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| Number | Title | Issue Date |
| 8171737 | Combustor assembly and cap for a turbine engine A combustor assembly for a turbine engine includes a cap assembly which gradually increases the volume of compressed air provided to the combustor assembly, and which slows the compressed air in a controlled manner before delivering the compressed air into a combust... | 05/08/2012 |
| 7870739 | Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions A curved diffuser (210) in a gas turbine engine (201) directs a primary portion of air flow from a compressor (202) through a curved discharge opening (213) into a plenum (220). The curved diffuser (210) also comprises ports... | 01/18/2011 |
| 7805946 | Combustor flow sleeve attachment system Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sl... | 10/05/2010 |
| 7685823 | Airflow distribution to a low emissions combustor An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustio... | 03/30/2010 |
| 7350358 | Exit duct of annular reverse flow combustor and method of making the same A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbi... | 04/01/2008 |
| 7350360 | Annular combustor for a gas turbine The invention relates to an annular combustor (13) for a gas turbine (10), into which combustor (13) burners (14, 15) open on an inlet side, and which combustor (13) extends in the axial direction from the inlet side to an outlet s... | 04/01/2008 |
| 7302802 | Aerodynamic trip for a combustion system A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the s... | 12/04/2007 |
| 7269958 | Combustor exit duct A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions. ... | 09/18/2007 |
| 7260935 | Method and apparatus for reducing gas turbine engine emissions A low emission turbine includes a reverse flow can-type combustor that generally includes a primary and secondary fuel delivery system that can be independently controlled to produce low CO, UHC, and NOx emissions at design set point and at conditions other than des... | 08/28/2007 |
| 7237384 | Counter swirl shear mixer The present invention provides a mixer for a gas turbine combustor comprising a plurality of generally annular walls interconnected by at least a plurality of first vanes. The vanes are oriented at angles, so as to create a shear layer between the two flows. A fuel ... | 07/03/2007 |
| 7137241 | Transition duct apparatus having reduced pressure loss A gas turbine transition duct having a reduced pressure loss is disclosed. The transition duct of the preferred embodiment comprises a panel assembly having a first panel fixed to a second panel and a mounting assembly for securing the transition duct to a turbine i... | 11/21/2006 |
| 7089748 | Combustion chamber, in particular of a gas turbine The invention relates to a combustion chamber, in particular of a gas turbine, comprising an external wall structure that surrounds an internal area and an internal wall, which is formed by the surface of a housing that is located in the internal area. Said combusti... | 08/15/2006 |
| 7080515 | Gas turbine can annular combustor A gas turbine engine (120) includes a cylindrical basket (146) having an axis (14) and a single main burner assembly (12) disposed within the basket. A burner insert (34) is disposed in an annular space between the burner assembly ... | 07/25/2006 |
| 7043921 | Tube cooled combustor An innovative cooling tube assembly is disclosed for use in cooling the liner of a combustor in a gas turbine engine. Each cooling tube has a serpentine shape that conforms to the contour of the liner as the tube extends from one end of the combustor to the other to... | 05/16/2006 |
| 7010921 | Method and apparatus for cooling combustor liner and transition piece of a gas turbine A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an... | 03/14/2006 |
| 7007480 | Multi-axial pivoting combustor liner in gas turbine engine A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and r... | 03/07/2006 |
| 7007475 | Conical helical of spiral combustor scroll device in gas turbine engine A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift re... | 03/07/2006 |
| 7003960 | Method and appliance for supplying fuel to a premixing burner A method and an appliance are described for supplying fuel to a premixing burner for operating a gas turbine, which premixing burner has at least one burner shell (1, 2) at least partially bounding an axially extending premixing burner space, having a premixi... | 02/28/2006 |
| 6973419 | Method and system for designing an impingement film floatwall panel system A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of d... | 12/06/2005 |
| 6957538 | Combustion chamber for a gas turbine The invention relates to a combustion chamber for a gas turbine having at least one closed-circuit-cooled burner insert which can be disposed in an inlet opening of the combustion chamber for the purpose of feeding and/or igniting a combustible gas/air mixture, and ... | 10/25/2005 |
| 6951109 | Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly Variations in dilution air leakage paths in a gas turbine combustion liner assembly are minimized or eliminated to reduce emissions and variations in emissions from combustor to combustor. Leakage paths between the liner sleeve and venturi outer liner are minimized ... | 10/04/2005 |
