Gas turbine module ventilation system having controllable baffle vanes - Patents.com

Abstract

To provide systems for ventilating a gas turbine enclosure.SOLUTION: A turbine ventilation system (26) includes a controller (52) that is coupled to an actuator (32) that is coupled to a vane (34) that is disposed across an intake port (36) between a gas turbine enclosure (12) and the turbine ventilation system (26). The controller (52) can cause the actuator (32) to change a position of the vane (34) to alter an air flow from the turbine ventilation system (26) into the gas turbine enclosure (12) based upon feedback from one or more sensors (58) disposed within the gas turbine enclosure (12).SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The subject matter disclosed herein relates to a system for ventilating a gas turbine enclosure. [Background technology]

[0002] Gas turbine generators may be used to generate electricity for power grids. Gas turbine generators are typically stationary units located within power plants, such as integrated gasification combined cycle (IGCC) power plants. However, gas turbine generators may also be used in mobile units, such as large trailers. Gas turbine generators typically include a gas turbine engine enclosed within an enclosure (e.g., a gas turbine enclosure). To avoid heat buildup around the gas turbine engine, gas turbine generators include a ventilation system that carries heat away from the gas turbine engine. Unfortunately, the design of the ventilation system may limit the use of the gas turbine generator to environments within a certain ambient temperature range, increasing the operating costs of the gas turbine generator. In addition, the ventilation system may not adequately cool the equipment within the gas turbine enclosure under all conditions (e.g., air density, temperature, etc.). Furthermore, the ventilation system may consume a significant amount of power, thus reducing the efficiency of the gas turbine generator. Summary of the Invention

[0003] Certain embodiments commensurate in scope with the initially claimed subject matter are summarized below. These embodiments are not intended to limit the scope of the claimed subject matter, but rather, these embodiments are intended only to provide a brief summary of possible forms of the subject matter. Indeed, the subject matter may encompass a variety of forms that may be similar to or different from the embodiments set forth below.

[0004] According to a first embodiment, a system includes a gas turbine enclosure and a gas turbine engine disposed within the gas turbine enclosure. The gas turbine engine outputs an exhaust flow. The system also includes a ventilation system coupled to the gas turbine enclosure. The ventilation system includes a vane disposed across an intake port between the gas turbine enclosure and the ventilation system, an actuator coupled to the vane, and a controller coupled to the actuator. The controller causes the actuator to change a position of the vane to alter airflow from the ventilation system to the gas turbine enclosure.

[0005] According to a second embodiment, a system includes a turbine ventilation system coupled to a gas turbine enclosure. The turbine ventilation system includes a vane disposed across an intake port between the gas turbine enclosure and the turbine ventilation system, an actuator coupled to the vane, and one or more sensors disposed within the gas turbine enclosure. The turbine ventilation system also includes a controller coupled to the actuator. The controller causes the actuator to change a position of the vane to modify airflow from the turbine ventilation system to the gas turbine enclosure based on feedback received from the one or more sensors.

[0006] According to a third embodiment, a system includes a gas turbine controller having a memory storing instructions and a processor coupled to the memory to execute the instructions. During execution of the instructions, the processor receives feedback from one or more sensors disposed within a gas turbine enclosure having a gas turbine engine disposed within the gas turbine enclosure. The processor also executes the instructions to cause an actuator coupled to a vane disposed across an intake port between the gas turbine enclosure and a ventilation system to change a position of the vane to modify an airflow from the ventilation system to the gas turbine enclosure.

[0007] These and other features, aspects, and advantages of the present subject matter will be better understood from the following detailed description when taken in conjunction with the accompanying drawings, in which like reference characters represent like parts throughout. [Brief description of the drawings]

