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Gas Turbine Engine patents

      

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




new patent Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity.
United Technologies Corporation


new patent D5/d5a df-42 integrated exit cone and splash plate
A combustor basket assembly for a gas turbine engine that includes a combustor basket having a basket liner including an input end and an output end. An integrated exit cone and splash plate member is affixed to the output end of the basket liner and includes a base portion, an exit cone portion and a splash plate portion.
Siemens Energy, Inc.


new patent Containment casing
The present invention provides a gas turbine engine comprising a tubular containment casing surrounding a rotary fan blade assembly. The radially outer perimeter (and optionally the radially inner perimeter) of the radial cross-sectional profile of the containment casing is non-circular e.g.
Rolls-royce Plc


new patent Gas turbine engine airfoil
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 100% span..
United Technologies Corporation


new patent Geared architecture for a gas turbine engine
A gear system for a gas turbine engine includes a planet gear system which includes an output attached to a carrier for rotating a first fan assembly in a first direction. A star gear system includes an output attached to a ring gear for rotating a second fan assembly in a second direction.
United Technologies Corporation


new patent Fuel system coking sensor
An improved system, apparatus and method may be configured for detecting coking in a gas turbine engine. The system may comprise one or more heatable collecting elements configured to be positioned in a fuel supply passage having an inlet and an outlet.
Rolls-royce North American Technologies, Inc.


new patent Igniter assembly for a gas turbine engine
In one aspect the present subject matter is directed to an igniter assembly for a gas turbine engine. The igniter assembly includes an outer housing and an igniter tube that extends radially through the outer housing.
General Electric Company


new patent Reduced stress boss geometry for a gas turbine engine
A case for a gas turbine engine includes a case wall and a boss that extends from the case wall. The boss includes a perimeter step..
United Technologies Corporation


new patent Systems and methods for passively providing one or more flows of cooling fluid to a hot cavity within a cooling circuit of a gas turbine engine
A thermal valve is disclosed. The thermal valve may provide one or more flows of cooling fluid to a hot cavity within a cooling circuit of a gas turbine engine.
General Electric Company


new patent Heat shield for a vane assembly of a gas turbine engine
A heat shield is provided for use in an inner cavity of a gas turbine engine component. The heat shield comprises a heat shield body comprising opposed side portions defining an inner channel.
United Technologies Corporation


new patent

Methods of washing gas turbine engines and gas turbine engines

Washing of the gas turbine engine, during operation of the gas turbine engine, comprises a washing phase that consists in spraying a detergent liquid substance towards the inlet of the compressor of the engine; the mass flow of the detergent liquid substance to be sprayed is set so that the liquid-to-gas ratio at the inlet of the compressor is more than 1% and less than 5% with reference to the rated mass flow of the compressor; the washing phase comprises a first sub-phase during which the flow of the detergent liquid substance is increased gradually and a second sub-phase during which the flow of the detergent liquid substance is maintained constant.. .
Nuovo Pignone Srl

new patent

Gas turbine exhaust diffuser mounted blade path thermocouple probe

A thermocouple probe assembly for monitoring the temperature of an exhaust gas flow at an output of a gas turbine engine. The probe assembly includes a plenum pipe positioned within an opening extending through an outer casing wall and a plenum plate of the engine, where an air gap is provided between the casing wall and the plate.
Siemens Energy, Inc.

new patent

Actuation arrangement

An actuation arrangement for effecting actuation of pivotable vane, for example, variable inlet guide vane in gas turbine engine. The actuation arrangement includes an actuator having a support plate and pivotable plate.
Rolls-royce Plc

new patent

Movable vane control system

A movable vane control system is disclosed for use with a gas turbine engine having a turbine axis of rotation. The system includes a plurality of rotatable turbine vanes in a gas flow path within a turbine case of the gas turbine engine.
Hamilton Sundstrand Corporation

new patent

Gas turbine engine rapid response clearance control system

An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies.
United Technologies Corporation

new patent

Article having cooling passage with undulating profile

An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface.
United Technologies Corporation

new patent

Abradable seal and producing a seal

An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer.
United Technologies Corporation

new patent

Electrical control system

An example aircraft electrical system includes a generator coupled with a gas turbine engine and a controller operable to distribute power of the generator. The controller includes a first control module positioned at a first location remote from the generator and a second control module positioned at a second location proximate the generator.
Hamilton Sundstrand Corporation

new patent

Conditioning gas turbine engine components for increasing fuel efficiency

The present invention relates to a conditioning method of gas turbine engine components (e.g. Compressor blades and vanes) for increasing fuel efficiency.
Envaerospace Inc.

