EP2773854A2

EP2773854A2 - Turbomachine

Info

Publication number: EP2773854A2
Application number: EP12781313.7A
Authority: EP
Inventors: Frank Eckert
Original assignee: Duerr Cyplan Ltd
Current assignee: Duerr Cyplan Ltd
Priority date: 2011-11-03
Filing date: 2012-11-02
Publication date: 2014-09-10
Anticipated expiration: 2032-11-02
Also published as: US9982539B2; EP2773854B1; US20140234094A1; WO2013064674A3; WO2013064674A2; HRP20170078T1

Abstract

The invention relates to a turbomachine (10) having a housing (12) which has a housing duct (24) for the inflow or outflow of working medium and which has a rotor (16), the rotor being arranged so as to be rotatable about an axis of rotation (18) and having a plurality of rotor blades (28) which form rotor blade ducts (84). The rotor blade ducts (84) communicate with the housing duct (24) via guide blade ducts (42) formed in the housing.

Description

Turbomachine Description

The invention relates to a turbomachine having a housing which has a housing channel for the in-flow of working fluid, and having an impeller rotatably disposed about a rotation axis and having a plurality of impeller vanes forming impeller vane channels.

Such turbomachines with a housing and an impeller are known (JP 9 264 106 A). Thus, the pressure energy of working fluid can be converted into mechanical work and vice versa. In such turbomachines, there is the problem that when the impeller blades are charged with working fluid that flows faster than the sonic velocity (supersonic flow), the efficiency for converting pressure energy in these turbomachines and thus the performance of these turbomachines due to pressure surges decreases.

The object of the invention is to provide a turbomachine with a high efficiency, in which the impeller blades can be acted upon with a supersonic flow. In particular, it is an object of the invention to provide a turbomachine suitable for use as a turbine or compressor in an ORC plant.

This object is achieved by a turbomachine of the aforementioned type, in which the impeller blade channels communicate with the housing channel via housing-fixed guide blade channels which have an impeller-side guide-blade channel opening and a housing-channel-side guide blade channel opening. The invention is based in particular on the idea that the working media in so-called ORC systems (ORC = Organic Rankine Cycle), in those with a thermodynamic cyclic process using a recycled organic working medium in the form of, for example, butane, toluene, silicone oil, ammonia, methylcyclohexane or ethylbenzene, which generally have a low evaporation temperature with respect to water, and in which the speed of sound is low , Heat can be converted into mechanical energy (ORC cycle). This has the consequence that even at comparatively low flow velocities in turbomachines that are operated in such systems, losses may occur, which affect the efficiency of such a system.

In order to minimize flow losses in a turbomachine, the turbomachine has a housing with vane channels configured to coalesce, i.e., coalesce into the vane channels. counteracts in the guide vane channels converging pressure surges.

The guide vane channels are therefore designed according to the invention as a Laval nozzle or similar to a Laval nozzle, ie as a flow member, which has a bottleneck and when operating the turbomachine as a turbine in the flow direction before the bottleneck has a convergent cross section and behind the bottleneck a divergent cross section. The transition from the convergent to the divergent section of the vane channels is gradual. In the guide vane channels so that a fluid flowing through can be accelerated to supersonic speed, without causing excessive compression shocks. The speed of sound is reached exactly in the narrowest section of the nozzle. The cross-section of the guide vane channels is preferably angular. However, it is also possible to carry out the guide vane channels with a round cross section. The guide vane channels preferably have a concave wall surface facing the impeller and to which the working medium can flow. The wall surface of the guide vane channels facing away from the impeller, which are flown by working medium. can, is convex on the other hand. In this case, the guide vane channels in a direction of the impeller channels facing flow direction for working fluid has a flow cross-section which increases monotonously. For this purpose, the guide vane ducts in the working medium flow direction facing the impeller passages may have a width in the plane perpendicular to the axis of rotation which increases monotonically and / or the vane passages may have a height in the direction of the axis of rotation in this direction which increases correspondingly monotonically.

The vane channels may each have a center evenly spaced from a wall surface facing the impeller and a wall surface facing away from the impeller, which divides the cross-sectional profile of a nozzle channel into a housing channel side portion and an impeller side portion, the cross sectional profile of each nozzle channel being related is asymmetrical to the middle. In this case, the housing-side portion and the impeller-side portion preferably each have a free cross-sectional area for the passage of working fluid, wherein the free cross-sectional area of the impeller-side portion is greater than the free cross-sectional area of the housing channel-side portion. The cross-sectional profile of a guide blade channel may in particular be trapezoidal.

A turbomachine according to the invention can be operated in particular as a so-called constant-pressure or impulse turbine, in which a gas and / or vaporous working medium is accelerated while reducing its pressure and the associated expansion between the guide vanes in the guide vane channels, in order then to impinge on the blades of the impeller , This leads to a momentum transfer to the impeller so that a torque can be exerted on an output shaft connected to the impeller. The resulting mechanical power can then be used, for example, to drive a generator for the generation of electrical energy. In order to obtain a resultant force in the direction of rotation of the impeller when the impeller blades are exposed to the working fluid, it is advantageous if the largest possible part of the flow leaving a guide vane duct for a working medium has an angle which is as ideal as possible for the impeller. According to the invention, therefore, the guide vanes of the turbomachine are designed so that the working fluid is guided with a flow to the impeller, which has a vertical to the radius of the impeller flow component. One idea of the invention is, in particular, to guide the working medium through guide vanes onto the impeller, which lie in a plane perpendicular to the axis of rotation of the impeller and are curved towards the impeller. Namely, the inventor has recognized that when the working fluid is directed onto the impeller in a straight flow path, only a comparatively small portion of the flow has the ideal angle to the impeller at the downstream end of a corresponding vane passage. The part of the flow which is closest to the vanes has either too little or too much inclination towards the impeller. In particular, in supersonic flows, this has the consequence that strong pressure surges between running and Leitbeschaufelung occur, which affect the efficiency of the turbomachine.

