EP2128448B1 - Drive turbo machine for a machine line, machine line with and drive for drive turbo machine - Google Patents

Description

The present invention relates to a geared turbo machine, in particular a radial geared turbo machine, with an integrated load gear for a machine train, an integrated load gear for such a geared turbo machine, and a machine train with such a geared turbo machine and a further compressor, in particular a main compressor.

A machine train generally has a drive unit, for example a steam turbine, a gas turbine or an expander, in particular an expansion or residual gas turbine, and one or more compressors driven by this drive unit, for example for compressing air or other gases.

From internal company practice, in particular, machine trains are known in which a double-driving steam turbine drives a booster compressor with several compressor stages on one side and a main compressor on the opposite side of the steam turbine, which draws in a medium, compresses it and feeds the booster compressor with a partial mass flow thereof, which for example, compressed to one to three pressure levels.

The speeds of the steam turbine, main and booster compressor must be coordinated with each other. While the speeds of the steam turbine and the compressor stages of the booster compressor should be relatively high for thermodynamic reasons, they are lower for the main compressor - due to its large diameter and the associated high centrifugal forces - and so far limit the speed of the steam turbine in particular, with regard to its Efficiency and their size is disadvantageous.

Therefore, it is known according to in-house practice to design the booster compressor as a gear compressor, such as that from the EP 1 691 081 A2 , which is a gear compressor with an integrated gear according to the preamble of claim 1, or the DE 42 41 141 A1 is known to operate its compressor stages at higher speeds than the main compressor. Even in one of the DE 2413 674 C2 known three-stage gear compressor, the drive speed is quickly translated to higher speeds in the compressor stages.

The publication GB-A-2321502 discloses a turbocharger for a diesel engine, particularly an engine rated at 10 MW or more with a single turbine in a housing that drives a number of compressor impellers of compressors through a system, the impellers not being driven on the same shaft as the turbine but on separate waves. For example, from DE-GM 7122098 it is also known in principle to reduce the speed of a steam turbine by means of a separate spur gear in front of the main compressor, which, however, due to the separate gear, not only the manufacturing and assembly costs, but also the axial length of the machine train and thus Transportation and building costs increased. Known machine trains have further disadvantages. For example, the previous arrangement of the main compressor and booster compressor on both sides of the steam turbine requires a radial outflow from the steam turbine. This worsens the efficiency. If a condenser is connected downstream of the steam turbine, this condenser, which is fed with the radially outflowing steam, must be arranged in a horizontal plane above or below the steam turbine, which considerably increases the overall height of the entire machine train and thus, in particular, the cost of a foundation or building that accommodates it.

The object of the present invention is to reduce at least one of the aforementioned disadvantages and to improve a machine train.

This object is achieved by an integrated gear with the features of claim 1, a geared turbo machine according to claim 10 or a machine train with the features of claim 12 or 18. Advantageous further developments are the subject of the dependent claims.

According to a first aspect of the present invention, it is proposed to integrate a speed-reducing load gear, which is arranged between the drive unit and a compressor, into a gearbox of a geared turbo machine and thus to separate it from the compressor at the same time.

For this purpose, a geared turbo machine for a machine train comprises a drive pinion, which is non-rotatably connected to a drive shaft, one with the Drive pinion meshing large wheel and one or more, preferably at least two, in particular three or four turbomachine rotors. These turbomachine rotors of the geared turbomachine each comprise a turbomachine shaft, one or more, preferably two, impellers non-rotatably connected to the turbomachine shaft and a turbomachine pinion rotatably connected to the turbomachine shaft, the turbomachine pinions of one or more turbomachine rotors being in engagement with the large wheel.

An impeller of a turbomachine rotor can be designed as a compressor or expander impeller. In particular, two or more compressor impellers of the same turbomachine rotor and / or compressor impellers of different turbomachine rotors, preferably designed as radial compressors, can form compressor stages of the geared turbo machine, which acts as a geared compressor. Alternatively, two expander impellers of the same turbomachine rotor and / or expander impellers of different turbomachine rotors, preferably designed as radial expanders, can form expander stages of the geared turbomachine, which act as gear expander. Both versions can also be combined, for example in that at least one turbomachine rotor equipped with one or more compressor impellers forms one or more compressor stages and at least one other turbomachine rotor equipped with one or more expander impellers forms one or more expander stages of the same geared turbomachine, and / or in that one or more turbomachine rotors are equipped with at least one compressor and at least one expander impeller and thus form both a compressor and an expander stage. Therefore, in the present case, both pure single or multi-stage gear compressors with one or more compressor shafts equipped with at least one compressor impeller, pure single or multi-stage gear expanders with one or more expander shafts equipped with at least one expander impeller, as well as combined gear compressor / expander ("gear compander") are generalizing referred to as a geared turbo machine, its rotors equipped with compressor and / or expander impellers as a turbo machine rotor.

According to the invention, the geared turbo machine now additionally has an output pinion of a speed-reducing load gear, which is connected in a rotationally fixed manner to an output shaft for driving a compressor drive shaft, which can be coupled to this output shaft, of a further compressor, in particular a main compressor of the machine train, which is separate from the geared turbo machine and is designed, in particular, as a single-shaft compressor can, preferably as an axial compressor, radial compressor, designed for example with a horizontal and / or vertical parting line or as an isothermal compressor, or as a combined axial-radial compressor.

This output pinion is in engagement with the drive pinion like the large wheel, preferably on a side of the drive pinion opposite this. A geared turbo machine according to the invention thus combines for the first time a multi-shaft gearbox of a geared turbo machine and a load gear for a compressor separate therefrom.

