Systems for cooling turbine shaft couplings

Abstract

The present invention is entitled "System for Cooling a Turbine Shaft Coupling." The present invention provides one or more cooling systems (100, 102, 104) for ventilating a turbine (20) and a rotating shaft (14) of a gas turbine system (10). The gas turbine system (10) includes a gas turbine engine (12) and a turbine exhaust collector (13) located in separate housings (2, 3). A first cooling system (104) includes an ejector (72) that draws exhaust gas through a diffuser (41) and directs the exhaust gas out of the turbine exhaust collector housing (3) based on suction pressure generated by the high-speed exhaust gas. A second cooling system (102) includes struts (98) that enable exhaust gas to flow from the diffuser (41) to a ventilation flow stack (28). A third cooling system (100) includes exhaust gas drawn from an opening to a top duct (68) based on suction pressure generated by the rotation of a rotating shaft (14) disposed around a coupling (48). Guide rails associated with the third cooling system (100) also direct exhaust gas flow to the top duct (68). These cooling systems (100, 102, 104) are designed to improve the efficiency of ventilation to the turbine (20) and rotating shaft (14), prevent misalignment of the rotating shaft (14) that could cause thermal stress, and allow the gas turbine system (10) to be used in higher ambient temperature environments.

Description

Background Art

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

[0002] Gas turbine systems can be used in a variety of applications, such as power generation. For example, a gas turbine generator may include a generator driven by a gas turbine to generate electricity for a power grid or local facility. A gas turbine system typically includes one or more shafts and associated couplings to connect to a load, such as a generator. In certain configurations, the shaft and couplings may be located downstream of the exhaust outlet, allowing for significant heat transfer from the exhaust gas to the shaft and couplings. Unfortunately, this heat transfer can cause thermal expansion and stress at the couplings, which in turn can lead to shaft misalignment and associated vibration. Consequently, heat transfer to the shaft and couplings can lead to performance issues, maintenance problems, and downtime for the gas turbine system. Consequently, there is a need to cool the turbine shaft couplings. Summary of the Invention

[0003] The following summarizes certain embodiments that are comparable in scope to the initially claimed invention. These embodiments are not intended to limit the scope of the claimed invention, but rather, these embodiments are intended only to provide a brief overview of possible forms of the invention. In fact, the present invention may include various forms that may be similar or different from the embodiments set forth below.

[0004] In a first embodiment, a system includes a turbine exhaust collector having a first housing with an exhaust inlet and an exhaust outlet, and a diffuser coupled to the exhaust inlet. The diffuser includes an inner diffuser wall disposed around a cavity having a rotating axis, an outer diffuser wall disposed around the inner diffuser wall, and an exhaust flow path between the inner diffuser wall and the outer diffuser wall. The turbine exhaust collector also includes a first cooling flow path extending through the cavity having the rotating axis, wherein the first housing is separate from a second housing surrounding a gas turbine.

[0005] In a second embodiment, a system includes a turbine exhaust collector having a diffuser, the diffuser having an inner diffuser wall disposed around a cavity having a rotating shaft, an outer diffuser wall disposed around the inner diffuser wall, and an exhaust flow path between the inner diffuser wall and the outer diffuser wall. The turbine exhaust collector further includes a duct extending through the cavity along the inner diffuser wall toward a turbine aft frame, wherein the rotating shaft is configured to be coupled to a turbine shaft extending through a hole in the turbine aft frame, wherein a first cooling flow path extends through the duct to direct a first cooling flow toward the turbine aft frame, and leakage flow between the turbine shaft and the turbine aft frame is configured to provide suction to draw the first cooling flow through the duct.

[0006] In a third embodiment, a system includes a turbine exhaust collector. The turbine exhaust collector includes a diffuser having an inner diffuser wall disposed around a cavity having a rotational axis, an outer diffuser wall disposed around the inner diffuser wall, and an exhaust flow path between the inner diffuser wall and the outer diffuser wall. Rotation of the rotational axis is configured to drive a first cooling flow through the cavity along a first cooling flow path. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] These and other features, aspects, and advantages of the present invention will be better understood when the following detailed description is read with reference to the accompanying drawings, in which like characters represent like parts throughout, and in which:

[0008] Figure 1 is a schematic diagram of an embodiment of a gas turbine system showing a cooling system configured to cool a turbine shaft and coupling assembly in a housing having an exhaust gas collector located downstream of a turbine section;

[0009] Figure 2 is a schematic diagram of an embodiment of one or more cooling systems in a housing having an exhaust collector;

[0010] Figure 3 yes Figure 2 A schematic diagram of an embodiment of a cooling system of FIG. 1 , showing an exhaust flow conduit (eg, an ejector) in an inner diffuser wall of a diffuser of an exhaust collector;

[0011] Figure 4 is Figure 3 A partial cross-sectional view of the inner wall of the diffuser having an exhaust flow conduit (e.g., an ejector) taken within arcuate line 4-4, further illustrating details of the cooling system;

[0012] Figure 5 It is along Figure 4 a cross-sectional view of an inner wall of a diffuser having a discharge flow conduit (e.g., an ejector) taken along line 5-5, further illustrating details of the baffles and corresponding openings (e.g., a single continuous opening);

[0013] Figure 6 It is along Figure 4 a cross-sectional view of an inner wall of a diffuser having a discharge flow conduit (e.g., an ejector) taken along line 5-5, further illustrating details of the baffle and the plurality of discrete openings;

[0014] Figure 7 Yes Figure 1 and Figure 2 A schematic diagram of an embodiment of a cooling system is shown;

[0015] Figure 8 yes Figure 7a schematic cross-sectional view of an embodiment of a cooling system showing an arrangement of exhaust flow conduits circumferentially spaced about the axis of the diffuser;

[0016] Figure 9 Yes Figure 1 and Figure 2 A schematic diagram of an embodiment of a cooling system is shown;

[0017] Figure 10 is Figure 9 a partial side elevational view of the turbine shaft and coupling assembly taken within line 10 - 10 of FIG. 1 , further illustrating details of various flow directing features; and

[0018] Figure 11 is with Figure 9 A partial side view of the deflector plate adjacent the inlet of the exhaust flow conduit, further illustrating details of the deflector plate. DETAILED DESCRIPTION

[0019] A gas turbine generator may include a gas turbine engine enclosed within a housing and a turbine exhaust collector enclosed within another housing. To prevent heat from accumulating around a turbine shaft disposed within the gas turbine engine, which is coupled to a rotating shaft disposed within the turbine exhaust collector, the gas turbine generator includes one or more cooling systems to separate heat from the turbine and the rotating shaft. Unfortunately, the design of the ventilation system may limit the use of the gas turbine generator to environments within certain ambient temperature ranges and increase the operating cost of the gas turbine generator. Furthermore, the ventilation system may consume significant electrical power, thereby reducing the efficiency of the gas turbine generator.

