Gas turbine module ventilation system with controllable vanes

Abstract

The present invention is entitled a gas turbine module ventilation system with controllable guide vanes. The present invention discloses a turbine ventilation system (26) including a controller (52) coupled to an actuator (32) coupled to a blade (34) disposed at an inlet (36) between a gas turbine housing (12) and the turbine ventilation system (26). The controller (52) can cause the actuator (32) to change the position of the blade (34) to alter the airflow entering the gas turbine housing (12) from the turbine ventilation system (26) based on feedback from one or more sensors (58) disposed within the gas turbine housing (12).

Description

Background Technology

[0001] The subject matter disclosed in this article relates to systems for ventilating gas turbine housings.

[0002] Gas turbine generators are commonly used to produce electricity for the power grid. They are typically stationary units located in power plants, such as integrated gasification combined cycle (IGCC) power plants. However, gas turbine generators can also be used as mobile units, such as large trailers. A gas turbine generator typically comprises a gas turbine engine enclosed in a housing (e.g., a gas turbine housing). To prevent heat buildup around the gas turbine engine, a ventilation system is included to remove heat from it. Unfortunately, the design of the ventilation system may limit the use of the gas turbine generator to environments with certain ambient temperature ranges and increase its operating costs. Furthermore, the ventilation system may not adequately cool the equipment within the gas turbine housing under all conditions (e.g., air density, temperature, etc.). Additionally, the ventilation system can consume significant amounts of electricity, thus reducing the efficiency of the gas turbine generator. Summary of the Invention

[0003] The following outlines some embodiments that are comparable to the scope of the originally claimed subject matter. These embodiments are not intended to limit the scope of the claimed subject matter, but are merely intended to provide a brief overview of the possible forms of this subject matter. In reality, this subject matter can encompass a variety of forms that may be similar to or different from the embodiments set forth below.

[0004] According to a first embodiment, the system includes a gas turbine housing and a gas turbine engine disposed within the gas turbine housing. The gas turbine engine outputs an exhaust flow. The system also includes a ventilation system coupled to the gas turbine housing. The ventilation system includes blades disposed at an intake port between the gas turbine housing and the ventilation system, an actuator coupled to the blades, and a controller coupled to the actuator. The controller can cause the actuator to change the position of the blades to alter the airflow entering the gas turbine housing from the ventilation system.

[0005] According to a second embodiment, a system includes a turbine ventilation system coupled to a gas turbine housing. The turbine ventilation system includes blades disposed at an inlet port between the gas turbine housing and the turbine ventilation system, an actuator coupled to the blades, and one or more sensors disposed within the gas turbine housing. The turbine ventilation system also includes a controller coupled to the actuator. The controller can cause the actuator to change the position of the blades to alter the airflow from the turbine ventilation system to the gas turbine housing based on feedback received from the one or more sensors.

[0006] According to a third embodiment, the system includes a gas turbine controller having a memory for storing instructions and a processor coupled to the memory and executing the instructions. When executing the instructions, the processor receives feedback from one or more sensors disposed within a gas turbine housing, the gas turbine housing having a gas turbine engine disposed therein. The processor executing the instructions also causes actuators coupled to blades to change the position of the blades to alter the airflow entering the gas turbine housing from a ventilation system, the blades being disposed at an inlet between the gas turbine housing and the ventilation system. Attached Figure Description

[0007] These and other features, aspects, and advantages of the subject matter of the invention will be better understood when the following detailed description is read with reference to the accompanying drawings, in which the same characters denote the same parts, wherein:

[0008] Figure 1 This is a schematic side view of an embodiment of a gas turbine generator in a gas turbine housing with a ventilation system having controllable blades, according to one embodiment.

[0009] Figure 2 It is a schematic block diagram of an embodiment of a ventilation system for a gas turbine system and a gas turbine housing, according to one embodiment;

[0010] Figure 3 This is a schematic diagram of an embodiment of a ventilation system for a gas turbine housing, according to one embodiment.

