Patent Description:
Gas turbine generators are often used to produce electricity for a power grid. The gas turbine generators are typically stationary units disposed in a power plant, such as an integrated gasification combined cycle (IGCC) power plant. However, the gas turbine generators also may be used in mobile units, such as large trailers. The gas turbine generators typically include a gas turbine engine enclosed within an enclosure (e.g., gas turbine enclosure). In order to avoid a buildup of heat around the gas turbine engine, the gas turbine generators include ventilation systems to carry heat away from the gas turbine engine. Unfortunately, the designs of the ventilation systems may limit the use of the gas turbine generators to environments within certain ambient temperature ranges and increase the operating costs of the gas turbine generators. In addition, the ventilation systems may not properly cool equipment within the gas turbine enclosure under all conditions (e.g., air densities, temperatures, etc.). Further, the ventilation systems may draw a considerable amount of power, and thus reduce the efficiency of the gas turbine generators.

<CIT> discloses a power generation device comprising a generator chamber and a turbine chamber that are connected by a communication duct. The power generation device's structure is simplified by feeding air to the turbine chamber from the generator chamber through the communication duct.

<CIT> discloses an airflow control system for a gas turbine system comprising an airflow generation system; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting at least a portion of the excess flow of air generated by the airflow generation system to provide bypass air; an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

<CIT> discloses a turbine ventilation system including at least one fan configured to provide a first air flow into a gas turbine enclosure, a fan bypass configured to circumvent the at loast one fan to provide a second air flow into the gas turbine enclosure and an educator configured to draw the first or second air flow through and out of the gas turbine enclosure.

The inventions refers to a system according to claim <NUM>.

These and other features, aspects, and advantages of the present subject matter will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:.

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 elements. Furthermore, the term "or" is intended to be inclusive indicating that A or B includes A alone, B alone, or both A and B.

The disclosed embodiments are directed to a system for ventilating enclosures that surround gas turbine engines. Proper ventilation of equipment (e.g., gas turbine engine) removes undesired emissions within the enclosure, as well as providing cooling within the enclosure. In the disclosed embodiments, a ventilation system includes a controllable vane (e.g., baffle vane) disposed across an intake port between the ventilation system and a gas turbine enclosure that directs air flow from the ventilation system in the gas turbine enclosure. The controllable vane, being actuated by an actuator, for example, is movable to a range of positions to provide for an increased distribution of air flow to a desired location within the gas turbine enclosure. The vane may be automatically controlled by a controller. In certain embodiments, the controller may adjust the vane based on feedback (pressure, temperature, etc.) from sensors disposed within the gas turbine enclosure. The controllable vane also provides for cooling and mixing of air in the gas turbine module for a range of air densities and temperature conditions. Proper air distribution may provide optimum cooling performance (e.g., by minimizing hot spots within the enclosure) to enable the equipment within the enclosure to operate within their respective rated temperature limits. In particular, the disclosed embodiments may protect gas turbine engines by effectively facilitating air flow (e.g., cooling distribution) in a plurality of air densities and boundary conditions throughout a gas turbine enclosure.

Turning to the figures, <FIG> is a schematic side view of an embodiment of a gas turbine system <NUM> in a gas turbine enclosure <NUM>. The gas turbine system <NUM> includes a combustion air intake system <NUM>, a gas turbine engine <NUM>, and a generator <NUM> (e.g., electrical generator) that is powered by the gas turbine engine <NUM>. The combustion air intake system <NUM> includes one or more filters <NUM> to filter air (e.g., combustion air) entering the gas turbine engine <NUM>. Particles to be filtered by the combustion air intake system <NUM> 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 <NUM>. In some embodiments, other structures may be included in the combustion air intake system <NUM> such as air hoods, air intake ports, and silencer baffles to name a few. The combustion air intake system <NUM> receives air and after processing the air (e.g., filtering), directs the air through intake port <NUM> and into gas turbine engine <NUM>. After being compressed and mixed with fuel, the air, or rather, the air-fuel mixture, combusts. The energy produced in the gas turbine engine <NUM> is used to rotate a shaft <NUM> that is coupled to the generator <NUM>. In other embodiments, the shaft <NUM> may be coupled to other devices or systems such a motor.

