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| Number | Title | Issue Date |
| 8151570 | Transition duct cooling feed tubes Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement s... | 04/10/2012 |
| 8109099 | Flow sleeve with tabbed direct combustion liner cooling air A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is... | 02/07/2012 |
| 7827801 | Gas turbine engine transitions comprising closed cooled transition cooling channels A transition (200) for a gas turbine engine (100) comprises a transition wall (201) comprising cooling channels (213L, 213R, 223L, 223R) that are adapted to pass a cooling fluid, such as compressed air from a compress... | 11/09/2010 |
| 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 |
| 6832482 | Pressure ram device on a gas turbine combustor 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... | 12/21/2004 |
| 6681578 | Combustor liner with ring turbulators and related method A combustor liner for a gas turbine includes a substantially cylindrical body having a plurality of raised circular ribs arranged in an array on an outside surface of the combustor liner, each rib defining an enclosed are on the outside surface of the lin... | 01/27/2004 |
| 6499993 | External dilution air tuning for dry low NOX combustors and methods therefor A combustor having a combustion liner and at least one combustor orifice assembly, the combustor orifice assembly comprising a boss, an orifice plate that defines an orifice, the orifice plate having a bottom surface that is adapted to be received by the ... | 12/31/2002 |
| 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 |
| 6351949 | Interchangeable combustor chute An interchangeable combustor chute for directing airflow into a gas turbine engine combustor. In one aspect the combustor chute is secured to the combustor liner by mechanical fastener. The combustor chute is formed of a high temperature resistant materia... | 03/05/2002 |
| 6331110 | External dilution air tuning for dry low NOx combustors and methods therefor Dilution sleeves are provided in radially aligned openings in the combustion liner and flow sleeve of a combustor for a gas turbine. The sleeves have a flange for seating on a collar of the flow sleeve about the opening therethrough enabling the dilution ... | 12/18/2001 |
| 6055813 | Plenum Described is a plenum, in particular the air plenum of a gas-turbine combustion chamber, having at least two flow inlets, for introducing gas flows into the plenum, in which the gas flows are guided essentially along the inner wall of the plenum and are d... | 05/02/2000 |
| 5918465 | Flow guiding body for a gas turbine combustion chamber A flow-guiding body is designed as a pointed, substantially conical molded shell. The projection of its base surface is formed by a straight line and by a curve that interconnects the ends of the straight line. The curve forms no significant angles. The m... | 07/06/1999 |
| 5727378 | Gas turbine engine This invention pertains to small air breathing gas turbine engines (1). Engines of the invention employ improved combustion systems, including improved fuel injection systems and improved combustor design. These improvements enable the engine to idle at s... | 03/17/1998 |
| 5488829 | Method and apparatus for reducing noise generated by combustion A combustor in which fuel is introduced into a combustion zone at a first acute angle with respect to the radially outward direction so as to swirl the fuel about the combustor axis, thereby improving the stability of the combustion process. Combustion ai... | 02/06/1996 |
| 5454221 | Dilution flow sleeve for reducing emissions in a gas turbine combustor Sleeves (28) are circumferentially spaced from one another about the liner of a combustor body (12) of a dry low NOx combustor. The sleeves carry dilution air into the dilution zone. Cooling air is supplied a venturi (20) to cool the venturi an... | 10/03/1995 |
| 5329773 | Turbine combustor cooling system A gas turbine engine has a low cost combustor liner cooling system combining the benefits of high internal heat removal with improved film cooling by employing a large number of strategically positioned, laser-drilled cooling passages. Cooling air flows t... | 07/19/1994 |
| 5235805 | Gas turbine engine combustion chamber with oxidizer intake flow control An oxidizer intake flow control system is disclosed for a gas turbine engine combustion chamber. The chamber has an oxidizer intake assembly which extends through the wall of the chamber such that an inlet aperture of the oxidizer intake and an exhaust ap... | 08/17/1993 |
| 5209067 | Gas turbine combustion chamber wall structure for minimizing cooling film disturbances A combustion chamber wall structure is formed of a plurality of segments, each segment having an upstream portion and a downstream portion. The upstream portion is attached to an outer surface of an adjacent wall segment at its downstream portion in an ov... | 05/11/1993 |
| 5207570 | Bluff body band register and bluff body band pilot A burner assembly includes a register including an annular wall defining a chamber, the annular wall including a plurality of coaxial annular bands and a plurality of parallel, axially spaced, circumferentially extending slots which separate the bands and... | 05/04/1993 |
| 5187937 | Gas turbine engine combustors A gas turbine engine combustor, eg of annular combustor configuration, has air inlets, typically in the dilution zone, which incorporate vortex generators operative to trip the inlet jet flow causing stabilizing vortex flow at the lateral edges of the jet... | 02/23/1993 |
| 5077969 | Cooled liner for hot gas conduit A plurality of gas diffusion openings (24) direct film cooling air (26) along the surface of sheet (20). Each opening (24) includes a baffle (28) extending into gas stream (10) defining gas chamber (30) with outlet opening (32). Cool air inlet opening (34... | 01/07/1992 |