[0008] [Figure 1] FIG. 1 is a schematic side view of an embodiment of a gas turbine generator in a gas turbine enclosure having a ventilation system with controllable vanes, according to one embodiment. [Diagram 2] FIG. 1 is a schematic block diagram of an embodiment of a ventilation system for a gas turbine system and a gas turbine enclosure, according to an embodiment. [Diagram 3] FIG. 1 is a schematic diagram of an embodiment of a ventilation system for a gas turbine enclosure, according to an embodiment. [Figure 4] FIG. 2 is a schematic diagram of a controllable vane according to one embodiment. [Diagram 5] FIG. 5 is a cross-sectional view of the controllable vane taken along line 5-5 of FIG. 4. [Figure 6] FIG. 5 is a cross-sectional view of a controllable vane having multiple segments taken along line 5-5 of FIG. 4. [Figure 7] 4 is a flowchart of a method for controlling aspects of a controllable vane according to one embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0009] One or more specific embodiments of the present disclosure are described below. In order to provide a concise description of these embodiments, not all features of an actual implementation are described herein. It should be understood that in the development of an actual implementation, such as an engineering or design project, numerous implementation-specific decisions must be made to achieve the developer's particular objectives, such as to accommodate system-related and business-related constraints, and that these constraints may vary from implementation to implementation. Moreover, it should be understood that such a development effort may be complex and time-consuming, but is nevertheless a routine undertaking of design, fabrication, and manufacture for those of ordinary skill in the art having the benefit of this disclosure.

[0010] When introducing elements of various embodiments of the present subject matter, the articles "a," "an," "the," and "said" are intended to mean that there are one or more of the element. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements. Furthermore, the term "or" is intended to be inclusive and indicates that A or B includes only A, only B, or both A and B.

[0011] Disclosed embodiments relate to a system and method for ventilating an enclosure surrounding a gas turbine engine. Proper ventilation of equipment (e.g., a gas turbine engine) removes unwanted emissions within the enclosure and provides cooling within the enclosure. In disclosed embodiments, the ventilation system includes controllable vanes (e.g., baffle vanes) positioned across an intake port between the ventilation system and the gas turbine enclosure to direct airflow from the ventilation system within the gas turbine enclosure. The controllable vanes, actuated, for example, by actuators, can be moved to various positions to increase the distribution of airflow to desired locations within the gas turbine enclosure. The vanes can be automatically controlled by a controller. In certain embodiments, the controller can adjust the vanes based on feedback (pressure, temperature, etc.) from sensors positioned within the gas turbine enclosure. The controllable vanes also provide cooling and mixing of air within the gas turbine module for various air density and temperature conditions. Proper air distribution can provide optimal cooling performance (e.g., by minimizing hot spots within the enclosure) and allow equipment within the enclosure to operate within their rated temperature limits. In particular, the disclosed embodiments may protect gas turbine engines by effectively facilitating airflow (e.g., cooling distribution) at multiple air densities and boundary conditions throughout the gas turbine enclosure.

[0012] Referring to the figures, FIG. 1 is a schematic side view of an embodiment of a gas turbine system 10 within a gas turbine enclosure 12. The gas turbine system 10 includes a combustion air intake system 14, a gas turbine engine 16, and a generator 18 (e.g., an electric generator) powered by the gas turbine engine 16. The combustion air intake system 14 includes one or more filters 20 that filter air (e.g., combustion air) entering the gas turbine engine 16. Particles filtered by the combustion air intake system 14 may include ice and / or other solid particles that may be harmful to components (e.g., compressor blades, turbine blades, etc.) within the gas turbine system 10. In some embodiments, other structures may be included in the combustion air intake system 14, such as an air hood, an air intake port, and a silencer baffle, to name a few. The combustion air intake system 14 receives air, processes (e.g., filters) the air, and then directs the air to the gas turbine engine 16 through an intake port 22. After being compressed and mixed with fuel, the air, or more precisely the air-fuel mixture, is combusted. The energy generated by the gas turbine engine 16 is used to rotate a shaft 24 that is coupled to a generator 18. In other embodiments, the shaft 24 may be coupled to other devices or systems, such as a motor.

[0013] Additionally, the gas turbine system 10 housed in the gas turbine enclosure 12 receives ventilation air from a ventilation air intake system 26 (e.g., a ventilation system). The ventilation air intake system 26 includes one or more filters 28, a baffle 30, and an actuator 32 coupled to a vane 34 (e.g., a controllable vane arm or baffle) that directs the ventilation air to a desired location within the gas turbine enclosure 12. The controllable vane 34 is disposed across a port 36 (e.g., an intake port) between the ventilation air intake system 26 and the gas turbine enclosure 12. A controller is enabled to automatically control the controllable vane 34. The controller can adjust the controllable vane 34 based on feedback received from a sensor disposed within the gas turbine enclosure 12. This enables the distribution of the ventilation air to be changed as needed based on changing conditions within the gas turbine enclosure 12. Air enters the gas turbine enclosure 12 from the ventilation air intake system 26 through the port 36. Although not shown, in some embodiments, the ventilation air intake system 26 may include other elements, structures, systems, or devices, such as one or more fans. The ventilation air flow may exit the gas turbine enclosure 12 via a ventilation exhaust duct 43. Gaseous emissions (e.g., exhaust gases) from the gas turbine engine 16 may exit the gas turbine enclosure 12 through a port 38 coupled to a combustion exhaust duct 40.