An integrated gearbox, a geared turbo machine with such an integrated gearbox or a machine train according to this first aspect of the present invention has a number of advantages: by means of the speed-reducing gearbox, a drive unit, for example a steam turbine, a gas turbine or an expander, in particular a relaxation device - or residual gas turbine, which drives the drive shaft, a further compressor, in particular a main compressor, and the turbomachine rotors of the geared turbomachine are each operated in speed ranges that are favorable for them.

For example, the speed-reducing load gear can reduce a speed of the drive pinion with a gear ratio to a speed of the output pinion which is in the range from 1.25 to 1.45, preferably in the range from 1.3 to 1.4 and in particular in the range between 1.32 to 1.38. In the present case, a gear ratio is defined in the customary manner as the quotient of the drive to output speed, here here from the drive pinion speed divided by the output pinion speed, so that a reversal of the direction of rotation is also described by a positive gear ratio. A turbomachine pinion can correspondingly have a transmission ratio with the drive pinion, which is in the range from 0.28 to 0.54, preferably in the range from 0.30 to 0.52 and in particular in the range between 0.32 to 0.50, the transmission ratio resulting from the amount of the quotient of the drive pinion speed divided by the turbo-machine pinion speed.

As a result, in one embodiment, for example, a steam turbine can be operated at a nominal speed in a range from 4000 to 7000 revolutions per minute (rpm), the turbo machine rotors of a booster compressor designed as a geared turbo machine at a nominal speed in a range from 10000 to 17000 rpm, and a main compressor designed as a single-shaft compressor at a nominal speed in a range from 2000 to 6000 rpm. This increases the efficiency of the steam turbine, which can also advantageously build smaller.

The drive and output pinions form a load gear, via which a large part of the power supplied by the drive unit, which can be in the range of 40 to 80 MW for steam turbines, for example, can be transmitted to the further compressor, which for example has a power in the range between 30 to 50 MW is applied. Preferably at least half, particularly preferably at least 60% of the power is transferred from the drive shaft to the output shaft. The large wheel distributes the remaining differential power accordingly to the turbomachine rotors in mesh with it. The toothing widths of the turbomachine pinion and the large wheel can therefore advantageously be made smaller and are preferably at most 0.91 times the toothing width of the drive pinion.

Another significant advantage is that a separate gearbox is no longer required to reduce the speed of the drive unit to the speed of the additional compressor, which saves manufacturing and assembly work as well as installation space.

The further compressor is preferably accommodated in a housing which is separate from a housing of the geared turbomachine. In this way, a vibration-like decoupling between the geared turbo machine and the further compressor can be achieved particularly advantageously. For this purpose, the further compressor is preferably spaced axially from the geared turbomachine, which is particularly advantageous if the further compressor is large as the main compressor.

Due to the inventive integration of a speed-reducing load gear of a further compressor, in particular a main compressor, into a geared turbomachine, the load gear is not accommodated in the housing of the further or main compressor, which can be advantageous in terms of vibration.

As stated above, the geared turbomachine can have one or more expander stages, in that one or more turbomachine rotors are each equipped with at least one, two or more expander impellers. In this way, for example, a waste medium from the process implemented in the machine train and / or the process medium previously compressed in the main compressor, preferably a partial mass flow thereof, can be relaxed and its enthalpy can be used to drive the further compressor and / or compressor stages of the geared turbomachine. Additionally or alternatively, the geared turbo machine, which then acts as a booster compressor of the machine train, can have one or more compressor stages, in that one or more turbomachine rotors are each equipped with at least one, two or more compressor impellers. In this way, for example, the medium compressed in the further compressor, preferably a partial mass flow from the main compressor, can be further compressed in order to act as a coolant, for example after recooling and expansion. Additionally or alternatively, other media that do not flow through the further compressor can also be compressed in the compressor stages of the geared turbine machine. The geared turbo machine can thus equally act as a work machine and / or an engine, the turbo machine shafts exerting a torque on an impeller or being acted upon by a torque from the impeller.

Additionally or alternatively, an electric machine supporting the drive unit and / or drivable by the drive unit, in particular a motor, a generator or a motor / generator, can be provided, the electric machine input shaft of which engages with the drive pinion, the large wheel, the output pinion or a turbomachine pinion stands or is coupled or non-rotatably connected to the drive shaft, the output shaft, the while of the large wheel or a turbine rotor. In this way, for example, additional Drive torque is introduced into the geared turbo machine by an electric motor or the mechanical power available there is converted into electrical power in a generator and stored, for example, made available to the machine train or fed into a power grid.

If the booster compressor is flowed through by a medium that was previously compressed in the main compressor, the cross-sections through which the flow passes, and thus the housing, impeller or blading diameters of the geared turbomachine, can be made smaller due to the higher pressures and in particular when only a partial mass flow flows through from the main compressor than with the other compressor. Preferably, a smallest cross-section of the further compressor through which flow therefore has at least 1.05 times, preferably at least 1.1 times and in particular at least 1.2 times the smallest cross-section of the geared turbomachine through which there is flow.

In the present case, a non-rotatable connection, for example between the drive pinion and drive shaft, turbomachine pinion and turbomachine shaft or output pinion and output shaft, is a detachable connection, which can comprise, for example, a spline shaft and / or screws, as well as a non-detachable connection, in particular a welded connection or an integral design , understood for example as a one-piece original and / or shaped part.

