TURBINE

Abstract

The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which is provided with a fuel injection means (7) and an ignition device (8) and which supplies the turbine with a combustion gas. An external compressor (3) is associated with the turbine. Said compressor has a separate electric drive and is not connected to the turbine by means of a drive shaft. Furthermore, at least two combustion chambers (5) are provided for discontinuous, pulsed combustion and supply of the turbine.

Claims

1. A turbine, in particular a combustion gas turbine, which has at least one combustion chamber (6) provided with a fuel injection means (7) and an ignition device (8), which supplies the turbine with a combustion gas in order to drive a high-speed generator (2) for generating current, characterized in that the turbine or the combustion chamber (6) is assigned at least one external compressor (3) which is provided with its own electric drive and which is not connected by a drive shaft to the turbine and that at least two combustion chambers (5) are provided for discontinuous pulsed combustion or supply of the turbine.

2. The turbine according to claim 1, characterized in that the electric drive is a controllable high-speed electric drive (4).

3. The turbine according to claim 1, characterized in that preferably up to six combustion chambers (5) are provided.

4. The turbine according to claim 1, characterized in that the combustion chambers (5) are preferably arranged uniformly spaced apart from one another on the circumference of the turbine.

5. The turbine according to claim 1, characterized in that the compressor (3) is configured as a double compressor.

6. The turbine according to claim 1, characterized in that a second external compressor (9) is provided, which is provided with its own controllable high-speed electric drive (10).

7. The turbine according to claim 1, characterized in that the compressor flow of the compressor(s) (3, 9) can be supplied to the impeller of the turbine via a divided conducting device independently of one another.

8. The turbine according to claim 1, characterized in that the turbine is connected to a counterflow heat exchanger (11) through which the waste gas flow of the turbine is guided.

9. The turbine according to claim 1, characterized in that the counterflow heat exchanger (11) is connected to a second external compressor (9) in such a manner that in compressor mode the thermal energy of the waste gas flow is transferred to the compressor air of the second compressor (9).

10. The turbine according to claim 1, characterized in that a second external compressor (9) is provided which is connected to the controllable high-speed electric drive (4) of the first compressor (9).

11. The turbine according to claim 2, characterized in that an inverter with an intermediate circuit is provided for controlling or regulating the high-speed electric drive (4, 10).

12. The turbine according to claim 1, characterized in that the compressors (3, 9) are configured to be controllable independently of one another by means of a control unit and the turbine is controlled according to an efficiency curve.

13. A method for operating a turbine according to claim 1 by means of pulsed and approximately isochoric combustion of a fuel in combustion chambers (5) in adjustable time intervals, wherein a turbine wheel (12) of the turbine is supplied by two separate compressor air flows and thermal energy of a waste gas flow is returned directly into the turbine and the turbine is controlled according to an efficiency curve.

14. The turbine according to claim 2, characterized in that preferably up to six combustion chambers (5) are provided.

15. The turbine according to claim 2, characterized in that the combustion chambers (5) are preferably arranged uniformly spaced apart from one another on the circumference of the turbine.

16. The turbine according to claim 3, characterized in that the combustion chambers (5) are preferably arranged uniformly spaced apart from one another on the circumference of the turbine.

17. The turbine according to claim 2, characterized in that the compressor (3) is configured as a double compressor.

18. The turbine according to claim 3, characterized in that the compressor (3) is configured as a double compressor.

19. The turbine according to claim 4, characterized in that the compressor (3) is configured as a double compressor.

20. The turbine according to claim 2, characterized in that a second external compressor (9) is provided, which is provided with its own controllable high-speed electric drive (10).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In the figures:

[0030] FIG. 1 shows a first embodiment of a turbine according to the invention,

[0031] FIG. 2 shows a second embodiment of the turbine according to the invention,

[0032] FIG. 3 shows a combustion chamber of the turbine according to the invention and

[0033] FIG. 4 shows a conducting device for the compressor air.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0034] FIG. 1 shows a turbine according to the invention for the example of an axial combustion gas turbine 1 for driving a high-speed generator 2 having two external compressors 3, 9. The compressors 3, 9 are not connected by a shaft or the like to the axial combustion gas turbine 1 but are provided with their own controllable high-speed electric drive 4.

[0035] Another feature is the non-continuous combustion by means of a plurality of combustion chambers 5 which are arranged so that their outflow nozzles 6 are aligned directly onto the turbine wheel 12, i.e. the turbine blades of the turbine wheel 12 are supplied parallel to the axis of rotation 16. At least two combustion chambers 5 are arranged but preferably in the example described six combustion chambers 5 which are arranged uniformly spaced apart from one another on the circumference of the axial combustion gas turbine 1 (FIG. 4).

[0036] Each combustion chamber 5 is provided with a fuel injection means 7, an ignition device 8 and an outflow nozzle 6. Fuel is injected into the combustion chamber 5 in a gaseous or liquid manner and brought to explode by means of the ignition device 8. As a result, an approximately isochoric combustion is achieved. The outflow nozzle 6 at the outlet of the combustion chamber 5 converts the generated pressure into a flow rate by means of which the turbine wheel 12 is supplied.

[0037] The combustion chambers 5 are successively brought to ignition by means of a controller not shown explicitly. In order to control the power of the axial combustion gas turbine 1, the frequency of the ignition sequence can be adjusted and regulated by means of the electronic controller.

[0038] In order to increase the turbine efficiency, the thermal energy of the waste gas flow is returned directly into the axial combustion gas turbine 1 by means of the second compressor 9 which is coupled to the first compressor 3 via a counterflow heat exchanger 11. The return into the axial combustion gas turbine 1 is made possible by a fluidically divided conducting device 17 upstream of the turbine wheel 12.

