METHOD AND SYSTEM FOR COOLING DOWN A GAS TURBINE

Abstract

A method for cooling down a gas turbine, wherein the gas turbine is run down from the power operation thereof to cool-down operation, and wherein a liquid is sprayed into air sucked in by a compressor of the gas turbine during the cool-down operation, and wherein the liquid is sprayed into the sucked-in air in dependence on a humidity of the sucked-in air, a flow velocity of cooling air flowing in the gas turbine in the region of at least one flow-guiding component of the gas turbine, which component is to be cooled, and a temperature difference between a temperature of the sucked-in air and a temperature of the at least one flow-guiding component of the gas turbine.

Claims

1. A method for cooling down a gas turbine, comprising: running down the gas turbine from the power mode thereof to a cool-down mode, and injecting a liquid into air sucked in by a compressor of the gas turbine during the cool-down mode, wherein the liquid is injected into the sucked-in air in dependence on an air humidity of the sucked-in air, a flow velocity of cooling air flowing in the gas turbine in the region of at least one flow-guiding component, which is to be cooled, of the gas turbine, and a temperature difference between a temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled and a temperature of the at least one flow-guiding component of the gas turbine.

2. A method for cooling down a gas turbine, comprising: wherein running down the gas turbine from the power mode thereof to a cool-down mode, and wherein injecting a liquid is injected into air sucked in by a compressor of the gas turbine during the cool-down mode, wherein the liquid into the sucked-in air in dependence on an air humidity of the sucked-in air, a flow velocity of cooling air flowing in the gas turbine in the region of at least one flow-guiding component, which is to be cooled, of the gas turbine, and a temperature difference between a temperature of the sucked-in air and a temperature of the at least one flow-guiding component of the gas turbine.

3. The method as claimed in claim 1, wherein an opening cross section of an inlet into the compressor is at least partially enlarged during the cool-down mode by means of appropriate control of adjustable inlet guide vanes.

4. A system for cooling down a gas turbine, having at least one device for injecting a liquid into air sucked in by a compressor of the gas turbine, which device can be arranged upstream of the compressor, and at least one electronic open-loop and/or closed-loop control unit, which can be connected to the device in terms of signal engineering and which is designed to control the device in an appropriate manner in order to inject the liquid into the sucked-in air during a cool-down mode of the gas turbine, wherein the system comprises: at least one sensor unit for detecting an air humidity of the sucked-in air, at least one sensor unit for detecting a flow velocity of cooling air flowing in the gas turbine in the region of at least one flow-guiding component, which is to be cooled, of the gas turbine, at least one sensor unit for detecting a temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled, and at least one sensor unit for detecting a temperature of the at least one flow-guiding component of the gas turbine, wherein the sensor units can be connected to the electronic open-loop and/or closed-loop control unit in terms of signal engineering, and wherein the electronic open-loop and/or closed-loop control unit is designed to determine a temperature difference between the temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled and the temperature of the at least one flow-guiding component of the gas turbine and to control the device in such a way that the liquid can be injected into the sucked-in air in dependence on the respectively detected air humidity of the sucked-in air, the respectively detected flow velocity of the cooling air and the respectively detected temperature difference between the temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled and the temperature of the at least one flow-guiding component of the gas turbine.

5. A system for cooling down a gas turbine, having at least one device for injecting a liquid into air sucked in by a compressor of the gas turbine, which device can be arranged upstream of the compressor, and at least one electronic open-loop and/or closed-loop control unit, which can be connected to the device in terms of signal engineering and which is designed to control the device in an appropriate manner in order to inject the liquid into the sucked-in air during a cool-down mode of the gas turbine, wherein the system comprises: at least one sensor unit for detecting an air humidity of the sucked-in air, at least one sensor unit for detecting a flow velocity of cooling air flowing in the gas turbine in the region of at least one flow-guiding component, which is to be cooled, of the gas turbine, at least one sensor unit for detecting a temperature of the sucked-in air, and at least one sensor unit for detecting a temperature of the at least one flow-guiding component of the gas turbine, wherein the sensor units can be connected to the electronic open-loop and/or closed-loop control unit in terms of signal engineering, and wherein the electronic open-loop and/or closed-loop control unit is designed to determine a temperature difference between the temperature of the sucked-in air and the temperature of the at least one flow-guiding component of the gas turbine and to control the device in such a way that the liquid can be injected into the sucked-in air in dependence on the respectively detected air humidity of the sucked-in air, the respectively detected flow velocity of the cooling air and the respectively detected temperature difference between the temperature of the sucked-in air and the temperature of the at least one flow-guiding component of the gas turbine.

