Patents by Inventor Donald Earl Floyd
Donald Earl Floyd 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).
-
Patent number: 10221717Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.Type: GrantFiled: May 25, 2016Date of Patent: March 5, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Maruthi Prasad Manchikanti, Donald Earl Floyd, Wojciech Grzeszczak, Asish Uppath Naraparambath Ramesh
-
Patent number: 10047633Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.Type: GrantFiled: May 14, 2015Date of Patent: August 14, 2018Assignees: General Electric Company, Exxon Mobil Upstream Research CompanyInventors: Maruthi Prasad Manchikanti, Kenneth Damon Black, Donald Earl Floyd, II, Gregory Allan Crum
-
Publication number: 20180010617Abstract: A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.Type: ApplicationFiled: July 11, 2016Publication date: January 11, 2018Inventors: Matthew Stephen Casavant, Kenneth Damon Black, Christian Michael Hansen, Donald Earl Floyd, James Adaickalasamy, Brett Darrick Klingler, Khoa Dang Cao, Kyle Eric Benson, Devin Patrick Perkins, Damian Anthony McClelland
-
Publication number: 20170321569Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.Type: ApplicationFiled: May 25, 2016Publication date: November 9, 2017Inventors: Maruthi Prasad Manchikanti, Donald Earl Floyd, Wojciech Grzeszczak, Asish Uppath Naraparambath Ramesh
-
Patent number: 9587510Abstract: A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold.Type: GrantFiled: July 1, 2014Date of Patent: March 7, 2017Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Eugene Delano White, Douglas Frank Beadie, Anthony Wayne Krull, Donald Earl Floyd, II
-
Patent number: 9458725Abstract: A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.Type: GrantFiled: October 4, 2013Date of Patent: October 4, 2016Assignee: General Electric CompanyInventors: Victor John Morgan, John Wesley Harris, Jr., Michael James Healy, Aaron Ezekiel Smith, Brian Gene Brzek, Donald Earl Floyd, II
-
Publication number: 20160084102Abstract: An abradable seal having a metallic substrate and a multi-layered ceramic coating on the metallic substrate. The multi-layered ceramic coating includes a base layer deposited on the metallic substrate, an abradable layer overlaying the first layer, and an abrading layer overlaying the second layer. The abrading layer is formed of an abrading material. A turbine system and a method for forming an abradable seal are also disclosed.Type: ApplicationFiled: September 18, 2014Publication date: March 24, 2016Inventors: Surinder Singh PABLA, Luc Stephane LEBLANC, Donald Earl FLOYD
-
Patent number: 9249667Abstract: A system includes a turbomachine that includes a stator and a rotor. The rotor is configured to rotate about a rotational axis relative to the stator. In addition, the rotor includes a least one rotary blade, and the at least one rotary blade has a patterned structure of beams and cavities.Type: GrantFiled: March 15, 2012Date of Patent: February 2, 2016Assignee: General Electric CompanyInventors: Patrick Daniel Noble, Joseph Anthony Weber, Donald Earl Floyd, II
-
Publication number: 20150330252Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.Type: ApplicationFiled: May 14, 2015Publication date: November 19, 2015Inventors: Maruthi Prasad Manchikanti, Kenneth Damon Black, Donald Earl Floyd, II, Gregory Allan Crum
-
Patent number: 9175571Abstract: A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component.Type: GrantFiled: March 19, 2012Date of Patent: November 3, 2015Assignee: General Electric CompanyInventor: Donald Earl Floyd
-
Patent number: 9121301Abstract: A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.Type: GrantFiled: March 20, 2012Date of Patent: September 1, 2015Assignee: General Electric CompanyInventors: Donald Earl Floyd, David Martin Johnson
-
Publication number: 20150096305Abstract: A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.Type: ApplicationFiled: October 4, 2013Publication date: April 9, 2015Applicant: General Electric CompanyInventors: Victor John Morgan, John Wesley Harris, Jr., Michael James Healy, Aaron Ezekiel Smith, Brian Gene Brzek, Donald Earl Floyd, II
-
Publication number: 20150033757Abstract: A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold.Type: ApplicationFiled: July 1, 2014Publication date: February 5, 2015Inventors: Eugene Delano White, Douglas Frank Beadie, Anthony Wayne Krull, Donald Earl Floyd, II
-
Publication number: 20140271154Abstract: A turbine inner shell for a turbine engine includes one or more mounting grooves, each of which receives a fluid conduit. A temperature controlling fluid is circulated through fluid conduit to selectively heat or cool surrounding portions of the turbine inner shell, to thereby control the thermal growth of those portions of the turbine inner shell. This makes it possible to selectively control a clearance between the tips of rotating turbine blades and the surrounding shrouds of the turbine.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Donald Earl FLOYD, Kenneth Black
-
Publication number: 20140070058Abstract: A tube holder for use in turbomachinery includes a housing having a passage for receiving a tube, the housing adapted for attachment to a turbomachinery component; and a metal foam component located within the housing and arranged to engage a length portion of the tube to thereby hold the tube within the housing and reduce undesirable vibrations in the tube during operation of the turbomachinery.Type: ApplicationFiled: September 10, 2012Publication date: March 13, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Bradley James MILLER, Donald Earl FLOYD, II
-
Publication number: 20130251515Abstract: A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.Type: ApplicationFiled: March 20, 2012Publication date: September 26, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Donald Earl Floyd, David Martin Johnson
-
Publication number: 20130243600Abstract: A system includes a turbomachine that includes a stator and a rotor. The rotor is configured to rotate about a rotational axis relative to the stator. In addition, the rotor includes a least one rotary blade, and the at least one rotary blade has a patterned structure of beams and cavities.Type: ApplicationFiled: March 15, 2012Publication date: September 19, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Patrick Daniel Noble, Joseph Anthony Weber, Donald Earl Floyd, II
-
Publication number: 20130243601Abstract: A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component.Type: ApplicationFiled: March 19, 2012Publication date: September 19, 2013Applicant: GENERAL ELECTRIC COMPANYInventor: Donald Earl FLOYD
-
Publication number: 20130202420Abstract: A turbine shell is provided, and includes a body portion and at least one plate. The body portion has a forward portion and an aft portion. The plate is located between the forward portion and the aft portion. The plate is part of a plate frame heat exchanger, which is part of the body portion of the turbine shell.Type: ApplicationFiled: February 7, 2012Publication date: August 8, 2013Applicant: GENERAL ELECTRIC COMPANYInventor: Donald Earl Floyd
-
Publication number: 20120009058Abstract: A system is provided that includes a first turbine alignment component for a turbine engine; and a shim comprises a metal foam. The shim mounts between a first surface of the first turbine alignment component and a second surface of a second turbine alignment component.Type: ApplicationFiled: July 9, 2010Publication date: January 12, 2012Applicant: General Electric CompanyInventors: Donald Earl Floyd, II, Kenneth Damon Black