A clutch between the output shaft and the separate compressor drive shaft that can be coupled with it can be realized, for example, via a flange connection, a clutch for compensating for axial and / or angular misalignment, and / or a switchable or self-switching clutch, for example an overload clutch. In this respect, both output shafts and compressor drive shafts that are connected to one another in a releasable and non-releasable manner are referred to as couplable. A coupling between the output shaft and the compressor drive shaft can advantageously dampen torsional vibrations, axial shocks or the like.

In the sense of the present invention, an engagement comprises, on the one hand, a direct engagement, ie a meshing of toothings, for example single or double helical toothings, of the two elements which are in engagement with one another. Equally, however, this also includes an indirect intervention with the interposition of one or more gear stages, in particular Includes spur gear and / or planetary gear stages, such as from the DE 42 41 141 A1 is known, the disclosure of which is expressly included in this description in this regard.

If a geared turbo machine according to the first aspect of the present invention has two or more turbo machine rotors, all turbo machine pinions can be meshed with the large wheel, which enables a more even loading of the large wheel and a narrower built geared turbo machine. Likewise, however, one or more turbomachine pinions can also be in engagement with the output pinion. This increases the distance between these turbomachine rotors and those driven by the large wheel, which advantageously increases the design freedom of the individual turbomachine rotors or the compressor and / or expander stages formed by them.

In a preferred embodiment, an axis of rotation of the drive pinion, an axis of rotation of the large wheel and an axis of rotation of the output pinion are arranged in a common, preferably substantially horizontal, plane. This advantageously reduces the overall height of the geared turbo machine perpendicular to this plane. The axis of rotation of a turbomachine pinion meshing with the large wheel and / or the axis of rotation of a turbomachine pinion meshing with the output pinion can also be arranged in this plane and thus further reduce the overall height. If further turbomachine pinions are in engagement with the large wheel, their axes of rotation are preferably arranged in a further common plane which is parallel to the plane in which the axis of rotation of the large wheel lies.

A geared turbo machine preferably has a multi-part housing which accommodates the drive pinion, the large wheel, the output pinion and the turbomachine pinion. In particular, if, as stated above, the axes of rotation lie in one or two mutually parallel, preferably horizontal planes, it is preferred that this housing is divided in this plane or these planes. This simplifies assembly and maintenance.

The output pinion and the large wheel are preferably arranged in the same transverse plane of the drive pinion. This builds the geared turbo machine advantageous axially particularly short. Similarly, the large wheel and the output pinion can also be arranged in axially offset planes, the large wheel or the drive pinion then advantageously being designed in two stages and two different pitch circle diameters for engagement with drive and turbo-machine pinions (for a two-stage large wheel) or for engagement with the large wheel and output pinion (for two-stage drive pinion). Such an arrangement can be made narrower, particularly in the plane of the axes of rotation of the drive pinion and large wheel.

Not all, but only a few, of the drive pinion, the large wheel, the turbomachine pinions and the output pinion are preferably axially mounted in a housing of the geared turbine machine, which for this purpose has, for example, two to six axial bearings. The rest of the drive pinion, the large wheel, the turbomachine pinions and the driven pinion can then be supported axially on these elements, in particular upper pressure combs, axially supported in the housing of the geared turbomachine, as is known from the DE 42 41 141 A1 are known, the disclosure of which is expressly included in this description in this regard. As a result, the axial thrust of the impellers or the drive unit can be absorbed with less structural effort.

In a machine train according to the invention, the further compressor can be arranged particularly advantageously on the side of the geared turbo machine opposite the drive unit. In this way in particular, it is possible to design the drive unit, which is thus free on the side opposite the geared turbomachine, as a steam turbine with an axial outflow. In contrast to conventional machine trains with steam turbines with radial outflow, this not only improves the efficiency. A condenser connected downstream of the steam turbine can also be arranged essentially on the same horizontal plane, which significantly reduces the overall height of such a machine train. Therefore, according to a second aspect of the present invention, in the case of a machine train with a geared turbo machine and a further compressor, in particular a main compressor, a steam turbine with axial outflow is provided as the drive unit. The above-explained first and second aspects of the present invention according to claims 1, 10 and 12 and 18 respectively solve the aforementioned Task to improve a machine train. Both aspects are particularly advantageously combined with one another, but this is not mandatory.

Fig. 1:

einen Maschinenstrang mit einer Getriebeturbomaschine mit integriertem Getriebe nach einer ersten Ausführung der vorliegenden Erfindung in einer Draufsicht von oben;

Fig. 2:

einen Maschinenstrang mit einer Getriebeturbomaschine mit integriertem Getriebe nach einer zweiten Ausführung der vorliegenden Erfindung in einer Draufsicht von oben;

Fig. 3A:

eine Getriebeanordnung der Getriebeturbomaschine nach Fig. 1 in axialer Ansicht;

Fig. 3B:

die Getriebeanordnung nach Fig. 3A in der Draufsicht von oben;

Fig. 4A:

eine Getriebeanordnung der Getriebeturbomaschine nach Fig. 2 in axialer Ansicht;

Fig. 4B:

die Getriebeanordnung nach Fig. 4A in der Draufsicht von oben;

Fig. 5:

eine Getriebeanordnung einer Getriebeturbomaschine mit integriertem Getriebe nach einer dritten Ausführung der vorliegenden Erfindung in der Draufsicht von oben;

Fig. 6:

eine Getriebeanordnung einer Getriebeturbomaschine mit integriertem Getriebe nach einer vierten Ausführung der vorliegenden Erfindung in der Draufsicht von oben; und

Fig. 7:

eine Getriebeanordnung einer Getriebeturbomaschine mit integriertem Getriebe nach einer fünften Ausführung der vorliegenden Erfindung in der Draufsicht von oben.