[0020] Embodiments disclosed herein relate to a system for ventilating and cooling a turbine shaft and coupling assembly disposed within a gas turbine system. The gas turbine system includes a gas turbine engine and a turbine exhaust collector, and the gas turbine system may be coupled to one or more air inlet systems, a variable bleed valve (VBV) flow stack, a ventilation flow stack, and an exhaust flow stack. A turbine shaft disposed within a gas turbine engine housing is coupled to a turbine shaft and coupling assembly disposed within a turbine exhaust collector housing. The housings surrounding the gas turbine engine and the turbine exhaust collector may be independent. To prevent heat accumulation around the turbine shaft and coupling assembly, one or more cooling systems may be disposed within the turbine exhaust collector housing. The one or more cooling systems, in combination with the variable bleed valve (VBV) flow stack, the ventilation flow stack, and the exhaust flow stack, may purge and ventilate heat and exhaust products associated with the turbine shaft and coupling assembly. In certain embodiments, the cooling system disclosed herein utilizes ventilation flow within the gas turbine engine housing to extract a coolant flow from the turbine exhaust collector housing, particularly from a cavity containing the turbine shaft and coupling assembly. In certain embodiments, the cooling systems disclosed herein use the exhaust flow from the exhaust diffuser of the exhaust collector to draw coolant flow from a cavity containing the turbine shaft and coupling assembly. In certain embodiments, the cooling systems disclosed herein use the rotation of the turbine shaft and coupling assembly to help drive coolant flow from 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 potential for thermal expansion of the turbine shaft coupling assembly, reducing thermal stresses, and reducing the potential for shaft misalignment.

[0021] Figure 1 is a schematic block diagram of an embodiment of a gas turbine system 10 having multiple ventilation or cooling systems 11. The gas turbine system 10 includes a gas turbine engine 12, a turbine exhaust collector 13, a housing 2 (e.g., a turbine housing or chamber) disposed around the gas turbine engine 12, and a housing 3 (e.g., an exhaust collector shell) disposed around the turbine exhaust collector 13. As discussed in detail below, the cooling system 11 is configured to ventilate and cool a turbine shaft and coupling assembly 14 within the turbine exhaust collector 13 disposed within the housing 3, thereby helping to maintain the temperature of the turbine shaft and coupling assembly 14 below a threshold temperature as hot exhaust gas flows through the turbine exhaust collector 13. The disclosed embodiments of the cooling system 11 may be used individually or in any combination with one another.

[0022] The gas turbine engine 12 includes a compressor section having one or more compressors 16 (e.g., 1-30 compressor stages), each having a plurality of compressor blades 15; a combustor section having one or more combustors 18 (e.g., an annular combustor or multiple combustor cans), each having one or more fuel nozzles 17; and a turbine section having one or more turbines 20 (e.g., 1-30 turbine stages), each having a plurality of turbine blades 19. As shown, the turbine section 20 is drivingly coupled to the compressor section 16 using a shaft 21, and the turbine section 20 is drivingly coupled to a load (e.g., a generator 22) via a turbine shaft and coupling assembly 14 extending through the casing 3 of the turbine exhaust collector 13. In operation, the compressor section 16 compresses air received from the engine air intake section (e.g., an air intake duct or stack 23), supplies the compressed air and fuel to the combustor section 18 via fuel nozzles 17 for combustion to generate hot combustion gases, and then flows the hot combustion gases through the turbine section 20, causing the turbine blades 19 to drive the rotation of the shaft 21 and the turbine shaft and coupling assembly 14. The hot combustion gases are then exhausted from the gas turbine system 10 through the exhaust collector 13 and the combustion exhaust section (e.g., the combustion exhaust duct or stack 39). As discussed in further detail below, a certain amount of leakage flow (e.g., hot combustion gases, heated air, heated lubricant, etc.) may enter the casing 3, particularly within the exhaust collector 13, proximate to the turbine shaft and coupling assembly 14. Additionally, a certain amount of heat may be transferred through the walls of the casing 3 and / or the walls of the exhaust collector 13 to the interior of the exhaust collector 13, proximate to the turbine shaft and coupling assembly 14. The disclosed embodiments of the cooling system 11 are configured to facilitate ventilating and cooling the turbine shaft and coupling assembly 14 in light of this leakage flow and heat transfer.

[0023] Gas turbine system 10 includes multiple air intake and exhaust systems coupled to casings 2 and 3. For example, gas turbine system 10 includes an engine air intake section (e.g., an air intake duct or stack 23) that is coupled to casing 2 and extends inwardly into the casing and is coupled to the air intake of compressor section 16. Air intake duct 23 may include one or more air handling units 24 (e.g., air filters, muffler baffles, anti-freeze systems, etc.) disposed along the air flow path of the intake airflow passing through air intake duct 23 and entering compressor section 16, as indicated by arrow 25.

[0024] The gas turbine system 10 also includes a ventilation intake section (e.g., a ventilation intake duct or stack 26) and a separate ventilation exhaust section (e.g., a ventilation exhaust duct or stack 28) that are coupled to the casing 2 and fluidly coupled to an interior volume or chamber 27 surrounding the gas turbine engine 12. In certain embodiments, the ventilation intake duct 26 and / or the ventilation exhaust duct 28 include one or more fans 29 (e.g., an electric motor with a plurality of protruding fan blades) configured to force ventilation airflow inwardly through the duct 26 along an intake flow path, as indicated by arrows 30, through the chamber 27 surrounding the gas turbine engine 12 along a cooling flow path, as indicated by arrows 31, and outwardly through the duct 28 along an exhaust flow path, as indicated by arrows 32, thereby facilitating the removal of any heat surrounding the gas turbine engine 12 to avoid heat buildup and control the temperature of the gas turbine engine 12. The ventilation intake duct 26 also includes one or more air handling units, such as air filters 33.

[0025] The gas turbine system 10 also includes a compressor bleed air system 34 coupled to the compressor section 16 and the compressor bleed air section (e.g., a compressor bleed air discharge duct or stack 35). For example, in the illustrated embodiment, a compressor bleed air line or duct 36 extends from at least one compressor stage of the compressor section 16 to the compressor bleed air discharge duct 35, wherein the duct 36 includes a variable bleed air valve (VBV) 37 that is configured to vary the flow of bleed air, as indicated by arrow 38, of compressor air extracted from the compressor section 16 and discharged through the duct 35. The VBV 37 is configured to help control the gas turbine engine 12 by diverting compressed air from the compressor section 16, and thus the amount of bleed air flow can be varied according to various operating conditions of the gas turbine engine 12.

[0026] The gas turbine system 10 also includes a combustion exhaust section (e.g., a combustion exhaust duct or stack 39) configured to discharge an exhaust flow of combustion gases generated in the combustion section 18 of the gas turbine engine 12. In the illustrated embodiment, the combustion exhaust stack 39 is coupled to the casing 3 above the turbine exhaust collector 13. Specifically, the combustion exhaust stack 39 is fluidly coupled to an exhaust flow path 40 through the turbine exhaust collector 13, which is fluidly coupled to the turbine section 20.