According to the invention, it is therefore proposed to form the guide vane channels with openings on one side of the housing channel lying on a cylinder surface arranged coaxially to the axis of rotation and to guide the working medium in the middle with a flow path which passes through the cylinder surface at an intersection in which the tangent to the flow path and the lying in a plane perpendicular to the axis of rotation plane tangent to the cylinder surface form an angle α, for which applies 5 ° <a1 <20 °, vorzugswese cd = 12 °. In this way, a high momentum transfer between the impeller and working fluid is made possible. In this case, it is advantageous if the guide vane channels are located on a wheel-side guide side lying on a cylinder jacket surface arranged coaxially to the rotation axis. felkanalöffnungen and the working medium in the middle lead with a flow path which passes through the cylinder surface at an intersection in which the tangent to the flow path and lying in a plane perpendicular to the axis of rotation perpendicular to the tangent surface to the cylindrical surface form an angle a2, applies to the applies 5 ° <a2 <20 °, preferably a2 = 12 °.

It is advantageous if the impeller blades have a substantially crescent-shaped cross-sectional contour and have a concave blade surface which extends from a first blade edge facing the guide blade channels to a second blade edge facing away from the blade channels, wherein a lying in a direction perpendicular to the axis of rotation plane tangent the first blade edge, which is applied to the concave blade surface, with an edge passing through the first blade edge and perpendicularly intersecting the axis of rotation forms an obtuse angle / ΐ = β1 + 90 ^ο , for which the following applies: 5 ° </> ΐ-90 ^ο <45 ^ο , especially 20 ° </? ΐ-90 ^ο <40 ^ο , preferably /? ΐ-90 ^ο = 29 °. It is particularly advantageous if in this case a tangent lying in a plane perpendicular to the axis of rotation at the second blade edge to the concave blade surface with a straight line intersecting the second blade edge and perpendicularly intersecting the axis of rotation forms an acute angle .theta.2 = 90.degree for which applies: 5 ° <90 -β2 <90 °, in particular 35 ° <90 - /? 2 <35 °, preferably 90 - /? 2 = 40.5 °. In particular, it is advantageous if the obtuse angle /? L = β1 + 90 ° and the acute angle /? 2 = 90 ° -β2 satisfy the following relation: β1 <180 ° - /? 2, ie β1 <β2. This makes it possible to achieve a particularly high energy efficiency of the turbomachine.

The inventor has recognized that when the distance r ₂ of the first blade edge of each impeller vane facing the vane channels from the axis of rotation and the distance n of the second vane edge of each impeller vane facing away from the vane channels from the axis of rotation satisfies the following relationship: 70% < r1 / r2 <80%, preferably r1 / r2 ^« 75%, the impeller blade channels have a favorable for supersonic speed working fluid, which is conducive to an adiabatic relax the working fluid. The inventor has found that by having the number Z of impeller vanes satisfy the relation Z << C xr1 / r2, where C is a constant of 70 <C <90, torque transmission between the impeller and a working medium can be maximized without that excessive flow losses occur.

In addition, the inventor has recognized that it is conducive to the energetic efficiency of the turbomachine when the distance r ₂ of the first blade edge of each impeller blade facing the guide vanes from the axis of rotation and the parallel height h _{E of} the first blade edge of each Impeller blade satisfies the following relationship: 12% <h _E / r ₂ ^ 28%.

The blade surfaces of the impeller blades may be parallel to the axis of rotation of the impeller. This allows a simple manufacture of the impeller blades. The impeller has an impeller blade carrier which receives the impeller blades and has a rotationally symmetrical guide contour that can be flowed through by working medium, which deflects a flow path for working medium between the impeller channels and a diffuser. By extending the guide contour of the blade carrier in the diffuser, it is possible to avoid a swirling of working medium, which emerges from the impeller blade channels. In the case of the turbomachine, the rotor blades can be releasably fixed to the impeller blade carrier or can be materially connected to it. The vane channels in the housing of the turbomachine are conveniently formed with a covered by an annular guide blade carrier covered by a cover spiral-shaped vanes having a rotation axis of the facing away from the convex blade surface. The guide vanes and the guide blade carrier can be connected cohesively. The guiding Blades have blade surfaces parallel to the axis of rotation. The distance between two adjacent guide vanes may increase here in a direction of the impeller channels facing the flow of working fluid. The height of the guide vanes decreases at least to a constriction at a certain radial distance from the axis of rotation with increasing distance from the axis of rotation. The vane support and the cover preferably define a compensating space opened to the housing channel and opening into the guide vane channels, with a cross-section tapering in the direction pointing to the axis of rotation.

The guide vane carrier and the guide vanes can in particular be manufactured from an integral pipe socket by means of erosion and / or milling and / or Elisieren, which allows a cost-effective production. The turbomachine is particularly suitable for use in an ORC cycle or as a compressor for compressing gaseous medium containing organic constituents.

Advantageous embodiments of the invention are shown schematically in the drawings and are described below:

Show it:

1 shows a turbomachine with a housing. FIG. 2 shows a vane carrier and an impeller in the turbomachine; FIG.

3 shows the guide vane carrier and the impeller in a side view; Fig. 4 is a perspective view of the impeller and vane carrier; 5 shows a section of impeller and vane carrier along the line VV of Fig. 3.

