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| Number | Title | Issue Date |
| 8096134 | Combustion chamber comprising chamber end wall heat shielding deflectors and gas turbine engine equipped therewith An annular combustion chamber for a gas turbine engine is disclosed. The combustion chamber includes an external wall, an internal wall, a chamber end wall connecting these two walls and provided with openings for the fuel injection systems, and heat shielding defle... | 01/17/2012 |
| 8091368 | Turbomachine combustion chamber A turbomachine combustion chamber including a chamber bottom with at least one opening designed to receive a combustion bowl in the axis of which an air and fuel injection device is mounted is disclosed. The downstream end of the flared bowl includes a divergent wit... | 01/10/2012 |
| 8037691 | Deflector for a combustion chamber endwall, combustion chamber equipped therewith and turbine engine comprising them A deflector takes the form of a plate provided with a hole. The plate is a portion of a conical surface of revolution about a cone axis with a concave face and a convex face. The plate includes a contour with four sides. Two of these the sides are concentric circula... | 10/18/2011 |
| 8006498 | Combustion chamber of a combustion system A combustion chamber of a combustion system comprises a combustion space, a support structure, a heat shield, and at least one through-opening. The heat shield has at least two segments, and each segment has an edge region, a gap communicating with the combustion sp... | 08/30/2011 |
| 7992391 | Transverse wall of a combustion chamber provided with multi-perforation holes An annular wall which transversely connects longitudinal walls of an annular combustion chamber of a turbine engine is disclosed. The wall is essentially flat, inclined in relation to a longitudinal axis of the turbine engine, and includes a plurality of deflectors,... | 08/09/2011 |
| 7954327 | Chamber endwall, method of producing it, combustion chamber comprising it, and turbine engine equipped therewith A combustion chamber which includes a chamber endwall which takes the form of a substantially frustoconical component including a succession of adjacent planar portions is disclosed. The invention can be applied to a combustion chamber of a turbine engine. ... | 06/07/2011 |
| 7849694 | Heat shield arrangement for a component guiding a hot gas in particular for a combustion chamber in a gas turbine The invention relates to a heat shield arrangement for a hot gas (m)-guiding component, which comprises a number of heat shield elements arranged side-by-side on a supporting structure while leaving a gap there between. A heat shield element can be mounted on the su... | 12/14/2010 |
| 7845174 | Combustor liner with improved heat shield retention A combustor liner including a dome section having a positioning hole defined at a first radial distance and sized to receive a first heat shield fastener to at least substantially prevent radial and circumferential motion of the first fastener, a circumferential slo... | 12/07/2010 |
| 7788929 | Combustion chamber end wall with ventilation A combustion chamber having a chamber end wall that presents a plurality of air and fuel injector devices, each of the devices including a bowl and a deflector mounted on a main axis forming a heat shield disposed around the bowl which flares in the gas flow directi... | 09/07/2010 |
| 7631503 | Combustor with enhanced cooling access A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openi... | 12/15/2009 |
| 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 |
| 7325402 | Pilot nozzle heat shield having connected tangs A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the ... | 02/05/2008 |
| 7308794 | Combustor and method of improving manufacturing accuracy thereof An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor... | 12/18/2007 |
| 7260936 | Combustor having means for directing air into the combustion chamber in a spiral pattern A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral patter... | 08/28/2007 |
| 7219498 | Waffled impingement effusion method A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal s... | 05/22/2007 |
| 7175422 | Method for accelerated aging of catalytic converters incorporating injection of volatilized lubricant A method and apparatus for accelerated aging of an automotive catalytic converter under conditions incorporating volatilized oil consumption. ... | 02/13/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7140874 | Method and apparatus for testing catalytic converter durability The present application relates in general to an apparatus and to methods for testing the performance of an automotive catalytic converter under conditions simulating those which occur in motor vehicles over extended driving conditions. The application provides a no... | 11/28/2006 |