[0027] The turbine exhaust collector 13 includes a diffuser 41 that at least partially defines an exhaust flow path 40 from an exhaust inlet 42 of the housing 3 to an exhaust outlet 43 of the housing 3. The exhaust inlet 42 is coupled to the exhaust discharge opening of the turbine section 20, and the exhaust outlet 43 is coupled to the combustion exhaust stack 39. In the illustrated embodiment, the diffuser 41 is coupled to the exhaust inlet 42 via a diffuser inner wall 44 and a diffuser outer wall 46. The diffuser inner wall 44 is disposed around (e.g., extends circumferentially around) a cavity 45 having a turbine shaft and the coupling assembly 14 (e.g., a rotating shaft). The diffuser outer wall 46 is disposed around (e.g., extends circumferentially around) the diffuser inner wall 44 at a radial offset from the diffuser inner wall 44. The exhaust flow path 40 is disposed between the diffuser inner wall 44 and the diffuser outer wall 46. For example, the exhaust flow path 40 may extend circumferentially around the diffuser inner wall 44. The diffuser inner wall 44 and the diffuser outer wall 46 may be at least partially or completely annular walls (e.g., concentric annular walls) that gradually diverge away 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 diffuser inner wall 44 and the diffuser outer wall 46 may diverge from the central axis 54 in a linear or nonlinear manner (e.g., along a curved path), such that the diffuser inner wall 44 and the diffuser outer wall 46 may include tapered wall portions and / or curved annular wall portions. In addition to diverging from the central axis 54, the diffuser inner wall 44 and the diffuser outer wall 46 may also diverge from each other in the downstream direction, as indicated by arrow 40, such that the offset distance (e.g., radial distance) between the diffuser inner wall 44 and the diffuser outer wall 46 increases in the downstream direction. In this way, the combustion gases flowing along the exhaust flow path 40 gradually expand or diffuse before entering the combustion exhaust stack 39.

[0028] As described above, the turbine shaft and coupling assembly 14 is disposed within a cavity 45 within the diffuser inner wall 44 of the diffuser 41. The turbine shaft and coupling assembly 14 may include a coupling 48 between a first shaft or turbine shaft portion 47 and a second shaft or generator shaft portion 49. The turbine shaft and coupling assembly 14 may also include a plurality of bearings 50, such as a bearing 51 along the first shaft 47 and a bearing 52 along the second shaft 49. The bearings 51 may be disposed at a turbine aft frame (TRF) section or wall 53 disposed at an upstream portion of the cavity 45 closest to the turbine section 20. The TRF wall 53 is coupled to the diffuser inner wall 44 such that the TRF wall 53 and the diffuser inner wall 44 substantially block combustion gases from entering the cavity 44. However, a certain amount of leakage flow may pass through the TRF wall 53, particularly at the bearings 51, and enter the cavity 44 housing the turbine shaft and coupling assembly 14. The cooling system 11 is configured to help ventilate and cool the turbine shaft and coupling assembly 14 , and thus the cooling system 11 may include various cooling features used alone or in combination with one another.

[0029] The cooling system 11 may include an air supply system 60 having one or more fans 61 (e.g., electric motors driving fan blades), a flow regulator 62 (e.g., valves), and / or an air handling unit 63 (e.g., an air filter). The air supply system 60 is configured to control the flow of air (or other coolant) into the cavity 45, as indicated by arrow 64. Alternatively or in addition, the air supply system 60 may be configured to control the flow of air 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 to control the flow into or out of the cavity 45. For example, cooling system 11 may include one or more intake flow conduits 65, 66 extending through housing 3 into cavity 45, one or more exhaust flow conduits 68 extending from cavity 45 through housing 3 to the external environment, one or more exhaust flow conduits 70 extending from cavity 45 through diffuser 41 from housing 3 to interior chamber 27 of housing 2 (i.e., into cooling flow path 31), and / or one or more exhaust flow conduits 72 extending from cavity 66 through diffuser inner wall 44 into exhaust flow path 40. These conduits 65, 66, 68, 70, and 72 may be used in various combinations to define a cooling flow path through cavity 45.

[0030] For example, in certain embodiments, one or more ducts 66 can supply a cooling flow (e.g., a cooling air flow) into the cavity 45, and then one or more ducts 68 can exhaust the cooling flow from the cavity 45 directly to the external environment. The one or more ducts 66 can direct the cooling flow into close proximity with the bearing 51, the TRF wall 53, and leakage flow at the bearing 51 and the TRF wall 53. Thus, the one or more ducts 66 can focus the cooling flow on hot spots in the cavity 45. In certain embodiments, the one or more ducts 65 and / or 66 can supply a cooling flow (e.g., a cooling air flow) into the cavity 45, the one or more ducts 70 can exhaust the cooling flow from the cavity 45 through the diffuser 41 into the interior chamber 27 of the housing 2, and then the ventilation exhaust duct 28 can exhaust the cooling flow out of the housing 2 in conjunction with the ventilation flow through the housing 2. As discussed in further detail below, each of the one or more ducts 70 can be coupled to or integrated with a strut extending between the diffuser inner wall 44 and the diffuser outer wall 46 of the diffuser 41. In certain embodiments, the one or more ducts 65 and / or 66 can supply a cooling flow (e.g., a cooling air flow) into the cavity 45, and the one or more ducts 72 can discharge the cooling flow from the cavity 45 into the exhaust flow path 40 between the diffuser inner wall 44 and the diffuser outer wall 46 of the diffuser 41. For example, the exhaust flow path 40 can draw the cooling flow from or out of the cavity 45 via the one or more ducts 72, so that each of the ducts 72 can be defined as an ejector. Alternatively or in addition, the air supply system 60 can use a fan 61 to push or force the cooling flow into the cavity 45 and out through the ducts 72 into the exhaust flow path 40. As discussed in further detail below, the ducts 70 can turn or bend along the exhaust flow path 40 in a downstream direction of the exhaust flow to facilitate drawing the cooling flow into the exhaust flow path 40 and / or to prevent exhaust gas from flowing back into the cavity 45. The cooling flow paths defined by conduits 65 , 66 , 68 , 70 , and 72 may represent individual cooling systems 11 and / or an integrated cooling system.

[0031] The cooling system 11 can also be configured to selectively control cooling flow along the cooling flow paths through the 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 completely open or close) the flow rate of coolant (e.g., ventilation or cooling air) into and / or out of the cavity 45 to help control the temperature within the cavity 45. The cooling system 11 can also include a plurality of sensors 76 (individually designated S) within the conduits 65, 66, 68, 70, and 72 and 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 coupling assembly 14, thereby helping to control the cooling flow to maintain the temperature of the cavity 45 and / or the turbine shaft and coupling assembly 14 at or below a threshold temperature. Sensors 76 may also monitor other operating parameters, such as the flow rate of the cooling flow, the pressure in cavity 45 and / or ducts 65, 66, 68, 70, and 72, vibrations or acoustic noise associated with the turbine shaft and coupling assembly 14, and thermal expansion or contraction of components (e.g., turbine shaft and coupling assembly 14, housing 3, exhaust collector 13, etc.). Cooling system 11 may also include a controller 78 coupled to air supply system 60, flow regulator 74, fan 29, and sensors 76.