Fig. 6 is a rear view of the vane carrier and impeller; Fig. 7 and Fig. 8, an annular cover for the vanes of the

guide vane;

9 shows a partial section of guide blade carrier and impeller; 10 shows a longitudinal section of a guide blade channel;

Fig. 1 1 shows a cross section of a guide vane channel;

Fig. 12 is a cross-sectional profile of a nozzle channel;

13 shows a longitudinal section of a guide vane in the turbomachine;

FIG. 14 shows a further partial section of guide blade carrier and impeller; FIG. Fig. 15 is a partial section of the impeller;

16 shows a further partial section of guide blade carrier and impeller;

FIG. 17 shows a pressure curve in working medium, which is moved by the flow maschine; FIG.

18 shows an ORC system with a turbomachine;

19 is a partial section of another turbomachine with a

Vane carrier and an impeller; FIG. 20 shows a longitudinal section of a guide blade channel in the further flow machine; FIG.

Fig. 21 is a cross section of the vane passage; FIG. 22 shows the cross-sectional profile of the guide vane channel; FIG.

FIG. 23 the cross-sectional profile of a guide vane channel in a further, third turbomachine; FIG. FIG. 24 shows a longitudinal section of a guide vane in the further turbomachine; FIG.

Fig. 25 is a partial section of another flow machine with a

Vane carrier and an impeller;

FIG. 26 shows a longitudinal section of a guide blade channel in the further flow machine; FIG.

FIG. 27 shows a fourth turbomachine with a housing; FIG.

FIG. 28 shows a section of the turbomachine along the line XXVI-XXVI from FIG. 25 with a connection wall; FIG.

FIG. 29 shows a section of the turbomachine along the line XXVII-XXVII from FIG. 25; FIG.

FIG. 30 shows a vane carrier with the guide vanes of the turbomachine formed thereon; FIG. FIG. 31 shows the guide blade carrier with the guide vanes as a section; FIG. Fig. 32 is an enlarged view of vane wearers and vanes; FIG. 33 is a side view of the impeller of the turbomachine; FIG. and FIG. 34 shows the housing of the fourth turbomachine.

The turbomachine 10 in FIG. 1 has a housing 12 with a pipeline inlet connection 14 for the supply or removal of working medium. In the housing 12, an impeller 16 is rotatably mounted on a shaft about an axis of rotation 18 which has a plurality of impeller blades 28 which form an impeller blade wreath. In the housing 12, a guide vane carrier 20 is fixed with vanes 22. The housing 12 has a housing channel 24, which can be acted upon via the pipe connection 14 in the flow direction of the arrow 15 flowed working medium when the turbomachine 10 is operated as a turbine. When the turbomachine 10 is operated as a compressor, the working medium is removed from the housing channel 24 through the pipe connection 14.

FIGS. 2 and 3 show the guide blade carrier 20 with the rotor 16 in a top view and a side view. 4, the impeller 16 and the vane support 20 is shown in a perspective view. Fig. 5 shows the vane support 20 with the impeller 16 along the line V-V of Fig. 3 as a section. FIG. 6 shows the guide blade carrier 20 and the rotor 16 as a rear view in the direction of the arrow 37 from FIG. 3.

The impeller 16 has an impeller blade carrier 26 to which the impeller blades 28 are fixed cohesively. The impeller blades 28 are stabilized and covered on their side facing away from the impeller blade carrier with an annular bandage member 30, which is connected by means of fastening screws 38 to the impeller blades 28. The impeller blade carrier 26 has a rotational position with respect to the axis of rotation 18. symmetrical guide contour 32, which extends into a diffuser space 34 of a diffuser 35. The impeller vanes 28 form impeller vane channels 84 which redirect the working medium flowing between the housing channel 24 and the diffuser space 34. The vanes 22 are materially connected to the guide vane carrier 20. Associated with the guide blade carrier 20 is an annular cover 36 held in the housing 12 and forming via a connection face 33 with the guide blade carrier 20 and the guide vanes 22 spirally curved guide vanes 42 which each act as Laval nozzles. The vane support 20 with the vanes 22 is made of a pipe stub. In terms of manufacturing technology, this opens up the possibility of working out the shape of the guide vanes 22 from the guide blade carrier 20, for example by means of milling, eroding or elimination, after they have been subjected to a turning operation in order to create a curved bevel on the side facing the annular cover 36. The vane support 20 has a mounting flange 40 with which it can be fixed in the housing 12 of the turbomachine 10. FIG. 7 shows the annular cover 36 in the turbomachine 10 in a perspective view. Fig. 8 shows the annular cover 36 as a section. Also, the cover 36 can be inexpensively produced as a rotationally symmetric rotary member having a matching pad 33 congruent with the vanes 22 of the vane carrier 22.

9 is a partial section of the vane carrier 20 and impeller 16. The vanes 22 each have a concave vane surface 46 facing the impeller 16 and a vane surface 44 that is convex. Each vane channel 42 has a center 62 corresponding to a curved line with a curvature vector 43 facing the impeller 16. The vanes 22 have impeller-side vane edges 51, 53 and housing-side vane edges 51 ', 53'. The vanes 22 may be machined on the vane support 20, in particular by means of a so-called end mill, since the bottom wall of a vane duct 42 is flat, the cross-sectional profile of a vane duct 42 has edges, and each vane duct 42 is basically the same. About the leadership of the end mill, it is possible, for example, any desired curved straight or curved, to the rotation axis 18 inclined towards, equal width or width-changing guide vane channel shape. 10 is a partial section of the vane support 20 along the center 62 in a sectional area parallel to the axis of rotation 18. By fitting the pad 33 of the annular cover 36 to this curved slope, fitting the annular cover 36 so as to produce a vane channel geometry which at the radius r _min with respect to the axis of rotation 18 has a constriction 50 with a narrowest cross section. Impeller side of the constriction 50, the cross section of the vane channel is divergent, ie, its free cross-sectional area increases towards the impeller 16 towards. Housing channel side of the constriction 50, the cross section of the guide vane channel 42 is convergent, ie its free cross-sectional area decreases starting from the housing channel 24 to the impeller 16 back. As shown in Fig. 1 1, each of the guide vanes 42 formed by the blade surfaces 44, 46 of the vanes wall surfaces has a flat bottom surface 47 and an inclined ceiling surface 49. Fig. 12 shows the trapezoidal cross-sectional profile of the guide vane 42. The flow path 60 for the working medium passes through the center 62 of the guide vane channel 42 which divides it into a housing-channel-side 65 and an impeller-side section 67. With respect to the center 62, the cross-sectional profile of the vane channel 42 is asymmetrical. The free cross-sectional area of the impeller-side section 67 is greater than the free cross-sectional area of the housing-channel-side section 65 thereof. FIG. 13 is a longitudinal section of a vane 22. Each vane 22 has a concave vane surface 46 and a convex vane surface 44.

