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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
04/07/16
20160097538 
 Fuel nozzle patent thumbnailFuel nozzle
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The air passageway has a swirl-inducing relief defined at an exit lip of an outer wall of the air passageway.
Pratt & Whitney Canada Corp.


04/07/16
20160097537 
 Fuel nozzle patent thumbnailFuel nozzle
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall.
Pratt & Whitney Canada Corp.


04/07/16
20160097536 
 Fuel nozzle patent thumbnailFuel nozzle
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall.
Pratt & Whitney Canada Corp.


04/07/16
20160097535 
 Combustor for gas turbine engine patent thumbnailCombustor for gas turbine engine
A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber.
Pratt & Whitney Canada Corp.


04/07/16
20160097346 
 Electric boost actuation system for translating rings patent thumbnailElectric boost actuation system for translating rings
An actuation system for a gas turbine engine oriented about a centerline includes a translating ring, at least one hydraulic actuator, and at least one electric actuator. The translating ring is oriented about the centerline and configured to move axially along the centerline.
Hamilton Sundstrand Corporation


04/07/16
20160097331 
 Gas turbine architecture patent thumbnailGas turbine architecture
A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure.
Rolls-royce Deutschland Ltd & Co Kg


04/07/16
20160097330 
 Gas turbine architecture patent thumbnailGas turbine architecture
A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure.
Rolls-royce Deutschland Ltd & Co Kg


04/07/16
20160097329 
 Corrosion and abrasion resistant coating patent thumbnailCorrosion and abrasion resistant coating
A gearbox adapted for use with a gas turbine engine and a method for making the same are disclosed herein. The gearbox comprising a housing made from a magnesium alloy, and an aluminum oxide coating on the magnesium alloy housing.
Rolls-royce Corporation


04/07/16
20160097328 
 Accessory drive system for a gas turbine engine patent thumbnailAccessory drive system for a gas turbine engine
The described accessory drive system for a gas turbine engine includes a gearbox driving a plurality of accessories including a cabin air compressor to provide cabin air and an engine starter to start the gas turbine engine. An electrical power supply separate from a main electrical power supply of the gas turbine engine is electrically coupled to the accessories.
Pratt & Whitney Canada Corp.


04/07/16
20160097327 
 Synchronized air modulating system patent thumbnailSynchronized air modulating system
A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening.
United Technologies Corporation


04/07/16
20160097325 

Cooled component


A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. The apertures are arranged at an angle to the second surface and each aperture has an inlet in the first surface and an outlet in the second surface.
Rolls-royce Plc


04/07/16
20160097324 

Filtration system for use in a gas turbine engine assembly and assembling thereof


A filtration system and methods of assembly and operation are provided. The filtration system includes an array of perforated tubes in flow communication with a flow of intake air.
Bha Altair, Llc


04/07/16
20160097323 

Anti-ice splitter nose


Splitter apparatus for gas turbine engines are disclosed. An example splitter apparatus may include a splitter including an annular outer wall substantially defining a convex leading edge; an annular splitter support positioned radially within the outer and including a forward end disposed substantially against a splitter inner; and an annular first bulkhead spanning between the outer wall and the splitter support.
General Electric Company


04/07/16
20160097304 

Gas turbine engine with low stage count low pressure turbine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section.
United Technologies Corporation


04/07/16
20160097303 

Cmc shroud support system of a gas turbine


A shroud support system with load spreading comprises a shroud hanger having a first wall and a second wall spaced apart in an axial direction by a retainer support wall, a ceramic matrix composite shroud segment disposed in the shroud hanger between the first and second walls and the retainer support wall, a retainer having circumferentially spaced first and second bolt holes, the retainer passing through the shroud, first and second bolts passing through the shroud hanger and engaging the first and second bolt holes of the retainer.. .
General Electric Company


