Patents by Inventor Michael Adelbert Sullivan
Michael Adelbert Sullivan 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: 8935910Abstract: Embodiments of the present disclosure include an oil degradation byproducts removal system. The oil degradation byproducts removal system includes a plurality of electrostatically-charged drum assemblies configured to pass through an oil flow. The oil degradation byproducts removal system is configured to be disposed within an accessory module of a turbine engine system.Type: GrantFiled: October 24, 2011Date of Patent: January 20, 2015Assignee: General Electric CompanyInventors: Mark Andrew Cournoyer, Huong Van Vu, Eric Milton Lafontaine, Bhalchandra Arun Desai, Avnit Singh, Michael Adelbert Sullivan
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Publication number: 20150007720Abstract: A filter assembly and method of operating the filter assembly includes a hinge attached to a first end of a filter while a lifting mechanism is attached to a second end of the filter. The lifting mechanism lifts and releases the second end of the filter causing an impact such that dust and debris caught in the filter is dislodged.Type: ApplicationFiled: July 3, 2013Publication date: January 8, 2015Applicant: BHA Altair, LLCInventors: Huong Van Vu, Michael Adelbert Sullivan, Avnit Singh, Eric Milton Lafontaine
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Patent number: 8894356Abstract: A gas turbine inlet heat exchange coil assembly includes a gas turbine inlet housing formed to include an inlet and an outlet and a flow path therebetween. A plurality of adjacent coils are located in proximity to the inlet, and moveable between a closed operative position where the coils are aligned substantially in a plane so as to maximize resistance to flow along the flow path, and an open inoperative position where said coils are individually rotated substantially 90° such that the coils lie in individual, parallel planes so as to minimize resistance to flow along the flow path.Type: GrantFiled: August 23, 2011Date of Patent: November 25, 2014Assignee: General Electric CompanyInventors: Eric Milton Lafontaine, Michael Adelbert Sullivan, Huong Van Vu, Bhalchandra Arun Desai, Mark Andrew Cournoyer
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Publication number: 20140242714Abstract: A filter element having filter media for filtering air passing therethrough and a detection strip attached thereto comprising a chemical compound that generates a chemical reaction with certain molecules that contact the detection strip.Type: ApplicationFiled: February 22, 2013Publication date: August 28, 2014Applicant: BHA Altair, LLCInventors: Bhalchandra Arun Desai, Huong Van Vu, Michael Adelbert Sullivan
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Patent number: 8465573Abstract: A system for conditioning air flow to a gas turbine includes a filter housing and a conditioning media inside the filter housing to adjust the temperature of the air flowing through the filter housing. At least one of a depth or a density of the conditioning media varies across the filter housing. A method for conditioning air flow to a gas turbine includes flowing air through a filter housing connected to the gas turbine and flowing the air across a conditioning media in the filter housing. The method further includes conditioning the air flow to reduce the temperature difference of the air exiting the filter housing across a dimension of the filter housing.Type: GrantFiled: October 5, 2011Date of Patent: June 18, 2013Assignee: General Electric CompanyInventors: Michael Adelbert Sullivan, Huong Van Vu, Bhalchandra Arun Desai, Eric M. Lafontaine, Mark Andrew Cournoyer
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Publication number: 20130097990Abstract: Embodiments of the present disclosure include an oil degradation byproducts removal system. The oil degradation byproducts removal system includes a plurality of electrostatically-charged drum assemblies configured to pass through an oil flow. The oil degradation byproducts removal system is configured to be disposed within an accessory module of a turbine engine system.Type: ApplicationFiled: October 24, 2011Publication date: April 25, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Andrew Cournoyer, Huong Van Vu, Eric Milton Lafontaine, Bhalchandra Arun Desai, Avnit Singh, Michael Adelbert Sullivan
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Publication number: 20130098767Abstract: Embodiments of the present disclosure include an accessory module for a turbine engine system comprising a lubricating oil reservoir and an oil degradation byproducts removal system. The oil degradation byproducts removal system includes electrostatically-charged collecting plates configured to remove oil degradation byproducts from lubricating oil flowing through the lubricating oil reservoir, wherein the oil degradation byproducts removal system is configured to be disposed internal to the lubricating oil reservoir.Type: ApplicationFiled: October 24, 2011Publication date: April 25, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Andrew Cournoyer, Huong Van Vu, Eric Milton Lafontaine, Bhalchandra Arun Desai, Avnit Singh, Michael Adelbert Sullivan