[0014] Additionally, components of the gas turbine engine 16 housed in the gas turbine enclosure 12 may be subject to temperature differences based on location (e.g., position in one, two, or three dimensions) within the gas turbine enclosure 12. For example, one or more components of the gas turbine engine 16 may radiate (e.g., diffuse) heat to a volume or section within the gas turbine enclosure 12, resulting in that volume or section being hotter than another volume or section within the gas turbine enclosure 12. Without proper cooling, this radiated heat may cause one or more components or functions of the gas turbine system 10 to have reduced performance or lifespan if not addressed. For example, a casing of the gas turbine 16 may exceed its rated temperature limit if the radiated heat is not addressed. Similarly, the ambient temperature may vary throughout operation of the gas turbine system 10 due to solar radiation that may be absorbed by the gas turbine system 10 and / or sections (e.g., walls) of the gas turbine enclosure 12, for example. Changes in ambient temperature throughout a day (or other period of operation of the gas turbine system 10) can induce hot spots within the gas turbine enclosure 12, which can change location as frequently as the ambient temperature changes. Indeed, hot spots (e.g., sections, areas, or volumes within the gas turbine enclosure 12 that are hotter than other sections, areas, or volumes within the gas turbine enclosure 12) may appear at various locations within the gas turbine enclosure 12 throughout operation of the gas turbine system 10. Furthermore, during operation of the gas turbine system 10, changes in air pressure can induce pressure differentials within the gas turbine enclosure 12 (e.g., pressure differentials between different locations within the gas turbine enclosure 12). Similar to temperature differentials, pressure differentials can occur at different locations at different times during operation of the gas turbine engine 16, as pressure conditions can change frequently throughout operation of the gas turbine engine 16. If the pressure differentials are not addressed, one or more components of the gas turbine system 10 may experience reduced performance or even lifespan.Gas turbine engines 16, gas turbine casings, and gas turbine enclosures 12 can be expensive to replace. Thus, a system that operates to maximize the performance and / or life of a gas turbine module is desirable.

[0015] 2 is a schematic block diagram of an embodiment of a ventilation air intake system 26 for the gas turbine system 10 and the gas turbine enclosure 12. In particular, the ventilation air intake system 26 is coupled to an air inlet 50 that receives air to be treated (e.g., filtered). As previously mentioned, the ventilation air intake system 26 includes one or more filters 28, a baffle 30, and an actuator 32 (e.g., positioner, motor, etc.) coupled to a controllable vane 34 that directs an air flow (indicated by arrow 60) into the gas turbine enclosure 12. A controller 52 includes computer readable instructions (e.g., non-transitory, tangible, and computer readable media / memory circuitry) stored in a memory 54 and a processor 56 that executes the instructions. More specifically, the memory 54 may include volatile memory, such as random access memory (RAM), and / or non-volatile memory, such as a read only memory (ROM), an optical drive, a hard disk drive, or a solid state drive. Additionally, the processor 56 may include one or more application specific integrated circuits (ASICs), one or more field programmable gate arrays (FPGAs), one or more general purpose processors, or any combination thereof. Furthermore, the term processor is not limited to integrated circuits referred to in the art as processors, but refers broadly to computers, processors, microcontrollers, microcomputers, programmable logic controllers, application specific integrated circuits, and other programmable circuits. The processor 56 and memory 54 may be used collectively to support operating systems, software applications, systems, and the like, and are useful in implementing the techniques described herein. For example, the memory 54 may store temperature and pressure ranges or limits for sections of the gas turbine enclosure 12. The memory 54 may also store desired positions for the controllable vanes 34, for example, in a look-up table. The look-up table may provide a mechanism for the controller 52 to access instructions for controlling the controllable vanes 34 with low latency.

