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Patent Searching and Data


Matches 701 - 750 out of 12,739

Document Document Title
WO/2015/047509A3
A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine ...  
WO/2015/047472A3
A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side ...  
WO/2015/046097A1
In order to prevent combustion vibration in a gas turbine combustor using a liquid fuel by means of a simple configuration having high cost performance, this gas turbine combustor (1) is equipped with a pilot burner (3) arranged in the c...  
WO/2015/047472A2
A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side ...  
WO/2015/045905A1
This fuel system (1A) is provided with: a constant volume pump (2i) and a centrifugal pump (2a) that pressurize and discharge a fuel (N) that is supplied to an aircraft engine (E); a calculation control means (4) that is configured so as...  
WO/2015/044413A1
The invention relates to a heat shield (20, 40) with a support structure (22) and a number of heat shield blocks (24, 42, 44, 56, 56a) which are arranged substantially over the entire surface of the support structure such that expansion ...  
WO/2015/047509A2
A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine ...  
WO/2015/043786A1
A burner for combustion a combustion mixture is provided. The burner comprises at least one burner body with at least one cooling element for cooling the burner body and at least one premixing element for mixing a fluidic combustion comp...  
WO/2015/042237A1
Regenerative burner for non-symmetrical combustion and a method of firing the burner. The burner includes a burner housing enclosing a burner plenum; a fuel conduit extending longitudinally within the housing and positioned coaxial with ...  
WO/2015/040228A1
The invention relates to a burner (24) for a gas turbine (1), having at least one air passage (26) which can be charged with compressor air, at least one fuel passage (28) which can be charged with at least one fuel gas, wherein the two ...  
WO/2015/038268A1
A can-annular gas turbine engine combustion arrangement (10), comprising: an outer casing (24) and a rotor casing (26) defining a plenum (22) there between; a diffuser configured to exhaust compressed air into the plenum (22); a turbine;...  
WO/2015/038256A1
A combustor panel an increased cooling holes provided at at least one of a pair of circumferential edges, a leading edge, a trailing edge or a hole circumference. The increase may be defined as a reduction in spacing or an increase in de...  
WO/2015/038274A1
A combustor liner assembly of a gas turbine engine comprises a dome (42) having a central axis aligned with an engine axis, the dome arranged at an inlet end (32) of a combustor (16), a first spring (70) disposed at a radially outward po...  
WO/2015/038245A1
Technologies are provided for applying energy to a combustion reaction. For example, a method may include supporting a combustion reaction; applying energy to the combustion reaction via one or more control signals; detecting a change in...  
WO/2015/039074A1
A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impinge...  
WO/2015/038293A1
A combustor includes a liner and a support. The liner includes first and second spaced apart liner walls defining a combustion chamber therebetween, and an end wall joining the first and second liner walls at a forward end. The support i...  
WO/2015/038232A1
A liner panel for a combustor of a gas turbine engine includes a rail which at least partially defines an impingement cavity. The rail includes a notch which faces toward the impingement cavity. A method of cooling a wall assembly within...  
WO/2015/036703A1
The invention relates to a method (1000) for monitoring a degree of coking at dynamic seals of a turbine engine comprising: a gas generator including a rotary shaft and an injection wheel mounted on the shaft; a fuel injection manifold d...  
WO/2015/039075A1
A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a...  
WO/2015/036430A1
The invention relates to a heat shield element (22) for a heat shield having a support structure (24). The heat shield element (22) comprises a hot side (26) which can be exposed to hot gas, a cold side (28) opposite the hot side (26), a...  
WO/2015/038259A1
A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface i...  
WO/2015/037295A1
Provided is a multi-fuel-supporting gas-turbine combustor that maintains excellent low-emission performance by premixed combustion with a main burner, and that combusts hydrogen gas with a reheating burner at low NOx. This gas-turbine co...  
WO/2015/034133A1
The present invention provides a gas turbine combustion instability control device, which is combustion instability device for controlling the operation of a gas turbine by measuring the combustion dynamics of the gas turbine, and the de...  
