|| List of recent Gas Turbine-related patents
|Rotor disc with fluid removal channels to enhance life of spindle bolt|
A rotor disc configured to reduce the likelihood of fractures developing in spindle bolts in gas turbine engines is disclosed. The spindle bolts extend axially through the rotor disc to retain the rotor assembly in place in the gas turbine engine.
|Airfoil for gas turbine, blade and vane|
The invention relates to an airfoil for a gas turbine, which comprises a compound fillet disposed between the airfoil and a platform. The compound fillet consists of a first arc and a second arc.
|Ni based forged alloy, and turbine disc, turbine spacer and gas turbine each using the same|
The ni based forged alloy has a composition containing, on the basis of mass percent, al: 0.5 to 1.0%, cr: 17 to 21%, fe: 17 to 19%, nb: 4.5 to 5.5%, ti: 0.8 to 1.3%, w: 3.0 to 6.0%, b: 0.001 to 0.03%, c: 0.001 to 0.015%, and mo: 1.0% or less, the balance being ni and inevitable impurities. The alloy includes carbide grains of the contained elements.
|Turbine casing having reinforcement elements in the containment area|
A turbine casing (100) for a gas turbine, having a casing section (5a, 5b, 5c, 5d, 5e), the casing section (5a, 5b, 5c, 5d, 5e) having a containment section (16) for containing blade fragments expelled radially outward. The casing section (5a, 5b, 5c, 5d, 5e) has a first reinforcing element (1a, 1b, 1c, 1d, 1e) which is joined in face-to-face contact with the radially inner and/or outer surface of the casing section (5a, 5b, 5c, 5d, 5e)..
|Method and device for operating a smelting reduction process|
In a method and a device for operating a smelting reduction process, at least part of an export gas from a blast furnace or a reduction unit is thermally utilized in a gas turbine and the exhaust gas of this gas turbine is used in a waste heat steam generator to generate steam. The remaining part of the export gas is fed to a co2 separation apparatus, the tail gas thereby obtained being fed to a waste heat steam generator and burned for additional steam generation.
|Mounting system for mounting engine nacelle components and associated method|
The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connecting the engine structure to the pylon, and a flexible connection provided between the hinged connections and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position..
|Gas turbine engine and electrical system|
One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine.
|Gas turbine power plant with exhaust gas recirculation|
What is described is a method for operating a gas turbine power plant, in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet. What is described, further, is a gas turbine power plant with a gas turbine, the compressor inlet of which is divided into two sectors which the flow duct of the compressor adjoins, a feeder for fresh air being connected to the first sector and a recirculation line for recirculating the first exhaust gas substream being connected to the second sector, and the second sector reaching so close to the compressor that, when the gas turbine is in operation, the static pressure at the outlet of the second sector is so low that the difference between total pressure and static pressure is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet..
|Method of operating a gas turbine power plant with exhaust gas recirculation and corresponding gas turbine power plant|
The invention relates, further, to a gas turbine power plant with a gas turbine having a compressor inlet which is followed by the flow duct of the compressor and which is divided into an inner sector and an outer sector, a feed for an oxygen-reduced gas being connected to the inner sector of the compressor inlet, and a fresh air feed being connected to the outer sector of the compressor inlet.. .
|Shell and tiled liner arrangement for a combustor|
A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell.
|Low calorific fule combustor for gas turbine|
A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the-liner also defining inner primary and intermediate regions of a combustion zone and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes.
|Support frame and method for assembly of a combustion module of a gas turbine|
A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough.
|System and method for sequential injection of reagent to reduce nox from combustion sources|
In a large exhaust duct from a lean burn combustion source, such as a boiler, diesel engine or gas turbine, multiple injectors can be used to inject a reagent, such as an aqueous solution of urea or ammonia, into the exhaust for use in the catalytic reduction of nox in a process known in the art as selective catalytic reduction (scr). When operating at low injection rates, such as during low combustor loads, the injectors are operated individually for short periods of time in a sequential manner..
|Microchannel systems and methods for cooling turbine components of a gas turbine engine|
The present application and the resultant patent thus provide a microchannel system for cooling a hot gas path surface of a turbine. The microchannel system may include a turbine component having an outer surface extending along a hot gas path of the turbine, a microchannel defined within the turbine component and extending about the outer surface, and a number of pockets defined within the turbine component and positioned along the microchannel.
|Gas turbine plant having exhaust gas recirculation|
The invention relates to a gas turbine plant, including a gas turbine device, which has a compressor and at least one burner and at least one gas turbine, a waste heat boiler assembly, which has a boiler inlet side connected to a turbine outlet and a first boiler outlet connected to a flue and a second boiler outlet, and an exhaust gas recirculation, which connects the second boiler outlet to a compressor inlet. A simplified structure can be achieved in that the waste heat boiler assembly has a first boiler exhaust gas path, which is connected to the boiler inlet side and leads to the first boiler outlet, and that the waste heat boiler assembly has a second boiler exhaust gas path, which is connected to the boiler inlet side and leads to the second boiler outlet separately from the first boiler exhaust gas path..
|Gas turbine engine thermal management system|
A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan.
|Probalistic high cycle fatigue (hcf) design optimization process|
A novel probabilistic method for analyzing high cycle fatigue (hcf) in a design of a gas turbine engine is disclosed. The method may comprise identifying a component of the gas turbine engine for high cycle fatigue analysis, inputting parametric data of the component over a predetermined parameter space into at least one computer processor, using the at least one computer processor to build a plurality of flexible models of the component based on the parametric data of the component over the predetermined parameter space, using the at least one computer processor to build a plurality of emulators of the component based on the plurality of flexible models, and using the at least one computer processor to predict a probability of hcf based at least in part on the parametric data of the component over the predetermined parameter space and the plurality of emulators..