[0016] The controller 52 is also communicatively coupled to one or more sensors 58 (e.g., temperature sensors, heat sensors, pressure sensors, etc.) disposed throughout the gas turbine enclosure 12. Based on feedback from the sensors 58 (e.g., temperature data, pressure data, etc.), the controller 52 can cause the actuators 32 to change the position or orientation of the controllable vanes 34. Indeed, the feedback can be utilized by the controller 52 to direct the controllable vanes 34 to positions that can cause increased cooling air distribution. For example, the controller 52 can compare the feedback to feedback threshold ranges. These threshold ranges can represent desired operating parameters (e.g., temperature, pressure, etc.) for a location within the gas turbine enclosure 12. Once a section of the gas turbine enclosure 12 is determined to have a hot spot and / or pressure differential based on feedback from the sensors 58, the controller 52 can send a command to the actuators 32 to change the position or orientation of the controllable vanes 34 to provide cooling or air flow to the section. For example, the controllable vanes 34 may be actuated to oscillate (e.g., swing back and forth) at a particular frequency between a first position or first angular orientation and a second position or second angular orientation based on the feedback. Also, as discussed in detail below, the amplitude of the angular displacement of the controllable vanes 34 between the first and second angular orientations may be dynamically controlled to direct ventilation air to a particular section of the gas turbine enclosure 12. Furthermore, the controller 52 may cause the controllable vanes 34 to rotate or maintain a particular angular orientation for a particular time to direct or modify airflow from the ventilation air intake system 26 to a particular section of the gas turbine enclosure 12 that is susceptible to hot spots and / or pressure differentials.By varying aspects of the controllable vanes 34 (e.g., angular orientation or position, vibration frequency and / or amplitude), the ventilation air intake system 26 can provide adequate airflow (e.g., via modifying the distributed cooling air) within the gas turbine enclosure 12 and minimize any hot spots within the gas turbine enclosure 12.

[0017] On another note, as shown in Figure 2, the combustion air intake system 14 channels combustion air through a filter 20 into the gas turbine system 10. As noted in Figure 1, the channeled combustion air flow exits the gas turbine enclosure 12 through a port 38 (indicated by arrow 38) and enters an exhaust outlet 64 that includes conduits such as a combustion exhaust duct 40 and a ventilation exhaust duct 43 (not shown in Figure 2). Similarly, the ventilation air flow may exit the gas turbine enclosure 12 through a port 90 (indicated by arrow 90) and proceed to the ventilation exhaust duct 43.

[0018] FIG. 3 is a schematic diagram of an embodiment of a ventilation air intake system 26 (e.g., a ventilation system) for a gas turbine enclosure 12 and a gas turbine system 10. The ventilation air intake system 26 and the gas turbine system 10 are not fully shown in FIG. 3, but are generally as described in FIGS. 1 and 2. The gas turbine system 10 includes a gas turbine engine 16 disposed within the gas turbine enclosure 12. Air enters a compressor 70 from the combustion air intake system 14 and is compressed in one or more compression stages (indicated by arrows 71). The compressed air 72 is then channeled to a combustor 74 coupled to fuel nozzles 76. In some embodiments, there may be multiple fuel nozzles in each combustor 74. In the combustor 74, the compressed air 72 is mixed with fuel and combusted to generate hot, pressurized exhaust gases. Each combustor 74 channels the exhaust gases through a turbine 78 toward an exhaust section 80, as indicated by arrows 82. The exhaust section 80 directs the exhaust gases toward the combustion exhaust duct 40, as indicated by arrow 73. As the exhaust gases pass through the turbine 78, the gases exert a force on turbine blades within the turbine 78, rotating a shaft 84 along the axis of the gas turbine engine 16. That is, energy from the combusted mixture causes the turbine blades within the turbine 78 to rotate. The blades within the turbine 78 are coupled to the shaft 84, which is also coupled to various components of the gas turbine engine 16, including the compressor 70. Nevertheless, as the shaft 84 rotates, the compressor blades within the compressor 70 also rotate, thereby compressing air through the compressor 70. The shaft 84 may also be connected to a load, such as, for example, an electrical generator (e.g., generator 18) in a power plant.

[0019] To ventilate the gas turbine enclosure 12, air from the ventilation air intake system 26 travels through one or more filter stages (e.g., filter 28, not shown in FIG. 3 ) and is then directed by a baffle 30 (e.g., baffle plate, diverter plate, divider plate) toward the controllable vanes 34 (indicated by arrows 86), which then direct the air into the gas turbine enclosure 12 (indicated by arrows 88). After ventilating the gas turbine enclosure 12, the ventilation air travels through a port 90 (indicated by arrows 92). The ventilation air is then directed through the port 90 into the ventilation exhaust duct 43 (indicated by arrows 92).

