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| Number | Title | Issue Date |
| 7966822 | Reverse-flow gas turbine combustion system A gas turbine combustion system for burning air and fuel into exhaust gases. The gas turbine combustion system may include a combustor, a turbine nozzle integral with the combustor for providing the air to the combustor, and a fuel injector for providing the fuel to... | 06/28/2011 |
| 7299634 | Combustion chamber A combustion chamber (4) for a gas turbine (1), the combustion chamber wall (24) of which is furnished on the inside with a lining formed of a number of heat shield elements (26), is to be designed for a particularly high level of operati... | 11/27/2007 |
| 7194866 | Static structure for an expendable gas turbine engine A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an exhaust pipe with relatively uncomplicated assembly interfaces. The sta... | 03/27/2007 |
| 6968693 | Method and apparatus for reducing gas turbine engine emissions A low emission turbine includes a reverse flow can-type combustor that generally includes a primary and secondary fuel delivery system that can be independently controlled to produce low CO, UHC, and NOx emissions at design set point and at conditions other than des... | 11/29/2005 |
| 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 |
| 6286317 | Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity A liner for a gas turbine engine combustor, including an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget joining the upstream and downstream liner sections for providing mechanical stiffness ... | 09/11/2001 |
| 6193502 | Fuel combustion device and method The fuel is fed centrally into a fire tube (3), where it is mixed with combustion air in a combustion zone. The air exits through first and second air line nozzles (4 or 5) which are arranged in two directly adjoining rows (6, 7) and inclined in the direc... | 02/27/2001 |
| 6029455 | Turbojet engine combustion chamber with heat protecting lining A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The combustion chamber also has at least two rows of insulating tiles ... | 02/29/2000 |
| 6018950 | Combustion turbine modular cooling panel A modular cooling panel for cooling a turbine member is provided. The cooling panel comprises a first panel having a relative width, relative length, upper surface and lower surface. The upper surface defines at least one corrugated portion traversing alo... | 02/01/2000 |
| 5826431 | Gas turbine multi-hole film cooled combustor liner and method of manufacture Provided are a gas turbine multi-hole film-cooled combustor liner, which can be manufactured with improved accuracy in shape and position of cooling holes in a very short time, ensuring desirable buckling strength and satisfactory cooling performance. A p... | 10/27/1998 |
| 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 |
| 5331803 | Method of obtaining a desired temperature profile in a turbine engine and turbine engine incorporating the same Undesirable high temperature gradients associated with inadequate mixing of dilution air with gases of combustion in turbines is avoided in a structure wherein dilution air is injected with a high degree of circumferential swirl through an opening (50) to... | 07/26/1994 |
| 4926630 | Jet air cooled turbine shroud for improved swirl cooling and mixing Warping of the rear turbine shroud 54 and the resulting cracking of turbine nozzle vanes 24 may be eliminated in a radial inflow turbine having an annular combustor 30 with a radially outer wall 32 opening on a compressed air plenum 48 by locating a plura... | 05/22/1990 |
| 4765146 | Combustion chamber for gas turbines The combustion chamber is characterized by an annular-cylindrical space, which consists of two reaction chambers (8), arranged at the end, and a collision chamber (12) placed therebetween. The reaction chambers (8) are fitted at their face-sided ends with... | 08/23/1988 |
| 4719748 | Impingement cooled transition duct A transition duct in an advanced heavy duty gas turbine engine is cooled by impingement jets formed by apertures in a sleeve spaced a distance from the surface to be cooled. The sleeve is configured so as to duct spent impingement air towards the combusto... | 01/19/1988 |
| 4676736 | Combustion device for combustion of a gaseous fuel A combustion device for combustion of a gaseous fuel with air is provided with means for supplying gas automatically at a mass flow rate corresponding to a mass flow of air governed by the demand of heat. The gas is supplied at a pressure slightly above a... | 06/30/1987 |
| 4642993 | Combustor liner wall A combustor liner wall is provided with an interior wall, an exterior wall and a honeycomb structure disposed therebetween. The honeycomb structure is formed with generally radially aligned cells. The cells are constructed to define alternate array of gap... | 02/17/1987 |
