Patents by Inventor Dennis Paul Dry
Dennis Paul Dry 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: 20240117756Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.Type: ApplicationFiled: August 2, 2023Publication date: April 11, 2024Inventors: Daniel Patrick Kerns, Mark Eugene Noe, Dennis Paul Dry, Brandon ALlanson Reynolds
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Patent number: 11739663Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.Type: GrantFiled: June 27, 2019Date of Patent: August 29, 2023Assignee: General Electric CompanyInventors: Daniel Patrick Kerns, Mark Eugene Noe, Dennis Paul Dry, Brandon ALlanson Reynolds
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Patent number: 11655719Abstract: An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.Type: GrantFiled: April 16, 2021Date of Patent: May 23, 2023Assignee: General Electric CompanyInventors: Matthew Mark Weaver, Dennis Paul Dry, Todd William Bachmann
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Publication number: 20220333491Abstract: An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.Type: ApplicationFiled: April 16, 2021Publication date: October 20, 2022Inventors: Matthew Mark Weaver, Dennis Paul Dry, Todd William Bachmann
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Patent number: 11015613Abstract: A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.Type: GrantFiled: January 12, 2017Date of Patent: May 25, 2021Assignee: General Electric CompanyInventors: Daniel Patrick Kerns, Dennis Paul Dry, Megan Elizabeth Scheitlin, Alexander Martin Sener, Jason David Shapiro
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Patent number: 10738644Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.Type: GrantFiled: August 30, 2017Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
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Publication number: 20190338676Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.Type: ApplicationFiled: June 27, 2019Publication date: November 7, 2019Inventors: Daniel Patrick Kerns, Mark Eugene Noe, Dennis Paul Dry, Brandon ALlanson Reynolds
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Patent number: 10400627Abstract: In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.Type: GrantFiled: March 31, 2015Date of Patent: September 3, 2019Assignee: General Electric CompanyInventors: Wei Ning, Dennis Paul Dry, Mullahalli Venkataramaniah Srinivas
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Patent number: 10385731Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.Type: GrantFiled: June 12, 2017Date of Patent: August 20, 2019Assignee: General Electric CompanyInventors: Daniel Patrick Kerns, Mark Eugene Noe, Dennis Paul Dry, Brandon ALlanson Reynolds
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Publication number: 20190063250Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
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Publication number: 20180355760Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.Type: ApplicationFiled: June 12, 2017Publication date: December 13, 2018Inventors: Daniel Patrick Kerns, Mark Eugene Noe, Dennis Paul Dry, Brandon ALlanson Reynolds
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Publication number: 20180195403Abstract: A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.Type: ApplicationFiled: January 12, 2017Publication date: July 12, 2018Inventors: Daniel Patrick Kerns, Dennis Paul Dry, Megan Elizabeth Scheitlin, Alexander Martin Sener, Jason David Shapiro
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Publication number: 20180087387Abstract: Coating systems for a turbine blade tip, such as a metal turbine blade tip, are provided. The coating system can include a thermal barrier coating on the surface of the turbine blade tip as well as one or more bond coats and/or metallic coatings. The coated blade tip can be used with a ceramic matrix composite shroud coated with an environmental barrier coating to reduce blade tip wear. Methods are also provided for applying the coating system onto a turbine blade tip.Type: ApplicationFiled: September 28, 2016Publication date: March 29, 2018Inventors: Jinjie Shi, Larry Steven Rosenzweig, Christopher Edward Wolfe, Dennis Paul Dry
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Publication number: 20160290157Abstract: In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.Type: ApplicationFiled: March 31, 2015Publication date: October 6, 2016Inventors: Wei Ning, Dennis Paul Dry, Mullahalli Venkataramaniah Srinivas