DE102005049938B3

DE102005049938B3 - Rotor for fluid flow machine e.g. pump, has wing profile unit including convex elevation on outer mantel surface, axial hollow space enclosed in interior, and opening between space and mantel surface in region of profile units

Info

Publication number: DE102005049938B3
Application number: DE102005049938A
Authority: DE
Inventors: Zeki Akbayir
Original assignee: Zeki Akbayir
Priority date: 2005-10-19
Filing date: 2005-10-19
Publication date: 2007-03-01
Anticipated expiration: 2025-10-20
Also published as: EA012818B1; AT453803T; CN101365882B; HRP20100174T1; AU2006303660A1; KR20080072847A; RS51350B; PT1937980E; PL1937980T3; EP1937980A1; WO2007045288A1; US20090022585A1; EP1937980B1; EA200801103A1; BRPI0617523A2; ES2343139T3; DE502006005806D1; DK1937980T3; SI1937980T1; JP2009511824A

Abstract

The invention relates to a rotor (2) for a turbomachine and to a turbomachine equipped therewith, wherein the rotor (2) circulates in a gaseous or liquid medium and at least on one of its lateral surfaces (4) has a profile (3) with at least one convex elevation ( 19) for generating a pressure difference. This rotor (2) is characterized in that the convex elevation (19) is designed like a wing profile (3) of an aircraft and the rotor (2) has an axial cavity (6) on the inside. In this case, the rotor (2) with at least one chamber (12, 21) for supplying or discharging the intended medium is connected, wherein between the cavity (6) and the outer lateral surface (4) in the region of the airfoil (3) at least one passage opening (5) is provided. Such a rotor (2) within different housing configurations (7) forms a turbomachine that can be used as a pump, compressor, compressor, blower, turbomachine, turbine or as a pressure neutralizer.

Description

The The invention relates to a rotor for a turbomachine and a turbomachine with such a rotor.
Turbomachinery are characterized by being in a gaseous or liquid Medium generate a pressure difference or by a pressure difference be driven in such a medium. To have such Turbomachinery usually a rotor, which in the gaseous or liquid medium against a Stator is rotatably mounted and by its shape or arrangement creates a pressure difference or the pressure difference in the medium converts into a rotational movement. Such turbomachines belong first Line most types of pumps, compressors, turbomachinery, turbines or wind energy converters that over Have rotors in different designs and usually rotatable in a housing are stored as a stator.

A rotor for a coolant pump as a turbomachine is from the DE 37 17 229 A1 known. The rotor is designed as a sheet-metal wheel for small flow rates. This sheet metal wheel consists of a disc with an inner central hub and at the outer edge bent at right angles blades. The tangentially outer surface of the blades is formed as a flat approximately rectangular surface, wherein at one of the blade edges in the end region, a blocking edge is bent radially outwards. The bent blades form a certain angle to the tangent at the disk circumference. Between the blades a distance is provided, through which the liquid to be pumped passes from the inner suction region in the pressure region formed on the outer circumference. Due to the flat inclined blades arise against the outer pump housing wall turbulence, which lead to the gap losses in the main flow, which adversely affect the efficiency. Even if these gap losses are to be kept low by the radially outwardly bent blocking flanks, these gap losses are thus limited to influence. Moreover, such sheet wheels with the blades held on one side of the disc are suitable only for small flow rates, so that the scope of such rotors is largely limited to that of vehicle coolant pumps.

From the DE 82 00 744 U1 is a turbine rotor for high-speed flows known. The rotor contains centrally in the region of the axis of rotation a rotor hub, are attached to the star-shaped outwardly projecting and inclined turbine blades. At the outer ends of the turbine blades additionally obliquely arranged end disks are arranged, which are to produce a flank pressure on the rotor axis in order to set the rotor in rotation. Such a rotor is obviously provided only for the conversion of a fast flow energy into a rotary motion, so that such a rotor is likely to be unsuitable in particular when used in pumps and the like.

