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Gas Turbine patents



      

This page is updated frequently with new Gas Turbine-related patent applications.




Date/App# patent app List of recent Gas Turbine-related patents
07/21/16
20160212360 
 In-situ inspection of power generating machinery patent thumbnailnew patent In-situ inspection of power generating machinery
Thermographic inspection of an internal component (28, 34) of power production equipment (20) by inserting an ultrasound energizer (74a) into an inspection portal of the equipment to contact an exterior of the component, and inserting a camera scope via a second portal into an interior (52, 54) of the component. A motorized drive (66) may mount on a pilot fuel port (58) of a gas turbine to move the scope robotically within a combustor (28) and transition duct (34).
Siemens Energy, Inc.


07/21/16
20160209040 
 Gas turbine combustor and gas turbine engine equipped with same patent thumbnailnew patent Gas turbine combustor and gas turbine engine equipped with same
The liquid fuel-using gas turbine combustor prevents the generation of combustion oscillation. The gas turbine combustor is provided with a pilot burner disposed on the central position of the combustion casing, main burners disposed so as to surround the pilot burner.
Mitsubishi Hitachi Power Systems, Ltd.


07/21/16
20160209038 
 Dual fuel nozzle with swirling axial gas injection for a gas turbine engine patent thumbnailnew patent Dual fuel nozzle with swirling axial gas injection for a gas turbine engine
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots..
United Technologies Corporation


07/21/16
20160209037 
 Dual fuel nozzle with liquid filming atomization for a gas turbine engine patent thumbnailnew patent Dual fuel nozzle with liquid filming atomization for a gas turbine engine
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler..
United Technologies Corporation


07/21/16
20160209036 
 Swirler, fuel and air assembly and combustor patent thumbnailnew patent Swirler, fuel and air assembly and combustor
An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability..
United Technologies Corporation


07/21/16
20160209034 
 Method and  cooling a hot gas wall patent thumbnailnew patent Method and cooling a hot gas wall
A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure.
General Electric Technology Gmbh


07/21/16
20160208926 
 Splined honeycomb seals patent thumbnailnew patent Splined honeycomb seals
A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure.
United Technologies Corporation


07/21/16
20160208818 
 Compressor flowpath patent thumbnailnew patent Compressor flowpath
A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis.
United Technologies Corporation


07/21/16
20160208737 
 System for actuating an exhaust cowl patent thumbnailnew patent System for actuating an exhaust cowl
In various embodiments, a cowl actuation system may comprise a cowl, an actuator, a bell crank, and a guide arm. The cowl may be configured to modulate at least a portion of the exhaust flow of a gas turbine engine.
United Technologies Corporation


07/21/16
20160208717 
 System and  load power management in a turboshaft gas turbine engine patent thumbnailnew patent System and load power management in a turboshaft gas turbine engine
A control system for a gas turbine engine including a power turbine is disclosed. The control system may also include an outer loop control module to determine a torque request.
United Technologies Corporation


07/21/16
20160208716 
new patent

Method for detecting a fault, fault detection system and gas turbine engine


A method for detecting a fault in a gas supply system for a gas turbine engine. The method comprises: measuring a pressure difference between two gas supplying ducts of the gas supply system; comparing the measured pressure difference to a threshold level; and determining a fault based on the measured pressure difference and the comparison..
Rolls-royce Plc.