It should be noted that also the impeller 16 with the impeller vane carrier 26 and the impeller vanes 28 can be made in a similar manner by means of milling, eroding or elimination. The impeller blade carrier 26 can basically be manufactured on a machine tool as a rotating part having a thick edge with a bevel. From this edge, the impeller blade channels 84 are then machined by eroding, Elisieren or milling. Again, the use of a finger milling cutter is particularly suitable since the bottom of the corresponding channels can be flat over the entire channel length and each channel is equally deep. By guiding the end mill, it is then possible to produce any desired straight or curved curved, to the rotation axis 18 inclined towards, equal width or width-changing channel shape. By means of the annular bandage member 30, the desired nozzle channel geometry is thus generated over the slope of the impeller blade carrier 26 with an inlet and outlet edge at each impeller blade. The guide vane channels 42 have openings 48 on the housing side. As shown in FIG. 14, they guide the working medium in the center 62 with the flow path 60, which passes through the cylinder jacket surface 56 at an intersection point 63. At the point of intersection 63, the tangent 64 to the center 62 and the tangent 66 lying in a plane perpendicular to the axis of rotation 18 form an acute angle cd to the cylinder jacket surface 56. On the impeller side, the guide vane channels 42 have openings 70 lying on a cylinder jacket surface 68 arranged coaxially to the axis of rotation 18. Here, the working medium flow path 60 in the middle 62 of the vane channels 42 passes through the cylinder jacket surface 68 at an intersection 72 in which the tangent 74 passes through Center 62 and in a direction perpendicular to the axis of rotation 18 Level lying tangent 76 to the cylinder surface 68 form an angle a2, for which applies: α2 ~ 12 °.

15 shows a portion of the impeller with impeller blades 28. The impeller blades 28 have a substantially crescent-shaped cross-sectional contour and have a concave blade surface 78 extending from a guide vane 42 facing the first run radschaufel edge 52 at the distance r ₂ of the rotation axis 18 to a guide vane channels 42 facing away from the second impeller blade edge 54 which has the distance n from the axis of rotation 18. The guide vane channels 42 facing impeller blade edges 52 lie on a coaxial with the axis of rotation 18 cylinder jacket surface 53 with the radius r ₂ . The rotation axis 18 facing the running wheel blade edges 54 are positioned on a coaxial with the axis of rotation 18 cylinder jacket surface 59 with the radius n.

A lying in a plane perpendicular to the axis of rotation 18 lying on the first impeller blade edge 52 to the concave blade surface 78 applied tangent 80 with a first impeller blade edge 52 passing through lying in a plane perpendicular to the axis of rotation 18 plane tangent 82 to the coaxial to the axis of rotation 18 Cylinder surface 53 while an angle ß1, for which applies: ß1 = 29 °. At the same time applies to a lying in a plane perpendicular to the axis of rotation 18, lying on the second impeller blade edge 54 to the concave blade surface 78 tangent 85 and a second impeller blade edge 54 passing tangent 86 to the cylinder jacket surface 59 in a plane perpendicular to the axis of rotation, that these form an angle ß2, for which applies: ß2 = 40.5 °. That is to say, the tangent 80 forms, with the straight line 81 passing through the first blade edge 52 and perpendicularly intersecting the rotation axis 18, an angle? Ϊ́: = β1 + 90 °, for which the following applies: l1: = 119 °. Accordingly, a lying in a plane perpendicular to the axis of rotation 18 level at the second blade edge 54 applied to the concave blade surface 78 tangent 80 forms with a the second vane edge 54 passing through and the axis of rotation 18 perpendicularly intersecting straight line 89 an angle /? 2: = 90 ° -β2, satisfies the following relationship: ßl -49.5 °.

16 shows a portion of the wheel carrier 20 with the impeller 16 of FIG. 5 in an enlarged view. When the turbomachine 10 is operated as a turbine, the working medium flows along the flow path 88 out of the housing channel 24 into the diffuser space 34. The working medium enters the guide vanes 42 formed by the vanes 22 through an equalization space 41, the entrance height h on the housing channel side _E and then act on the blades 28 of the impeller 16 at the impeller inlet radius r _e . The height of the guide vane channels 42 at the impeller-side outlet opening corresponds to the entry height h _E. Here, the working medium flows in the direction of the straight line 80 from FIG. 15 onto the impeller blades, which have the height h _E at the leading edge 52. The impeller 16 has a discharge radius r _A. At the exit edge 54, the impeller blades 28 have the height h _A. At the vane edges 51, 53, ie where the working medium exits the vanes, the vanes have the height h _L A- The distance r ₂ of the vane channels 42 facing first blade edge 52 of each impeller blade 28 of the rotation axis 18 and the distance n the second blade edge 54 of each impeller blade 28 facing away from the guide vane channels from the axis of rotation 18 satisfies the following relationship: n / r ₂ «75%.

