|
Match
|
Document |
Document Title |
|
|
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...
|
|
|
7617688 |
Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas stream, annular wall forming a cap of the upstream fairing of the chamber, and gas turbine engine with the chamber
The present invention is concerned with an annular combustion chamber of a gas turbine engine with an external annular wall and an internal annular wall, including an upstream fairing for...
|
|
|
7617684 |
Impingement cooled can combustor
A can combustor includes a generally cylindrical housing having an interior, an axis, and a closed axial end. The closed axial end includes means for introducing fuel to the housing interior. A...
|
|
|
7614235 |
Combustor cooling hole pattern
A combustor assembly includes an inner and outer liner defining a combustion chamber. The inner and outer liners include a plurality of cooling holes spaced a specified distance apart. The cooling...
|
|
|
7614234 |
Turbomachine combustion chamber with helical air flow
The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area,...
|
|
|
7600370 |
Fluid flow distributor apparatus for gas turbine engine mid-frame section
A plenum ( 210 ) in a gas turbine engine mid-frame section ( 200 ) comprises one or more annular flow splitters ( 240 ) spaced from an inboard annular wall ( 232 ) that partition air flow flowing...
|
|
|
7594401 |
Combustor seal having multiple cooling fluid pathways
A combustor for a gas turbine includes a first combustor component and a second combustor component. The second combustor component is at least partially insertable into the first combustor...
|
|
|
7584620 |
Support system for transition ducts
Aspects of the invention relate to a system for supporting the exit end of a transition duct. The system includes a plurality of support ring segments that collectively form an annular support ring...
|
|
|
7581923 |
Gas turbine engine with purge air pump and guide
A pump/flow guide is positioned in a gas turbine engine and attached to a transition duct to face a turbine disk. The pump/flow guide provides a smooth path for guiding purge flow to resist the...
|
|
|
7578134 |
Methods and apparatus for assembling gas turbine engines
A method for assembling a gas turbine engine is provided. The method includes providing a combustor liner support including a first portion formed with a plurality of circumferentially-spaced...
|
|
|
7574865 |
Combustor flow sleeve with optimized cooling and airflow distribution
Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. The flow sleeve can be configured to optimize cooling and airflow distribution. The flow sleeve can include...
|
|
|
7571611 |
Methods and system for reducing pressure losses in gas turbine engines
A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an...
|
|
|
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...
|
|
|
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...
|
|
|
7540156 |
Combustion liner for gas turbine formed of cast nickel-based superalloy
A combustion liner for a gas turbine combustion system is provided. The combustion liner comprises a combustion zone between an inlet end and an exhaust end. The combustion liner comprises a...
|
|
|
7540155 |
Thermal shield stone for covering the wall of a combustion chamber, combustion chamber and a gas turbine
A thermal shield stone for covering the wall of a combustion chamber. The stone includes a hot side which can be exposed to a hot medium and a wall side which is arranged opposite the hot side. A...
|
|
|
7524167 |
Combustor spring clip seal system
Aspects of the invention are directed to a sealing system for the interface between a combustor liner and transition duct. The system includes a spring clip seal. A first end of the spring clip...
|
|
|
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.
|
|
|
7500364 |
System for coupling flow from a centrifugal compressor to an axial combustor for gas turbines
A system is provided for aerodynamically coupling air flow from a centrifugal compressor to an axial combustor. The system includes a diffuser, a deswirl assembly, combustor inner and outer annular...
|
|
|
7493767 |
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 turbulators arranged in an array axially along a length...
|
|
|
7481037 |
Cooling structure of gas turbine tail pipe
A plate spring 6 having a hook-shaped cross section from the lower part is installed in the neighborhood of one end “b” of an impingement-cooling plate 4 . One end “c” on the lower side...
|
|
|
7461719 |
Resonator performance by local reduction of component thickness
Aspects of the invention are directed to a system for improving the damping performance of an acoustic resonator. According to aspects of the invention, a resonator, such as a Helmholtz resonator,...
|
|
|
7441409 |
Combustor liner v-band design
A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a...