[0020] In particular, the direction of air entering the gas turbine enclosure 12 may be guided, at least in part, by the controllable vanes 34 that are automatically controlled (e.g., rotated) by the actuators 32. Specifically, the actuators 32 (e.g., motors) are coupled to the controllable vanes 34 and move the controllable vanes 34 in response to commands received from the controller 52. That is, as described above, one or more sensors 58 (e.g., thermal sensors, pressure sensors, etc.) are disposed throughout the gas turbine enclosure 12 and include circuitry that measures various parameters (e.g., temperature and / or pressure). The sensors 58 may be coupled to the controller 52 via wireless or wired connections. Thus, the controller 52 receives feedback from the sensors 58 via wireless or wired connections and instructs the actuators 32 to change the angular orientation or position of the controllable vanes 34. Additionally, the sensors 58 may be mounted on the walls of the gas turbine enclosure 12, directly on various components of the gas turbine system 10, and / or on the casing of the gas turbine engine 16. For example, the controller 52 may receive measurements from one or more sensors 58 indicating an increase in ambient temperature and / or pressure at a location or region of the gas turbine enclosure 12. In response to a determination that the gas turbine enclosure 12 (or gas turbine module) is experiencing an increase in ambient temperature and / or pressure in a particular section, the angular orientation, vibration frequency (e.g., rotational frequency), or vibration amplitude of the controllable vanes 34 may be modified (e.g., changed, altered, updated) to vary the distribution of air provided to improve cooling (e.g., minimize hot spots) throughout the gas turbine enclosure 12. Commands may also be sent to the actuators 32 via the controller 52 when measurements from the sensors 58 indicate a decrease in ambient temperature and / or pressure.

[0021] The movement of the controllable vanes 34 may be continuous or incremental. That is, in the case of continuous movement, the controllable vanes 34 may rotate from a first angular orientation or first position to a second angular orientation or second position without the movement of the controllable vanes 34 stopping at any angular orientation or position between the completion of the rotation from the first angular orientation or first position to the second angular orientation or second position. The incremental movement of the controllable vanes 34 may be such that the controllable vanes 34 stop moving at different pre-set positions or angular orientations along a path between the closed position and the fully open position.

[0022] FIG. 4 is a schematic side view of the baffle 30 (e.g., a directional airflow baffle) and the controllable vane 34. An axis 98 is along the width of the controllable vane 34, an axis 100 is along the longitudinal length of the gas turbine enclosure 12, and an axis 102 is along the height of the gas turbine enclosure 12. Specifically, the baffle 30 at least partially directs air exiting the ventilation air intake system 26 and entering the gas turbine enclosure 12 through a section 104 or a section 106 of the port 36. The baffle 30 is located within a duct of the ventilation air intake system 26 and may extend over a region perpendicular or nearly perpendicular to the duct of the ventilation air intake system 26. The baffle 30 may effectively split the airflow indicated by the arrow 86 into two portions such that the airflow exits the duct of the ventilation air intake system 26 through the section 104 or the section 106. In some embodiments, the baffle 30 may extend only a portion of the conduit. Downstream of the baffle 30 is a controllable vane 34, which is disposed across a port 36 between the ventilation air intake system 26 and the gas turbine enclosure 12. The controllable vane 34 rotates circumferentially about an axis 108 (parallel to the axis 98). The controllable vane 34 rotates about the axis 108 in response to the actuator 32 varying the angular orientation of the controllable vane 34 to alter (e.g., modify, shift, redirect) the airflow from the ventilation air intake system 26 to the gas turbine enclosure 12. In effect, the actuator 32 (e.g., a motor) applies a torque to the controllable vane 34 to rotate about the axis 108. As a result, based on the angular orientation of the controllable vane 34, the air emerging from the ventilation air intake system 26 and entering the gas turbine enclosure 12 is directed to a specific location. Specifically, the angle at which the airflow enters the gas turbine enclosure 12 is determined by the angular orientation of the controllable vanes 34 relative to the axis 103. Different positions or angular orientations can direct the ventilation airflow to different locations within the gas turbine enclosure 12.For example, when the controllable vanes 34 are at an angular orientation 110 about the axis 108, arrow 112 corresponds to the general direction of the airflow emerging through section 104, and arrow 114 corresponds to the general direction of the airflow emerging through section 106. A shift in the angular orientation of the controllable vanes 34 may cause a change in the angle at which the airflow emerges through sections 104 and 106. Thus, based on the angular orientation of the controllable vanes 34, the airflow is controlled to penetrate the gas turbine enclosure 12 in different directions, as indicated by arrows 112, 114.