Additionally, the gas turbine system <NUM>, being housed in the gas turbine enclosure <NUM>, receives ventilation air from a ventilation air intake system <NUM> (e.g., ventilation system). The ventilation air intake system <NUM> includes one or more filters <NUM>, a baffle <NUM>, and an actuator <NUM> that is coupled to a vane <NUM> (e.g., controllable vane arm or baffle) that directs ventilation air to desired locations within the gas turbine enclosure <NUM>. The controllable vane <NUM> is disposed across a port <NUM> (e.g., intake port) between the ventilation air intake system <NUM> and the gas turbine enclosure <NUM>. A controller enables the controllable vane <NUM> to be automatically controlled. The controller may adjust the controllable vane <NUM> based on feedback received from sensors disposed within the gas turbine enclosure <NUM>. This enables a distribution of the ventilation air to be altered as needed based on changes in conditions within the gas turbine enclosure <NUM>. Air enters the gas turbine enclosure <NUM> from the ventilation air intake system <NUM> through the port <NUM>. Although not shown, in some embodiments, ventilation air intake system <NUM> may include other elements, structures, systems, or devices such as one or more fans. Ventilation air flow may exit the gas turbine enclosure <NUM> via a ventilation exhaust duct <NUM>. Gaseous emissions (e.g., exhaust gases) from the gas turbine engine <NUM> may exit the gas turbine enclosure <NUM> through a port <NUM>, which is coupled to a combustion exhaust duct <NUM>.

Furthermore, components of gas turbine engine <NUM> housed in gas turbine enclosure <NUM> may be subject to temperature differentials based upon a location (e.g., one dimensional, two dimensional, or three-dimensional position) in the gas turbine enclosure <NUM>. For instance, one or more components of the gas turbine engine <NUM> may emit (e.g., diffuse) heat into a volume or section within the gas turbine enclosure <NUM> such that the volume or section has a high temperature relative to another volume or section in the gas turbine enclosure <NUM>. Without proper cooling, this emitted heat may cause one or more components or functions of the gas turbine system <NUM> to have a reduction in performance or lifespan if not addressed. For example, without addressing the emitted heat, a casing of the gas turbine <NUM> may exceed a rated temperature limit. Likewise, ambient temperature may change throughout an operation of the gas turbine system <NUM> due to the gas turbine system <NUM> and/or, for example, sun rays that may be absorbed at a section (e.g., a wall) of the gas turbine enclosure <NUM>. The changes in ambient temperature throughout a day (or another time period of an operation of the gas turbine system <NUM>) may induce hot spots in the gas turbine enclosure <NUM> that may change locations as frequently as ambient temperature changes. Indeed, hot spots (e.g., sections, areas, or volumes in the gas turbine enclosure <NUM> containing high temperatures relative to other sections, areas, or volumes in the gas turbine enclosure <NUM>) may appear in various locations inside of the gas turbine enclosure <NUM> throughout the operation of the gas turbine system <NUM>. Further, during an operation of the gas turbine system <NUM>, changes in barometric pressure may cause pressure differentials in the gas turbine enclosure <NUM> (e.g., pressure differences between different locations in the gas turbine enclosure <NUM>) to be induced. Like the temperature differentials, the pressure differentials may arise in different locations at different points in time of the operation of the gas turbine engine <NUM>, since pressure conditions can frequently change throughout the operation of the gas turbine engine <NUM>. Without addressing the pressure differentials, one or more components of the gas turbine system <NUM> may have a reduction in performance, or even in lifespan. Gas turbine engines <NUM>, gas turbine casings, and gas turbine enclosures <NUM> may be costly to replace. Thus systems that function to maximize the performance and/or lifespan of gas turbine modules are desirable.

