Follow us on Twitter
twitter icon@FreshPatents


Gas Turbine patents

      

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




 Combustor replacement method and gas turbine plant patent thumbnailCombustor replacement method and gas turbine plant
A combustor replacement method and a gas turbine plant capable of efficiently replacing a combustor using an existing facility. The combustor replacement method includes a step of separating, from a plurality of fuel supply systems, a first combustor that includes a plurality of nozzle systems connected to any of the plurality of fuel supply systems and supplied with fuel from the connected fuel supply systems, and removing the first combustor from a gas turbine plant.
Mitsubishi Hitachi Power Systems, Ltd.


 Combustor for a gas turbine engine patent thumbnailCombustor 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


 Axial flow compressor, gas turbine including the same, and stator blade of axial flow compressor patent thumbnailAxial flow compressor, gas turbine including the same, and stator blade of axial flow compressor
An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion.
Mitsubishi Hitachi Power Systems, Ltd.


 Method and arrangement for gas turbine engine surge control patent thumbnailMethod 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


 Sealing arrangement for gas turbine transition pieces patent thumbnailSealing arrangement for gas turbine transition pieces
A sealing arrangement for sealing between adjacent first and second exit frames each associated with a transition piece of a turbine. The arrangement includes a transition side seal having bristles that extend from a rail wherein the rail is bendable in a plurality of directions to accommodate bowing of an associated exit frame.
Siemens Energy, Inc.


 Cooling system patent thumbnailCooling 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


 Power generation system patent thumbnailPower generation system
A power generation system, including: a solar energy concentration system, a biomass gasification device, a gas-powered generator, a steam turbine, a steam-powered generator. The solar energy concentration system is connected to a solar energy heat exchange system.
Wuhan Kaidi Engineering Technology Research Institute Co., Ltd.


 Handling device patent thumbnailHandling device
A handling device is provided for handling a burner of a stationary gas turbine during assembly and disassembly, including a base body having at least one contact surface designed to contact a rear end surface of a burner, fixing means for fixing the base body to the rear end surface of the burner, and two arms fixed to and protruding from the base body to different sides of the contact surface, wherein each arm is provided with receiving means, which are designed for removably receiving a fixing component of a lifting appliance and which are spaced apart from each other in the longitudinal direction of a burner during its handling.. .
Siemens Aktiengesellschaft


 Bearing support housing for a gas turbine engine patent thumbnailBearing 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 patent thumbnailGas 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


First stage turbine vane arrangement

A first stage vane arrangement having an array of first stage vanes and an array of frame segments and method for cooling frame segments of the first vane arrangement of a gas turbine are disclosed. The frame segments are designed for axially receiving aft ends of a combustor transition pieces.
Ansaldo Energia Switzerland Ag

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

Magnetic sensor system for detecting abnormal movement in a gas turbine shaft

The present invention relates to a system (100, 300, 400) for detecting abnormal movement of a gas turbine shaft. The system comprises: a magnetic circuit (104, 302, 402) comprising a first magnetic portion (110, 304) and a second portion (112, 404), and including at least one air gap between the first portion and the second portion; and a detection coil (106) wound around the first magnetic portion.
Weston Aerospace Limited

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

The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.. .
Mtu Aero Engines Ag

Method for repairing a gas turbine blade having at least one cavity

Disclosed is a method of repairing gas turbine blade which has at least one cavity and which has damage in the region of its blade tip, which damage extends through a rim region and a core region of the blade into the at least one cavity. The method comprises at least: a) removing blade material at least in the region of the damage, forming at least one cutaway reaching into the cavity; b) replacing the damaged region by filling the at least one cutaway with a repair material using at least one generative production method; and c) finishing the blade at least in the region of the at least one refilled cutaway.
Mtu Aero Engines Ag

Cowling part and combustor assembly for a gas turbine

A covering part for a combustion chamber of a gas turbine is configured and provided to guide a fluid flow downstream of a diffuser of the gas turbine at least partially into a flow area outside of a combustion space of the combustion chamber so as to cool a combustion chamber wall that delimits the combustion space and has at least one mounting edge at which at least one attachment site is provided for fixating the covering part at the combustion chamber wall by means of a separate attachment element. At least one guiding element is provided at the covering part in the area of the mounting edge, which during operation of the gas turbine guides the partial flow of the fluid flow to be guided in the direction of the flow area over and above a part of the attachment element that protrudes from the mounting edge..
Rolls-royce Deutschland Ltd & Co Kg

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

Diffuser part for a gas turbine

A diffuser component for a gas turbine is provided, where a fluid flow in the direction of a combustion chamber of the gas turbine can be slowed down by the diffuser component, and a flow cross-section of the diffuser component, which is defined by a diffuser wall is widened to do so. The diffuser wall is at least locally braced, in that at least one stiffening element with a lattice-type structure is provided on the diffuser wall..
Rolls-royce Deutschland Ltd & Co Kg

A casing made of organic matrix composite material that facilitates the discharge of smoke

A gas turbine casing made of organic matrix composite material includes reinforcement densified by an organic matrix defines an inside volume. On its inside face the casing has a structural part with a first face facing the inside face of the casing, and an opposite second face defining a flow passage portion.
Snecma

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


  • Follow us on Twitter
    twitter icon@FreshPatents

    ###

    This listing is a sample listing of patent applications related to Gas Turbine 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 with additional patents listed. Browse our RSS directory or Search for other possible listings.


    1.0377

    file did exist - 2884

    0 - 1 - 58