From the DE 43 19 291 C1 For example, a rotor for a wind energy converter is known. This rotor contains at least three rotor blades arranged vertically to the wind direction, which are arranged symmetrically about a rotational axis on two opposite rotor disks. The rotor disks are connected to a central rotatable shaft, which is mounted stationary. The rotor blades have a strongly asymmetrical profile cross section, which has outwardly against the direction of the axis of rotation, a highly convex curved surface area which is exposed to the wind. The blowing into this buoyancy side wind caused by this profile training a rotation of the rotor about its axis of rotation, which is preferably used for energy. However, such a rotor is obviously only intended for the conversion of a wind power into a rotational energy, and therefore not suitable for use in other turbomachines, in particular pumps and the like.

From the DE 197 19 692 A1 is known a rotor pump with internal gear rotor, which has a very robust design of an internally toothed rotor. In this case, the pump consists of a housing in which a rotatable eccentric ring is arranged, in which an outer and an inner impeller are rotatably mounted. In this case, the inner impeller is an inner rotor with arranged on its outer circumferential surface of a plurality of teeth, which is rotatably disposed in an outer rotor. The outer rotor encloses the inner rotor with its inner circumferential surface, on which also inwardly directed teeth are arranged. In this case, both the inner and the outer teeth extend over the entire length of the lateral surface and consist essentially of a convex symmetrical elevation, wherein arranged on the outer surface of the inner rotor six convex elevations and on the inner surface of the outer rotor seven convex elevations are. The inner cavity of the outer rotor is in each case connected to an inlet and an outlet opening, which are located opposite one another. The rotational movement of the inner rotor is also a rotational movement of the outer rotor in the eccentric ring, resulting in a number form chambers with variable volumes between the teeth of the inner and outer rotor. Thereby, a fluid in the chambers is sucked into the enlarging chambers and ejected from the decreasing chambers. In this case, a hydraulic fluid is provided as the fluid, which is pressed by the pressure differences thus generated from the inlet opening into the outlet opening. Since such a rotor consists of at least two toothed parts arranged coaxially with one another, which still have to have a different number of teeth and engage precisely with one another only at the most accurate design, such a rotor assembly is very complicated to manufacture and is equipped with a series of parts subject to friction are wear-dependent.

Of the The invention is therefore based on the object, a universally applicable Rotor for to create a variety of types of turbomachinery the robust and virtually maintenance-free and also easy to produce is.

These The object is achieved by the invention specified in claim 1 solved. Further developments and advantageous embodiments of the invention are in the subclaims specified.

The Invention has the advantage that by the airfoil on one of the lateral surfaces of the Rotor due to the Bernoulli effect due to the movement of the rotor or the flow a gaseous one or liquid Medium a negative pressure effect above the wing profile arises, so that such a rotor both in turbomachinery for liquid as also for gaseous Media is used. Since the pressure or suction effect is not through the formation of circumferential sealing chambers is created, so that advantageously also a medium mixed with solids are conveyed, so that such rotors also to a continuous transport of bulk materials or Dispersions are well suited.

The At the same time, the invention has the advantage that due to the aerodynamic airfoil profile only a slight vortex formation in the medium used and except Storage no contact with a stator or other rotor parts occurs, so that turbomachinery, which are equipped with such a rotor, particularly quiet work and hardly any flow or have friction losses. As the rotor according to the invention inside is hollow and only by a flat airfoil on one of the lateral surfaces of the Pressure difference generated, this is particularly lightweight can be produced so that only small masses are accelerated have to, which advantageously also overall in connection with the low friction and the low flow turbulences a turbomachine can be achieved with high efficiency.

By the only small rotor mass and the largely symmetrical training as well as a centric rotation even small centrifugal force effects, so that such a rotor advantageously with high speeds is operable. As a result, high pressure differences with high flow rates producible, thereby advantageously simultaneously high flow rates of the intended gaseous or liquid Medium or the solids contained therein can be achieved.