In the following, therefore, both aspects are explained together using exemplary embodiments of the present invention which makes use of both aspects, it being expressly emphasized that the present invention necessarily only has at least the features of the first or second aspect. Further features and advantages of both aspects result accordingly from the subclaims and these exemplary embodiments. Here shows, partly schematically:

Fig. 1:

a machine train with a geared turbo machine with integrated gear according to a first embodiment of the present invention in a plan view from above;

Fig. 2:

a machine train with a geared turbo machine with integrated gear according to a second embodiment of the present invention in a plan view from above;

Fig. 3A:

a gear arrangement of the geared turbo machine Fig. 1 in axial view;

3B:

the gear arrangement after Figure 3A in top view from above;

4A:

a gear arrangement of the geared turbo machine Fig. 2 in axial view;

4B:

the gear arrangement after Figure 4A in top view from above;

Fig. 5:

a gear arrangement of a geared turbo machine with integrated gear according to a third embodiment of the present invention in plan view from above;

Fig. 6:

a gear arrangement of a geared turbo machine with integrated gear according to a fourth embodiment of the present invention in plan view from above; and

Fig. 7:

a gear arrangement of a geared turbo machine with integrated gear according to a fifth embodiment of the present invention in a plan view from above.

Fig. 1 , 3rd show the essential elements of a machine train according to a first embodiment of the present invention, in which the first and second aspects of the present invention are realized together.

First referring to Fig. 1 4 denotes a main compressor designed as an axially suction single-shaft compressor, which draws air in the manner indicated by an arrow and compresses it to, for example, 7 bar.

A partial mass flow of this compressed air is then fed in a manner not shown to a first turbomachine rotor 3.10 of a booster compressor, which is designed as a geared turbomachine 2 explained in more detail below.

The first turbomachine rotor 3.10 comprises two compressor impellers 3.12, 3.13 (indicated by triangles) Figure 3B ), which sit on a common turbomachine shaft and rotate in spiral housings (not shown) in order to further compress the air supplied by the main compressor, and thus form two compressor stages of the booster compressor 2. From these, the air then becomes a second turbomachine rotor 3.20 of the booster compressor in a manner not shown in any more detail 2 supplied, the two compressor impellers 3.22, 3.23 (also indicated as triangles ( Figure 3B ) have a smaller diameter and rotate faster than the impellers of the first turbomachine rotor 3.10 in order to further compress the air and thus form two further compressor stages of the booster compressor 2. The air which is further compressed therein is then fed to a third turbomachine rotor 3.30 of the booster compressor 2, the two compressor impellers 3.32, 3.33 ( Figure 3B ) have a further smaller diameter and rotate faster than the impellers of the second turbomachine rotor 3.20 in order to finally compress the air to a desired final pressure of 75 bar and thus form two further compressor stages of the six-stage booster compressor 2. Incidentally, three turbo machine rotors 3.10, 3.20 and 3.30 of the booster compressor 2 are structurally analogous.

As in 3A, 3B Shown in more detail in an axial or plan view from above, the turbomachine shafts of the three turbomachine rotors 3.10, 3.20 and 3.30, on which the impellers 3.12 and 3.13, 3.22 and 3.23 or 3.32 and 3.33 are seated, one turbo machine sprocket 3.11, 3.21 or 3.31 connected in a rotationally fixed manner, for example cut onto the turbo machine shaft or attached to it as a separate sprocket via a shaft-hub connection. All three turbo machine pinions 3.11, 3.21 and 3.31 mesh with a common large wheel 2.2 of the booster compressor 2, which is thus designed as a multi-shaft compressor. In order to achieve the different speeds of the three turbo machine rotors, the turbo machine pinion 3.11 of the first, slowest rotating turbo machine rotor 3.10 has the largest diameter, the turbomachine pinion 3.31 of the third, fastest rotating turbomachine rotor 3.30 the smallest diameter. Of course, in a modification of the exemplary embodiment, more, for example four or five turbomachine rotors, each with one, two or more impellers, are also possible.

The large wheel 2.2 is in turn driven by a drive pinion 2.1 of smaller diameter, which is rotatably fixed in a manner not shown with a drive shaft of a steam turbine 1 ( Fig. 1 ) or another drive unit, for example a gas turbine or an expander, is connected so that the turbine speed is rapidly translated to the turbomachine shafts of the three turbomachine rotors with different transmission ratios.

According to the first aspect of the present invention, in the same horizontal plane, in which the axes of rotation of the drive pinion 2.1, the large wheel 2.2 and the turbo machine pinion 3.11 are also arranged, the axis of rotation of an output pinion 2.3 is arranged, which is connected to the drive pinion 2.1 on the large wheel 2.2 opposite side is engaged. Drive pinion 2.1, large gear 2.2 and output pinion 2.3 are in the same transverse plane (plane of the Figure 3A ) arranged so that the same toothing of the drive pinion 2.1 meshes with both the large gear 2.2 and the output pinion 2.3. As in Figure 3B schematically indicated, due to the different torque flows, the tooth width of the turbo machine pinion 3.11, 3.21, 3.31 is smaller than that of the input and output pinion 2.1, 2.3.

The diameter of the driven pinion 2.3 is larger than the diameter of the driving pinion 2.1, so that the speed of the steam turbine 1, which drives the driving pinion 2.1 seated on its drive shaft, onto the driven shaft with the driven pinion 2.3 is slowed down. The output shaft with the output pinion 2.3 is by a in Fig. 1 indicated coupling with a compressor drive shaft 4.1 of the main compressor 4 designed as a single-shaft compressor ( Fig. 1 ) connected, so that the turbine drives it with a reduction in the slow. Input and output pinions 2.1, 2.3 thus form a speed-reducing load gear, via which the majority of the turbine power is transferred to the main compressor 4.

