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Gas Turbine Engine patents

      

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




 Non-destructive inspection apparatus patent thumbnailNon-destructive inspection apparatus
A non-destructive inspection apparatus is configured to perform non-destructive inspection of a bonded place between a base material and a bonding material of a gas turbine engine part formed by bonding the bonding material formed of a metal material to the base material formed of a fiber-strengthened material, and includes a moving apparatus configured to move the gas turbine engine part, a light source apparatus configured to emit a laser beam, an infrared imaging apparatus configured to image the gas turbine engine part to which the laser beam is radiated, and a control and arithmetic processing apparatus configured to store form data of the gas turbine engine part, control the moving apparatus such that the laser beam is radiated to the bonded place based on the form data, and obtain a result showing a state of the bonded place based on imaging data obtained by the infrared imaging apparatus.. .
Ken Automation, Inc.


 Combustor shape cooling system patent thumbnailCombustor shape cooling system
A gas turbine engine includes a combustor which has at least one annular wall defining a combustion chamber therein. The annular wall is formed by a circumferential array of panels overlapping one with another to define a plurality of radial gaps between respective adjacent two panels.
Pratt & Whitney Canada Corp.


 Combustor hole arrangement for gas turbine engine patent thumbnailCombustor hole arrangement for gas turbine engine
A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole..
United Technologies Corporation


 Apparatus and  water and ice flow management in a gas turbine engine patent thumbnailApparatus and water and ice flow management in a gas turbine engine
A compressor of a gas turbine engine includes at least one rotor, and at least one stator, wherein the at least one stator includes a water channel wall located on a surface of the stator, wherein the water channel wall is configured to direct water away from a center line of the turbine engine and is located an offset distance from an outside wall of the compressor, wherein the offset distance is zero percent to twenty percent of the span of the stator.. .
United Technologies Corporation


 Panel for lining a gas turbine engine fan casing patent thumbnailPanel for lining a gas turbine engine fan casing
A panel for lining a gas turbine engine fan casing includes a honeycomb core sandwiched between a backing skin and an outer skin. The backing skin is attached to an inner surface of the casing such that the outer skin forms a radially inward facing surface of a fan duct of the engine.
Rolls-royce Plc


 Integrated environmental control system manifold patent thumbnailIntegrated environmental control system manifold
A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge.
United Technologies Corporation


 Gas turbine engine stall margin management patent thumbnailGas turbine engine stall margin management
A method for operating a gas turbine engine having a starter-electric generator driven by one of a plurality of shafts of the gas turbine engine is provided. The method includes determining a desired amount of thrust to be produced by the gas turbine engine, as well as a desired amount of electrical power to be drawn from the starter-electric generator of the gas turbine engine.
General Electric Company


 Heat exchanger for a gas turbine engine propulsion system patent thumbnailHeat exchanger for a gas turbine engine propulsion system
A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine..
Rolls-royce North American Technologies, Inc.


 Folded heat exchanger for cooled cooling air patent thumbnailFolded heat exchanger for cooled cooling air
A heat exchanger (hex) for cooling air in a gas turbine engine is provided. The hex may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion.
United Technologies Corporation


 Heat exchanger for cooled cooling air patent thumbnailHeat exchanger for cooled cooling air
A heat exchanger (hex) for cooling air in a gas turbine engine is provided. The hex may comprise an intake manifold in fluid communication with a compressor section and configured to receive air from the compressor section, an outtake manifold in fluid communication with the intake manifold via a tube, and a cooling air flow path defined by at least one of an outer surface of the tube, an outer surface of the intake manifold, and an outer surface of the outtake manifold, wherein the cooling air flow path is orthogonal to said tube.
United Technologies Corporation


Heat exchanger for cooled cooling air with adjustable damper

A heat exchanger (hex) for cooling air in a gas turbine engine is provided. An adjustable damper is provided.
United Technologies Corporation

Pre-diffuser with high cant angle

A gas turbine engine is provided. The engine includes a combustor configured at a combustor angle relative to an engine axis and a pre-diffuser configured to supply air to the combustor and configured at a diffuser angle relative to the engine axis, wherein the diffuser angle is greater than the combustor angle.
United Technologies Corporation

Blade outer air seal for a gas turbine engine

A gas turbine engine includes a turbine section including a plurality of blade outer air seals (boas) disposed therein, the boas including a boas body including a plurality of cooling holes defined in substantial conformance with a set of cartesian coordinates as set forth in at least one of table 1 and table 2.. .
United Technologies Corporation

Flexibly mounted ceramic matrix composite seal segments

A segmented turbine shroud for radially encasing a turbine in a gas turbine engine comprises a carrier comprising a flange; a ceramic matrix composite (cmc) seal segment comprising a portion defining a pin-receiving bore; an elongated pin extending through the pin-receiving bore; a bushing surrounding the elongated pin within the bore; and a flexible mounting member, the flexible mounting member being connected to the bushing and the carrier flange to thereby flexibly mount the cmc seal segment to the carrier.. .