| 7140185 | Heatshielded article A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated co... | 11/28/2006 |
| 7134286 | Gas turbine floating collar arrangement A simplified floating collar mounting arrangement for receiving a fuel nozzle swirler body of a gas turbine engine combustor is provided. The assembly comprises a floating collar mounted between a spaced-apart mounting flange and cap, and slidably trapped therebetwe... | 11/14/2006 |
| 7124588 | Combustion chamber of gas turbine with starter film cooling A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumfere... | 10/24/2006 |
| 7124487 | Method for controlling carbon formation on repaired combustor liners A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion o... | 10/24/2006 |
| 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 |
| 7051532 | Methods and apparatus for film cooling gas turbine engine combustors A method facilitates assembling a combustor for a gas turbine engine. The method includes providing a dome assembly that includes at least one cooling slot lip and at least one filler projection, wherein a gap defined between the cooling slot lip and the at least on... | 05/30/2006 |
| 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 |
| 7013647 | Outer casing covering gas turbine combustor A combustor structure of a gas turbine, in which a sheet-like vibration damper, which resonates with the air vibration in the intake chamber and absorbs the energy of the air vibration, is attached to the inner wall of the casing by an attaching member via a space. | 03/21/2006 |
| 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 |
| 6978618 | Bulkhead panel for use in a combustion chamber of a gas turbine engine The invention relates to a bulkhead panel for use in a combustion chamber of a gas turbine engine. The bulkhead panel comprises a first side and a second side, a plurality of panel holes extending from the first side to the second side through which cooling air flow... | 12/27/2005 |
| 6976363 | Combustor dome assembly of a gas turbine engine having a contoured swirler A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed ... | 12/20/2005 |
| 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 |
| 6945051 | Low NOx emission diffusion flame combustor for gas turbines A diffusion flame combustor for a gas turbine comprising a flame tube that delimits a combustion chamber, the flame tube having a fuel injector unit mounted at one end, the other end of the tube being connected to a duct that conveys combustion gases to the turbine.... | 09/20/2005 |
| 6931728 | Test model for a gas turbine combustor dome and method of fabricating A method of fabricating a test model of a gas turbine engine combustor dome, and the test model produced thereby. The method entails individually stamping a plurality of dome wall segments and first and second mounting band segments. Each wall segment comprises at l... | 08/23/2005 |
| 6886341 | Gas-turbine engine combustor A gas-turbine engine combustor having a plurality of venturi mixers, each connected to an air supply path that passes air compressed by a compressor and to a supply source of gaseous fuel, which mix the air and the gaseous fuel to produce an air-fuel mixture and sup... | 05/03/2005 |
| 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 |
| 6810672 | Gas turbine combustor, particularly for an aircraft engine A gas turbine combustor, in particular for an aircraft engine, has at least one chamber, through which combustion gas flows in use, and which is defined by a lateral wall with channeling for feeding cooling air into the chamber and cooling the lateral wall; part of ... | 11/02/2004 |
| 6761031 | Double wall combustor liner segment with enhanced cooling A connector segment for connecting a combustor liner and a transition piece in a gas turbine has a substantially cylindrical shape and is of double-walled construction including inner and outer walls and a plurality of cooling channels extending axially along the se... | 07/13/2004 |
| 6751961 | Bulkhead panel for use in a combustion chamber of a gas turbine engine The invention relates to a bulkhead panel for use in a combustion chamber of a gas turbine engine. The bulkhead panel comprises a first side and a second side, a plurality of panel holes extending from the first side to the second side through which cooling air flow... | 06/22/2004 |
| 6745571 | Method of combustor cycle airflow adjustment A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to inc... | 06/08/2004 |
| 6735950 | Combustor dome plate and method of making the same A method of making a dome plate for a gas turbine engine combustor includes forming an annular body and forming a plurality of swirler openings in the annular body. Then, an array of impingement cooling holes and an array of blow-off holes are electrically discharge... | 05/18/2004 |