Due to the reduction or translation of the turbine or drive pinion speed to the slower output pinion speed or faster turbo machine pinion speeds, steam turbine 1, booster compressor 2 and main compressor 4 can be operated simultaneously in optimal speed ranges. In particular, the speed of the steam turbine 1 can be higher with a lower main compressor speed, which improves the efficiency of the steam turbine 1 and allows the use of smaller, faster rotating steam turbines. Due to the design as an integral gearbox, a separate load gearbox is advantageously not required for this; the machine train and foundation can be kept more compact in terms of construction.

Input and output pinions 2.1, 2.3, the large gear 2.2 and the engaging turbo machine pinions 3.11, 3.21 and 3.31 are accommodated in a common housing (not shown). This three-part housing is in the Figure 3A Dash-dotted plane, in which the axes of rotation of the input and output pinions 2.1, 2.3, large gear 2.2 and turbo machine pinion 3.11 lie, horizontally divided, so that they can be easily mounted in a first, lower housing part on which a second, middle housing part is put on.

The axes of rotation of the turbomachine pinions 3.21, 3.31 of the second and third turbomachine rotors 3.20 and 3.30 lie in one Figure 3A dash-dot indicated further horizontal plane, which is parallel to the plane in which the axes of rotation of the input and output pinions 2.1, 2.3, large wheel 2.2 and turbo machine pinion 3.11 lie. The housing is also divided horizontally in this plane, so that the turbomachine pinions 3.21, 3.31 can be mounted in the middle housing part in a simple manner after the middle housing part has been put in place. on which a third, upper housing part is placed. The arrangement of both turbo machine pinions 3.21, 3.31 in the further horizontal plane vertically above the plane of the input, output pinion and large wheel axis of rotation advantageously means that no installation space is required below the large wheel 2.2 for the arrangement of turbo machine rotors.

The main compressor 4 has a housing which is separate from the booster compressor 2 and is connected to it only via the compressor drive shaft 4.1. The two housings of the main compressor and the booster compressor, which for example rest on a concrete or metal foundation (not shown), can thus be largely decoupled in terms of vibration technology.

As especially in Fig. 1 Recognizable, the steam turbine 1 drives the booster compressor 2 and the main compressor 4 arranged on the opposite side with only one drive shaft. In contrast to the previous double-driving turbines, such a steam turbine with only one end of the shaft advantageously has other natural frequencies or critical speeds - in particular, the area between neighboring natural frequencies or critical speeds, from which a sufficient distance should be kept during operation, to avoid resonance problems avoid, advantageously enlarged and thus the permissible operating range can be expanded.

The arrangement of the booster compressor 2 and the main compressor 4 on the same side of the steam turbine 1 enables an in Fig. 1 axial outflow indicated by an arrow from the steam turbine 1 to the opposite side of the main compressor 4 and the booster compressor 2 (to the left in Fig. 1 ) according to the second aspect of the present invention. This advantageously improves the efficiency of the steam turbine 1.

The axial exhaust steam from the steam turbine 1 flows into one of these condensers (not shown). In contrast to conventional machine trains, in which the booster compressor and main compressor are arranged on both sides of the steam turbine, which can cause a radial outflow and thus an arrangement of a downstream condenser in the vertical direction above or below the level of the steam turbine and accordingly a two-storey foundation structure with a corresponding vertical height the capacitor of a machine train according to the second aspect of the present invention, due to the axial outflow of the steam turbine 1, are arranged essentially on the same horizontal plane as this. This advantageously enables a one-storey structure of the machine train, which leads to considerable cost savings due to the more compact foundation and the lower construction and thus building height. The arrangement of the axes of rotation of the input and output pinions, the large wheel and the turbomachine pinion in the same or in a further horizontal plane arranged parallel to this, advantageously also contributes to this.

The Fig. 2 , 4th show in Fig. 1 , 3rd corresponding illustration, the essential elements of a machine train according to a second embodiment of the present invention, which essentially coincides with the first embodiment and in which the first and second aspects of the present invention are also realized together. Elements that correspond to the first embodiment are identified by identical reference numerals, so that in this respect reference is made to the above explanations of the essentially identical first embodiment and only the differences between the first and second embodiments are discussed below.

As in Fig. 2 indicated by an arrow, the main compressor 4 sucks radially in the second embodiment. The booster compressor 2 of the second embodiment differs from the booster compressor 2 of the first embodiment in the arrangement of the second and third turbomachine rotors 3.20, 3.30. While the axes of rotation of their turbomachine pinions 3.21, 3.31, as in Figure 3A shown, lie in a common further horizontal plane, which is parallel to the plane of the axes of rotation of the input, output pinion and large wheel, are inferior in the second embodiment Fig. 4 only the turbomachine pinions 3.11, 3.21 of the first and second turbomachine rotors 3.10, 3.20 mesh with the large wheel 2.2, the turbomachine pinions 3.11, 3.21 of the first and second turbomachine rotors 3.10, 3.20 and the drive pinion 2.1 in the circumferential direction preferably offset by 90 ° each the large wheel 2.2, ie the axis of rotation of the second turbomachine pinion 3.21 is horizontal between the axes of rotation of the drive pinion 2.1 and the turbomachine pinion 3.11 of the first turbomachine rotor and vertically above the common horizontal plane of input, output pinion 2.1, 2.3, large gear 2.2 and turbo machine pinion 3.11. In this common horizontal plane of the axes of rotation of the input, output pinion 2.1, 2.3, large gear 2.2 and turbomachine pinion 3.11 is the axis of rotation of the turbomachine pinion 3.31 of the third turbomachine rotor 3.30, which is in engagement with the output pinion 2.1 on the side of the output pinion 2.3, so that it is driven by the drive pinion 2.1 not via the large wheel 2.2, but via the output pinion 2.3.