04/07/16
20160097301 

Aircraft gas turbine engine with shock-absorbing element for fan blade loss


An aircraft gas-turbine engine having a fan mounted on a fan shaft and including several fan blades, where the fan shaft is mounted on an engine structure by means of an upstream fan bearing, when seen in the flow direction, and a downstream bearing, where at least one predetermined breaking point is provided in the area of the fan bearing, characterized in that at least one shock-absorbing element designed as metal fabric damper is arranged at a radial gap to have a parallel effect relative to the predetermined breaking point.. .
Rolls-royce Deutschland Ltd. & Co Kg


04/07/16
20160097295 

Sealing element


A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition.
Rolls-royce Plc


04/07/16
20160097292 

Gas turbine having at least two shafts designed as hollow shafts at least in some areas and arranged coaxially relative to one another


The present invention describes a gas turbine having two shafts, which are rotatably mounted using bearing devices in the area of a casing. An intermediate shaft sealing device is arranged between the bearing devices, which includes a sealing element connected to a first shaft, in which a further sealing element connected to the second shaft radially engages.
Rolls-royce Deutschland Ltd & Co Kg


04/07/16
20160097291 

Stator assembly for a gas turbine engine


A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane..
United Technologies Corporation


04/07/16
20160097290 

Engine nacelle


A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.. .
Rolls-royce North American Technologies, Inc.


04/07/16
20160097289 

Slider


A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot.
Rolls-royce Plc


04/07/16
20160097287 

Fan


Fan for gas turbine engine includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root.
Rolls-royce Plc


04/07/16
20160097286 

Internal cooling of engine components


A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (ngv), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. Curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion.
Rolls-royce Plc


04/07/16
20160097285 

Cooled component


A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface.
Rolls-royce Plc


04/07/16
20160097281 

Gas turbine engine airfoil mistuning


A circumferential airfoil array that provides a total airfoil count for the stage and that includes first and second sets of airfoils with different vibrational frequencies. First and second arcuate regions are arranged opposite one another and third and fourth arcuate regions are arranged opposite one another.
United Technologies Corporation


04/07/16
20160096288 

Tooling production method


A method is provided of producing a tooling to be used for manufacturing a rigid panel formed of polymer matrix composite material. The panel is for attachment to a gas turbine engine and has a curved shape which allows the panel to be wrapped around at least a part of a circumference of the engine.
Rolls-royce Plc


04/07/16
20160096134 

Filtering chamber for gas turbines and maintenance thereof


A filter system for filtering intake air of a gas turbine, comprising a first filter arrangement and a second filter arrangement, located downstream from the first filter arrangement and having a higher collection efficiency than the first filter arrangement. Furthermore, a guard filter arrangement, having a lower collection efficiency than the first filter arrangement, is located between the first filter arrangement and the second filter arrangement..
Nuovo Pignone Srl


03/31/16
20160091207 

Combustor and gas turbine having the same


A combustor is equipped with a burner case, and a base plate spreading from a downstream end of the burner case in a radial direction. The base plate defines a purging air space at an upstream side of the base plate.
Mitsubishi Hitachi Power Systems, Ltd.


03/31/16
20160090998 

Grid scale energy storage systems using reheated air turbine or gas turbine expanders


Electrical power systems, including generating capacity of a gas turbine, where additional power is generated from an air expander and gas turbine simultaneously from a stored compressed air and thermal system.. .
Fastlight Llc


03/31/16
20160090916 

Inner bypass duct


An inner bypass duct of a gas turbine engine includes a plurality of non-structural front panels arranged circumferentially. Each front panel has an outer surface and an inner surface.
Pratt & Whitney Canada Corp.


03/31/16
20160090915 

Inlet door control for startup of gas turbine engine


A gas turbine engine inlet door control system includes an actuator, an engine controller and a door controller. The actuator opens and closes an inlet door of a gas turbine engine.
United Technologies Corporation


03/31/16
20160090913 

Gas turbine system with cooling fluid generator


A gas turbine system (1a) includes a gas turbine unit (2) and a cooling fluid generator (5). The gas turbine unit (2) includes a first compressor (21) and a first expansion turbine (23) coupled to each other by a first shaft (22), a combustor (26), and a fuel tank (30).
Panasonic Intellectual Property Management Co., Ltd.