| 4989407 | Thrust augmentor flameholder A radial flameholder (18) extends from the augmentor case (22) through an opening (30) in a coaxial liner (20) and into the hot exhaust gas stream (26). A portion of a cool, annular fan air stream (28) enters an upstream facing opening (34) and discharged... | 02/05/1991 |
| 4938020 | Low cost annular combustor The expense of fabricating an annular combustor for use with a small diameter gas turbine engine is minimized in a construction including a bell-shaped housing 52, an axially extending sleeve 66 within the housing 52, an annular liner 74 within the housin... | 07/03/1990 |
| 4887432 | Gas turbine combustion chamber with air scoops A gas turbine combustion chamber with an inlet and outlet has apertures in the combustion chamber wall and air scoops provided in the apertures, the air scoops having an outer tubular member and coaxially spaced inner tubular member. The spaced tubular me... | 12/19/1989 |
| 4875339 | Combustion chamber liner insert An air admission insert particularly adapted for air admission holes in a combustor liner in a gas turbine combustion system comprises a pair of sleeve members, one of which is inserted in the other in axial but eccentric relationship so that the sides of... | 10/24/1989 |
| 4805397 | Combustion chamber structure for a turbojet engine A combustion chamber for a turbojet engine is disclosed which utilizes double walled construction. Hot walls are attached to adjacent cold walls solely by an orifice member which defines an orifice to supply primary of dilution air to the combustion chamb... | 02/21/1989 |
| 4790140 | Liner cooling construction for gas turbine combustor or the like A liner cooling construction for a gas turbine combustor or the like in which twisted or helical tapes in the spaces defined between the liner walls and the partition walls cause the cooling air to swirl so that the efficient cooling of the liner walls ca... | 12/13/1988 |
| 4700544 | Combustors A refilmer for placing the film of cool air impeded by combustion/dilution air holes of a combustor for a gas turbine engine includes a grommet with a lip extending axially in the combustion chamber. The outer side wall of the grommet is recessed in the a... | 10/20/1987 |
| 4629416 | Bluff body register A burner assembly includes a register having a circular front wall and an annular side wall; a plurality of cylindrical bluff body elements circumferentially spaced about the annular side wall in a plurality of axially spaced rows for supplying air to the... | 12/16/1986 |
| 4628694 | Fabricated liner article and method A method of fabricating sheet metal panels and the article produced thereby. According to one form, the method of fabrication includes the steps of providing a panel of sheet metal, perforating the panel to provide a plurality of holes, forming the panel ... | 12/16/1986 |
| 4607487 | Combustion chamber wall cooling A gas turbine combustion including a combustion wall having a plurality of generally cylindrical passages therein which extend around and are generally parallel to, the chamber axis, each of said passages having a series of air inlets disposed along the p... | 08/26/1986 |
| 4562699 | Mixing chambers for continuous flow engines A combustion system comprising a tubular structure having an upstream end and defining within it a longitudinal passage. A tubular wall surrounding the structure and defining with the structure a further longitudinal passage, of annular cross section. The... | 01/07/1986 |
| 4549402 | Combustor for a gas turbine engine A combustor for a gas turbine is provided, the combustor including a reverse flow type combustion chamber defined by an inner cylindrical wall and an outer wall concentric with the inner wall and connected at one end by an annular dome. The outer wall has... | 10/29/1985 |
| 4458481 | Combustor for regenerative open cycle gas turbine system A counter flow combustor for regenerative open cycle turbine systems has an outer casing defining a head cavity at one end, an inner casing mounting in said outer casing, said inner casing defining a combustion chamber. An annular insulated partition and ... | 07/10/1984 |
| 4446692 | Fluidic control of airflow in combustion chambers The airflow from the compressor of a gas turbine engine into the combustion chamber or chambers principally comprises combustion air which enters the upstream end of the combustion chamber and dilution air which enters the combustion chamber at some point... | 05/08/1984 |
| 4301657 | Gas turbine combustion chamber A gas turbine combustion chamber in which the primary air inlets in a peripheral wall of the combustion chamber are defined by open-ended tubes extending inwardly from the peripheral wall by a substantial distance into the combustion chamber and having th... | 11/24/1981 |
| 4297842 | NOx suppressant stationary gas turbine combustor The NOx emissions of a stationary gas turbine are reduced by concentrating a NOx suppressant in the reaction zone of the gas turbine combustor by dividing the flow of air to the reaction zone and the dilution zone of the combustor by means of an air flow ... | 11/03/1981 |
| 4288980 | Combustor for use with gas turbines A counter flow combustor has a generally elongated hollow cylindrical outer casing or shell with a closure means at the upper end defining a head space and a generally elongated smaller hollow annular inner casing or combustion wall mounted therein in spa... | 09/15/1981 |
| 4232527 | Combustor liner joints A combustor apparatus for use in gas turbine engines includes an annular dome of porous laminated material joined by a solid metal joint ring to inner and outer annular porous wall segments also constructed of porous laminated material; and wherein the so... | 11/11/1980 |
| 4211069 | Combustion chamber for a gas turbine A combustion chamber of a gas turbine engine has a combustion cowl and transition piece with at least one air gap provided therebetween. The air gap opens into an intermediate chamber having two throttles which are arranged oppositely with respect to one ... | 07/08/1980 |