<FIG> is a schematic block diagram of an embodiment of the ventilation air intake system <NUM> for the gas turbine system <NUM> and the gas turbine enclosure <NUM>. In particular, the ventilation air intake system <NUM> is coupled to an air intake <NUM>, which receives air that is to be processed (e.g., filtered). As aforementioned, the ventilation air intake system <NUM> includes one or more filters <NUM>, the baffle <NUM>, and the actuator <NUM> (e.g., positioner, motor, etc.) that is coupled to the controllable vane <NUM> which directs air flow (as indicated by arrows <NUM>) into the gas turbine enclosure <NUM>. A controller <NUM> contains computer-readable instructions stored in memory <NUM> (e.g., non-transitory, tangible, and computer-readable medium/memory circuitry) and a processor <NUM> which executes the instructions. More specifically, the memory <NUM> may include volatile memory, such as random access memory (RAM), and/or non-volatile memory, such as read-only memory (ROM), optical drives, hard disc drives, or solid-state drives. Additionally, the processor <NUM> 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 just those integrated circuits referred to in the art as processors, but broadly refers to computers, processors, microcontrollers, microcomputers, programmable logic controllers, application specific integrated circuits, and other programmable circuits. The processor <NUM> and memory <NUM> may be used collectively to support an operating system, software applications and systems, and so forth, useful implementing the techniques described herein. For example, the memory <NUM> may store temperature and pressure ranges or limits of for sections of the gas turbine enclosure <NUM>. The memory <NUM> may also store desired positions for the controllable vane <NUM> in, for example, look-up tables. The look up tables may provide a mechanism for the controller <NUM> to access instructions for controlling the controllable vane <NUM> with low latency.

Also, the controller <NUM> is communicatively coupled to one or more sensors <NUM> (e.g., temperature sensors, thermal sensors, pressure sensors, etc.) disposed through the gas turbine enclosure <NUM>. Based upon feedback (e.g., temperature data, pressure data, etc.) from sensors <NUM>, the controller <NUM> may cause the actuator <NUM> to change a position or orientation of the controllable vane <NUM>. Indeed, feedback may be utilized by the controller <NUM> to direct the controllable vane <NUM> to positions that may cause in increase in cooling air distribution. For example, the controller <NUM> may compare feedback to threshold ranges for feedback. These threshold ranges may represent a desired operating parameter (e.g., temperature, pressure, etc.) for a location within the gas turbine enclosure <NUM>. Upon a determination that a section of the gas turbine enclosure <NUM> has a hot spot and/or a pressure differential based on the feedback from the sensors <NUM>, the controller <NUM> may send a command to the actuator <NUM> to alter a position or orientation of the controllable vane <NUM> to provide cooling or air flow to the section. For instance, the controllable vane <NUM> may be actuated to oscillate (e.g., swing back and forth) at a certain frequency between a first position or first angular orientation and a second position or second angular orientation based on feedback. Also, as will be discussed in detail later, an amplitude of an angular displacement of the controllable vane <NUM> between the first angular orientation and the second angular orientation may be dynamically controlled so that ventilation air is directed to specific section(s) of the gas turbine enclosure <NUM>. Further, the controller <NUM> may cause the controllable vane <NUM> to rotate to or remain at a specific angular orientation for a specific amount of time to direct or alter an air flow from the ventilation air intake system <NUM> to a specific section of the gas turbine enclosure <NUM> enduring a hot spot and/or pressure differential. By altering an aspect (e.g., an angular orientation or position, oscillation frequency and/or amplitude) of the controllable vane <NUM>, the ventilation air intake system <NUM> may provide proper air flow (e.g., via altering of distribution cool air) within the gas turbine enclosure <NUM> to minimize any hot spot within the gas turbine enclosure <NUM>.

On another note, as shown in <FIG>, combustion air intake system <NUM> directs combustion air through a filter <NUM> and into the gas turbine system <NUM>. As mentioned in <FIG>, the directed combustion air flow exits the gas turbine enclosure <NUM> through the port <NUM> (as indicated by an arrow <NUM>) and goes into an exhaust flow output <NUM>, which includes conduits such as the combustion exhaust duct <NUM> and the ventilation exhaust duct <NUM> (not shown in <FIG>). Similarly, the ventilation air flow may exit the gas turbine enclosure <NUM> through a port <NUM> (as indicated by an arrow <NUM>) and proceed into the ventilation exhaust duct <NUM>.