In this case, for the number Z = 59 of the impeller blades 28 of the impeller 16, the following relationship applies: Z ^« C ^■ Π / Γ ₂ , the distance r ₂ of the first blade edge 52 of each impeller blade 28 facing the guide blade channels 42 from the axis of rotation 18 and the distance n the second vane edge 54 of each impeller vane facing away from the vane channels 42 is 28 from the axis of rotation 18 and C = 78.66 is a constant which lies in the number interval [70, 90].

The distance r ₂ of the first vane edge 52 of each impeller vane 28 facing the vane channels 42 from the axis of rotation 18 and the height h _{E of} the first vane edge 52 of each impeller vane 28 parallel to the axis of rotation 18 satisfies the following relation: 12% <h _E / r ₂ <28%.

The apparent in particular in FIG. 10 form of each Leitschaufel- channel 42 in the turbomachine 10 ensures that it can act as a Lava- Idüse. That this shape allows impeller 50, the working medium with a supersonic flow is movable impeller, when the pressure of the working medium in the housing channel 24 exceeds a threshold. This can be achieved that the impeller 16 can be acted upon with working fluid that moves faster than the speed of sound. The course of the guide vane channels 42 in the manner of a spiral section, the curvature of which faces the impeller 16, ensures that a pressure gradient substantially radially symmetrical with respect to the axis of rotation 18 is established in the vane channels 42.

FIG. 17 shows a typical pressure curve in the guide vane channels 42 and the impeller vane channels 84 when the working medium of the turbomachine 10 flows in the direction of the arrows 45 with supersonic flow. The pressure field isobaric 90 which is formed in the guide vane channels 42 is essentially radially symmetrical with respect to the axis of rotation 18 of the impeller 16 of the turbomachine. This causes the pressure in the impeller blade channels 50 and the guide vane channels 42 to be prevented. The working medium can thus flow out of the housing channel 24 through the guide vane channels 42 via the impeller 16 to the diffuser space 34 in such a way that it almost completely impulses its impulse Impeller blades 28 transmits and not in pressure surges, which reduce the efficiency of the turbomachine 10.

The above-described turbomachine 10 is particularly suitable for use as a turbine in an Organic Rankine cycle or the working medium used for compacting in an Organic Rankine cycle.

FIG. 18 shows an ORC system 100 with a turbomachine 110, which is operated as a steam turbine and which is arranged in a working medium circuit 105. As fluid working agents, for example, butane, toluene, silicone oil, ammonia, methylcyclohexane or ethylbenzene are used. To the turbomachine 1 10, which has the structure described with reference to the preceding figures, a generator 121 is coupled. The ORC system 100 has a working fluid condenser 124. In the ORC system 100, there is a feed pump 122 acting as a working medium pump. The feed pump 122 brings the fluid working fluid in the liquid state of aggregation to operating pressure. The liquid working fluid flows through a heat exchanger 123 acting as an evaporator. In this process, the working fluid evaporates. At the output of the heat exchanger 123 saturated steam or dry steam is then provided. As a result of the energy input in the heat exchanger 123, the specific volume and the temperature of the steam increase. The steam of the working fluid is then released almost isentropically to a lower pressure via the turbomachine 1 10 connected to a generator 121. This increases the specific volume due to expansion. The associated increase in volume of the working fluid, caused by the pressure difference, causes a resulting work in the form of a volume change work, which the turbomachine 1 10th converted into mechanical energy at their blades. The turbomachine 1 10 drives the generator 121.

From the turbomachine 1 10, the steam passes into the working fluid condenser 124. The working fluid condenser 124 is a heat exchanger through which a coolant circuit 131, which contains a cooling fluid, is guided. Via the coolant circuit 131, the heat released during the condensation is fed into a heat network (not shown). Alternatively, it is also possible to discharge the heat of the coolant guided in the coolant line 131 to the environment via a heat exchanger.

In the working as a working fluid condenser 124 heat exchanger condenses the working fluid and goes completely into the liquid state of aggregation. With the working as a pump pump feed pump 122, the working fluid is then brought back to operating pressure and passes again in the acting as an evaporator heat exchanger 123. The circuit for the working fluid in the ORC system 2 is then closed.

19 is a partial section of a guide rail carrier 220 and of a rotor 216 in a further flow machine 210, the structure of which essentially corresponds to the turbomachine 10 described with reference to FIGS. 1 to 16. Functionally identical elements in the figures for the turbomachine 10 and the turbomachine 210 are therefore identified below with numbers increased by the number 200 as reference numerals. The turbomachine 210 has guide vanes 242, through which the working fluid with the flow path 260 from the housing channel on the impeller blades 228 of the impeller 216 can pass.

20 shows a guide vane duct 242 along the flow path 260 running in its center 262 in the direction of the arrows XX-XX of FIG. 19. In FIG. 21, the vane passage 242 is shown as a section in the drawing tion of the arrows XXI-XXI shown in FIG. 19. The Leitschaufelkanal 242 also acts for flowing out of the housing channel working fluid here as a Laval nozzle with the overflow stream, the blade surfaces 278 of the impeller 216 at the angle o2 = 12 ° with respect to a plane perpendicular to the axis of rotation of the impeller 216 plane tangent to a in With respect to the axis of rotation of the impeller 216 coaxial cylinder jacket surface 268 can flow. In modified embodiments, angles 8 ° <a2 <22 ° are also possible.

FIG. 22 shows the rectangular cross-sectional profile of the guide vane channel 222. FIG. 23 shows the cross-sectional profile 222 'of a vane channel of a further flow machine, which is constructed corresponding to the above turbomachines. The cross-sectional profile 222 'of this Leitschaufelkanals is not rectangular, but round. FIG. 24 shows a guide blade 222 from FIG. 19 in a longitudinal section.