Swirler for a burner of a gas turbine engine

A fuel injection structure for a swirler of a burner of a gas turbine engine, wherein the swirler includes a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, of the fuel injection structure which includes at least two injection ports to inject fuel into the channeled air. A swirler for a burner of a gas turbine engine, and a burner of a gas turbine engine and a gas turbine engine includes the fuel injection structure..
Siemens Aktiengesellschaft

W501 d5/d5a df42 combustion system

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and nox emissions, and eliminated impingement of cooling water on walls of the combustor.
Siemens Energy, Inc.

Internally cooled seal runner and cooling seal runner of a gas turbine engine

The seal runner has an annular body secured to a rotating shaft of the gas turbine engine whereas ring segments are secured to a case of the gas turbine, with the seal runner having a radially-outer surface having a contacting portion adapted to rubbingly receive ring segments of the contact seal assembly during use, the seal runner having a radially-inner surface opposite to the radially-outer surface. The method includes rotating the seal runner relative to the ring segments and generating heat from the rubbing engagement therebetween; and feeding a flow of cooling fluid against the radially-inner surface to cool the seal runner from said generated heat including maintaining a pool of cooling fluid having a given depth against the radially-inner surface..
Pratt & Whitney Canada Corp.

Clutch with redundant engagement systems

A clutch for use in a gas turbine engine is disclosed herein. The clutch is adapted to selectively transmit rotation from a first shaft of the clutch to a second shaft of the clutch..
Rolls-royce North American Technologies, Inc.

Gas turbine stator with winglets

A stator airfoil of a gas turbine engine according to one embodiment includes at least two winglets projecting transversely from opposed sides of a stator airfoil, respectively. Each winglet includes a leading edge axially and outwardly extending from one of the opposed sides of the stator airfoil and a trailing edge extending from the stator airfoil to join with the leading edge of the winglet.
Pratt & Whitney Canada Corp.

Compressor airfoil with compound leading edge profile

A compressor airfoil of a gas turbine engine includes a pressure side and a suction side of the airfoil extending downstream from a stagnation point, the suction side including a suction side surface portion within a leading edge region, and a main suction side airfoil surface downstream from the suction side surface portion and extending contiguously therewith. The suction side surface portion having a compound curvature profile which includes at least a leading edge having a first curvature profile and a chamfered surface having a second curvature profile different from the first curvature profile.
Pratt & Whitney Canada Corp.

Gas turbine engine airfoil

An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span..
United Technologies Corporation

Fan blade attachment root with improved strain response

A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided.
United Technologies Corporation

Translating gaspath bleed valve

A bleed of valve comprises a ring axially translatable between a retracted position in which the ring is configured to close an annular bleed off opening defined in a converging portion of a radially outer annular wall of a gas turbine engine gaspath and a deployed position in which the ring protrudes into the gaspath to mechanically scoop out incoming air and water/hail particles.. .
Pratt & Whitney Canada Corp.

Fuel purge system and purging

A fuel purge system for a gas turbine engine includes a fuel manifold configured to receive a liquid fuel from a fuel supply and distribute the liquid fuel to a combustor assembly. Also included is a liquid pump configured to receive a liquid from a liquid supply and distribute the liquid to the fuel manifold for pressurization of the fuel manifold during a purge operation of the combustor assembly..
General Electric Company

Combustion stability logic during off-load transients

A method for operating a gas turbine engine is disclosed. The method includes detecting an off-load transient of the gas turbine engine.
Solar Turbines Incorporated

Geared turbofan engine with counter-rotating shafts

A gas turbine engine turbine comprises a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis. A low pressure turbine is configured to rotate with a low pressure compressor as a low pressure spool in a second direction about the central axis.
United Technologies Corporation

Method of starting a gas turbine engine

A method of starting a gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor.. .
General Electric Company

Brackets for gas turbine engine components

A bracket includes a rigid member and a resilient member for coupling a coolant collector to a coolant supply manifold. The coolant collector is movable between a first position and a second position with respect to the coolant supply manifold due to thermal heating.
United Technologies Corporation

Flow sleeve for thermal control of a double-walled turbine shell and related method

A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface.
General Electric Company

Rotor resonance disturbance rejection controller

A speed control system for an engine comprising at least one rotary load is provided. The speed control system may include a rotor speed controller configured to regulate speed in the rotary load based on a sensed rotor speed, exclusive of resonant mode speed oscillations, in closed loop feedback with a commanded rotor speed.
Pratt & Whitney Canada Corp.

High speed recorder for a gas turbine engine

A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder.
Solar Turbines Incorporated

Integral instrumentation in additively manufactured components of gas turbine engines

A pressure probe includes a non-deflecting airfoil, a sensing feature, and an interior passage. The non-deflecting airfoil is made of a metal and configured for use in a gas turbine engine.
United Technologies Corporation

Ceramic matrix composite seal segment for a gas turbine engine

A ceramic matrix composite (cmc) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The cmc seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein.

