Patent application number | Description | Published |
20080282703 | INTERFACE BETWEEN A COMBUSTOR AND FUEL NOZZLE - A floating collar assembly is provided comprising a substantially flat floating collar trapped between a heat shield and a dome panel of the combustor. Axial engagement between the floating collar and the fuel nozzle is maintained via a nozzle cap mounted over the fuel nozzle tip. | 11-20-2008 |
20090126368 | FUEL INJECTION SYSTEM FOR A GAS TURBINE ENGINE - A fuel injection system comprises a fuel conveying member and a nozzle tip assembly threadably engaged thereto. A pair of sealing elements is engaged in a fuel passage between the fuel conveying member and the nozzle tip for sealing the junction therebetween. The pair of sealing elements includes a first and a second sealing element located proximate each other and having different cross-sectional shape. | 05-21-2009 |
20100071663 | EXTERNAL RIGID FUEL MANIFOLD - A fuel manifold of a gas turbine engine includes a tube assembly having substantially rigid inner tubes disposed inside of substantially rigid outer tubes in pairs, concentrically spaced apart by a spacer apparatus. The inner tubes form a primary fuel passage for directing a primary fuel flow and the outer tubes form a secondary fuel passage for directing a secondary fuel flow, the secondary flow being greater than the primary flow. | 03-25-2010 |
20100077758 | INTERNAL FUEL MANIFOLD HAVING TEMPERATURE REDUCTION FEATURE - A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced. | 04-01-2010 |
20100146928 | FUEL MANIFOLD FOR GAS TURBINE ENGINE - A fuel manifold for a gas turbine engine comprises manifold adaptors each supporting a nozzle for outputting fuel from a fuel supply. The manifold adaptors have a primary conduit and a secondary conduit extending between connection ends of the manifold adaptor. The primary conduit and the secondary conduit are in fluid communication with the nozzle to supply fuel thereto. Transfer units are between adjacent manifold adaptors, and each comprises a primary transfer tube matingly connected at opposite ends to the primary conduits of the adjacent manifold adaptors for fuel circulation between the primary conduits. A secondary transfer tube in each transfer unit is matingly connected at opposite ends to the secondary conduits of the adjacent manifold adaptors for fuel circulation between the secondary conduits. A drain sleeve in each transfer unit is connected at opposite ends to the adjacent manifold adaptors. | 06-17-2010 |
20100236257 | GAS TURBINE COMBUSTOR EXIT DUCT AND HP VANE INTERFACE - An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound. | 09-23-2010 |
20100281881 | GAS TURBINE COMBUSTOR AND FUEL MANIFOLD MOUNTING ARRANGEMENT - A mounting system for locating a combustor and a fuel manifold of a gas turbine engine within a gas generator casing thereof is described. The mounting system comprises at least three support pin assemblies which extend radially inwardly from the gas generator casing. The support pin assemblies support both the fuel manifold and at least an upstream end of the combustor and maintaining engagement between the fuel manifold and the combustor during operation of the gas turbine engine. | 11-11-2010 |
20110048023 | FUEL NOZZLE SWIRLER ASSEMBLY - 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. | 03-03-2011 |
20120240588 | HYBRID SLINGER COMBUSTION SYSTEM - A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions. | 09-27-2012 |
20120304651 | INTEGRATED FUEL NOZZLE AND IGNITION ASSEMBLY FOR GAS TURBINE ENGINES - There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage. | 12-06-2012 |
20130247574 | FUEL MANIFOLD HEAT SHIELD FOR A GAS TURBINE ENGINE - A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly. | 09-26-2013 |
20130247575 | COMBUSTOR HEAT SHIELD - A heat shield for a gas turbine engine having a combustor includes an annular configuration extending substantially 360 degrees about the combustor for protecting a dome portion thereof, which is formed by radially extending flanges of inner and outer liners of the combustor. The heat shield fixedly secures the radially extending flanges of the inner and outer liners together in a sealing relationship such as to structurally form the dome portion of the combustor. The heat shield is disposed internally within the combustor and substantially entirely overlying the dome portion. The heat shield includes at least two separate heat shield segments cooperating to provide the annular heat shield, each heat shield segment being sheet metal and including at least two circumferentially spaced apart openings therein for receiving fuel nozzles therethrough. Each of the heat shield segments has a circumferential span not exceeding 180 degrees. | 09-26-2013 |
20130327054 | HYBRID SLINGER COMBUSTION SYSTEM - A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions. | 12-12-2013 |
20140260260 | COMBUSTOR FOR GAS TURBINE ENGINE - A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber. | 09-18-2014 |
20140318145 | HYBRID SLINGER COMBUSTION SYSTEM - There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand. | 10-30-2014 |