JPS58204901A - Radial turbine - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a radial turbine having a floatingly supported turbine wheel through which flow flows inwardly in the radial direction, the turbine wheel having at least one movable wheel. It has winglets and is connected to the shaft. , 5 □ West German Patent No. 1 144 738 discloses a radial turbine having two rotor blades. This known radial turbine has a very high peripheral efficiency at a given steam velocity, i.e. at a given heat drop. This peripheral efficiency roughly corresponds to that of a single turbine, but the peripheral speed can be significantly lower. The rotor blades are manufactured separately,
By its base it is mounted in a suitable manner on the turbine wheel and is connected thereto. The base of the wing and the connecting element must be sufficiently dimensioned for strength reasons, so that a relatively long axial length results. As a result, if the rotational speed of the turbine wheel is high, correspondingly large body forces occur.

Therefore, in some of the above-mentioned wrinkled radial turbines produced by the applicant in the past, the turbine wheel had to be supported at both shaft ends, as also according to German Patent No. 1 144 738. . It is pointed out here that the above-mentioned known radial turbines could only be applied in special cases, especially because they were restricted by construction methods that were wasteful and caused high manufacturing costs. It was about. Up to now, due to the relatively high mass of turbine wheels, the circumferential speed required for thermodynamic reasons could not be controlled in practice without very great outlay.

German Published Application No. 1 551 190 discloses a two-ring radial turbine, 9 of which the turbine wheel has a shaft receptacle which is supported at one end. The diameters of the bore 9 and the shaft are matched to each other for strength reasons. The optimal diameter can be obtained depending on the design rotation speed, turbine size, and other considerations.
Such a connection between the shaft and the turbine wheel is unsuitable for the homology and standardization of radial turbines. Furthermore, as a result of stress concentration, plastic deformation can occur in the middle υ region.

Finally, integral turbine wheels for exhaust turbine superchargers are known 9, which are connected to the shaft by butt welding. That is, for example, MTZ issued in November 1955
Magazine, Vol. 16, No. 1@l1 (7) g 3 2 3 H-U describes a turbine wheel whose blades are extended until they reach the axial outlet area. In such an example, the centrifugal force acting on the rotor blade virtually does not create a bending moment at the joint between the rotor blade and the turbine wheel. In radial turbines of the type mentioned at the outset, the rotor blades are fixed on the at least generally radially extending surface of the turbine wheel and the bending stresses due to p1 centrifugal forces are absorbed by the correspondingly thicker and wider turbine wheel. Must be accepted.

Moreover, in a series of recent experiments, non-negligible damage due to contamination of the steam supplied to the turbine was found, especially on
It was found that this occurs in the region of l. This situation has been observed especially in steam-wet zones that are cut off at certain times, for example on weekends. Although the above situation could in principle be rectified by dirt separators, filters, etc., these sophisticated solutions not only require high investment costs but also result in additional fluid losses. As a result of this, the high economy that could in principle be achieved with radial turbines of the above-mentioned type was called into question, and the further expansion and development of new areas of application could not be easily achieved due to these points.

The object of the invention is therefore to construct a radial turbine of the type described above which requires only a small constructional outlay, which radial turbine has a maximum efficiency of
This can be achieved reliably even when the circumferential speed is high. The peripheral speed required for thermodynamic reasons can be controlled with essential reliability. Also, for cost-effective production and stock management, the radial turbine and in particular the turbine wheel and shaft can be standardized and premanufactured according to the hot series. Depending on the particular application, the radial turbine can be assembled in a unitary manner from various prefabricated components and can be easily installed.Finally, the radial turbine can The turbine is constructed in such a way that damage caused by incoming dirt particles is largely avoided to ensure a functionally reliable operating method, the turbine being manufactured cost-effectively and free of incoming dirt particles. The radial turbine is also highly safe in operation and meets the operational requirements.