There the pressure difference that can be generated in the case of such a profile according to the invention Rotor mantle increases almost proportionally to the speed, can at a constant rotor speed advantageously barely or volume fluctuations occur. Through the wing profile on the lateral surface arises with driven rotor always a pressure difference, the independently from the ambient pressure of the medium, so that advantageously also gaseous High density media still promoted or liquids from great depth can be pumped to the surface at a high static pressure.

Of the rotor according to the invention and a turbomachine equipped therewith can not only be used in the driven state for conveying or pressure generation be used, but is at flow correct introduction of a druckkraftbeaufschlagten medium also to a speed generation usable, advantageously from hydropower or wind energy such as generating electricity.

at a multi-stage design of the rotor according to the invention and a thus equipped turbomachine are at axial stages and constant flow rate advantageously higher pressures producible or at coaxial stages because of increasing the profile surface at constant pressure difference advantageously also higher flow rates be conveyed.

The Invention is based on an embodiment, which is shown in the drawing, explained in more detail. Show it:
1 a perspective view of a pump with a single-stage pump rotor;
2 a front view of the pump with the pump rotor;
3 a plan view of the pump with the pump rotor;
4 a vane ring of an impeller for the pump rotor;
5 an array of fin elements of an impeller for the pump rotor;
6 a sectional view of a pump with a multi-stage pump rotor, and
7 : a sectional view of a drive turbine.
In 1 The drawing is a turbomachine as a pump 1 shown in perspective, the one-stage hollow rotor 2 contains as a pump rotor, on an outer circumferential surface 4 nine airfoil elements 3 has, between which passage openings 5 to the inner cavity 6 are arranged.
In the illustrated pump 2 It is a version that is preferably operated with water as a liquid medium. The pump 2 consists essentially of a stationary housing 7 as a stator in which the pump rotor 2 is arranged. The rotor is in the housing 7 in two camps 8th rotatably mounted and has a shaft in its center 9 , with a drive motor, not shown 9 connected is. The housing 7 is substantially cylindrical in shape and includes on its outer circumferential surface an outlet opening 11 for the discharge of the water to be pumped. At the left end or lateral surface of the housing 7 is to the inlet of the water to be pumped to the cavity 6 an inlet opening 10 provided, which is connectable to a feed line, not shown. The inlet opening 10 is with the cavity 6 of the rotor 2 connected and forms with this an inlet chamber 12 , With such a pump 1 can basically all liquid media such. As water, oil and the like, as well as all liquids that are mixed with solids, such. As dispersions are transported.
In 2 The drawing is the pump described above 1 shown in front view, from the detail and the arrangement and design of the rotor 2 is apparent. There is the rotor 2 essentially of a cylindrical impeller 20 Inside a cylindrical cavity 6 having, in the illustrated pump 1 an inlet chamber 12 forms. On the outer surface 4 of the rotor 2 are distributed in equal angular intervals nine convex elevations 3 arranged, which has an axially extending airfoil on the outer tangential lateral surface 4 of the rotor 2 form. Because the rotor 2 on its outer tangential lateral surface 4 several airfoil elements 3 has, in a rotation according to the Bernoulli effect in gaseous media such as air form a negative pressure range, so that all gaseous media and the interspersed with bulk materials gaseous media can be transported, compressed or sucked.
In the end of the wing profile 3 are passageways 5 to the internal cavity 6 or to the inlet chamber 12 the pump 1 provided in which there is the medium to be pumped, such as water. The axial design of the pump 1 is in detail in 3 the drawing shown in plan view. Out 3 The drawing shows that the rotor 2 is constructed lamellar in the axial direction. These fins are because of the airfoil profile 3 cut out of flat sheets, preferably with the help of a laser or punched out. There is the rotor 2 mainly made of lamellar rings 13 and an array of fin elements 14 the impeller 20 form.