03/31/16
20160090911 

Gas turbine facility


A gas turbine facility 10 in an embodiment includes: a combustor 20; a fuel nozzle 21; a turbine 22; a heat exchanger 24 cooling the combustion gas. The gas turbine facility 10 includes: a pipe 42 guiding a part of the cooled combustion gas to an oxidant supply pipe; a pipe 44 passing a mixed gas composed of the oxidant and the combustion gas through the heat exchanger 24 to heat it, and guising it to the fuel nozzle 21; a pipe 40 passing another part of the cooled combustion gas through the heat exchanger 24 to heat it, and guiding it to the combustor 20; a pipe 45 passing still another part of the cooled combustion gas through the heat exchanger 24 to heat it, and guiding it to the fuel nozzle 21; and a pipe 46 exhausting a remaining part of the cooled combustion gas..
Kabushiki Kaisha Toshiba


03/31/16
20160090909 

Geared gas turbine engine with reduced fan noise


A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction.
United Technologies Corporation


03/31/16
20160090870 

Gas turbine engine module adapter to a carrier


An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis.
Pratt & Whitney Canada Corp.


03/31/16
20160090868 

Gas turbine engine mounting arrangement


A failsafe pin for providing a backup load path for attaching a gas turbine engine to an aircraft structure is provided with a driving element that allows a torque to be provided to the pin in order to check whether the pin has been engaged, and thus whether a primary load path has failed. The pin is provided with anti-tamper arrangements in order to ensure that the pin itself is not compromised when being tested for engagement..
Rolls-royce Plc


03/31/16
20160090867 

Apparatus for mounting a component in a gas turbine engine


Apparatus for mounting a component in a gas turbine engine, the apparatus comprising: a casing for a gas turbine engine, the casing including a flange; a first connector to connect a component of the gas turbine engine to the casing at a first location adjacent to the flange; and a second connector to connect the component of the gas turbine engine to the casing at a second location adjacent to the flange.. .
Rolls-royce Plc


03/31/16
20160090866 

Shroud segment retainer


A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor.. .
Rolls-royce Plc


03/31/16
20160090862 

Tripod buckle for split fairing of a gas turbine engine


A fairing for a turbine engine strut includes: inner and outer bands; a vane extending between the bands; the fairing is split along a generally transverse plane passing through the bands and the vane, defining nose and tail pieces; wherein the vane is defined by spaced-apart sidewalls extending between a leading edge and a trailing edge, each sidewall split into forward and aft portions by the transverse plane; wherein each sidewall portion carries a radially-inwardly extending post, the posts positioned such that pairs of the posts lie adjacent to each other when the nose piece and tail piece are assembled, wherein each pair of adjacent posts includes at least two non-parallel faces; and a pair of slotted buckles, wherein each slotted buckle surrounds and clamps together a pair of the posts, wherein each pair of adjacent posts contacts a slot of the corresponding buckle in a tripod contact configuration.. .
General Electric Company


03/31/16
20160090859 

Gas turbine engine and a washing a gas turbine engine


There is disclosed a method of washing a gas turbine engine (10) of a type having an anti-icing arrangement comprising a fluid delivery system (33) configured to deliver a flow of hot gas to a region (36) of the engine during operation of the engine. The method comprises the steps of: connecting a supply of cleaning liquid to said fluid delivery system (33); creating a flow of said cleaning liquid through at least part of said fluid delivery system (33) for delivery to said region (36) of the engine; and directing said cleaning liquid towards internal components (25, 27, 30) of the engine.
Rolls-royce Plc


03/31/16
20160090856 

Stator vane adjusting device of a gas turbine


A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane, as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device, where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring, characterized in that a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer, the bush being made from a plastic material with a high thermal expansion coefficient.. .
Rolls-royce Deutschland Ltd & Co Kg


03/31/16
20160090852 

Gas turbine engine


In a gas turbine engine, an annular intermediate-temperature space is formed by a first partition member extending from an inner platform radially inward and a second partition member having a radially inner end portion fixed to the first partition member and a radially outer end portion facing the inner platform, the inner platform being connected to radially inner ends of nozzle guide vanes of a turbine, and the intermediate-temperature space overlapping with the inner platform over substantially its axial entire length. The low-temperature space, supplied with a low-temperature air from a compressor, is formed on a radially inside of the second partition member.
Honda Motor Co., Ltd.