<FIG> is a schematic view of an embodiment of the ventilation air intake system <NUM> (e.g., ventilation system) for the gas turbine enclosure <NUM> and gas turbine system <NUM>. The air intake ventilation system <NUM> and the gas turbine system <NUM>, although not fully shown in <FIG>, are as generally described in <FIG> and <FIG>. The gas turbine system <NUM> includes the gas turbine engine <NUM> disposed in the gas turbine enclosure <NUM>. Air flows from combustion air intake system <NUM> into compressor <NUM> to be compressed at one or more compression stages (as indicated by arrows <NUM>. Compressed air <NUM> is then directed into combustors <NUM>, which are coupled to fuel nozzles <NUM>. In some embodiments, multiple fuel nozzles may be in each combustor <NUM>. At the combustor <NUM>, compressed air <NUM> is mixed with fuel and is combusted, creating hot pressurized exhaust gases. Each combustor <NUM> directs the exhaust gases through a turbine <NUM> toward an exhaust section <NUM> as indicated by arrows <NUM>. The exhaust section <NUM> directs the exhaust gases toward the combustion exhaust duct <NUM> as indicated by arrows <NUM>. As the exhaust gases pass through the turbine <NUM>, the gases force turbine blades in the turbine <NUM> to rotate a shaft <NUM> along an axis of the gas turbine engine <NUM>. That is, energy from the combusted mixture cause turbine blades in the turbine <NUM> to rotate. The blades in the turbine <NUM> are coupled to the shaft <NUM> which is also coupled to various components of the gas turbine engine <NUM> including the compressor <NUM>. Even so, as the shaft <NUM> rotates, compressor blades within the compressor <NUM> also rotate, thereby compressing air through the compressor <NUM>. The shaft <NUM> may also be connected to a load, such as an electrical generator (e.g., generator <NUM>) in an electrical power plant, for example.

In order to ventilate the gas turbine enclosure <NUM>, air from the ventilation air intake system <NUM> courses through one or more filter stages (e.g., filters <NUM> not shown in <FIG>) and then is directed by the baffle <NUM> (e.g., baffle plate, diverter plate, divider plate) towards the controllable vane <NUM> (as indicated by arrows <NUM>), which then directs the air into the gas turbine enclosure <NUM> (as indicated by arrows <NUM>). After ventilating the gas turbine enclosure <NUM>, the ventilating air proceeds through the port <NUM> (as indicated by arrow <NUM>). The ventilating air is then directed to enter the ventilation exhaust duct <NUM> (as indicated by the arrow <NUM>) via the port <NUM>.

In particular, the direction of the air flowing into the gas turbine enclosure <NUM> may be guided, at least in part, by the controllable vane <NUM>, which is automatically controlled (e.g., rotated) by the actuator <NUM>. Specifically, the actuator <NUM> (e.g., motor) is coupled to the controllable vane <NUM> and moves the controllable vane <NUM> in response to commands received from the controller <NUM>. That is, as discussed above, one or more sensors <NUM> (e.g., thermal sensors, pressure sensors, etc.) are disposed throughout gas turbine enclosure <NUM> and contain circuitry to measure various parameters (e.g., temperature and/or pressure). The sensors <NUM> may be coupled to the controller <NUM> via a wireless or wired connection. Accordingly, the controller <NUM> receives feedback from the sensors <NUM> via the wireless or wired connection, and commands the actuator <NUM> to change an angular orientation or position of the controllable vane <NUM>. Further, the sensors <NUM> can be attached to the walls of the gas turbine enclosure <NUM>, directly on various components of the gas turbine system <NUM>, and/or on the casing of the gas turbine engine <NUM>. For example, the controller <NUM> may receive measurements from one or more sensors <NUM> that are indicative of an increased ambient temperature and/or pressure in a location or region of the gas turbine enclosure <NUM>. In response to determining that the gas turbine enclosure <NUM> (or gas turbine module) is experiencing an increase in ambient temperature and/or pressure at a specific section, the angular orientation, oscillation frequency (e.g., frequency of rotation), or amplitude of oscillation of the controllable vane <NUM> may be modified (e.g., changed, altered, updated) in order change the distribution of air provided to improve the cooling throughout the gas turbine enclosure <NUM> (e.g., to minimize hot spots). Commands may also be sent to the actuator <NUM>, via the controller <NUM>, when measurements from sensors <NUM> are indicative of a decreased ambient temperature and/or pressure.