Turbine shroud having ceramic matrix composite seal segment

A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (cmc) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the cmc seal segment defines a pin-receiving seal segment bore.

Turbine shroud segment sealing

An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments.
Pratt & Whitney Canada Corp.

Sealing attachment for a gas turbine engine

A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.. .
Rolls-royce Plc

Dual alloy gas turbine engine rotors and methods for the manufacture thereof

Dual alloy gas turbine engine (gte) rotors and method for producing gte rotors are provided. In one embodiment, the method include includes arranging bladed pieces in an annular grouping or ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces.
Honeywell International Inc.

Apparatus and cooling gas turbine engine components

A rotor assembly for a gas turbine engine includes a rotor disc having an axially extending rotor disc arm and a plurality of rotor blades extending radially outwardly from the rotor disc. A cover plate is located at an axial face of the rotor disc and at least partially retained at a rotor disc arm.
United Technologies Corporation

Monitoring system for a gas turbine engine

A method of monitoring a plurality of turbomachines is disclosed herein. In embodiments, the method includes a fleet data system receiving first event data from a first monitoring connection system and second event data from a second monitoring connection system.
Solar Turbines Incorporated

Monitoring system for a gas turbine engine

A system for monitoring a plurality of turbomachinery systems is disclosed herein. In embodiments, the system includes a monitoring system data provider, a plurality of monitoring system servers, and a monitoring device.
Solar Turbines Incorporated

Monitoring system for turbomachinery

A method of monitoring a gas turbine engine is disclosed herein. The method includes periodically receiving sensor data for the gas turbine engine at a monitoring device from a monitoring system server.
Solar Turbines Incorporated

Image conduit for fuel nozzle assemblies

A fuel nozzle for a gas turbine engine includes a feed arm including a fuel passage for issuing a spray of fuel. A nozzle assembly is fixed at an upstream end of the feed arm having a fuel inlet in fluid communication with the fuel passage.
Delavan Inc

Fuel nozzle having aerodynamically shaped helical turning vanes

A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.. .
Rolls-royce Plc

Free gas turbine with constant temperature-corrected gas generator speed

A method of controlling a speed of a gas turbine engine, the gas turbine engine including a high pressure spool and a low pressure spool rotating independently from one another, including determining a temperature-corrected rotational speed of the high pressure spool based on an actual rotational speed of the high pressure spool and on an air temperature measured outside of the gas turbine engine; controlling the rotation of the high pressure spool to maintain the temperature-corrected rotational speed of the high pressure spool at least substantially constant throughout a range of a power demand on the gas turbine engine; and controlling a rotational speed of the low pressure spool independently of the rotation of the high pressure spool.. .
Pratt & Whitney Canada Corp.

Air mixing systems having mixing chambers for gas turbine engines

Air mixing systems for gas turbine engines include a heat exchanger, a first extraction conduit fluidly coupled to an inlet of the heat exchanger, a second extraction conduit fluidly coupled to an outlet of the heat exchanger, an injection conduit fluidly coupled to the second extraction conduit, an onboard injector supply chamber fluidly coupled to the injection conduit, and an onboard injector fluidly coupled to the onboard injector supply chamber.. .
United Technologies Corporation

Systems and methods for augmenting gas turbine power output with a pressurized air tank and/or an external compressor

A system for augmenting gas turbine power output is disclosed. The system may include a gas turbine engine having a compressor, a combustor, and a turbine.
General Electric Company

Turbine shroud segment with side perimeter seal

A turbine shroud segment of a turbine shroud for use in a turbine of a gas turbine engine is disclosed herein. The turbine shroud segment includes a carrier segment and a blade track segment.
Rolls-royce North American Technologies, Inc.

Gas turbine engine component with performance feature

A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated..
Siemens Energy, Inc.

Rotating components with blind holes

A rotating component used in a gas turbine engine includes a body and a blind hole formed in the body. The blind hole is configured to receive a pin for locating a secondary component relative to the body..
Rolls-royce Corporation

Partial cavity baffles for airfoils in gas turbine engines

An airfoil of a gas turbine engine having a hollow body defining at least one airfoil cavity therein, the hollow body defining an inner diameter and an outer diameter and a baffle positioned within the at least one airfoil cavity and extending over less than an entire length between the inner diameter and the outer diameter, the baffle configured to reduce the cross-sectional area within the at least one airfoil cavity. The at least one airfoil cavity includes a first portion having a length that is defined by an open cavity having a full cross-sectional area and a second portion having a length that is defined by a reduced cross-sectional area, the second portion being the length of the baffle within the at least one airfoil cavity..
United Technologies Corporation

Auxillary power unit assembly and a using the same

The controller is operable to control a flow rate of a fuel supplied to the gas turbine engine responsive to a power demand on the auxiliary power unit, and also to restrict an inlet air flow into the gas turbine engine, so as to maintain an air pressure inside the aircraft cabin within a pre-determined range.. .

