MXPA05006926A

MXPA05006926A - Universal engine for a multi-fuel radial gas turbine.

Info

Publication number: MXPA05006926A
Authority: MX
Inventors: Eduardo Lopez Sandoval; Juan Fernando Alcara Acosta
Original assignee: Juan Fernando Alcara Acosta
Priority date: 2005-06-23
Filing date: 2005-06-23
Publication date: 2007-01-10
Also published as: WO2006137723A1

Abstract

The present invention refers to a universal engine for a portable radial gas turbine, which uses any type of fuel including pure hydrogen and vapour, thus providing an affordable, ecological and effective engine compared to the state-of-the-art engines. The present invention is useful for generating power or propelling alternative transport means, the engine including two novel and simple pieces; an effective rotor and a novel stator, both elements generating a maximum mechanical power, thus actuating an electric generator for supplying power or propelling any alternative transport means, such as aircrafts, helicopters, automobiles, vertical take off vehicles, maritime vehicles, air cushion vehicles, or a combination thereof. The inventive engine is manufactured by a casting process in any size and material, and may be useful for any stationary industrial application, as well as robotic micro-machines and military applications.

Description

I. THE ROTOR. The rotor contained in this novel invention consists of a rotating mobile mechanical part with differentiated functional zones. The compressor-turbine rotor set is axial initial flow but radial final effect. The remarkable and transcendent difference of our rotor with respect to other rotors that are currently in the According to the state of the art for the same applications, the compressor-turbine set has a much more efficient shape than the current rotors, due to the air flow geometry involved. Novel, simple, practical and efficient, the parts of this rotor can be manufactured with great precision in cast steel, alloys, special polymers or any other new material used for the manufacture of gas turbines. Said rotor is basically formed by three zones: the compression zone with its exit arrow, the radial flow turbine area with reaction blades and the J 0 deflection zone of the exit gas. The output arrow is the mechanical power take-off or torque arrow where the shaft work or power delivery of the motor is performed, said mechanical element being the main axis of the motor itself and inherent to the rotor described herein. Said rotor is designed to rotate at approximately 30,000 revolutions per minute and withstand all the mechanical, thermal and corrosion stresses that this implies. Each part of the rotor is described below: a) Compression zone. Concentric to the main rotor shaft and inherent to it, (5) said zone is formed by axial compressor blades combined with radial compressor blades, separated from each other in a regular manner.Each axial compression blade is a blade very similar to the blades or blade elements of the propellers of an airplane, While each centrifugal compression vane has a semi-asymptotic transverse shape, with a superior brow bent at an optimum angle for air aspiration, each centrifugal compression vane is bent backward with respect to the direction of rotation of the rotor to compress a larger mass of air per unit of time with 0 less amount of energy, each vane, both centrifugal and axial, is attached to the output shaft in the center of said rotor in the form of exact regular angles.The compressor plate is formed by the surface of the rotor where each vane of the centrifugal compression zone and each vane of the turbine area are mounted, this air compression system is very efficient, since It allows to compress large amount of mass per unit of time and simultaneously combines the natural power of centrifugal compression with low energy demand of the axial compression, while the current compressors require a greater amount of kinetic energy extracted from the turbine to compress the same mass of air in a same time differential, so that those current compressors are less efficient than the present compressor described here, b) Radial flow turbine area. Concentric to the axis of the rotor and inherent in the horizontal periphery thereof, said zone for generating force is formed by a set of reaction blades separated from one another in a regular manner, adhered to the compressor plate and separated from it 0 By a distance of such circular crown, which is necessary to allow the optimal existence of the corresponding combustion zone, described later in the stator. These turbine blades are aerodynamically shaped reaction blades that use the Bernouili principle used in the transverse design of the wings of the aircraft, said blades are designed for high speed and serve to deflect the corresponding radial combustion force at an optimum angle, in a semi-opposite