[0023] Additionally, the controllable vanes 34 can be rotated (relative to sections 104 and 106) between a fully open position and a closed position. The fully open position relative to section 104 corresponds to an angular orientation 116, whereby a minimum airflow appears through section 106 and a maximum airflow appears through section 104. The closed position of the controllable vanes 34 relative to section 104 corresponds to an angular orientation 118, whereby a minimum airflow appears through section 104 and a maximum airflow appears through section 106. Additionally, the fully open position of the controllable vanes 34 relative to section 106 corresponds to an angular orientation 118, whereby a minimum airflow appears through section 104 and a maximum airflow appears through section 106. The closed position of the controllable vanes 34 relative to section 106 corresponds to an angular orientation 116, whereby a minimum airflow appears through section 106 and a maximum airflow appears through section 104. Thus, the closed position of the controllable vanes 34 relative to the section 104 corresponds to a fully open position of the controllable vanes 34 relative to the section 106. Furthermore, the closed position of the controllable vanes 34 relative to the section 106 corresponds to a fully open position of the controllable vanes 34 relative to the section 104. In some embodiments, the controllable vanes 34 are axially located along the axis 100 and extend across the entire port 36. In these embodiments, the closed position may correspond to a minimum airflow through both the section 104 and the section 106, while the fully open position corresponds to a maximum airflow through both the section 104 and the section 106. Furthermore, as previously mentioned, the rotation of the controllable vanes 34 may be continuous or progressive. The controllable vanes 34 may be actuated or controlled to be oriented in a number of angular orientations to provide proper air cooling distribution to the components of the gas turbine system 10 within the gas turbine enclosure 12. Finally, in FIG. 4, the ventilation airflow exits the gas turbine enclosure 12 through the port 90 and proceeds to the ventilation exhaust duct 43.

[0024] Figure 5 is a cross-sectional view of the controllable vane 34 taken along line 5-5 of Figure 4. In particular, the controllable vane 34 is rotated about an axis 108 along the longitudinal length of the controllable vane 34 due to torque applied by the actuator 32. The controllable vane 34 may be made of a metal such as iron, a plastic, an alloy such as steel, or the like, or another material capable of directing the airflow emerging from the ventilation air intake system 26 into the gas turbine enclosure 12.

[0025] As shown in FIG. 6, in some embodiments, the controllable vane 34 may be segmented into two parts. Specifically, the segmented controllable vane 130 has a first vane segment 132 with a first actuator 134 and a second vane segment 136 with a second actuator 138. The first vane segment 132 and the second vane segment 136 rotate about the axis 108 and move independently relative to each other. Thus, for example, the controller 52 may send a command to the first actuator 134 to change the position or angular orientation of the first vane segment 132 without sending a command to the second actuator 138 to change the position or angular orientation of the second vane segment 136. Also, the controller 52 may send a command to both the first actuator 134 and the second actuator 138 to change the position or angular orientation of the first vane segment 132 and the second vane segment 136, respectively, such that the commands are executed simultaneously. As shown, the segmented controllable vane 130 includes two segments 132, 136. In some embodiments, the number of vane segments may vary (e.g., three, four, or more). Additionally, in some embodiments, the segments may be coupled to the same actuator. In other embodiments, the ventilation air intake system 26 includes two or more rotatable vanes, each located at a different axial location along the port 36 relative to the axis 100. In this case, the airflow from the ventilation air intake system 26 may be more precisely guided in a particular direction within the gas turbine enclosure 12.

