OPERATION OF A GAS TURBINE COMPRISING AN INTERPOLATED OPERATING CURVE DEVIATION

Abstract

An operating method for a gas turbine by partial-load operation, includes setting of a power setpoint value for a predefined temperature value; determining the two operating curves as a function of temperature according to the power of the gas turbine, wherein the power setpoint value is located between said operating curves; determining the difference in power of said two operating curves at the substantially constant predetermined temperature value; determining a power deviation from the predetermined power setpoint value of one of the two operating curves at the substantially constant predetermined temperature value; calculating an interpolated operating curve deviation on the basis of the difference in power and the power deviation, wherein the temperature is a turbine outlet temperature or a computationally determined turbine inlet temperature.

Claims

1. An operating method for a gas turbine during partial load operation, comprising the following steps: specifying a power output setpoint value at a predetermined temperature value; determining two operating curves of the temperature as a function of the power output of the gas turbine, wherein the power output setpoint value is arranged between these operating curves; determining the power output difference of these two operating curves at the essentially constant, predetermined temperature value; determining a power output deviation of the predetermined power output setpoint value from one of the two operating curves at the essentially constant, predetermined temperature value; calculating an interpolated operating curve deviation on the basis of the power output difference and the power output deviation, wherein the temperature is a turbine exit temperature or a computationally determined turbine inlet temperature.

2. An operating method for a gas turbine during partial load operation, comprising the following steps: specifying a setpoint value of a temperature at a predetermined power output; determining two operating curves of the temperature as a function of the power output of the gas turbine, wherein the setpoint value of the temperature is arranged between these operating curves; determining the difference of the temperatures of these two operating curves at the essentially constant, predetermined power output; determining a deviation of the predetermined setpoint value of the temperature from the temperature of one of the two operating curves at the essentially constant, predetermined power output; calculating an interpolated operating curve deviation on the basis of the difference of the temperatures and the deviation of the setpoint value of the temperature, wherein the temperature is a turbine exit temperature of a computationally determined turbine inlet temperature.

3. The operating method as claimed in claim 1, wherein one of the two operating curves is the operating curve currently in use in the control system of the gas turbine.

4. The operating method as claimed in claim 1, wherein the interpolated operating curve deviation is calculated by means of a linear interpolation.

5. The operating method as claimed in claim 1, wherein the interpolated operating curve deviation takes into consideration, or also includes, a change of the compressor guide vane position.

6. The operating method as claimed in claim 1, further comprising: determining a set of individual fuel quantities which are fed to a multiplicity of burners or burner stages of the gas turbine, taking into consideration the interpolated operating curve deviation.

7. A gas turbine control system, comprising: a control unit, wherein the control unit is designed to implement a method as claimed in claim 1.

8. A gas turbine comprising: a control system as claimed in claim 7.

9. The operating method as claimed in claim 2, wherein one of the two operating curves is the operating curve currently in use in the control system of the gas turbine.

10. The operating method as claimed in claim 2, wherein the interpolated operating curve deviation is calculated by means of a linear interpolation.

11. The operating method as claimed in claim 2, wherein the interpolated operating curve deviation takes into consideration, or also includes, a change of the compressor guide vane position.

12. The operating method as claimed in claim 2, further comprising: determining a set of individual fuel quantities which are fed to a multiplicity of burners or burner stages of the gas turbine, taking into consideration the interpolated operating curve deviation.

13. A gas turbine control system, comprising: a control unit, wherein the control unit is designed to implement a method as claimed in claim 2.

14. A gas turbine comprising: a control system as claimed in claim 13.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In this case, in the drawing:

[0035] FIG. 1 shows a schematic view in diagram form of the slope of different operating curves for operating a gas turbine, and also of the determination of a power output setpoint value according to a first embodiment of the invention;

[0036] FIG. 2 shows a further schematic view in diagram form of different operating curves for operating a gas turbine, taking into consideration a setpoint value of a temperature, according to a further embodiment of the invention;

[0037] FIG. 3 shows a further schematic view in diagram form of a slope of different operating curves for determining a power output setpoint value or setpoint value of a temperature according to a further embodiment of the invention.

DETAILED DESCRIPTION OF INVENTION

[0038] FIG. 1 shows a schematic view in diagram form of a number of operating curves FL1, FL2, FL3 for operating a gas turbine, which run largely parallel to each other. The operating curves FL1, FL2, FL3 can be described as a function of the temperature T in dependence of the power output L of the gas turbine 1 (not shown in the present case) or also as a function of the power output L in dependence of the temperature T. The depicted operating curves FL1, FL2, FL3 have in this case a uniform increase of the power output L with increasing temperature T. Such an operating curve slope is typically distinguished for example by increased feed of fuel to the individual burners or burner stages of the gas turbine 1. In other words, the operating curves FL1, FL2 and FL3 are easily described by for example only the total quantity of fuel being increased with already existing and established distribution of the individual proportionate fuel quantities for the burners or burner stages of the gas turbine 1.

