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Matches 1 - 50 out of 8,751

Document Document Title
WO/2019/104614A1
Disclosed is an oxidant-mutifuel burner capable of being used for solid fuel and gas fuel, the burner including: a flameproof unit (10), a metal member (20), a fuel-oxidant supply system (11) including a fuel burner and several fuel-oxid...  
WO/2019/104375A1
The present invention in one aspect is directed to an autonomous vehicle energy replenishment system (10) comprising: 1. a source of renewable ammonia (14); 2. an electricity generating module (16) operatively coupled to and fuelled by a...  
WO/2019/104417A1
A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal an...  
WO/2019/102156A1
The autonomous device (100) for providing electricity comprises: a storage tank (105) for liquefied natural gas (hereinafter "GNL") comprising a GNL supply inlet (110), a means (115) for the combustion of GNL provided by the storage tank...  
WO/2019/098836A1
When the temperature of ambient air is relatively low, thermal output and thermal efficiency of a micro gas turbine (1) decrease. In order to compensate for the loss of thermal efficiency, the micro gas turbine (1) is equipped with a val...  
WO/2019/088107A1
Provided are a combustor and a combustion method with which it is possible to inhibit generation of nitrogen oxides. A combustor (10) provided with: a first wall (13A) forming a combustion chamber (12); a fuel injection nozzle (11) which...  
WO/2019/084208A1
A bottoming cycle power system includes an expander disposed on a crankshaft. The expander being operable to receive a flow of exhaust gas from a combustion process and to rotate the crankshaft as the exhaust gas passes through. An absor...  
WO/2019/063635A1
The invention concerns a turbine exhaust casing (TEC) for a gas turbine engine in which portions of the inner surface of the casing against which exhaust gas flows are provided with recesses extending into the surfaces. The recesses are ...  
WO/2019/059888A1
An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives...  
WO/2019/057512A1
A gas turbine engine system is equipped with a tempering system for a selective catalyst reduction system. The subject tempering system for a selective catalyst reduction system comprises a tempering compartment equipped with a plurality...  
WO/2019/045997A1
A disc turbine engine with a multi disc engine where each disc engine includes a turbine blade, a low-pressure compressor blade, a high-pressure compressor blade, and a bearing. Each disc engine runs freely and individually, counter-rota...  
WO/2019/043556A1
The present disclosure provides systems and methods for power production. In particular, the systems and methods utilize the addition of heat to an expanded turbine exhaust stream in order to increase the available quantity of heat for r...  
WO/2019/037816A1
The invention relates to a jet engine, which has a stationary housing, in which housing a primary flow is formed, in which inflowing air is burned in at least one combustion chamber, and in which housing a secondary flow is formed, in wh...  
WO/2019/035774A1
A chamber rotary combustion engine constituted by a static and a moving part, wherein the static part is formed by an engine block with a cylindrical annulus case (1), a casing (2) with openings (2a), wherein the bearings (3) for mountin...  
WO/2019/015925A1
The invention relates to a method for improving the performance of a gas turbine (1), in which a hub (6) annually surrounding a rotor (2) is machined when the rotor (2) is in the non-stacked state and hot shield elements that are arrange...  
WO/2019/006352A1
Effluent water is combined with carbon dioxide sourced from a carbon dioxide- containing emission stream to produce a reaction solution. The pH of the reaction solution is controlled to induce precipitation of a carbonate salt from the r...  
WO/2018/236838A2
The disclosed embodiments concern methods, apparatus, and systems for providing differential diagnosis of autoimmune diseases including, Systemic Lupus Erythematosus (SLE) and Rheumatoid Arthritis (RA). The disclosed embodiments provide ...  
WO/2018/236449A1
The present invention is a centrifuge to be used for removing ice particles from the air fed to a gas turbine system. In an embodiment, the centrifuge is comprised of three ducts defining an air-path which comprises of two bends greater ...  
WO/2018/234684A1
This arrangement comprises two turboshaft engines (10, 20) interwoven so as to exchange thermal energy by heat exchangers (16, 26) which improve their efficiency, without greatly increasing head losses since the pipes (19, 29) imposed to...  
WO/2018/225923A1
A combined power generation apparatus, according to the present invention, comprises: an engine (110); a first flow line (120); a power turbine (113); a turbo charger (115); a second flow line (125); a third flow line (126); a compressor...  
WO/2018/225922A1
A combined power generation apparatus, according to the present invention, comprises: an engine (110); a first flow line (121); a turbo charger (130); a second flow line (122); a third flow line (123); a compressor (211); a first medium ...  
WO/2018/222734A1
Thermal energy storage systems and methods are provided including a bed, a blend of aggregates packed in the bed, and a high-density heat transfer fluid flowing through the blend of aggregates. The blend of aggregates includes rock mater...  
