Patent application number | Description | Published |
20090000303 | COMBUSTOR HEAT SHIELD WITH INTEGRATED LOUVER AND METHOD OF MANUFACTURING THE SAME - A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield. | 01-01-2009 |
20090025224 | METHOD FOR MANUFACTURING OF FUEL NOZZLE FLOATING COLLAR - A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks. | 01-29-2009 |
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 |
20090211097 | METHOD FOR MANUFACTURING OF FUEL NOZZLE FLOATING COLLAR - A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks. | 08-27-2009 |
20090214375 | METHOD FOR MANUFACTURING OF FUEL NOZZLE FLOATING COLLAR - A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks. | 08-27-2009 |
20100050650 | GAS TURBINE ENGINE REVERSE-FLOW COMBUSTOR - A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands to aid in repairability of the combustor. The cooling of the bands improves the durability of the combustor and provides a method of repair for the combustor. | 03-04-2010 |
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 |
20100139283 | COMBUSTOR LINER WITH INTEGRATED ANTI-ROTATION AND REMOVAL FEATURE - A combustor liner for a gas turbine engine including first and second annular liner portions engaged to one another with an interference fit. The first liner portion includes at least one anti-rotation feature extending therefrom and engaging the second liner portion and having a threaded hole defined therethrough at least substantially perpendicularly to an adjacent radially extending surface of the second liner portion for threadingly receiving a pushing tool for pushing against that surface. | 06-10-2010 |
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 |
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 |
20110079667 | FUEL NOZZLE AND METHOD OF REPAIR - A method of repairing a modular gas turbine fuel nozzle tip, having a fuel-conveying body and an annular cap fastened to the body by at least two fasteners, includes removing the fasteners, replacing the annular cap with a replacement annular cap, and interconnecting the replacement annular cap and the body using new fasteners. | 04-07-2011 |
20110120142 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER - A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs. | 05-26-2011 |
20110173982 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER - A fuel conveying member for a gas turbine engine, the fuel conveying member including a fuel manifold having a plurality of fuel nozzles extending therefrom. The fuel manifold is mounted within the engine by a support system, including integral attachment lugs on the fuel manifold for mounting the fuel manifold within the gas turbine engine. The attachment lugs re adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs. | 07-21-2011 |
20110271528 | METHOD OF REPAIRING A GAS TURBINE ENGINE COMBUSTOR - A method of repairing an annular sheet metal combustor liner of a gas turbine engine includes cutting circumferentially around combustor liner bands bounding an effusion patch extending circumferentially around the liner, the effusion patch having effusion cooling holes and being bounded on either side by at least one effusionless band free from effusion cooling holes, to thereby remove a portion of the combustor liner having the effusion patch. A replacement liner portion including an effusion patch is provided and welded to the liner assembly, the weld extending circumferentially around the cut band to provide a welded effusionless band. The welded effusionless bands is cooled during engine use using one of film cooling of an inner surface of the welded effusionless band and impingement cooling of an outer surface of the welded effusionless band. | 11-10-2011 |
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 |
20130031909 | COMBUSTOR HEAT SHIELD WITH INTEGRATED LOUVER AND METHOD OF MANUFACTURING THE SAME - A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield. | 02-07-2013 |
20130139513 | FUEL NOZZLE AND METHOD OF REPAIR - A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body. | 06-06-2013 |
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 |
20140260296 | SLINGER COMBUSTOR - A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger. | 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 |
20150040568 | COMBUSTOR FLOATING COLLAR ASSEMBLY - A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss. | 02-12-2015 |