[0039] The individual operating curves FL1, FL2, FL3, however, can differ to the effect that the proportionate quantities of individual fuel flows which are fed to the individual burners or burner stages of the gas turbine differ. If, therefore, for example an operating change in the middle of an operation which uses the operating curve FL2 as a reference value is to be carried out to the effect that the operating curve FL1 is now to be used as a reference value, a corresponding change of the respectively associated parameter set would have to be undertaken in the control system of the gas turbine 1. Since the operating curves FL1 and FL2 also differ with regard to the proportionate quantities of fuel to the individual burners or burner stages, this would bring about a sometimes comparatively sharp jump in the distribution change of the fuel, which can transfer the gas turbine into an unstable operating state. In order to prevent this, a power output setpoint value LS which is arranged between the two operating curves FL1 and FL2 is now to be determined. In order to determine this power output setpoint value LS more specifically, according to one embodiment of the invention an interpolation which calculates the corresponding operating parameters for the power output setpoint value LS is undertaken. To this end, at a predetermined temperature TO, which during this process is not supposed to change, or not supposed to change significantly, a power output difference LU which exists between the two operating curves FL2 and FL1 at the basically constant, predetermined temperature value TO is determined. Similarly, a power output deviation LA of the predetermined power output setpoint value LS from the second operating curve FL2 at the basically constant, predetermined temperature value TO is also determined. With the aid of these two values of the power output difference LU and the power output deviation LA, an interpolated operating curve deviation IFA can now be determined via a simple rule of three calculation, which curve deviation virtually includes all the operating parameters for an operating curve FL, but makes reference to an intermediate position between the two operating curves FL1 and FL2. If this interpolated operating curve deviation IFA is now additionally computationally associated for example with the second operating curve FL2, a new operating curve slope can be defined and connects for example the operating curve 2 to the operating curve 1 (see the highlighted areas of the respective operating curves).

[0040] By determining such a power output setpoint value LS, an intermediate state can therefore be initiated during a change between the operating curves FL2 and FL1, which intermediate state allows a comparatively more stable intermediate operation to be undertaken during a change of the controlled operation. Naturally, it is also conceivable that a larger number, a multiplicity, of different power output setpoint values between the respective operating curves FL1 and FL2 are determined. Accordingly, it can therefore be calculated that the thereby established gas turbine operation can be carried out in an even more stable manner. In other words, by calculating one or more power output setpoint values between the operating curves FL1 and FL2 a new overall operating curve can be defined and can be used as a suitable reference value within the scope of the gas turbine control system. In this case, it is also conceivable that the thereby calculated intermediate states are not only different with regard to the parameters of the proportionate individual fuel quantity flows but for example also different with regard to the guide vane positions. Especially the transition between the operating curves FL2 and FL1, shown in FIG. 1, which indeed is carried out at the basically constant, predetermined temperature TO, that is to say with a basically unaltered fuel mass flow, is typically also undertaken as a result of a change of the compressor inlet guide vane positions in addition to a change of the proportionate fuel flows to the individual burners or burner stages.

[0041] This situation is different during a change of the gas turbine operation between an operating curve FL2 and an operating curve FL1, as shown in FIG. 2. If the operating curves FL1 and FL2 are specified basically at invariable temperature values, wherein only the associated power output values are altered, by an adjustment of the compressor inlet guide vanes practically no change between the two operating curves FL1 and FL2 is carried out. Since in essence the total fuel mass flow is responsible for the creation of the relevant temperatures (e.g. turbine exit temperatures), the currently shown change between the operating curve FL2 and the operating curve FL1 requires the specifying of a setpoint value ST of a temperature T which is arranged between the two operating curves FL2 and FL1. For calculating the interpolated operating curve deviation IFA, a difference is calculated in turn, but this time between the temperatures of the two operating curves at the basically constant, predetermined power output L0. Moreover, a deviation AST of the predetermined setpoint value ST of the temperature T from the temperature T of the operating curve FL2 at a basically constant, predetermined power output L0 is calculated. In turn, by means of a rule of three equation the interpolated operating curve deviation IFA can be calculated from these two values of the deviation AST of the predetermined setpoint value ST of the temperature T and of the difference UT of the temperature T.

[0042] The further principles when determining the setpoint value ST of a temperature T correspond in this case to the principles as under FIG. 1 for determining the power output setpoint value LS. The transition between the two operating curves FL2 and FL1, on the other hand, is brought about in the first instance by a change of the total fuel mass flow which is fed to the individual burners or burner stages of the gas turbine 1 (not shown in the present case).

[0043] FIG. 3 shows a further diagrammatic view of different operating curves FL1, FL2, FL3 and FL4, wherein the cases shown in FIGS. 1 and 2 are now combined. By combining the cases, a mixed region MB is produced in the region of the transition between the operating curves FL1, FL2 and FL3, FL4 and is shown in a chequered pattern. Whereas the transition from the operating curve FL2 to the operating curve FL1 via the power output setpoint value LS, shown in FIG. 1, can be achieved in the main by means of an adjustment of the compressor inlet guide vanes and the transition between the operating curve FL2 and FL1 according to FIG. 2 can be achieved in the main by means of a change of the total fuel mass flow, wherein the setpoint value ST of the temperature T is taken into consideration, in the mixed region MB a combination of adjustment of the total fuel mass flow and compressor inlet guide vane adjustment can now be carried out in order to optionally make a change between the individual operating curves. The adjustment of total fuel mass flow and compressor inlet guide vane position can in this case be carried out basically at the same time.

[0044] Further embodiments are gathered from the dependent claims.