The lamellar rings 13 are in 4 the drawing and the lamellar elements 14 in 5 the drawing shown in more detail, as the axial disk set the impeller 20 with the tangential lateral surfaces 4 form. The in 3 the rotor shown in the drawing 1 consists of three arrangements of lamellar elements 14 , on whose outer side surfaces in each case a lamellar ring 13 is attached. There is the lamellar ring 13 preferably made of a flat steel sheet, which is corrosion-resistant to water-containing liquids or consists of a stainless steel. The lamellar rings 13 as well as the lamellar elements 14 usually consist of the same material, which may consist of other metals, hard plastics, synthetic fiber composites or ceramics depending on the medium used. Each lamellar ring 13 has a circular bore inside 23 for example, 250 mm diameter and a smallest outer diameter of about 360 mm. The lamellar ring contains 13 preferably nine identical angular ranges of 40 °, at its outer tangential lateral surface 4 each a convex survey 19 is arranged, which is opposite to the direction of rotation 18 flat with a sloping slope in an outlet area 24 passes over and a wing profile 3 forms. The convex elevation 19 has opposite the expiring end preferably a survey 19 of about 45 mm and has a radius of about 20 mm. The opposite to the direction of rotation 18 outgoing sloping profile area 24 has a concave curvature with a radius of 167 mm and extends over a length of about 70 mm. The convex elevation 19 with the sloping concave outgoing area 24 thus forms on the lateral surface 4 a profile of a wing wing of flight testify. The wing profile 3 ends up in a slightly rising peak 25 , which acts as a spoiler and largely prevents turbulence at the tear-off edge.
After the vortex preventing tip 25 follows opposite to the direction of rotation 18 a tangential straight surface that is the smallest distance to the axis of rotation 26 and tangent to this over a length of about 5 mm. This straight surface limits the passage openings 5 in the axial direction and terminates each individual airfoil 3 on the tangential outer surface 4 of the rotor 2 , In doing so, each lamellar ring becomes 13 preferably similar wing profiles 3 formed in the same angular ranges and the same distance from the axis of rotation 26 are arranged.
Between two outer lamellar rings 13 are for the execution of the illustrated pump rotor 2 three lamellar layers of nine lamella elements each 14 arranged, which at their outer radial edges also the same airfoil profile 3 like the lamellar rings 13 exhibit. To form an impeller 20 a rotor 2 become the individual lamellar elements 14 congruent alignment with the airfoil 3 with a lamellar ring 13 or connected to other lamellar arrangements and thereby constitute an axial impeller or an impeller part, which on its outer tangential lateral surface 4 a uniform axially aligned airfoil 3 forms. Here are the lamellar elements 14 but tangentially spaced from each other and arranged in total with the lamellar rings 13 connected, wherein the distance between the lamellar elements has a passage opening 5 forms, through which the intended medium of the inner cylindrical cavity 6 by the negative pressure along the sloping wing profile 3 is sucked outward by the Bernoulli effect.
For aerodynamic design of these openings 5 are the individual lamellar elements 14 in its rear area with a convex curvature 15 and in its front region with a concave curvature 16 provided that allow a largely vortex-free flow during rotation. It goes the convex curvature 15 at the inner edge also in a concave curvature about the radius of the bore 23 of the lamellar ring 13 of 125 mm, for example. This forms the rotor 2 inside an axially continuous cylindrical cavity 6 as inlet chamber 12 ,
For attachment of the impeller 20 with the drive shaft 9 Preferably, not shown star-shaped connecting elements are provided, the torsionally rigid with the drive shaft 9 and preferably with at least one of the laminar rings 13 are connected. In another embodiment of the invention, the airfoil profile 3 Also be arranged on the inner tangential lateral surface, wherein the rotor 2 then outside a circular lateral surface 4 which reverses the direction of flow and the outlet chamber 21 in the cavity 6 the impeller 20 or the rotor 2 is formed.
To operate the pump 1 becomes the rotor 2 with a given speed and direction of rotation 18 driven, so that on the outer lateral surface 4 in the direction of rotation 18 behind the convex elevation 19 According to the Bernoulli effect, a negative pressure or a pressure difference to the surrounding gaseous or liquid medium forms, so that from the higher-pressure interior 6 the medium is sucked outwards. The pressure difference depends essentially on the speed or the peripheral speed of the impeller 20 from. The pressure difference increases approximately linearly until the vortex formation at the trailing edge or other turbulence elements becomes so great that it results in a significant backpressure. However, this can be achieved by an advantageous embodiment, in particular the tear-off edge and by the formation of circular inlet 12 and outlet chambers 21 be reduced so that at speeds of at least 10,000 rev / min, a linear pressure increase occurs.