Shroud cartridge having a ceramic matrix composite seal segment

A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (cmc) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore.

Shroud cartridge having a ceramic matrix composite seal segment

A cartridge for a ceramic matrix composite (cmc) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a cmc seal segment.

Pressure activated seals for a gas turbine engine

An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap..
Rolls-royce North American Technologies, Inc.

Seal and bearing assembly for a gas turbine engine and assembling same

A seal and bearing assembly of a gas turbine engine having an engine case with a cooling fluid nozzle located between a bearing outer ring and ring segments, and a rotary shaft for rotation in the engine case around a main axis, the seal and bearing assembly can be assembled by positioning the engine case and the rotary shaft in axial alignment, and axially moving the engine case relative to the rotary shaft including moving the bearing outer ring across the axial location of the runner portion and into an assembled condition. The rotary shaft having mounted thereon a bearing inner ring and a runner assembly having a runner portion, a sleeve portion being concentric and radially internal to the runner portion, and a cooling fluid passage having a radial segment leading from an outgoing segment to a returning segment extending in a direction leading back toward the bearing inner ring..
Pratt & Whitney Canada Corp.

Split line flow path seals

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod..
Rolls-royce High Temperature Composites, Inc.

Exhaust fume isolator for a gas turbine engine

Exhaust ducting for a gas turbine engine includes a lower plenum, an upper plenum, an exhaust fume isolator, and an inner duct seal positioned between the upper plenum and the exhaust fume isolator. The lower plenum is in flow communication with an exhaust collector of the gas turbine engine.
Solar Turbines Incorporated

Gas turbine engine liquid fuel supply system and method

A method of supplying liquid fuel in a gas turbine engine is provided and includes sealing a fuel manifold with a fluid in the fuel manifold. The method also includes initiating routing of a liquid fuel from a liquid fuel supply structure to the fuel manifold.
General Electric Company

Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade

A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity.
United Technologies Corporation

Gas turbine engine airfoil

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle..
United Technologies Corporation

Compressor tip injector

A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system.
Rolls-royce Plc

Gas turbine engine airfoil

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span.
United Technologies Corporation

Gas turbine engine airfoil

An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve.
United Technologies Corporation

Gas turbine engine airfoil

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear..
United Technologies Corporation

Full ring sliding nacelle with thrust reverser

A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation

Accessory apparatus and assembling accessories with a turbine engine

A method of assembling accessories with a turbine engine and an accessory apparatus for a gas turbine engine having a first shaft that rotates when the gas turbine engine is energized. The accessory apparatus includes a mount rail attached to the gas turbine engine and extending parallel to the first shaft of the gas turbine engine a first accessory having a first mounting block, to mount the first accessory to the mount rail, and an first accessory shaft to power the first accessory and a second accessory having a second mounting block, to mount the second accessory to the mount rail, and a second accessory shaft to power the second accessory..
General Electric Company

Cooled cooling air system for a gas turbine engine

A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed.
United Technologies Corporation

Turbocooled vane of a gas turbine engine

The present invention discloses a novel apparatus and methods for providing a flow of cooling air to one or more turbine nozzles or turbine blade outer air seals. The flow of cooling air is provided by an external source and regulated in order to improve turbine nozzle and air seal cooling efficiency and component life..
Powerphase Llc

Lubrication system for a reconfigurable gas turbine engine

According to the present disclosure, a gas turbine assembly includes a gas turbine engine and a gearbox. The gearbox includes a lubrication system including a first sump and a second sump.
Rolls-royce Corporation

Pre-skewed capture plate

A coupling arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a conduit between a first frame case defining a frame axis and a second frame case. A flange is coupled to the conduit defining a first axis and abuts the first frame case.
United Technologies Corporation

System for arranging an emission reducing catalyst in an exhaust duct of a gas turbine engine

An exhaust section for a gas turbine power plant including: an exhaust duct in fluid communication with exhaust gas from a gas turbine engine, wherein the exhaust gas flows through the exhaust duct along a flow direction; a catalyst supporting platform spanning a flow passage in the exhaust duct such that the exhaust gas passes through the platform, wherein the platform includes apertures having catalyst coated surfaces and the catalyst supporting platform has a front face which is no perpendicular to the flow direction.. .
General Electric Company

Energy dissipating core case containment section for a gas turbine engine

A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments..
United Technologies Corporation

Lubrication system for a turbine engine

A lubrication system for a gas turbine engine includes a tank, a circulation pump, and a heat exchanger. The circulation pump generates a flow of lubricant from the tank to, e.g., a power gear box of the gas turbine engine and the heat exchanger removes an amount of heat from such flow of lubricant provided to the power gear box.
General Electric Company

