DE3119068A1 - Turbine rotor (wheel) and its method - Google Patents

Abstract

A method proposed as a converter of the energy of flowing particles of a medium is to use tangential jets to direct the medium, led from a compressor into pressure-equalising chambers and converted into flow (stream) energy, onto the turbine rim rotor and guide it into the turbine rotor so as to produce pressure channels and reaction channels. A pressure channel (half wave) curved forwards in elongated fashion from the circumference merges into a smaller diameter than that with which the flow guide (stator) blade ends. This blade is consequently superimposed with respect to the circumference, the start of a further curved channel, with the result that continuous channels are produced. The external channel wall, curved with respect to the circumference, produces a (triangular) flow entrance chamber relative to the blade with a superimposed channel inlet. The flow simultaneously enters the pressure channel and, moving backwards through the guide blade, the reaction channel. The channels are divergent. This process can be performed by guiding the outlet over a plurality of stages. A windward forward channel arranged in the rotor rim, which acts also on a reverse surface leading to the reaction nozzle channel. Both methods can be accommodated in a rotor circular surface. Flow-guiding surfaces can be provided in an integrated fashion instead of jet (thrust) nozzles.

Description

Turbine rotor and its process.

The invention relates to turbine rotors for converting flow energy into mechanical or electrical energy of a medium such as gases, air, steam, as also wind.

By pressure and recoil on evasive form-bound tarpaulins - Flow-guiding channels that act tangentially or as a cross-flow, connected with a generator as a flow supplier.

In the state energy program, the trend is towards reality development a future-oriented safeguard and the increasing global energy consumption.

The use of high suSth pressure generated by a generator, implemented into flow energy, which is converted in the turbine runner, is supposed to be a decisive factor Be part of the drive energy.

It is known that turbines - combustion engines with a variety on shovels and their various shapes. Are also known Turbines with a recoil effect in engine construction, generators with free-floating pistons.

The high pressure process is also known in the laid-open specification 2847672 of May 14, 1980, same applicant.

These turbines, and their blades, are more or less to the extreme high temperatures and high speeds exposed to something special Requires material, these engines also only work with the flow pressure are coupled with a suction compressor and do not allow any major variable adjustments, are fluidic and determined in terms of their efficiency. In the case of the recoil turbines, keep the extreme flow velocities of the recoil outlet in cross section small, the flow is directed from the inside, radially out of the small axial space to the outside. These thrusters have more or less only vane pressure, or only recoil to do. With free-flying pistons with combustion pressure, only the exhaust gases for a turbine drive used.

The present invention has set itself the task of a radical change to create for turbines that work more economically than the previously known engines.

The object is achieved according to the invention of a turbine to convert the flowing particles e.g.

proposed from air, gases and steam into mechanical or electrical energy, characterized in that one or more turbine rotors from the inlet flow, be conducted in the runner itself in such a way that a channel formed for pressure and recoil arises, a divergent channel is also created by the inlet flow has a lucrative effect. The turbine runner itself can have a Many staggered channels, according to the scope, have these also in the Circular rotor surface can be accommodated. Instead of jet nozzles can also Flow guide surfaces are used, which can be integrated in front of the circular rotor area, in order to optimally counteract the formation of a vortex, so that also low flow velocities like wind, with a correspondingly larger diameter, to the effect in the turbine runner come.

In the high air pressure process, an air compressor, e.g. flying pistons that generate the flow and convert it to the jet. The jet is in the turbine runner through the shaped channels until the flow is completely reversed led in the canal to the recoil and canal outlet. Every single channel becomes divergent to the pressure channel and recoil channel.

The advantages achieved by the invention are that the flow in the turbine runner, taking into account a given diameter, one Effective area is provided for two functions, once to initiate the recoil and the second time to record the flow pressure. Because the recoil channel is divergent also becomes an inlet, there is a double effect; only the inlet channel can also act lead to recoil, thus also absorbing the flow pressure., this arises a four times higher torque.

In order to achieve the best possible effect, a runner can be staggered arranged channels can be provided which are arranged in several rotor stages. To a prophylaxis also in the motor vehicle sector a realistic development as an alternative, a generator should be mentioned as an air compressor, which is operated by the flying piston has a better thermo-mechanical efficiency and the Mass forces be used more efficiently from dead center to dead center, especially since the aforementioned turbine rotors are independent of the degree of compression of the generator are loaded, as the compression ratio during operation at the flying piston can be changed, comes a variable adjustment of the situation more economical to the 1st effect. The air compression temperatures are also not so higher than that of the exhaust gases, which is reflected in the lower material costs Impact turbine rotor channels. Also, the exhaust gases can with that of the sucked in air compression are mixed in order to obtain thermal utilization of the exhaust gases, the mixing temperature remains essentially low.

An Ausfürungsbeispiel is shown in the drawings and will described in more detail below. Fig. 1 shows a section of a turbine rotor.

Fig. 2 a section of a high air pressure generator.

Fig. 3 shows a cross section of a three-stage runner.

Fig. 4 a section of the first stage.

Fig. 5 a section of the second stage.

Fig. 6 a section of the third stage.

Fig. 7 a development of a transversely loaded turbine rotor.

Fig. 8 is a cross-section of part of the development.

Fig. 9 is a plan view of a circular surface of the turbine rotor.

Fig. 10 a further angle of a transversely loaded turbine rotor.

Fig. 11 shows a cross section of a turbine runner of the development.

Fig. 12 a developed part with a nozzle.

Figs. 13, 14, and 15 are symbols of the wreath travelers.

The turbine runner 1 Fig.l has several inlet channels in the rotor ring 21 which open into the channels 3, 3 '. Through several nozzles 7 in the housing stator 2 of the circumference, the flow enters the rotor channel 21 once the flow, deflected by the pressure surface 4 to the channel 3, which acts as a recoil channel, at the same time the flow comes from channel 21 into channel 3 'to release pressure at 4'.

When the rotor turns, the channels become divergent, 3 creating a pressure effect and 3 'to the recoil effect. The flow guide 6 in the channel space 21 is the Flow to the reversal and pressure surface 4 guided, also derived divergently to the outlet antechamber 8 with the outlet 9. The turbine rotor - circumferential surface parts 5 prevent the Inlet flow flows directly into the outlet antechamber 8, this runner effect described is performed several times at the same time. The housing 2 with the inlet nozzles 7 and the Outlet vestibules 8 is close to the runner, but this freely movable Housing cover surfaces 10 and 11 form a channel space with the rotor circumferential surfaces 5 21.

The high pressure generator shown in Fig. 2 consists of two combustion cylinders in the two-stroke process and a double-acting high-pressure air cylinder 13, it should simplify the process. The centrifugal forces of the pistons are generated by the two-stroke compression and the high air pressure compression, the high air pressure cylinder has both sides Inlet and outlet valves, the air to be sucked in can be drawn from the excreted flow of the turbine rotor stages are also mixed with the exhaust gases from the combustion so that an overpressure arises in the suction chamber 17 Fig.3 of the air compressor 13, which is to be determined and escapes as an excess at 19. The generated high pressure air from the cylinder 13 is led into the pressure equalization chambers 12 Fig, 2 and Fig.4, the Chambers are designed as nozzles for the pressure recoil turbine runner, and thus set converts the pressure into flow velocity. The turbine rotors 14, 15 and 16 Fig.3 are the same in Fig. 1 of the surfaces and channel arrangements, also in Figs. 4, 5 and 6, but subdivided as a single step 14 and offset Fig. 4 dashed channels arranged so that an uninterrupted series of surfaces and recoil channels in the Turbine rotor consists.

The flow course in the turbine rotors is described under Fig. 1, the flow entry takes place through the pressure equalization chambers 12 Fig.4, the exit the remaining flow of the first turbine rotor stage 14 reaches the outlet vestibule 8 and is led into the pressure equalization chamber 12 'Fig.5 and leaves through the Outlet vestibule 8 'the second rotor stage. The rest of the flow enters the Pressure equalization chamber 12 "of the third turbine rotor stage Fig.6 and is passed through the outlet vestibule 8" in the channel 20 of the housing Fig.3 diverted to the rotor unit 1 located conveyor vanes 18 Fig.4, Fig.5 and Fig.6 and conveyed to the suction chamber 17 Fig.3 as overpressure, the excess air mixed with exhaust gases in the intake chamber is indicated by 19 Fig.3 derived into the open. The flow cycle can be enriched with sliding particles its specific weight is higher than that of air.

Turbine rotor with the pressure and recoil channels 3 and 3 'in the rotor circular area Fig.9 and the development part Fig.7, have several lateral inlet nozzles 7 of the Circular area accordingly with the outlets 8 as the housing stator.

The cover surface 5 with the flow guide 6, for the channel 3 and 3 'of the rotor 1 also prevents, as already described under Fig.l, an overflow from the jet into the outlet. The eanals are also flowed through divergently here, the arrangement of the channels is fan-shaped, also Fig.11 dashed lines. the The upper subdivided development Fig.7 has flow guide surfaces instead of nozzles 22 Windward side with the inflow opening 7 'and the outlet as a housing stator, the outlet cladding 23 Fig.8 shows the cross-section of this part, with 8 'being the outlet to the open on the leeward side around the runner, inside and outside. There can be several of these inflow openings 7 'in the circular area Fig.9.

The development part Fig. 10 shows a turbine runner 1 'as a circular area with the rotor inlet channel 21 ', the Flow at the pressure effect surface 4 is guided to reverse in the recoil channel 3 ", this recoil channel is as Recoil nozzle formed and directs the flow through the runner through leeward from, while on the windward side integrating flow guide surfaces 22 'are provided as a stator are, with the inflow openings 7 '. Fig.l.l shows this circular surface runner in cross section wherein the channels of the rotor 1 'can be fan-like, dashed lines.

This development shown in Fig.7, as well as Fig. 9 and Fig. 10 with the superior flow guide surfaces 22 respectively. 22 'of the circular surface runner, are for small flow velocities, such as wind and can in diameter be adapted to the required ratio.

Also with nozzles 7 fig.12 a short development as a turbine ring rotor 1 "with the rotor recoil nozzles 3" can be arranged in different ways, as shown in Figure 13, the nozzles 7 acting laterally to the turbine ring rotor 1 ″.

Fig.14 shows a nozzle arrangement 7 from the inside, through the turbine ring rotor 1 "to the outside. Fig.15, on the other hand, shows a nozzle arrangement 7 from the outside through the turbine ring rotor 1 "inwards. There can be several nozzles distributed around the circumference of this ring traveler be.

In this description for turbine rotors listed arrangements, are flow velocities from low to high in pressure and recoil processes recorded on the scale.

Claims (5)

P a t e n t a n s p r ü c h e Turbine rotor for converting flow energy into mechanical energy of a medium such as small to large particles in suspension Flow velocity, due to pressure and recoil in the flow guides of the circular rotor surface and limit in the rotor ring, characterized in that the flow guide in the Runner (l, l ', l' ') runs like a canal, essentially connecting over the circumference are designed - roughly the shape of a describes, with the pressure - reversal surfaces (4, x ') flow channels (3, 3', 3 '') formed in a form-fitting manner are assigned in such a way that that a recoil resistance of the latter arises, in two directions in diverging directions Flow channels is steerable to the pressure reversal surface form-fitting flow guides (6) form the flow channels (3, 3 ') in such a way that they are each on the inlet and outlet side Communicate over the circumference of the rotor distributed flow spaces (21,21 '). 2. Turbine ring rotor and its process, by a generator Generated compressed medium at low temperatures to drive turbine rotors according to claim 1, characterized in that a double-acting cylinder (13) the resulting compression pressure is fed to the pressure equalization chambers (12), in the latter converted into flow energy as a nozzle stator tangential to the turbine rotor are directed, the curved ones arranged twice offset Channels (14) are assigned in several ring rotor stages, the flow is from Step by step weidergereiclit and is the respective remaining flow velocity adapted, through the outlet (8) of the first crane stage (14) into the pressure equalization chambers (12 ') of the second turntable stage (15), through the outlet (8') of the second stage into the pressure equalization chambers (12 '') of the third stage (16) through which The remainder of the flow passes over the outlet (8 ") of the last crane stage here a feed channel (20) to the T-runner unit formed fan (18) in the overpressure space (17), which serves as the suction space for the compression cylinder (13). 3. turbine ring rotor and its method according to claim 1 and 2, characterized characterized in that one or more ring rotor units (lIt) are arranged, the flow of several nozzles (7) with the rotor channels (21 '), the reversal surface (4) are implicit with the thrust nozzles (3 '') and different flow directions genes, as a transverse centrifugal centripetal flow. 4. Turbine rotor with low flow velocity Claim 1, characterized in that the circular rotor surface (1,1 ') with the flow channels (3,3 ', 3' ') several fan-like flow guide surfaces (22,22') are placed in front of the windward side are that several diverging channels (3,3 ') with the flow cover surface (5) and the Integrating outlet (8) with the flow-deflecting hood (23) get lost. 5. Turbine rotor according to claim 1 to 4, characterized in that the rotor units and stators can be composed differently.