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Publication number: 20130087045Abstract: A system for conditioning air flow to a gas turbine includes a filter housing and a conditioning media inside the filter housing to adjust the temperature of the air flowing through the filter housing. At least one of a depth or a density of the conditioning media varies across the filter housing. A method for conditioning air flow to a gas turbine includes flowing air through a filter housing connected to the gas turbine and flowing the air across a conditioning media in the filter housing. The method further includes conditioning the air flow to reduce the temperature difference of the air exiting the filter housing across a dimension of the filter housing.Type: ApplicationFiled: October 5, 2011Publication date: April 11, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Michael Adelbert Sullivan, Huong Van Vu, Bhalchandra Arun Desai, Eric M. Lafontaine, Mark Andrew Cournoyer
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Publication number: 20130051994Abstract: A gas turbine inlet heat exchange coil assembly includes a gas turbine inlet housing formed to include an inlet and an outlet and a flow path therebetween. A plurality of adjacent coils are located in proximity to the inlet, and moveable between a closed operative position where the coils are aligned substantially in a plane so as to maximize resistance to flow along the flow path, and an open inoperative position where said coils are individually rotated substantially 90° such that the coils lie in individual, parallel planes so as to minimize resistance to flow along the flow path.Type: ApplicationFiled: August 23, 2011Publication date: February 28, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Eric Milton LAFONTAINE, Michael Adelbert SULLIVAN, Huong Van VU, Bhalchandra Arun DESAI, Mark Andrew COURNOYER
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Publication number: 20130048265Abstract: A chiller coil system for an asymmetric gas turbine filter house includes a plurality of chiller coil modules arranged in a substantially vertical array, each chiller coil module provided with a cooled fluid inlet pipe and a fluid outlet pipe. Each outlet pipe is connected to a common return pipe and at least some of the inlet pipes are connected to the common return pipe. A mixing control valve is provided for controlling an amount of cooling fluid in the common return pipe to be added to at least some of the inlet pipes.Type: ApplicationFiled: August 23, 2011Publication date: February 28, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Bhalchandra Arun DESAI, Michael Adelbert SULLIVAN, Huong Van VU, Eric Milton LAFONTAINE, Mark Andrew COURNOYER
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Patent number: 8057178Abstract: A turbine bucket for a turbomachine includes a main body portion having a base portion and an airfoil portion, the base portion includes a bucket cavity forward region and a shank cavity. The turbine bucket also includes a cooling channel that extends through the main body portion. At least one flow passage extends between one of the cooling channel and the shank cavity, toward the bucket cavity forward region. The at least one flow passage delivers a flow of cooling gas toward the bucket cavity forward region. The flow of cooling gas limits ingestion of hot gases into the bucket cavity forward region.Type: GrantFiled: September 4, 2008Date of Patent: November 15, 2011Assignee: General Electric CompanyInventors: Gary Michael Itzel, Michael Adelbert Sullivan, Yang Liu, Mahesh Madhukar Athavale
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Publication number: 20100054954Abstract: A turbine bucket for a turbomachine includes a main body portion having a base portion and an airfoil portion, the base portion includes a bucket cavity forward region and a shank cavity. The turbine bucket also includes a cooling channel that extends through the main body portion. At least one flow passage extends between one of the cooling channel and the shank cavity, toward the bucket cavity forward region. The at least one flow passage delivers a flow of cooling gas toward the bucket cavity forward region. The flow of cooling gas limits ingestion of hot gases into the bucket cavity forward region.Type: ApplicationFiled: September 4, 2008Publication date: March 4, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Gary Michael Itzel, Michael Adelbert Sullivan, Yang Liu, Mahesh Madhukar Athavale
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Patent number: 7467920Abstract: The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.Type: GrantFiled: January 3, 2007Date of Patent: December 23, 2008Assignee: General Electric CompanyInventors: Michael Adelbert Sullivan, Dale W. Ladoon, Ferruccio Candela, Adam J. Fredmonski
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Publication number: 20080175707Abstract: The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.Type: ApplicationFiled: January 3, 2007Publication date: July 24, 2008Applicant: General Electric CompanyInventors: Michael Adelbert Sullivan, Dale W. Ladoon, Ferruccio Candela, Adam J. Fredmonski