Matches 1 - 50 out of 353 1 2 3 4 5 6 7 8 >


Match Document Document Title
8973369 Gas-turbine burner having inflow guide means  
A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of...
8950192 Gas turbine  
A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an...
8938978 Gas turbine engine combustor with lobed, three dimensional contouring  
A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the...
8938970 Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall  
A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the...
8925324 Turbomachine including a mixing tube element having a vortex generator  
A turbomachine includes a compressor section, a combustor operatively connected to the compressor section, an end cover mounted to the combustor, and an injection nozzle assembly operatively...
8910481 Advanced quench pattern combustor  
A combustor for a gas turbine engine is provided. The combustor includes a forward bulkhead, an inner radial combustor wall, and an outer radial combustor wall. The bulkhead includes a plurality...
8839627 Annular combustor  
An annular combustor includes an annular outer shell that includes a first flange that defines an inner diameter IDOS and an annular inner shell that includes a second flange that defines an outer...
8763401 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...
8745989 Reverse flow ceramic matrix composite combustor  
A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor...
8707708 3D non-axisymmetric combustor liner  
A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The...
8707706 Combustion chamber  
A combustion chamber includes at least one annular wall. The annular wall includes a plurality of segments and each segment has a first portion, a second portion and a third portion. The first...
8661829 Aerodynamic shroud for the back of a combustion chamber of a turbomachine  
An annular shroud (42), having an internal face intended to cover the back end wall (33) of an annular combustion chamber (12) of a turbomachine (14) fitted with a centrifugal compressor, together...
8646279 Segment component in high-temperature casting material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for the manufacture of an annular combustion chamber  
The present invention relates to a segment component in high-temperature casting material for an annular combustion chamber of an aircraft engine, characterized by a combustion-chamber wall which...
8590313 Precision counter-swirl combustor  
A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The...
8511099 Combustor system  
A combustor system is provided for a gas turbine engine. The combustor system includes an annular combustion chamber, and outer and inner casings housing the combustion chamber. The outer casing...
8505304 Fuel nozzle detachable burner tube with baffle plate assembly  
A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube...
8495881 System and method for thermal control in a cap of a gas turbine combustor  
A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle...
8474268 Method of mitigating undesired gas turbine transient response using event based actions  
A method of managing transient events regularly seen during gas turbine operation that may cause undesirable operation and hardware damage. During certain transient operations, a lag may be seen...
8474267 Radial turbine engine floating ring seal  
A turbo machine is provided that includes a turbine nozzle having a wall. The wall provides spaced apart first and second surfaces. A combustor includes a liner having an annular lip that engages...
8448417 Pistonless, rotary internal combustion engine and associated support systems  
A stationary crankshaft, cylindrical rotor, low friction, adjustable timing, pistonless, rotary internal combustion engine. A cylindrical rotor rotates freely about a stator, also cylindrical in...
8438858 Rotational system for an expendable gas turbine engine  
A rotational system for a miniature gas turbine engine includes a rotor shaft rotationally mounted to a forward bearing and an aft bearing. The rotor shaft is located axially with a single...
8438852 Annular ring-manifold quaternary fuel distributor  
A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through...
8438853 Combustor end cap assembly  
A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate...
8434313 Thermal machine  
A thermal machine, especially a gas turbine, includes an annular combustor which is outwardly delimited by an outer shell and an inner shell (33) and through which a hot gas axially flows. The...
8387394 Gas-turbine burner  
A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of...
8381526 Systems and methods of providing high pressure air to a head end of a combustor  
A combustor includes a first flow path and a second flow path. The first flow path places a diffuser in indirect fluid communication with a combustor cap assembly by way of an intervening lower...
8376700 Compressed air starter for turbomachine  
An air starter for turbomachine, including a forward casing, an aft casing, an annular exhaust flow path opening up between an aft end of the forward casing and a forward end of the aft casing,...