03/31/16
20160090849 

Fan blade with static dissipative coating


The present disclosure relates generally to a fan blade for use in a gas turbine engine, wherein the fan blade includes a metallic fan blade body, including a fan blade body leading edge and body outer surface, extending radially outward from a root, and a static dissipative coating material disposed on the body outer surface.. .
United Technologies Corporation


03/31/16
20160090847 

Cooling scheme for a turbine blade of a gas turbine


A turbine blade of a gas turbine includes a radially extending airfoil with a suction side and pressure side, which extend each in axial direction between a leading edge and a trailing edge of the airfoil. The leading edge is cooled by means of impingement cooling with rows of radially distributed jets of a cooling medium impinging on the inner side of the leading edge.
Alstom Technology Ltd


03/31/16
20160090846 

Gas turbine engine airfoil trailing edge suction side cooling


An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges.
United Technologies Corporation


03/31/16
20160090845 

Dual wall components for gas turbine engines


A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall..
Rolls-royce Corporation


03/31/16
20160090844 

Gas turbine engine airfoil cooling passage configuration


A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another.
United Technologies Corporation


03/31/16
20160090841 

Gas turbine engine blade slot heat shield


A gas turbine engine rotor assembly includes a rotor disk with a slot. A rotor blade has a root supported within the slot.
United Technologies Corporation


03/31/16
20160090840 

Carriers for turbine components


A carrier segment for forming a carrier section for one or more gas turbine engine components, the carrier segment including a carrier wall extending between front and rear carrier ends and having a circumferential profile, the carrier segment being configured for defining radially inwardly thereof a chamber for receiving cooling air from an outboard feed source via the front end, wherein the circumferential profile of the carrier wall is undulating, e.g. With a simple waveform configuration or a more complex arrangement of interleaved series of oppositely oriented part-conical surface formations..
Rolls-royce Plc


03/31/16
20160089722 

Method of manufacturing gas turbine engine component from a molybdenum-rich alloy


A method for manufacturing a gas turbine engine component from a molybdenum-rich alloy. The method includes the steps of providing a molybdenum powder of at least 50% molybdenum by weight, extruding the molybdenum powder to provide a first shape, forming the first shape to a second shape and forging the second shape to provide a third shape..
United Technologies Corporation


03/24/16
20160084736 

Systems and methods for attaching a probe to a casing of a gas turbine engine


A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing.
General Electric Company


03/24/16
20160084503 

Fuel nozzle


A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a plurality of concentrically-arranged nozzle tip projections disposed at a downstream portion of the body. Each of the plurality of nozzle tip projections has a radially inwardly facing fuel filming surface communicating with respective fuel passages.
Pratt & Whitney Canada Corp.


03/24/16
20160084265 

Gas turbine engine with partial inlet vane


A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path.
Pratt & Whitney Canada Corp.


03/24/16
20160084260 

Gas turbine engine


A compressor disc for a compressor of a gas turbine engine includes a circumferentially extending groove for receiving blade roots of a plurality of compressor blades. The circumferentially extending groove includes a planar surface offset into the groove..
Rolls-royce Plc


03/24/16
20160084169 

Method of operating a multi-stage flamesheet combustor


The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels..

03/24/16
20160084168 

Chemistry based methods of manufacture for maxmet composite powders


A method of manufacturing a gas turbine engine air seal comprising forming at least one max phase particle. The method includes coating the at least one max phase particle with a metallic shell.
United Technologies Corporation


03/24/16
20160084167 

Self-modulated cooling on turbine components


Systems and methods are disclosed herein for passively managing cooling air in a gas turbine engine. A cooling air supply line may supply cooling air to a component in the gas turbine engine.
United Technologies Corporation


03/24/16
20160084164 

Plate for metering flow


A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side.
United Technologies Corporation


03/24/16
20160084162 

Gas turbine engine inlet


An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan.
Pratt & Whitney Cananda Corp.