The above-mentioned object is achieved according to the invention, in which the turbine wheel is formed as a closed disc with a thin wall in the direction of the axis of rotation,
Furthermore, this is achieved by being made of a single body together with the rotor blades and being connected to the shaft through a plane tooth row. By forming the turbine wheel and rotor blades in one piece, the rotating mass is considerably reduced, so that, surprisingly, a turbine wheel supported on one side or floating is particularly advantageous. This makes it a cost-effective structure. The mass can also be reduced to a considerable extent by forming the turbine wheel, which has a substantially rectangular cross section, in a closed form with a thin wall in the direction of the axis of rotation. What is important is that the turbine wheel is connected to the shaft via a planar toothing, which has a bore that is fixed to the shaft. This makes it possible, on the one hand, to achieve a high strength of the turbine wheel and, on the other hand, to provide the prerequisites for typification and standardization with unexpected ease.

Turbine wheels and shafts can be standardized and premanufactured according to manufacturing specifications, with corresponding planar toothing being provided in each case. That is, the turbine wheel and shaft can be combined with each other depending on the application and requirements. The planar dentition is suitable for the purpose of Hirth-Verz dentition.
This toothing ensures precise and functionally reliable alignment of the turbine wheel. By virtue of the axially thin and integral design of the turbine wheel with rotor blades, the circumferential speed required for thermodynamic reasons is rotor-rotically controlled.

These advantages arise when the turbine wheel and shaft are conventionally manufactured from a single piece to which the rotor blades are mounted, or alternatively when the turbine wheel is fixed to a properly aligned shaft. This cannot be achieved with boring. The planar toothing proposed by the invention makes it particularly easy to combine one and the same shaft with the respective required turbine wheel and vice versa. It is clear that the hilt toothing is particularly suitable in practice since it ensures precise and functionally reliable alignment with the respective axis of the turbine wheel with low manufacturing outlays.

Due to the integral construction of the turbine wheel and rotor blades, special fixing means such as receiving notches or the like for the rotor blades are not required. In turbine wheels designed in this way, even high circumferential speeds can be reliably controlled, whereby the maximum efficiency of the radial turbine is also effectively overridden. 1 The radial turbine proposed by the present invention has an unexpectedly simple structure;
It allows the most favorable and economical application in terms of investment and energy costs.

In their essential structure, the blades are arranged on a turbine wheel formed in a thin disk through an area having a roughly triangular cross section, the wheel having a radius extending inwardly relative to the axis of rotation. direction, it has a shorter axial length than in the approximately triangular region described above. Due to this embodiment, which is essential to the invention, bending stresses caused by centrifugal forces are accommodated particularly reliably, even when the mass of the turbine wheel is low. The turbine wheels are optimized with regard to strength requirements and low mass, so that even the high circumferential speeds required to achieve maximum efficiency are effectively controlled.

In order to significantly avoid damage to the radial turbine due to dirt particles entering with the flowing medium, a special embodiment is such that the travel path of the dirt particles leaves the region of the rotor blades and/or nozzle ring so that the radial turbine path is reflected. It is characterized by being changed under the use of abilities °・1″:′, :・:.

shall be.

The radial turbine according to the invention is distinguished by a simple and cost-effective construction and is highly insensitive to dirt particles. The invention is based on the recognition that incoming dirt particles move slower than the circumferential velocity and are constantly reflected between the nozzle ring and the rotor blades. That is, each particle of dirt is repeatedly passed back and forth between the rotor blades and the nozzle ring, thoroughly pulverizing it until it is small enough to be carried by the fluidizing medium. Finally, dirt particles of relatively large mass should also be considered, and the overall high probability of damage due to frequent reflections of dirt particles is confirmed by practical results. By modifying the course of movement of dirt particles according to the invention, they are surprisingly quickly and simply guided out of the region of the rotor blades and nozzle ring. That is, according to the present invention,
The dirt particles are no longer forced to make multiple trips between the rotor blades and the nozzle ring and leave this highly exposed area within a short period of time. For this purpose, various construction measures are taken in practice, which are selected and provided in each case in an optimal manner and in response to the surrounding conditions, depending on the field of application and the case of use. However, by changing the path or course of movement of the particles,
All of the above measures have in common that they are guided out of the area of the rotor blades and nozzle ring as quickly and immediately as possible, taking into account their reflective ability.