The motion of the controllable vane <NUM> may be a continuous motion or an incremental motion. That is, for a continuous motion, the controllable vane <NUM> may rotate from a first angular orientation or first position to a second angular orientation or second position without the motion of the controllable vane <NUM> ceasing at any angular orientation or position in between the completion of the rotation from the first angular orientation or first position to the second angular orientation or second position. The incremental motion of the controllable vane <NUM> may be such that the controllable vane <NUM> ceases motion at different preset positions or angular orientations along a path between a closed position and a fully open position.

<FIG> is a schematic side view of the baffle <NUM> (e.g., a directional air flow baffle) and the controllable vane <NUM>. An axis <NUM> is along a width of the controllable vane <NUM>, an axis <NUM> is along a longitudinal length of the gas turbine enclosure <NUM>, and an axis <NUM> is along a height of the gas turbine enclosure <NUM>. Specifically, the baffle <NUM>, at least in part, directs the air that exits the ventilation air intake system <NUM> and enters the gas turbine enclosure <NUM> through a section <NUM> or a section <NUM> of the port <NUM>. The baffle <NUM> is located in a conduit of the ventilation air intake system <NUM> and may extend across a region perpendicular or approximately perpendicular to the conduit of the ventilation air intake system <NUM>. The baffle <NUM> may effectively cause the air flow that is indicated by arrows <NUM> to divide into two portions such that the air flow exits the conduit of the ventilation air intake system <NUM> through the section <NUM> or the section <NUM>. In some embodiments, the baffle <NUM> may only extend across a portion of the conduit. Downstream of the baffle <NUM> is the controllable vane <NUM>, which is disposed across the port <NUM> between the ventilation air intake system <NUM> and gas turbine enclosure <NUM>. The controllable vane <NUM> rotates in a circumferential direction about an axis <NUM> (which is parallel to the axis <NUM>). The controllable vane <NUM> rotates about the axis <NUM> in response to the actuator <NUM> changing an angular orientation of the controllable vane <NUM> to alter (e.g., modify, shift, redirect) the air flow from the ventilation air intake system <NUM> into the gas turbine enclosure <NUM>. Indeed the actuator <NUM> (e.g., motor) applies torque to the controllable vane <NUM> such that it rotates about the axis <NUM>. Consequently, based on the angular orientation of the controllable vane <NUM>, air emerging out of the ventilation air intake system <NUM> and into the gas turbine enclosure <NUM> is directed to a particular location. Specifically, an angle at which an air flow enters into the gas turbine enclosure <NUM> is determined by the angular orientation of the controllable vane <NUM> relative to the axis <NUM>. Different positions or angular orientations may direct the ventilating air flow to different locations within the gas turbine enclosure <NUM>. For example, when the controllable vane <NUM> is at an angular orientation <NUM> about the axis <NUM>, arrow <NUM> corresponds to the general direction of the air flow emerging through the section <NUM> and arrow <NUM> corresponds to the general direction of the air flow emerging through the section <NUM>. A shift in the angular orientation of the controllable vane <NUM> can cause a change in the angle at which the air flow emerging through section <NUM> and section <NUM>. Thus, based upon the angular orientation of the controllable vane <NUM>, the air flow is controlled to penetrate the gas turbine enclosure <NUM> in different directions as indicated by arrows <NUM>, <NUM>.

Further, the controllable vane <NUM> is able to rotate between a fully open position and a closed position (relative to sections <NUM> and <NUM>). The fully open position relative to section <NUM> corresponds to an angular orientation <NUM> whereby minimum air flow emerges through section <NUM> and maximum air flow emerges through the section <NUM>. The closed position of the controllable vane <NUM> relative to the section <NUM> corresponds to an angular orientation <NUM> whereby minimum air flow emerges through section <NUM> and maximum air flow emerges through the section <NUM>. Further, the fully open position of the controllable vane <NUM> relative to section <NUM> corresponds to the angular orientation <NUM> whereby minimum air flow emerges through the section <NUM> and maximum air flow emerges through the section <NUM>. The closed position of the controllable vane <NUM> relative to the section <NUM> corresponds to the angular orientation <NUM> whereby minimum air flow emerges through the section <NUM> and maximum air flow emerges through the section <NUM>. Thus, the closed position of the controllable vane <NUM> relative to the section <NUM> corresponds to the fully open position of the controllable vane <NUM> relative to the section <NUM>. Moreover, the closed position of the controllable vane <NUM> relative to the section <NUM> corresponds to the fully open position of the controllable vane <NUM> relative to the section <NUM>. In some embodiments, the controllable vane <NUM> is axially located along the axis <NUM> and extends across the entire port <NUM>. In these embodiments, the closed position may correspond to minimum air flow through both the section <NUM> and the section <NUM>, while a fully opened position corresponds to maximum air flow through both sections <NUM> and <NUM>. Further, as aforementioned, the rotation of the controllable vane <NUM> may be continuous or incremental. The controllable vane <NUM> may be actuated or controlled to orient to a plurality of angular orientations to provide a proper air cooling distribution for components of the gas turbine system <NUM> within the gas turbine enclosure <NUM>. Finally, in <FIG>, the ventilation air flow exits the gas turbine enclosure <NUM> through the port <NUM> and proceeds into the ventilation exhaust duct <NUM>.