As in the first embodiment, the interposition of large wheel 2.2 or output pinion 2.3 can maintain the direction of rotation of the drive shaft in the turbomachine shafts, but can be reversed in the output shaft. If it is advantageous, the direction of rotation can of course also be oriented differently by interposing further gear stages between the input and output pinion, large wheel and / or turbo machine pinion. In particular, it is possible to design the turbomachine pinion as ring gears of a planetary gear which drives the turbomachine shaft, as is shown in FIG DE 42 41 141 A1 is described, the disclosure of which is expressly included in the present description.

Fig. 5 shows In Figure 3B , 4B Corresponding representation of the essential elements of a gear arrangement of a geared turbo machine with an integrated gear according to a third embodiment of the present invention, which essentially corresponds to the first and second embodiments and in which the first and second aspects of the present invention are also realized jointly. Elements corresponding to the first and second versions are identified by identical reference numerals, so that reference is made to the above explanations regarding the essentially identical first and second versions and only the differences between the first, second and third versions are discussed below.

In the third embodiment, the first turbomachine rotor 3.10 is replaced by an electric machine input shaft 5.1, which is connected to an electric machine 5, for example an electric motor or generator, via a clutch. The electric machine input shaft 5.1 has an electric machine pinion 2.4, which engages with the large wheel 2.2 instead of the turbo machine pinion 3.11. By appropriate selection of the gear ratios between the electrical machine pinion 2.4 and the large wheel 2.2, for example, a higher speed of the drive pinion 2.1 can be reduced to a lower speed of the electrical machine pinion, which is - depending on a mains frequency - for example 3000 or 3600 rpm.

If the electric machine 5 is designed as a generator or motor / generator, mechanical power of the steam turbine 1, which is not required to drive the main compressor 4 and the compressor stages of the geared turbine machine 2, can be converted into electrical energy and fed into a power supply network, for example.

If the electric machine 5 is designed as a motor or motor / generator, conversely, additional torque for driving the main compressor 4 and the compressor stages of the geared turbo machine 2 can be fed into the geared turbo machine 2.

This is another difference from the first and second embodiments explained above in the third embodiment Fig. 5 one impeller of the third turbomachine rotor 3.30 is designed as an expander impeller 3.34, the other as in the first and second embodiment as a compressor impeller 3.33, which is In Fig. 5 is indicated by triangles in the same direction. The geared turbo machine 2 thus has five compressor stages and one expander stage and at the same time acts as a working machine and as an engine (compander). While in the compressor stages a partial mass flow of the air compressed in the main compressor 4 is further compressed, a medium, for example a residual gas arising in the process, can be relaxed in the expander stage of the expander impeller 3.34 and thus additional torque for driving the main compressor 4 and the compressor stages of the geared turbine engine 2 in the geared turbo machine 2 are fed.

Fig. 6 shows in Fig. 5 Corresponding representation of the essential elements of a gear arrangement of a geared turbomachine with an integrated gear according to a fourth embodiment of the present invention, which essentially corresponds to the third embodiment and in which the first and second aspects of the present invention are also realized jointly. With the third version Matching elements are identified with identical reference numerals, so that in this respect reference is made to the above explanations for the essentially identical third embodiment and only the differences between the third and fourth embodiments are discussed below.

In the third embodiment, the turbomachine pinions 3.21, 3.31 of the second and third turbomachine rotors 3.20, 3.30 both mesh with the large wheel 2.2 and their axes of rotation are arranged in a common horizontal plane, in which a dividing or separating joint of the housing of the geared turbomachine 2 is also arranged In the fourth embodiment, only the turbomachine pinion 3.21 of the turbomachine rotor 3.20 meshes with the large gear 2.2, while the turbomachine pinion 3.31 of the turbomachine rotor 3.30, which carries a compressor impeller 3.33 and an expander impeller 3.34, is in engagement with the output pinion 2.3, as is also the case in the second version (cf. Figure 4B ) the case is.

Fig. 7 shows In Flg. 6 corresponding representation, the essential elements of a gear arrangement of a geared turbomachine with an integrated gear according to a fifth embodiment of the present invention, which essentially corresponds to the fourth embodiment and in which the first and second aspects of the present invention are also realized jointly. Elements that correspond to the fourth embodiment are identified by identical reference numerals, so that in this respect reference is made to the above explanations of the fourth embodiment, which is essentially identical in construction, and only the differences between the fourth and fifth embodiments are discussed below.

In addition to the turbomachine rotor 3.20, whose turbomachine pinion 3.21 is in engagement with the large gear 2.2, and the turbomachine rotor 3.30, whose turbomachine pinion 3.31 is in engagement with the output pinion 2.3, is the fifth embodiment Fig. 7 a further turbomachine rotor 3.10 is provided with two compressor impellers 3.12, 3.13, the turbomachine pinion 3.11 of which engages with the electric machine pinion 2.4 on the side opposite the large wheel 2.2.