In a particularly advantageous embodiment, the two-sial turbine has at least one dust collection chamber in the nozzle ring for collecting and, in particular, continuously discharging the dust particles reflected back by the turbine wheel.

That is, in such a radial turbine, the nozzle ring is interrupted at at least one point 9 around its circumference, thereby forming the dust collection chamber.

This dust collection chamber is expediently connected to a conduit which continuously discharges the dust particles. If the dust particles are equipped with a chamber in which, even in the most unfavorable case, they do not have to make almost one revolution, it is expedient for these collection chambers to be distributed symmetrically over the entire circumference. . One or more of the above-mentioned dust collection chambers can be arranged in the turbine casing with little constructional outlay.

In a suitable embodiment, the rotor blade ring is capable of passing dirt particles at at least one point on its circumference, the pitch being expanded or a gap being present in the rotor blade ring. . That is, in this example, the turbine wheel is asymmetric and p.

Dust particles can penetrate radially inwards without being reflected outwards at these points. The course of movement of the dirt particles extends substantially radially inward.

In a preferred embodiment, at least one of the nozzle rings
The outlet surfaces of the nozzles are arranged obliquely with respect to the rotational axis of the radial turbine.

as a result of which the core particles are very rapidly deflected axially out of the annular gap between the nozzle ring and the rotor blade ring. It is obvious that all exit surfaces can be constructed in the same way, especially in order to simplify the construction. It is expressly pointed out here that all forms of the outlet surface which are not of cylindrical construction and which are coaxial to the axis of rotation of the turbine wheel are within the scope of the invention.

In a further advantageous embodiment, the inlet face of at least one of the rotor blades of the turbine wheel is arranged obliquely to the axis of rotation. In this case too, the specific example shown in connection with the upwardly inclined outlet gap is correspondingly valid. It is also important here that the inclination of the at least one inlet face deflects dirt particles axially out of the annular gap between the nozzle ring and the rotor blade.

In a variant of the invention, the radial turbine preferably has an annular space arranged in axial alignment with the nozzle ring and the rotor blade ring in the turbine casing, into which a small amount of fluid medium can leak with a rate of leak. At this time, it is preferable that a slit IQ ring be present between the nozzle ring and the rotor blade ring in order to obtain the smallest possible leakage rate. In the annular space mentioned above, a fluidizing medium is stored, which in the case of hitherto known radial turbines, in particular two-stage or multi-stage radial turbines, is subsequently introduced back into the original flow path and is then again introduced into the flow path. Acceleration takes place. It has been found that this requires a non-negligible amount of energy and ultimately reduces efficiency. In order to avoid this difficulty, the present invention provides that into the above-mentioned annular space or equivalent object,
It is proposed to suitably open a regulating hole which is connected to the exhaust pipe of the radial turbine. Therefore, the part of the fluid medium that reaches the annular space, even if only at low leakage rates, does not need to be accelerated again and is discharged via the V4 hole adjustment proposed by the invention. This provides a significant improvement in the overall efficiency of the radial turbine.

In order to obtain a particularly simple and economical construction, the turbine wheel is connected directly to the shaft of the transmission and is supported on a common support of the transmission housing. The radial turbine and the transmission connected thereto are particularly easily integrated, so that no special support is required for the turbine wheel. Furthermore, the radial turbine can be combined without problems with transmissions of various configurations, thereby achieving the desired rotational speed matching.

The radial turbine is purposefully constructed as follows. In other words, due to the reaction force of the moving blade equipped with the pressure at the back of the nozzle of the nozzle ring, the pressure becomes large enough to cause a force component to act on the turbine wheel in the space between the turbine wheel and the cushioning. With this force component, the shaft end thrust can be expediently compensated, at least to a large extent, in the area of the design point. Therefore, the rotor blades provided are realized with a certain degree of recoil, and the pressure behind the intake nozzle is greater than the exhaust pressure in the exhaust duct. In practice, approximately 9 of the energy
It has been found to be particularly advantageous if 0.7-cents is converted at the nozzle and within 10/Q-cents at the turbine wheel.