Due to a high differential pressure, the flow rate per unit time can also be increased at the same time, but by the cross-sectional areas of the passages 5 is limited. However, the flow rate or the flow volume in a simple manner by increasing the surface of the airfoil 3 increase. Basically, there is already a pressure difference with only one wing profile 3 on the circumference of the rotor 2 or the impeller 20 produced. To increase the flow rate and to improve the flow ratio, however, were preferably nine airfoils 3 circular around the tangential outer rotor shell 4 arranged, but also a smaller as well as a higher number of profile surfaces is executable. Such a rotor 2 with at least one airfoil profile 3 does not have to be cylindrical, but can also be a spherical or conical outer surface 4 have, by which a pressure difference can be generated. In this case, such a rotor also requires no closed inlet 12 and outlet chambers 21 since a rotation within a gaseous or liquid medium without a housing part already produces a pressure difference which can only be used by means of a delivery or supply line which is merely connected to one of the inlet and outlet passages. 12 or outlet chambers 21 must be connected. This essentially determines the possibility of using the print balances the design of the turbomachine. Thus, a turbomachine with a closed inlet chamber connected to a pipe as a suction machine can also be designed for gaseous media or as a vacuum cleaner. On the other hand is a rotor 2 with a closed outlet chamber 21 advantageously used as a compressor or blower for a gaseous medium or as a pump for transport or pressure equalization of liquid media. Such a rotor 2 but can also be used to generate a speed at an existing pressure difference of a surrounding medium and to generate energy in existing water or air pressure differences.
At an in 6 the drawing shown particular embodiment of the invention are a plurality of impellers 20 axially juxtaposed and by separate outlet chambers 21 separated from each other. Here are the four illustrated impellers 20 on a common drive shaft 9 arranged in two camps 8th is mounted on a stator and the housing part. All impellers 20 are of a multi-part housing 7 surrounded, the three partitions 22 and thereby four exhaust chambers 21 forms, in each of which a similar impeller 20 is rotatably arranged.
Each impeller is like this after 1 to 5 the impeller described in the drawing 20 formed and basically consists of nine on the outer surface 4 arranged airfoils 3 , between which passages 5 to the inner cavity 6 are provided. At the first impeller 20 is a first inlet opening 10 to the exterior of the case 7 provided as a circular recess, which connects to the cavity 6 of the first impeller 20 as inlet chamber 12 manufactures. This first inlet opening 10 the intended gaseous or liquid medium is supplied, so that this as the cavity 6 formed first inlet chamber 12 of the first impeller 20 arrives. Will the rotor 2 driven at a predetermined speed, so arises on the airfoil 3 in the region of the passage opening 5 a pressure difference, causing the medium outward into the the impeller 20 surrounding first outlet chamber 21 is sucked. This results in this outlet chamber 21 a pressure increase through the second inlet opening 27 in the cavity or the inlet chamber of the second impeller 28 acts. Through this rotating second impeller 28 In turn, a pressure difference is generated, so that the medium with a pressure increase in a second outlet chamber 29 arrives. As in the second outlet chamber 29 an inlet opening is provided to the third impeller, in the subsequent two outlet chambers each have a further equal increase in pressure, so that such a four-stage pump leads to a four times higher pressure increase as in a single-stage pump 1 with only one impeller 20 , Such a multi-stage pump as turbomachine can be equipped with a variety of pressure increase stages, so that it can be produced depending on the intended speed almost any pressure increases.
Such a multi-stage pump as a turbomachine can also be formed with radial steps. These are several impellers 20 with different sized outer diameters coaxially arranged inside each other and by a common drive shaft 9 set in rotation. With such a coaxial turbomachine not only very high pressures can be generated, but also convey high passage volumes per unit time by the high effective surface of the airfoils.
In 7 The drawing shows a further particular embodiment of the invention is shown, which shows a drive turbine, preferably for a liquid medium. This is a single-stage cylindrical rotor 2 with arranged on its outer circumferential surface airfoils 3 and passageways 5 provided to its cavity, in a cylindrical housing 7 is arranged. The housing 7 Contains at its one axial end an inlet opening 10 and its other axial end an outlet opening 11 , which is bottle-necked. The one in the case 7 arranged rotor 2 is through its inlet 10 over a wave 9 driven by the also preferably liquid medium such. B. Water is supplied. Through a rotation, the water in the surrounding housing as an outlet chamber 21 sucked, so that in this an overpressure arises, from the streamlined narrow bottleneck-like outlet opening 11 enters the surrounding medium. Depending on the drive speed and cross-sectional area of the outlet opening 11 the water flows with a certain outflow velocity into the surrounding standing water, whereby a turbine-like recoil effect is generated. As a result, can preferably drive watercraft or radiate high pressure direction dependent in similar or other media.