| 6935116 | Flamesheet combustor A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, a... | 08/30/2005 |
| 6923642 | Premixed prevaporized combustor The present invention is an improved a combustor incorporating a pre-mix/pre-evaporation chamber arranged and configured to produce both a cool portion and a hot portion that cooperate to vaporize a liquid fuel to produce a lean to low-rich combustion mixture that i... | 08/02/2005 |
| 6837053 | Gas turbine combustion chamber and air guidance method therefore In order to provide a method of air guidance and a design for a gas turbine combustion chamber which permits improved cooling and reduced pressure losses and which avoids the overcooling phenomena by specific reaction to hot spots, a gas turbine combustion chamber i... | 01/04/2005 |
| 6826912 | Design of adiabatic combustors An adiabatic combustor for a gas turbine including: (a) a combustion chamber designed and configured to produce high-pressure combustion gases for the turbine, the combustion chamber having a primary combustion zone containing a substantially vitiated-air zone; (b) ... | 12/07/2004 |
| 6772595 | Advanced cooling configuration for a low emissions combustor venturi A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said coolin... | 08/10/2004 |
| 6691503 | Gas turbine having first and second combustion chambers and cooling system A gas turbine (5) according to the invention, which comprises a main combustion chamber (10), a cooling system for air cooling of at least the guide vanes (26, 29) and guide rings (28, 38) of various stages (25, 27) of the gas turbine (5), and a main gas ... | 02/17/2004 |
| 6634175 | Gas turbine and gas turbine combustor A gas turbine combustor has homogenous air inflow by elimination of turbulence from the air, reducing combustion instability. A combustor 3 has, at its center, a pilot nozzle 8 and eight main nozzles 7 around the pilot nozzle 8. The air flows in around th... | 10/21/2003 |
| 6615588 | Arrangement for using a plate shaped element with through-openings for cooling a component The present invention relates to an arrangement for the cooling of a component, in particular of the combustion chamber of a turbo machine, wherein at least one cooling duct (5) is provided between a wall (1) to be cooled and a plate-shaped element (2) sp... | 09/09/2003 |
| 6609376 | Device in a burner for gas turbines Device in a burner for gas turbines, comprising a cylindrical housing (10) and a fuel inlet tube (16) arranged centrally within said housing, said housing (10) and fuel inlet tube (16) mutually defining an annular chamber (28). The annular chamber (28) ex... | 08/26/2003 |
| 6594999 | Combustor, a gas turbine, and a jet engine A combustor can simultaneously reduce the amount of NOx exhaust and combustion oscillation. The combustor has an internal cylinder which accommodates a premixing nozzle and an external cylinder which accommodates the internal cylinder, and includes an air... | 07/22/2003 |
| 6568188 | Bypass air injection method and apparatus for gas turbines A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through th... | 05/27/2003 |
| 6553766 | Cooling structure of a combustor tail tube A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets (5) extend in t... | 04/29/2003 |
| 6494044 | Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method A transition piece assembly for a gas turbine includes a transition duct having one end adapted for connection to a gas turbine combustor and an opposite end adapted for connection to a first turbine stage, and a pair of side panels. The assembly also inc... | 12/17/2002 |
| 6484505 | Combustor liner cooling thimbles and related method A combustor for a turbine includes a combustor liner; a first flow sleeve surrounding the liner, the flow sleeve having a plurality of rows of cooling holes formed about a circumference of the flow sleeve; and a transition piece connected to the combustor... | 11/26/2002 |
| 6449956 | Bypass air injection method and apparatus for gas turbines A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through th... | 09/17/2002 |
| 6446438 | Combustion chamber/venturi cooling for a low NOx emission combustor A method and apparatus for providing air cooling to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes providing an annular air passage surrounding said combustion chamber and venturi where... | 09/10/2002 |
| 6438959 | Combustion cap with integral air diffuser and related method A combustion cap assembly for closing a forward end of a combustion chamber includes a radially inner substantially cylindrical component; a radially outer substantially conical component, extending substantially along an entire length dimension of the ra... | 08/27/2002 |
| 6430933 | Oscillation attenuation in combustors The devices and methods according to the invention are used to attenuate acoustic and/or thermoacoustic oscillations in a combustor. The combustor may be, in most cases, constructed as a premixing combustor with low emissions of noxious substances and inc... | 08/13/2002 |
| 6430932 | Low NOx combustion liner with cooling air plenum recesses A combustion liner assembly for reducing nitric oxide (NOx) emissions is disclosed. This combustion liner utilizes an annular plenum outside the liner shell for the purpose of containing cooling air that has been heated and reintroducing it into the combu... | 08/13/2002 |