Particularly in its essential construction, the radial bearing of the shaft is associated with an outer bearing damping element, in which case the design rotational speed of the turbine is expediently greater than the primary spring number. Due to the induced outer bearing damping, supercritical operation of the turbine is possible with a high degree of safety. The braking element is 1-super, l:
1:,,,.

It reliably limits the amplitude of vibrations in the event of an overload, guaranteeing a high degree of functional reliability.

In a particularly essential construction, a deflection duct is present in the region between the housing and the turbine wheel behind the rotor blade return in the direction of flow. This deflection duct is constructed or useful as follows. That is, optionally, a rear diffuser made of rotor blades is created or
Alternatively, at least a two-ring radial turbine is created by arranging guide vanes on the casing and arranging the second rotor 1jtm on the turbine wheel. This makes it particularly easy to standardize the radial turbine and to produce it in a cost-effective manner in a modular manner. In the case mentioned above, a correspondingly optimized deflection duct functions as a diffuser after the turbine stage. In the second case, □1 in the deflection duct is also equipped with a guide blade on one side and a second rotor blade on the other side.
′:,・.

, thus creating at least one bicyclic radial turbine. It is clear that for this purpose only a few parts of the radial turbine, namely the #1 annular part of the turbine casing and the turbine wheel itself, have to be suitably adapted to each other, while the remaining parts can remain as they are. be.

In an expedient construction of a radial turbine in which the turbine wheel has rotor blades on one axial face, a counterweight is arranged on the other axial face, which counterweight is preferably divided in the circumferential direction. It is formed as a ring. It is self-explanatory that the rotor blades arranged on one front face introduce relatively high bending and/or compressive stresses on the turbine wheel, especially at high rotational speeds, on the other front face behind the turbine stage. Compensation could in principle be achieved by a counterweight placed at . However, it has been found that in the case of a continuous ring-shaped counterweight, the requirements for high circumferential speeds are not sufficiently taken into account. Owing to the division of the counterweight proposed by the invention, which is realized in that the preferably ring-shaped counterweight is provided with an axially extending slit, offset reinforcement of the turbine wheel is particularly advantageously avoided. The individual rotor blades and the nine counterweights, which are also divided into segments, provide centrifugal or centripetal forces that at least substantially cancel each other out;
As a result, unacceptable bending moments of the turbine wheel and thus additional stresses are avoided.

Embodiments demonstrating further advantages and essential features of the invention will be explained in detail below with reference to the accompanying drawings.

FIG. 1 shows the area of a radial turbine, particularly the turbine wheel 2. As shown in FIG. The turbine casing 6 receives the turbine wheel 2 in a known manner and includes a nozzle ring 8 with supply air nozzles 10 distributed over its entire circumference. The turbine wheel is rotatable around a longitudinal axis 20 and is radially outwardly moved by a first motor. After passing through the g17 connected to the turbine casing 6, it reaches the inner rotor blade 30 of the second rotor blade 21, which is the second rotor blade. A two-stage radial turbine is thus provided, in which the medium exits in a known manner, for example axially, via a diffuser after leaving the second bucket bed 21 .

The turbine wheel 2 is formed integrally with the moving blades 4, 30, and is made of special steel having high tensile strength. The turbine wheel 2 has a radius R1 in the radially inner region of the blade base 230, which is manufactured by precision casting, and the axial length of this region is L1. According to the invention, the ratio L1 to R1 is less than 0.15, which ratio
It is maintained throughout the range up to zero wealth. The cross section of this area is approximately square #1. The turbine wheel 2 is generally designed as a narrow disc in the direction of the longitudinal axis 20, which ensures that the mass of the turbine wheel is low. Surprisingly, it has become clear that the body force that appears when the rotational speed of the turbine wheel 2 is high is reliably absorbed. Due to the integral formation of the turbine wheel and rotor blades, a fairly heavy blade base receiver is not required with the present invention. The rotor blade 30 is connected to the turbine wheel 2 via a region 45 having a substantially triangular cross section. Via the above-mentioned triangular area, bending stresses due to centrifugal force are reliably accepted. The turbine wheel 2 has an axial length L2 in the top region of the triangular region 45 and at the base of the rotor blade 30 located radially inwardly. According to the invention, this axial length L2 is designed to be relatively short, with a ratio of less than 0.8 to the radius R2 present in the same area.