|Use of ss data trends in fault resolution process|
An automated method for resolving fault in an engine is disclosed. The method may include providing a reasoner module for recommending a set of maintenance actions to resolve fault in the engine, inputting steady state performance data from the engine into the reasoner module, and using the reasoner module to recommend a set of maintenance actions based at least in part on the steady state performance data.
|Method for manufacturing gas turbine blade, and gas turbine blade|
A third step of applying al coating only into the set al-coating-applying portion.. .
|Turbine segmented cover plate retention method|
An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features.
|Low hub-to-tip ratio fan for a turbofan gas turbine engine|
A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge.
|Gas turbine engine vane assembly and method of mounting same|
The gas turbine engine vane assembly has a vane having an elongated airfoil body extending to a tip and a grommet disposed around the tip. An insert having a closed loop shape with an inner surface matingly shaped to receive the outer surface of the grommet, and an outer surface matingly shaped to be snugly received in the slot.
|Grain microstructure in dampers of gas turbine engine|
A damper for a gas turbine engine is provided. The damper comprises a first portion, a second portion, and a surface.
|Gas turbine with honeycomb seal|
A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30. The turbine 30 includes: a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5a-5c rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5a-5c facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4.
|Geared turbofan engine with integral gear and bearing supports|
A gas turbine engine includes a bearing. A bearing support includes a first wall that extends between the first and second ends and is operatively supported by the bearing at a first end.
|Gas turbine engine and electric machine|
An electric machine is disclosed integrated to rotate with a shaft of a gas turbine engine. In one form the electric machine is integrated with a fan of the gas turbine engine.
|Dampers for fan spinners of aircraft engines|
Dampers for fan spinners of aircraft engines are disclosed. An example fan module for a gas turbine engine may include a fan disk; fan blades mounted to the fan disk and extending radially therefrom; a fan spinner operatively coupled to the fan disk at an axially upstream position; and/or one or more elastic vibration dampers operatively interposing the fan spinner and the fan disk.
|Gas turbine engine heat exchanger system|
An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air.
|System and method for controlling ice formation on gas turbine inlet guide vanes|
Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces.
|Method for closing an aperture on a blade of a gas turbine|
The invention relates to a method for closing an aperture on a blade of a gas turbine, wherein the blade of the gas turbine comprises a tip end with a top surface and a bottom surface. The aperture is formed on the tip end of the blade, and the aperture includes a peripheral edge.
|Dry steam cleaning a surface|
A device and method for cleaning a surface using dry steam is disclosed. A dry steam wand is fitted with a custom nozzle that permits the dry steam to be angled to clean difficult to access surfaces of a gas turbine.
|Gas turbine engine system and an associated method thereof|
A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor.
|Two-shaft gas turbine|
The two-shaft gas turbine includes a power generator 21 having a compressor 11, a combustor 12 and a high-pressure turbine 13; a low-pressure turbine 14 driven by exhaust gas from the high-pressure turbine 13; a generator motor 23 connected to the gas generator 21; and a control unit 24. When either one of a value of the inlet temperature of the high-pressure turbine 13 and a value of the air quantity of the compressor 11 reaches a rated value before the other value reaches a rated value, the control unit 24 drives the generator motor 23 to bring the other value close to the rated value..
|Gas turbine engine and method of operating thereof|
A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine.
|Gas turbine efficiency and regulation speed improvements using supplementary air system continuous and storage systems and methods of using the same|
The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include additional heated compressed air injection, steam injection, water recovery, exhaust tempering, fuel heating, and stored heated air injection..
|Intercooled gas turbine with closed combined power cycle|
A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air.
|Cooled cooling air system for a gas turbine|
In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.. .
|Gas turbine engine fuel system with ecology valve|
A gas turbine engine fuel system has an ecology valve for withdrawing residual fuel from primary and secondary fuel manifolds upon engine shut-down. The ecology valve has primary and secondary reservoirs respectively connected in fluid flow communication with the primary and secondary fuel manifolds.
|Balancing body for a continuous blade arrangement|
The present invention relates to a balancing body (1) for fastening to a ring (4, 5) of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body has a first stop (11) for the form-fitting attachment of the balancing body in one peripheral direction (r) to a first axial shoulder (6; 7) of the ring.. .
|Exhaust diffuser for a gas turbine engine exhaust system|
An exhaust diffuser for a gas turbine engine includes a diffuser inlet, a diffuser exit, an inner diffuser wall, and an outer diffuser wall. The inner diffuser wall may include a first tubular member with a flared downstream portion.
|Conjoined gas turbine interface seal|
A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘l’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer..
|Airfoil cooling circuit|
An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit.
|Oil baffle for gas turbine fan drive gear system|
A turbine engine includes a housing supporting compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear.
|Turbomachine stage and method for detecting a sealing gap of such a turbomachine stage|
A turbomachine stage, in particular a turbine stage or compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, in particular conical, housing in which a rotor blade arrangement having a plurality of rotor blades is disposed which have an outer shroud having at least one radial sealing flange.
|Turbomachine stage and method for determining a seal gap and/or an axial position of such a turbomachine stage|
A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange.
|Noise reducing vane|
A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region.
|Sensor mounting attachment|
A mountable attachment for positioning a sensor in an environment, like a combustion chamber of a gas turbine is disclosed. The mountable attachment includes a mounting member having a hollow elongated configuration for incorporating the sensor therewithin.
|Aircraft using turbo-electric hybrid propulsion system for multi-mode operation|
A vehicle incorporating a hybrid propulsion system. In one form, the vehicle may be an aircraft such that the system includes gas turbine engines as a first motive power source, and one or more battery packs as a second motive power source.