07/21/16
20160208714 
new patent

Gas turbine engine and blocker door assembly


A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture.
United Technologies Corporation


07/21/16
20160208713 
new patent

Gas turbine engine with high speed and temperature spool cooling system


A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel.
United Technologies Corporation


07/21/16
20160208712 
new patent

Gas turbine engine control for rotor bore heating


A gas turbine engine comprises a compressor rotor including blades and a disk, with a bore defined radially inwardly of the disk, and a combustor. A tap directs the products of combustion first to a valve and then into the bore of the disk.
United Technologies Corporation


07/21/16
20160208705 
new patent

Bore-cooled film dispensing pedestals


A cooling circuit for a gas turbine engine comprises a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity. A second wall is spaced outwardly of the second surface of the first wall to provide at least one second cavity.
United Technologies Corporation


07/21/16
20160208704 
new patent

Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor


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 a therethrough. The effusion passage includes an inlet in an outer periphery of a wall.
United Technologies Corporation


07/21/16
20160208703 
new patent

Overcooled air cooling system with annular mixing passage


A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger.
United Technologies Corporation


07/21/16
20160208701 
new patent

Cooling passages for a mid-turbine frame


A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case.
United Technologies Corporation


07/21/16
20160208698 
new patent

Gas turbine engine thermal management system


The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit..
United Technologies Corporation


07/21/16
20160208697 
new patent

Mid-turbine frame buffer system


A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame.
United Technologies Corporation


07/21/16
20160208695 
new patent

Gas turbine engine inlet


In or for an aircraft turbine engine, the invention comprises a fitting comprising at least one blade, said blade being elongate and being adapted to be located such that it lies across the mouth of the engine inlet in use, such that, in use, the blade shears the air flowing towards it, such that the force of at least a portion of the air flowing into the turbine is reduced, the invention also comprises a housing for a gas turbine engine, comprising a fitting of the invention and wherein the fitting is mounted at the, in use, front of the housing, the front of the housing having an inside periphery, and wherein the fitting is mounted within the inside periphery of the housing,. .

07/21/16
20160208693 
new patent

Power plant having a gas turbine and a hydrogen-cooled generator


A power station having a gas turbine, a generator driven by the gas turbine for generation of electrical power, and a hydrogen cooling circuit for discharging lost heat from the generator, wherein the hydrogen cooling circuit has a feed line for feeding hydrogen from a hydrogen tank into the generator and a discharge line for discharging heated hydrogen from the generator, and wherein the discharge line is connected to a mixing device, such that the heated hydrogen from the discharge line can be mixed with a further fuel and is fed by means of a fuel feed line to the gas turbine.. .
Siemens Aktiengesellschaft


07/21/16
20160208692 
new patent

Gas turbine engine with a multi-spool driven fan


A gas turbine engine includes low and high spools constructed and arranged to rotate about an engine axis. The low spool drives at least one leading stage of a fan section and the high spool drives an aft stage of the fan section.
United Technologies Corporation


07/21/16
20160208690 
new patent

Gas turbine engine split torque fan drive gear system


A gas turbine engine includes a turbine section configured to rotate about an engine axis relative to an engine static structure. A fan section is configured to rotate about the engine axis relative to the engine static structure.
United Technologies Corporation


07/21/16
20160208689 
new patent

Modifying a gas turbine engine to use a high pressure compressor as a low pressure compressor


A method comprises the steps of modifying an existing engine which includes a high pressure compressor driven by a high pressure turbine and a low pressure turbine to drive a low pressure compressor. The modifying step includes utilizing the high pressure compressor as a low pressure compressor in a modified gas turbine engine, and designing and incorporating a new high pressure compressor downstream of the low pressure compressor section in the modified engine, such that a portion of the design of the existing engine is utilized in the modified engine.
United Technologies Corporation


07/21/16
20160208688 
new patent

Inflow radial turbine with reduced bore stress concentration


A gas turbine engine is provided comprising an impeller configured to rotate about an axis. A combustor is in fluid communication with the impeller.
United Technologies Corporation


07/21/16
20160208655 
new patent

Tie rod for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a bolt opening and at least one spoke for connecting an outer frame case to the inner frame case that includes an inlet passage that extends in a radial direction. A central bolt extends through the bolt opening for securing at least one spoke to the inner frame case..
United Technologies Corporation