Claims

Rotor for a turbomachine, which rotates in a gaseous or liquid medium and at least on one of its lateral surfaces ( 4 ) an airfoil ( 3 ) with at least one convex survey ( 19 ), wherein the rotor ( 2 ) inside an axial cavity ( 6 ) and the rotor ( 2 ) with at least one chamber ( 12 . 21 ) to the or Discharge of the medium is connected, wherein between the cavity ( 6 ) and the outer lateral surface ( 4 ) in the area of the airfoil ( 3 ) at least one passage opening ( 5 ) is provided.
Rotor according to claim 1, comprising at least one impeller ( 20 ) and a torsionally rigid connected shaft ( 9 ) contained in a stator ( 7 ) is rotatably storable.
Rotor according to claim 1 or 2, wherein the impeller ( 20 ) is formed substantially cylindrical and inside a cylindrical cavity ( 6 ), wherein the airfoil profile ( 3 ) either on the outer lateral surface ( 4 ) or on the inner circumferential surface is arranged.
Rotor according to one of the preceding claims, wherein at least one axially aligned airfoil ( 3 ) on one of the inner or outer tangential lateral surfaces ( 4 ) of the impeller ( 20 ), the wing profile ( 3 ) at least one radial convex elevation ( 19 ), which counter to the direction of rotation ( 18 ) in an elongated sloping outlet area ( 24 ), whose distance from the axis of rotation ( 26 ) at an outer lateral surface ( 4 ) and increased at an inner circumferential surface and at or in its end region at least one passage opening ( 5 ) to the inner cavity ( 6 ) is arranged.
Rotor according to one of the preceding claims, in which the impeller ( 20 ) consists of a metal, a plastic, a Glasfaserverbund- or a ceramic material.
Rotor according to one of the preceding claims, in which the impeller ( 20 ) is constructed like a lamella and consists of at least one lamellar ring ( 13 ) with at least one airfoil ( 3 ) and an arrangement of at least one lamella element ( 14 ) with a wing profile ( 3 ), which are axially aligned with each other, wherein the lamellar elements ( 14 ) are tangentially spaced so far apart that thereby at least one passage opening ( 5 ).
Rotor according to one of the preceding claims, in which the convex elevation ( 19 ) describes a pitch circle surface with a predetermined radius, which is opposite to the direction of rotation ( 18 ) in the sloping outlet area ( 24 ) passes, which is rectilinear, slightly convex or slightly concave and in the region or at the end of the passage opening ( 5 ) is arranged.
Rotor according to one of the preceding claims, in which the sloping outlet region ( 24 ) is slightly concave and at its end a radially outwardly directed tip ( 25 ) is arranged as a tear-off spoiler-like.
Rotor according to one of the preceding claims, in which the impeller ( 20 ) is axially multi-stage, wherein in the direction of the axis of rotation ( 26 ) axially spaced a plurality of spaced Flügelradteile ( 20 . 28 ) are arranged, each as a separate impeller ( 20 . 28 ), but these torsionally rigid with each other or the shaft ( 9 ) are connected.