WO/2015/034861A1
A heat shield for a combustor includes a ring shaped body including a central opening defining a radially inner edge of the ring shaped body. The ring shaped body is at least partially made of a ceramic material. The heat shield includes...  
WO/2015/033786A1
A fuel supply system for a gas turbine engine is provided with: a confluence passage (19) connected to a combustion nozzle (11); a first pump (P1) for discharging fuel into the confluence passage (19); a first electric motor (M1) for dri...  
WO/2015/032650A1
The invention relates to a tubular combustion chamber (22) for a gas turbine (1) having a combustion chamber head end (24), on which at least one first burner arrangement (11, 26) is arranged, a substantially cylindrical flame tube (28),...  
WO/2015/032936A1
The invention relates to a combustion chamber (10) for a gas turbine (1), having at least one housing component (33) with a housing wall (23) which is arranged around a hot-gas path and which comprises a hot side (25), which can be charg...  
WO/2015/030928A1
A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a...  
WO/2015/031823A1
A fuel supply manifold for a gas turbine engine includes a first manifold segment includes a first multiple of double-barrel fittings in communication with a primary fuel circuit and a secondary fuel circuit. A second manifold segment in...  
WO/2015/031816A1
A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A...  
WO/2015/030927A1
A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than...  
WO/2015/026760A1
In various embodiments, a dual fuel nozzle (200) for use in a gas turbine engine is provided. The nozzle may be configured to supply and gas and a liquid. The dual fuel nozzle (200) may include an interior wall (217). The interior wall (...  
WO/2015/025109A1
The invention relates to a system for injecting fuel into a combustion chamber of an engine, comprising at least two fuel circuits, one with a constant flow rate (1) and the other with an intermittent flow rate (2), members (4, 5) for do...  
WO/2015/024139A1
Disclosed is a centrifugal conical-spray atomization device. The head portion of a needle valve (5) in a needle valve body (1) is provided with a throttling guidance cone (13); a seat surface (16) of the needle valve (5) mates a seat sur...  
WO/2015/023042A1
The present invention relates to a swirler. A swirler according to an embodiment of the present invention comprises: a casing; a pilot body placed inside the casing; and a plurality of vanes arranged along the periphery of the pilot body...  
WO/2015/022222A1
The invention relates to a heat shield (30) for a combustion chamber (25). The heat shield comprises a support structure (32), a number of heat shield elements, and at least one Helmholtz resonator (48), wherein the heat shield elements ...  
WO/2015/023576A1
One exemplary embodiment of this disclosure relates to a gas turbine engine including a plate, a frame attached to the plate, and a panel. The panel is supported by the frame.  
WO/2015/023339A2
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmenta...  
WO/2015/023733A1
An apparatus (8) for dampening acoustic pressure oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor (14). The apparatus (8) includes at least one resonating tube (10) with a closed end, an ...  
WO/2015/023764A1
A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages...  
WO/2015/023339A3
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmenta...  
WO/2015/023863A1
A fuel injector is provided for a gas turbine engine. The fuel injector includes a fuel conduit and a cooling fluid circuit through a strut. A gas turbine engine is provided that includes a multiple of fuel injectors in communication wit...  
WO/2015/017427A1
A heat shield for a combustion chamber of a gas turbine engine is disclosed. The heat shield includes a plate portion, an inner ring, and a plurality of standoffs. The plate portion includes an annular sector shape. The inner ring extend...  
WO/2015/017084A1
A combustor may include a nonmetallic combustor body configured to hold a combustion reaction and one or more electrodes disposed outside the nonmetallic combustor body and configured to apply an electric field, an electric field effect,...  
WO/2015/017454A1
In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through...  
WO/2015/017002A2
A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged t...  
WO/2015/017002A3
A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged t...  
WO/2015/017180A1
A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor section. The combustor includes a combustor region defined by...  
WO/2015/016995A3
An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators...  
WO/2015/017078A1
A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to ...  

Matches 701 - 750 out of 12,739