WO/2018/222192A1
An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, wh...  
WO/2018/219254A1
A heat pipe engine, comprising a housing (1), a shaft sleeve (4) disposed in the middle of the housing and fixedly connected with the housing, a spindle (5) disposed in the shaft sleeve through a bearing, and a combustion chamber (6) dis...  
WO/2018/205889A1
In a combustor (10) for a gas turbine, a head end turning scoop (12) is provided associated with at least one premix nozzle (22,24), each scoop (12) being U-shaped and having a first leg (58), a second leg (60), and a curved base portion...  
WO/2018/203941A2
A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main ...  
WO/2018/203941A3
A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main ...  
WO/2018/198932A1
A shaft 13 for turbo chargers comprises a low-strength section 25 set to a breaking strength at which same breaks when a preset prescribed load is applied, said section being in an area between a compressor-side bearing 15 and a compress...  
WO/2018/197856A1
The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid...  
WO/2018/186925A3
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine...  
WO/2018/187731A1
Re-lithiation methods and systems are disclosed. Example re-lithiation methods include separating lithium depleted active cathode material from a cathode and introducing lithium containing materials. Also disclosed are re-lithiation elec...  
WO/2018/186925A2
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine...  
WO/2018/180773A1
Provided is a combustion device equipped with: an ammonia supply unit (6) that, by supplying primary reduction ammonia as a nitrogen oxide reducing agent to within a combustor (2) and mixing secondary reduction ammonia with combustion ex...  
WO/2018/181063A1
This combustion device (C) causes the combustion of fuel ammonia and combustion air within a combustion chamber (N), and is equipped with a combustor liner (3a) which forms the combustion chamber, a burner (3c) which is attached to one e...  
WO/2018/180781A1
Provided is a gas turbine (A) using a denitration catalyst and ammonia as a reducing agent for the denitration of combustion gas, wherein the ammonia is supplied, along with cooling air supplied from a compressor (1), to turbine vanes (3...  
WO/2018/180996A1
This combustion device uses compressed combustion air to cause the combustion of fuel ammonia within a combustion chamber, and is equipped with a combustion air cooling unit (6) that cools the combustion air by means of heat exchange wit...  
WO/2018/181030A1
This combustion device (C) is equipped with a compressor (2a) for compressing combustion air, a combustor (2b) for causing the combustion of fuel ammonia and the compressed combustion air, and an ammonia injection unit (3) for injecting ...  
WO/2018/181002A1
This combustion device (C) is provided with a combustor (3) for causing the combustion of fuel ammonia and combustion air within a combustion chamber (N), and the combustor is equipped with a cooling ammonia supply unit (3g) for mixing t...  
WO/2018/180984A1
This combustion device uses combustion air to cause the combustion of fuel ammonia within a combustor (2), and is equipped with a catalyst reduction unit (4) for reducing nitrogen oxides in combustion exhaust gas supplied from the combus...  
WO/2018/178565A1
A device for temporarily increasing power (13) for increasing the power of at least one first turbomachine (5A) and at least one second turbomachine (5B), said device comprising a coolant reservoir (14), a first injection circuit (16A), ...  
WO/2018/173122A1
This combustor 20 comprises a tubular combustor liner 70, and a fuel nozzle 21A that is provided to one end of the combustor liner 70 and that sprays fuel and an oxidant into the combustor liner. The fuel nozzle 21A is provided with a pl...  
WO/2018/173012A1
A micro-combustion device (1) for the generation of electrical power, capable of raising the global performance of the system, with greater compactness and fewer losses by exploiting the principles of a combustion chamber with induced he...  
WO/2018/168747A1
Provided is a combustor nozzle equipped with a nozzle main body (2) extending along an axis, said nozzle main body (2) being equipped with: a first fuel passage (21) formed along the axis (Am) and through which a first fuel (F1) flows; f...  
WO/2018/169578A2
The present disclosure is directed to a method of operating a gas turbine engine with an interdigitated turbine section. The engine includes a fan rotor, an intermediate pressure compressor, a high pressure compressor, a combustion secti...  
WO/2018/169578A3
The present disclosure is directed to a method of operating a gas turbine engine with an interdigitated turbine section. The engine includes a fan rotor, an intermediate pressure compressor, a high pressure compressor, a combustion secti...  
WO/2018/167223A1
The installation (10) comprises: – at least one air-cooled heat exchanger (22), the air-cooled heat exchanger (22) comprising a tube bundle capable of accepting a flow (24) that is to be cooled, and a fan capable of causing a flow of a...  
WO/2018/162994A1
The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a pow...  
WO/2018/164775A1
A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an ...  
WO/2018/156262A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial center...  
WO/2018/156235A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial center...  

Matches 1 - 50 out of 8,751