25 is a partial section of a guide blade carrier 220 ^" and an impeller 216 ^" in a further flow machine 210 ^" , the structure of which fundamentally corresponds to the turbomachine 10 described with reference to FIGS.1 to 16. Functionally identical elements in the figures to the flow chart FIG - Mungmaschine 10 and the turbomachine 210 ^" are therefore identified below with numbers increased by 200 numbers as reference numerals. The turbomachine 210 ^"has Leitschaufelkanäle ^242" through which the working medium to the flow path 260 ^'from the housing channel to the impeller blades 228 ^"of the impeller ^216' can pass. The guide vanes ^222" are provided on their side facing the housing channel ends 223 ^'in the manner of a Cylindrical shell portion rounded designed to allow ingress of working medium from the housing channel in the guide vane channels with reduced flow losses, in particular, the guide vanes 228 ^" in their gem. Fig. 25 illustrated cross section a radius between 1 mm and 5 mm. At least one guide vane channel 242 ^" , preferably all the cored air channels, have at least one sectional constant width b. The portion of constant width b preferably extends along at least half of a housing channel bounded by two vanes 222 ^" .

Fig. 26 shows a vane channel 242 ^"along the in the center ^262" extending flow path 260 ^'in the direction of arrows XX ^{^"XX"} of Fig. 25. Each Leitschaufelkanal 242 ^"acts for flowing out of the housing passage working medium also as a Laval nozzle, the vane surfaces 278 ^"of the impeller ^216" o2 = with respect to the one to the axis of rotation of the impeller 216 ^"lying perpendicular plane tangent with respect to the axis of rotation of the impeller 216 at ^a" 12 ° coaxial with excess jet flow at the angle Cylinder surface 268 ^" can flow.

Each vane duct 242 ^" in the turbomachine 210 ^" has a throat 250 ^" with a narrowest cross-section at the distance a from the cylinder jacket surface 268 ^" . Impeller side of the constriction 250 ^" is the cross section of the guide vane channel divergent, ie at constant width b, the height h to the impeller 216 ^" added. On the housing channel side of the constriction 250 ^" , the cross-section of the guide blade channel 242 ^" converges, ie its free cross-sectional area decreases from the housing channel to the impeller 216 ^" , in modified embodiments also other nozzle geometries, in particular also subsonic nozzles, can be provided.

FIG. 27 shows a further, fourth turbomachine 310. Functionally corresponding elements in the figures for the turbomachine 10 and the turbomachine 310 are therefore identified below with numbers increased by the number 300 as reference numerals. The turbomachine 310 has a cylindrical housing 312 with a pipe connection 314 designed as a pipe socket. FIG. 28 shows the flow machine as a section along the line XXVIII-XXVIII from FIG. 27 with an additional connection wall 301. In Fig. 29 is the Turbomachine can be seen as a section along the line XXIX-XXIX of FIG. 27. In contrast to the turbomachine 10, the housing channel 324 surrounds the impeller 316 annularly. The guide vanes 322 are rounded at their ends 323 facing the housing channel 324 in order to allow the entry of working medium from the housing channel into the guide blade channels with the lowest possible flow losses. The guide blade carrier 320 with the guide vanes 322 shown in FIGS. 30, 31 and 32 is likewise made from a pipe socket into which the guide vanes 322 are machined by means of milling, eroding or elimination. The vane carrier 320 has a mounting flange 340, with which it can be fixed in the housing 312 of the turbomachine 310.

The guide vanes 322 in the turbomachine 310 are also covered here with an annular cover 336. This cover 336 forms with the vane support 320 and the vanes 322 formed thereon vane channels 342, each having an opening communicating with the housing channel 324. The vane channels 324 also have a helical course here and guide the working fluid on a flow path between the housing channel 324 and the impeller 316, which has a curvature facing the impeller 316. Starting from the housing channel 325 toward the impeller 316, the cross-section of the nozzle channels 342 with respect to the axis of rotation 318 tapers at a substantially constant width to the constriction 350 having the distance r _nm in from the axis of rotation 318. From there, the free cross-section of the vane channels 342 in the direction of the impeller 316 then increases again. Each guide vane channel 342 thus also has the shape of a spiral-curved nozzle which, in the manner of a Laval nozzle, initially tapers in the direction pointing to the impeller 316, starting from the housing channel 324 and then widening, the nozzle having a trapezoidal opening cross-section. 33 shows the impeller 316 in the turbomachine 310 without the bandage member 330 covering the impeller blades 328 to form the impeller blade channels 384. FIG. 34 shows the housing 312 of the turbomachine 310. The housing 310 is a tubular body in which are preferably incorporated by means of turning flange portions 315, where the vane support 320 and the cover 336 is fixed to the guide vane channels 342.

Above all, this new geometry increases the efficiency of turbo machines in ORC systems, where the flow within the blasting is usually above the speed of sound. Also reduce the manufacturing costs, since the flow channels are easier to shape.

In summary, it should be noted that with the above-described geometries of the guide vane channels 42, 242, 342 and the impeller blades 28, 228, 328 a very high efficiency of a turbomachine can be achieved. This high efficiency can be achieved in particular when using such a turbomachine as turbomachinery for ORC systems, in which the flow velocity for the working medium within the impeller blading is generally above the speed of sound. Because the flow channels in the turbomachines described above are very easy to form, these turbomachines can be produced with very low production costs. In this context, it should be noted that the above-described manufacturing methods for the impeller blades and the guide vanes of the turbomachines described above are also suitable for corresponding assemblies of axial turbines. In this case, the geometry of the channels is preferably adapted to the direction of flow changed with respect to a radial turbine to the impeller axis. In particular, the following preferred features of the invention are to be noted: The invention relates to a turbomachine 10 with a housing 12, which has a housing channel 24 for the inflow or outflow of working medium. The turbomachine includes a rotatable about an axis of rotation 18 arranged impeller 16 with a plurality of impeller blades 50, the impeller blades form channels 84. The impeller vane channels 84 communicate with the housing channel 24 via vane channels 42 formed in the housing.