Rotor according to one of claims 1 to 8, in which the impeller ( 20 ) is formed radially multi-stage, wherein a plurality of impellers ( 20 ) with different diameters coaxial with each other and symmetrical to the axis of rotation ( 26 ) and torsionally rigid with each other and / or the shaft ( 9 ) are connected.
Turbomachine with a rotor according to one of claims 1 to 10, which as stator a housing ( 7 ) in which the rotor is mounted, which either with an outer circumferential surface ( 4 ) and / or an inner circumferential surface of the rotor ( 2 ) at least one chamber ( 12 . 21 ), which on rotation has a pressure difference to the surrounding gaseous or liquid medium.
Turbomachine according to claim 11, wherein the housing ( 7 ) as a chamber ( 12 . 21 ), in which the medium is supplied, an inlet chamber ( 12 ) and as a chamber in which the medium is discharged, an outlet chamber ( 21 ).
Turbomachine according to claim 11 or 12, the at least one rotor ( 2 ) whose outer surface ( 4 ) of a housing part ( 7 ) is surrounded and with this on the rotor ( 2 ) an inlet ( 12 ) or outlet chamber ( 21 ) and at least one input ( 10 ) and / or outlet opening ( 11 ) having.
Turbomachine according to claim 11 or 12, the at least one rotor ( 2 ) whose inner cavity ( 6 ) of at least one housing part ( 7 ) and with the cavity ( 6 ) an inlet ( 12 ) or outlet chamber ( 21 ) and at least one input ( 10 ) and / or outlet opening ( 11 ) having.
Turbomachine according to one of claims 11 to 14, comprising at least one inlet ( 12 ) and an outlet chamber ( 21 ), each chamber ( 12 . 21 ) an input ( 10 ) or outlet opening ( 11 ) having.
Turbomachine according to one of claims 11 to 15, the at least one rotor ( 2 ) with an axially multi-stage impeller ( 20 . 28 ) and whose outer lateral surfaces ( 4 ) of a separate housing part ( 7 . 22 ) are surrounded, respectively an inlet opening ( 27 ) to the next stage with another impeller part ( 28 ) or an input ( 10 ) or outlet opening ( 11 ) owns.
Turbomachine according to one of claims 11 to 15, the at least one rotor ( 2 ) with a radially multi-stage impeller, which by a common housing part ( 7 ) and / or its cavities ( 6 ) of at least one housing part ( 7 ) are covered, wherein at least one housing part ( 7 ) with an input ( 10 ) or outlet opening ( 11 ) is provided.
Turbomachine according to one of claims 11 to 17, which is designed as a drive turbine and at least one rotor ( 2 ) with an impeller ( 20 ), of a cylindrical housing part ( 7 ) is surrounded and the rotor ( 2 ) and an axial inlet opening ( 10 ) for supplying a gaseous or liquid medium and for introducing a shaft ( 9 ) and at the opposite axial end of a bottle neck-shaped outlet opening ( 11 ) having.
flow machine according to one of the claims 11 to 17, used as a pump, compressor, compressor, turbine, turbomachinery or pressure neutralizer is formed.
Turbomachine according to one of claims 11 to 17, which is designed for generating rotational speed by means of a gaseous or liquid medium and at least one inlet chamber ( 12 ) for the directional supply of the pressurized gaseous or liquid medium, which is formed so that the flow direction to the convex elevation ( 19 ) of the rotatably mounted rotor ( 2 ).