07/21/16
20160208649 
new patent

Wall for a hot gas channel in a gas turbine


A wall for a hot gas channel in a gas turbine is described, the wall having a back side and a front side and an impingement sheet having impingement cooling holes, the wall being for exposure to a hot fluid at the front side, and the wall having an array of pins attached to the back side and extending between the back side and the impingement sheet, the wall additionally having a plurality of ribs attached to the back side, each rib extending between two pins to delineate an array of cells on the back side, and/or at least one compartment wall attached to the back side to delineate compartments on the back side. Embodiments include an impingement sheet with impingement cooling holes and cooling exit holes.
General Electric Technology Gmbh


07/21/16
20160208648 
new patent

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes at least one spoke for connecting an outer frame case to an inner frame case. At least one spoke includes an inlet passage and at least two branches that extend transverse to the inlet passage..
United Technologies Corporation


07/21/16
20160208647 
new patent

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction..
United Technologies Corporation


07/21/16
20160208646 
new patent

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case.
United Technologies Corporation


07/21/16
20160208644 
new patent

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case.
United Technologies Corporation


07/21/16
20160208642 
new patent

Turbine exhaust cylinder/turbine exhaust manifold bolted full span turbine exhaust flaps


A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface.
Siemens Energy, Inc.


07/21/16
20160208640 
new patent

Gas turbine engine


A fan containment system has a fan case having an annular casing element for encircling an array of fan blades and a hook projecting generally radially inwardly from the annular casing element. An annular fan track liner is positioned substantially coaxial to the annular casing element, and positioned such that a forward end of the fan track liner is axially spaced from the hook so that there is a gap between the hook and the fan track liner.
Rolls-royce Plc


07/21/16
20160208639 
new patent

System and controlling a gas turbine engine


A control system for a gas turbine engine including a power turbine is disclosed. The control system may include a control module to receive engine operating goals and an estimated current engine state, wherein the estimated current engine state is produced by a model-based estimation module using a bandwidth signal produced by an adaptation logic module.
United Technologies Corporation


07/21/16
20160208637 
new patent

Variable vane bushing


A variable vane assembly includes a variable vane, a trunnion arranged on one end of the variable vane, an inner bushing configured to receive the trunnion in a press fit relationship, and an outer bushing configured to rotatably receive the inner bushing. A retention feature is configured to retain the trunnion axially with respect to the outer bushing.
United Technologies Corporation


07/21/16
20160208635 
new patent

Turbine shroud with tubular runner-locating inserts


A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner.
Rolls-royce North American Technologies, Inc.


07/21/16
20160208634 
new patent

Repair or remanufacture of blade outer air seals for a gas turbine engine


A method of remanufacturing a turbine component is provided. This method includes removing a donor portion from a damaged component; removing a to-be-replaced portion from a serviceable component generally equivalent to the donor portion leaving a remainder; and welding the donor portion to the remainder.
United Technologies Corporation


07/21/16
20160208629 
new patent

Anti-rotation vane


A vane for a gas turbine engine includes a radially inner platform and a radially outer platform. At least two airfoils extend between the radially inner platform and the radially outer platform.
United Technologies Corporation


07/21/16
20160208628 
new patent

Inner housing hub for a gas turbine


An inner housing hub is arranged in a gas turbine about a gas turbine shaft and is formed as a component of an inner housing used to deflect hot gases exiting combustion chambers towards a turbine inlet region arranged in the direction of the gas turbine shaft. The inner housing hub includes at least one substantially cylinder casing-shaped securing portion having a cylinder casing-shaped main part, which has a hot side facing a hot gas path and a cold side facing away from the hot gas path.
Siemens Aktiengesellschaft


07/21/16
20160208626 
new patent

Integrally bladed rotor with pressure side thickness on blade trailing edge


An integrally bladed rotor comprises a hub centered about an axis and having a plurality of blades extending radially outwardly of the axis across a span. Each of the blades includes an airfoil extending between a leading edge and a trailing edge, and having a pressure side and a suction side.
United Technologies Corporation


