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Gas Turbine patents

      

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




 Swirler for a burner of a gas turbine engine patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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


 Operation of a gas turbine system in part load operation patent thumbnailnew patent Operation of a gas turbine system in part load operation
A method for operating a gas turbine system in part load operation wherein a compressor pre-guide blade adjustment for part load operation is initiated in case of a given state of a flow medium which flows into a compressor, a value of the initiated compressor pre-guide blade adjustment is compared with a compressor pre-guide blade adjustment limit value which is determined depending on the state of the flow medium, and, if the value of the initiated compressor pre-guide blade adjustment meets a predefined condition with regard to the compressor pre-guide blade adjustment limit value, at least one measure is initiated for changing the state of the flow medium which flows into the compressor in part load operation. An arrangement has an actuating device, determining device and control unit to carry out the method.
Siemens Aktiengesellschaft


 Fan blade attachment root with improved strain response patent thumbnailnew patent 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 patent thumbnailnew patent 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.


new patent

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

new patent

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

new patent

Operation of a gas turbine plant having a compressor and a turbine

A method for operating a gas turbine plant having a compressor and a turbine, where a limit value of a guide blade adjustment for the compressor of the gas turbine is identified depending on at least one drive shaft speed of the gas turbine plant. For the at least one drive shaft speed, a maximum allowable turbine entry temperature corresponding to the limit value of the guide vane adjustment for the compressor or a maximum allowable temperature for the turbine of the gas turbine, which is dependent on the turbine entry temperature, is identified.
Siemens Aktiengesellschaft

new patent

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

new patent

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

new patent

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

new patent

Universal zero carbon thermal electric clean engines with maximum absolute efficiency and power density, and supreme universal mobility

This universal technology eternal zero carbon, thermal electric clean engines and gas turbines, with universal cryogenic eternal systems converting all gases in cryogenic working fluids, for solar/atmospheric and geo thermal energy eternal systems, is eliminating 100% all the fossil fuels from energy and universal mobility, variable power, with constant maximum compression pressure and constant maximum combustion pressure, resulting constant maximum efficiency in all the variable eternal power electric generation and universal mobility systems.. .

new patent

Advanced humid air turbine system and exhaust gas treatment system

An exhaust gas treatment system for an advanced humid air turbine system includes a water recovery unit for recovering a moisture contained in an exhaust gas discharged from a gas turbine system by cooling the exhaust gas with a coolant, and an exhaust gas reheater disposed downstream of the water recovery unit with respect to the flow of the exhaust gas, for heating the exhaust gas that has passed through the water recovery unit with a heat medium. The coolant that has exchanged heat with the exhaust gas in the water recovery unit is used as the heat medium for the exhaust gas reheater..
Mitsubishi Hitachi Power Systems, Ltd.

new patent

Gas turbine diffuser outer diameter and inner diameter wall strips for turbine exhaust manifold pressure oscillation reduction

An arrangement to minimize vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a projection coupled to an inner cylindrical surface or the outer cylindrical surface of a fluid flow path of the gas turbine exhaust diffuser.
Siemens Energy, Inc.

new patent

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

new patent

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.

new patent

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

new patent

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

new patent

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.

new patent

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.

new patent

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.

new patent

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.

new patent

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.

new patent

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.



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


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    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.


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