[0032] The controller 78 may include one or more processors 79, a memory 80, and instructions 91 stored on the memory 80 and executable by the processor 79 to perform various monitoring functions using the sensors 76 and control functions using the cooling system 11 and the gas turbine system 11. The processor 79 may include one or more microprocessors, one or more "general-purpose" microprocessors, one or more special-purpose microprocessors, and / or one or more application-specific integrated circuits (ASICs), or some combination thereof. For example, the processor 66 may include one or more reduced instruction set computing (RISC) processors. The memory 80 may include tangible, non-transitory, 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, a hard drive, or any other suitable optical, magnetic, or solid-state storage medium, or a combination thereof). The instructions 81 stored on the memory 80 include machine-readable 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 circuitry, data processing circuitry, monitoring circuitry, and control circuitry. 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 set points and desired operating parameters, checking error logs and historical operations, etc.

[0033] In operation, in response to feedback from sensor 76, controller 78 may be configured to adjust air supply system 60, flow regulator 74, and / or fan 29 to change (i.e., increase or decrease) the flow rate and / or temperature of the cooling flow through cavity 45, thereby ventilating and cooling turbine shaft and coupling assembly 14. In certain embodiments, controller 78 may be configured to control cooling system 11 to provide cooling flow along a cooling flow path that passes through only one, all, or any number of conduits 65, 66, 68, 70, and 72. The controller 78 may be configured to control the cooling system 11 based on feedback from the sensors 76, historical data and trends of operating parameters (e.g., temperature, pressure, flow rate, vibration, or noise, etc.) within the cavity 45, lookup tables that correlate the monitored sensor data with various control functions (e.g., target flow rates through each of the ducts 66, 68, 70, 72, target fan speeds for the fans 29 and 61, target positions for the flow regulator 74, etc.), and computer models that correlate the monitored sensor data with the control functions. The controller 78 may also be configured to control the cooling system 11 based on upper and lower thresholds for operating parameters (e.g., temperature, pressure, flow rate, vibration, or noise, etc.) within the cavity 45. The controller 78 may also be configured to control the cooling system 11 based on various factors, such as gas turbine engine operation, ambient temperature, and relative humidity in the surrounding environment (i.e., outside the gas turbine system 10).

[0034] Figure 2 yes Figure 1 1 is a schematic side view of an embodiment of a gas turbine system 10, which shows a housing 2 having a gas turbine engine 12 exploded from a housing 3 having an exhaust collector 13. As shown, the housings 2 and 3 are separated from each other so that the side wall 90 of the housing 2 faces the side wall 92 of the housing 3. When the gas turbine system 10 is as shown in FIG. Figure 1 When fully assembled as shown, sidewalls 90 and 92 are disposed against (or at least in close proximity to) each other at interface 91. In certain embodiments, an upstream diffuser portion 94 may protrude from sidewall 92 of casing 3, and a diffuser recess 96 may extend into sidewall 90 of casing 2 adjacent turbine section 20. Upstream diffuser portion 94 may include a plurality of support struts 98 extending between diffuser inner wall 44 and diffuser outer wall 46 at an upstream position relative to duct 70. Figure 1 When fully assembled as shown, the upstream diffuser portion 94 extends into a diffuser recess 96 adjacent 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, such as Figure 2 shown.

[0035] As mentioned above Figure 1As discussed, the gas turbine system 10 includes one or more cooling systems 11, which may be independent of one another or integrated with one another. For example, the cooling system 11 may include a cooling system 100, which includes at least one or more intake flow ducts 65 and / or 66 and one or more exhaust flow ducts 68; a cooling system 102, which includes at least one or more intake flow ducts 65 and / or 66 and one or more exhaust flow ducts 70; and a cooling system 104, which includes at least one or more intake flow ducts 65 and / or 66 and one or more exhaust flow ducts 72. These cooling systems 100, 102, and 104 may be used individually or in combination with one another as components 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.

[0036] Heat sources within the gas turbine system 10 may be associated with heat transferred through a turbine rear frame (TRF) leak (e.g., at 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. A TRF leak 110 near the TRF wall 53 may transfer heat into the cavity 45. The TRF leak 110 may include a heated fluid leak, such as a heated gas leak (e.g., heated air, hot exhaust gases, etc.) and / or a heated liquid leak (e.g., heated lubricant), or heat transfer through the TRF wall 53. Along with the TRF leak 110, exhaust gases along the exhaust flow path 40 may transfer heat into the cavity 45 through the diffuser inner wall 44, as indicated by arrows 112, and heat from the turbine shaft and coupling assembly 14 may transfer into the cavity 45, as indicated by arrows 114. Thus, the TRF leak 110, heat transfer 112, and heat transfer 114 each contribute to heat accumulation 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 (eg, 100 , 102 , and / or 104 ) circulate a coolant flow through the cavity 45 .

[0037] 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 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, preformed sleeve bearings, plain bearings, and any combination thereof. The bearings 51 may be configured to absorb axial or radial loads. The bearings 51 may include one or more seals (e.g., elastomeric and / or metal sealing rings) within their housings to prevent fluid leakage (e.g., gas and / or liquid leakage) along the respective shafts (e.g., shafts 47 and 49 of the turbine shaft and coupling assembly 14). However, some leakage may occur at the bearings 51, such as the TRF leak point 110 described above. Unfortunately, leakage (e.g., TRF leak point 110) may also transfer heat into the cavity 45. Cooling system 11 (eg, 100 , 102 , and / or 104 ) is configured to help mitigate heat transfer associated with this leakage by ventilating and cooling cavity 45 .

[0038] For example, the cooling system 100 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) along a cooling flow path, as indicated by arrows 116 and 118, through one or more intake flow conduits 65 and / or 66 into the cavity 45, as indicated by arrows 120, through the cavity 45 to ventilate the cavity 45 and cool any hot spots (e.g., the turbine coupling assembly 14 and the TRF wall 53), and out of the cavity 45 through one or more exhaust flow conduits 68 as indicated by arrows 122. In certain embodiments, the cooling system 100 includes 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 (e.g., openings and / or tubes) are disposed in a sidewall 124 of the housing 3. The intake flow conduits 65 may include a filter, a flow conditioner 74, a sensor 76, or any combination thereof. The intake flow conduit 66 may extend laterally along a bottom portion of the diffuser 41, such as in a generally horizontal direction from the sidewall 124 toward the TRF wall 53. For example, the intake flow conduit 66 may extend along the diffuser inner wall 44 directly from the sidewall 124 to a distal end 126 proximate the TRF wall 53. In certain embodiments, the intake flow conduit 66 may extend at least 80%, 85%, 90%, or 95% of the horizontal distance between the sidewall 124 and the TRF wall 53. In this manner, the intake flow conduit 66 may help to focus the cooling flow directly onto hot spots associated with the TRF wall 53, the bearings 51, and the TRF leak points 110. Within the cavity 45, coolant flows from the intake flow conduits 65 and / or 66, may flow along the turbine shaft and coupling assembly 14, and along the diffuser inner wall 44, before being discharged through the exhaust flow conduit 68. In certain embodiments, the air supply system 60 (see Figure 1 ) uses fan 61 to force a coolant flow (e.g., airflow) into intake flow ducts 65 and / or 66, through cavity 45, and out through exhaust flow duct 68. However, in some embodiments, the rotational motion of the turbine shaft and coupling assembly 14 can help force the coolant flow to rotate, thereby helping to force the coolant flow out through exhaust flow duct 68. For example, the turbine shaft and coupling assembly 14 can include one or more flow directing features 128 (e.g., protrusions, recesses, bolts, nuts, fins, impeller blades, etc.) circumferentially spaced about axis 54 to help force the coolant flow to circulate throughout cavity 45 and then out through exhaust flow duct 68. Additionally, cooling system 100 can also rely in part on the natural upward rise of heat from cavity 45 through exhaust flow duct 68. In the illustrated embodiment, exhaust flow duct 68 comprises a vertical duct or stack.