As a further difference from the fourth embodiment explained above, in the fifth embodiment according to Fig. 7 both impellers 3.34, 3.35 of the third turbomachine rotor 3.30 trained as expander impellers, which in Fig. 7 is indicated by triangles opposite to the compressor impellers 3.12, 3.13, 3.21 and 3.22. The geared turbo machine 2 thus has four compressor stages and two expander stages and also acts as a compander. While a partial mass flow of the air compressed in the main compressor 4 is further compressed in the compressor stages, a medium, for example a residual gas arising in the process, can be relaxed in the expander stages and thus additional torque for driving the main compressor 4 and the compressor stages of the geared turbo machine 2 into the geared turbo machine 2 be fed.

As with the second version after Fig. 2 , 4th the axes of rotation of the turbomachine pinions 3.11, 3.31, the electric machine pinion 2.4, the large wheel 2.2, the drive pinion 2.1 and the output pinion 2.3 are preferably all in the same horizontal division plane of the housing of the geared turbomachine 2.

As with the embodiments described above, some or all of the compressor impellers of the geared turbomachine 2 can compress medium, preferably a partial mass flow thereof, that has flowed through the main compressor, or another medium, for example another process gas. The geared turbo machine 2 can also compress different media with its different compressor impellers.

As in the previous versions, the steam turbine, main compressor and the turbomachine rotors of the geared turbomachine can each be operated in optimal speed ranges, which can be coordinated with one another by appropriate selection of the ratios in the gearbox of the geared turbomachine 2 and the load gear 2.1, 2.3. In particular, the steam turbine can rotate faster due to the coupling with the slower rotating main compressor 4 via the speed-reducing load transmission, so that its efficiency improves and smaller steam turbine sizes can be used.

The integration of the load gear in the geared turbo machine 2 advantageously means that no separate load gear is required, which leads to a more compact machine train and less manufacturing and assembly work. Because of the main compressor housing, which is separate from this, it is partially vibration-related Decoupling of main compressor and geared turbo machine possible.

Due to the axial outflow of the steam turbine, which only drives to one side facing away from the outflow, it is possible to arrange a downstream condenser essentially on the same horizontal plane as the steam turbine 1, which is in contrast to conventional two-storey machine trains in which the condenser is arranged vertically below the radially outflowing steam turbine, advantageously allows a single-story machine train structure and thus more compact foundations and buildings to accommodate such a train.

The invention was explained above using a machine train with a steam turbine as the drive unit. However, other turbomachines, in particular a gas turbine or an expander such as a relaxation or residual gas turbine, can equally be used.

Reference symbol list

1

Steam turbine

2nd

Booster compressor

2.1

Drive pinion

2.2

Big wheel

2.3

Output pinion

2.4

Electric machine pinion

3.10, 3.20, 3.30

Turbo machine rotor

3.11, 3.21, 3.31

Turbo machine pinion

3.12, 3.13, 3.22, 3.23, 3.32, 3.33

Compressor impeller

3.34, 3.35

Expander wheel

4th

Single compressor (main compressor)

4.1

Compressor drive shaft

5

Electric machine

5.1

Electric machine shaft

Claims (22)