<FIG> is a cross-sectional view of the controllable vane <NUM> taken along line <NUM>-<NUM> in <FIG>. In detail, the controllable vane <NUM> is rotated about the axis <NUM>, which is along a longitudinal length of the controllable vane <NUM>, due to torque applied by the actuator <NUM>. The controllable vane <NUM> may be made of a metal such as iron, a plastic, an alloy such as steel, etc., or another material that is capable of directing the air flow that emerges from the ventilation air intake system <NUM> into gas turbine enclosure <NUM>.

As shown in <FIG>, in some embodiments, the controllable vane <NUM> can be segmented into two parts. Specifically, a segmented controllable vane <NUM> has a first vane segment <NUM> having a first actuator <NUM> and a second vane segment <NUM> having a second actuator <NUM>. The first vane segment <NUM> and the second vane segment <NUM> rotate about the axis <NUM> and move independently relative to each other. Thus, for example, the controller <NUM> can send a command to the first actuator <NUM> to change a position or angular orientation of the first vane segment <NUM> without sending a command to the second actuator <NUM> to change a position or angular orientation of the second vane segment <NUM>. Also, the controller <NUM> may send a command to both the first actuator <NUM> and the second actuator <NUM> to change a position or angular orientation of the first vane segment <NUM> and the second vane segment <NUM> respectively such that they execute the command simultaneously. As depicted, the segmented controllable vane <NUM> includes two segments <NUM>, <NUM>. In some embodiments, the number of vane segments may vary (e.g., <NUM>, <NUM>, or more). Further, in some embodiments, the segments may be coupled to the same actuator. In other embodiments, the ventilation air intake system <NUM> includes more than one rotatable vane with each vane located at a different axial location along the port <NUM> relative to the axis <NUM>. In this case, the air flow from the ventilation air intake system <NUM> may be more precisely guided to specific directions in the gas turbine enclosure <NUM>.

<FIG> is a flow chart of an embodiment of a method <NUM> for ventilating the gas turbine enclosure <NUM>, not falling under the claimed subject matter. In certain embodiments, one or more steps of the method <NUM> may be executed by the controller <NUM>. The method <NUM> includes receiving one or more operating parameters from sensors <NUM> disposed throughout the gas turbine enclosure <NUM> at block <NUM>. The sensors <NUM> may detect a temperature, pressure, or other parameter at one or more locations throughout the gas turbine enclosure <NUM>. For example, as discussed above, the temperature and pressure of the gas turbine enclosure <NUM> may change throughout a time period of operation of the gas turbine engine <NUM>, since ambient temperatures and pressures may fluctuate during the time period (e.g., hours, days, months, etc.). As the temperature and/or pressure changes, one or more hot spots may be detected by the sensors <NUM>, which provide feedback (e.g., temperature and/or pressure data) to the controller <NUM>. At block <NUM>, the method <NUM> also includes determining if the received operating parameters are within a desired range for a current operation of a rotating vane (e.g., controllable vane <NUM>). The current operation of the rotating vane can correspond to a current oscillation amplitude and/or frequency or angular orientation or position of the rotating vane. For instance, the controller <NUM> may determine based on the feedback if a characteristic (i.e. oscillation amplitude and/or frequency or a current angular orientation or position) of the rotating vane needs to be changed for proper cooling and air distribution within the gas turbine enclosure <NUM>. Upon determining that the received operating parameter(s) are within a predetermined range (e.g., pressure range and/or temperature range), the method <NUM> proceeds with maintaining the current operation of the rotating vane at block <NUM>. That is, an aspect of the current operation (e.g., amplitude or frequency of oscillation or an angular position or orientation) of the rotating vane is not changed. In response to determining that the received operating parameter(s) are not within a predetermined range (e.g., pressure range and/or temperature range), the method, at block <NUM>, proceeds with changing an aspect of the current operation of the rotating vane (e.g., changing a frequency or amplitude of oscillation or an angular orientation or position). Consequently, the controller <NUM> may cause the rotating vane to change an angular orientation or position, and/or a frequency and amplitude of oscillation of the rotating vane. For example, in response to determining that the operating parameter(s) are not within a desired range, the controllable vane <NUM> may be automated to increase its frequency and amplitude of motion.