direction to that of rotor rotation, thereby generating a torca of instantaneous reaction in said direction, this reaction is multiplied by the number of blades that are subjected to the combustion force in the same time differential, forming with it and between all the turbine blades also due to the lever arm formed by the radius of the rotor, a very large integral of torque, which translates into a huge final mechanical power in the rotor shaft and by consequently a great turning force. The notable and transcendent difference with other turbines that are currently in the state of the art, is the physical form of each of the blades: 0 while those current blades are pressure, those of the present turbine are reaction, which for the effects of the gas exit velocity and the use of this velocity, it is much more efficient for us, a fact that is complemented by the next zone, the deviation of the exit gas, c) Departure gas diversion zone. Concentric to the axis of the rotor and inherent in the periphery of the same, said zone of deviation is formed by the physical prolongation of the surface of the plate or face of the compressor-turbine game, which first has a radial direction, 5 and then has a deflection in axial direction downwards with respect to the axis of the rotor. What it produces, is that after having burned the fuel and have passed through the blades of the turbine, this surface together with the surface of the stator, what they do between the two is to form a convergent annular nozzle that deflects downwards the output of the burnt gases, achieving a reaction effect that translates into an ascending vertical pushing force 5, which is of enormous utility for any alternative air transport, air-ground or air-cushion machine that uses the principles of vertical take-off by propulsion to jet. The foregoing is done without prejudice to the use as a multipurpose source for power generation. The variation of vertical thrust achieved by this extension, is achieved by subjecting the whole machine to different amounts of mechanical load. That is, the greater the mass of load that must be moved by means of the motor shaft, the lower the vertical thrust force obtained, and the lower the mass of load that must be moved by means of the motor shaft, the greater the force of the motor. vertical thrust achieved by means of this machine. II. THE STATOR. Like the rotor - rotating part -, the stator that contains this invention is the static part thereof. It also consists of a set of simple mechanical parts, with differentiated functional zones. Novel, simple and practical, the stator can also be manufactured with great precision in the same materials with which the rotor is manufactured, only that in this case the manufacturing material can vary freely and optionally according to the J 5 design considerations, may be slightly softer than that used for the rotor, because it will never be subjected to the same mechanical, thermal and corrosive stresses to which the rotor is subjected. Said stator is also formed by three differentiated functional zones: the air inlet or diffuser zone, the combustion zone and the outlet gas bypass zone. Said stator constitutes in itself the housing of the whole invention. Each part of the stator is described below: a) Air intake or diffuser area. Concentric to the axis of the rotor and inherent to the compression zone, the zone of air intake or diffuser is nothing more than the mouth of the engine where atmospheric air enters, which is an asymptotic mouth converging as a hopper or aerodynamic funnel circular-concentric to the axis of the rotor and forming part of the casing thereof, whose largest diameter is 50% of the total diameter of the stator and its smaller diameter is 25% of said total diameter. Said area is also composed of a multi-perforated circular lid that allows air to enter and where two high-speed mixed load bearing units are inserted, which finally support the rotor and unite it with respect to the stator. that said element serves as a coupling between the invention and its final application; such functional mechanical joint can be reinforced for safety purposes by mounting an optional third bearing to the shaft externally on the end application surface of the motor. The air inlet zone ends with the addition of an annular compressor charter, which is a kind of ring-conduit of circular rolled metal concentric to the center of the rotor that stops, stores, regulates and filters the passage of air previously 0 compressed by the centrifugal compressor to the combustion chambers and carries in itself a regular module of ducts through which air passes from the compressor to the combustion chambers. Said device is inserted directly into the stator, and is adjusted by rubbing against the external periphery of each centrifugal compressor blade of the rotor, said element