1. An integrated transmission for a transmission turbo machine (2) of a machine train, having a drive pinion (2.1), which is non-rotatably connected to a driveshaft;
   a bull gear (2.2) that is in mesh with the drive pinion; and at least one turbo machine rotor (3.10, 3.20, 3.30) having a turbo machine shaft for the torque transmission having at least one impeller (3.12, 3.13, 3.22, 3.23, 3.32, 3.33, 3.34) of the transmission turbo machine, and
   a turbo machine pinion (3, 11, 3.21, 3.31) that is non-rotatably connected to the turbo machine shaft and in mesh with the bull gear;
   wherein an output pinion (2.3) of a rotational speed step-down power transmission is in mesh with the drive pinion (2.1), which is non-rotatably connected to an output shaft for driving a compressor driveshaft (4.1) that can be coupled to the output shaft, of a further compressor (4) separated from the transmission turbo machine, in particular of a main compressor of the machine train, characterized in that the further compressor (4) can be coupled on the side of the transmission turbo machine (2) located opposite the drive unit (1) and an axis of rotation of the drive pinion (2.1), of the bull gear (2.2), at least of one turbo machine pinion (3.11; 3.21; 3.31) and of the output pinion (2.3) are substantially arranged in a common horizontal plane and the bull gear (2.2) and the output pinion (2.3) are arranged in a common transversal plane of the drive pinion (2.1).
2. The integrated transmission according to Claim 1, characterized in that it comprises at least two, in particular three or four turbo machine rotors (3.10, 3.20, 3.30) each with a turbo machine shaft and a turbo machine pinion (3.11, 3.21, 3.31) that is non-rotatably connected to this turbo machine shaft, wherein a turbo machine pinion (3.11, 3.21, 3.31) of at least one turbo machine rotor (3.10, 3.20, 3.30) is in mesh with the bull gear (2.2) and/or a turbo machine pinion (3.31) of a turbo machine rotor (3.30) is in mesh with the output pinion (2.3).
3. The integrated transmission according to any one of the preceding claims, characterized in that it comprises a multi-part housing which receives the drive pinion (2.1), the bull gear (2.2), the output pinion (2.3) and the at least one turbo machine pinion (3.11, 3.21, 3.31), wherein the housing is split in a plane in which an axis of rotation of the drive pinion, of the bull gear, of a turbo machine pinion and/or of the output pinion are arranged.
4. The integrated transmission according to any one of the preceding claims, characterized in that at least one of the drive pinion, the bull gear, the turbo machine pinions and the output pinion is axially mounted in a housing of the transmission turbo machine and at least on other one of the drive pinion, the bull gear, the turbo machine pinions and the drive pinion supports itself axially on the one of the drive pinion, the bull gear, the turbo machine pinions and the output pinion that are axially mounted in the housing of the transmission turbo machine, in particular via a thrust cone.
5. The integrated transmission according to any one of the preceding claims, characterized in that the rotational speed step-down power transmission reduces a rotational speed of the drive pinion (2.1) with a transmission ratio (i2.1/2.3) to a rotational speed of the output pinion (2.3), which is in the range from 1.25 to 1.45, preferentially in the range from 1.3 to 1.4 and in particular in the range between 1.32 to 1.38, wherein the transmission ratio (i2.1/2.3) is defined as quotient of drive pinion rotational speed divided by output pinion rotational speed.
6. The integrated transmission according to any one of the preceding claims, characterized in that a turbo machine pinion (3.11, 3.21, 3.31) with the drive pinion (2.1) has a transmission ratio (i2.1/3.n1), which is in the range from 0.28 to 0.54, preferentially in the range from 0.30 to 0.52 and in particular in the range between 0.32 to 0.50, wherein the transmission ratio (i2.1/3.n1) is defined as quotient of drive pinion rotational speed divided by turbo machine pinion rotational speed.
7. The integrated transmission according to any one of the preceding claims, characterized in that a teeth width of the drive pinion (2.1) amounts to at least 1.1 times the teeth width of the bull gear (2.2).
8. A transmission turbo machine (2) for a machine train having an integrated transmission according to any one of the preceding claims, characterized in that at least one impeller (3.12, 3.13, 3.22, 3.23, 3.32, 3.33, 3.34) of a compressor or expander stage of the transmission turbo machine is non-rotatably connected to a turbo machine shaft of a turbo machine rotor (3.10, 3.20, 3.30).
9. The transmission turbo machine according to Claim 8, characterized in that an impeller (3.12, 3.22, 3.32) of a compressor or expander stage of the transmission turbo machine and a further impeller (3.13, 3.23, 3.33, 3.34) of a compressor or expander stage of the transmission turbo machine is non-rotatably connected to at least one turbo machine shaft of a turbo machine rotor (3.10, 3.20, 3.30).
10. A machine train having a drive unit, in particular a steam turbine (1), a gas turbine or an expander, having a transmission turbo machine (2) according to any one of the preceding Claims 8 to 10, and having a further compressor (4) in particular a main compressor separated from the transmission turbo machine, which is spaced apart from the transmission turbo machine (2) in the axial direction.
11. The machine train according to Claim 10, characterized in that the further compressor is a single-shaft compressor formed in particular as axial compressor, radial compressor, preferentially with horizontal and/or vertical split joint, radial isothermal compressor or combined axial-radial compressor.
12. The machine train according to any one of the preceding Claims 10 to 11, characterized in that the further compressor (4) is received in a housing that is separated from a housing of the transmission turbo machine (2).
13. The machine train according to any one of the preceding Claims 10 to 12, characterized in that the transmission turbo machine is formed as booster compressor having at least one compressor stage, which is maximally supplied with a part mass flow of medium compressed by the main compressor and/or a medium not compressed by the main compressor.
14. The machine train according to any one of the preceding Claims 10 to 13, characterized in that a smallest flowed-through cross section of the further compressor is at least 1.05 times, preferentially at least 1.1 times and in particular at least 1.2 times the smallest flowed-through cross section of the transmission turbo machine.
15. The machine train according to any one of the Claims 10 to 14, characterized in that the further compressor (4) is arranged on the side of the transmission turbo machine (2) located opposite the drive unit (1).
16. The machine train, in particular according to any one of the Claims 10 to 15, having a steam turbine (1), a transmission turbo machine (2), and a separate further compressor (4), in particular a main compressor, characterized in that the steam turbine (1) has an axial outflow.
17. The machine train according to Claim 16, characterized in that the steam turbine and a condenser connected downstream of the steam turbine are substantially arranged on the same horizontal plane.
18. The machine train according to any one of the Claims 10 to 17, characterized in that in nominal operation at least 50 %, preferentially at least 60 % of the output is transmitted from the driveshaft to the driveshaft.
19. The machine train according to any one of the Claims 10 to 18, characterized in that it comprises a driving electric machine (5), in particular a motor or a motor/generator, and/or a drivable electric machine, in particular a generator or a motor/generator with an electric machine input shaft (5.1), which is in mesh, non-rotatably connected or coupled to the drive pinion (2.1), the bull gear (2.2), the output pinion (2.3) or a turbo machine pinion (3.11).
20. The machine train according to Claim 19, characterized in that the electric machine input shaft (5.1) has an electric machine pinion (2.4) which is in mesh with the bull gear (2.2) and/or a turbo machine pinion (3.31) of a turbo machine rotor.
21. The machine train according to the preceding Claims 19, characterized in that it comprises a multi-part housing which receives the drive pinion (2.1), the bull gear (2.2), the output pinion (2.3), at least one turbo machine pinion (3.11, 3.21, 3.31) and the electric machine pinion (2.4), wherein the housing is split in a plane in which an axis of rotation of the drive pinion, of the bull gear, of a turbo machine pinion, of the electric machine pinion and/or of the output pinion are arranged.
22. The machine train according to any one of the preceding Claims 20 to 21, characterized in that at least one of the drive pinion, the bull gear, the turbo machine pinions, the electric machine pinion and the output pinion is axially mounted in a housing of the transmission turbo machine and at least one other one of the drive pinion, the bull gear, the turbo machine pinions, the electric machine pinion and the output pinion supports itself axially on the one of the drive pinion, the bull gear, the turbo machine pinions, the electric machine pinion and the output pinion axially mounted in the housing of the transmission turbo machine, in particular by way of a thrust cone.

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