07/21/16
20160208621 
new patent

Gas turbine engine airfoil with wishbone baffle cooling scheme


A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity.
United Technologies Corporation


07/21/16
20160208620 
new patent

Gas turbine engine airfoil turbulator for airfoil creep resistance


A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction.
United Technologies Corporation


07/21/16
20160208614 
new patent

Gas turbine engine truncated airfoil fillet


An integrally bladed rotor includes a rim integral with a web that extends radially inward to a bore. The rim provides an end wall from which integral blades extend radially outward to a tip.
United Technologies Corporation


07/21/16
20160208613 
new patent

Gas turbine engine integrally bladed rotor


A rotor disk includes a web that extends from a rim radially inward to a bore. A spacer is integral with and extending generally axially from the rim.
United Technologies Corporation


07/21/16
20160207632 
new patent

Upper bifi frame for a gas turbine engine and methods therefor


An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case is provided. The upper bifi frame includes a forward fairing having a forward fairing midsection extending between the engine casing and the fan case.
United Technologies Corporation


07/21/16
20160207630 
new patent

Aircraft


An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (a), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (d32-d42). The rotational plane (d32-d42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (a) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b)..
Rolls-royce Plc


07/14/16
20160201917 

Cooled fuel injector system for a gas turbine engine


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.
United Technologies Corporation


07/14/16
20160201916 

System and an oxidant passageway in a gas turbine system with exhaust gas recirculation


A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway.
Exxonmobil Upstream Research Company


07/14/16
20160201915 

Swirler mount interface for gas turbine engine combustor


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 combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface..
United Technologies Corporation


07/14/16
20160201914 

Sealed combustor liner panel for a gas turbine engine


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.
United Technologies Corporation


07/14/16
20160201912 

Wedge-shaped ceramic heat shield of a gas turbine combustion chamber


A heat shield element for a heat shield has a support structure. The heat shield element includes a hot side which can be exposed to hot gas, a cold side opposite the hot side, and peripheral sides connecting the hot side to the cold side.
Siemens Aktiengesellschaft


07/14/16
20160201910 

Protective panel and frame therefor


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..
United Technologies Corporation


07/14/16
20160201909 

Gas turbine engine wall assembly with support shell contour regions


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.
United Technologies Corporation


07/14/16
20160201908 

Vena contracta swirling dilution passages for gas turbine engine combustor


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.
United Technologies Corporation


07/14/16
20160201805 

Wide differential pressure range air riding carbon seal


An exemplary carbon seal assembly generally may include a stator fixable to a static component, such as a mechanical housing of a gas turbine engine, and a rotor fixable to a rotating component, such as a shaft of the gas turbine engine, where the rotating component is rotatable relative to the static component. The carbon seal assembly may also include a carbon ring and a spring attached thereto positioned between the stator and the rotor, where the spring may be configured to move the carbon ring fore and aft between the stator and the rotor.
Rolls-royce Corporation


07/14/16
20160201688 

Gas turbine engine diffuser cooling and mixing arrangement


A diffuser for a gas turbine engine includes a diffuser housing that has a circumferential array of hollow struts that provide a cavity. The diffuser housing includes inlet and outlet apertures that are in fluid communication with the cavity.
United Technologies Corporation


07/14/16
20160201684 

Compressor area splits for geared turbofan


A gas turbine engine has an upstream compressor having an upstream entrance area leading into a first vane upstream of the upstream compressor. A downstream compressor has an exit area at a leading edge of an exit vane for the downstream compressor.
United Technologies Corporation


07/14/16
20160201682 

Split axial-centrifugal compressor


A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor.
Rolls-royce Corporation


07/14/16
20160201608 

Systems and methods controlling fan pressure ratios


A system for varying the fan pressure ratio of a gas turbine engine is provided. The system may comprise a stator having a variable area component.
United Technologies Corporation


07/14/16
20160201607 

Efficient, low pressure ratio propulsor for gas turbine engines


A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades.
United Technologies Corporation