also contains in its lower base lubricated load rollers for suppression of eventual vibrations, b) Combustion zone . The stator on its internal face contains eight bolted combustion chambers, Also known as combustors, said static elements are disposed radially and in a regular manner with respect to the axis of longitudinal symmetry of each chamber, and perpendicular to the axial axis of the rotor, these chambers have a general volumetric form in the shape of an ovoid, to make them efficient. combustion at both instants of ignition and in constant flame. The narrowest side of each ovoid is the outlet nozzle of each combustor, and the widest part is the compressed air inlet and fuel supply next to the annular compressor charter, the eight l combustors} 0 can be bolted to the chartered or bolted to the stator roof. They are interchangeable combustors whose only maintenance is to sporadically clean the soot that is formed by combustion in the case of using fossil fuels, because if hydrogen is used, it self-clean the combustion chambers with the steam that is formed by combustion. In the same combustion zone and alternately between one combustor and another, the cooling tubes are located. These conduits are made of metal and cool turbine blades based on ejections 45 radial cold water or cold air from external systems while the rotor rotates at high revolutions per minute. c) Zone of deflection of the exit gas. Concentric to the axis of the rotor, finally there is the zone of deviation of the exit gas, which is if not the radial zone of the stator furthest from the axis of the rotor, same area in which the periphery of the stator plays a vital role at the time of mounting the device in its specific application while serving as an external protection for hot gases. It is formed by the extension of the stator bent at its extreme periphery downwards, thereby forming a vertical cylindrical wall parallel to the axial axis of the rotor that serves internally as a static outside part of the annular nozzle of output of the entire motor, and externally as a housing protection. III. FUNCTIONING. By means of an external electric starting motor, the rotor described above starts to rotate at speeds of between 1200 and 2500 revolutions per minute. As the rotor is rotating, a constant flow of atmospheric air mass is sucked axially into the diffuser by means of the blades of the compression zone described above which are the ones that aspirate the air. Said air flow is turned from an axial direction towards a radial direction and is compressed by the blades of the compression zone, said flow being stopped in the charter, where it is filtered and divided by means of said annular device. Then, the air flow enters the combustion zone divided between the combusers that make up this area, mixes with the fuel, burns releasing kinetic energy and pressure directed directly towards the blades of the radial flow turbine. By directing the flow of hot gas leaving the combustors in the radial direction towards the reaction blades of the turbine, said flow changes from a radial direction to a semi-tangential direction with respect to the diameter thereof. After having passed through said turbine blades, by means of the deflecting nozzle the hot gases are diverted back to their initial axial direction, thereby generating both a large turning torque and a vertical upward reaction thrust by jet propulsion. The same process occurs continuously at 30,000 revolutions per minute for the duration of the fuel supply, making use of the cooling and lubrication systems described above. IV. ADVANTAGE. An engine designed and configured in the manner described above, involves, produces or accumulates the following verifiable competitive advantages: uniform operation against atmospheric-environmental variations with tolerance to the ingestion of particles; Easy repair and replacement, as well as little maintenance; easy assembly and operation that dispenses with experienced personnel; portability, durability and lightness, compact and resistant size; manufacturing economy, industrial reproduction by casting for all sizes, power and capacity, from micromachines to industrial stationary systems; feeding with any gaseous fuel: LP gas, natural gas, gasoline, biogas, pure hydrogen, hydrocarbons, oils, etc .; simplicity of mechanical design, simple scientific theory and absolute technical feasibility; obvious and ideal utility for multipurpose energy generation, propulsion in alternative transports, micro-compressors; micro-turbines, servo-mechanical devices, low selling price and general public accessibility; total energy efficiency of 90% can be up to 95% depending on the type of fuel used and atmospheric-environmental conditions where it operates. This invention is probably one of the most efficient machines that exist in the state of the art.

