Abstract: A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: A gas turbine combuster ia provided with a dome heat shield having a fuel nozzle opening, the opening receiving a floating collar assembly for permitting relative movement between nozzle and heat shield. The floating collar is provided with a louver to provide film cooling to the face of the combustor heat shield and, thus, improve cooling thereof.

Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.

Abstract: A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in regions intermediate each diffuser pipe than in other areas of the combustor liner.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: 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 pattern around an axis along which fuel is injected into the combustor by the fuel nozzles.

Abstract: A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots.

Abstract: A gas turbine fuel nozzle head includes an outlet passage having a curved annular transitional surface extending smoothly to a substantially radial and annular surface relative to a central axis of the fuel nozzle head, for providing a low cost and compact structure with improved cold start and altitude re-light capabilities.

Abstract: A gas turbine engine combustor includes an apparatus for directing air around the axis along which fuel is injected into the combustor to thereby improve the combustor.

Abstract: A gas turbine fuel nozzle head includes an outlet passage having a curved annular transitional surface extending smoothly to a substantially radial and annular surface relative to a central axis of the fuel nozzle head, for providing a low cost and compact structure with improved cold start and altitude re-light capabilities.

Abstract: A method of making a gas turbine engine combustor using the steps of: providing a combustor; providing a circumferentially extending louver member for ducting a flow of compressed air through at least one inlet opening in a combustor wall from a source of compressed air outside the combustor; and mounting the louver member in a non-destructive manner for releasable connection and disconnection to an interior surface of the combustor wall and at least partially covering the at least one inlet opening, the louver having a number of outlet openings in flow communication with an inlet opening.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall into the chamber, the nozzle tip including a first air passage forming an annular array of individual air passages spaced radially from the first air passage and communicating the pressurized air from outside the combustor wall into the combustor. A fuel gallery extends through the fuel injector tip and defines an annular fuel nozzle radially within the first air passages, whereby the first air passages are arranged to atomize the fuel emanating from the annular fuel nozzle, and second fuel passages are arranged in annular array in the injector tip spaced radially outwardly from the first air passages whereby the second passages are arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.

Abstract: A fuel injector for a combustor presented either as a simplex or duplex pressurized fuel injector, wherein the fuel is introduced into the injector to provide a swirl to the fuel in a first annular channel which communicates with a coaxial conical fuel swirl chamber and then the primary nozzle. In a duplex version, a secondary annular swirl channel is provided for spinning the fuel and communicating downstream with a conical fuel swirl chamber and eventually an annular nozzle whereby the fuel is atomized as it exits the nozzle. An air swirler is also provided with the fuel injector, and the air swirler includes air passages arranged in an annular array about the fuel injector tip. A second array of auxiliary air passages can be arranged spaced radially from the first array and also to provide an air swirl and to control the spray cone of the fuel air mixture.

Abstract: The invention relates to a simple low cost fuel nozzle support stem that can be manufactured to meet extremely close tolerances with enhanced structural rigidity through use of a cylindrical stem body machined from solid bar stock. Superior thermal control to regulate thermal displacement of the stem body and to prevent fuel coking is provided by a concentric secondary fuel bore and a primary fuel tube disposed within the bore. The low pressure secondary fuel flow encircles the high pressure primary flow tube and serves to cool the fuel tube and cylindrical stem body in a uniform symmetric manner. An outer cylindrical insulating sleeve mounted on shoulders extending from the cylindrical body of the stem defines an elongate annular insulating air gap between the sleeve and cylindrical stem body. The support stem includes a dual fuel spray nozzle and a fuel adapter/mounting flange that are mounted to the stem body with simple cylindrical sockets.

Abstract: A method and device are provided to enable optimizing combustion conditions of a continuous combustion device to produce low emissions of nitric oxide, carbon monoxide and hydrocarbons at all operative conditions. The continuous combustion device includes a slidable baffle to regulate, according to power levels, not only an airflow directly into a primary combustion zone and a secondary combustion zone but also an airflow into a fuel/air premix device to maintain the fuel/air ratio in the primary combustion zone optimized both at an average level and in local areas. Such that, low objectionate or harmful emissions can be reached without performance penalties of the combustion device, such as anti-ignition, flashback or flameout.

Abstract: The invention provides in a gas turbine engine combustion chamber, an array of elongate louver strips between fuel nozzles of a combustion chamber dome wall, to cool the dome wall and contain combustion gases in the area between nozzles. The elongate louver strips are each disposed symmetrically along the median line on the inner surface dome wall and extend between each nozzle cup of the annular array. Each strip includes an elongate flange extending into the combustion chamber from the inner dome wall. The flange has an inner surface, and lateral side walls, with the inner surface generally parallel to the inner surface of the dome wall. Compressed air outlets are disposed along each flange lateral side wall, for directing a compressed air film along the inner surface of the dome wall in a direction away from the median line. A compressed air inlet extends from the outer surface of the dome wall to the outlets.

Abstract: A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall into the chamber, the nozzle tip including a first air passage forming an annular array communicating the pressurized air from outside the wall into the combustion chamber. A second air passage is made up of an annular array of individual air passages spaced radially from the first air passage and communicating the pressurized air from outside the combustor wall into the combustor.

Abstract: A one piece cold combustor wall for lining the reverse flow hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of the hot combustor wall results from the addition of impingement cooling air injected through orifices in the cold combustion wall directed at the hot combustion wall together with film cooling by air conducted between the hot and cold combustor walls. The cold combustor wall is perforated with a pattern of air impingement inlet orifices through the cold combustor wall conducting compressed air from the outer surface of the cold combustor wall in compressed air jets directed at the outer surface of the hot combustor wall. The provision of a cold combustor wall also improves conventional air film cooling by adding impingement cooling and reusing the air after impingement to form a contained air film between the hot and cold walls.