03/24/16
20160084161 

Inlet air filtration system with self-cleaning hydrophobic filter bag


The present application provides a pulse filtration system for use with a compressor of a gas turbine engine. The pulse filtration system may include a pulse filter, a compressed air system in communication with the pulse filter, and a hydrophobic filter bag surrounding the pulse filter in whole or in part..
General Electric Company


03/24/16
20160084160 

System for turbine combustor fuel mixing


A system includes a plurality of interconnected mixing assemblies configured to mix a first fuel and water to generate a first mixture, and mix a second fuel and the water to generate a second mixture. The first and second fuel mixtures are configured to combust in a plurality of combustors of a gas turbine.
General Electric Company


03/24/16
20160084113 

Nacelle mounted latching system


A nacelle for a gas turbine engine includes a bifurcation, an outer diameter cowl and a first latch system. The outer diameter cowl extends from the bifurcation and the first latch system is mounted on the outer diameter cowl.
United Technologies Corporation


03/24/16
20160084111 

Methods and systems for preventing lube oil leakage in gas turbines


A sump pressurization system comprising an off-board source of pressurized air is provided to supplement pressurized air to a bearing sump arrangement when the operating conditions of the gas turbine engine are such that the on-board pressurized air source, e.g. The compressor of the gas generator, are such that the air pressure generated thereby is insufficient to pressurize a sump pressurization cavity.
Nuovo Pignone Srl


03/24/16
20160084109 

Gas turbine ring segment cooling apparatus


A gas turbine shroud ring segment assembly (36) with an outer structural block (32a) having cooling channels (72) between inlets (60) on a front face and outlets (74, 76) on a front hanger rail (48). The outlets may be positioned on a radially inner surface (77) of the front rail for impingement and forced convection cooling of backsides of radially inner front lips (44) of adjacent shroud ring segments (30a, 30b) mounted on front and rear rails (48, 50) of the block.
Siemens Energy, Inc.


03/24/16
20160084106 

Anti-icing core inlet stator assembly for a gas turbine engine


A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing..
United Technologies Corporation


03/24/16
20160084105 

Fan drive gear system


A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism..
United Technologies Corporation


03/24/16
20160084104 

Fan drive gear system


A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism..
United Technologies Corporation


03/24/16
20160084101 

Gas turbine engine blade outer air seal assembly


A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades.

03/24/16
20160084100 

System and seal retention and protection


A sheath and seal assembly for protecting, containing and insulating a seal is provided. The seal may be installable within the sheath forming a seal-sheath assembly.
United Technologies Corporation


03/24/16
20160084095 

Diaphragm assembly with a preswirler


A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring.
Solar Turbines Incorporated


03/24/16
20160084091 

High pressure turbine blade cooling hole distribution


A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one set of holes selected from the group consisting of a first set, a second set, a third set, a fourth set, a fifth set and a sixth set, wherein the first, second, third, fourth, fifth and sixth sets of holes respectively include the holes numbered a1 to a8, b1 to b10, c1 to c9, d1 to d6, e1 to e7 and f1 to f6 each located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the x, y, z cartesian coordinate values set forth in table 3..
Pratt & Whitney Canada Corp.


03/24/16
20160084090 

Method and assembly for reducing secondary heat in a gas turbine engine


A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage..
United Technologies Corporation


03/24/16
20160084088 

Stress relieving feature in gas turbine blade platform


A gas turbine engine blade (10) having: an airfoil (12) having a leading edge (14), a trailing edge (16), a pressure side (22), and a suction side (24); an inner platform (30) associated with a base (18) of the airfoil, wherein the inner platform includes a platform aft face (34) spanning between an platform pressure side face (36) and a platform suction side face (38); and a trailing edge undercut (70) across the aft face. The trailing edge undercut tapers to zero penetration before reaching the platform suction side face.
Siemens Energy, Inc.


03/24/16
20160084086 

Gas turbine engine


A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element.
Rolls-royce Plc




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

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