8272220 Impingement cooling plate for a hot gas duct of a thermal machine  
A thermal machine including a wall defining a hot gas duct for transferring a hot gas stream and a cooling jacket disposed at a distance from the wall on an outside of the hot gas duct so as to...
8261555 Injection nozzle for a turbomachine  
A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the...
8234872 Turbine air flow conditioner  
A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular...
8215118 Optimizing the angular positioning of a turbine nozzle at the outlet from a turbomachine combustion chamber  
A turbomachine including an annular combustion chamber fitted with fuel injectors and nozzle vanes arranged at the outlet from the chamber, the number of nozzle vanes being an integer multiple of...
8171737 Combustor assembly and cap for a turbine engine  
A combustor assembly for a turbine engine includes a cap assembly which gradually increases the volume of compressed air provided to the combustor assembly, and which slows the compressed air in a...
8171740 Annular rich-quench-lean gas turbine combustors with plunged holes  
A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second...
8171736 Combustor with chamfered dome  
A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a...
8161750 Fuel nozzle for a turbomachine  
A turbomachine includes a compressor, a turbine, and a combustor operatively connected to the turbine. The turbomachine further includes a cap member mounted to the combustor. The cap member...
8156744 Annular combustion chamber for a gas turbine engine  
An annular gas turbine engine combustion chamber including an outer wall and an inner wall connected by a wall forming the chamber bottom is disclosed. The walls delimit sources of combustion with...
8146365 Fuel nozzle providing shaped fuel spray  
A fuel injection nozzle for a gas turbine engine has a central fuel ejection nozzle and a plurality of airflow passages within the spray tip that include a first and second group of...
8146372 Gas turbine combustion chamber having inner and outer walls subdivided into sectors  
An annular combustion chamber has an inner wall and an outer wall of ceramic matrix composite material, together with a chamber end wall that is connected to the inner and outer walls....
8141371 Gas turbine combustion chamber made of CMC material and subdivided into sectors  
An assembled annular combustion chamber comprises an annular inner wall and an annular outer wall made of ceramic matrix composite material together with a chamber end wall connected to the inner...
8141365 Plunged hole arrangement for annular rich-quench-lean gas turbine combustors  
A combustor may include an outer liner having a first row and a second row of circumferentially distributed air admission holes. The second row of the outer liner may be downstream of the first...
8132417 Cooling of a gas turbine engine downstream of combustion chamber  
A gas turbine system includes a combustion chamber (2), a turbine (3), a radially inward and/or radially outward axial gap (4; 16, 17) between the combustion chamber (2) and the turbine (3), at...
8127551 Turbomachine with a diffuser  
A turbomachine including an annular combustion chamber, a centrifugal compressor, an annular diffuser enabling the flow of gas leaving the compressor to be diffused and directing this flow of gas...
8113003 Transition with a linear flow path for use in a gas turbine engine  
A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have an internal passage...
8104284 Combustor and a fuel supply method for the combustor  
A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The, air hole plate includes a plurality of rows disposed...
8091362 Fuel injector sans support/stem  
A fuel nozzle is provided. The fuel nozzle includes a heat shield, a fuel tube and a plurality of support members. The support members are radially interposed between the heat shield and the fuel...
8091365 Canted outlet for transition in a gas turbine engine  
A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine has an internal passage from an inlet to an outlet. The outlet may...
8065881 Transition with a linear flow path with exhaust mouths for use in a gas turbine engine  
A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have an internal passage...
8056346 Combustor  
A combustor includes a first wall, a second wall, an injector grommet, a combustor longitudinal axis, and a connection assembly indirectly connecting the first wall to the second wall. A portion...
8056343 Off center combustor liner  
The present application provides a liner for a combustor. The combustor liner may include a mouth, a passage for a flow of fuel, a passage for a flow of air, a first zone for mixing the flow of...
8042339 Lean direct injection combustion system  
The present invention is directed to a lean direct injection (LDI) combustion system for a gas turbine using a shell and tube heat exchanger concept to construct a shell and tube lean direct...

Matches 1 - 50 out of 353 1 2 3 4 5 6 7 8 >