|
|
|
7421842 |
Turbine spring clip seal
An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner...
|
|
|
7415827 |
Arrangement for controlling fluid jets injected into a fluid stream
In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with...
|
|
|
7415826 |
Free floating mixer assembly for combustor of a gas turbine engine
A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a...
|
|
|
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...
|
|
|
7395669 |
Gas turbine engine combustor
A combustor for a gas turbine engine comprising at least one combustor air intake chute wherein at least one of the air intake chutes is configured to enhance the heat transfer relationship between...
|
|
|
7389643 |
Inboard radial dump venturi for combustion chamber of a gas turbine
A double wall venturi chamber having a converging section, a diverging section and a cylindrical section wherein said chamber defines a venturi zone in which compressed air, fuel and combustion...
|
|
|
7386980 |
Combustion liner with enhanced heat transfer
A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a...
|
|
|
7377117 |
Transition piece for gas turbine
As used to connect a combustor of a gas turbine to a stage of the gas turbine, a transition piece has a generally tubular body, an inlet to receive hot gases from the combustor, and an outlet to...
|
|
|
7377116 |
Gas turbine combustor barrier structures for spring clips
A barrier structure ( 302 ) blocks exit of spring clip fragments ( 317 ) that may break off from a spring clip assembly disposed between a gas turbine engine combustor ( 300 ) and a transition...
|
|
|
7373778 |
Combustor cooling with angled segmented surfaces
A combustor liner for a gas turbine includes a body having a plurality of angled strips on an outside surface of the combustor liner. The plurality of angled strips are arranged in an array about...
|
|
|
7373774 |
Enhanced performance torroidal coolant-collection manifold
A system for cooling a combustion chamber of an engine, such as a rocket engine, is provided. The system has a plurality of coolant tubes or passages surrounding the combustion chamber, a torroidal...
|
|
|
7373772 |
Turbine combustor transition piece having dilution holes
A transition piece body, having an inlet end for receiving combustion products from a turbine combustor and an outlet end for flowing the gaseous products into a first stage nozzle, has dilution...
|
|
|
7363763 |
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...
|
|
|
7360364 |
Method and apparatus for assembling gas turbine engine combustors
A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein...
|
|
|
7350619 |
Auxiliary power unit exhaust duct with muffler incorporating an externally replaceable acoustic liner
Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a...
|
|
|
7350360 |
Annular combustor for a gas turbine
The invention relates to an annular combustor ( 13 ) for a gas turbine ( 10 ), into which combustor ( 13 ) burners ( 14, 15 ) open on an inlet side, and which combustor ( 13 ) extends in the axial...
|
|
|
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...
|
|
|
7328580 |
Chevron film cooled wall
A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and...
|
|
|
7322196 |
Combustion chamber for combusting a combustible fluid mixture
A combustion chamber ( 1 ) for combusting a combustible fluid mixture having a burner ( 2 ) disposed on the combustion chamber ( 1 ) and a method for cooling a combustion chamber ( 1 ). A fixing...
|
|
|
7310952 |
Methods and apparatus for attaching swirlers to gas turbine engine combustors
A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a...
|
|
|
7310938 |
Cooled gas turbine transition duct
A transition duct ( 40 ) for a gas turbine engine ( 10 ) incorporating a combination of cooling structures that provide active cooling in selected regions of the duct while avoiding cooling of...
|
|
|
7308794 |
Combustor and method of improving manufacturing accuracy thereof
An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and...
|
|
|
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...
|
|
|
7299618 |
Gas turbine combustion apparatus
A gas turbine combustion apparatus has a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each combustor comprising a combustor...
|
|
|
7299617 |
Combustion chamber intermediate part for a gas turbine
This invention relates to a gas turbine having a combustion chamber arrangement and a turbine chamber connected downstream of said combustion chamber arrangement, wherein the combustion chamber...
|
|
|
7278254 |
Cooling system for a transition bracket of a transition in a turbine engine
A heat shield for a transition of a turbine engine for coupling a transition component of a turbine engine to a turbine vane assembly to direct combustor exhaust gases from the transition into 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...
|