Patents by Inventor Marwan Al-Roub
Marwan Al-Roub 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: 7654091Abstract: A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid channel therebetween. The flare cone has a plurality of cooling injectors extending therethrough. The plurality of injectors are spaced circumferentially about a centerline axis of the flare cone and are coupled in flow communication with the fluid source. The plurality of injectors has a plurality of first injectors and a plurality of second injectors. The method also includes directing a portion of the fluid through the plurality of first injectors. The method further includes directing a portion of the fluid through the plurality of second injectors, wherein the first plurality of injectors facilitates cooling a portion of the deflector more than the second plurality of injectors.Type: GrantFiled: August 30, 2006Date of Patent: February 2, 2010Assignee: General Electric CompanyInventors: Marwan Al-Roub, Steven Vise
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Publication number: 20080053102Abstract: A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid channel therebetween. The flare cone has a plurality of cooling injectors extending therethrough. The plurality of injectors are spaced circumferentially about a centerline axis of the flare cone and are coupled in flow communication with the fluid source. The plurality of injectors has a plurality of first injectors and a plurality of second injectors. The method also includes directing a portion of the fluid through the plurality of first injectors. The method further includes directing a portion of the fluid through the plurality of second injectors, wherein the first plurality of injectors facilitates cooling a portion of the deflector more than the second plurality of injectors.Type: ApplicationFiled: August 30, 2006Publication date: March 6, 2008Inventors: Marwan Al-Roub, Steven Vise
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Patent number: 7104066Abstract: A unitary swirler assembly that provides improved service life, having a ferrule body and a unitary swirler body. The unitary swirler body has oppositely-directed primary swirler passages and secondary swirler passages. A pair of rails formed on the unitary swirler body engage the ferrule body to limit relative movement, and prevent relative rotation, of the ferrule body and the unitary swirler body.Type: GrantFiled: August 19, 2003Date of Patent: September 12, 2006Assignee: General Electric CompanyInventors: Thomas Anthony Leen, Marwan Al-Roub, John Robert Staker
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Publication number: 20050039458Abstract: Aunitary swirler assembly that provides improved service life, having a ferrule body and a unitary swirler body. The unitary swirler body has oppositely-directed primary swirler passages and secondary swirler passages. A pair of rails formed on the unitary swirler body engage the ferrule body to limit relative movement, and prevent relative rotation, of the ferrule body and the unitary swirler body.Type: ApplicationFiled: August 19, 2003Publication date: February 24, 2005Applicant: GENERAL ELECTRIC COMPANYInventors: Thomas Leen, Marwan Al-Roub, John Staker
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Patent number: 6834505Abstract: A swirler includes a tubular body having a row of secondary radial swirl vanes. A tubular ferrule adjoins the body at the secondary vanes, and includes a row of primary swirl vanes. The primary vanes are disposed axially obliquely to the secondary vanes, with a common annular inlet facing radially outwardly for swirling air radially inwardly therefrom with axial momentum into the tubular body.Type: GrantFiled: October 7, 2002Date of Patent: December 28, 2004Assignee: General Electric CompanyInventors: Marwan Al-Roub, Stanford P. Seto, John Robert Staker, Ting-Yu Tu
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Publication number: 20040065090Abstract: A swirler includes a tubular body having a row of secondary radial swirl vanes. A tubular ferrule adjoins the body at the secondary vanes, and includes a row of primary swirl vanes. The primary vanes are disposed axially obliquely to the secondary vanes, with a common annular inlet facing radially outwardly for swirling air radially inwardly therefrom with axial momentum into the tubular body.Type: ApplicationFiled: October 7, 2002Publication date: April 8, 2004Inventors: Marwan Al-Roub, Stanford P. Seto, John Robert Staker, Ting-Yu Tu
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Patent number: 6655146Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.Type: GrantFiled: July 31, 2001Date of Patent: December 2, 2003Assignee: General Electric CompanyInventors: Ella Christine Kutter, Marwan Al-Roub, Thomas Anthony Leen, Daniel Dale Brown, Craig Douglas Young, Gilbert Farmer, Mohammad Ehteshami
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Patent number: 6651439Abstract: A combustor for a gas turbine engine that facilitates reducing combustor chamber dump pressure losses to improve combustor and engine performance is described. The combustor includes a diffuser that diffuses airflow directed into the combustor. The diffuser includes an outer wall, an inner wall, and a plurality of splitter vanes between the outer wall and the inner wall. The splitter vanes are spaced radially apart, and each is spaced radially from a respective diffuser wall such that an outer passage, an inner passage, and a central passage are defined by the splitter vanes.Type: GrantFiled: January 12, 2001Date of Patent: November 25, 2003Assignee: General Electric Co.Inventors: Marwan Al-Roub, Clifford Stephen Creevy, Hubert Smith Roberts, Jr., Anthony Paul Greenwood
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Patent number: 6557350Abstract: A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.Type: GrantFiled: May 17, 2001Date of Patent: May 6, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, Ella Christine Kutter, Steven Clayton Vise, John Robert Staker, Marwan Al-Roub, Tariq Kay Harris
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Publication number: 20030027093Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.Type: ApplicationFiled: July 31, 2001Publication date: February 6, 2003Inventors: Ella Christine Kutter, Marwan Al-Roub, Thomas Anthony Leen, Daniel Dale Brown, Craig Douglas Young, Gilbert Farmer, Mohammad Ehteshami
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Publication number: 20020170293Abstract: A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.Type: ApplicationFiled: May 17, 2001Publication date: November 21, 2002Inventors: Gilbert Farmer, Ella Christine Kutter, Steven Clayton Vise, John Robert Staker, Marwan Al-Roub, Tariq Kay Harris
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Publication number: 20020092303Abstract: A combustor for a gas turbine engine that facilitates reducing combustor chamber dump pressure losses to improve combustor and engine performance is described. The combustor includes a diffuser that diffuses airflow directed into the combustor. The diffuser includes an outer wall, an inner wall, and a plurality of splitter vanes between the outer wall and the inner wall. The splitter vanes are spaced radially apart, and each is spaced radially from a respective diffuser wall such that an outer passage, an inner passage, and a central passage are defined by the splitter vanes.Type: ApplicationFiled: January 12, 2001Publication date: July 18, 2002Inventors: Marwan Al-Roub, Clifford Stephen Creevy, Hubert Smith Roberts, Anthony Paul Greenwood
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Patent number: 6205763Abstract: A method for determining the appropriate hole parameters to achieve the desired airflow in a swirler with as-cast air jet holes includes the steps of determining the desired airflow through the holes and selecting a hole angle for the holes. Next, the ratio of the hole exit area to the hole inlet area is calculated based on the desired airflow and the selected hole angle using a regression equation. Then a value is determined for either of the hole exit area or the hole inlet area, and the other area is calculated from the known ratio. Once the hole angle, hole exit area and hole inlet area have been determined, then a swirler can be cast with as-cast holes using these hole parameters.Type: GrantFiled: May 24, 1999Date of Patent: March 27, 2001Assignee: General Electric CompanyInventors: Gilbert Farmer, James A. Groeschen, Jason P. Hoppa, Stanford P. Seto, Marwan Al-Roub