Patents by Inventor Richard William Jendrix
Richard William Jendrix 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: 11970946Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.Type: GrantFiled: July 29, 2021Date of Patent: April 30, 2024Assignee: General Electric CompanyInventors: Travis J. Packer, James Hamilton Grooms, David Fasig, Richard William Jendrix, Scott Alan Schimmels, Bradford Alan Tracey, Michael Alan Hile, Thomas Ryan Wallace
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Publication number: 20230035302Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.Type: ApplicationFiled: July 29, 2021Publication date: February 2, 2023Inventors: Travis J. Packer, James Hamilton Grooms, David Fasig, Richard William Jendrix, Scott Alan Schimmels, Bradford Alan Tracey, Michael Alan Hile, Thomas Ryan Wallace
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Patent number: 10094228Abstract: Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.Type: GrantFiled: May 1, 2015Date of Patent: October 9, 2018Assignee: General Electric CompanyInventors: Richard William Jendrix, Christopher Thomas Schuppe, Christopher John Van Derven, Samuel Joseph Stoughton, Charles Thomas McMillan, John David Bibler
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Publication number: 20160319681Abstract: Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.Type: ApplicationFiled: May 1, 2015Publication date: November 3, 2016Inventors: Richard William Jendrix, Christopher Thomas Schuppe, Christopher John Van Derven, Samuel Joseph Stoughton, Charles Thomas McMillan, John David Bibler
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Patent number: 9453422Abstract: A turbine disk and blade assembly comprises a turbine disk including a plurality of disk posts extending radially therefrom and a plurality of disk slots between adjacent disk posts. The turbine disk is of a first material having a first coefficient of thermal expansion. The assembly further comprises a plurality of turbine blades. One of the turbine blades is received in each disk slot. The turbine blades are of a second material having a second coefficient of thermal expansion. The assembly further comprises a plurality of seal plates, wherein one of the seal plates is positioned in each disk slot radially inward of the turbine blade. The seal plates are of a material having a coefficient of thermal expansion substantially similar to that of either the disk posts or the turbine blade.Type: GrantFiled: March 8, 2013Date of Patent: September 27, 2016Assignee: General Electric CompanyInventors: Michael Alan Hile, Brian Agnew, James Hamilton Grooms, Richard William Jendrix
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Patent number: 9033652Abstract: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.Type: GrantFiled: September 30, 2011Date of Patent: May 19, 2015Assignee: General Electric CompanyInventors: Steve Mark Molter, Steven Robert Brassfield, Richard William Jendrix, Cory Michael Williams, Renee Solomon Wenstrup, Mark Willard Marusko, Mark Edward Stegemiller
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Publication number: 20130081408Abstract: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.Type: ApplicationFiled: September 30, 2011Publication date: April 4, 2013Inventors: Steve Mark Molter, Steven Robert Brassfield, Richard William Jendrix, Cory Michael Williams, Renee Solomon Wenstrup, Mark Willard Marusko, Mark Edward Stegemiller
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Publication number: 20110229337Abstract: The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using a melt infiltration (MI) process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.Type: ApplicationFiled: June 30, 2010Publication date: September 22, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Douglas Melton Carper, Suresh Subramanian, Richard William Jendrix, James Dale Steibel
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Patent number: 7377746Abstract: An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.Type: GrantFiled: February 21, 2005Date of Patent: May 27, 2008Assignee: General Electric CompanyInventors: Steven Robert Brassfield, Ching-Pang Lee, Roger Lee Doughty, Richard William Jendrix, Cory Michael Williams
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Publication number: 20080080979Abstract: An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.Type: ApplicationFiled: February 21, 2005Publication date: April 3, 2008Applicant: GENERAL ELECTRIC COMPANYInventors: Steven Robert Brassfield, Ching-Pang Lee, Roger Lee Doughty, Richard William Jendrix, Cory Michael Williams
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Patent number: 7341429Abstract: A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.Type: GrantFiled: November 16, 2005Date of Patent: March 11, 2008Assignee: General Electric CompanyInventors: Julius John Montgomery, Robert Proctor, Nathan Gerard Cormier, Christopher Charles Glynn, Glen William Royal, Richard William Jendrix