LIST OF REFERENCE NUMBERS

10 turbomachine

12 housing

14 pipe connection

15 arrow

16 impeller

18 rotation axis

20 vane carrier

22 vane

24 housing channel

26 impeller carrier

28 impeller blade

30 bandage organ

32 lead contour

33 connection area

34 diffuser room

35 diffuser

36 cover

37 arrow

38 fixing screw

40 mounting flange

41 compensation room

42 vane channel

43 curvature vector

44, 46 Scoop surface, wall surface

45 arrow

47 floor area

49 ceiling area

48 opening, vane channel opening

50 bottleneck

51, 53, 51 \ 53 ^' edges 51, 53, 51 V, 53 'vane edge

52, 54 barrel blade edge

53, 59 cylindrical surface

55, 57 blade surface

56 cylindrical surface

60.88 flow path

62 middle

63 intersection

64 area

65, 67 section

66 tangent

68 cylinder jacket surface

70 vane channel opening

72 intersection

74, 76 tangent

78, 79 blade surface

80, 82, 85, 86 tangent

81, 89 Straight

84 impeller blade channel

87 lead contour

90 isobars

100 ORC system

1 10 turbomachine

121 generator

122 feed pump

123 heat exchangers

124 working fluid condenser

131 coolant circuit

210, 210 ^" turbomachine

216, 216 ^" impeller

220, 220 ^" vane carrier 216 impeller

222, 222 ', 222 ^" vane

228, 228 ^" impeller blade

236, 236 ^" cover

242, 242 ^" vane channel

248, 248 ^" opening

250, 250 ^" bottleneck

260, 260 ^" flow path

268, 268 ^" cylindrical surface

278 blade surface

301 connection wall

310 turbomachine

312 housing

314 Pipe connection

316 impeller

320 vane carrier

322 vanes

223 ^" , 323 end

324, 325 housing channel

328 impeller blade

336 cover

338 vane

340 mounting flange

342 vane channel

384 impeller vane channel

Claims

claims

1 . Turbomachine (10) having a housing (12) having a housing channel (24) for the in-or outflow of working medium, and having a rotatably about an axis of rotation (18) arranged impeller (16) having a plurality of impeller blades (28 ), the impeller blade channels (42), characterized in that the impeller blade channels (28) via housing fixed guide vanes (42) having a impeller side Leitschaufelkanaloffnung (70) and a housing channel side Leitschaufelkanaloffnung (48) communicate with the housing channel (24).

2. Turbomachine according to claim 1, characterized in that the guide vane channels (42) have a the impeller (16) facing of working medium anströmbare concave wall surface (46).

3. Turbomachine according to claim 1 or 2, characterized marked, that the guide vane channels (42) have a the impeller (16) facing away from working medium convex wall surface (44).

4. Turbomachine according to one of claims 1 to 3, characterized in that the Leitschaufelkanäle (42) have a constriction (50) ben and between the constriction (50) and the impeller-side Leitschaufelkanaloffnung (70) have a divergent cross-section.

5. Turbomachine according to claim 4, characterized in that the Leitschaufelkanäle (42) between the constriction (50) and the housing sekanalkanal Leitschaufelkanaloffnung (48) a convergent

Have cross-section. Turbomachine according to claim 4 or 5, characterized in that the Leitschaufelkanäle (42) between the Gehäusekanalseitig guide vane channel opening (48) and the impeller-side housing channel opening (70) in a plane perpendicular to the axis of rotation (18) one of the constriction (50) the impeller-side vane channel opening (70) have increasing width.

6. Turbomachine according to one of claims 4 to 6, characterized in that the guide vane channels (242 ^" ) between the housing-channel-side vane channel opening (248 ^" ) and the impeller-side housing channel opening (70) have a plane perpendicular to the axis of rotation (18) the constriction (250 ^" ) to the impeller-side guide vane channel opening (70) towards increasing height (h) have.

Turbomachine according to one of claims 1 to 7, characterized in that the guide vane channels (42) each one of the impeller (16) facing wall surface (46) and of the impeller (16) facing away from the wall surface (44) evenly spaced center (62 ), which divides the cross-sectional profile of a vane passage (42) into a housing-channel-side portion (65) and an impeller-side portion (67), wherein the cross-sectional profile of each vane passage with respect to the center (62) is asymmetrical.

Turbomachine according to claim 8, characterized in that the housing-channel-side portion (65) and the impeller-side portion (67) each have a free cross-sectional area for the passage of working medium, wherein the free cross-sectional area of the impeller-side portion (67) is greater than the free cross-sectional area of the Casing side section (65).

10. Turbomachine according to one of claims 1 to 9, characterized in that the housing-channel-side guide vane channel openings (48) on a to the rotation axis (18) coaxially arranged cylinder jacket surface (56) and the Leitschaufelkanäle (42) the working medium in the middle with a flow path (60) passing through the cylinder jacket surface (56) at an intersection (63) in which the tangent (64) to the flow path (60) and the tangent (60) in a plane perpendicular to the rotation axis (18) ( 66) form an angle cd on the cylinder jacket surface (56), for which the following applies: 5 ° <a1 <20 °, preferably cd = 12 °.

