4466results about "Turbine/propulsion engine cooling" patented technology

A power generation system capable of eliminating NO, components in the exhaust gas by using a 3-way catalyst, comprising a gas compressor to increase the pressure of ambient air fed to the system; a combustor capable of oxidizing a mixture of fuel and compressed air to generate an expanded, high temperature exhaust gas; a gas turbine engine that uses the force of the high temperature gas; an exhaust gas recycle (EGR) stream back to the combustor; a 3-way catalytic reactor downstream of the gas turbine engine outlet which treats the exhaust gas stream to remove substantially all of the NOx components; a heat recovery steam generator (HRSG); an EGR compressor; and an electrical generator.

A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween including a plurality of axial channels (C) extending over a portion of an aft end portion of the liner parallel to each other, the cross-sectional area of each channel either constant or varying along the length of the channel, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.

A method and apparatus for increasing the efficiency of a combined cycle generation plant by assisting the vaporization of cold liquid including liquefied natural gas ("LNG") or liquefied petroleum gas (LPG) in a combined cycle power plant. Cold liquid vaporization is assisted by circulating a warm heat transfer fluid to transfer heat to a LNG / LPG vaporizer. The heat transfer fluid is chilled by LNG / LPG cold liquid vaporization and warmed by heat from a gas turbine. The heat transfer fluid absorbs heat from the air intake of a gas turbine and from a secondary heat transfer fluid circulating in a combined cycle power plant. Chilling the gas turbine air intake densifies the air and increases the gas turbine output. Chilling the steam condenser cooling water increases steam turbine output. The effects of chill recovery is higher output and better efficiency of the combined cycle plant.

A system comprises a rotary apparatus, a control law and a processor. The rotary apparatus comprises a rotor and a housing forming a gas path therebetween, and the control law controls flow along the gas path. The processor comprises an output module, a plurality of temperature modules, a thermodynamic module, a comparator and an estimator. The output module generates an output signal as a function of a plurality of rotor and housing temperatures defined along the gas path, and the temperature modules determine time derivatives of the rotor and housing temperatures. The thermodynamic module models boundary conditions for the gas path, and the comparator determines errors in the boundary conditions. The estimator estimates the rotor and housing temperatures based on the time derivatives, such that the errors are minimized and the flow is controlled.

A gas turbine engine cooling system includes a heat exchanger in fluid communication with a source of cooling air, a first cooling circuit including a first heat exchanger circuit in the heat exchanger and a first bypass circuit with a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit. A second cooling circuit may be used having a second heat exchanger circuit in the heat exchanger and a shutoff control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit and the heat exchanger. A circuit inlet of the first cooling circuit may be used to bleed a portion of compressor discharge bleed air for the first airflow to cool turbine blades mounted on a rotor disk using an annular flow inducer downstream of the first bypass valve and the heat exchanger.

Compressor discharge air flows through a heat exchanger in heat exchange relation with cooling water and is supplied at reduced temperature in atomizing air and purge modes to combustors in a dual-fuel gas turbine. The heat exchanger has a pair of bypass passages in parallel with a temperature regulating valve controlling flow of water through the heat exchanger in response to the temperature of the compressor discharge air exiting the heat exchanger. Should the flow control valve close in response to low temperature of the compressor discharge air, in the air atomizing mode, the bypass passages with orifices therein provide a minimum protective flow of cooling water to the heat exchanger. In the purge mode where only half the air flow and heat rejection is required in the heat exchanger and the flow control valve closes, a bypass valve in one of the bypass passages closes to enable reduced flow of cooling water through the heat exchanger.

A process and system which improves the capacity and efficiency of a power plant. A LNG supply system fuels the plant. Gasified LNG in a combustor mixes with the air from an air compressor to provide the hot combustion gas for a gas turbine. The expanding LNG is used to chill a heat exchange fluid, e.g. water, which heat exchange fluid cools and densifies the intake air for the air compressor. Subsequently, the heat exchange fluid is used in another heat exchange step and is then re-chilled and recycled to cool and densify the intake air.

A mid turbine frame is disposed between high and low pressure turbine assemblies. A cooling air system defined in the mid turbine frame of a gas turbine engine includes internal cavities for containing pressurized cooling air to cool the inter-turbine duct and the hollow struts, and discharges the used cooling air to further cool respective high and low pressure turbine assemblies.

A method and system for operating at partial load a gas turbine system having a compressor, a combustor, and a turbine. The method and system may include the steps of lowering a flow of fuel to the combustor, extracting air from the compressor so as to lower a flow of air to the compressor, and returning the extracted air to the turbine or a component of the gas turbine system other than the combustor. Extracting air from the compressor raises a combustion temperature within the combustor. Raising the combustion temperature maintains a combustion exhaust below a predetermined level, maintains stable combustion, and extends turbine turndown values.