[0026] FIG. 7 is a flow chart of an embodiment of a method 160 for ventilating the gas turbine enclosure 12. In certain embodiments, one or more steps of the method 160 may be executed by the controller 52. The method 160 includes receiving one or more operating parameters from sensors 58 disposed throughout the gas turbine enclosure 12 at block 162. The sensors 58 may detect temperature, pressure, or other parameters at one or more locations throughout the gas turbine enclosure 12. For example, as described above, the temperature and pressure of the gas turbine enclosure 12 may change throughout the operation of the gas turbine engine 16 as the ambient temperature and pressure may vary during a period of time (e.g., hours, days, months, etc.). As the temperature and / or pressure change, one or more hot spots may be detected by the sensors 58, which provide feedback (e.g., temperature and / or pressure data) to the controller 52. At block 164, the method 160 also includes determining whether the received operating parameters are within a desired range for a current operation of the rotating vanes (e.g., the controllable vanes 34). The current operation of the rotary vanes may correspond to a current vibration amplitude and / or frequency or an angular orientation or position of the rotary vanes. For example, the controller 52 may determine, based on the feedback, whether a characteristic of the rotary vanes (i.e., vibration amplitude and / or frequency, or current angular orientation or position) needs to be changed for proper cooling and air distribution within the gas turbine enclosure 12. Upon determining that the received operating parameters are within a predetermined range (e.g., a pressure range and / or a temperature range), the method 160 proceeds with maintaining the current operation of the rotary vanes at block 166. That is, an aspect of the current operation of the rotary vanes (e.g., vibration amplitude or frequency, or angular position or orientation) is not changed.In response to a determination that the received operating parameters are not within a predetermined range (e.g., a pressure range and / or a temperature range), the method proceeds with modifying an aspect of the current movement of the rotary vanes (e.g., changing the frequency or amplitude of vibration, or the angular orientation or position) at block 168. As a result, the controller 52 may cause the rotary vanes to change their angular orientation or position, and / or the frequency and amplitude of vibration. For example, in response to a determination that the operating parameters are not within a desired range, the controllable vanes 34 may be automated to increase the frequency and amplitude of their movement.

[0027] In addition to providing improvements for cooling the gas turbine enclosure 12 at various ambient temperatures and pressures, the present embodiment of the controllable vanes 34 may be particularly useful in geographic locations that endure significant changes in environmental conditions throughout the day, season (e.g., summer, winter, etc.), year, or another period of time. Climate changes induce ambient temperature and pressure boundary conditions within the gas turbine enclosure 12 that may change frequently throughout the operation of the gas turbine system 10. Specifically, as the ambient temperature and / or pressure increases or decreases, elements within the gas turbine enclosure 12 (e.g., the gas turbine system 10) may change (e.g., decrease) in performance based on the changes in the ambient temperature and / or pressure. Baffle vanes that are deployed to be oriented at a fixed angle are less effective at adequately cooling equipment within the gas turbine enclosure 12 when the ambient temperature, pressure, and air density change. These changes in ambient temperature, pressure, and air density can occur frequently and may have different patterns in different climates, months, or seasons (e.g., summer months vs. winter months), especially in geographic locations where there are significant temperature differences between summer and winter months, resulting in higher daily average temperatures in some months compared to other months where the daily average temperatures are lower. As a result, deploying controllable vanes 34 (e.g., rotating air directional baffle vanes) provides an effective solution for providing proper cooling and mixing of air for a variety of ambient temperatures, air densities, and pressures.

[0028] In some embodiments, the sensor 58 may not be present in or on the gas turbine enclosure 12. Thus, the controller 52 may include instructions that, when executed, can rotate the controllable vanes 34 according to a schedule that may be predetermined by using ambient pressure and temperature data over a particular period of time prior to operation of the controllable vanes 34, and actuate (e.g., rotate) the controllable vanes 34 according to the schedule.

[0029] A technical effect of the disclosed embodiments includes providing a system for ventilating a gas turbine enclosure surrounding a gas turbine engine. The ventilation air intake system 26 includes a controller 52 communicatively coupled to an actuator 32 coupled to a controllable vane 34. The controllable vane 34 automatically rotates about an axis 108 to direct air entering the gas turbine enclosure 12 from the ventilation air intake system 26. Specifically, the controller 52 sends commands to the actuator 32 to change the angular orientation of the controllable vane 34 to distribute, or more precisely, redistribute, the airflow within the gas turbine enclosure 12. This distribution, via redistribution of the airflow, may help to cool and / or equalize the temperature distribution within the gas turbine enclosure 12. The controllable vane 34 is particularly useful for enabling proper ventilation for equipment within the gas turbine enclosure 12 at various pressures and temperatures. Indeed, sensors 58 distributed within the gas turbine enclosure 12 may provide feedback (temperature, pressure, etc.) to the controller 52. In response to determining that a section of the gas turbine enclosure 12 contains a temperature or pressure differential, the controller 52, via the actuators 32, may rotate the controllable vanes 34 to a particular angular position or orientation or vary the frequency and / or amplitude of vibration of the controllable vanes 34. The disclosed systems and methods are designed to protect the gas turbine engine 16 and increase the efficiency of the ventilation air intake system 26 in accurately ventilating the gas turbine enclosure 12 at multiple ambient temperatures and pressures.