Combustor for a gas turbine engine

A combustor for a gas turbine engine which includes a flame tube made of a ceramic material and a metal casing which surrounds the flame tube. The combustor further includes a thermal insulation layer between the flame tube and the casing which protects the casing from the high temperatures produced by combustion in the combustor and a loading structure which holds the flame tube in a state of axial and radial compression at all engine operating conditions..
Rolls-royce Plc

Method and arrangement for gas turbine engine surge control

The invention relates to a surge control method for a gas turbine engine. The method includes providing a gas turbine engine having a compressor, a combustor, downstream of the compressor, with a hot gas path, a turbine downstream of the combustor, with a hot gas path.
General Electric Technology Gmbh

Cooling system

A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of heat source exchangers and at least one heat sink exchanger.
General Electric Company

Bearing support housing for a gas turbine engine

A bearing support housing for a gas turbine engine includes, in radial sequence from a center outwards: an inner ring defining a central bore; a middle ring including an array of inner slots, an outer web including an array of outer slots, wherein the inner and outer slots are positioned, sized, and shaped so as to divide the middle ring and the outer web into an array of tangentially-extending beams and radially-extending inner and outer struts; and an outer ring.. .
General Electric Company

Gas turbine engine frame assembly

A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section.
General Electric Company

Turbine vane rear insert scheme

An internally cooled turbine vane for a gas turbine engine has coolant flow channels between the interior walls of the vane and an insert, where the channels serve to convey a portion of the cooling air flow from a pressure side chamber to a suction side chamber. The turbine vane defines a radially extending passage with a dividing wall defining a front section and a rear section; the rear section having interior walls spaced apart from an insert to define the pressure side chamber and the suction side chamber.
Pratt & Whitney Canada Corp.

Use of ss data trends in fault resolution process

An automated method for resolving fault in an engine is disclosed. The method may include providing a reasoner module for recommending a set of maintenance actions to resolve fault in the engine, inputting steady state performance data from the engine into the reasoner module, and using the reasoner module to recommend a set of maintenance actions based at least in part on the steady state performance data.
United Technologies Corporation

Dynamic system estimation device and method

A dynamic system estimation device and method, whereby estimation for more performance parameters than there are sensors can be performed, the estimation taking temporal changes into account. The dynamic system estimation device includes: a prescribed number of sensors that detect prescribed observation values from a gas turbine engine; and a kalman filter that uses a dynamic model of the gas turbine engine and estimates the state of the gas turbine engine, on the basis of the observation values detected by the sensors.
Ihi Corporation

Turbine section with tip flow vanes

A turbine section of a gas turbine engine comprises a gas path having an outer boundary wall. A circumferential array of turbine blades projects radially into the gas path.
Pratt & Whitney Canada Corp.

Nozzle guide vane and forming such nozzle guide vane

A nozzle guide vane for a gas turbine engine includes an integrally formed angled nozzle with radially outer and inner platforms and an airfoil extending therebetween. An internal cooling air passage extends between the platforms.
Rolls-royce Deutschland Ltd & Co Kg

Turbine blade with hot-corrosion-resistant coating

A turbine blade of a gas turbine engine is described which includes an airfoil extending away from the hub platform to a blade tip. The airfoil defines a leading edge, a trailing edge, and a span-wise length extending between the platform and the blade tip.
Pratt & Whitney Canada Corp.

Turbine airfoils with micro cooling features

A blade used in a gas turbine engine includes a pair of pedestals and an airfoil coupled between the pedestals. The airfoil includes cooling features to cool the airfoil..
Rolls-royce 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 has a relationship between a stacking offset and a span position that includes at least one positive and negative slope.
United Technologies Corporation

Gas turbine engine combustor and forming same

A gas turbine engine combustor is described which includes outer and inner annular combustor liners formed of sheet metal. The exit duct circumscribes an annular combustor exit and defines a combustion gas path.
Pratt & Whitney Canada Corp.

Transfer bearing for geared turbofan

A gear reduction for a gas turbine engine comprises a carrier driven to rotate gears. The gears are supported by journal bearings.
United Technologies Corporation

Cooling system for a turbine engine

A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine.
General Electric Company

Fan blade with adhesive fabric stackup

A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material.
United Technologies Corporation

Fan blade with segmented fan blade cover

A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic body having a pressure side and a suction side.
United Technologies Corporation

Fan blade with composite cover and sacrificial filler

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover.
United Technologies Corporation

Fan blade with integrated composite fan blade cover

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side.
United Technologies Corporation

Fan blade with composite cover and structural filler

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover.
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 has a relationship between a tangential leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally s-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope.
United Technologies Corporation

Gas turbine engine airfoil

In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending 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 tangential leading and trailing edge curves and a tangential stacking offset curve.
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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