A method for supplying power to a remote load includes coupling a gas turbine engine to a vessel that is not used to provide propulsion for the vessel, coupling a generator to the gas turbine engine, coupling an intercooler system downstream from a first compressor such that compressed air discharged from the first compressor is channeled therethrough, the intercooler system includes an intercooler and a first heat exchanger, channeling a first working fluid through the intercooler to facilitate reducing an operating temperature of air discharged from the intercooler to a second compressor, channeling a second working fluid flowing through the first heat exchanger to extract energy from the first working fluid to facilitate reducing an operating temperature of the first working fluid, and operating the gas turbine engine and generator to supply power to a load that is located remotely from the vessel.

A method for assembling a turbine engine includes assembling a heat exchanger assembly that includes at least a radially inner plate, a radially outer plate, and a heat exchanger coupled between the radially inner and outer plates, forming the heat exchanger assembly such that the heat exchanger assembly has a substantially arcuate shape, and coupling the heat exchanger to a fan casing such that the heat exchanger is positioned upstream or downstream from the fan assembly.

A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system in operable communication with the engine, a fuel source to supply a fuel, a fuel stabilization unit to receive the fuel from the fuel source and to provide the fuel to the engine, and a heat exchanger in thermal communication with the fuel to transfer heat from the heat generating sub-system to the fuel. A method of managing thermal transfer in an aircraft includes removing oxygen from a stream of a fuel fed to an engine used to drive the aircraft, transferring heat from a heat generating sub-system of the aircraft to the fuel, and combusting the fuel. A system for the thermal management of an aircraft provides for powering the aircraft, supplying a fuel deoxygenating the fuel, and transferring heat between a heat generating sub-system of the aircraft and the fuel.

The invention discloses a sound insulation cabin of a turbine engine. The sound insulation cabin is arranged on the turbine engine in a sleeving mode, and comprises a cabin body, an intake noise reduction unit and a ventilation noise reduction unit; the intake noise reduction unit and the ventilation noise reduction unit are arranged on the cabin body, and the periphery of the cabin body is filledwith sound insulation materials; and the intake noise reduction unit is used for intake noise reduction of the turbine engine, and the ventilation noise reduction unit is used for noise reduction ofa ventilation system of the turbine engine. The sound insulation cabin has the beneficial effects that the intake noise reduction unit is additionally arranged at an air inlet of the turbine engine, and intake noise reduction of the turbine engine is achieved; the ventilation noise reduction unit is additionally arranged in the transmission direction of the turbine engine, and the ventilation andcooling noise reduction for the turbine engine is achieved; the periphery of the cabin body is filled with the sound insulation materials, and the overall noise reduction for the periphery of the turbine engine is achieved.

Embodiments of a power provision system of the present invention generally include a transformer, a drive assembly, a motor control center, rectifiers, circuit breakers, and a cooling system, all of which are enclosed in a cabinet that is divided into a plurality of compartments that house various components and that is adapted and configured to be skid mounted on a trailer. In one embodiment, high voltage power is supplied to the power provision system, wherein it is stepped down to lower voltages by the transformer and the lower voltage power is utilized to drive a fracking pump motor via the drive assembly, as well as auxiliary equipment, such as the cooling system, via the motor control center. Embodiments of a method of using the power provision system are also provided.

An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented. In order to achieve the object, the present invention provides a ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades comprising a plurality of individual units which define an annular form by being arranged around the peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from the tips of the moving blades, wherein grooves which extend along the axial direction of the main shaft of the turbine are formed upon of the individual units so as mutually to confront one another; a seal plate which is inserted into each mutually confronting pair of the grooves so as to connect together the adjacent pair of individual units; and contact surfaces which are formed at positions more radially inward than the seal plates, which extend in the axial direction and the peripheral direction and which mutually contact one another.

The power plant combusts a hydrocarbon fuel with oxygen to produce high temperature high pressure products of combustion. These products of combustion are routed through an expander to generate power. The products of combustion are substantially free of oxides of nitrogen because the oxidizer is oxygen rather than air. To achieve fast starting, oxygen, fuel and water diluent are preferably stored in quantities sufficient to allow the power plant to operate from these stored consumables. The fuel can be a gaseous or liquid fuel. The oxygen is preferably stored as liquid and routed through a vaporizer before combustion in a gas generator along with the hydrocarbon fuel. In one embodiment, the vaporizer gasifies the oxygen by absorption of heat from air before the air is routed into a separate heat engine, such as a gas turbine. The gas turbine thus operates on cooled air and has its power output increased.