[0039] As another example, cooling system 102 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) along a cooling flow path, as indicated by arrows 116 and 118, through one or more intake flow conduits 65 and / or 66 into cavity 45, as indicated by arrows 120, through cavity 45 to ventilate cavity 45 and cool any hot spots (e.g., turbine coupling assembly 14 and TRF wall 53), and out of cavity 45 through one or more exhaust flow conduits 70, as indicated by arrows 130. Similar to cooling system 100, certain embodiments of cooling system 102 may include 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. Intake flow conduits 65 and 66 have the features described above with reference to cooling system 100. Within cavity 45, coolant flows from intake flow conduits 65 and / or 66, may flow along the turbine shaft and coupling assembly 14, and along diffuser inner wall 44, before being exhausted through exhaust flow conduit 70. The coolant flow may be driven by the rotational movement of the air supply system 60 and / or the turbine shaft and coupling assembly 14, as described above with reference to the cooling system 100. Additionally or alternatively, the coolant flow may be driven (e.g., pulled or drawn) by ventilation flow through the housing 2, such as Figure 1 31 (e.g., ventilation flow 31 from the ventilation intake duct or stack 26 to the ventilation exhaust duct or stack 28 through the chamber 27). Specifically, the exhaust flow conduit 70 can be fluidly coupled to the chamber 27 of the housing 2, such as Figure 1 As shown. Figure 2As shown, each of the exhaust flow conduits 70 includes a first conduit portion 132 (e.g., a hollow support strut) extending between the diffuser inner wall 44 and the diffuser outer wall 46 of the diffuser 41, and a second conduit portion 134 extending between the diffuser outer wall 46 and the sidewall 92 of the housing 3. The first conduit portion 132 and the second conduit portion 134 are fluidically and structurally coupled together to define an exhaust flow path from the cavity 45 within the interior of the diffuser 41 to the chamber 27 within the interior of the housing 2. Thus, the first conduit portion 132 and the second conduit portion 134 are fluidically coupled together via an opening 136 in the diffuser outer wall 46, and the second conduit portion 134 is configured to be fluidically coupled to the chamber 27 within the interior of the housing 2 via an opening 138 in the sidewall 92 and an opening 140 in the sidewall 90. The ventilation flow 31 within the housing 2 facilitates the drawing (e.g., by negative pressure or suction) of the coolant flow through the exhaust flow conduits 70. In certain embodiments, cooling system 102 may use suction to draw coolant flow through conduits 65 and / or 66 , cavity 45 , and conduit 70 without requiring any additional fans (eg, fan 61 of air supply system 60 ).

[0040] As another example, cooling system 104 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) along a cooling flow path, as indicated by arrows 116 and 118, through one or more intake flow conduits 65 and / or 66 into cavity 45, as indicated by arrow 120, through cavity 45 to ventilate cavity 45 and cool any hot spots (e.g., turbine coupling assembly 14 and TRF wall 53), and out of cavity 45 through one or more exhaust flow conduits 72, as indicated by arrow 142. Similar to cooling systems 100 and 102, certain embodiments of cooling system 104 may include 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. Intake flow conduits 65 and 66 have the features described above with reference to cooling system 100. Inside the cavity 45, coolant flows from the intake flow conduits 65 and / or 66, may flow along the turbine shaft and coupling assembly 14 and along the diffuser inner wall 44, and then exits through the exhaust flow conduit 72. The coolant flow may be driven by the rotational motion of the air supply system 60 and / or the turbine shaft and coupling assembly 14, as described above with reference to the cooling system 100. Additionally or alternatively, the coolant flow may be driven (e.g., pulled or drawn) by the exhaust gas flow through the diffuser 41 along the exhaust flow path 40 between the diffuser inner wall 44 and the diffuser outer wall 46. As described below with reference to Figures 3 to 6Discussed in more detail, the exhaust flow conduit 72 fluidly couples the cavity 45 to the exhaust flow path 40 via one or more openings 144 through the diffuser inner wall 44. Exhaust flow along the exhaust flow path 40 facilitates drawing (e.g., by negative pressure or suction) the coolant flow through the exhaust flow conduit 72. The exhaust flow conduit 72, which induces flow by using suction, can be described as an ejector. In certain embodiments, the cooling system 104 can use suction to draw the coolant flow through the conduits 65 and / or 66, the cavity 45, and the conduit 72 without requiring any additional fan (e.g., the fan 61 of the air supply system 60). The exhaust flow conduit 72 shown defines an exhaust flow path that turns (e.g., turns the exhaust flow conduit) in a downstream direction of the exhaust flow passing along the exhaust flow path 40. By turning in the downstream direction, the exhaust flow conduit 72 helps prevent the exhaust flow from flowing back into the cavity 45. By turning in the downstream direction, the exhaust flow conduit 72 may also increase or control the suction provided by the exhaust flow to pull the coolant flow out of the cavity 45 and into the exhaust flow path 40 .

[0041] The aforementioned cooling systems 100, 102 and 104 may be used independently or in any combination with each other. Figure 1 As discussed, each of the conduits 65, 66, 68, 70, and 72 may include one or more flow regulators 74 and sensors 76 coupled to a controller 78. The controller 78 may monitor conditions (e.g., temperature, pressure, flow rate, vibration, noise, etc.) within the cavity 45 and the respective conduits 65, 66, 68, 70, and 72 and then adjust the cooling systems 100, 102, and 104 via the flow regulators 74, the air supply system 60, the fans 29, or any combination thereof. The cooling systems 100, 102, and 104 are hereinafter referred to as Figures 3 to 11 Discuss in more detail.

[0042] Figure 3 Yes Figure 1 and Figure 2 A schematic diagram of an embodiment of the cooling system 104 is shown. Figure 3 The cooling system 104 is shown without the cooling systems 100 and 102 and without the intake flow conduit 66. However, as described above, the cooling system 104 may be used alone or in combination with the cooling systems 100 and 102, and the cooling system 104 may include the intake flow conduit 66 in combination with the intake flow conduit 65. In the illustrated embodiment, the cooling system 104 is similar to the cooling system 100 described above with reference to FIG. Figure 1 and Figure 2The cooling systems described above are substantially the same. As described above, the cooling system 104 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) along a cooling flow path, as indicated by arrow 116, through one or more intake flow conduits 65 (and optionally conduit 66) into the cavity 45, through the cavity 45 as indicated by arrow 120 to ventilate the cavity 45 and cool any hot spots (e.g., the turbine coupling assembly 14 and the TRF wall 53), and out of the cavity 45 through one or more exhaust flow conduits 72 as indicated by arrow 142. Within the cavity 45, the coolant flows from the intake flow conduits 65, may flow along the turbine shaft and coupling assembly 14, and along the diffuser inner wall 44, before being exhausted through the exhaust flow conduits 72. The coolant flow may be driven (e.g., pulled or drawn) by the exhaust gas flow through the diffuser 41 along the exhaust flow path 40 between the diffuser inner wall 44 and the diffuser outer wall 46. Therefore, the exhaust flow conduits 72, which induce flow by using suction, may be described as ejectors. In certain embodiments, the cooling system 104 can use suction to draw the coolant flow through the conduit 65, the cavity 45, and the conduit 72 without requiring any additional fans (e.g., the fan 61 of the air supply system 60). The exhaust flow conduit 72 shown defines an exhaust flow path that turns (e.g., turns the exhaust flow conduit) in a downstream direction of the exhaust flow passing along the exhaust flow path 40. To simplify the drawings, as shown in FIG. Figures 1 to 2 The flow regulator 74 and sensor 76 in the conduit 72 are not Figure 3 Further details of the discharge flow conduit 72 (eg, ejector) are provided below with reference to Figures 4 to 6 Have a discussion.

[0043] Figure 4 is Figure 3 FIG4 is a partial cross-sectional view of the diffuser inner wall 44 having the exhaust flow conduit 72 (e.g., an ejector) taken within arcuate line 4-4 of FIG4 , further illustrating details of the cooling system 104. The exhaust flow conduit 72 (e.g., an ejector) may include one or more openings 144 (e.g., circular, oval, square, or polygonal openings) through the diffuser inner wall 44, and one or more baffles 202 and 204 coupled to the diffuser inner wall 44 and projecting into the exhaust flow path 40. The diffuser inner wall 44 includes an outer wall 206, an inner wall 208, and an insulating layer 210 disposed between the outer wall 206 and the inner wall 208. The insulating layer 210 helps block or resist heat transfer from the exhaust gas flow into the cavity 45 through the diffuser inner wall 44. The openings 144 extend through the inner wall 208, the insulating layer 210, and the outer wall 206. The baffles 202 and 204 are coupled to the outer wall 206 of the diffuser inner wall 44.

[0044] The opening 144 extends through the diffuser inner wall 44 along a central axis 200, wherein the central axis 200 can be straight or curved, can be oriented perpendicular to the diffuser inner wall 44, and / or can be angled relative to the diffuser inner wall 44 (e.g., angled in a downstream direction relative to the exhaust flow path 40). The opening 144 can also have a cross-sectional area or width that decreases or converges (e.g., defines a converging flow path) in the direction of the coolant flow 142 passing through the diffuser inner wall 44. In some embodiments, the cross-sectional area or width of the opening 144 can be at least partially uniform and / or decrease (e.g., diverge) in the direction of the coolant flow 142 passing through the diffuser inner wall 44. However, the converging cross-sectional area of ​​the opening 144 shown defines a throat 146, which can help prevent exhaust gas from flowing back from the exhaust flow path 40 into the cavity 45 within the diffuser 41.

[0045] Baffles 202 and 204 are generally steered relative to the central axis 200 of the opening 144, and specifically, steered in a downstream direction relative to the exhaust flow path 40. For example, baffles 202 and 204 may be steered approximately 90 degrees, until the exhaust outlet 203 is substantially parallel to the exhaust flow path 40 (e.g., the centerline between the diffuser inner wall 44 and the diffuser outer wall 46), or until the exhaust outlet 203 is substantially parallel to the surface 205 of the diffuser inner wall 44. Baffles 202 and 204 may include turning portions 207 and 209, respectively, which may include curved turning portions, tapered or angled turning portions, or any combination thereof. For example, turning portions 207 and 209 may include curved scoops (e.g., concave scoops), angled scoops, or any combination thereof. Baffles 202 and 204 may be equally spaced, converging, and / or diverging in the direction of coolant flow 142 through the diffuser inner wall 44 and the exhaust flow duct 72. The downstream orientation of baffles 202 and 204 can help block exhaust gas from flowing back from exhaust flow path 40 into cavity 45 inside diffuser 41. Additionally, baffle 204 is positioned downstream of baffle 202, and baffle 204 can help capture any liquid or debris in the exhaust flow. For example, if any liquid or debris is disposed along surface 205 of diffuser inner wall 44, baffle 204 can help block liquid or debris 202 from entering opening 144. Baffle 204 can also be positioned in a circumferential direction around diffuser inner wall 44 (i.e., circumferentially around axis 54 (see FIG. 1 )). Figure 1 )) redirects the liquid or debris, and then directs the liquid or debris to the exhaust pipe 148, such as Figure 1 For example, Figure 1 As shown, a conduit or collection trough 150 may be provided below the diffuser 41 so that any redirected liquid or debris flows into the drain 148 .

[0046] In certain embodiments, the cooling system 104 may include multiple sets of baffles 202 and 204, each associated with a corresponding opening 144. For example, Figure 5 It is along Figure 4 5 , 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) through the diffuser inner wall 44 extends circumferentially about the axis 54, for example, extending circumferentially about the axis 54 for approximately 180 degrees. Similarly, the baffles 202 and 204 of the discharge flow conduit 72 are positioned on opposite sides (i.e., upstream and downstream) of the opening 144 and extend circumferentially about the axis 54 for approximately 180 degrees. In certain embodiments, the opening 144 and the baffles 202 and 204 may extend at least 30, 45, 60, 75, 90, 120, 150, or 180 degrees about the axis 54. In some embodiments, the openings 144 may be continuous and uniform in a circumferential direction about the axis 54 , or the openings 144 may be continuous but have a varying geometry (eg, width) in a circumferential direction about the axis 54 .

[0047] Alternatively or in addition, the cooling system 104 may include a plurality of discrete groups of openings 144 located between the baffles 202 and 204. For example, Figure 6 It is along Figure 45 , further illustrating details of the baffles 202 and 204 and the plurality of discrete openings 144. In the illustrated embodiment, the openings 144 are circumferentially spaced apart from one another in a circumferential direction about the axis 54, and the openings 144 extend a circumferential distance of approximately 180 degrees about the axis 54. In certain embodiments, the openings 144 and the baffles 202 and 204 may extend a circumferential distance of at least 30, 45, 60, 75, 90, 120, 150, or 180 degrees about the axis 54. Each of the illustrated openings 144 converges from the inner wall 208 of the diffuser inner wall 44 to the outer wall 206, and the openings 144 have the same geometry and are equidistantly spaced apart from one another. In some embodiments, the openings 144 can have converging, diverging, and / or uniform flow paths from the inner wall 208 to the outer wall 206 of the diffuser inner wall 44. The openings 144 can have different geometries, such as different converging geometries (e.g., converging geometries with different convergence angles, different cross-sectional areas, etc.), different diverging geometries, different uniform geometries, or a combination of various types of geometries (e.g., converging, diverging, and / or uniform geometries). In the illustrated embodiment, a set of baffles 202 and 204 extends along all of the openings 144. In some embodiments, a pair of baffles 202 and 204 can be dedicated to each of the openings 144, or a pair of baffles 202 and 204 can be dedicated to two or more of the openings 144 (but less than the total number of openings 144 in the diffuser inner wall 44).

[0048] Figure 7 Yes Figure 1 and Figure 2 A schematic diagram of an embodiment of the cooling system 102 is shown. Figure 7 The cooling system 102 is shown without the cooling systems 100 and 104 and without the intake flow conduit 66. However, as described above, the cooling system 102 may be used alone or in combination with the cooling systems 100 and 104, and the cooling system 102 may include the intake flow conduit 66 in combination with the intake flow conduit 65. In the illustrated embodiment, the cooling system 102 is similar to the cooling system 102 described above with reference to FIG. Figure 1 and Figure 2The cooling systems described above are substantially the same. As described above, the cooling system 102 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) along a cooling flow path, as indicated by arrow 116, through one or more intake flow conduits 65 (and optionally conduit 66) into the cavity 45, through the cavity 45 as indicated by arrow 120 to ventilate the cavity 45 and cool any hot spots (e.g., the turbine coupling assembly 14 and the TRF wall 53), and out of the cavity 45 through one or more exhaust flow conduits 70 as indicated by arrow 130, and then out through the ventilation exhaust duct or stack 28 coupled to the casing 2. Within the cavity 45, the coolant flows from the intake flow conduits 65, may flow along the turbine shaft and coupling assembly 14, and along the diffuser inner wall 44, before being discharged through the exhaust flow conduits 70. The exhaust flow conduits 70 are fluidly coupled to the chamber 27 within the casing 2, where the ventilation flow 31 flows from the ventilation intake duct or stack 26 through the casing 2 to the ventilation exhaust duct or stack 28 to help ventilate the gas turbine engine 12. The ventilation flow 31 provides the motive force or negative pressure to draw the coolant flow from the exhaust flow conduit 70. Thus, the coolant flow can be driven (e.g., pulled or sucked) by the ventilation flow 31 passing through the housing 2, thereby pulling the coolant flow into the chamber 27 and out through the ventilation exhaust duct or stack 28. For these reasons, the exhaust flow conduit 70 can be described as an ejector. In certain embodiments, the cooling system 102 can use suction to pull the coolant flow through the conduit 65, the cavity 45, and the conduit 70 without the need for any additional fan (e.g., the fan 61 of the air supply system 60). Additional details of the exhaust flow conduit 70 (e.g., ejector) are provided below with reference to Figure 8 Have a discussion.

[0049] Figure 8 yes Figure 7Schematic cross-sectional view of an embodiment of a cooling system 102 of the diffuser 41 is shown, which shows an arrangement of exhaust flow conduits 70 (e.g., radial conduits) circumferentially spaced about the axis 54 of the diffuser 41. The exhaust flow conduits 70 can have a variety of shapes and sizes, such as cylindrical conduits, conduits having an airfoil-shaped cross-section, conduits having an elliptical cross-section, etc. As described above, each of the exhaust flow conduits 70 includes a first conduit portion 132 (e.g., a hollow support strut or radial strut) extending between the diffuser inner wall 44 and the diffuser outer wall 46 of the diffuser 41, and a second conduit portion 134 extending between the diffuser outer wall 46 and the sidewall 92 of the casing 3. Each of the exhaust flow conduits 70 has a first conduit portion 132 that is fluidly coupled to the cavity 45 inside the diffuser inner wall 44 and a second conduit portion 134 that is fluidly coupled to the chamber 27 inside the casing 2 that houses the gas turbine engine 12. Specifically, the second conduit portion 134 is coupled to the opening 138 in the side wall 92 of the shell 3, which in turn is fluidly coupled to the opening 140 in the side wall 90 of the shell 2. In the illustrated embodiment, the exhaust flow conduits 70 are equally spaced in the circumferential direction about the axis 54, and each of the exhaust flow conduits 70 has the same geometry. In some embodiments, the exhaust flow conduits 70 may be unevenly spaced in the circumferential direction about the axis 54, and / or the geometry of the exhaust flow conduits 70 may vary from conduit to conduit. For example, the exhaust flow conduits 70 may be more closely spaced or concentrated in areas having hot spots, the exhaust flow conduits 70 may have a larger cross-sectional area in areas having hot spots, or a combination thereof. Although Figure 8 A specific number of exhaust flow conduits 70 are shown, but embodiments of the cooling system 102 may have any number of exhaust flow conduits 70 (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 15, 20, or more).

[0050] Figure 9 Yes Figure 1 and Figure 2 A schematic diagram of an embodiment of a cooling system 100 is shown. Figure 9 The cooling system 100 is shown without the cooling systems 102 and 104 and without the intake flow conduit 65. However, as described above, the cooling system 100 may be used alone or in combination with the cooling systems 102 and 104, and the cooling system 100 may include the intake flow conduit 65 in combination with the intake flow conduit 66. In the illustrated embodiment, the cooling system 100 is similar to the cooling system 100 described above with reference to FIG. Figure 1 and Figure 2The cooling systems described above are substantially the same. As described above, the cooling system 100 is configured to push or pull a coolant flow (e.g., ventilation or cooling air) along a cooling flow path, as indicated by arrows 118 through one or more intake flow conduits 66 (and optionally conduit 65) into the cavity 45, as indicated by arrows 120 through the cavity 45 to ventilate the cavity 45 and cool any hot spots (e.g., the turbine coupling assembly 14 and the TRF wall 53), and then out of the cavity 45 through one or more exhaust flow conduits 68 as indicated by arrows 122.

[0051] The intake flow duct 66 may include multiple intake sections 250, such as an intake section 252 coupled to the sidewall 124 and an intake section 254 extending upward from a bottom wall 256 of the housing 3. The intake sections 250 (e.g., 252 and 254) may include one or more openings, ducts, and / or baffles configured to direct coolant flow into the intake flow duct 66. The intake sections 250 may also include air handling units, such as an air handling unit 258 in the intake section 252 and an air handling unit 260 in the intake section 254. The air handling units 258 and 260 may include screens, filters, or any combination thereof. The illustrated intake flow duct 66 extends along a bottom portion of the diffuser 41 (e.g., along the diffuser inner wall 44) and may include a walkway or user access platform 262. The intake flow duct 66 extends toward a hot spot associated with a TRF leak point 110 at the TRF wall 53 and the bearing 51. The distal end 126 of the intake flow conduit 66 is positioned proximate to the TRF leak point 110, the TRF wall 53, and / or the bearing 51, thereby helping to focus the coolant flow at the hot spot. In certain embodiments, one of the intake flow conduits 66 may extend to each hot spot in the cavity 45. Thus, after exiting the intake flow conduit 66, the coolant flow initially contacts the hot spot and then circulates throughout the cavity 45.

