CompanyInventors: Brandon Allanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher, Aaron Michael Dziech, Brett Joseph Geiser
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Publication number: 20190249556Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.Type: ApplicationFiled: April 23, 2019Publication date: August 15, 2019Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher, Aaron Michael Dziech, Brett Joseph Geiser
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Patent number: 10378373Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.Type: GrantFiled: February 23, 2017Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher
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Patent number: 10309240Abstract: An airfoil assembly for a gas turbine engine and a method of transferring load from the ceramic matrix composite (CMC) airfoil assembly to a metallic vane assembly support member are provided. The airfoil assembly includes a forward end and an aft end with respect to an axial direction of the gas turbine engine. The airfoil assembly includes a radially outer end component, a radially inner end component, and a hollow airfoil body extending therebetween. The radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly and formed integrally with the outer end component, the load-bearing feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure and selectively positioned orthogonally to a force imparted into the airfoil assembly.Type: GrantFiled: July 24, 2015Date of Patent: June 4, 2019Assignee: General Electric CompanyInventors: Bryce Loring Heitman, Darrell Glenn Senile, Michael Ray Tuertscher, Greg Scott Phelps, Brian Gregg Feie, Steven James Murphy
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Patent number: 10301954Abstract: A ceramic airfoil is provided. The ceramic airfoil may include a leading edge, a trailing edge, and a pair of sidewalls. The pair of sidewalls may include a suction sidewall and a pressure sidewall spaced apart in a widthwise direction and extending in the chordwise direction between the leading edge and the trailing edge. The pair of sidewalls may also define cooling cavity and a plurality of internal cooling passages downstream of the cooling cavity to receive a pressurized cooling airflow. The internal cooling passages may be defined across a diffusion section with a set diffusion length, and include one or more predefined ratios or angles.Type: GrantFiled: January 8, 2016Date of Patent: May 28, 2019Assignee: General Electric CompanyInventors: Jason Randolph Allen, Robert Alan Frederick, Robert David Briggs, Michael Ray Tuertscher
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Patent number: 10180073Abstract: A turbine nozzle includes an arcuate inner band having opposed flowpath and back sides, and an aft flange extending outward from the back side; an arcuate outer band having opposed flowpath and back sides; an airfoil-shaped turbine vane extending between the flowpath sides of the inner and outer bands, wherein the inner and outer bands and the vane comprise a ceramic low-ductility material; and a metallic collar surrounding the aft flange.Type: GrantFiled: August 6, 2014Date of Patent: January 15, 2019Assignee: General Electric CompanyInventors: Michael Ray Tuertscher, Darrell Glenn Senile, Greg Phelps
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Publication number: 20180238181Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.Type: ApplicationFiled: February 23, 2017Publication date: August 23, 2018Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher
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Publication number: 20180238184Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.Type: ApplicationFiled: February 23, 2017Publication date: August 23, 2018Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher, Aaron Michael Dziech, Brett Joseph Geiser
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Patent number: 10017425Abstract: Methods and materials for forming in-situ features in a ceramic matrix composite component are described. The method of forming a ceramic matrix composite component with cooling features, comprises forming a preform tape, laying up said preform tape to a desired shape, placing a high-temperature resistant fugitive material insert of preselected geometry in the preform tape of the desired shape, compacting the preform tape of the desired shape, burning out the preform tape of the desired shape, melt infiltrating the desired shape, removing the high-temperature resistant insert to form the cooling features during one of the burning out or the melt infiltrating or following the burning out or the melt infiltrating.Type: GrantFiled: April 23, 2014Date of Patent: July 10, 2018Assignee: General Electric CompanyInventors: Michael Ray Tuertscher, Mark Eugene Noe, Glen Harold Kirby, Sheena Kum Foster Walker
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Patent number: 9915159Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: GrantFiled: December 18, 2014Date of Patent: March 13, 2018Assignee: General Electric CompanyInventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps