System for cooling turbine shaft couplings

Abstract

To provide a system for cooling a turbine shaft coupling.SOLUTION: Cooling systems for ventilating a turbine 20 and a rotary shaft 14 of a gas turbine system 10 are provided. The gas turbine system comprises a gas turbine engine 12 and a turbine exhaust collection pipe 13 in enclosures 2, 3. A first cooling system 104 comprises an educator 72 which sucks exhaust gas through a diffuser 41, and directs it out of the turbine exhaust collection pipe enclosure 3 on the basis of suction pressure created from the high velocity exhaust gas. A second cooling system 102 comprises a strut 98 which enables the exhaust gas to flow from the diffuser to a ventilation flow stack. A third cooling system 100 includes exhaust gas sucked from an opening to a top duct 68 on the basis of suction pressure created from the rotation of the rotary shaft. A guideway introduces the exhaust gas to flow to the top duct 68. These cooling systems increase the efficiency of ventilating the turbine 20 and the rotary shaft 14.SELECTED DRAWING: Figure 2

Description

Technical Field

[0001] The subject matter disclosed herein relates to cooling a turbine shaft joint of a gas turbine system, such as a turbine shaft joint downstream of an exhaust outlet of the gas turbine system.

Background Art

[0002] Gas turbine systems can be used for various applications such as power generation. For example, a gas turbine generator can include a generator driven by a gas turbine to generate electricity for a power grid or a local facility. A gas turbine system generally includes one or more shafts and associated joints for connection to a load such as a generator. In certain configurations, the shaft and joint can be located downstream of the exhaust outlet, such that a significant amount of heat transfer from the exhaust gas to the shaft and joint can occur. Unfortunately, this heat transfer can cause thermal expansion and stress in the joint, which can then cause misalignment of the shaft and associated vibrations. As a result, heat transfer to the shaft and joint can cause performance problems, maintenance problems, and downtime in the gas turbine system. Therefore, it is necessary to cool the turbine shaft joint.

Summary of the Invention

[0003] Certain embodiments corresponding to the scope of the invention claimed at the time of filing are summarized below. These embodiments are not intended to limit the scope of the claimed invention; rather, these embodiments are only intended to provide an overview of possible forms of the invention. Of course, the invention can include various forms that may be similar to or different from the embodiments described below.

[0004] In the first embodiment, the system comprises a turbine exhaust manifold having a first enclosure with an exhaust inlet and an exhaust outlet, and a diffuser coupled to the exhaust inlet. The diffuser comprises an inner diffuser wall arranged around a cavity having a rotating shaft, an outer diffuser wall arranged around the inner diffuser wall, and an exhaust passage between the inner and outer diffuser walls. The turbine exhaust manifold also comprises a first cooling passage extending through a cavity having a rotating shaft, and the first enclosure is separate from a second enclosure surrounding a gas turbine.

[0005] In a second embodiment, the system comprises a turbine exhaust manifold having a diffuser comprising an inner diffuser wall positioned around a cavity having a rotating shaft, an outer diffuser wall positioned around the inner diffuser wall, and an exhaust passage between the inner and outer diffuser walls. The turbine exhaust manifold also comprises a duct extending through the cavity along the inner diffuser wall toward the turbine rear frame, the rotating shaft being coupled to a turbine shaft extending through a bore of the turbine rear frame, a first cooling passage extending through the duct to guide a first cooling flow toward the turbine rear frame, and a leakage flow between the turbine shaft and the turbine rear frame being configured to provide an attractive force for drawing in the first cooling flow through the duct.

[0006] In a third embodiment, the system includes a turbine exhaust manifold. The turbine exhaust manifold comprises a diffuser having an inner diffuser wall positioned around a cavity having a rotating shaft, an outer diffuser wall positioned around the inner diffuser wall, and an exhaust passage between the inner and outer diffuser walls. The rotation of the rotating shaft is configured to drive a first cooling flow along a first cooling passage through the cavity.

[0007] These and other features, aspects, and advantages of the present invention will be better understood by reading the following descriptions of embodiments for carrying out the invention with reference to the accompanying drawings, and throughout the drawings, similar reference numerals represent similar parts. [Brief explanation of the drawing]

[0008] [Figure 1] This is a schematic diagram of one embodiment of a gas turbine system, showing a cooling system configured to cool the turbine shaft and coupling assembly within an enclosure having an exhaust manifold downstream of the turbine section. [Figure 2] This is a schematic diagram of one or more embodiments of a cooling system in an enclosure having an exhaust manifold. [Figure 3] This is a schematic diagram of one embodiment of the cooling system shown in Figure 2, illustrating the discharge flow conduit (e.g., eductor) within the inner diffuser wall of the exhaust manifold diffuser. [Figure 4] Figure 3 is a partial cross-sectional view of the inner diffuser wall having a discharge flow conduit (e.g., an eductor) taken within the arc-shaped line 4-4, further illustrating the details of the cooling system. [Figure 5] Figure 4 shows a cross-sectional view of the inner diffuser wall having a discharge flow conduit (e.g., an eductor) taken along line 5-5, further illustrating the details of the baffle and the corresponding opening (e.g., a single continuous opening). [Figure 6] A cross-sectional view of the inner diffuser wall having a discharge flow conduit (e.g., an eductor) taken along line 5-5 in Figure 4, further illustrating the baffle and the details of the multiple discontinuous openings. [Figure 7] Figures 1 and 2 are schematic diagrams of one embodiment of the cooling system shown. [Figure 8] Figure 7 is a schematic cross-sectional view of one embodiment of the cooling system, showing the configuration of discharge flow conduits arranged at intervals in the circumferential direction with the diffuser axis as the center. [Figure 9] Figures 1 and 2 are schematic diagrams of one embodiment of the cooling system shown. [Figure 10]Further details of various flow induction mechanisms are shown in the partial side view of the turbine shaft and coupling assembly taken within line 10-10 in Figure 9. [Figure 11] Figure 9 is a partial side view of the divertor plate adjacent to the inlet of the discharge flow conduit, further illustrating the details of the divertor plate. [Modes for carrying out the invention]

[0009] A gas turbine generator may comprise a gas turbine engine housed in an enclosure and a turbine exhaust manifold housed in a separate enclosure. To avoid heat buildup around the turbine shaft located within the gas turbine engine coupled to the rotating shaft located within the turbine exhaust manifold, the gas turbine generator includes one or more cooling systems to carry heat away from the turbine and rotating shaft. Unfortunately, the design of the ventilation system can limit the use of the gas turbine generator to environments within a specific ambient temperature range, increasing the operating costs of the gas turbine generator. Furthermore, the ventilation system consumes a considerable amount of electricity and can therefore reduce the efficiency of the gas turbine generator.

[0010] The disclosed embodiments relate to a system for ventilating and cooling a turbine shaft and coupling assembly located within a gas turbine system. The gas turbine system comprises a gas turbine engine and a turbine exhaust manifold, and the gas turbine system may be coupled to one or more intake systems, a variable bleed valve (VBV) flow tube, a ventilation flow tube, and an exhaust flow tube. The turbine shaft, located within the gas turbine engine enclosure, is coupled to the turbine shaft and coupling assembly located within the turbine exhaust manifold enclosure. The enclosures surrounding the gas turbine engine and the turbine exhaust manifold may be separate. To prevent heat buildup around the turbine shaft and coupling assembly, one or more cooling systems may be located within the turbine exhaust manifold enclosure. One or more cooling systems, together with the variable bleed valve (VBV) flow tube, the ventilation flow tube, and the exhaust flow tube, can purge and ventilate heat and exhaust products associated with the turbine shaft and coupling assembly. In certain embodiments, the disclosed cooling system uses the ventilation flow within the gas turbine engine enclosure to draw a coolant flow from the turbine exhaust manifold enclosure, particularly from the cavity containing the turbine shaft and coupling assembly. In certain embodiments, the disclosed cooling system uses the exhaust flow within the exhaust diffuser of the exhaust manifold to draw a coolant flow from the cavity containing the turbine shaft and coupling assembly. In certain embodiments, the disclosed cooling system uses the rotation of the turbine shaft and coupling assembly to help push a coolant flow out of the cavity containing the turbine shaft and coupling assembly. These cooling systems are designed to cool the turbine shaft and coupling assembly, thereby reducing the possibility of thermal expansion of the turbine shaft and coupling assembly, reducing thermal stress, and reducing the possibility of shaft displacement.

[0011] Figure 1 is a schematic block diagram of one embodiment of a gas turbine system 10 having multiple ventilation or cooling systems 11. The gas turbine system 10 comprises a gas turbine engine 12, a turbine exhaust manifold 13, an enclosure 2 (e.g., a turbine housing or turbine chamber) positioned around the gas turbine engine 12, and an enclosure 3 (e.g., an exhaust manifold housing) positioned around the turbine exhaust manifold 13. As will be described in detail below, the cooling systems 11 are configured to ventilate and cool the turbine shaft and coupling assembly 14 positioned inside the turbine exhaust manifold 13 within the enclosure 3, thereby helping to maintain the temperature of the turbine shaft and coupling assembly 14 below a threshold temperature as the hot exhaust gas flow passes through the turbine exhaust manifold 13. The disclosed embodiments of the cooling systems 11 may be used individually or in any combination with each other.

[0012] The gas turbine engine 12 comprises a compressor section having one or more compressors 16 (e.g., 1 to 30 compressor stages) each having a plurality of compressor blades 15; a combustor section having one or more combustors 18 (e.g., annular combustors or multiple combustor cans) each having one or more fuel nozzles 17; and a turbine section having one or more turbines 20 (e.g., 1 to 30 turbine stages) each having a plurality of turbine blades 19. As shown in the figure, the turbine section 20 is drivably coupled to the compressor section 16 by a shaft 21, and the turbine section 20 is drivably coupled to a load (e.g., a generator 22) via a turbine shaft and coupling assembly 14 extending through an enclosure 3 of the turbine exhaust manifold 13. During operation, the compressor section 16 compresses the air received from the engine intake section (e.g., intake duct or intake cylinder 23), and supplies the compressed air and fuel through the fuel nozzle 17 into the combustor section 18 for combustion to generate hot combustion gases. These hot combustion gases then flow through the turbine section 20 to drive the turbine blades 19 to rotate the shaft 21 and the turbine shaft and coupling assembly 14. The hot combustion gases are then discharged from the gas turbine system 10 through the exhaust manifold 13 and the combustion exhaust section (e.g., combustion exhaust duct or exhaust pipe 39). As will be described in more detail below, certain amounts of leakage flow (e.g., hot combustion gases, heated air, heated lubricant, etc.) may pass through the enclosure 3, particularly inside the exhaust manifold 13 in close proximity to the turbine shaft and coupling assembly 14. In addition, certain amounts of heat may be transferred through the walls of the enclosure 3 and / or the walls of the exhaust manifold 13 into the interior of the exhaust manifold 13 in close proximity to the turbine shaft and coupling assembly 14. The disclosed embodiments of the cooling system 11 are configured to help ventilate and cool the turbine shaft and coupling assembly 14, taking into account this leakage flow and heat transfer.

[0013] The gas turbine system 10 comprises a plurality of intake and exhaust systems coupled to enclosures 2 and 3. For example, the gas turbine system 10 comprises an engine intake section (e.g., an intake duct or intake cylinder 23) coupled to enclosure 2, extending inward into enclosure 2, and coupled to the intake port of compressor section 16. The intake duct 23 may comprise one or more air processing units 24 (e.g., an air filter, a silencer baffle, an anti-icing system, etc.) arranged along the air passage of the intake airflow entering the compressor section 16 through the intake duct 23, as indicated by arrow 25.

[0014] The gas turbine system 10 also includes a ventilation air intake section (e.g., a ventilation air intake duct or intake pipe 26) and a separate ventilation air exhaust section (e.g., a ventilation air exhaust duct or exhaust pipe 28) coupled to the enclosure 2 and fluidly coupled to the internal space or chamber 27 surrounding the gas turbine engine 12. In certain embodiments, the ventilation air intake duct 26 and / or ventilation air exhaust duct 28 include one or more fans 29 (e.g., electric motors with multiple protruding fan blades) configured to push the ventilation airflow inward, through the duct 26 along the intake passage as indicated by arrow 30, through the chamber 27 surrounding the gas turbine engine 12 along the cooling passage as indicated by arrow 31, and outward through the duct 28 along the exhaust passage as indicated by arrow 32, thereby helping to remove heat surrounding the gas turbine engine 12 to avoid heat buildup and control the temperature of the gas turbine engine 12. The ventilation air intake duct 26 also includes one or more air processing units, such as an air filter 33.

[0015] The gas turbine system 10 further comprises a compressor bleed system 34 coupled to a compressor section 16 and a compressor bleed exhaust section (e.g., a compressor bleed exhaust duct or exhaust stack 35). For example, in the illustrated embodiment, a compressor bleed line or conduit 36 ​​extends from at least one compressor stage of the compressor section 16 to the compressor bleed exhaust duct 35, and the conduit 36 ​​includes a variable bleed valve (VBV) 37 configured to change the bleed flow of compressed air extracted from the compressor section 16 and exhausted through the duct 35, as indicated by arrow 38. The VBV 37 is configured to help control the gas turbine engine 12 by bleeding compressed air from the compressor section 16, thereby allowing the amount of bleed flow to be varied according to various operating conditions of the gas turbine engine 12.

[0016] The gas turbine system 10 further comprises a combustion exhaust section (e.g., a combustion exhaust duct or exhaust pipe 39) configured to discharge the exhaust flow of combustion gases generated in the combustor section 18 of the gas turbine engine 12. In the illustrated embodiment, the combustion exhaust pipe 39 is coupled to the enclosure 3 above the turbine exhaust manifold 13. In particular, the combustion exhaust pipe 39 is fluidly coupled to the exhaust flow path 40 through the turbine exhaust manifold 13, which is fluidly coupled to the turbine section 20.

[0017] The turbine exhaust manifold 13 includes a diffuser 41 that at least partially defines an exhaust passage 40 from an exhaust inlet 42 of the enclosure 3 to an exhaust outlet 43 of the enclosure 3. The exhaust inlet 42 is coupled to an exhaust discharge opening of the turbine section 20, and the exhaust outlet 43 is coupled to a combustion exhaust pipe 39. In the illustrated embodiment, the diffuser 41 is coupled to the exhaust inlet 42 via an inner diffuser wall 44 and an outer diffuser wall 46. The inner diffuser wall 44 is positioned around (e.g., extending circumferentially around) a cavity 45 having a turbine shaft and coupling assembly 14 (e.g., a rotary shaft). The outer diffuser wall 46 is positioned around the inner diffuser wall 44 (e.g., extending circumferentially around) with a radial offset from the inner diffuser wall 44. The exhaust passage 40 is positioned between the inner diffuser wall 44 and the outer diffuser wall 46. For example, the exhaust passage 40 may extend circumferentially around the inner diffuser wall 44. The inner and outer diffuser walls 44 and 46 may be at least partially or completely annular walls (e.g., concentric annular walls) that gradually expand from the central axis 54 along the turbine shaft and coupling assembly 14 in the downstream flow direction, as indicated by arrow 40. For example, the inner and outer diffuser walls 44 and 46 may expand linearly or non-linearly (e.g., along a curved path) from the central axis 54, thereby allowing the inner and outer diffuser walls 44 and 46 to include conical wall portions and / or curved annular wall portions. In addition to expanding from the central axis 54, the inner and outer diffuser walls 44 and 46 may expand from each other downstream, as indicated by arrow 40, thereby increasing the offset distance (e.g., radial distance) between the inner diffuser wall 44 and the outer diffuser wall 46 in the downstream direction. In this way, the combustion gases flowing along the exhaust passage 40 gradually expand or diffuse before entering the combustion exhaust pipe 39.

[0018] As described above, the turbine shaft and coupling assembly 14 is located inside the cavity 45 within the inner diffuser wall 44 of the diffuser 41. The turbine shaft and coupling assembly 14 may include a coupling 48 between the first shaft or turbine shaft portion 47 and the second shaft or generator shaft portion 49. The turbine shaft and coupling assembly 14 may also include a number of bearings 50, such as a bearing 51 along the first shaft 47 and a bearing 52 along the second shaft 49. The bearing 51 may be located in a turbine rear frame (TRF) section or wall 53 located in the upstream portion of the cavity 45 closest to the turbine section 20. The TRF wall 53 is coupled to the inner diffuser wall 44, so that the TRF wall 53 and the inner diffuser wall 44 largely prevent combustion gases from entering the cavity 45. However, a certain amount of leakage flow may pass through the TRF wall 53, particularly in the bearing 51, and enter the cavity 45 housing the turbine shaft and coupling assembly 14. The cooling system 11 is configured to assist in the ventilation and cooling of the turbine shaft and coupling assembly 14, and thereby the cooling system 11 may be equipped with various cooling mechanisms for use individually or in combination with each other.

[0019] The cooling system 11 may include an air supply system 60 having one or more fans 61 (e.g., an electric motor-driven fan blade), a flow regulator 62 (e.g., a valve), and / or an air treatment unit 63 (e.g., an air filter). The air supply system 60 is configured to control the air flow (or other coolant flow) into the cavity 45 as indicated by arrow 64. Alternatively or additionally, the air supply system 60 may be configured to control the air flow out of the cavity 45 in a direction opposite to arrow 64. The cooling system 11 may also include one or more baffles or ducts for controlling the flow into and out of the cavity 45. For example, the cooling system 11 may include one or more intake ducts 65, 66 that extend into the cavity 45 through the enclosure 3, one or more discharge ducts 68 that exit the cavity 45 and extend through the enclosure 3 to the external environment, one or more discharge ducts 70 that extend from the cavity 45 through the diffuser 41 through the enclosure 3 to the internal chamber 27 of the enclosure 2 (i.e., into the cooling flow path 31), and / or one or more discharge ducts 72 that exit the cavity 66 and extend through the inner diffuser wall 44 into the exhaust flow path 40. These ducts 65, 66, 68, 70, and 72 can be used in various combinations to define a cooling flow path through the cavity 45.

[0020] For example, in a particular embodiment, one or more conduits 66 can supply a cooling flow (e.g., a cooling air flow) into the cavity 45, and then one or more conduits 68 can discharge the cooling flow directly from the cavity 45 to the external environment. One or more conduits 66 can define the path of the cooling flow close to the bearing 51, the TRF wall 53, and the leakage flow in the bearing 51 and the TRF wall 53. In this way, one or more conduits 66 can concentrate the cooling flow over high-temperature spots in the cavity 45. In a particular embodiment, one or more conduits 65 and / or 66 can supply a cooling flow (e.g., a cooling air flow) into the cavity 45, and one or more conduits 70 can discharge the cooling flow from the cavity 45 through the diffuser 41 into the internal chamber 27 of the enclosure 2, and then the ventilation air exhaust duct 28 can discharge the cooling flow from the enclosure 2 in combination with the ventilation flow through the enclosure 2. As will be described in more detail below, each of the one or more conduits 70 may be coupled to or integrated with struts extending between the inner diffuser wall 44 and the outer diffuser wall 46 of the diffuser 41. In certain embodiments, one or more conduits 65 and / or 66 can supply a cooling flow (e.g., a cooling air flow) into the cavity 45, and one or more conduits 72 can discharge the cooling flow from the cavity 45 into an exhaust passage 40 located between the inner diffuser wall 44 and the outer diffuser wall 46 of the diffuser 41. For example, the exhaust passage 40 can draw in or draw in the cooling flow from the cavity 45 through one or more conduits 72, thereby defining each of the conduits 72 as an eductor. Alternatively or additionally, an air supply system 60 may use a fan 61 to push the cooling flow into the cavity 45 and also push it out of the cavity 45 through the conduits 72 into the exhaust passage 40. As will be described in more detail below, the conduit 70 can be redirected or bent downstream of the exhaust flow along the exhaust passage 40, thereby generating an attractive force to draw the cooling flow into the exhaust passage 40 and / or help prevent backflow of the exhaust gas into the cavity 45.These cooling channels defined by conduits 65, 66, 68, 70, and 72 can represent individual cooling systems 11 and / or an integrated cooling system.

[0021] The cooling system 11 can also be configured to selectively control the cooling flow along the cooling channels through conduits 65, 66, 68, 70, and 72. Thus, in certain embodiments, each of the illustrated conduits 65, 66, 68, 70, and 72 can include a flow regulator 74 (e.g., a valve) configured to selectively control (e.g., partially or fully open or close) the flow rate of coolant (e.g., ventilation or cooling air) entering and exiting the cavity 45 to assist in controlling the temperature within the cavity 45. The cooling system 11 can also include a plurality of sensors 76, each designated individually as S, in the conduits 65, 66, 68, 70, and 72 and in the cavity 45. The sensors 76 are configured to monitor the temperature within the cavity 45 and / or the temperature of the turbine shaft and joint assembly 14, thereby assisting in controlling the cooling flow to maintain the temperature of the cavity 45 and / or the turbine shaft and joint assembly 14 below a threshold temperature. The sensors 76 can also monitor other operating parameters such as the flow rate of the cooling flow, the pressure within the cavity 45 and / or conduits 65, 66, 68, 70, 72, vibrations or noises associated with the turbine shaft and joint assembly 14, and thermal expansion or contraction of components (e.g., turbine shaft and joint assembly 14, enclosure 3, exhaust manifold 13, etc.). The cooling system 11 can also include a controller 78 coupled to the air supply system 60, the flow regulator 74, the fan 29, and the sensors 76.

[0022] The controller 78 may include one or more processors 79, a memory 80, and instructions 81 stored in the memory 80 that can be executed by the processor 79 to perform various monitoring functions using the sensor 76 and control functions using the cooling system 11 and the gas turbine system 10. The processor 79 may include one or more microprocessors, one or more "general-purpose" microprocessors, one or more dedicated microprocessors, and / or one or more application-specific integrated circuits (ASICs), or any combination thereof. For example, the processor 79 may include one or more reduced instruction set (RISC) processors. The memory 80 may include tangible, non-transient, machine-readable media such as volatile memory (e.g., random-access memory (RAM)) and / or non-volatile memory (e.g., read-only memory (ROM), flash memory, hard drives, or any other suitable optical, magnetic, or solid-state storage medium, or a combination thereof). The instructions 81 stored in the memory 80 include machine-readable instructions and / or processor-executable instructions (e.g., firmware or software) for execution by the processor 79. The controller 78 may also include an analog-to-digital (A / D) converter, input / output circuits, data processing circuits, monitoring circuits, and control circuits. The controller 78 may also include components for operator interaction with the system, such as a display panel and / or input / output devices for checking operating parameters, inputting control signals representing setpoints and desired operating parameters, and checking error logs and operating history.

[0023] During operation, in response to feedback from the sensor 76, the controller 78 may be configured to adjust the air supply system 60, the flow regulator 74, and / or the fan 29 to change (i.e., increase or decrease) the flow rate and / or temperature of the cooling flow through the cavity 45 to ventilate and cool the turbine shaft and coupling assembly 14. In certain embodiments, the controller 78 may be configured to control the cooling system 11 to supply cooling flow along cooling channels passing through one or all of the conduits 65, 66, 68, 70, and 72, or any number between one and all of them. The controller 78 may be configured to control the cooling system 11 based on feedback from the sensor 76, historical data and trends of operating parameters in the cavity 45 (e.g., temperature, pressure, flow rate, vibration, or noise), lookup tables that correlate the monitored sensor data with various control functions (e.g., target flow rates through conduits 66, 68, 70, and 72, target fan speeds for fans 29 and 61, target position of flow regulator 74, etc.), and computer models that correlate the monitored sensor data with control functions. The controller 78 may also be configured to control the cooling system 11 based on upper and lower threshold values ​​for operating parameters in the cavity 45 (e.g., temperature, pressure, flow rate, vibration, or noise, etc.). The controller 78 may also be configured to control the cooling system 11 based on various factors such as the operation of the gas turbine engine, ambient temperature, and relative humidity in the surrounding environment (i.e., outside the gas turbine system 10).

[0024] Figure 2 is a schematic side view of one embodiment of the gas turbine system 10 of Figure 1, showing the enclosure 2, which has the gas turbine engine 12, disassembled from the enclosure 3, which has the exhaust manifold 13. As shown, the enclosures 2 and 3 are separated from each other, with the side wall 90 of enclosure 2 facing the side wall 92 of enclosure 3. When the gas turbine system 10 is fully assembled as shown in Figure 1, the side walls 90 and 92 are positioned facing each other (or at least close to each other) at the interface 91. In certain embodiments, an upstream diffuser portion 94 may protrude from the side wall 92 of enclosure 3, and a diffuser recess 96 may extend into the side wall 90 of enclosure 2 adjacent to the turbine section 20. The upstream diffuser portion 94 may include a plurality of support struts 98 extending between the inner diffuser wall 44 and the outer diffuser wall 46 at a position upstream of the conduit 70. As fully assembled as shown in Figure 1, the upstream diffuser portion 94 extends into the diffuser recess 96 adjacent to the turbine section 20. However, other embodiments of the gas turbine system 10 may not include the upstream diffuser portion 94 and the diffuser recess 96, as shown in Figure 2.

[0025] As described above in relation to Figure 1, the gas turbine system 10 includes one or more cooling systems 11, which may be independent or integrated with one another. For example, the cooling system 11 may include a cooling system 100 comprising at least one or more intake flow conduits 65 and / or 66 and one or more discharge flow conduits 68, a cooling system 102 comprising at least one or more intake flow conduits 65 and / or 66 and one or more discharge flow conduits 70, and a cooling system 104 comprising at least one or more intake flow conduits 65 and / or 66 and one or more discharge flow conduits 72. These cooling systems 100, 102, and 104 may be used individually or in combination with one another as part of the cooling system 11. The cooling systems 11 (e.g., 100, 102, and / or 104) are configured to ventilate and / or cool the cavity 45 and the turbine shaft and coupling assembly 14.

[0026] Heat sources within the gas turbine system 10 may include heat transferred through leaks in the turbine rear frame (TRF) (e.g., leaks in the TRF wall 53), heat transferred from exhaust gases, heat transferred from the turbine shaft and coupling assembly 14 coupled to the shaft 21, and any combination thereof. TRF leaks 110 near the TRF wall 53 may transfer heat into the cavity 45. TRF leaks 110 may include leaks of heated fluids such as heated gases (e.g., heated air, hot exhaust gases, etc.) and / or heated liquids (e.g., heated lubricant), or heat transfer through the TRF wall 53. Along with TRF leaks 110, exhaust gases along the exhaust passage 40 may transfer heat into the cavity 45 through the inner diffuser wall 44 as indicated by arrow 112, and heat from within the turbine shaft and coupling assembly 14 may be transferred into the cavity 45 as indicated by arrow 114. Therefore, the TRF leak 110, heat transfer 112, and heat transfer 114 each contribute to the accumulation of heat within the cavity 45. To ventilate or cool the cavity 45 and the turbine shaft and coupling assembly 14, one or more cooling systems 11 (e.g., 100, 102, and / or 104) circulate a coolant flow through the cavity 45.

[0027] As described above, the turbine shaft and coupling assembly 14 is coupled to the shaft 21 of the gas turbine engine 12 and the shaft of the generator 22, and the bearings 50 (e.g., bearings 51 and 52) provide rotational support for the shafts 47 and 49 of the turbine shaft and coupling assembly 14. The bearings 51 may include ball bearings, roller bearings, perforated sleeve bearings, sliding bearings, and any combination thereof. The bearings 51 may be configured to absorb axial or radial loads. The bearings 51 may be provided with one or more seals (e.g., elastomer and / or metal seal rings) within the bearing housing to prevent fluid leakage (e.g., gas and / or liquid leakage) along the respective shafts, e.g., the shafts 47 and 49 of the turbine shaft and coupling assembly 14. However, some leakage may occur in the bearings 51, such as TRF leakage 110 as described above. Unfortunately, leakage (e.g., TRF leakage 110) can also transfer heat into the cavity 45. The cooling systems 11 (e.g., 100, 102, and / or 104) are configured to help mitigate the heat transfer associated with this leakage by ventilating and cooling the cavity 45.

[0028] For example, the cooling system 100 is configured to cool hot spots (e.g., turbine shaft and coupling assembly 14 and TRF wall 53) by ventilating the cavity 45 through one or more intake flow conduits 65 and / or 66 along the cooling flow path as indicated by arrows 116 and 118, and by pushing or pulling a coolant flow (e.g., ventilation or cooling air) from the cavity 45 through one or more discharge flow conduits 68 as indicated by arrow 122. In certain embodiments, the cooling system 100 comprises one or more intake flow conduits 65 only, one or more intake flow conduits 66 only, or a combination of both intake flow conduits 65 and 66. The intake flow conduits 65 (e.g., openings and / or tubes) are located in the side wall 124 of the enclosure 3. The intake flow conduits 65 may include filters, flow regulators 74, sensors 76, or any combination thereof. The intake flow conduit 66 can extend laterally along the bottom of the diffuser 41, such as substantially horizontally from the side wall 124 toward the TRF wall 53. For example, the intake flow conduit 66 may extend directly along the inner diffuser wall 44 from the side wall 124 to a distal end 126 close to the TRF wall 53. In certain embodiments, the intake flow conduit 66 can extend at least 80, 85, 90, or 95% of the horizontal distance between the side wall 124 and the TRF wall 53. In this way, the intake flow conduit 66 can help concentrate the cooling flow directly onto the hot spots associated with the TRF wall 53, the bearing 51, and the TRF leak 110. Within the cavity 45, the coolant flow from the intake flow conduits 65 and / or 66 can flow along the turbine shaft and coupling assembly 14 and along the inner diffuser wall 44 before being discharged through the discharge flow conduit 68. In certain embodiments, the air supply system 60 (see Figure 1) uses a fan 61 to push the coolant flow (e.g., airflow) into the intake flow conduits 65 and / or 66, through the cavity 45, and out through the discharge flow conduit 68. However, in some embodiments, the rotational motion of the turbine shaft and coupling assembly 14 can help to force the coolant flow to rotate, thereby helping to push the coolant flow out through the discharge flow conduit 68.For example, the turbine shaft and coupling assembly 14 may include one or more flow induction mechanisms 128 (e.g., projections, recesses, bolts, nuts, fins, impeller blades, etc.) arranged circumferentially around the shaft 54 ​​at intervals, thereby helping to force the coolant flow to circulate throughout the cavity 45 and then exit through the discharge flow conduit 68. In addition, the cooling system 100 may also partially rely on heat that naturally rises upward from the cavity 45 through the discharge flow conduit 68. In the illustrated embodiment, the discharge flow conduit 68 includes a vertical conduit or vertical cylinder.

[0029] As another example, the cooling system 102 is configured to cool hot spots (e.g., the turbine shaft and coupling assembly 14 and the TRF wall 53) by ventilating the cavity 45 through one or more intake flow conduits 65 and / or 66 along the cooling flow path as indicated by arrows 116 and 118, and by pushing or pulling a coolant flow (e.g., ventilation or cooling air) from the cavity 45 through one or more discharge flow conduits 70 as indicated by arrow 130. Similar to the cooling system 100, a particular embodiment of the cooling system 102 may comprise one or more intake flow conduits 65 only, one or more intake flow conduits 66 only, or a combination of both intake flow conduits 65 and 66. The intake flow conduits 65 and 66 have the features described above in relation to the cooling system 100. Within the cavity 45, coolant flows from intake flow conduits 65 and / or 66 can flow along the turbine shaft and coupling assembly 14 and along the inner diffuser wall 44 before being discharged through the discharge flow conduit 70. The coolant flows can be driven by the air supply system 60 and / or by the rotational motion of the turbine shaft and coupling assembly 14, as described above in relation to the cooling system 100. Additionally or alternatively, the coolant flows can be driven (e.g., by being drawn or sucked) by ventilation flows through the enclosure 2 (e.g., ventilation flows 31 through the chamber 27 from the ventilation air intake duct or intake pipe 26 to the ventilation air exhaust duct or exhaust pipe 28), as indicated by arrow 31 in Figure 1. In particular, the discharge flow conduit 70 can be fluidically coupled to the chamber 27 of the enclosure 2, as shown in Figure 1. As shown in Figure 2, each of the discharge flow conduits 70 comprises a first conduit portion 132 (e.g., a hollow support strut) extending between the inner diffuser wall 44 and the outer diffuser wall 46 of the diffuser 41, and a second conduit portion 134 extending between the outer diffuser wall 46 and the side wall 92 of the enclosure 3. The first and second conduit portions 132 and 134 are fluidly and structurally coupled to one another to define a discharge flow path from the inner cavity 45 of the diffuser 41 to the inner chamber 27 of the enclosure 2.Therefore, the first and second conduit sections 132 and 134 are fluidically coupled to each other via an opening 136 in the outer diffuser wall 46, and the second conduit section 134 is fluidically coupled to the chamber 27 on the side of the enclosure 2 via an opening 138 in the side wall 92 and an opening 140 in the side wall 90. The ventilation flow 31 inside the enclosure 2 helps to draw in the coolant flow through the discharge flow conduit 70 (e.g., by negative pressure or suction for drawing it in). In certain embodiments, the cooling system 102 can use suction force to draw in the coolant flow through the conduits 65 and / or 66, the cavity 45, and the conduit 70 without requiring any additional fans (e.g., the fan 61 of the air supply system 60).

[0030] As another example, the cooling system 104 is configured to cool hot spots (e.g., the turbine shaft and coupling assembly 14 and the TRF wall 53) by ventilating the cavity 45 through one or more intake flow conduits 65 and / or 66 along the cooling flow path as indicated by arrows 116 and 118, and by pushing or pulling a coolant flow (e.g., ventilation or cooling air) from the cavity 45 through one or more discharge flow conduits 72 as indicated by arrow 142. Similar to the cooling systems 100 and 102, a particular embodiment of the cooling system 104 may comprise only one or more intake flow conduits 65, only one or more intake flow conduits 66, or a combination of both intake flow conduits 65 and 66. The intake flow conduits 65 and 66 have the features described above in relation to the cooling system 100. Within the cavity 45, coolant flows from intake flow conduits 65 and / or 66 can flow along the turbine shaft and coupling assembly 14 and along the inner diffuser wall 44 before being discharged through the discharge flow conduit 72. The coolant flows can be driven by the air supply system 60 and / or by the rotational motion of the turbine shaft and coupling assembly 14, as described above in relation to the cooling system 100. Additionally or alternatively, the coolant flows can be driven (e.g., by being drawn in or sucked in) by the exhaust flow through the diffuser 41 along the exhaust passage 40 located between the inner diffuser wall 44 and the outer diffuser wall 46. As will be described in more detail below in relation to Figures 3 to 6, the discharge flow conduit 72 fluidly connects the cavity 45 to the exhaust passage 40 through one or more openings 144 through the inner diffuser wall 44. The exhaust flow along the exhaust passage 40 helps to draw in (e.g., by negative pressure or suction) the coolant flows through the discharge flow conduit 72. The discharge flow conduit 72 can be described as an eductor by using suction to induce flow. In certain embodiments, the cooling system 104 can use suction force to draw coolant flow through conduits 65 and / or 66, cavities 45, and conduit 72 without requiring any additional fans (e.g., fan 61 of air supply system 60).The illustrated discharge flow conduit 72 defines a discharge flow path (e.g., a redirecting discharge flow conduit) that redirects the exhaust flow passing along the exhaust flow path 40 downstream. By redirecting the flow downstream, the discharge flow conduit 72 helps prevent backflow of the exhaust flow into the cavity 45. By redirecting the flow downstream, the discharge flow conduit 72 can also increase or control the suction force generated by the exhaust flow to draw the coolant flow from the cavity 45 into the exhaust flow path 40.

[0031] The cooling systems 100, 102, and 104 described above may be used independently or in any combination thereof. As described above in relation to Figure 1, each of the conduits 65, 66, 68, 70, and 72 may be equipped with one or more flow regulators 74 and sensors 76 coupled to the controller 78. The controller 78 monitors the conditions (e.g., temperature, pressure, flow rate, vibration, noise, etc.) within the cavity 45 and the various conduits 65, 66, 68, 70, and 72, and can then adjust the cooling systems 100, 102, and 104 via the flow regulators 74, the air supply system 60, the fan 29, or any combination thereof. The cooling systems 100, 102, and 104 will be described in further detail below in relation to Figures 3 to 11.

[0032] Figure 3 is a schematic diagram of one embodiment of the cooling system 104 shown in Figures 1 and 2. Figure 3 shows a cooling system 104 without cooling systems 100 and 102 and without an intake airflow conduit 66. However, as described above, the cooling system 104 may be used alone or in combination with cooling systems 100 and 102, and the cooling system 104 may be equipped with an intake airflow conduit 66 in combination with the intake airflow conduit 65. In the illustrated embodiment, the cooling system 104 is substantially the same as that described above in relation to Figures 1 and 2. As described above, the cooling system 104 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) through one or more intake flow conduits 65 (and possibly conduit 66) along the cooling passage as indicated by arrow 116, to ventilate the cavity 45 through the cavity 45 as indicated by arrow 120, to cool hot spots (e.g., the turbine shaft and coupling assembly 14 and the TRF wall 53), and through one or more discharge flow conduits 72 from the cavity 45 as indicated by arrow 142. Within the cavity 45, the coolant flow from the intake flow conduit 65 can flow along the turbine shaft and coupling assembly 14 and along the inner diffuser wall 44 before being discharged through the discharge flow conduit 72. The coolant flow can be driven (e.g., by being pulled or sucked) by the exhaust flow passing through the diffuser 41 along the exhaust passage 40 located between the inner diffuser wall 44 and the outer diffuser wall 46. Therefore, the discharge flow conduit 72 can be described as an eductor by using suction to induce flow. In certain embodiments, the cooling system 104 can draw coolant flow through conduit 65, cavity 45, and conduit 72 using suction force without requiring any additional fans (e.g., fan 61 of air supply system 60). The illustrated discharge flow conduit 72 defines a discharge flow path (e.g., a redirecting discharge flow conduit) that redirects the exhaust flow passing along the exhaust flow path 40 downstream. For simplicity of the drawings, the flow regulator 74 and sensor 76 in the conduit 72 described in Figures 1 and 2 are not shown in Figure 3. Further details of the discharge flow conduit 72 (e.g., eductor) are described below in relation to Figures 4 to 6.

[0033] Figure 4 is a partial cross-sectional view of the inner diffuser wall 44 having a discharge flow conduit 72 (e.g., an eductor) taken within the arc-shaped line 4-4 of Figure 3, further illustrating the details of the cooling system 104. The discharge flow conduit 72 (e.g., an eductor) may comprise one or more openings 144 (e.g., openings of circular, elliptical, square, or polygonal shape) penetrating the inner diffuser wall 44, and one or more baffles 202 and 204 coupled to the inner diffuser wall 44 and projecting into the exhaust flow path 40. The inner diffuser wall 44 comprises an outer wall 206, an inner wall 208, and an insulating layer 210 positioned between the outer wall 206 and the inner wall 208. The insulating layer 210 helps to block or withstand heat transfer from the exhaust flow through the inner diffuser wall 44 into the cavity 45. The opening 144 extends through the inner wall 208, the insulation layer 210, and the outer wall 206. Baffles 202 and 204 are connected to the outer wall 206 of the inner diffuser wall 44.

[0034] The opening 144 extends through the inner diffuser wall 44 along a central axis 200, which may be straight or curved, which may be oriented perpendicular to the inner diffuser wall 44, and / or which may be angled with respect to the inner diffuser wall 44 (for example, angled downstream with respect to the exhaust passage 40). The opening 144 may also have a cross-sectional area or width that decreases or converges in the direction of the coolant flow 142 through the inner diffuser wall 44 (for example, defining a converging passage). In some embodiments, the cross-sectional area or width of the opening 144 may be at least partially uniform in the direction of the coolant flow 142 through the inner diffuser wall 44, and / or decrease (for example, widen). However, the illustrated converging cross-sectional area of ​​the opening 144 defines a throat 146 which can help prevent backflow of exhaust gas from the exhaust passage 40 back into the inner cavity 45 of the diffuser 41.

[0035] The baffles 202 and 204 are generally reoriented with respect to the central axis 200 of the opening 144, and specifically reoriented downstream with respect to the exhaust passage 40. For example, the baffles 202 and 204 may be rotated by about 90 degrees, or reoriented until the outlet 203 is substantially parallel to the exhaust passage 40 (e.g., the center line between the inner diffuser wall 44 and the outer diffuser wall 46), or reoriented until the outlet 203 is substantially parallel to the surface 205 of the inner diffuser wall 44. The baffles 202 and 204 may each include reoriented sections 207 and 209, which may include curved reoriented sections, tapered or angled reoriented sections, or any combination thereof. For example, the reoriented sections 207 and 209 may include curved scoops (e.g., concave scoops), angled scoops, or any combination thereof. Baffles 202 and 204 may converge and / or diverge, and be positioned at equal intervals in the direction of the coolant flow 142 through the inner diffuser wall 44 and the discharge flow conduit 72. The downstream direction of baffles 202 and 204 may help prevent backflow of exhaust gas from the exhaust passage 40 into the inner cavity 45 of the diffuser 41. In addition, baffle 204 is positioned downstream of baffle 202, and baffle 204 may help trap liquid or debris in the exhaust flow. For example, if liquid or debris is placed along the surface 205 of the inner diffuser wall 44, baffle 204 may help prevent the liquid or debris from entering the opening 144. The baffle 204 can also redirect liquid or debris circumferentially around the inner diffuser wall 44 (i.e., circumferentially around the axis 54 (see Figure 1)), and then guide the liquid or debris into the drain 148, as shown in Figure 1. For example, a conduit or catch basin 150 may be located below the diffuser 41, as shown in Figure 1, so that any redirected liquid or debris flows into the drain 148.

[0036] In certain embodiments, the cooling system 104 may comprise multiple sets of baffles 202 and 204, each associated with a corresponding opening 144. For example, Figure 5 is a cross-sectional view of an inner diffuser wall 44 having a discharge flow conduit 72 (e.g., an eductor) taken along line 5-5 in Figure 4, further illustrating details of the baffles 202 and 204 and the corresponding opening 144. In the illustrated embodiment, the opening 144 (e.g., a single circumferentially elongated opening or a semicircular slot) passing through the inner diffuser wall 44 extends circumferentially about an axis 54, for example, about 180 degrees around the axis 54. Similarly, the baffles 202 and 204 of the discharge flow conduit 72 are located on both sides of the opening 144 (i.e., upstream and downstream) and extend circumferentially about an axis 54, for example, about 180 degrees around the axis 54. In certain embodiments, the opening 144 and baffles 202 and 204 can extend at least 30, 45, 60, 75, 90, 120, 150, or 180 degrees around the axis 54. In some embodiments, the opening 144 may be continuous and uniform in the circumferential direction around the axis 54, or the opening 144 may be continuous but its geometric shape (e.g., width) may change in the circumferential direction around the axis 54.

[0037] Alternatively or additionally, the cooling system 104 may have multiple discontinuous sets of openings 144 between baffles 202 and 204. For example, Figure 6 is a cross-sectional view of an inner diffuser wall 44 having a discharge flow conduit 72 (e.g., an eductor) taken along line 5-5 in Figure 4, further illustrating details of baffles 202 and 204 and multiple discontinuous openings 144. In the illustrated embodiment, the openings 144 are arranged circumferentially with respect to each other and spaced circumferentially around an axis 54, and the openings 144 extend over a circumferential distance of about 180 degrees around the axis 54. In certain embodiments, the openings 144 and baffles 202 and 204 may extend over circumferential distances of at least 30, 45, 60, 75, 90, 120, 150, or 180 degrees around the axis 54. Each of the illustrated openings 144 converges from the inner wall 208 to the outer wall 206 of the inner diffuser wall 44, the openings 144 have the same geometric shape, and the openings 144 are spaced equally apart from one another. In some embodiments, the openings 144 may converge, expand, and / or have uniform flow paths from the inner wall 208 to the outer wall 206 of the inner diffuser wall 44. The openings 144 may have different shapes, such as different convergence shapes (e.g., convergence shapes with different convergence angles, different cross-sectional areas, etc.), different expansion shapes, different uniform shapes, or combinations of shape types (e.g., convergence, expansion, and / or uniform geometric shapes). In the illustrated embodiment, a pair of baffles 202 and 204 extend along all of the openings 144. In some embodiments, a pair of baffles 202 and 204 may be dedicated to one of the openings 144, or a pair of baffles 202 and 204 may be dedicated to two or more of the openings 144 (but fewer than the total number of openings 144 in the inner diffuser wall 44).

[0038] Figure 7 is a schematic diagram of one embodiment of the cooling system 102 shown in Figures 1 and 2. Figure 7 shows a cooling system 102 without cooling systems 100 and 104 and without the intake airflow conduit 66. However, as described above, the cooling system 102 may be used alone or in combination with cooling systems 100 and 104, and the cooling system 102 may be equipped with an intake airflow conduit 66 in combination with the intake airflow conduit 65. In the illustrated embodiment, the cooling system 102 is substantially the same as that described above in relation to Figures 1 and 2. As described above, the cooling system 102 is configured to push or pull the coolant flow (e.g., ventilation or cooling air) through one or more intake flow conduits 65 (and optionally conduit 66) along the cooling flow path as indicated by arrow 116 into the cavity 45, ventilate the cavity 45 as indicated by arrow 120 to cool hot spots (e.g., the turbine shaft and fitting assembly 14 and the TRF wall 53), and push or pull the coolant flow (e.g., ventilation or cooling air) through one or more discharge flow conduits 70 from the cavity 45 as indicated by arrow 130, and then exit through a ventilation air exhaust duct or exhaust pipe 28 coupled to the enclosure 2. Within the cavity 45, the coolant flow from the intake flow conduit 65 can flow along the turbine shaft and fitting assembly 14 and along the inner diffuser wall 44 before being discharged through the discharge flow conduit 70. The discharge flow conduit 70 is fluidically coupled to the chamber 27 inside the enclosure 2, and the ventilation flow 31 assists in the ventilation of the gas turbine engine 12 by passing through the enclosure 2 from the ventilation air intake duct or intake pipe 26 to the ventilation air exhaust duct or exhaust pipe 28. This ventilation flow 31 provides the driving force or negative pressure for drawing the coolant flow from the discharge flow conduit 70. Thus, the coolant flow is driven (e.g., by being pulled or sucked) by the ventilation flow 31 passing through the enclosure 2, thereby drawing the coolant flow into the chamber 27 and drawing it out through the ventilation air exhaust duct or exhaust pipe 28. For these reasons, the discharge flow conduit 70 can be described as an eductor.In certain embodiments, the cooling system 102 can draw coolant flow through conduits 65, cavities 45, and conduit 70 using suction force without requiring any additional fans (e.g., fan 61 of air supply system 60). Further details of the discharge flow conduit 70 (e.g., eductor) are described below in relation to Figure 8.

[0039] Figure 8 is a schematic cross-sectional view of one embodiment of the cooling system 102 of Figure 7, showing the configuration of discharge flow conduits 70 (e.g., radial conduits) arranged at circumferential intervals around the axis 54 of the diffuser 41. The discharge flow conduits 70 can have various shapes and sizes, such as cylindrical conduits, conduits with airfoil-shaped cross-sections, and conduits with elliptical cross-sections. As described above, each of the discharge flow conduits 70 comprises a first conduit portion 132 (e.g., a hollow support strut or radial strut) extending between the inner diffuser wall 44 and the outer diffuser wall 46 of the diffuser 41, and a second conduit portion 134 extending between the outer diffuser wall 46 and the side wall 92 of the enclosure 3. Each discharge flow conduit 70 has a first conduit portion 132 that is fluidically coupled to a cavity 45 inside the inner diffuser wall 44, and a second conduit portion 134 that is fluidically coupled to a chamber 27 inside the enclosure 2 housing the gas turbine engine 12. In particular, the second conduit portion 134 is coupled to an opening 138 in the side wall 92 of the enclosure 3, and this opening 138 is fluidly coupled to an opening 140 in the side wall 90 of the enclosure 2. In the illustrated embodiment, the discharge flow conduits 70 are arranged at equal intervals circumferentially around the axis 54, and each discharge flow conduit 70 has the same geometric configuration. In some embodiments, the discharge flow conduits 70 may be arranged at uneven intervals circumferentially around the axis 54, and / or the geometric configuration of the discharge flow conduits 70 may differ from conduit to conduit. For example, the discharge conduits 70 may be more closely spaced, i.e., concentrated, in areas with high-temperature spots, or the discharge conduits 70 may have a larger cross-sectional area in areas with high-temperature spots, or a combination of these. Figure 8 shows a specific number of discharge conduits 70, but embodiments of the cooling system 102 can have any number of discharge conduits 70 (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 15, 20, or more).

[0040] Figure 9 is a schematic diagram of one embodiment of the cooling system 100 shown in Figures 1 and 2. Figure 9 shows a cooling system 100 without cooling systems 102 and 104 and without the intake airflow conduit 65. However, as described above, the cooling system 100 may be used alone or in combination with cooling systems 102 and 104, and the cooling system 100 may be equipped with an intake airflow conduit 65 in combination with the intake airflow conduit 66. In the illustrated embodiment, the cooling system 100 is substantially the same as that described above in relation to Figures 1 and 2. As described above, the cooling system 100 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) into the cavity 45 through one or more intake flow conduits 66 (and optionally conduits 65) along the cooling path as indicated by arrow 118, ventilate the cavity 45 through the cavity 45 as indicated by arrow 120, cool hot spots (e.g., turbine shaft and coupling assembly 14 and TRF wall 53), and then push or pull a coolant flow (e.g., ventilation or cooling air) out of the cavity 45 through one or more discharge flow conduits 68 as indicated by arrow 122.

[0041] The intake flow conduit 66 may include a plurality of intake sections 250, such as an intake section 252 coupled to the side wall 124 and an intake section 254 extending upward from the bottom wall 256 of the enclosure 3. The intake sections 250 (e.g., 252 and 254) may include one or more openings, conduits, and / or baffles configured to guide the coolant flow into the intake flow conduit 66. The intake sections 250 may also include air processing units, such as an air processing unit 258 in the intake section 252 and an air processing unit 260 in the intake section 254. The air processing units 258 and 260 may include screens, filters, or any combination thereof. The illustrated intake flow conduit 66 extends along the bottom of the diffuser 41, for example along the inner diffuser wall 44, and may include a passage or user access platform 262. The intake flow conduit 66 extends toward the hot spots associated with the TRF leak 110 in the TRF wall 53 and the bearing 51. The distal end 126 of the intake flow conduit 66 is positioned close to the TRF leak 110, the TRF wall 53, and / or the bearing 51, thereby helping to concentrate the coolant flow to the hot spots. In certain embodiments, one of the intake flow conduits 66 may extend to each hot spot within the cavity 45. Thus, after leaving the intake flow conduit 66, the coolant flow first contacts the hot spots and then circulates throughout the cavity 45.

[0042] Within the cavity 45, the coolant flow from the intake flow conduit 66 can flow along the turbine shaft and coupling assembly 14 and along the inner diffuser wall 44 before being discharged through the discharge flow conduit 68. In certain embodiments, the rotational motion of the turbine shaft and coupling assembly 14 can help to force the coolant flow to rotate, thereby helping to push the coolant flow through the discharge flow conduit 68. Thus, as described above, one or more flow induction mechanisms 128 on the turbine shaft and coupling assembly 14 (e.g., protrusions, recesses, bolts, nuts, fins, impeller blades, etc.) help to drive the coolant flow as the mechanism 128 rotates with the assembly 14. However, the cooling system 100 may also partially rely on heat rising naturally upward through the discharge flow conduit 68, the fan 61 of the air supply system 60, or any combination thereof. The cooling system 100 may also include a mechanism for controlling the discharge of the coolant flow through the discharge flow conduit 68. For example, a diverter plate 264 (e.g., one or more baffles or walls) may be positioned inside the cavity 45 adjacent to the inlet 266 of the discharge flow conduit 68. The diverter plate 264 is configured to bypass (e.g., redirect) at least a portion of the coolant flow inside the cavity 45 so that the coolant flow exits through the discharge flow conduit 68. The discharge flow conduit 68 may also include one or more processing units 266 (e.g., screens, filters, sound-absorbing sections, etc.) and a cap 268 which may be configured to disperse the coolant flow. Further details of the flow induction mechanism 128 and the diverter plate 264 are described below in reference to Figures 9 and 10.

[0043] Figure 10 is a partial side view of the turbine shaft and coupling assembly 14 taken within line 10-10 of Figure 9, further illustrating details of various flow induction mechanisms 128 arranged on shaft 47, coupling 48, and shaft 49. In certain embodiments, the flow induction mechanisms 128 arranged on shafts 47 and 49 may comprise radial projections 280 (e.g., fins, impeller blades, or rectangular plates) spaced circumferentially around the shaft 54. Additionally or alternatively, the flow induction mechanisms 128 arranged on coupling 48 may comprise fasteners 282 (e.g., threaded fasteners) spaced circumferentially around the shaft 54. The fasteners 282 can connect shafts 47 and 49 together at their respective flanges 284 and 286. Each of the fasteners 282 extends axially through flanges 284 and 286 and can compress flanges 284 and 286 toward each other. For example, each of the fasteners 282 may include a threaded bolt 288 and a threaded nut 290. In a particular embodiment, as the turbine shaft and coupling assembly 14 rotate during the operation of the gas turbine engine 12, the fasteners 282 can provide sufficient force to push the coolant flow through the discharge flow conduit 68, with or without the radial projection 280.

[0044] Figure 11 is a partial side view of the divertor plate 264 adjacent to the inlet 266 of the discharge flow conduit 68 in Figure 9, further illustrating the divertor plate 264. As shown, the divertor plate 264 protrudes inward (i.e., radially inward with respect to the shaft 54) from the inner diffuser wall 44 toward the turbine shaft and coupling assembly 14. For example, the divertor plate 264 can extend by a radial distance of at least 10, 20, 30, 40, 50, 60, 70, or 80% of the total radial distance between the inner diffuser wall 44 and the turbine shaft and coupling assembly 14. The divertor plate 264 is configured to capture the coolant flow indicated by arrow 120 and then redirect the coolant flow toward the discharge flow conduit 68.

[0045] The technical effect of the present invention is to include one or more cooling systems 11 (e.g., 100, 102, and / or 104) configured to ventilate an enclosure 3 having an exhaust manifold 13. Heat sources arise from turbine rear frame (TRF) leakage, exhaust heat, and shafts 21 coupled to the turbine shaft and coupling assembly 14 within the gas turbine system 10. Each embodiment of the present disclosure provides a system comprising one or more cooling systems 11 located within the gas turbine system. In a particular embodiment, cooling system 104 comprises a discharge flow conduit 72 (e.g., an eductor) located in the inner diffuser wall 44 of the turbine exhaust manifold 13 so that the exhaust flow along the exhaust passage 40 draws a coolant flow from a cavity 45 surrounding the turbine shaft and coupling assembly 14 based on high-speed combustion exhaust. In certain embodiments, the cooling system 102 may comprise one or more discharge flow conduits 70, each comprising a first conduit portion 132 (e.g., a hollow support strut) extending between the inner diffuser wall 44 and the outer diffuser wall 46 of the diffuser 41, and a second conduit portion 134 extending between the outer diffuser wall 46 and the side wall 92 of the enclosure 3. The ventilation flow 31 inside the enclosure 2 draws the coolant flow from the cavity 45 through the discharge flow conduits 70 and then discharges the coolant flow together with the ventilation flow through the ventilation air exhaust duct or exhaust pipe 28. In certain embodiments, the cooling system 100 takes in the coolant flow through an intake flow conduit 66 (e.g., along a passage or user access platform 262), thereby directing the coolant flow to a high-temperature spot (e.g., a TRF leak 110). The cooling system 100 can also use the rotation of the turbine shaft and coupling assembly 14 to help push the coolant flow out of the cavity 45 through the discharge flow conduit 68. These cooling systems 100, 102, and 104 may be used independently or in any combination with each other to ventilate the cavity 45 and cool the turbine shaft and coupling assembly 14.

[0046] This specification uses examples to disclose the present invention, including the best mode. The examples also allow any person skilled in the art to carry out the invention, including constructing and using any apparatus or system and performing any incorporated method. The patentable scope of the present invention is defined by the claims and may include other embodiments conceivable by a person skilled in the art. Such other embodiments are intended to be within the claims if they have structural elements not different from the language of the claims, or if they include equivalent structural elements that are substantially indistinguishable from the language of the claims. [Explanation of symbols]

[0047] 2 enclosures 3 Enclosures 10 Gas Turbine Systems 11 Cooling System 12 Gas turbine engines 13. Turbine exhaust manifold 14. Turbine shaft and coupling assembly 15 Compressor Blades 16 Compressor Section / Compressor 17 Fuel nozzle 18 Combustor Section / Combustor 19 Turbine Blades 20 Turbine Section / Turbine 21 Shaft 22 Generators 23 Intake duct / intake cylinder 24 Air Processing Unit 25 Arrows 26 Ventilation air intake duct / intake pipe 27 Internal space / chamber 28 Ventilation air exhaust duct / exhaust pipe 29 Fans 30 Arrows 31 Arrow / Ventilation Flow 32 Arrows 33 Air filter 34 Compressor extraction system 35 Compressor extraction exhaust duct / exhaust pipe 36 Compressor extraction lines / conduits 37 Variable Blow Valve (VBV) 38 Arrows 39 Combustion exhaust duct / exhaust pipe 40 Exhaust passage / arrow 41 Diffuser 42 Exhaust Inlet 43 Exhaust outlet 44 Inner diffuser wall 45 Cavity 46. ​​Outer diffuser wall 47. First shaft / turbine shaft section 48 Fittings 49 Second shaft / generator shaft section 50 bearings 51 Bearing 52 Bearings 53 Turbine Rear Frame Section / TRF Wall 54 Center axis 60 Air supply system 61 Fans 62 Flow regulator 63 Air Processing Unit 64 Arrows 65 Intake airflow conduit 66 Intake airflow conduit 68 Discharge flow conduit 70 Discharge flow conduit 72 Discharge flow conduit 74 Flow regulator 76 sensors 78 Controllers 79 processors 80 memory 81 command 90 side wall 91 Interface 92 Side wall 94 Upstream diffuser section 96 Diffuser recess 98 Support strut 100 Cooling System 102 Cooling System 104 Cooling System 110 TRF leak 112 Heat transfer / Arrow 114 Heat transfer / Arrow 116 Arrow 118 Arrow 120 Arrows 122 Arrow 124 Side wall 126 Distal end 128 Flow Induction Mechanism 130 Arrow 132 First conduit section 134 Second conduit section 136 Opening 138 Opening 140 opening 142 Coolant flow / arrow 144 openings 146 Throat 148 Drain 150 Conduit / Sump 200 center axis 202 Baffle 203 Discharge outlet 204 Baffle 205 Surface 206 Exterior Wall 207 Direction change section 208 Interior wall 209 Direction change section 210 Insulation layer 250 Intake Section 252 Intake Section 254 Intake Section 256 Bottom wall 258 Air Processing Unit 260 Air Processing Unit 262 Passageway / User Access Platform 264 Diverter Plate 266 Air Treatment Unit 266 Entrance 268 Cap 280 Radial protrusion 282 Fasteners 284 Flange 286 Flange 288 Threaded bolts 290 Threaded Nut

Claims

1. A turbine exhaust manifold (13), A first enclosure (3) having an exhaust inlet (42) and an exhaust outlet (43), wherein the exhaust inlet (42) is configured to receive exhaust gas from a gas turbine, A diffuser (41) coupled to the exhaust inlet (42), wherein the diffuser (41) comprises an inner diffuser wall (44) arranged around a cavity (45), an outer diffuser wall (46) arranged around the inner diffuser wall (44), and an exhaust passage (40) between the inner diffuser wall (44) and the outer diffuser wall (46), and the cavity is configured to extend from the outer surface of the rotating shaft to the inner surface of the inner diffuser wall, A first cooling channel having a first portion and a second portion, wherein the second portion receives a first cooling flow from the first portion and A turbine exhaust manifold (13) is provided. Equipped with, The first portion of the first cooling passage includes a duct extending through the cavity (45) along the inner diffuser wall (44) toward the turbine rear frame (53), the rotating shaft (14) is configured to be coupled to a turbine shaft (14) extending through the bore of the turbine rear frame (53), the first portion of the first cooling passage is configured to guide the first cooling flow toward the turbine rear frame (53), and the leakage flow between the turbine shaft and the turbine rear frame is configured to provide an attractive force for drawing in the first cooling flow through the duct. A system wherein the second portion of the first cooling channel includes the cavity configured to extend from the outer surface of the rotating shaft to the inner surface of the inner diffuser wall, and the first cooling flow flowing through the second portion of the first cooling channel flows along the outer and inner surfaces.

2. The system according to claim 1, wherein the first enclosure does not surround the gas turbine (12), and the first enclosure is separate from the second enclosure (2) that surrounds the gas turbine (12), and the second enclosure (2) includes a space having a chamber arranged around the gas turbine.

3. The system according to claim 2, comprising a ventilation system (11) coupled to a second cooling channel passing through the second enclosure (2), wherein the ventilation system includes one or more fans.

4. A ventilation air intake section (26) and a ventilation air exhaust section (28) are connected to the second enclosure (2). The ventilation air intake section (26) and / or the ventilation air exhaust section (28) have one or more fans to allow a second cooling flow to flow through the second cooling passage. The system according to claim 3, wherein the first cooling channel is coupled to the second cooling channel, and the second cooling flow passing through the second cooling channel provides another attractive force to draw the first cooling flow out of the first cooling channel.

5. The first enclosure (3) and the second enclosure (2) include one or more discharge flow conduits (70) fluidically coupled to each other. The system according to claim 3, wherein the first cooling flow flowing through the first cooling channel flows through one or more discharge flow conduits (70) and is pushed out into or drawn into the second cooling flow flowing through the second cooling channel that passes through the second enclosure.

6. The system according to claim 1, wherein the first cooling channel passes through at least one passage penetrating the inner diffuser wall (44), extends outward from the cavity, and extends toward the exhaust channel between the inner diffuser wall and the outer diffuser wall of the diffuser.

7. The system according to claim 6, wherein the at least one passage extends outward from the cavity and in the direction toward the exhaust flow path between the inner diffuser wall and the outer diffuser wall of the diffuser, the cross-sectional area of ​​the inner diffuser wall (44) decreases.

8. The system according to claim 6, further comprising a first baffle (202) coupled to the inner diffuser wall (44) upstream of the at least one passage, wherein the first baffle (202) is redirected downstream of the exhaust passage (32).

9. The system according to claim 8, comprising at least one passage and a second baffle (204) coupled to the inner diffuser wall (44) downstream of the first baffle, wherein the second baffle extends to a wall portion of the inner diffuser wall and is configured to capture liquid or debris.

10. The system according to claim 1, wherein the rotation of the rotating shaft (14) rotates the first cooling flow in the second portion of the first cooling channel that passes through the cavity.

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