[0011] Figure 4 This is a schematic diagram of a controllable blade according to one implementation scheme;

[0012] Figure 5 It is along Figure 4 A cross-sectional view of the controllable blade taken from line 5-5 in the figure;

[0013] Figure 6 It is along Figure 4 A cross-sectional view of a controllable blade with multiple sections, taken from line 5-5; and

[0014] Figure 7 This is a flowchart of one aspect of a method for controlling a controllable blade, according to an implementation plan. Detailed Implementation

[0015] One or more specific embodiments of this disclosure will now be described. To provide a concise description of these embodiments, not all features of the actual implementation may be described in the specification. It should be understood that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developer's specific objectives, such as complying with system-related and business-related constraints, which may vary from implementation to implementation. Furthermore, it should be understood that such development work can be complex and time-consuming, but remains a routine task of design, fabrication, and manufacturing for those skilled in the art who benefit from this disclosure.

[0016] When describing elements of various embodiments of the subject matter of this invention, the articles “a,” “an,” “the,” and “described” are intended to refer to one or more elements present in the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that additional elements may be present in addition to the listed elements. Furthermore, the term “or” is intended to be inclusive, meaning that A or B includes A alone, B alone, or both A and B.

[0017] The embodiments disclosed in this invention relate to systems and methods for ventilating the casing of a gas turbine engine. Proper ventilation of equipment (e.g., a gas turbine engine) eliminates unwanted emissions within the casing and provides cooling within the casing. In the disclosed embodiments, the ventilation system includes controllable blades (e.g., guide vanes) disposed at an inlet between the ventilation system and the gas turbine casing, which guide airflow from the ventilation system into the gas turbine casing. The controllable blades, actuated by an actuator, can be moved, for example, to a range of locations to provide increased airflow distribution to desired locations within the gas turbine casing. The blades can be automatically controlled by a controller. In some embodiments, the controller can adjust the blades based on feedback (pressure, temperature, etc.) from sensors disposed within the gas turbine casing. The controllable blades also provide cooling and mixing of air within the gas turbine module under a range of air density and temperature conditions. Proper air distribution provides optimal cooling performance (e.g., by minimizing hot spots within the casing) so that equipment within the casing can operate within its respective rated temperature limits. Specifically, the disclosed embodiments can protect the gas turbine engine by effectively promoting airflow (e.g., cooling distribution) under various air densities and boundary conditions throughout the gas turbine housing.

[0018] Turn to the attached diagram. Figure 1This is a schematic side view of an embodiment of a gas turbine system 10 within a gas turbine housing 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 to filter air (e.g., combustion air) entering the gas turbine engine 16. Particles to be filtered by the combustion air intake system 14 may include ice and / or other solid particles that may be harmful to components within the gas turbine system 10 (e.g., compressor blades, turbine blades, etc.). In some embodiments, the combustion air intake system 14 may include other structures, such as air shrouds, air intake ports, and muffler deflectors. The combustion air intake system 14 receives air and, after processing (e.g., filtering), directs the air through intake port 22 into the gas turbine engine 16. After being compressed and mixed with fuel, the air, or more precisely, the air-fuel mixture, is combusted. The energy generated in the gas turbine engine 16 is used to rotate the shaft 24, which is connected to the generator 18. In other embodiments, the shaft 24 may be connected to other devices or systems such as a motor.

[0019] Additionally, the gas turbine system 10, housed within the gas turbine housing 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, deflectors 30, and actuators 32 coupled to blades 34 (e.g., controllable blade arms or deflectors) that direct the ventilation air to a desired location within the gas turbine housing 12. Controllable blades 34 are positioned at a port 36 (e.g., an intake port) between the ventilation air intake system 26 and the gas turbine housing 12. A controller enables the controllable blades 34 to be automatically controlled. The controller can adjust the controllable blades 34 based on feedback received from sensors disposed within the gas turbine housing 12. This allows the distribution of ventilation air to be varied as needed based on changes in conditions within the gas turbine housing 12. Air enters the gas turbine housing 12 from the ventilation air intake system 26 through 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. Ventilation airflow can exit the gas turbine housing 12 via ventilation exhaust duct 43. Gas exhaust (e.g., exhaust gas) from the gas turbine engine 16 can exit the gas turbine housing 12 via port 38 connected to combustion exhaust duct 40.

[0020] Furthermore, components of the gas turbine engine 16 housed within the gas turbine housing 12 can be subjected to temperature differences based on their location within the gas turbine housing 12 (e.g., one-dimensional, two-dimensional, or three-dimensional). For example, one or more components of the gas turbine engine 16 can emit (e.g., diffuse) heat into a volume or section within the gas turbine housing 12, causing that volume or section to have a higher temperature relative to another volume or section within the gas turbine housing 12. Without proper cooling, if the problem is not addressed, this emitted heat can lead to a reduction in the performance or lifespan of one or more components or functions of the gas turbine system 10. For example, if the emitted heat is not addressed, the cylinder block of the gas turbine 16 can exceed its rated temperature limit. Similarly, ambient temperature can vary throughout the operation of the gas turbine system 10 due to sunlight absorbed, for example, at a section (e.g., a wall) of the gas turbine housing 12. Variations in ambient temperature throughout the day (or at another time of operation of the gas turbine system 10) can create hot spots within the gas turbine housing 12, which can change location as frequently as variations in ambient temperature. In practice, hot spots (e.g., sections, regions, or volumes within the gas turbine housing 12 containing high temperatures relative to other sections, areas, or volumes within the gas turbine housing 12) can occur at various locations within the gas turbine housing 12 throughout the operation of the gas turbine system 10. Furthermore, changes in gas pressure during the operation of the gas turbine system 10 can cause pressure differentials within the gas turbine housing 12 (e.g., pressure differences between different locations within the gas turbine housing 12). Similar to temperature differences, pressure differentials can occur at different locations at different points in time during the operation of the gas turbine engine 16, as pressure conditions can change frequently throughout the operation of the gas turbine engine 16. Without addressing these pressure differentials, the performance or even the lifespan of one or more components of the gas turbine system 10 may be degraded. Replacement of the gas turbine engine 16, the gas turbine cylinder block, and the gas turbine housing 12 can be costly. Therefore, a system for maximizing the performance and / or lifespan of the gas turbine module is desirable.

[0021] Figure 2This is a schematic block diagram of an embodiment of a ventilation air intake system 26 for a gas turbine system 10 and a gas turbine housing 12. Specifically, the ventilation air intake system 26 is coupled to an air inlet 50 that receives air to be treated (e.g., filtered). As described above, the ventilation air intake system 26 includes one or more filters 28, a deflector 30, and an actuator 32 (e.g., a positioner, a motor, etc.) coupled to a controllable blade 34 that directs airflow (as indicated by arrow 60) into the gas turbine housing 12. The controller 52 includes computer-readable instructions (e.g., non-transitory, tangible, and computer-readable medium / 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 read-only memory (ROM)), an optical drive, a hard disk drive, or a solid-state drive. Additionally, 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 those integrated circuits referred to as processors in the art, but broadly refers to computers, processors, microcontrollers, microcomputers, programmable logic controllers, ASICs, and other programmable circuits. Processor 56 and memory 54 may work together to support operating systems, software applications, and systems that can be used to implement the techniques described herein. For example, memory 54 may store temperature and pressure ranges or limits for various sections of the gas turbine housing 12. Memory 54 may also store the desired location of the controllable blades 34, for example, in a lookup table. The lookup table can provide controller 52 with a mechanism for low-latency access to instructions used to control the controllable blades 34.