[0052] Within cavity 45, coolant flows from intake flow duct 66, may flow along turbine shaft and coupling assembly 14, and along diffuser inner wall 44, before exiting through exhaust flow duct 68. In certain embodiments, the rotational motion of turbine shaft and coupling assembly 14 may help force the coolant flow to rotate, thereby helping to force the coolant flow out through exhaust flow duct 68. Thus, as described above, one or more flow-directing features 128 (e.g., protrusions, recesses, bolts, nuts, fins, impeller blades, etc.) on turbine shaft and coupling assembly 14 help drive the coolant flow as the features 128 rotate with assembly 14. However, cooling system 100 may also rely in part on natural upward heat rise through exhaust flow duct 68, fan 61 of air supply system 60, or any combination thereof. Cooling system 100 may also include features to control the discharge of coolant flow through exhaust flow duct 68. For example, a deflector plate 264 (e.g., one or more baffles or walls) may be disposed within cavity 45 adjacent to inlet 266 of exhaust flow duct 68. The deflector plate 264 is configured to deflect (e.g., redirect) at least a portion of the coolant flow within the cavity 45 so that the coolant flow exits through the exhaust flow conduit 68. The exhaust flow conduit 68 may also include one or more treatment units 266 (e.g., screens, filters, sound absorbing sections, etc.) and a top cover 268 that may be configured to disperse the coolant flow. Additional details of the flow directing features 128 and the deflector plate 264 are provided below with reference to Figure 9 and Figure 10 A discussion was held.

[0053] Figure 10 is Figure 9 FIG10 is a partial side view of the turbine shaft and coupling assembly 14 taken within line 10-10 of FIG10, further illustrating details of various flow-guiding features 128 disposed on shaft 47, coupling 48, and shaft 49. In certain embodiments, the flow-guiding features 128 disposed on shafts 47 and 49 may include radial protrusions 280 (e.g., fins, impeller blades, or rectangular plates) spaced circumferentially about axis 54. Additionally or alternatively, the flow-guiding features 128 disposed on coupling 48 may include fasteners 282 (e.g., threaded fasteners) spaced circumferentially about axis 54. The fasteners 282 may couple shafts 47 and 49 together at respective flanges 284 and 286. Each of the fasteners 282 may extend axially through flanges 284 and 286 and 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 certain embodiments, the fasteners 282 may provide sufficient motive force to drive coolant flow out through the exhaust flow conduit 68 with or without the radial protrusions 280 as the turbine shaft and coupling assembly 14 rotates during operation of the gas turbine engine 12 .

[0054] Figure 11 is with Figure 9 A partial side view of a deflector plate 264 adjacent to the inlet 266 of the exhaust flow duct 68 is shown, further illustrating details of the deflector plate 264. As shown, the deflector plate 264 projects inwardly from the diffuser inner wall 44 toward the turbine shaft and coupling assembly 14 (i.e., in an inward radial direction relative to the axis 54). For example, the deflector plate 264 may extend a radial distance of at least 10%, 20%, 30%, 40%, 50%, 60%, 70%, or 80% of the total radial distance between the diffuser inner wall 44 and the turbine shaft and coupling assembly 14. The deflector plate 264 is configured to capture the coolant flow, indicated by arrows 120, and then redirect the coolant flow into the exhaust flow duct 68.

[0055] The technical effects of the present invention include one or more cooling systems 11 (e.g., 100, 102, and / or 104) configured to ventilate a housing 3 having an exhaust collector 13. The heat sources are derived from leakage from a turbine rear frame (TRF), exhaust heat, and heat from a shaft 21 coupled to a turbine shaft and coupling assembly 14 within the gas turbine system 10. An embodiment of the present disclosure provides a system comprising one or more cooling systems 11 disposed within a gas turbine system. In certain embodiments, the cooling system 104 comprises an exhaust flow duct 72 (e.g., an ejector) disposed on an inner wall 44 of a diffuser in the turbine exhaust collector 13 such that the exhaust flow along the exhaust flow path 40 draws a coolant flow from a cavity 45 surrounding the turbine shaft and coupling assembly 14 based on the high velocity of the combustion exhaust gas. In certain embodiments, the cooling system 102 may include one or more exhaust flow ducts 70, each including a first duct portion 132 (e.g., a hollow support strut) extending between the diffuser inner wall 44 and the diffuser outer wall 46 of the diffuser 41, and a second duct portion 134 extending between the diffuser outer wall 46 and the sidewall 92 of the housing 3. The ventilation flow 31 within the housing 2 draws coolant flow from the cavity 45 through the exhaust flow duct 70 and then discharges the coolant flow with the ventilation flow using the ventilation exhaust duct or stack 28. In certain embodiments, the cooling system 100 draws coolant flow through the intake flow duct 66 (e.g., along a walkway or user access platform 262), thereby directing the coolant flow to hot spots (e.g., TRF leak points 110). The cooling system 100 may also use the rotation of the turbine shaft and coupling assembly 14 to help drive coolant out of the cavity 45 through the exhaust flow duct 68. These cooling systems 100 , 102 , and 104 may be used independently or in any combination with one another to ventilate the cavity 45 and cool the turbine shaft and coupling assembly 14 .

[0056] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims

1. A system for cooling a turbine shaft coupling, comprising: A turbine exhaust collector (13) comprising: A first housing (3) having an exhaust inlet (42) and an exhaust outlet (43); a diffuser (41) coupled to the exhaust inlet (42), The diffuser (41) includes a diffuser inner wall (44) arranged around a cavity (45) having a rotation axis (14), a diffuser inner wall (46) arranged around the diffuser inner wall (46) a diffuser outer wall (46) provided, and an exhaust flow path (40) between the diffuser inner wall (44) and the diffuser outer wall (46); and A first cooling flow path extending through the cavity (45) having the rotating shaft (14), wherein the first housing (3) Separated from a second housing (2) surrounding a gas turbine (12), wherein the first cooling flow path extends through at least one passage through the diffuser inner wall (44) into the exhaust flow path (40), The at least one passage has a cross-sectional area that decreases in a direction from the cavity (45) to the exhaust flow path (40).

2. The system for cooling a turbine shaft coupling according to claim 1, comprising the second housing (2) having the gas turbine (12).

3. The system for cooling a turbine shaft coupling according to claim 2, comprising a ventilation system (11) coupled to the second housing (2), wherein the ventilation system comprises a second cooling flow path through the second housing (2).

4. The system for cooling a turbine shaft coupling of claim 3, wherein the first cooling flow path is coupled to the second cooling flow path, wherein the second cooling flow through the second cooling flow path is configured to provide suction to draw the first cooling flow from the first cooling flow path.

5. The system for cooling a turbine shaft coupling of claim 1, wherein the first cooling flow path extends through the cavity (45) and at least one hollow strut (132) extending between the diffuser inner wall (44) and the diffuser outer wall (46).

6. The system for cooling a turbine shaft coupling of claim 1, comprising a first baffle (202) coupled to the diffuser inner wall (44) upstream of the at least one passage, wherein the first baffle (202) turns in a downstream direction of the exhaust flow path.

7. The system for cooling a turbine shaft coupling of claim 6, comprising a second baffle (204) coupled to the diffuser inner wall (44) downstream of the at least one passage, wherein the second baffle (204) is configured to capture liquid or debris.

8. The system for cooling a turbine shaft coupling according to claim 1, comprising a duct extending through the cavity (45) along the diffuser inner wall (44) toward a turbine aft frame (53), wherein the rotating shaft (14) is configured to be coupled to a turbine shaft (14) extending through a hole in the turbine aft frame (53), and wherein the first cooling flow path extends through the duct to direct a first cooling flow toward the turbine aft frame (53).

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