[0030] This specification uses examples to disclose the subject matter, including the best mode, and to enable those skilled in the art to practice the subject matter, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the subject matter is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims. [Explanation of symbols]

[0031] 10 Gas Turbine System 12 Gas Turbine Enclosure 14 Combustion air intake system 16 Gas Turbine Engine 18. Generator 20 Filters 22 Intake port 24 Shaft 26 Ventilation Air Intake System / Ventilation System 28 Filters 30 Baffle 32 Actuator 34 Controllable Vane 36 Intake port 38 Ports 40 Combustion Exhaust Duct 43 Ventilation exhaust duct 50 Air Intake 52 Controller 54 Memory 56 processors 58 Sensors 60 Air Flow 64 Exhaust outlet 70 Compressor 71 Air 72 Compressed Air 73 Exhaust Gas 74 Combustor 76 Fuel Nozzle 78 Turbine 80 Exhaust Section 82 Exhaust Gas 84 Shaft 86 Air Flow 88 Air Flow 90 Port 92 Ventilation Air 98 Axis 100 Axis 102 Axis 103 Axis 104 Section Section 106 108 Axis 110 Angle Orientation 112 Air Flow 114 Air Flow 116 Angular Orientation 118 Angular Orientation 130 Segmented Controllable Vane 132 First vane segment 134 First Actuator 136 Second vane segment 138 Second Actuator 160 method 162 blocks 164 blocks 166 blocks 168 blocks

Claims

1. A gas turbine enclosure (12); a gas turbine engine (16) disposed within the gas turbine enclosure (12), the gas turbine engine (16) configured to output an exhaust flow (64); A ventilation system (26) coupled to the gas turbine enclosure (12), the ventilation system (26) comprising: conduit, an intake port (36) between the gas turbine enclosure (12) and the ventilation system (26), the intake port (36) being an opening in a wall of the gas turbine enclosure (12), the intake port (36) extending across an interface between the conduit of the ventilation system (26) and the gas turbine enclosure (12); a vane (34) disposed across the intake port (36); an actuator (32) coupled to the vane (34); and a controller (52) coupled to the actuator (32), the controller (52) configured to cause the actuator (32) to vary a position of the vane (34) to modify airflow from the ventilation system (26) to the gas turbine enclosure (12), the vane (34) extending into the gas turbine enclosure (12) at several positions of the vane (34) caused by the actuator (32); A ventilation system (26) comprising: A system (10) comprising:

2. 2. The system (10) of claim 1, wherein the controller (52) is configured to vary the airflow from the ventilation system (26) to the gas turbine enclosure (12) based on feedback received from one or more sensors (58) disposed within the gas turbine enclosure (12).

3. The system (10) of claim 2, comprising one or more sensors (58) disposed within the gas turbine enclosure (12), the one or more sensors (58) comprising a temperature sensor, a pressure sensor, or both a temperature sensor and a pressure sensor.

4. 2. The system (10) of claim 1, wherein varying the position of the vane (34) to modify the airflow from the ventilation system (26) to the gas turbine enclosure (12) comprises rotating the vane (34) about an axis along a longitudinal length of the vane (34).

5. 5. The system (10) of claim 4, wherein the vane (34) is configured to be rotated between a fully open position and a closed position relative to a portion of the intake port (36), the fully open position enabling maximum airflow through the portion of the intake port (36) and the closed position preventing the airflow from entering the gas turbine enclosure (12) through the portion of the intake port (36).

6. 2. The system (10) of claim 1, wherein varying the position of the vanes (34) and modifying the airflow from the ventilation system (26) to the gas turbine enclosure (12) is configured to redistribute the airflow within the gas turbine enclosure (12) and minimize any hot spots within the gas turbine enclosure (12).

7. The system (10) of claim 1, wherein the actuator (32) comprises a motor.

8. The vane (34) comprises a first vane segment (132) and a second vane segment (136), the first vane segment (132) and the second vane segment (136). The system of claim 1 , wherein the segments are configured to move independently relative to one another.

9. 9. The system of claim 8, wherein the actuator comprises a first actuator coupled to the first vane segment and a second actuator coupled to the second vane segment, the first and second actuators being coupled to the controller.

10. The system (10) of claim 1, wherein the ventilation system (26) comprises a baffle disposed upstream of the vane (34).

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