| 4628687 | Gas turbine combustor with pneumatically controlled flow distribution A combustor for a gas turbine including a burner defining an axial fluid flow path between upstream and downstream ends, a burner casing coaxially surrounding the burner and defining an annular conduit for inlet gas flow from downstream to upstream ends o... | 12/16/1986 |
| 4475344 | Low smoke combustor for land based combustion turbines An improved combustor basket for a land-based combustion turbine comprises a plurality of ring segments joined in telescoping fashion to form a constant diameter basket, the downstream end of each ring segment having an extended lip for improved film cool... | 10/09/1984 |
| 4446693 | Wall structure for a combustion chamber A cooled wall structure for a gas turbine engine comprises a perforated and an inner wall in which the walls are capable of relative movement to cope with the thermal strains experienced by the combustion chamber during operation of the engine. The inner ... | 05/08/1984 |
| 4365951 | Device for combustion of a volatile fuel with air A combustion device of the type in which fuel is supplied in liquid phase through a "walking-stick" is improved by imparting a rotary movement to the air passing the "walking-stick". The fuel will form a film which is volatired and mixed so thoroughly wit... | 12/28/1982 |
| 4339925 | Method and apparatus for cooling hot gas casings A method and apparatus for cooling the hot gas casing of a gas turbine power plant is disclosed. The apparatus includes a shell which is spaced from but which encompasses the hot gas casing so as to form an air channel about the casing. A compressor provi... | 07/20/1982 |
| 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 |
| 4244179 | Annular combustion chamber for gas turbine engines An annular combustion chamber which has structural elements for delivery of primary air to sustain and stabilize burning and elements for admission of secondary air into the dilution zone. The primary air delivery elements intended for stabilization of bu... | 01/13/1981 |
| 4211073 | Combustion chamber principally for a gas turbine This invention concerns an improved combustion chamber comprising two concentric sheet metal cases forming a space into which air is admitted. The air passes from the space to the interior of the chamber in primary, secondary, annular, and tertiary air fl... | 07/08/1980 |
| 4151709 | Gas turbine engines with toroidal combustors A gas turbine engine is described in which a compressor, combustor and turbine are arranged in series flow relationship. The compressor discharge is outwardly angled. This pressurized air is then introduced into a toroidal combustion chamber of the combus... | 05/01/1979 |
| 4090360 | Single chamber type combustion structure for a gas turbine engine A single chamber type combustion structure particularly for industrial gas turbine plants in which the axis of the chamber forms a perpendicular to the axis of the compressor-turbine group wherein primary combustion air, delivered by the compressor couple... | 05/23/1978 |
| 4088437 | Combustion chamber A combustion chamber with an evaporator that projects into the combustion zone of the flame tube and includes a coaxial channel and to which air and fuel are supplied separately; a deflection surface is thereby arranged at the end of the evaporator channe... | 05/09/1978 |
| 4054028 | Fuel combustion apparatus A fuel combustion apparatus of a double-shell construction in which the inner shell is composed of an upstream small-diameter section, a downstream large-diameter section, and a conically-shaped connecting section between the two sections of different dia... | 10/18/1977 |
| 4038815 | Gas turbine A gas turbine includes a rotatable unit having a compression component and an expansion component, and a toroidal combustion chamber between the compression and expansion components. The gas turbine has a gas flow path serially through the compression com... | 08/02/1977 |
| 3977186 | Impinging air jet combustion apparatus A combustion liner for a gas turbine combustion apparatus or the like has a head wall and a side wall extending downstream to an outlet for combustion products. A reaction zone is contained within the upstream end of the side wall and a dilution zone down... | 08/31/1976 |
| 3968644 | Fuel admitting and conditioning means on combustion chambers for gas turbine engines Apparatus for supplying air and fuel to a flame tube of a combustion chamber of a gas turbine engine which includes primary air supply ports for supplying air under high pressure toward the center of the flame tube and fuel tubes projecting into and openi... | 07/13/1976 |
| 3952501 | Gas turbine control A continuous combustion device of the type having a combustion chamber and an outer casing forming with it an annular air delivery passage for distributing a continuous supply of compressed air into the combustion chamber, and a fuel injector at one end o... | 04/27/1976 |