6. The system as claimed in claim 4, having comprising: at least one assembly, which can be connected to the electronic open-loop and/or closed-loop control unit in terms of signal engineering, for varying an opening cross section of an inlet into the compressor, which assembly has at least one inlet guide vane ring comprising adjustable inlet guide vanes, wherein the electronic open-loop and/or closed-loop control unit is designed to control the assembly in a manner appropriate to the at least partial enlargement of the opening cross section of the inlet into the compressor during the cool-down mode.

7. The system as claimed in claim 5, comprising at least one assembly, which can be connected to the electronic open-loop and/or closed-loop control unit in terms of signal engineering, for varying an opening cross section of an inlet into the compressor, which assembly has at least one inlet guide vane ring comprising adjustable inlet guide vanes, wherein the electronic open-loop and/or closed-loop control unit is designed to control the assembly in a manner appropriate to the at least partial enlargement of the opening cross section of the inlet into the compressor during the cool-down mode.

8. The method as claimed in claim 2, wherein an opening cross section of an inlet into the compressor is at least partially enlarged during the cool-down mode by means of appropriate control of adjustable inlet guide vanes.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The invention is explained by way of example below by means of an embodiment with reference to the attached figure, wherein the features explained below can in each case represent one aspect of the invention taken individually or in various combinations. In the drawing:

[0025] FIG. 1 shows a schematic illustration of one illustrative embodiment of a system according to the invention.

DETAILED DESCRIPTION OF INVENTION

[0026] FIG. 1 shows a schematic illustration of one illustrative embodiment of a system 1 according to the invention for cooling down a gas turbine 2. The gas turbine 2 comprises a compressor 3, a turbine 4 and a combustion chamber 5, which connects the compressor 3 fluidically to the turbine 4.

[0027] The system 1 comprises a device 6, arranged upstream of the compressor 3 of the gas turbine 2, for injecting a liquid into air sucked in by the compressor 3. Moreover, the system 1 comprises an electronic open-loop and/or closed-loop control unit 7, which can be connected to the device 6 in terms of signal engineering by a signal connection S. The electronic open-loop and/or closed-loop control unit 7 is designed to control the device 6 in an appropriate manner in order to inject the liquid into the sucked-in air during a cool-down mode of the gas turbine 2.

[0028] The system 1 furthermore comprises at least one sensor unit 8, arranged downstream of the device 6, for detecting an air humidity of the air sucked in by the compressor 3, a sensor unit 9, arranged in the gas turbine 2, for detecting a flow velocity of cooling air flowing in the gas turbine 2 in the region of at least one flow-guiding component (not shown), which is to be cooled, of the gas turbine 2, a sensor unit 10, arranged in the gas turbine 2, for detecting a temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled, and a sensor unit 11, arranged in the gas turbine 2, for detecting a temperature of the at least one flow-guiding component of the gas turbine 2. The sensor units 8 to 11 are each connected to the electronic open-loop and/or closed loop control unit 7 in terms of signal engineering by a signal connection S.

[0029] The electronic open-loop and/or closed-loop control unit 7 is designed to determine a temperature difference between the temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled and the temperature of the at least one flow-guiding component of the gas turbine 2. The electronic open-loop and/or closed-loop control unit 7 is furthermore designed to control the device 6 in such a way that the liquid can be injected into the sucked-in air in dependence on the respectively detected air humidity of the sucked-in air, the respectively detected flow velocity of the cooling air and the respectively detected temperature difference between the temperature of the cooling air flowing in the region of the at least one flow-guiding component to be cooled and the temperature of the at least one flow-guiding component of the gas turbine 2.

[0030] The system 1 furthermore comprises an assembly 12, which can be connected to the electronic open-loop and/or closed-loop control unit 7 in terms of signal engineering by a signal connection S, for varying an opening cross section (not shown) of an inlet into the compressor 3. The assembly 12 comprises at least one inlet guide vane ring (not shown) comprising adjustable inlet guide vanes. The electronic open-loop and/or closed-loop control unit 7 is designed to control the assembly 12 in a manner appropriate to the at least partial enlargement of the opening cross section of the inlet into the compressor 3 during the cool-down mode.

[0031] Although the invention has been illustrated and described more specifically in detail by means of the preferred illustrative embodiment, the invention is not restricted by the example disclosed, and other variations can be derived therefrom by a person skilled in the art without exceeding the scope of protection of the invention.