Claims

CLAIMS Having broadly, sufficiently and sufficiently described our invention, we consider it as a novelty, the result of our inventive activity and susceptible to its industrial application. Therefore, and based on Articles 9, 10, 10 Bis, 13, 15 and 16, as well as the Second Paragraph of Article 186 of the current Industrial Property Law, we claim as our exclusive property, being prevented from physical or moral person to reproduce for industrial, commercial or mercantile purposes without our express and subscribed legal authorization contained in one or more of the following clauses: 1. "Motor of Universal Gas Turbine of Multicombustible Radial Flow" composed of: a) Rotor with compressor-turbine axial-radial flow suit consisting of a rotating plate with arrow that has an axial compressor combined with a centrifugal compressor, and a turbine area of intrinsic radial flow in the same piece of rotor with reaction blades of optimum pitch with a range between 44 ° and 45 ° degrees for flow deviation with respect to the radial direction, mounted in a regular manner on the horizontal periphery of the rotor covering a rea concentric circular and radial peripheral action; the rotor plate finishes in downward deflection, concentric in its extreme periphery located after the turbine blades, it bends being parallel with respect to the axial arrow thereof, said arrow is integrated with the whole rotor and is extended upwards, with respect to the placement of the rotor with the part of the deflector down, b) Stator with annular compression casing and combustion chambers; both charter and combustion chambers are inserted and (or) bolted to the stator forming an integrated piece. The charter is a circular ring made of thick metal containing at its base, lubricated vibration suppressor load rollers, and transverse perforations for compressed air transmission. Each combustion chamber is screwed to the stator and is interchangeable, likewise each one has an ovoid volumetric form, the narrowest part of the ovoid has an aerodynamic opening and constitutes the nozzle of each combustion chamber, the widest part is the entrance of the combustion chamber. compressed air and fuel supply to each combustion chamber with its respective holes for fuel supply, ignition, installation and ventilation, the compressed air inlets of each chamber are adjusted to the annular compression charter. In turn, the stator contains all the necessary alternating regular radial perforations where the corresponding conduits are inserted for fuel supply, ignition systems, conduits for cooling by water or air and lubrication ducts, all the conduits are arranged in alternating radial form corresponding to each other. Likewise, said stator contains in the diffuser, a multiperforated circular cover, in such a way that it will have mounted two bearings, bearings or mixed external high speed independent bearings that join the rotor with the stator. At the extreme periphery of said stator and in accordance with the rotor, the stator contains a downward deflecting extension. The deflection of the stator with the deflection of the rotor, both form a rotating annular nozzle in the rotor for high-speed hot gas output and eventual production of vertical upward thrust or horizontal thrust according to the design considerations and (or) load of the system itself for each particular case. The mouth of the diffuser and in general the entire compression zone has a convergent-divergent shape for maximum compression efficiency. 2. Combined axial-centrifugal compressor in the rotor with variable number of vanes and variable number of steps, both axial and centrifugal, always arranged in the form of regular angles. Each axial blade has the appearance of a blade or blade element of an aircraft propeller with an optimum pitch angle between 44 ° and 45 ° degrees of inclination, and each centrifugal blade has a semi-asymptotic appearance containing a vacuum bend bent at an optimum angle between 44 ° to 45 ° degrees of inclination with respect to the horizon, and at the same time it is aerodynamically curved backwards with respect to the direction of rotation of the rotor for maximum compression efficiency. The present claim clause includes legal protection against any type of semi-asymptotic curved compression blade whose function is the maximum compression of mass of air per unit of time with minimum amount of energy required for this design. 3. Radial flow turbine in the rotor with variable number of blades, including any number, always arranged in the form of regular angles, always respecting the geometry thereof under the concept of reaction blades with optimum flow deflection angle, said Optimal angle will oscillate between 44 ° and 45 ° with respect to the radial flow of combustion. The present claim clause includes the legal protection of any type of reaction blade for "this design, including all vanes that use the Bernoulli principle relative to the pressure difference 4. Exchangeable combustion chambers, with volumetric form of ovoid type , with perforations for fuel supply, perforations for ignition systems, perforations for supply of compressed air, perforations for ventilation and perforations to be inserted and (or) bolted to the stator, said combustion chambers will always be inserted radially, so The axis of the nozzle of each chamber should point directly to the blades of the rotor turbine.These cameras will always be inserted in the form of regular angles and the total number of these inserted in the stator can vary according to the application needs. Claims clause includes legal protection covering any cham combustion that has at all times, a general volumetric ovoidal shape for maximum combustion efficiency.