07/14/16
20160201606 

Low weight large fan gas turbine engine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan configured to deliver airflow to a bypass passage, and a core engine configured to rotate the fan. The core engine includes a high pressure turbine section configured to drive a high pressure compressor section, and a low pressure turbine section configured to drive the fan and a low pressure compressor section.
United Technologies Corporation


07/14/16
20160201600 

Thrust reverser sliding door assembly


A gas turbine engine assembly has a pylon with a first side and a second side. A first rail is mounted to the first side and a second rail is mounted to the second side.
United Tecnologies Corporation


07/14/16
20160201573 

Automated tuning of gas turbine combustion systems


A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system.
Gas Turbine Efficiency Sweden Ab


07/14/16
20160201568 

Geared gas turbine engine with reduced oil tank size


A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction.

07/14/16
20160201567 

System and diversified gearbox


A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions..
United Technologies Corporation


07/14/16
20160201566 

Large displacement high temperature seal


A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall.
United Technologies Corporation


07/14/16
20160201562 

Fuel manifold for a gas turbine engine


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 includes a second multiple of double-barrel fittings in communication with the primary fuel circuit and the secondary fuel circuit.
Untied Technologies Corportion


07/14/16
20160201560 

Cooling air line for removing cooling air from a manhole of a gas turbine


A gas turbine having a compressor, a turbine unit, at least one combustion chamber and a secondary air system, which secondary air system has at least one cooling line having a compressor-side inlet for removing cooling air from the compressor and a turbine-side outlet for leading the cooling air onward into the turbine unit, wherein the cooling air line at the compressor-side inlet is connected fluidically to a housing opening of the gas turbine which adjoins a cavity in the gas turbine and which, during operation, guides compressor air, and wherein the housing opening is formed as a manhole.. .
Siemens Aktiengesellschaft


07/14/16
20160201559 

Tubular combustion chamber having a flame tube end region and gas turbine


A tubular combustion chamber for a gas turbine has a combustion chamber head end, on which at least one first burner arrangement is arranged, a substantially cylindrical flame tube, which encloses a first combustion zone and includes a cylindrical flame tube end region, and a transition duct, the cylindrical flame tube end region projecting into the transition duct and the transition duct fluid-connecting the flame tube to a combustion chamber outlet, which can be arranged on a turbine inlet region, wherein the cylindrical flame tube end region has a number of cooling ducts, which run substantially parallel to the lateral face of the flame tube end region in the interior of the flame tube end region. The cooling ducts are configured and/or arranged such that on average less cooling air flows through regions under low thermal load than through regions under high thermal load of the flame tube end region..
Siemens Aktiengesellschaft


07/14/16
20160201557 

Gas turbine engine thermal management system


A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger. A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid.
United Technologies Corporation


07/14/16
20160201516 

Gas turbine engine mid-turbine frame tie rod arrangement


A gas turbine engine mid-turbine frame includes an annular case which includes a first face. A tie rod includes a flange that is secured to the annular case.
United Technologies Corporation


07/14/16
20160201515 

Connection for a fairing in a mid-turbine frame of a gas turbine engine


A fairing assembly for a gas turbine engine includes an inner fairing platform; an outer fairing platform located radially outward of the inner fairing platform; a plurality of vanes radially outward from the inner fairing platform between the inner fairing platform and outer fairing platform; a mount located on a radially outer side of the outer fairing platform, the mount attached to the outer fairing platform on the radially outer side; and a link that includes an elongated member with a first end and an opposite second end, the first end configured to fit within the mount and define a pivot axis of the link with respect to the mount.. .
United Technologies Corporation


07/14/16
20160201512 

Gas turbine engine mid-turbine frame tie rod arrangement


A gas turbine engine mid-turbine frame includes inner and outer cases that are arranged about an engine axis. A radial plane is arranged normal to the engine axis.
United Technologies Corporation


07/14/16
20160201511 

Shielding pockets for case holes


A case is provided for a gas turbine engine. The case includes a wall defining a through-hole.
Mitsubishi Heavy Industries America, Inc.


