• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    It is a system for adjusting the amount of air delivered through a pressure boundary in a gas turbine disclosed having a passage (30) disposed at the pressure boundary. Further, mounted in the passageway (30) is a temperature activatable valve (32) configured to initiate at a predetermined temperature threshold. In particular, the temperature-activatable valve (32) triggers to switch from a closed position to an open position when the local temperature at the temperature-activatable valve (32) reaches or exceeds the predetermined temperature threshold to allow air to flow through the passage.
    公开号:CH702540B1
    申请号:CH00007/11
    申请日:2011-01-03
    公开日:2016-06-15
    发明作者:Henry Langdon Richard；Charles Liotta Gary
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Field of the invention
    The subject matter disclosed herein relates to a system for adjusting the amount of air delivered by a pressure limit in a gas turbine and a gas turbine having such a system. The system is designed to relieve high temperature areas in a gas turbine, with temperature activated valves for installation in a gas turbine to selectively flow air to high temperature areas.
    Background to the invention
    Gas turbines are widely used in commercial enterprises for energy production. A conventional gas turbine includes a plurality of combustors arranged in an annular array about the axis of the engine. A compressor supplies compressed air to each combustion chamber, mixing and burning the compressed air and fuel. Hot combustion gases flow from each combustion chamber to the turbine section of the engine where energy is withdrawn from the combustion gases to perform work.
    It is well known that the thermodynamic efficiency of a gas turbine increases when the operating temperature, namely the combustion gas temperature increases. Higher temperature combustion gases contain more energy and produce more work as the combustion gases expand in the turbine. However, as temperatures have been increased to improve the efficiency of gas turbines, it has become necessary to supply cooling air to the turbine components to maintain the temperatures of such components at allowable levels. Thus, in higher temperature operating conditions, the amount of cooling air that is needed is relatively high. In contrast, less cooling air is needed for certain turbine components during lower temperature operating conditions. In addition, the required cooling capacity can e.g. vary from machine to machine due to leakage from the first stage blades, hot gas suction, or environmental conditions.
    Despite these different operating conditions and variations between machines, the prior art has generally not provided a system that adjusts the flow of air delivered to the turbine components. As a result, since the machine must be designed to ensure operation at the maximum temperature, too much cooling air is supplied during operation at a lower temperature, which generally reduces the efficiency of the machine during such periods of operation.
    Accordingly, there is a need for a system in a gas turbine that supplies cooling air to turbine components only as needed, e.g. during operation at higher temperatures. Such a system would provide improved efficiency and increased power output during lower temperature operation without affecting the turbine components during higher temperature operation.
    Brief description of the invention
    In accordance with the present invention, a system for adjusting the amount of air delivered through a pressure boundary in a gas turbine includes a passage located at the pressure boundary and a temperature-activatable valve mounted in the passage. The temperature activatable valve is configured to actuate at a predetermined temperature threshold. According to the present invention, the temperature-activatable valve triggers to switch from a closed position to an open position when the local temperature at the temperature-activatable valve reaches or exceeds the predetermined temperature threshold to allow cooling air to flow through the passage.
    According to an advantageous development of the present invention, the system comprises at least one temperature-activated thermo valve, a plurality of temperature-activated anti-suction valves and a plurality of passages which are arranged at a pressure limit in the gas turbine. The thermal valve is mounted in one of the passages and is configured to actuate at a predetermined temperature threshold. In particular, the thermal valve is normally in a closed position and, when activated based on the local temperature on the thermo-valve, switches to an open position to allow cooling air to flow through the passage. In addition, the anti-wicking valves are mounted in the remaining passages, an anti-wicking valve in each pass, and are configured to trigger against each other at increasing predetermined temperature thresholds. Each anti-siphon valve is initially in a closed position and permanently shifts to an open position upon actuation based on the local temperature at each anti-siphon valve to allow anti-siphoning air through the passageway Passages through it, so that the anti-intake air flowing through the plurality of anti-suction passages causes a pressure increase downstream of the pressure limit, whereby a suction of hot gases downstream of the pressure limit is reduced.
    The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present invention and, together with the description, serve to explain the principles of the present subject matter.
    Brief description of the drawings
    A complete and an implementation enabling disclosure of the present subject matter, including the best mode thereof, which is directed to a person skilled in the art is given in the description which refers to the accompanying figures, in which:<Tb> FIG. 1 <SEP> is a cross-sectional view of a part of a gas turbine;<Tb> FIG. 2 <SEP> is a cross-sectional view of one embodiment of a system for adjusting the amount of air flowing through a pressure boundary according to one aspect of the present subject matter;<Tb> FIG. 3 <SEP> is a cross-sectional view of one embodiment of a temperature-activated valve in a closed position according to one aspect of the present subject matter;<Tb> FIG. 4 is a cross-sectional view of the embodiment illustrated in FIG. 3 in an open position according to an aspect of the present subject matter;<Tb> FIG. 5 is a cross-sectional view of another embodiment of a temperature activated valve in a closed position according to an aspect of the present subject matter;<Tb> FIG. FIG. 6 is a cross-sectional view of the embodiment illustrated in FIG. 5 in an open position according to an aspect of the present subject matter; FIG.<Tb> FIG. 7 is a cross-sectional view of another embodiment of a system for adjusting the amount of air flowing through a pressure boundary in accordance with an aspect of the present subject matter;<Tb> FIG. 8 is a cross-sectional view of one embodiment of a temperature activated valve in a permanently open position according to an aspect of the present subject matter; and<Tb> FIG. FIG. 9 is a cross-sectional view of one embodiment of a system for adjusting both the amount of cooling air and the amount of anti-intake air flowing through a pressure boundary according to one aspect of the present subject matter.
    Detailed description of the invention
    [0010] The present invention will now be described in detail, one or more examples of which are illustrated in the drawings. Each example is provided to illustrate and not limit the present subject matter.
    A cross-sectional view of a portion of a gas turbine is illustrated in FIG. Pressurized air discharged from the compressor section 10 passes through a chamber 24 formed through the compressor exhaust housing 12 and into the combustion section 14, generally characterized by a plurality of combustors 16 which are annularly disposed about an annular array the axis of the engine or the engine are arranged (of which in Fig. 1, only a single is shown). As is generally understood, the compressor exit air forms the high pressure air flowing within a gas turbine. The pressurized air is mixed with fuel in each combustion chamber 16 and burned. The hot combustion gases flow from the combustion section 14 into the turbine section 18 to drive the turbine and generate energy. The turbine section 18 includes a plurality of rotor wheels 20 having the turbine rotor with each rotor wheel 20 rotatably mounted to the rotor shaft.
    In the various sections of a gas turbine numerous pressure limits are present. As used herein, the term pressure limit refers to any location where the pressure on one side of a stationary structure is greater than the pressure on the opposite side of that structure. These pressure limits also usually define locations where significant temperature differences exist. As a result, it is common to place passages or holes, such as dilution holes or boreholes, at such pressure limits to allow cooler, high pressure air to flow into and cool the higher temperature and lower pressure areas.
    As illustrated in Fig. 1, e.g. pressurized air flowing in the chamber 24, a pressure limit defined by the compressor discharge housing 12 between the chamber 24 and the front wheel space 28. Often, at this pressure limit, e.g. at position A, a wellbore (not shown) to allow a constant flow of the high pressure, cooler compressor exit air to enter the front wheel space 28 to reduce the high temperatures and to cool the turbine components. However, the operating temperatures in the front wheel space 28 may vary significantly due to differing operating condition temperatures and expected variations between engines, such as the amount of first stage rotor blades or hot gas suction leakage. As such, the wellbore must be configured to provide sufficient cooling air at the maximum operating temperatures. As a result, at a lower operating temperature, an excessive amount of cooling air enters the front wheel space 28, resulting in reduced output powers of the engine. To address this problem, a system, as described in greater detail below, may be introduced at such pressure limits to supply cooling air only as needed to maintain the output of the engine at cooler operating temperatures.
    Fig. 2 shows an inventive system for adjusting or adjusting the amount of cooling air, which is supplied by a pressure limit in a gas turbine. The system includes a thermal valve passage 30 disposed at a pressure boundary in a gas turbine. As used herein, the term "passage" refers to any through hole that extends from one side of one pressure boundary to another. Thus, e.g. the term "passage" includes a wellbore drilled through a pressure boundary or a preformed hole formed through a pressure boundary.
    As illustrated, the passageway 30 is located at a location A (FIG. 1) at the pressure boundary defined by the compressor discharge housing 12. However, it should be appreciated by those skilled in the art that the passageway 30 could be located anywhere along such pressure boundary or at any other pressure boundary within the gas turbine engine. In addition, it should be understood that numerous thermal valve passages could be located at a pressure boundary.
    The system further includes a temperature-activated, hereinafter also referred to as "temperature-activated", thermo valve 32 which is mounted in the passage 30. The thermal valve 32 may be mounted in the passageway by any method. For example, For example, the thermal valve 32 could be press fit into the passage 30, or both the thermal valve 32 and the passage 30 could be threaded to allow the thermal valve 32 to be mounted in the passage 30.
    As described in greater detail below, the thermal valve 32 may normally be in a closed position and may be configured to be triggered at a predetermined temperature threshold based on the local temperature at the thermal valve 32 to switch to an open position. When open, the thermal valve 32 allows cooling air to flow through the passageway 30 to a high temperature area. Thus, in the illustrated embodiment, the thermal valve 32 may be configured to switch to an open position upon activation when the temperature of the front wheel space 28 near the position A reaches a predetermined temperature threshold. This allows higher pressure and lower temperature derived air, derived from the compressor 10, to flow through the passageway 30 to reduce the temperature of the wheelspace and to cool turbine components.
    It should be readily understood that the predetermined temperature threshold at which thermo-valve 32 is designed to initiate according to its configuration may vary depending on numerous factors. The temperature threshold may be dependent upon the estimated operating condition temperatures for a particular turbine, the temperature ranges generally expected at a particular temperature limit, or other varying engine conditions. In the illustrated embodiment, the predetermined temperature threshold may be e.g. depend on the factors mentioned above as well as the amount of hot gas suction within the front gear space 28 and the properties of the materials used in the manufacture of the adjacent turbine components, such as the rotor wheels 20 (Figure 1). If a suitable temperature threshold is calculated, the thermal valve 32 may be configured to trip at that temperature threshold to switch to the open position.
    It should be further understood that the thermal valve 32 may be a temperature-activated valve of any type, as well known to those skilled in the art. As used herein, the term "temperature-activated valve" refers to any valve that triggers or activates due to temperature-activated elements disposed in the valve. Thus, a temperature-activated valve triggers due to its own internal components. Accordingly, the term "temperature-activated valve" does not include a valve that is connected to a sensor or other sensing device and that triggers or activates temperatures or other parameters sensed externally (outside the valve) by the sensor or sensing device.
    In one embodiment, as illustrated in Figs. 3 and 4, the temperature-activated thermo valve 32 is a bimetal element valve. Such valves are commonly used in the steam generation industry and are known e.g. in U.S. Patent No. 4,427,149 (Adachi). Referring to FIGS. 3 and 4, the thermal valve 32 includes a housing 34 having an upper chamber 38 and a lower chamber 36. The upper chamber 38 includes exhaust ports 40 and an opening 42 defined by the valve seat 44. The lower chamber 36 receives opposite pairs 46, 48 of bimetallic elements 50 and includes an opening 52 that allows local air to enter the lower chamber 36. A valve head 54 is attached to a valve stem 56 and configured such that when the thermal valve 32 is in a closed position (FIG. 3), the valve head 54 sealingly engages the valve seat 44.
    The opposing pairs 46, 48 of bimetallic elements 50 are disposed along the valve stem 56 in the lower chamber 36 and may be secured thereto by any attachment mechanism 58, as is well known to those skilled in the art. The opposed inner sides 60 of each pair of bimetallic elements 50 have coefficients of thermal expansion that are smaller than the thermal expansion coefficients of the outer sides 62 so that the elements 50 have an arrangement when exposed to temperatures below a certain threshold temperature and occupy a second configuration. when heated to or above such a temperature threshold. In particular, the opposed pairs 46, 48 may be configured such that the bimetallic elements 50 change from a substantially horizontal arrangement to arcuate shapes as the temperature of the air in the lower chamber 36 reaches or exceeds the predetermined temperature threshold, the elements 50 each pair 46, 48 are arranged such that the curved sides face each other.
    As a result of this configuration, the valve head 54 is pulled away from the valve seat 44 to an open position (Figure 4) allowing pressurized cooling air to flow through the passageway 30 (not illustrated) into and into the opening 42 flows through the outlet channels 40. When the local temperature at the bimetallic elements 50 decreases below the predetermined temperature threshold, the thermal valve 32 returns to the closed position (FIG. 3) which prevents the cooling air from flowing through the valve 32. It should be understood, of course, that the bimetallic elements 50 may be constructed of different combinations of metals and thus may fire at different temperatures to ensure that the thermal valve 32 is triggered at the desired temperature threshold.
    According to an alternative embodiment of a temperature-activated thermo valve 32, as illustrated in Figs. 5 and 6, the thermal valve 32 is a fluid-filled bellows valve. Similar to the bimetal element valve described above in FIGS. 3 and 4, liquid-filled bellows valves are commonly used in the steam generation industry. Such valves are e.g. in U.S. Patent No. 4,560,105 (Jiandani).
    Referring to Figs. 5 and 6, the thermal valve 32 includes a housing 34 having an upper chamber 38 and a lower chamber 36. The upper chamber 38 includes exhaust ports 40 and an opening 42 defined by the valve seat 44. The lower chamber 36 receives a fluid-filled bellows 64 and includes an opening 52 that allows air to enter the lower chamber 36. A valve head 54 is attached to a valve stem 56 and configured such that when the thermal valve 32 is in a closed position (FIG. 5), the valve head 54 sealingly engages the valve seat 44. The valve stem 56 is mounted to an end 66 of the bellows 64 which has opposite ends 66, 68 which are interconnected via an accordion-shaped sidewall 70.
