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Match Document Document Title
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 row...
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 of...
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...
8037691 Deflector for a combustion chamber endwall, combustion chamber equipped therewith and turbine engine comprising them  
A deflector takes the form of a plate provided with a hole. The plate is a portion of a conical surface of revolution about a cone axis with a concave face and a convex face. The plate includes a...
8028530 Device for attaching a combustion chamber  
A turbomachine including an annular combustion chamber is disclosed. The combustion chamber includes a radially inner wall and a radially outer wall exhibiting symmetry of revolution. An annular...
8015829 Combustor  
A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one...
8001793 Gas turbine engine reverse-flow combustor  
A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple...
7971439 Annular turbomachine combustion chamber  
An annular turbomachine combustion chamber comprising an inner wall, an outer wall, and a chamber end wall disposed between said inner and outer walls in the upstream region of said chamber, the...
7966818 Gas turbine combustion chamber with fuel injection over an entire combustion chamber annulus  
A gas turbine combustion chamber includes an annular combustion chamber (3) confined by an outer (1) and an inner combustion chamber wall (2) and is provided with several fuel injection nozzles...
7966832 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 of...
7954327 Chamber endwall, method of producing it, combustion chamber comprising it, and turbine engine equipped therewith  
A combustion chamber which includes a chamber endwall which takes the form of a substantially frustoconical component including a succession of adjacent planar portions is disclosed. The invention...
7950233 Combustor  
A combustor is provided having one or more apertures adapted to asymmetrically introduce air adjacent the fuel nozzles to reduce smoke resulting from unburned hydrocarbons in a gas turbine engine...
7886545 Methods and systems to facilitate reducing NOx emissions in combustion systems  
A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer...
7856830 Noise reducing combustor  
A combustor having liners with a plurality of angled effusion holes defined therethrough at a first angle with respect to a surface of the liners and at a second angle with respect to a...
7856826 Combustor dome mixer retaining means  
A method of assembling a combustor for use in a turbine engine is disclosed. The method includes providing a dome assembly ring including a plurality of assembly ring openings, positioning a...
7854126 Annular combustion chamber with a removable end wall  
A one-piece combustion chamber having an end wall subdivided into sectors. The combustion chamber comprises a chamber end wall interconnecting the inner and outer walls, and it includes windows...
7849696 Assembling an annular combustion chamber of a turbomachine  
An annular combustion chamber comprising axial walls interconnected by a chamber end wall having a coefficient of thermal expansion that is different from that of the axial walls, the chamber end...
7775051 Arrangement for a jet engine combustion chamber  
The combustion chamber includes a chamber endwall perforated by at least one passage hole. An injection system is mounted so that it can slide diametrically with respect to the passage hole. A...
7762083 Gas turbine plant and gas turbine power generator plant  
In a gas turbine plant and a gas turbine power generator plant, as a device of reducing the heat transfer from the gas turbine to the compressor, for instance, an air flow path for circulating part...
7703290 Air thrust bearing for a gas turbine engine  
A gas turbine engine comprises a rotary compressor (6) which is subject to forward thrust forces and is mounted on an axial shaft (50) which has a forward facing surface (67) located in a thrust...
7690896 Gas turbine disk slots and gas turbine engine using same  
A gas turbine engine comprises a compressor section, a combustion section disposed downstream from the compressor section, and a turbine section disposed downstream from the combustion section. The...
7673457 Turbine engine combustion chamber with tangential slots  
A turbine engine annular combustion chamber, including longitudinal walls connected by a transverse chamber bottom and a single-piece cowling, the chamber bottom and the cowling each including an...
7637111 Easily demountable combustion chamber with improved aerodynamic performance  
The component elements of a jet engine combustion chamber are assembled together in a manner that is designed to facilitate maintenance while also improving aerodynamic performance. In an...
7628020 Combustor with improved swirl  
A combustor having a combustor wall with a plurality of angled effusion holes defined therethrough. The tangential component of the hole direction of the effusion holes corresponds to a same...
7624577 Gas turbine engine combustor with improved cooling  
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...
7549294 Turbomachine with angular air delivery  
A turbomachine assembly comprising: an annular compression section; a casing formed by an outer annular shell (204) and an inner annular shell (206) secured inside the outer shell by means of a...
7546737 Segmented effusion cooled gas turbine engine combustor  
A combustor includes two or more sets of effusion cooling holes that extend through the inner and outer liners. Each set of effusion cooling holes includes one or more initial rows of effusion...
7546736 Methods and apparatus for low emission gas turbine energy generation  
A low-emission method for producing power using a gas turbine includes premixing a plurality of fuel and air mixtures, injecting the fuel and air mixtures into a combustion chamber using a...
7536862 Fuel nozzle for gas turbine engines  
A gas turbine engine fuel nozzle includes an axis of symmetry extending therethrough, the nozzle body including a first passage extending coaxially therethrough, a second passage, and a third...
7509813 Combustor heat shield  
A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield.
7412834 Annular combustion chamber for a turbomachine with an improved inner fastening flange  
An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and...
7328582 Annular combustion chamber for a turbomachine  
An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section...
7318317 Combustion chamber for a gas turbine  
A combustion chamber 10 for a gas turbine that operates in a highly diluted mode of combustion has a substantially toroidal plenum 30. At least one combustion fluid injector is located at the...
7269958 Combustor exit duct  
A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall...
Matches 1 - 50 out of 322 1 2 3 4 5 6 7 >