1 1. Turbomachine according to one of claims 1 to 10, characterized in that the impeller-side Leitschaufelkanalöffnungen (70) on a to the rotation axis (18) coaxially arranged cylinder jacket surface (68) and run the working medium in the middle with a flow path (60), which passes through the cylinder jacket surface (68) at an intersection (72) in which the tangent (74) to the flow path (60) and the tangent (76) lying in a plane perpendicular to the axis of rotation (18) contact the cylinder jacket surface (68). form an angle o2, for which applies: 5 <a2 <20 °, preferably a2 = 12 °.

12. Turbomachine according to claim 10 or 1 1, characterized in that the impeller blades (28) have a substantially crescent-shaped cross-sectional contour and have a concave blade surface (78) extending from a Leitschaufelkanälen (42) facing first blade edge (52 ) extends to a second blade edge (54) facing away from the guide blade channels (42), wherein a tangent (80), which is disposed on the first blade edge (52) in a plane perpendicular to the axis of rotation (18), has a tangent (80) attached to the concave blade surface (78) the first blade edge (52) passing through and the rotation axis (18) perpendicularly intersecting straight line (82) forms an obtuse angle /? ΐ = β1 +90 ^ο , for which applies: 5 ° </? ΐ-90 ^ο <45 ^ο , esp - in particular 20 ° </? l-90 ° <40 °, preferably /? l-90 ° = 29 °.

13. Turbomachine according to claim 12, characterized in that in a direction perpendicular to the axis of rotation (18) plane lying on the second blade edge (54) on the concave Schaufelflä- surface (78) applied tangent (80) with a second blade edge

(54) and perpendicular to the axis of rotation (18) intersecting straight line (84) forms an acute angle /? 2: = 90 ° -β2, for which applies: 5 ° <90 -ß2 <90 °, in particular 35 <90 - / ? 2 <35 °, preferably 90? /? 2 = 40.5 °.

14. Turbomachine according to claim 13, characterized in that the obtuse angle ßl = ß1 + 90 ° and the acute angle ß2: = 90 ° - ß2 satisfy the following relationship: / Π <180 ° - /? 2, i. ß1 <ß2.

15. Turbomachine according to claim 12 to 14, characterized in that the blade surface (78) of the impeller blades (28) to the rotation axis (18) are parallel.

16. Turbomachine according to one of claims 12 to 15, characterized in that the distance r ₂ of the guide vane channels (42) facing first blade edge (52) of each impeller blade (28) of the rotation axis (18) and the distance n of the Guide vane channels facing away from the second blade edge (54) of each impeller blade (28) of the rotation axis (18) satisfies the following relationship: 70% <n / r ₂ <80%, preferably n / r ₂ * 75%.

17. Turbomachine according to one of claims 12 to 16, characterized in that the number Z of the impeller blades (28) of the impeller (16) satisfies the following relationship:

Z * C ^■ ri / r _2> wherein the distance r ₂ of the first blade edge (52) of each impeller blade (28) from the rotation axis (18) and the distance n of the second blade edge (54) of each impeller blade (28) facing away from the guide blade channels (42) ) from the axis of rotation (18) and C is a constant with 70 <C <90.

18. Turbomachine according to one of claims 12 to 17, characterized in that the distance r ₂ of the Leitschaufelkanalen (42) facing first blade edge (52) of each impeller blade (28) from the axis of rotation (18) and to the axis of rotation ( 18) parallel height (h _E ) of the first blade edge (52) of each impeller blade (28) satisfies the following relationship: 12% <h _E / r ₂ ^ 28%.

19. Turbomachine according to one of claims 1 to 18, character- ized in that the impeller (16) has an impeller blades (28) receiving impeller blade carrier (26) with a rotationally symmetrical flowable by working medium guide contour (87) having a flow path (88 ) deflects the working medium between the impeller blade channels (50) and a diffuser space (34).

20. Turbomachine according to claim 19, characterized in that the guide contour (87) in the diffuser space (34) extends.

21. Turbomachine according to claim 19 or 20, characterized in that the impeller blades (28) on the impeller blade carrier (26) are releasably fixed.

22. Turbomachine according to claim 19 or 20, characterized in that the impeller blades (28) and the impeller blade carrier (26) are materially connected.

Turbomachine according to claim 22, characterized in that the impeller blades (28) and the impeller blade carrier (26) are made by turning and / or eroding and / or milling and / or elimination of a solid material from one piece.

24. Turbomachine according to one of claims 1 to 23, characterized in that the guide vane channels (42) in the housing (12) with an annular guide vane carrier (20) received by means of a cover (36) covered helical guide vanes (22) are formed having a convex blade surface (44) facing away from the axis of rotation (18).

25. Turbomachine according to claim 24, characterized in that the guide blade carrier (20) and the guide vanes (22) are materially connected.

26. Turbomachine according to claim 24 or 25, characterized in that the guide vanes (22) have blade surfaces (44, 46) which are parallel to the axis of rotation (18).

27. Turbomachine according to claim 26, characterized in that the distance between two adjacent guide vanes (22) increases in a direction of the impeller (42) facing the flow direction for the working medium.

28. Turbomachine according to claim 27, characterized in that the height of the guide vanes (22) decreases with increasing distance from the axis of rotation (18).

29. Turbomachine according to one of claims 23 to 27, characterized in that the guide vane carrier (20) and the cover

(36) one to the housing channel (24) open and in the Leitschau- Defined felkanäle (42) opening compensating space (41) with a tapering in the direction of the axis of rotation (18) direction cross-section.

30. Turbomachine according to one of claims 24 to 29, characterized in that the guide blade carrier (20) and the guide vanes (22) are made of a one-piece pipe socket by means of eroding and / or milling and / or Elisieren.

31. Use of a turbomachine (10) designed according to one of claims 1 to 30 as a turbine in an organic Rankine

Circular process or as a compressor for compressing gaseous medium.