Besides providing an improvement for cooling a gas turbine enclosure <NUM> in varying ambient temperatures and pressures, the present embodiments of the controllable vane <NUM> may be particularly useful in geographical locations that endure significant changes in environmental conditions through a day, a season (e.g., summer, winter, etc.), a year, or another time period. Climate changes induce ambient temperatures and pressure boundary conditions in the gas turbine enclosure <NUM> that can frequently change throughout an operation of the gas turbine system <NUM>. Specifically, as ambient temperatures and/or pressures increase or decrease, elements in the gas turbine enclosure <NUM> (e.g., gas turbine system <NUM>) are subject to changes (e.g., decreases) in performance based on the changes in ambient temperature and/or pressure. Baffle vanes that are deployed to be oriented at a fixed angle are less effective in properly cooling equipment in the gas turbine enclosure <NUM> when ambient temperatures, pressures, and air densities change. These changes in ambient temperature, pressures, and air densities, may occur frequently and have different patterns in different climates, months, or seasons (e.g., summer months versus winter months) especially in geographical locations that have significant temperature differences between summer and winter months, whereby, for example, an average daily temperature is higher as compared with another month where the average daily temperature is lower. Consequently, deploying the controllable vane <NUM> (e.g., rotating air directional baffle vane) provides an effective solution to providing proper cooling and mixing of air for a range of ambient temperatures, air densities, and pressures.

In some embodiments, sensors <NUM> may not be present in or on the gas turbine enclosure <NUM>. As such, the controller <NUM> may contain instructions that upon execution may cause the controllable vane <NUM> to rotate in accordance with a schedule that may be predetermined by using data of ambient pressures and temperatures over a specific amount of time before an operation of the controllable vane <NUM>, and causing the controllable vane <NUM> to be actuated (e.g., rotated) in accordance with the schedule.

Claim 1:
A system, comprising:
a gas turbine enclosure (<NUM>);
a gas turbine engine (<NUM>) disposed in the gas turbine enclosure (<NUM>), wherein the gas turbine engine (<NUM>) is configured to output an exhaust flow (<NUM>); and
a ventilation system (<NUM>) coupled to the gas turbine enclosure (<NUM>), wherein the ventilation system (<NUM>) comprises:
a baffle (<NUM>) located in a conduit of the ventilation system (<NUM>) and adapted to direct, at least in part, air exiting the ventilation system (<NUM>) and entering the gas turbine enclosure (<NUM>) through a first section (<NUM>) or a second section (<NUM>) of an intake port (<NUM>); the intake port (<NUM>) being between the gas turbine enclosure (<NUM>) and the ventilation system (<NUM>);
a vane (<NUM>) disposed across the intake port (<NUM>), wherein the vane (<NUM>) is located downstream the baffle (<NUM>);
an actuator (<NUM>) coupled to the vane (<NUM>); and
a controller (<NUM>) coupled to the actuator (<NUM>), wherein the controller (<NUM>) is configured to cause the actuator (<NUM>) to change a position of the vane (<NUM>) to alter an air flow from the ventilation system (<NUM>) into the gas turbine enclosure (<NUM>) comprising rotating the vane (<NUM>) about an axis along a longitudinal length of the vane (<NUM>),
characterized in that a shift in the angular orientation of the controllable vane (<NUM>) causes a change in the angle at which the airflow emerges from the first section (<NUM>) and the second section (<NUM>) of the intake port (<NUM>).