07/14/16
20160201508 

Gas turbine engine and foil bearing system


A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure.
Rolls-royce Corporation


07/14/16
20160201507 

Engine component for a gas turbine engine


An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. A film hole in the wall has an inlet, an outlet, and a passage connecting the inlet and outlet that defines an inflection point..
General Electric Company


07/14/16
20160201506 

Turbine exhaust cylinder/ turbine exhaust manifold bolted stiffening ribs


Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path.
Siemens Energy, Inc.


07/14/16
20160201501 

Method for testing an overspeed protection apparatus of a single-shaft system


A method for testing an overspeed protection apparatus of a single-shaft system that includes: a) operating the system at nominal speed and under electrical load, wherein the load is selected to be low enough that, after dropping the load, the speed of the system rises such that the speed remains below steam turbine threshold speed lower than gas turbine threshold speed, such that first overspeed protection is triggered when the speed of the steam turbine reaches the steam turbine threshold speed, and second overspeed protection is triggered when the speed of the gas turbine reaches the gas turbine threshold speed; b) dropping the load; c) increasing the mass flow of the steam introduced into the steam turbine and/or of the fuel introduced into the gas turbine such that the speed of the steam turbine reaches the steam turbine threshold speed; d) testing whether the first overspeed protection is triggered.. .
Siemens Aktiengesellschaft


07/14/16
20160201497 

Gas turbine and mounting method


An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side.
Siemens Aktiengesellschaft


07/14/16
20160201496 

Gas turbine and mounting method


A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side.
Siemens Aktiengesellschaft


07/14/16
20160201495 

Gas turbine and mounting method


A gas turbine includes a turbine having a rotor blade row and a ring that is arranged around the rotor blade row and is made up of multiple ring segments. An insert element covers a recess of a ring segment body of the turbine.
Siemens Aktiengesellschaft


07/14/16
20160201492 

Tangential on-board injection vanes


A tangential on-board injection (tobi) system for gas turbine engines includes a first endwall and a second endwall radially spaced apart from the first endwall. A plurality of airfoils extend radially from the first endwall to the second endwall.
United Technologies Corporation


07/14/16
20160201484 

Turbine wheel with clamped blade attachment


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material.
Rolls-royce North American Technologies, Inc.


07/14/16
20160201483 

Turbine wheel with clamped blade attachment


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material.
Rolls-royce North American Technologies, Inc.


07/14/16
20160201478 

Braided blades and vanes having dovetail roots


A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail.
General Electric Company


07/14/16
20160201477 

Gas turbine engine airfoil crossover and pedestal rib cooling arrangement


A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction.
United Technologies Corporation


07/14/16
20160201475 

Cooling for gas turbine engine components


A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces.
United Technologies Corporation


07/14/16
20160201474 

Gas turbine engine component with film cooling hole feature


A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface.
United Technologies Corporation


07/14/16
20160201472 

Vane, gas turbine provided with the same, manufacturing vane, and remodeling vane


A retainer that protrudes from an inner shroud of a vane to a radially inner side and extends in a circumferential direction is formed with an opening that passes through the retainer in an axial direction and defines a space through which air flows. A width of the opening in the circumferential direction is wider than a width of a vane body in the circumferential direction at a radially inner end of the vane body at a position of the retainer in the axial direction..
Mitsubishi Hitachi Power Systems, Ltd.


07/14/16
20160201466 

Coating pocket stress reduction for rotor disk of a gas turbine engine


A rotor is provided for a gas turbine engine. The rotor includes a rim that extends transverse to the web.
United Technologies Corporation




Gas Turbine topics: Gas Turbine, Gas Turbine Engine, Internal Combustion Engine, Distributed, Combustion, Uv Radiation, Exhaust Gas, Circulation, Downstream

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