190 results about "Axial turbine" patented technology

There has been invented a turbine engine with a single rotor which cools the engine, functions as a radial compressor, pushes air through the engine to the ignition point, and acts as an axial turbine for powering the compressor. The invention engine is designed to use a simple scheme of conventional passage shapes to provide both a radial and axial flow pattern through the single rotor, thereby allowing the radial intake air flow to cool the turbine blades and turbine exhaust gases in an axial flow to be used for energy transfer. In an alternative embodiment, an electric generator is incorporated in the engine to specifically adapt the invention for power generation. Magnets are embedded in the exhaust face of the single rotor proximate to a ring of stationary magnetic cores with windings to provide for the generation of electricity. In this alternative embodiment, the turbine is a radial inflow turbine rather than an axial turbine as used in the first embodiment. Radial inflow passages of conventional design are interleaved with radial compressor passages to allow the intake air to cool the turbine blades.

A turbocharger, having an axial compressor wheel and an axial turbine wheel mounted on a first shaft supported by a housing, and a radial compressor wheel and a radial turbine wheel mounted on a second shaft, the second shaft concentrically extending around the first shaft and being supported by the housing. The housing defines a first duct extending axially from the exducer of the axial compressor to the inducer of the radial compressor, and a second duct extending axially from the exducer of the radial turbine to the inducer of the axial turbine. A plurality of controllable compressor guide vanes extend through the first duct, and a plurality of controllable turbine stator vanes extend through the second duct. The housing is provided with variable diffuser vanes at the exducer of the radial compressor, and with variable turbine vanes at the inducer of the radial turbine. The variable turbine vanes and the turbine stator vanes are controlled to accurately control the rotation rate of the radial and axial turbines. The compressor guide vanes are controlled to minimize surge and maximize choke flow rate.

This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The abradable coating system includes columns of an abradable material. Thus, interference between the blades and the abradable coating system causes the individual columns to break off at the base. This abrasion mechanism may reduce blade wear and spalling of the coating system when compared to conventional coatings.

An axial turbine has a turbine stage including stator blades fixedly provided on a stationary section and moving blades fixedly provided on a rotating section and has a structure in which a flow blowing out from a space formed between the stator blades and the moving blades exists. In order to prevent a decrease in stage output power due to such blowout flow thereby to improve the turbine stage efficiency, the axial turbine comprises a member coupling an inner circumferential side of the stator blades, and a structure provided on a surface of the member opposed to the moving blades for bending a flow blowing out from the side of the rotating section into a space between the stator blades and the moving blades in a rotational direction of the rotating section.

The present application relates to an axial turbine engine with a turbine, a low-pressure compressor, and a fan. The turbine drives the compressor and the fan via a plurality of epicyclic reducing gears. The rotor of the compressor includes upstream a disc with a row of vanes and downstream a drum with a plurality of rows of vanes. The disc and the drum are connected to different parts of the epicyclic reducing gears, so as to be counter-rotating. The turbine engine includes a row of stator vanes arranged between two rows of rotor blades of the drum of the compressor, so as to straighten the flow and improve the efficiency. The turbine engine includes at least two epicyclic reducing gears, so that the vane rows of the drum turn faster than that downstream, which itself turns faster than the fan.

A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.

In an axial turbine wheel including a rotor disk and a plurality of turbine blades each having a base end retained by the rotor disk via a joint and extending radially from the rotor disk, a seal plate is received in outer and annular slots formed in the base ends of the turbine blades and rotor disk, respectively, and an annular shoulder is formed in the wall defining the inner annular slot on a side remote from the rotor disk, the annular shoulder thereby defining an inner narrow section and an outer wide section in the inner annular slot. Thus, the seal plate can be easily placed in position by first fitting the inner peripheral edge thereof in the inner narrow section of the inner annular slot, fitting the outer peripheral edge thereof in the outer annular slot until the inner peripheral edge clears the annular shoulder. Thereby, the outer and inner peripheral edges of the seal plate are received in the outer annular slot and outer wide section of the inner annular slot. The outer peripheral edge of the seal plate may abut the bottom of the outer annular slot so as to allow the seal plate to be firmly retained even when subjected to a large centrifugal force.

An electrical energy generating system is mounted on a structure and includes a ducted shroud facing the wind and concentrating its flow through Coanda effect to inlet mouths each directed to a respective one of a plurality of small centrifugal or axial turbines connected to brushless DC generators. The air exits each turbine axially and is directed to flow along the wall, merging with the natural vertical airflow and is discarded at the top of the structure where another deflector creates a negative pressure helping the residual airflow to merge with wind blowing over the top. The efficiency of generation is proportional to the difference between the front wind pressure and the back air pressure. While each wind cell generates only a few tens of watts, the array can generate a large amount of electricity to be used for the structure and/or to be made available to a grid.

A method of constructing self-powered air-conditioner comprises a convergent divergent nozzle where powered fan pushes air into said nozzle. While the pushed air accelerates toward the nozzle throat it becomes colder as air internal energy transformed into kinetic energy. An axial turbine installed within the nozzle throat extracts energy from the air in the nozzle and drives an electrical generator that provides electricity to the fan electric motor. Alternatively the turbine and fan are installed on common shaft, which could be the electric generator shaft. The cold air within the nozzle throat cools the nozzle throat skin, which serves as air-conditioner core. The cold nozzle skin is wrapped with coiled pipes in which liquid flows, becomes colder and this cold liquid flows away to heat exchanger where air is flowing through it and becomes colder. This cold air is then flows into spaces needed to be air-conditioned.

A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.

A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

The present application relates to a stator for a low-pressure compressor of an axial turbine engine. The stator includes an annular row of stator vanes with connection vanes, and support vanes which are grouped into vaned casings. The casings include internal platforms and external platforms, and are integrally produced by means of additive production based on titanium powder. The stator has a circular internal shroud which is formed by the internal platforms of the vanes of the casings and internal shroud segments which are fixed to the connection vanes. The internal platforms include pairs of contact surfaces in order to interlock the shroud segments therein by moving into abutment and sliding against the contact surfaces. The contact surfaces are perpendicular to the rotation axis and form axial stops.

A rotor, in particular a drum of a low-pressure compressor of a turbojet aero engine, is disclosed. The rotor includes an outer annular wall delimiting a primary annular flow of the turbine engine, sealing devices with two rubbing strips or annular ribs formed on the wall. The rubbing strips cooperate by abrasion with inner shrouds. In addition, the annular wall includes rows of intake orifices for leakages which are arranged between each pair of rubbing strips in order to aspirate the recirculation leakages there. A plenum for leakages is formed inside the rotor by means of a composite partitioning, then evacuates the parasitic flow downstream of the turbine engine via the central shaft.

A turbine (100) of a turbine installation, especially a steam turbine of a steam turbine installation, includes at least one radial or diagonal turbine stage (120) with radial or diagonal inflow and axial outflow, and also at least one axial turbine stage (121-125) with axial inflow and axial outflow. The at least one radial or diagonal turbine stage (120) forms the first stage of the turbine (100) and the at least one axial turbine stage (121-125) is arranged downstream of the radial or diagonal turbine stage (121) as an additional stage of the turbine. The at least one radial or diagonal turbine stage (120) has a higher temperature resistance than the at least one axial turbine stage (121-125). The turbine (100) makes it possible to significantly increase the process temperature of the steam turbine installation, wherein measures for increasing the temperature resistance need only to be adopted for components of the radial or diagonal turbine stage (120).