A region 47 having a substantially rectangular cross section is connected to the radially inner side of the triangular region 450, and this region has an axial length shorter than L2. This also achieves a substantial reduction in the mass of the turbine wheel 2. The turbine wheel 2 formed according to the invention is realized as a single-piece, axially thin disk together with the rotor blades 4, 30. The total mass of the turbine wheel 2 can therefore be kept very low, so that even the high circumferential speeds and rotational speeds required for thermodynamic reasons are reliably controlled.

The turbine wheel 2 is connected to the shaft 34 via a planar toothing 32 , 33 , a rigid connection being established by means of a screw 29 . Both the turbine wheel 2 and the shaft 34 have a plurality of holes distributed over the entire circumference in the above-mentioned square area 47, into which the screws 29 extend. The hole in the shaft 34 is formed as a screw hole. The planar tooth rows 32, 33 lie substantially in a radial plane and have conical teeth that precisely center the turbine wheel. With this construction essential to the invention, differently configured turbine wheels and shafts can be connected to one another particularly easily. The turbine wheel and shaft can be prefabricated and standardized according to a type series, so that the two are connected to each other in the required manner as required. The planar toothing is expediently designed as a hilt toothing, with which the turbine wheel is well aligned. The shaft 34 is a component of a transmission device, which is connected to the casing 6 on the right side of this figure. However, it has special significance within the scope of the invention that the turbine wheel 2 can be easily connected to the shaft 34.

That is, the transmission can also be standardized, so that depending on the requirements, a transmission with the desired transmission ratio or special power data can be coupled to the turbine. Turbine wheel 2 is connected to shaft 3
4, there is no need for a special bearing for the turbine wheel. The turbine and the transmission are integrated with each other, the transmission bearing supporting both the turbine wheel 2 and the shaft 34 of the transmission, in which according to the invention the turbine wheel 2 is supported in a floating state. It will be pointed out that, therefore, only one shaft packing 31 is required, which results in correspondingly low steam leakage losses.

The radial turbine is realized with a slight reaction force in the first stage, in which about 90% is converted in the supply nozzle 10 of the nozzle ring 8 and about 10%
It has been found that converting within IQ cents with a turbine wheel is suitable for the purpose. This corresponds directly to the design point region of the radial turbine. That is, a given pressure is generated in a region 25 existing between the air supply nozzle 10 and the shaft nozzle 31 and further delimited by the casing 6 on the one hand and by the turbine wheel 2 on the other hand, Pressure is arrow 35
act on the turbine wheel in the direction of , which is useful for compensating for end-of-shaft thrust.

FIG. 2 schematically shows a known per se outer bearing brake for the shaft 34. Figure 2 shows the shaft 34 shown at the bottom of Figure 1.
Connect properly to the end of the extension.

The shaft 34 is surrounded by a ring-shaped bearing 37,
This bearing is arranged on a bearing stand 39 of the casing 6. Between the bearing pedestal 39 and the housing 6 there is a hydraulic slot 41, which is sealed off by a socket 43, here designed as an O-ring. This outer bearing braking element shown here - as an example:
For example, plate-shaped packet damper, wire cushion damper/Q
It is also possible to substitute other braking elements which are sufficiently known such as. According to the present invention, in combination with the turbine wheel proposed by the present invention, the maximum efficiency of the radial turbine is reliably achieved even when the circumferential speed is high. Book
The design speed of the light radial turbine is suitable for the purpose, −
It is larger than the next critical rotation speed.

FIG. 3 schematically shows a turbine wheel 2 with rotor blades 4. As shown in FIG. The turbine wheel is arranged in a manner well known and recognized inside a turbine casing 6, which casing includes a nozzle ring 8 arranged opposite the rotor blades 4 with a number of nozzles 10. . Dust particles that pass through the nozzle 10 and enter with the fluidizing medium, especially the steam, also
The annular gap between the rotor blades 4 and the nozzle ring 8 is reached.

Since the above-mentioned dust particles move slower than the circumferential speed, the particles are, in principle, constantly reflected back and forth between the rotor blades 4 and the nozzle ring, and this back and forth reflection is faster as the particles are carried by the fluid medium. It continues until it becomes fine. The debris sensitivity of the radial turbine, conditioned by the frequent impingement of debris particles on the rotor blades 4 and the nozzle ring 8, is reduced by the dust collection chamber 1 in the turbine casing 6 provided by the present invention.
4, it is significantly reduced. The travel path of the dirt particles is interrupted by the dust collection chamber 14 and thus further reflections are prevented. There may also be several such dust collection chambers 14 distributed over the circumference of the radial turbine, so that the incoming dust particles are removed from the annular gap 12 after only a slight reflection process. It is clearly pointed out that the dust has already reached the inside of the dust collection chamber 14. A conduit 16 is connected to the dust collection chamber 14 by means of which the dust particles are continuously removed from the dust collection chamber 14 . Dust collection chamber 14
lies substantially in the same radial plane as the rotor blades 4 as well as the nozzle ring 8 with the nozzles 10.

In one embodiment, not shown, of a radial turbine according to the invention, the turbine wheel 2 is missing at least one, and possibly more than one, of the rotor blades 4 which are normally arranged symmetrically in the circumferential direction. That is, gaps are deliberately provided between the rotor blades 4, which allow dirt particles to pass through, here inwardly in the radial direction. A similar effect can also be achieved by widening the pitch of the rotor blades 4 at least at one point on the circumference, again providing an asymmetry so that dirt particles can be attracted inward.

It should be noted here that the methods already mentioned and the methods described below can be combined with each other within the scope of the invention, so that, depending on the individual requirements and application conditions, the most favorable relationship, particularly in terms of high efficiency, is obtained. It should be clearly pointed out that

FIG. 4 shows a longitudinal sectional view of a radial turbine in which the outlet surface of the nozzle ring is arranged obliquely with respect to the rotation axis 20. As shown in FIG. One-point chain #i! As represented by 22,
The dirt particles reach into the annular space 24 immediately after a slight reflection process. The travel course represented by the dash-dotted line 22 extends in the circumferential direction rather than in the thermal plane:
.

The rotor blade 4 is located on a first axial front face, while a ring-shaped counterweight 26 is provided on a second axial front face opposite to the turbine wheel 2 .

The ring-shaped counterweight 26 has an axial slit 28
It is divided into several segments by this, which prevents offset reinforcement of the turbine wheel 2 and additional loads resulting therefrom as much as possible. The turbine wheel 2 is designed as a relatively thin disk in the direction of the rotational axis, with the rotor blades 4 mentioned above as well as a separate rotor blade 30 of the second rotor blade being integrally connected to the turbine wheel 2. It is formed. As a material, high-strength special steel is suitable for the purpose, and by means of this one-piece design, preferably used in precision casting, a relatively low rotational mass is achieved. The turbine wheel 2 is connected to a shaft 34 via a planar toothing 32, here designed as a toothing. The turbine wheel 2 is thus formed as a thin, complete disk with a central hole for connection to the shaft.

In the specific example shown in FIG. 5, the inlet surface 36 of the rotor blade 4 is the rotation axis IIj! It differs substantially from the previous embodiment in that it is inclined or conically shaped with respect to 20. This also causes the incoming dirt particles to be subjected to a motive component, which forces them out of the annulus @12 very rapidly. The turbine casing 6 has in this example an approximately ring-shaped component 38 which is designed in such a way that the annular space 24 already mentioned above is created in the area of the rotor blades 4 . A small but not negligible amount of flowing medium reaches into this annular space 24 via the packing slit 40 with a leakage rate that corresponds to the given conditions at the time. This partial volume of fluid medium is now first stored and thereby accelerated again as it flows through the further /9 slot 42. Here, a reduction in efficiency is in principle prevented. In order to obtain a high efficiency, therefore, at least one regulating hole 44 opens into the annular space 24 and leads to an exhaust duct 46 .

The leakage portion of the fluid medium that exits through the /Q distribution slit 40 is therefore discharged and no longer needs to be accelerated.

FIG. 6 shows an enlarged view of the nozzle ring 8 in which the inlet surface 36 is arranged obliquely to the factor plane and thus to the axis of rotation of the turbine wheel 2. FIG. Due to the inclination of the exit surface, the dirt particles acquire an axial force component and are thereby quickly ejected from the annular gap 12.

FIG. 7 shows a monocyclic radial turbine in which a deflection duct 48 is provided between the turbine wheel 2 and the turbine housing 6 or its ring-shaped component 38. This deflection duct 48 is designed as a well-known diffuser. It can be appreciated in connection with FIGS. 2 and 3 that in this embodiment only the second rotor blade of the turbine wheel and the vane of the component 38 of the turbine casing are missing. That is, with this simple omission, a bicyclic radial turbine becomes a monocyclic radial turbine with a diffuser. This means that only the component 38 as well as the turbine wheel 2 can be properly formed, while the remaining components of the radial turbine can be kept intact.
Achieved at extremely low cost. This method therefore has normative significance from the perspective of turbine standardization.

[Brief explanation of the drawing]

Fig. 1 is an axial longitudinal cross-sectional view of a radial turbine in which the turbine impeller is connected to the shaft via a planar tooth row, Fig. 2 is a schematic explanatory diagram showing the shaft support in the casing, and Fig. 3 4 is a schematic partial sectional view of a radial turbine across the rotational axis; FIG. 4 is a vertical sectional view of a radial turbine in which the exit surface of the nozzle of the nozzle ring is inclined; and FIG. Fig. 6 is an enlarged view of several nozzles with inclined exit faces; Fig. 7 is a cross-sectional view of a radial turbine with
The figure is a longitudinal sectional view of a monocyclic radial filter 39 with a diffuser. 2... Turbine wheel, 4.30... Moving blade, 6...
Turbine casing, 8... Nozzle ring, 10...
・Nozzle, 12... annular gap, 13.21・
... moving wing monkey, 14 ... dust collection chamber, 16 ... conduit,
DESCRIPTION OF SYMBOLS 17... Stationary blade, 18... Exit surface, 20... Rotation axis line, 22... Dot-dash line, 23... Blade base, 24...
...Annular space, 25...Space, 26...Counterweight, 28...Slit, 29...Screw, 3
1... Shaft packing, 32.33... Plane tooth row, 3
4...Axis, 35...Arrow, 36...Entrance surface, 3
7... i bearing, 38... constituent part, 39... bearing stand, 40, 42... packing slit, 41...
Hydraulic slit, 43... Packing, 44... Adjustment hole, 45... Triangular area, 46... Exhaust duct, 14
7... Rectangle -', 48... Deflection duct.

Claims (9)