A gas turbine vane to improve vane performance by addressing known failure mechanisms. A cooling circuit to the trailing edge of a vane airfoil is fed from the outer diameter platform, which prevents failure due to an oxidized and eroded airfoil trailing edge. The gas turbine includes an outer diameter platform, a hollow airfoil and an inner diameter platform with a plurality of cooling tubes extending radially through the airfoil. The cooling tubes are open at the outer diameter end and closed with covers at the inner diameter end. The inner diameter platform is also cooled and includes a meterplate for a portion of the cooling passageway and includes an undercut to improve thermal deflections of the inner diameter platform.

The present invention generally relates to a system that enables one to address various thermal management issues in advanced gas turbine engines. In one embodiment, the present invention relates to a method to extract heat from an air stream, utilize a significant fraction for on-board power generation, and reject a small quantity of heat to the fuel stream safely at, for example, a lower temperature. In another embodiment, the present invention relates to a method to extract heat from an air stream, utilize a significant fraction for on-board power generation, and reject a small quantity of heat to the fuel stream safely at, for example, a lower temperature with no potential air / fuel contact is disclosed.

Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least two heat exchangers are associated with the reservoir and operable to effect condensation of vaporized cooling fluid and return of same to the reservoir. Preferably the apparatus is a closed system incorporating three heat exchangers respectively adapted to effect heat exchange with engine fuel, compressed air derived from a fan or low pressure compressor of the engine and ambient air. Means may advantageously be provided to ensure return of condensed cooling fluid to the reservoir when the attitude of the reservoir is altered as a result of aircraft maneuvers.

Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air / fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.

A motor driven assembly includes a motor having a motor shaft mounted for rotation about a rotational axis and a rotor radially located about the shaft. The motor drives a compressor that receives air from the motor, compresses the air, and circulates the compressed air to a space. The motor includes a first cooling flow passage and a second cooling flow passage that each receive air to provide internal cooling of the motor. A portion of the air compressed in the compressor is diverted from the compressor to a heat exchanger. The heat exchanger cools the compressed air from before the air circulates into the first cooling flow passage to cool the motor. The second cooling flow passage receives air from the environment surrounding the motor driven assembly to further cool the motor.

The invention relates to an air-oil heat exchanger located at the inner shroud of the secondary duct of a turbojet. In characteristic manner, it comprises an oil circuit placed inside the separator nose and fins placed outside the top wall of the separator nose, between the leading edge of the separator nose and the outlet guide vanes.

The invention discloses a movable electric power system. The whole movable electric power system is divided into two transport tools, effective integration is achieved, and the number of the transporttools and transport cost are decreased. Through side connection of the two transport tools, fast and convenient connection in the working state is achieved, and the needed installation time is greatly shortened. By arranging a gas turbine starting device on a gas exhaust auxiliary transport unit, a gas turbine can be started when the whole movable electric power system is blacked out.

A dual wall structure for a combustor of a gas turbine engine including an inner liner and an outer liner coupled to a combustor dome and defining a combustion chamber there between. Each of the inner liner and the outer liner include an outer wall and an inner wall. Each of the outer walls includes a plurality of impingement holes formed therein for allowing a coolant to flow therethrough. Each of the inner walls is coupled to the outer wall via a plurality of threaded studs and includes a plurality of forward heat shield panels and a plurality of aft heat shield panels. Each of the plurality of forward heat shield panels and aft heat shield panels includes a plurality of side rails, a forward rail, and an aft rail including a plurality of controlled openings, that when coupled to the outer wall defines a single cavity there between. A plurality of cavities being formed by the plurality of forward and aft heat shield panels.

A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.

The invention discloses turbine fracturing equipment. The turbine fracturing equipment comprises a transporting device, a turbine engine, a reduction gearbox, a transmission mechanism and a fracturingpump, wherein the output end of the turbine engine is connected with one end of the reduction gearbox; the other end of the reduction gearbox is in transmission connection with the fracturing pump; the transportation device is used for bearing the turbine engine, the reduction gearbox, the transmission mechanism and the fracturing pump and comprises a chassis; the chassis is provided with a transporting section, a bearing section and a lapping section which are connected in sequence; when the turbine fracturing equipment is in a working state, the bearing section can be contacted with the ground; and when the turbine fracturing equipment is in a transporting state, the bearing section does not make contact with the ground. The turbine fracturing equipment has the beneficial effects that the equipment adopts the design of linear connection and a special chassis, so that the gravity center of the turbine fracturing equipment is doubly reduced, and the stability and the safety are well ensured; the structure is simpler, and the investment cost and the operation cost are reduced; the collapse risk of the whole fracturing site is reduced; and the turbine fracturing equipment is good intransmission property and is suitable for long-time and bulky load continuous operation conditions.