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| Number | Title | Issue Date |
| 5081844 | Combustion chamber of a gas turbine In an annular combustion chamber (A), a row of premixed burners (B, C) are located in the peripheral direction at the inlet end. The large premixed burners (B), which are the main burners of the annular combustion chamber (A), and the small premixed burne... | 01/21/1992 |
| 5074111 | Seal plate with concentrate annular segments for a gas turbine engine The clearance between a seal assembly 46 and a turbine wheel 14 in a turbine engine of the type having a radial outflow compressor 24 and a radial inflow turbine wheel 14 may be minimized by utilizing a diaphragm assembly 76 as part of the seal assembly 4... | 12/24/1991 |
| 4903477 | Gas turbine combustor transition duct forced convection cooling In a gas turbine the transition duct is subject to high temperature since it conducts the combustion products to the power turbine. It is normally cooled by air from the compressor. This invention improves the uniformity of cooling by forcing the cooling ... | 02/27/1990 |
| 4850187 | Gas turbine having components composed of heat resistant steel A heat resistant steel of the present invention contains 0.05 to 0.2 wt. % of C, less than 0.5 wt. % of Si, less than 0.6 wt. % of Mn, 8 to 13 wt. % of Cr, 1.5 to 3 wt. % of Mo, 2 to 3 wt. % of Ni, 0.05 to 0.3 wt. % of V, 0.02 to 0.2 wt. % in total of eit... | 07/25/1989 |
| 4843825 | Combustor dome heat shield An annular combustor has a plurality of fuel injectors 14, each supporting a heat shield 30. Each shield has an overlap portion 42 deflecting cooling air passing between the shields, thereby avoiding a curtain of air between the flames of adjacent fuel in... | 07/04/1989 |
| 4720970 | Sector airflow variable geometry combustor An improved annular combustor having a plurality of annularly disposed fuel nozzles for supplying fuel to the combustor dome, and a structure defining a dome plenum adjacent each said fuel nozzle is provided, wherein means in the form of partitions or wal... | 01/26/1988 |
| 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 |
| 4573315 | Low pressure loss, convectively gas-cooled inlet manifold for high temperature radial turbine A toroidally shaped double-walled gas-cooled inlet manifold for a radial in-flow turbine has a plurality of can-type combustors mounted on one axially facing side of the torous, arrays of coolant gas inlet holes in the outer wall located midway between th... | 03/04/1986 |
| 4553386 | Combustion chamber for dual turbine wheel engine A turbine engine for powering aircraft, land vehicles and the like having a stationary member inclusive of casing portions defining a plurality of radially extending, spaced combustion chambers. A rotary member within the stationary member has two or more... | 11/19/1985 |
| 4422288 | Aft mounting system for combustion transition duct members A structural support system for the aft end of advanced design combustion transition duct members of specially configured to withstand high temperature gradients and mechanical loads developed in heavy-duty cannular gas turbine combustion systems. A compo... | 12/27/1983 |
| 4411134 | Apparatus for the repair and replacement of transition ducts on jet engines and bracket therefor A replacement transition duct assembly for a jet engine comprised of a plurality of complementary louvered sections having joining ends that are assembled together about the engine by means of a novel bracket. The bracket is formed with a spaced array of ... | 10/25/1983 |
| 4373327 | Gas turbine engine combustion chambers In a gas turbine engine having a can annular combustion system, the diffusion passage between the outlet annulus of the engine compressor and the inlets to the individual combustion chambers located in an annular casing, is partially defined diffusion con... | 02/15/1983 |
| 4359861 | Gas turbine A gas turbine utilizing the spontaneous ignition of preheated fuel, said gas turbine including a series of combustion chambers supplied with fuel from pumping and preheating subassemblies.... | 11/23/1982 |
| 4356693 | Gas turbine engine combustion chambers In a gas turbine engine having a can annular combustion system, the diffusion passage between the outlet annulus of the engine compressor and the inlets to the individual combustion chambers located in an annular housing, is partially defined by diffusion... | 11/02/1982 |
| 4297843 | Combustor of gas turbine with features for vibration reduction and increased cooling A combustor of a gas turbine having a plurality of liners defining combustion chambers, and transition pieces adapted to rectify the flow of the combustion gas discharged from the liners before the combustion gas is introduced to the turbine. A guide plat... | 11/03/1981 |
| 4255927 | Combustion control system A combustion system for gas turbines is disclosed which is capable of burning gaseous and liquid fuels. Excess air injected into the reaction zone of the combustor produces either a fuel-lean or fuel-rich mixture which lowers the temperature at which comb... | 03/17/1981 |
| 4249372 | Cross-ignition assembly for combustion apparatus A cross-ignition assembly with a cross-fire tube supported intermediate two adjacent combustors by mounting plates affixed thereto so as to provide a conduit for the flow of hot combustion gases therebetween. The cross-fire tube comprises coaxial telescop... | 02/10/1981 |
| 4201046 | Burner nozzle assembly for gas turbine engine An axial flow gas turbine engine has a combustion section with a number of nozzle assemblies for injecting fluent materials, such as fuel, combustion enhancers, or pollutant reducers, into a burner which is supplied with air from the combustion section pl... | 05/06/1980 |
| 4195474 | Liquid-cooled transition member to turbine inlet An improved structure is provided for liquid cooling a transition member which conducts hot motive gases from a combustor to a turbine inlet in a gas turbine power plant. The liquid-cooled structure includes a transition member body having a longitudinal ... | 04/01/1980 |
| 4186554 | Power producing constant speed turbine A power producing constant speed rotary turbine in which an elongate shaft is rotatably supported in longitudinally spaced, axially aligned first and second housings that have a housing assembly disposed thereinbetween. The first housing rotatably support... | 02/05/1980 |
| 4129985 | Combustor device of gas turbine engine A combustor device of a gas turbine engine, which combustor device is supplied with compressed air from a compressor and delivers combustion gas to a turbine, comprises an outer casing and an inner casing defining therein a combustion chamber and forming ... | 12/19/1978 |
| 4016718 | Gas turbine engine having an improved transition duct support An axial flow gas turbine engine is provided with a plurality of combustion chambers distributed circumferentially about the engine axis and a plurality of transition ducts which carry propulsive gases between the burners and an annular turbine inlet at a... | 04/12/1977 |
| 4009569 | Diffuser-burner casing for a gas turbine engine A diffuser-burner casing in the combustion section of an axial flow gas turbine engine transmits axial engine loads between the compressor section and the turbine section and serves as a housing for the combustion chamber assemblies and as a bearing suppo... | 03/01/1977 |
| 3991560 | Flexible interconnection for combustors An interconnection or crossover construction is provided for interconnecting the combustors of a combustion apparatus such as a gas turbine. The connection between adjacent combustors is made by means of a flexible tube which permits a substantial amount ... | 11/16/1976 |
| 3978658 | Variable load gas turbine A system for bypassing compressed air and regulating the fuel to rapidly vary the load on a gas turbine so that the turbine can absorb energy and pick up load rapidly without inducing high temperature stresses within the turbine.... | 09/07/1976 |
| 3949775 | Fuel supply and distribution system A fuel supply and distribution system is provided for a gas turbine engine wherein a plurality of flow dividing valves disposed about a manifold are positively controlled through an actuator which interconnects the flow dividing valves by linkage means ex... | 04/13/1976 |
| 3940924 | Rotary engine This invention relates to a rotary engine that functions without internal gears, off-centered rotors, reciprocating pistons, crankshafts, trochoidal chamber, chains, nor belts. (While no claim can be made on missing parts, the fact that such conventional ... | 03/02/1976 |