[Claims] (1) A radial turbine having a floatingly supported turbine wheel through which flow flows radially inward, the turbine wheel having at least one rotor blade ring and coupled to a shaft. The turbine wheel is formed as a closed disk with a thin wall in the direction of the rotational axis, is made of a single body together with the rotor blades, and is connected to the shaft through a plane tooth row. radial turbine. (2) The planar tooth rows of the turbine wheel and shaft are arranged substantially in a radial plane, characterized in that these tooth rows have conical teeth that center the turbine wheel. A radial turbine according to claim 1. (3) The radial turbine according to claim 1 or 2, wherein the plane tooth row is formed as a hilt tooth row. (4) The pressure of the fluid medium in the air supply nozzle is limited to such a magnitude that the equipped rotor blades have a given degree of reaction, in the space between the air supply nozzle and the shaft nozzle. The radial turbine according to any one of the preceding claims, characterized in that a force component in the opposite direction to the shaft end thrust acts on the turbine wheel, and the shaft end thrust is at least almost compensated at the design point. (5) Claim 1 that the turbine wheel is connected to a shaft of a transmission device and is supported by a bearing of the shaft located within the transmission case.
The radial turbine according to any one of items 1 to 4. (6) An outer bearing braking element is attached to the radial bearing of the shaft, and the design rotational speed of the radial turbine is preferably larger than the primary critical rotational speed. The radial turbine according to any of the above. (7) For the turbine wheel and shaft to have coupling screws,
The radial turbine according to any one of claims 1 to 6, characterized in that the radial turbine has a hole arranged eccentrically from the rotation axis. (8) Claims 1 to 7, characterized in that the blades are disposed on a turbine wheel formed as a thin disk through a region having a substantially triangular cross section. The radial turbine according to any of the above. (9) The screw and the plane tooth row are located inside in the radial direction, and tl is arranged in a region having a rectangular cross section, and the axial length of this region is the same as the axial direction of the triangular region of the turbine blade □ wheel. The radial turbine according to any one of claims 1 to 8, characterized in that the radial turbine is shorter than the length of the radial turbine. θ1 A radial turbine having a turbine wheel through which flow is directed inward in the radial direction and having at least one rotor blade ring and a nozzle ring arranged in the turbine casing, the travel course of incoming dirt particles; Patented turbine, characterized in that the course is modified by means of reflection capabilities so that it leaves the area of the rotor blades and/or the nozzle ring. (1) The radial turbine according to any one of claims 1 to 10, characterized in that at least one dust collection chamber is provided within the turbine casing and/or within the nozzle ring. A conduit opens into the dust collection chamber to continuously discharge dust particles. The radial turbine according to claim 11, characterized in that: Stage 0 characterized in that the rotor blade ring has at least one penetration means at at least one point on its circumference, the pitch and /t of the rotor blades or the spacing between the rotor blades being preferably widened. A radial turbine according to any one of claims 1 to 12. The radial turbine according to any one of claims 1 to 13, characterized in that the outlet surface of at least one nozzle of the nozzle ring is arranged obliquely with respect to the axis of rotation. . 0!9 According to any one of claims 1 to 14, wherein the inlet surface of at least one rotor blade of the turbine wheel is arranged at an angle with respect to the axis of rotation. radial turbine. aυ A radial turbine in which the fluid medium exits with a leakage rate into the annular space of the turbine casing, preferably via a nine-way slit between the nozzle ring and the rotor blades, preferably with a leakage rate into the annular space of the turbine casing. A radial turbine according to any one of claims 1 to 15, characterized in that the adjustment hole connected to the exhaust duct is open. (1η) The preferably one-piece turbine wheel, which is supported in a floating manner on one side, is formed as a complete disk with thin walls in the axial direction and has a planar toothing, preferably formed as a hilt toothing. Claims 1 to 16, characterized in that the shaft is connected to the shaft through the
The radial turbine according to any of paragraphs. a8 The radial according to any one of claims 1 to 17, characterized in that the turbine wheel is supported together with the shaft of the transmission by a bearing for the shaft located in a common casing. turbine. α■ In the nozzle ring, the pressure of the fluid medium is limited to such a magnitude that the equipped rotor blades have a given degree of reaction, and in the space between the turbine wheel and the turbine casing there is an axial thrust and Radial turbine according to any one of claims 1 to 18, characterized in that opposite force components are effective and the shaft end thrust is at least substantially compensated at the design point. (2G The radial bearing of the shaft is attached with an outer bearing braking element, and the design rotational speed of the turbine is larger than the primary critical rotational speed. The radial turbine according to any one of the following: (2υ) A deflection duct is provided and/or formed in the region between the turbine casing and the turbine wheel, which is behind the rotor blade in the flow direction. 9. Thereby, a diffuser can be configured selectively, or if a guide vane is arranged on the turbine casing and another rotor blade is arranged on the turbine wheel... A radial turbine according to any of the patents characterized in that a two-ring radial turbine is created.The turbine impeller has a moving blade on one axial front surface,
Further, a counterweight is arranged on the other axial front surface, and this counterweight is preferably formed as a ring divided into several segments by axial slits in the circumferential direction. In particular, a radial turbine according to any one of claims 1 to 21yL.