[0022] Additionally, the controller 52 is communicatively coupled to one or more sensors 58 (e.g., temperature sensors, thermal sensors, pressure sensors, etc.) distributed throughout the gas turbine housing 12. Based on feedback from the sensors 58 (e.g., temperature data, pressure data, etc.), the controller 52 can cause the actuator 32 to change the position or orientation of the controllable blades 34. In practice, the controller 52 can utilize the feedback to guide the controllable blades 34 to a position that would result in an increase in the distribution of cooling air. For example, the controller 52 can compare the feedback to a range of threshold values. These threshold ranges can represent desired operating parameters (e.g., temperature, pressure, etc.) for a location within the gas turbine housing 12. When feedback from the sensors 58 determines that a section of the gas turbine housing 12 has a hot spot and / or a pressure differential, the controller 52 can send a command to the actuator 32 to change the position or orientation of the controllable blades 34, thereby providing cooling or airflow to that section. For example, the controllable blades 34 can be actuated to oscillate (e.g., swing back and forth) at a specific frequency between a first position or first angular orientation and a second position or second angular orientation based on feedback. Additionally, as will be discussed in detail later, the amplitude of the angular displacement of the controllable blade 34 between a first angular orientation and a second angular orientation can be dynamically controlled, thereby directing ventilation air to a specific section of the gas turbine housing 12. Furthermore, the controller 52 can cause the controllable blade 34 to rotate to or remain in a specific angular orientation for a specific amount of time to direct or alter airflow from the ventilation air intake system 26 to a specific section of the gas turbine housing 12 that experiences hot spots and / or pressure differentials. By changing aspects of the controllable blade 34 (e.g., angular orientation or position, oscillation frequency and / or amplitude), the ventilation air intake system 26 can provide appropriate airflow within the gas turbine housing 12 (e.g., by altering the distribution of cool air) to minimize any hot spots within the gas turbine housing 12.

[0023] For example, such as Figure 2 As shown, the combustion air intake system 14 guides combustion air through the filter 20 and into the gas turbine system 10. (As indicated...) Figure 1 As shown, the guided combustion airflow exits the gas turbine housing 12 through port 38 (as indicated by arrow 38) and enters the exhaust outlet 64, which includes ducts such as combustion exhaust duct 40 and ventilation exhaust duct 43. Figure 2 (Not shown in the image). Similarly, ventilation airflow can exit the gas turbine housing 12 through port 90 (as indicated by arrow 90) and enter the ventilation exhaust duct 43.

[0024] Figure 3 This is a schematic diagram of an embodiment of a ventilation air intake system 26 (e.g., a ventilation system) for the gas turbine housing 12 and the gas turbine system 10. The air intake ventilation system 26 and the gas turbine system 10 are not shown in the diagram. Figure 3 It is not fully shown, but generally as Figure 1and 2 As described above. The gas turbine system 10 includes a gas turbine engine 16 disposed within a gas turbine housing 12. As indicated by arrow 71, air flows from a combustion air intake system 14 into a compressor 70 to be compressed in one or more compression stages. The compressed air 72 is then directed to a combustor 74, which is coupled to a fuel nozzle 76. In some embodiments, multiple fuel nozzles may be located in each combustor 74. At the combustor 74, the compressed air 72 is mixed with fuel and combusted, producing a thermocompressed exhaust gas. As indicated by arrow 82, each combustor 74 directs the exhaust gas through a turbine 78 to an exhaust section 80. As indicated by arrow 73, the exhaust section 80 directs the exhaust gas to a combustion exhaust duct 40. As the exhaust gas passes through the turbine 78, the gas forces the turbine blades in the turbine 78 to rotate the shaft 84 along the axis of the gas turbine engine 16. That is, the energy from the combustion mixture causes the turbine blades in the turbine 78 to rotate. The blades in turbine 78 are connected to shaft 84, which is also connected to various components of gas turbine engine 16, including compressor 70. Thus, when shaft 84 rotates, the compressor blades within compressor 70 also rotate, thereby compressing air through compressor 70. Shaft 84 can also be connected to a load, such as a generator in a power plant (e.g., generator 18).

[0025] To ventilate the gas turbine housing 12, air from the ventilation air intake system 26 is directed through one or more filtration stages (e.g., Figure 3 The air, initially filtered (not shown as filter 28), is then guided by a deflector 30 (e.g., a deflector, splitter, or partition) toward a controllable blade 34 (as shown by arrow 86), which in turn directs the air into the gas turbine housing 12 (as shown by arrow 88). After ventilation of the gas turbine housing 12, the ventilation air travels through port 90 (as shown by arrow 92). The ventilation air is then directed through port 90 into the ventilation exhaust duct 43 (as shown by arrow 92).

[0026] Specifically, the direction of air flowing into the gas turbine housing 12 can be guided at least partially by controllable blades 34, which are automatically controlled (e.g., rotated) by actuators 32. Specifically, actuators 32 (e.g., motors) are coupled to controllable blades 34 and move controllable blades 34 in response to commands received from controllers 52. That is, as described above, one or more sensors 58 (e.g., thermal sensors, pressure sensors, etc.) are disposed throughout the gas turbine housing 12 and contain circuitry for measuring various parameters (e.g., temperature and / or pressure). Sensors 58 can be coupled to controllers 52 via wireless or wired connections. Therefore, controllers 52 receive feedback from sensors 58 via wireless or wired connections and command actuators 32 to change the angular orientation or position of controllable blades 34. Furthermore, sensors 58 can be attached to the walls of the gas turbine housing 12, directly to various components of the gas turbine system 10, and / or to the cylinder block of the gas turbine engine 16. For example, controller 52 may receive measurements from one or more sensors 58 indicating an increase in ambient temperature and / or pressure in a location or region of the gas turbine housing 12. In response to determining that the gas turbine housing 12 (or gas turbine module) experiences an increase in ambient temperature and / or pressure in a particular section, the angular orientation, oscillation frequency (e.g., rotational frequency), or oscillation amplitude of the controllable blades 34 may be modified (e.g., altered, changed, updated) to change the distribution of supplied air, thereby improving cooling of the entire gas turbine housing 12 (e.g., minimizing hot spots). Commands may also be sent via controller 52 to actuator 32 when measurements from sensor 58 indicate a decrease in ambient temperature and / or pressure.

[0027] The movement of the controllable blade 34 can be continuous or incremental. That is, for continuous movement, the controllable blade 34 can rotate from a first angular orientation or a first position to a second angular orientation or a second position, wherein the movement of the controllable blade 34 does not stop at any angular orientation or position between completing the rotation from the first angular orientation or the first position to the second angular orientation or the second position. Incremental movement of the controllable blade 34 allows it to stop at different preset positions or angular orientations along a path between the closed position and the fully open position.

[0028] Figure 4This is a schematic side view of the deflector 30 (e.g., a directional airflow deflector) and the controllable blades 34. Axis 98 is along the width of the controllable blades 34, axis 100 is along the longitudinal length of the gas turbine housing 12, and axis 102 is along the height of the gas turbine housing 12. Specifically, the deflector 30 at least partially guides air leaving the ventilation air intake system 26 and entering the gas turbine housing 12 through section 104 or section 106 of port 36. The deflector 30 is located within the duct of the ventilation air intake system 26 and may extend through a region perpendicular to or substantially perpendicular to the duct of the ventilation air intake system 26. The deflector 30 effectively splits the airflow indicated by arrow 86 into two parts, causing the airflow to exit the duct of the ventilation air intake system 26 through section 104 or section 106. In some embodiments, the deflector 30 may extend only through a portion of the duct. Downstream of the deflector 30 is a controllable blade 34 disposed at port 36 between the ventilation air intake system 26 and the gas turbine housing 12. The controllable blade 34 rotates circumferentially about axis 108 (parallel to axis 98). The controllable blade 34 rotates about axis 108 in response to an actuator 32 changing its angular orientation to alter (e.g., modify, shift, redirect) the airflow from the ventilation air intake system 26 to the gas turbine housing 12. In practice, the actuator 32 (e.g., a motor) applies torque to the controllable blade 34, causing it to rotate about axis 108. Therefore, based on the angular orientation of the controllable blade 34, air exiting the ventilation air intake system 26 and entering the gas turbine housing 12 is directed to a specific location. Specifically, the angle at which the airflow enters the gas turbine housing 12 is determined by the angular orientation of the controllable blade 34 relative to axis 103. Different positions or angular orientations can direct the ventilation airflow to different locations within the gas turbine housing 12. For example, when the controllable blade 34 is in angular orientation 110 about axis 108, arrow 112 corresponds to the approximate direction of the airflow appearing through section 104, and arrow 114 corresponds to the approximate direction of the airflow appearing through section 106. A shift in the angular orientation of the controllable blade 34 can cause a change in the angle at which the airflow appears through sections 104 and 106. Therefore, based on the angular orientation of the controllable blade 34, the airflow is controlled to penetrate the gas turbine housing 12 in different directions as indicated by arrows 112 and 114.

[0029] Furthermore, the controllable blade 34 is capable of rotating between a fully open position and a closed position (relative to sections 104 and 106). The fully open position relative to section 104 corresponds to angular orientation 116, where minimum airflow occurs through section 106 and maximum airflow occurs through section 104. The closed position of the controllable blade 34 relative to section 104 corresponds to angular orientation 118, where minimum airflow occurs through section 104 and maximum airflow occurs through section 106. Similarly, the fully open position of the controllable blade 34 relative to section 106 corresponds to angular orientation 118, where minimum airflow occurs through section 104 and maximum airflow occurs through section 106. The closed position of the controllable blade 34 relative to section 106 corresponds to angular orientation 116, where minimum airflow occurs through section 106 and maximum airflow occurs through section 104. Therefore, the closed position of the controllable blade 34 relative to section 104 corresponds to the fully open position of the controllable blade 34 relative to section 106. Furthermore, the closed position of the controllable blade 34 relative to section 106 corresponds to the fully open position of the controllable blade 34 relative to section 104. In some embodiments, the controllable blade 34 is axially positioned along axis 100 and extends across the entire port 36. In these embodiments, the closed position may correspond to the minimum airflow through both sections 104 and 106, while the fully open position corresponds to the maximum airflow through both sections 104 and 106. Furthermore, as mentioned above, the rotation of the controllable blade 34 can be continuous or incremental. The controllable blade 34 can be actuated or controlled to be oriented to multiple angular orientations to provide appropriate air cooling distribution to the components of the gas turbine system 10 within the gas turbine housing 12. Finally, in Figure 4 In the middle, the ventilation airflow leaves the gas turbine housing 12 through port 90 and enters the ventilation exhaust duct 43.

[0030] Figure 5 It is along Figure 4 The image shows a cross-sectional view of the controllable blade 34 taken from line 5-5. Specifically, due to the torque applied by the actuator 32, the controllable blade 34 rotates about axis 108, which runs along the longitudinal length of the controllable blade 34. The controllable blade 34 may be made of metal (such as iron), plastic, alloy (such as steel), or another material capable of guiding the airflow from the ventilation air intake system 26 into the gas turbine housing 12.

[0031] like Figure 6As shown, in some embodiments, the controllable blade 34 may be segmented into two parts. Specifically, the segmented controllable blade 130 includes a first blade segment 132 having a first actuator 134 and a second blade segment 136 having a second actuator 138. The first blade segment 132 and the second blade segment 136 rotate about axis 108 and move independently of 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 blade segment 132 without sending a command to the second actuator 138 to change the position or angular orientation of the second blade segment 136. Alternatively, the controller 52 may send commands to both the first actuator 134 and the second actuator 138 to change the position or angular orientation of the first blade segment 132 and the second blade segment 136 respectively, such that they execute the command simultaneously. As shown, the segmented controllable blade 130 includes two segments 132, 136. In some embodiments, the number of blade segments may vary (e.g., 3, 4 or more). Furthermore, in some embodiments, the segments may be coupled to the same actuator. In other embodiments, the ventilation air intake system 26 includes more than one rotatable blade, wherein each blade is located at a different axial position relative to the axis 100 along the port 36. In this case, the airflow from the ventilation air intake system 26 can be more precisely directed in a specific direction within the gas turbine housing 12.

[0032] Figure 7This is a flowchart of an embodiment of a method 160 for ventilating a gas turbine housing 12. In some embodiments, one or more steps of method 160 may be performed by a controller 52. Method 160 includes receiving one or more operating parameters from sensors 58 distributed throughout the gas turbine housing 12 at block 162. Sensors 58 may detect temperature, pressure, or other parameters at one or more locations throughout the gas turbine housing 12. For example, as described above, the temperature and pressure of the gas turbine housing 12 may change throughout the entire operating period of the gas turbine engine 16, as ambient temperature and pressure may fluctuate within that period (e.g., hours, days, months, etc.). When the temperature and / or pressure changes, sensors 58 may detect one or more hot spots, and sensors 58 provide feedback (e.g., temperature and / or pressure data) to the controller 52. At block 164, method 160 also includes determining whether the received operating parameters are within the expected range of the current operation of the rotating blades (e.g., controllable blade 34). The current operation of the rotating blades may correspond to the current oscillation amplitude and / or frequency, or angular orientation or position of the rotating blades. For example, controller 52 can determine, based on feedback, whether it is necessary to change the characteristics of the rotating blade (i.e., oscillation amplitude and / or frequency, or current angular orientation or position) to achieve proper cooling and air distribution within the gas turbine housing 12. When it is determined that the received operating parameters are within a predetermined range (e.g., pressure range and / or temperature range), method 160 continues to maintain the current operation of the rotating blade at block 166. That is, it does not change one aspect of the current operation of the rotating blade (e.g., oscillation amplitude or frequency, or angular position or orientation). In response to determining that the received operating parameters are not within a predetermined range (e.g., pressure range and / or temperature range), the method continues to change one aspect of the current operation of the rotating blade (e.g., changing the oscillation frequency or amplitude, or angular orientation or position) at block 168. Thus, controller 52 can cause the rotating blade to change its angular orientation or position, and / or the oscillation frequency and amplitude of the rotating blade. For example, in response to determining that the operating parameters are not within the desired range, controllable blade 34 can automatically increase its motion frequency and amplitude.

[0033] In addition to providing improvements for cooling the gas turbine casing 12 under varying ambient temperatures and pressures, this embodiment of the controllable blades 34 is particularly suitable for geographical locations that experience significant variations in environmental conditions over a day, a season (e.g., summer, winter, etc.), a year, or another period of time. Climate change causes the ambient temperature and pressure boundary conditions in the gas turbine casing 12 to change frequently throughout the operation of the gas turbine system 10. Specifically, as ambient temperature and / or pressure increases or decreases, the components in the gas turbine casing 12 (e.g., the gas turbine system 10) are affected by performance changes (e.g., reductions) based on changes in ambient temperature and / or pressure. When ambient temperature, pressure, and air density change, guide vane blades deployed at a fixed angle are less efficient for properly cooling the equipment in the gas turbine casing 12. These changes in ambient temperature, pressure, and air density can occur frequently and exhibit different patterns in different climates, months, or seasons (e.g., summer months versus winter months), particularly in geographical locations with significant temperature differences between summer and winter months, where, for example, the average daily temperature is higher compared to another month with a lower average daily temperature. Therefore, deploying controllable blades 34 (e.g., rotating air-directing guide blades) provides an effective solution for providing proper cooling and air mixing under a range of ambient temperatures, air densities, and pressures.

[0034] In some embodiments, sensor 58 may not be present in or on the gas turbine housing 12. Therefore, controller 52 may include instructions that, upon execution, cause the controllable blade 34 to rotate according to a schedule, which can be predetermined using data on ambient pressure and temperature over a specific time period prior to the operation of the controllable blade 34, such that the controllable blade 34 is actuated (e.g., rotated) according to the schedule.

[0035] The technical effects of the disclosed embodiments include providing a system for ventilating the gas turbine housing surrounding a gas turbine engine. The ventilation air intake system 26 includes a controller 52 communicatively coupled to an actuator 32, which is coupled to a controllable blade 34. The controllable blade 34 rotates automatically about an axis 108 and directs air from the ventilation air intake system 26 into the gas turbine housing 12. Specifically, the controller 52 sends commands to the actuator 32 to change the angular orientation of the controllable blade 34 to cause the airflow to be distributed, or more precisely, redistributed, within the gas turbine housing 12. This redistribution of airflow can help cool the gas turbine housing 12 and / or equalize the temperature distribution within the gas turbine housing 12. The controllable blade 34 is particularly suitable for allowing proper ventilation of equipment within the gas turbine housing 12 under varying pressures and temperatures. In practice, sensors 58 distributed throughout the gas turbine housing 12 can provide feedback (temperature, pressure, etc.) to the controller 52. In response to determining that a section of the gas turbine housing 12 contains a temperature or pressure difference, the controller 52 may, via the actuator 32, rotate the controllable blades 34 to certain angular positions or orientations, or change the oscillation frequency and / or amplitude of the controllable blades 34. The disclosed systems and methods are designed to protect the gas turbine engine 16 and improve the efficiency of the ventilation air intake system 26 in adequately ventilating the gas turbine housing 12 under various ambient temperatures and pressures.

[0036] This written description uses examples to disclose the subject matter, including best practices, and also enables any person skilled in the art to practice the subject matter, including making and using any device or system and performing any combined methods. The patentable scope of the subject matter is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are contemplated within the scope of the claims if they have structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A system comprising: Gas turbine housing (12); A gas turbine engine (16), the gas turbine engine (16) being disposed within the gas turbine housing (12), wherein the gas turbine engine (16) is configured to output an exhaust flow (64); and A ventilation system (26) is disposed outside the gas turbine housing (12) and connected to the gas turbine housing (12), wherein the ventilation system (26) comprises: A deflector (30) located in the duct of the ventilation system (26) is adapted to at least partially guide air through a first section (104) or a second section (106) of the air inlet port (36) out of the ventilation system (26) and into the gas turbine housing (12); the air inlet port (36) is located between the gas turbine housing (12) and the ventilation system (26); Blade (34), the blade (34) is disposed on the air intake port (36), wherein the blade (34) is located downstream of the deflector (30); Actuator (32), said actuator (32) being coupled to said blade (34); and A controller (52) is coupled to the actuator (32), wherein the controller (52) is configured to cause the actuator (32) to change the position of the blade (34) to change the airflow from the ventilation system (26) into the gas turbine housing (12); The change in the angular orientation of the blade (34) causes a change in the angle at which the airflow leaves the first section (104) and the second section (106) of the air intake port (36).

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

3. The system according to claim 2, wherein the ventilation system (26) includes the one or more sensors (58) disposed within the gas turbine housing (12), and the one or more sensors (58) include a temperature sensor, a pressure sensor, or both the temperature sensor and the pressure sensor.

4. The system according to claim 1, wherein changing the position of the blade (34) to change the airflow from the ventilation system (26) into the gas turbine housing (12) comprises rotating the blade (34) about an axis along the longitudinal length of the blade (34).

5. The system of claim 4, wherein the blade (34) is configured to rotate between a fully open position and a closed position relative to a portion of the inlet port (36), wherein the fully open position allows maximum airflow to pass through the portion of the inlet port (36), and the closed position prevents the airflow from entering the gas turbine housing (12) via the portion of the inlet port (36).

6. The system of claim 1, wherein changing the position of the blade (34) to change the airflow from the ventilation system (26) into the gas turbine housing (12) is configured to redistribute the airflow within the gas turbine housing (12) to minimize any hot spots within the gas turbine housing (12).

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

8. The system of claim 1, wherein the blade (34) comprises a first leaf segment (132) and a second leaf segment (136), and the first leaf segment (132) and the second leaf segment (136) are configured to move independently of each other.

9. The system of claim 8, wherein the actuator (32) comprises a first actuator (134) coupled to the first leaf segment (132) and a second actuator (138) coupled to the second leaf segment (136), and the first actuator (134) and the second actuator (138) are coupled to the controller (52).

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