Patents Examined by Gerald Luther Sung
-
Patent number: 10197284Abstract: A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.Type: GrantFiled: December 19, 2014Date of Patent: February 5, 2019Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Shinji Akamatsu, Hiroaki Kishida, Kenji Sato, Kentaro Tokuyama, Keisuke Matsuyama, Takayoshi Takashima
-
Patent number: 10151487Abstract: The invention refers to a sequential combustor arrangement including a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, and a second burner for admixing a second fuel and a second combustion chamber. To assure good mixing over a wide operating range, the ratio of the pressure loss of the first combustor to the pressure loss of the dilution gas admixer is in the range of 1 to 6. The invention further refers to a gas turbine including such a sequential combustor arrangement as well as method for operating a gas turbine with such a sequential combustor arrangement.Type: GrantFiled: January 9, 2015Date of Patent: December 11, 2018Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Michael Duesing, Ewald Freitag
-
Patent number: 9982890Abstract: A combustor heat shield has lips with fins distributed on the lips. The lip-fins have an extended end portion projecting rearwardly from the back face of the heat shield. Impingement jets may be directed against the rearwardly extended end portions of the lip-fins to enhance cooling. The heat shield may define a fuel nozzle opening surrounded by a rail on the back side of the heat shield. Impingement holes or slots may be defined in the rail for allowing cooling air passing therethrough to impinge upon the lip-fins.Type: GrantFiled: November 20, 2013Date of Patent: May 29, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Papple, Robert Sze, Sri Sreekanth
-
Patent number: 8869536Abstract: A liner stop for retaining a flow sleeve relative to a combustion liner in a combustor is disclosed. The liner stop includes a female component defining a recess and a male component comprising a protrusion, the protrusion insertable in the female component. The liner stop further includes an insert disposable between the female component and the male component, the insert comprising a surface protrusion configured to interfere with one of the female component or the male component.Type: GrantFiled: July 26, 2012Date of Patent: October 28, 2014Assignee: General Electric CompanyInventors: Robert Wade Clifford, Jonathan Hale Kegley
-
Patent number: 8555649Abstract: A fuel nozzle air swirler assembly has a slotted cap to provide stress-relief. The stress-relief slits in the cap have an axial and a tangential component to impart a swirl to the air leaking therethrough in the same direction as that of the air exiting the swirler body.Type: GrantFiled: September 2, 2009Date of Patent: October 15, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
-
Patent number: 8499566Abstract: A combustor liner is disclosed. The combustor liner includes an upstream portion, a downstream end portion extending from the upstream portion along a generally longitudinal axis, and a cover layer associated with an inner surface of the downstream end portion. The downstream end portion includes the inner surface and an outer surface, the inner surface defining a plurality of microchannels. The downstream end portion further defines a plurality of passages extending between the inner surface and the outer surface. The plurality of microchannels are fluidly connected to the plurality of passages, and are configured to flow a cooling medium therethrough, cooling the combustor liner.Type: GrantFiled: August 12, 2010Date of Patent: August 6, 2013Assignee: General Electric CompanyInventors: Benjamin Paul Lacy, Mert Enis Berkman