Patents by Inventor Keith Santeler
Keith Santeler 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: 8935926Abstract: An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.Type: GrantFiled: October 28, 2010Date of Patent: January 20, 2015Assignee: United Technologies CorporationInventors: Joel H. Wagner, Shankar S. Magge, Keith A. Santeler
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Patent number: 8439639Abstract: A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.Type: GrantFiled: February 24, 2008Date of Patent: May 14, 2013Assignee: United Technologies CorporationInventors: Christopher R. Joe, Eric A. Hudson, Keith A. Santeler
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Publication number: 20120102969Abstract: An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.Type: ApplicationFiled: October 28, 2010Publication date: May 3, 2012Inventors: Joel H. Wagner, Shankar S. Magge, Keith A. Santeler
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Publication number: 20110315336Abstract: A method for manufacturing an investment casting core uses a metallic blank having a thickness between parallel first and second faces less than a width and length transverse thereto. The blank is locally thinned from at least one of the first and second faces. The local thinning forms a taper on a leading portion of the RMC. The blank is through-cut across the thickness. The blank is inserted into the leading portion into a slot in a pre-formed ceramic core.Type: ApplicationFiled: June 25, 2010Publication date: December 29, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel A. Snyder, Keith A. Santeler, Amanda J. Learned
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Patent number: 7607890Abstract: A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a flow of coolant into the cooling microcircuit, a plurality of fluid exit slots for distributing a film of the coolant over the airfoil portion, and structures for substantially preventing one jet of the coolant exiting through one of the fluid exit slots from overpowering a second jet of the coolant exiting through the one fluid exit slot.Type: GrantFiled: June 7, 2006Date of Patent: October 27, 2009Assignee: United Technologies CorporationInventors: Francisco J. Cunha, Keith A. Santeler
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Publication number: 20090214329Abstract: A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.Type: ApplicationFiled: February 24, 2008Publication date: August 27, 2009Inventors: Christopher R. Joe, Eric A. Hudson, Keith A. Santeler
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Patent number: 7575039Abstract: A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.Type: GrantFiled: October 15, 2003Date of Patent: August 18, 2009Assignee: United Technologies CorporationInventors: James T. Beals, Joshua Persky, Dilip M. Shah, Venkat Seetharaman, Sudhangshu Bose, Jacob Snyder, Keith Santeler, Carl Verner, Stephen D. Murray, John Marcin, Dinesh Gupta, Daniel A. Bales, Daniel Francis Paulonis, Glenn Cotnoir, John Wiedemer
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Publication number: 20090114797Abstract: A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.Type: ApplicationFiled: October 15, 2003Publication date: May 7, 2009Inventors: James T. Beals, Joshua Persky, Dilip M. Shah, Venkat Seetharaman, Sudhangshu Bose, Jacob Snyder, Keith Santeler, Carl Verner, Stephen D. Murray, John J. Marcin, Dinesh Gupta, Daniel A. Bales, Daniel Francis Paulonis, Glenn Cotnoir, John Wiedemer
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Patent number: 7438118Abstract: At least one feedcore and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.Type: GrantFiled: July 31, 2007Date of Patent: October 21, 2008Assignee: United Technologies CorporationInventor: Keith A. Santeler
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Publication number: 20080060781Abstract: At least one feedcore and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.Type: ApplicationFiled: July 31, 2007Publication date: March 13, 2008Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Keith Santeler
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Publication number: 20070286735Abstract: A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a flow of coolant into the cooling microcircuit, a plurality of fluid exit slots for distributing a film of the coolant over the airfoil portion, and structures for substantially preventing one jet of the coolant exiting through one of the fluid exit slots from overpowering a second jet of the coolant exiting through the one fluid exit slot.Type: ApplicationFiled: June 7, 2006Publication date: December 13, 2007Inventors: Francisco J. Cunha, Keith A. Santeler
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Patent number: 7270170Abstract: A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.Type: GrantFiled: August 26, 2004Date of Patent: September 18, 2007Assignee: United Technologies CorporationInventors: James T. Beals, Samuel D. Draper, Jose A. Lopes, Stephen D. Murray, Brandon W. Spangler, Michael K. Turkington, Bryan P. Dube, Keith A. Santeler, Jacob A. Snyder
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Patent number: 7270173Abstract: A composite core for an investment casting process, the core including both a ceramic portion and a refractory metal portion, with the refractory metal portion being so disposed as to perform the function of a plurality of such refractory metal elements. In particular, a refractory metal element attached to a trailing edge of a ceramic element extends beyond the plane of a tip end of the ceramic element so as to replace the refractory metal element otherwise extending from the ceramic tip edge. The refractory metal element also extends beyond the space to be occupied by the wax casting, both in the direction of the tip end and the trailing edge such that improved placement and securing of the core is facilitated during the casting process. A further embodiment uses a single refractory metal element that extends into both the airfoil portion and an orthogonal extending platform portion thereof.Type: GrantFiled: September 18, 2006Date of Patent: September 18, 2007Assignee: United Technologies CorporationInventors: John D. Wiedemer, Keith A. Santeler
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Patent number: 7258156Abstract: At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.Type: GrantFiled: September 19, 2006Date of Patent: August 21, 2007Assignee: United Technologies CorporationInventor: Keith A. Santeler
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Patent number: 7255536Abstract: An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.Type: GrantFiled: May 23, 2005Date of Patent: August 14, 2007Assignee: United Technologies CorporationInventors: Frank J. Cunha, Eric Couch, Keith A. Santeler, Scott W. Gayman, Eric A. Hudson, Christopher Joe, Eric Letizia
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Publication number: 20070144702Abstract: A composite core for an investment casting process, the core including both a ceramic portion and a refractory metal portion, with the refractory metal portion being so disposed as to perform the function of a plurality of such refractory metal elements. In particular, a refractory metal element attached to a trailing edge of a ceramic element extends beyond the plane of a tip end of the ceramic element so as to replace the refractory metal element otherwise extending from the ceramic tip edge. The refractory metal element also extends beyond the space to be occupied by the wax casting, both in the direction of the tip end and the trailing edge such that improved placement and securing of the core is facilitated during the casting process. A further embodiment uses a single refractory metal element that extends into both the airfoil portion and an orthogonal extending platform portion thereof.Type: ApplicationFiled: September 18, 2006Publication date: June 28, 2007Applicant: United Technologies CorporationInventors: John Wiedemer, Keith Santeler
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Publication number: 20070089850Abstract: A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.Type: ApplicationFiled: August 26, 2004Publication date: April 26, 2007Inventors: James Beals, Samuel Draper, Jose Lopes, Stephen Murray, Brandon Spangler, Michael Turkington, Bryan Dube, Keith Santeler, Jacob Snyder
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Patent number: 7185695Abstract: At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.Type: GrantFiled: September 1, 2005Date of Patent: March 6, 2007Assignee: United Technologies CorporationInventor: Keith A. Santeler
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Publication number: 20070044933Abstract: At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.Type: ApplicationFiled: September 1, 2005Publication date: March 1, 2007Inventor: Keith Santeler
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Publication number: 20070044934Abstract: At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.Type: ApplicationFiled: September 19, 2006Publication date: March 1, 2007Inventor: Keith Santeler