Bearing locking assemblies and methods of assembling the same

A bearing assembly for use in a gas turbine engine is provided. The bearing assembly includes a bearing retainer having an inner portion, an outer portion spaced radially apart from the inner portion, and an intermediate portion connecting the inner portion and the outer portion, wherein the inner portion and the outer portion define a space there-between.
General Electric Company

Compressed chopped fiber composite fan blade platform

The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine..
United Technologies Corporation

Gas turbine engine having energy dissipating gap and containment layer

A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly.
United Technologies Corporation

Gas turbine engine uncontrolled high thrust accommodation system and method

A system and method of accommodating an uncontrolled high thrust condition in a turbofan gas turbine engine includes processing engine data from the turbofan gas turbine engine to determine when a potential for an uncontrolled high thrust condition exists. When the potential for an uncontrolled high thrust condition exists, the engine data are processed to determine whether corrective action for the uncontrolled high thrust condition should be implemented by varying turbofan gas turbine engine effective geometry to (i) increase turbofan gas turbine engine rotational speed or (ii) decrease turbofan gas turbine engine rotational speed.
Honeywell International Inc.

Support assembly for a gas turbine engine

A support assembly for a gas turbine engine includes an outer support that extends about a circumferential axis and includes at least one engagement member. An inner support forms a cavity.
United Technologies Corporation

Support assembly for a gas turbine engine

A support assembly for a gas turbine engine includes at least one inner support that extends about a circumferential axis and defines a cavity for receiving a control ring. At least one cover plate is attached to at least one inner support to enclose the cavity.
United Technologies Corporation

Support assembly for a gas turbine engine

A support assembly for a gas turbine engine includes a control ring that extends about a circumferential axis. A plurality of first supports has a cavity that receives the control ring.
United Technologies Corporation

Heat exchanger seal segment for a gas turbine engine

Described is a seal segment (310) for a gas turbine engine, comprising: a gas facing wall (312) having a gas facing surface (314) and a first internal surface (316); an outboard wall (318) having an outboard facing surface (320) and a second internal surface (322) which is radially separated from the first internal surface with a gap therebetween; a first conduit (324) located between the first and second internal surfaces; and, a second conduit (326) located between the first and second internal surfaces, wherein the first and second conduits are radially separated by a party wall (328).. .
Rolls-royce Plc

Seals for a gas turbine engine

A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support.
Rolls-royce North American Technologies, Inc.

Support assembly for a gas turbine engine

A seal assembly for a gas turbine engine includes a first member including a first seal land for contacting a first structure. A second member includes a second seal land for contacting a second structure and a third seal land for contacting a third structure.
United Technologies Corporation

Gas turbine engine cooling fluid composite tube

A cooling arrangement for a turbine engine includes a cooling source and first and second structures. A ceramic-based composite cooling tube fluidly provides a fluid connection between the first and second structures.
United Technologies Corporation

Gas turbine engine component with an abrasive coating

A gas turbine engine component having a raised rim located along one or more edges of a tip region of the component, and an abrasive coating formed of hard particles embedded in a retaining matrix covering the tip region within an area bounded by the raised rim.. .
Rolls-royce Plc

Rotary blade manufacturing method

The present invention provides a method of designing a manufacturing geometry for a tip portion of a rotary blade for a gas turbine engine. The method comprises first devising a theoretical hot running geometry of the tip portion at a specified design condition.
Rolls-royce Plc

Gas turbine engine component with diffusive cooling hole

A component for a gas turbine engine includes a gas path wall having a first surface, a second surface exposed to hot gas flow, and a cooling hole extending through the gas path wall. The cooling hole includes an inlet formed in the first surface, an outlet formed in the second surface, cooling hole surfaces that define the cooling hole between the inlet and the outlet, and a longitudinal ridge formed along at least one of the cooling hole surfaces.
United Technologies Corporation

Method for forming components using additive manufacturing and re-melt

A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified..
United Technologies Corporation



Gas Turbine Engine topics:
  • Gas Turbine
  • Gas Turbine Engine
  • Downstream
  • High Speed
  • Circulation
  • Heat Exchanger
  • Attenuation
  • Variable Inlet Guide Vanes
  • Variable Inlet Guide Vane
  • Guide Vane
  • Guide Vanes
  • Inlet Guide Vanes


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    This listing is a sample listing of patent applications related to Gas Turbine Engine for is only meant as a recent sample of applications filed, not a comprehensive history. There may be associated servicemarks and trademarks related to these patents. Please check with patent attorney if you need further assistance or plan to use for business purposes. This patent data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Gas Turbine Engine with additional patents listed. Browse our RSS directory or Search for other possible listings.


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