[0039] The turbine wheel 12 is supplied by two separate compressor air flows. The combustion energy is supplied to the air flow from the first compressor 3 and the energy from the waste gas flow is supplied to the air flow from the second compressor 9. The thermal energy from the waste gas flow is transferred via the counterflow heat exchanger 11 to the compressor air of the second compressor 9 and the axial combustion gas turbine 1.

[0040] Pipelines for flowing gases are shown in simplified form and giving the flow direction (arrow direction).

[0041] The second compressor 9 is required for use of the waste gas heat. However, it is also conceivable that the compressor air is divided by a compressor. There are also two-stage compressors. The separate compressor drives are a preferred variant since an efficient control of the turbine is thereby possible.

[0042] An axial combustion gas turbine 1 with external compressor is not known from the prior art. As a result of the external compressor or compressors 3, 9, the axial combustion gas turbine 1 can be started with compressor air and the rotational speed of the axial combustion gas turbine 1 can be efficiently influenced and delimited.

[0043] In contrast to the first embodiment according to FIG.

[0044] 1, FIG. 2 shows a variant in which the second external compressor 9 is provided with its own controllable high-speed electric drive 10. The separate compressor drives form a preferred variant since a more efficient control of the axial combustion gas turbine 1 is thereby possible.

[0045] FIG. 3 shows details of the combustion chamber 5 and a conducting device 17 surrounding it. The combustion chamber 5 is in this case integrated into a pre-chamber 15. The compressor air 14 flows permanently through the pre-chamber 15 and drives the turbine wheel 12. Fuel is injected into the combustion chamber 5 via the fuel nozzle 8 and brought to explode by the ignition device 7. The expansion discharges through the outflow nozzle 6 directly into a channel 13 (nozzle effect) of the conducting device 17 and additionally drives the turbine wheel 12.

[0046] In the axial combustion gas turbine 1 according to the invention, the plurality of combustion chambers 5 are arranged so that they are always successively brought to ignition in the same sequence, in adjustable time intervals. The sequences in the combustion chamber such as the injection quantity and the ignition time are variably controllable. The time intervals between the ignitions of the individual combustion chambers are also variably controllable. The power of the turbine is regulated by the variable injection quantity and the combustion chamber ignition sequence.

[0047] As can be seen from FIG. 3, no insurances against a blowback of air or combustion gas are provided and also are not necessary. Each combustion chamber 5 has air from the first compressor 3 continuously flowing around it and the expansion pressure of the combustion gases of the combustion chamber 5 is converted by the outflow nozzle 6 into flow rate.

[0048] The axial combustion gas turbine 1 according to the invention is primarily started by the compressor air. The compressors 3, 9 are designed so that the nominal rotation speed of the axial combustion gas turbine 1 is achieved by the compressors 3, 9. In addition, e.g. for assisting the starting of the axial combustion gas turbine 1, this can be started by the high-speed generator 2 operated as a motor. The fuel consumption is only required for operation of the axial combustion gas turbine 1.

[0049] FIG. 4 shows a conducting device 17 in which the compressor air and also the combustion gases are supplied via the guide vanes 18 to the turbine wheel 12 which is arranged downstream of the conducting device 17. The compressor air from the second compressor 9 is supplied to the turbine wheel 12 via the guide vanes 18. The regions of the conducting device 17 shown are fluidically completely separated. In the conducting device 17, in the example six combustion chambers 5 are provided, i.e. the compressor air only flows into the guide vanes 18 via the six combustion chambers 5 and the pre-chambers 15 thereof and acts upon the turbine wheel 12.

[0050] In principle, the same thermodynamic conditions apply to both compressor circuits. The pressure produced by the compressor 3, 9 remains constant, only the volume is increased due to the heating. The fluid relaxes over the axial combustion gas turbine 1, with the result that a pressure increase is not possible. The independent compressor circuits (compressor circuits) function in the same way, only the respective heat source is a different one.

[0051] It is important that the two compressor circuits are supplied separately to the axial combustion gas turbine 1 in order to avoid mutual influences.

[0052] In the second drive train it is therefore prevented that the heat introduced through the counterflow heat exchanger 11 does not result in any expansion in the pressure line which could have a braking effect on the compressor 9 of the second drive train.

[0053] For the high-speed generator 2 and the high-speed drives 4, 10, an inverter developed for this application is used which supplies the high-frequency generator current, via an intermediate circuit, the high-speed drives 4, 10 and the turbine controller and converts the remaining current into consumer voltage.

[0054] An electronic controller is used for regulating the axial combustion gas turbine 1, which calculates the optimal power via sensors for temperature, pressure and rotational speed and the data from the inverter.

[0055] In the case of turbines, which use high-speed drives, an inverter is necessary. Since a high-frequency high voltage is produced due to the high rotational speed of the generator, this must be converted into a low-frequency consumer voltage. This is accomplished by means of an inverter. Since high-speed drives according to the invention are used for the drive of the compressor 3, 9, it is not appropriate to use commercially available inverters which convert the consumer voltage into a high-frequency voltage. Thus, an inverter with a so-called intermediate circuit is provided for the high-speed drives 4, 10. Due to the inverter according to the invention, it is possible to use the high-frequency voltage directly from the generator 2.

[0056] The efficiency of the turbine according to the invention is increased considerably compared with previously known solutions.

REFERENCE LIST

[0057] 1 Axial combustion gas turbine
2 High-speed generator

3 Compressor

[0058] 4 High-speed electric drive
5 Combustion chamber
6 Outflow nozzle
7 Fuel injection means
8 Ignition device

9 Compressor

[0059] 10 High-speed electric drive
11 Counterflow heat exchanger
12 Turbine wheel

13 Channel

14 Compressor air

15 Pre-chamber

[0060] 16 Axis of rotation
17 Conducting device
18 Guide vanes