    The bellows 64 contains a liquid whose saturation temperature corresponds to a predetermined temperature threshold, so that at such a temperature threshold, the liquid in the interior of the bellows 64 changes to a gaseous state and causes the bellows expands and the valve 32 triggers to in to change an open position. As the bellows expands, the valve head 54 moves away from the valve seat 44 toward an open position (FIG. 6) allowing pressurized cooling air to flow through the passageway 30 (not illustrated) into the opening 42; and flows through the exhaust passages 40. When the local temperature near the bellows 64 drops below the predetermined temperature threshold, the thermal valve 32 returns to the closed position (Figure 5), where it prevents the cooling air from flowing through the valve. Similar to the different combinations of metals for the bimetallic elements 50 described above, it should be appreciated that different mixtures of liquids may be included in the bellows 64 to ensure that the thermo-valve 50 trips at the desired temperature threshold.
    As indicated above, the thermal valve may be designed to normally assume a closed position (FIGS. 3 and 5). Thus, when the local temperature at the thermo-valve 32 is below the predetermined temperature threshold, the thermo-valve remains closed, and no cooling air is supplied through the thermo-valve passage 30. This could e.g. can be accomplished by incorporating a simple (not illustrated) biasing mechanism, such as a spring, into the thermal valve 32 to ensure that the valve head 54 remains sealingly connected to the valve seat 50 when the temperature-activated elements are not activated.
    In addition, it should be appreciated that the thermal valve 32 may be configured to either preemptively or reactively actuate based on the local temperature at the thermal valve 32 to change to its open position. In particular, the thermal valve may be configured to initiate preventive to ensure that the temperatures remain at allowable levels at the pressure limit. Since components in the inner wheel cavities are not designed to withstand the same temperature levels as components directly exposed to the combustion product flow, the thermal valve 32 may be e.g. Preventively trigger to ensure that the components in the wheel cavities are not affected. In contrast, the thermal valve may be configured to responsively trigger in response to excessive temperatures at a pressure limit, such as temperatures that, when maintained, may affect turbine components.
    In addition, the thermal valve 32 may be configured to switch immediately or gradually into an open position during the activation or activation. For example, For example, the thermal valve 32 may be configured such that when the local temperature reaches the predetermined temperature threshold, the thermal valve 32 will only slightly open and gradually open to a fully open position as the local temperature continues to rise.
    The thermal valve 32, as described above, can be used at any pressure limit within a gas turbine. As another example, a thermal valve passage 30 may be located at the pressure boundary at a location B (FIG. 1) in which a thermal valve 32 could be mounted. As illustrated in FIG. 1, the location B is at a pressure boundary formed on the housing that separates the inner housing chamber 90 from the front portion of the front wheel space 28 that extends beyond the interconnect 92. Usually, compressor discharge air from the compressor section 10 seeps into the inner housing chamber 90. A thermal valve 32 installed along this pressure boundary may be configured such that when the temperature near the point B reaches or exceeds a predetermined temperature threshold, the thermo-valve 32 trips to open to allow cooling air out of the inner housing chamber 90 flow to the front wheel space 28 to cool the interconnect 92 and nearby areas.
    It should also be understood that the temperature activated valve 32 may be oriented in any manner or otherwise configured to allow high pressure cooling air to flow into a high temperature low pressure region rather than the exact configuration or orientation as they do in Figs. 2-6 are illustrated must have. For example, For example, the valve 32 may be oriented such that the temperature-activated elements are positioned on the side of the higher pressure, lower temperature pressure boundary. For example, For example, in the illustrated embodiment, the orientation of the valve could be reversed such that the temperature-activated elements are located on the side of the chamber 24 of the pressure boundary formed by the compressor exit housing 12. In such an embodiment, the temperature-activated elements of the valve 32 may be disposed in a valve housing (not shown) mounted on the compressor exhaust housing 12. The valve housing may be connected to the front wheel space via an opening (not shown) formed through the compressor exhaust housing 12 and allowing hot air from the front wheel space to enter the housing and activate the valve 32. Once the valve 32 is activated to open, cooling air may flow from the compressor 10 through a separate port or passage to the front wheel space 28 to reduce high temperatures.
    By now addressing an advantageous development of the present invention, the overheating of components within the turbine section 18 of a gas turbine is often caused by hot gas intake or suction. This is generally due to the fact that the hot combustion gases exiting the combustion section 10 and flowing through the turbine section 18 are at a higher pressure than the pressure in the inner turbine wheel cavities, such as the front wheel space 28. This pressure differential causes intrusion or sucking the hot gases into the turbine wheel cavities, often resulting in temperatures exceeding the allowable operating ranges for turbine components.
    Thus, Fig. 7 illustrates according to an advantageous embodiment of the present invention, an embodiment of a system for adjusting the amount of anti-intake air, which is supplied by a pressure limit in a gas turbine. The system includes a plurality of anti-suction valve passages 72, 74, 76 disposed at a pressure boundary in a gas turbine engine. As illustrated, the passages 72, 74, 76 are located at a location C (FIG. 1) at the pressure boundary defined by the compressor exit housing 12. It should be understood, however, that the passages 72, 74, 76 may be located anywhere along such pressure boundary or at any other pressure boundary within a gas turbine. In addition, it should be readily understood that a fewer or greater number of passes than illustrated in FIG. 7 could be used in the present system.
    The system further includes a plurality of temperature-activated anti-suction valves 78, 80, 82 mounted in the passages 72, 74, 76. The anti-wicking valves 78, 80, 82 may be mounted in the passages 72, 74, 76 by any method. For example, For example, the anti-wicking valve 78 may be press fit into the passageway 72, or both the anti-wicking valve 78 and the passageway 72 may be threaded to facilitate installation of the anti-wicking valve 78 in the passageway 72 to enable.
    As described below, the anti-wicking valves 78, 80, 82 may initially be in a closed position and configured to rise to predetermined temperature thresholds that are at the local temperature at the anti-siphoning valves 78 , 80, 82 are based on permanently switching to an open position. When open, the anti-wicking valves 78, 80, 82 provide a constant anti-suction airflow through the passages 72, 74, 76. Thus, in the illustrated embodiment, the anti-suction valves 78, 80, 82 may actuate to change to an open position when the temperature in the front wheel space 78 near the point C reaches or exceeds certain rising temperature thresholds. This would allow anti-intake air to flow continuously into the front wheel space 28. As a result, the pressure within the front wheel space 28 increases, thereby reducing the amount of hot gas intake into the wheel space. It should be understood, however, that the anti-intake air, other than being used to increase the pressure within the inner wheel cavity, may also be used as cooling air for turbine components.
    The temperature-activated anti-suction valves 78, 80, 82 may be configured to permanently change to the open state. In other words, in such an embodiment, when an anti-aspiration valve rises by triggering at a certain temperature threshold, it will remain in an open position to allow a constant flow of anti-aspirating air through the pressure boundary.
    Fig. 8 illustrates, as another embodiment of a temperature activatable valve, an anti-wicking valve 78. As illustrated, the anti-wicking valve 78 is a bimetal element valve as described in detail above. However, the anti-wicking valve 78 further includes a locking mechanism 84 which prevents the valve 78 from closing again at temperatures below its corresponding predetermined temperature threshold. The locking mechanism 84 may be e.g. a spring-loaded member which would allow an associated projection 86 attached to the valve stem 56 to pass through as the valve 78 transitions to the open position, which, however, would prevent the projection 86 from passing when the local temperatures at the valve 78 decrease. It should be understood, however, that the locking mechanism 78 may have any configuration that would prevent the anti-wicking valve 78 from reclosing when local temperatures cool down to the pressure limit below a particular predetermined temperature threshold. In addition, it should be understood that the anti-wicking valves 78, 80, 82 need not be bimetal element valves, but could be temperature activated valves of any type, including the fluid-filled bellows valves described above.
    Similarly, the anti-suction valves 78, 80, 82 need not have the orientation illustrated in Figs. 7 and 8, and may generally have any orientation that permits pressurized cooling air into which To flow in areas with low pressure and higher temperature. As described above with respect to the thermal valve 32, the anti-suction valves 78, 80, 82 may be e.g. be oriented so that the temperature-activated elements are on the high pressure low temperature side of a pressure limit.
    According to an advantageous development of the present invention, the anti-suction valves 78, 80, 82 are configured to permanently change to the open state with increasing predetermined temperatures. Of course, such rising temperature thresholds will vary depending on various factors, including, but not limited to, operating temperature and typical machine-to-machine variations. As an example, and referring to FIG. 7, the anti-wicking valve 78 may be configured to permanently change to an open state at a predetermined temperature threshold, based on assumed operating condition temperatures and assumed amounts of hot gas suction in the front wheel space 28. If temperatures in the wheelspace 28 reach or exceed such a temperature threshold, the anti-intake valve 78 would permanently trip to the open state by triggering, thereby allowing a constant flow of anti-intake air to enter the wheelspace 28. If local temperatures near the valves continue to increase, the anti-aspiration valve 80, which may be configured to actuate at a higher temperature threshold, would be activated to change to the open state to provide additional anti-aspiration air allow to flow into the wheel space 28. Similarly, the anti-wicking valve 82 may be configured to change to the open state by tripping at an even higher temperature threshold to allow the air gap 28 to flow in the event of further temperature increase of further anti-intake air. It should be readily understood that this scheme could be extended by incorporating additional anti-suction valves.
    In addition, the anti-suction valves 78, 80, 82 may have openings 42 of equal area or size to allow substantially identical amounts of the anti-intake air to pass through the passages 72, 74 when the valves are opened , 76 stream. Conversely, the anti-wicking valves 78, 80, 82 may have openings of different sizes to permit metered flow of the anti-suction air through the passages 72, 74, 76. For example, For example, the anti-suction valves 78, 80, 82 may each have an opening 42 of increasing size that corresponds to the increasing predetermined temperature thresholds of the anti-suction valves 78, 80, 82. Thus, referring to the above example, the anti-suction valve 78, which is configured to actuate at the lowest temperature threshold, may have the smallest opening size, while the anti-suction valve 80 may have a larger orifice size and the anti-suction valve. Valve 82 may have an even larger opening size. Similarly, the anti-suction valves 78, 80, 82 could each have an opening 42 of decreasing size that corresponds to the increasing predetermined temperature thresholds. In such an embodiment, the valve configured to actuate at the lowest temperature threshold would have the largest orifice size, while the subsequent higher temperature threshold valves would have smaller orifice sizes.
    Still further, the anti-suction valves 78, 80, 82 may be juxtaposed along a certain pressure limit, as generally illustrated in FIG. 7, or they may be spaced significantly apart from one another at a pressure limit. For example, For example, the anti-suction valve 78 may be located at a location A (FIG. 1) while the anti-suction valves 80 and 82 may be located at location C. In addition, it should be understood that the anti-wicking valves 78, 80, 82 may be configured similar to the thermal valve 32 discussed above to either preventively or reactively trigger depending on the particular function of each valve to switch to an open position.
    With the aid of the system according to the invention, both the amount of cooling air and the amount of anti-intake air supplied by a pressure limit in a gas turbine can be adjusted. According to an advantageous further development, the gas turbine contains at least one thermovalve passage 30 and at least one temperature-activated thermo valve 32, both of which can be configured, designed or otherwise configured in the manner illustrated and described above. The system also includes a plurality of anti-siphon valve passages 72, 74, 76 and a plurality of temperature-activated anti-siphoning valves 78, 80, 82, all of which may be configured, configured, or otherwise configured in the manner illustrated and described herein. As illustrated in FIG. 9, the system is installed at the pressure boundary defined by the compressor exhaust housing 12 to allow both cooling and anti-suction air to flow into the front wheel space 28. However, it should be appreciated that the system could be installed at any pressure limit within a gas turbine.
    It is a system for adjusting the amount of air delivered through a pressure boundary in a gas turbine disclosed having a passage 30 disposed at the pressure boundary. Also mounted in the passage 30 is a temperature-activatable valve 32 configured to actuate at a predetermined temperature threshold. In particular, the temperature-activatable valve 32 triggers to switch from a closed position to an open position when the local temperature at the temperature-activated valve 32 reaches or exceeds the predetermined temperature threshold to allow air to flow through the passage.
    LIST OF REFERENCE NUMBERS
    [0043]<Tb> 10 <September> compressor section<Tb> 12 <September> compressor outlet housing<Tb> 14 <September> combustor section<Tb> 16 <September> combustion chambers<Tb> 18 <September> turbine section<Tb> 20 <September> Wheels<Tb> 24 <September> Chamber<tb> 28 <SEP> front wheel space<Tb> 30 <September> Continuity<tb> 32 <SEP> temperature activated thermo valve<Tb> 34 <September> Housing<tb> 36 <SEP> lower chamber<tb> 38 <SEP> upper chamber<Tb> 40 <September> exhaust ports<Tb> 42 <September> opening<Tb> 44 <September> valve seat<tb> 46, 48 <SEP> opposite pairs of bimetallic elements<Tb> 50 <September> bimetal<Tb> 52 <September> valve opening<Tb> 54 <September> valve head<Tb> 56 <September> valve stem<Tb> 58 <September> attachment mechanism<tb> 60 <SEP> opposite insides<Tb> 62 <September> outsides<tb> 64 <SEP> fluid-filled bellows<tb> 66, 68 <SEP> opposite ends<Tb> 70 <September> sidewall<tb> 72, 74 76 <SEP> Passages<tb> 78, 80, 82 <SEP> temperature-activated anti-suction valves<Tb> 84 <September> locking mechanism<tb> 90 <SEP> inner housing chamber<Tb> 92 <September> Between junction
    权利要求:
    Claims (10)
    [1]
    A system for adjusting the amount of air delivered by a pressure limit in a gas turbine, the system comprising:a passage (30) disposed at the pressure boundary in the gas turbine;a temperature activatable valve (32) mounted in the passageway (30) and arranged to actuate at a predetermined temperature threshold; andwherein the temperature-activatable valve (32) triggers to change from a closed position to an open position when a local temperature at the temperature-activatable valve (32) reaches or exceeds the predetermined temperature threshold to allow air to flow through the passageway (30).
    [2]
    2. System according to claim 1, wherein the temperature-activatable valve (32) is a temperature-activated bimetallic valve or a temperature-activated liquid-filled bellows valve.
    [3]
    A system according to any one of the preceding claims, wherein the temperature-activated valve (32) is configured to be normally closed such that the temperature-activatable valve (32) is in a closed position when the local temperature at the temperature-activated valve (32) is below the predetermined temperature threshold.
    [4]
    A system according to any one of the preceding claims, further comprising a plurality of passages (72, 74, 76) and a plurality of temperature-activatable valves (78, 80, 82), wherein the plurality of temperature-activatable valves (78, 80, 82) in the plurality of passages ( 72, 74, 76) are mounted.
    [5]
    5. The system of claim 4, wherein the plurality of temperature-activatable valves (78, 80, 82) are configured to initiate at predetermined temperature thresholds that increase relative to each other.
    [6]
    6. The system of claim 5, wherein each of the plurality of temperature-activatable valves (78,80,82) is configured to initially be in a closed position and to trigger based on the local temperature at the respective one of the plurality of temperature-activated valves (78, 78). 80, 82) in an open position and can be locked in the open position.
    [7]
    The system of claim 5, wherein each of said plurality of temperature-activatable valves (78, 80, 82) has a different sized orifice (40), the size of said orifice (40) entering each of said plurality of temperature-activated valves (78, 80, 82). greater according to the increasing predetermined temperature thresholds.
    [8]
    8. The system of claim 5, wherein each of the plurality of temperature-activated valves (78, 80, 82) has a different size orifice (40), the size of the orifice (40) in each of the plurality of temperature-activated valves (78, 80, 82). smaller according to the rising temperature thresholds.
    [9]
    9. The system of claim 1, wherein the temperature-activatable valve (32) as a thermal valve (32) for adjusting the amount of cooling air, which is available through the pressure limit in the gas turbine, is formed, so that in the open position, air as the cooling air through the passage (30) flows; andthe anti-intake air adjustment system further comprises a plurality of anti-suction passages (72, 74, 76) located at the pressure limit and a plurality of temperature-activated anti-suction valves (78, 80, 82) incorporated in US Pat the anti-suction passages (72, 74, 76) are mounted and arranged to initiate at predetermined predetermined temperature thresholds relative to each other as compared to the anti-suction valves;wherein the plurality of anti-suction valves (78, 80, 82) are configured to initially be in a closed position and to be based on a local temperature at the respective one of the plurality of anti-suction valves (78, 80, 82). trigger to switch to an open position and be locked in the open position to allow air to flow as anti-intake air through the plurality of anti-wicking passages (72, 74, 76) so that the anti-siphoning passes through the plurality of anti-suction passages (72, 74, 76) Ansaugungs passages (72, 74, 76) flowing anti-suction air downstream of the pressure limit causes a pressure increase, whereby a suction or intake of hot gases is reduced downstream of the pressure limit.
    [10]
    10. A gas turbine with a system according to any one of claims 1 to 9, wherein the pressure limit in the gas turbine between a chamber (24) formed by a compressor outlet housing (12) and a front Radzwischenraum (28) or between an inner housing chamber (90) and the front wheel space (28) is located.
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    同族专利:
    公开号 | 公开日
    CH702540A2|2011-07-15|
    CN102121420A|2011-07-13|
    JP2011140941A|2011-07-21|
    CN102121420B|2015-01-28|
    DE102010061592A1|2011-07-14|
    US8549864B2|2013-10-08|
    US20110162384A1|2011-07-07|
    JP6035008B2|2016-11-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2787440A|1953-05-21|1957-04-02|Westinghouse Electric Corp|Turbine apparatus|
    US3575528A|1968-10-28|1971-04-20|Gen Motors Corp|Turbine rotor cooling|
    JPS5154833U|1975-09-03|1976-04-27|
    US4213738A|1978-02-21|1980-07-22|General Motors Corporation|Cooling air control valve|
    US4217755A|1978-12-04|1980-08-19|General Motors Corporation|Cooling air control valve|
    US4296599A|1979-03-30|1981-10-27|General Electric Company|Turbine cooling air modulation apparatus|
    US4427149A|1981-11-13|1984-01-24|Erwel Inc.|Bi-metallic steam trap|
    DE3207080C2|1982-02-26|1986-08-21|Mannesmann Rexroth GmbH, 8770 Lohr|Pilot operated pressure valve|
    US4807433A|1983-05-05|1989-02-28|General Electric Company|Turbine cooling air modulation|
    US4560105A|1984-01-11|1985-12-24|Spirax Sarco, Inc.|Bellows-actuated thermostatic steam traps|
    JPS61186879U|1985-05-14|1986-11-21|
    US4928240A|1988-02-24|1990-05-22|General Electric Company|Active clearance control|
    US5022817A|1989-09-12|1991-06-11|Allied-Signal Inc.|Thermostatic control of turbine cooling air|
    JPH048207U|1990-05-08|1992-01-24|
    US5263643A|1992-12-24|1993-11-23|Therm-O-Disc, Incorporated|Thermally responsive relief valve|
    JPH07167378A|1993-12-15|1995-07-04|Kubota Corp|Heat insulating container|
    JPH08296455A|1995-04-27|1996-11-12|Ishikawajima Harima Heavy Ind Co Ltd|Turbo-engine|
    US6070406A|1996-11-26|2000-06-06|Alliedsignal, Inc.|Combustor dilution bypass system|
    US5996331A|1997-09-15|1999-12-07|Alliedsignal Inc.|Passive turbine coolant regulator responsive to engine load|
    US6116852A|1997-12-11|2000-09-12|Pratt & Whitney Canada Corp.|Turbine passive thermal valve for improved tip clearance control|
    FR2884867B1|2005-04-21|2007-08-03|Snecma Moteurs Sa|DEVICE FOR REGULATING AIR FLOW CIRCULATING IN A ROTARY SHAFT OF A TURBOMACHINE|
    US7445424B1|2006-04-22|2008-11-04|Florida Turbine Technologies, Inc.|Passive thermostatic bypass flow control for a brush seal application|
    DE102006021327A1|2006-05-05|2007-11-08|Otto Egelhof Gmbh & Co. Kg|Control method for expansion valves in car air conditioning systems uses bellows filled with inert gas which pushes rods against spring attached to the valve stem so as to open valve when threshold pressure or temperature is exceeded|JP3117231B2|1991-03-11|2000-12-11|三井化学株式会社|Method for producing syndiotactic poly-α-olefin having a broad molecular weight distribution|
    EP0949273B1|1997-08-21|2003-04-02|Sumitomo Chemical Company, Limited|Modified particles, carrier prepared therefrom, olefin polymerization catalyst component prepared therefrom, olefin polymerization catalyst prepared therefrom, and process for preparing olefin polymer|
    US9025333B1|2011-05-10|2015-05-05|The United States Of America As Represented By The Secretary Of The Airforce|Tunable thermal switch|
    US8684660B2|2011-06-20|2014-04-01|General Electric Company|Pressure and temperature actuation system|
    US20130170966A1|2012-01-04|2013-07-04|General Electric Company|Turbine cooling system|
    US9228441B2|2012-05-22|2016-01-05|United Technologies Corporation|Passive thermostatic valve|
    US9028206B2|2012-06-12|2015-05-12|General Electric Company|Thermally actuated assembly for a gas turbine system and method of controlling a cooling airflow path|
    US9316152B2|2012-06-13|2016-04-19|General Electric Company|Active control of bucket cooling supply for turbine|
    US9297310B2|2012-10-18|2016-03-29|General Electric Company|Part load performance improvement using deformable bore plugs|
    US20140255145A1|2013-03-08|2014-09-11|General Electric Company|Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application|
    US8899190B2|2013-04-26|2014-12-02|GM Global Technology Operations LLC|Temperature dependent flow control for combustion engine piston squirters|
    US9617921B2|2013-07-31|2017-04-11|General Electric Company|Thermal actuator including fluid with high temperature stability|
    CN104696986A|2015-02-26|2015-06-10|北京华清燃气轮机与煤气化联合循环工程技术有限公司|Anti-tempering nozzle for combustion chamber of gas turbine|
    US20160298783A1|2015-04-09|2016-10-13|Hamilton Sundstrand Corporation|Thermally actuated flow control valve|
    US10337343B2|2015-08-13|2019-07-02|General Electric Company|Turbine component surface cooling system with passive flow modulation|
    US20170191373A1|2015-12-30|2017-07-06|General Electric Company|Passive flow modulation of cooling flow into a cavity|
    US10337411B2|2015-12-30|2019-07-02|General Electric Company|Auto thermal valvefor dual mode passive cooling flow modulation|
    CN105695440B|2016-01-14|2019-12-31|江苏大学|Streptococcus suis phage lyase with enhanced antibacterial activity and preparation method thereof|
    US10335900B2|2016-03-03|2019-07-02|General Electric Company|Protective shield for liquid guided laser cutting tools|
    PL232314B1|2016-05-06|2019-06-28|Gen Electric|Fluid-flow machine equipped with the clearance adjustment system|
    US10309246B2|2016-06-07|2019-06-04|General Electric Company|Passive clearance control system for gas turbomachine|
    US10605093B2|2016-07-12|2020-03-31|General Electric Company|Heat transfer device and related turbine airfoil|
    US10392944B2|2016-07-12|2019-08-27|General Electric Company|Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium|
    US10337739B2|2016-08-16|2019-07-02|General Electric Company|Combustion bypass passive valve system for a gas turbine|
    FR3061739B1|2017-01-06|2020-07-31|Safran Aircraft Engines|TURBOMACHINE SET|
    US10712007B2|2017-01-27|2020-07-14|General Electric Company|Pneumatically-actuated fuel nozzle air flow modulator|
    US10738712B2|2017-01-27|2020-08-11|General Electric Company|Pneumatically-actuated bypass valve|
    US10962128B2|2018-10-26|2021-03-30|Hamilton Sundstrand Corporation|Fire activated cooling fluid valve|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-08-31| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/683,787|US8549864B2|2010-01-07|2010-01-07|Temperature activated valves for gas turbines|
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