Pressurized damping fluid injection for damping turbine blade vibration

Abstract

The present invention is entitled "Pressurized Damping Fluid Injection for Damping Turbine Blade Vibrations". The invention provides a blade damping system (118) that, in opposition to the vibratory movement of a plurality of blades (114) of a turbine (108), impinges a pressurized damping fluid (176) onto the surface of at least one of the turbine blades to dampen vibrations of the blades (114) during operation of the turbine (108). The system includes a fluid injection nozzle (174) located in a stationary component adjacent to the plurality of blades (114). A valve (182) selectively allows pressurized damping fluid (176) from a pressurized damping fluid source (184) into the fluid injection nozzle (174), and a control system (190) controls the valve (182) to operate the fluid injection nozzle (174) in response to operating parameters exceeding a threshold during operation of the turbine (108). The invention also provides an associated turbine housing (126) and method.

Description

[0001] This invention was carried out under U.S. Department of Energy Contract No. DE-FE0031613, and the Government holds all rights to this invention. Background Technology

[0002] This disclosure relates in general to turbines, and more specifically, to damping the vibration of turbine blades using pressurized damping fluid injection.

[0003] One problem in turbine operation is the tendency of blades to experience vibrational stress during operation. In many facilities, turbines operate under conditions of frequent acceleration and deceleration. During turbine acceleration or deceleration, the blades are temporarily subjected to vibrational stress at at least some frequencies, and in many cases, to second or third frequencies. When blades are subjected to vibrational stress, the amplitude of the vibration can easily increase to a degree that alters the operation.

[0004] The turbine and compressor sections within an axial turbine typically include a rotor assembly comprising a rotating disk and multiple rotor blades arranged circumferentially around the disk. Each blade includes a root, an airfoil, and a platform positioned in the transition region between the root and the airfoil. The blade root is received in a recess of complementary shape within the disk. The blade platform extends laterally outward and together forms a working fluid flow path for fluid to flow through the rotor stage. The leading edge of each blade is generally referred to as the leading edge, and the trailing edge as the trailing edge. Forward is defined as the rearward upstream direction in the working fluid flow through the turbine.

[0005] During operation, blades can be excited into vibration by a number of different forces. For example, changes in the temperature, pressure, and / or density of the working fluid can excite vibrations throughout the rotor assembly, particularly within the blade surfaces and / or tips. Gas leaving the turbine and / or compressor sections upstream in a periodic or “pulsating” manner can also induce unwanted vibrations.

[0006] To test vibrations in blades, a current testing system uses a piezoelectrically actuated reciprocating valve to generate high-speed jets of air pulses to excite / vibrate the blades, thereby determining their resonant frequency. Another testing system for steam turbines (see U.S. Patent 4,776,216) provides a controlled fluid jet positioned around the blade row to excite rotating blades to determine their resonant frequency based on the amplitude of the vibration. This testing system is located upstream of the blade stage (see, for example...). Figure 2 Steam pulses are introduced (at the position of the nozzle 18 relative to the blade 22) and are used when the steam turbine is operating at a constant shaft rotation speed. However, during actual turbine operation, none of the aforementioned test systems can correct for vibrations.

[0007] One approach to addressing vibrations during turbine operation involves altering the physical structure of the blades to enhance their resistance to vibration. For example, a mid-span shroud connecting adjacent blades can be used. Modifying or adding to the structure presents additional challenges by altering the blade's aerodynamic properties and increasing its weight and / or length. Other approaches employ mechanisms that passively absorb the pressure that generates vibrations during operation. In one example, a cavity may be provided adjacent to the blade tip, or in another, a deflector may be provided to absorb pressure changes during operation. In another case, a high-pressure airflow may be directed from an upstream location to the leading edge of the blade stage. The effectiveness of the latter approach is limited because the airflow is directed only towards the leading edge of the blade. Summary of the Invention

[0008] One aspect of this disclosure provides a housing for a turbine, the housing comprising: a stationary member defining at least a portion of a working fluid path to guide working fluid through a blade stage including a plurality of blades operatively coupled to a rotor; and a fluid injection nozzle located in the stationary member, the fluid injection nozzle being configured to impinge pressurized damped fluid onto the surface of at least one of the plurality of blades of the blade stage in opposition to the vibratory movement of the plurality of blades of the blade stage, to induce damping of the vibration of at least one of the plurality of blades during turbine operation.

[0009] Another aspect of this disclosure provides a blade damping system for a turbine, the system comprising: a fluid injection nozzle located in a stationary component adjacent to a plurality of blades in the turbine, the fluid injection nozzle being configured to impinge pressurized damping fluid onto the surface of at least one of the blades in opposition to vibratory movement in the plurality of blades, to damping vibration of at least one of the blades during turbine operation; a valve for selectively allowing pressurized damping fluid from a pressurized damping fluid source into the fluid injection nozzle; and a control system for controlling the valve to operate the fluid injection nozzle in response to an operating parameter exceeding a threshold during turbine operation.

[0010] Another aspect of this disclosure provides a method comprising: operating a turbine by transmitting working fluid through a working fluid path defined between a stationary component of a housing and a rotor and through a plurality of blades operatively coupled to the rotor; and damping the vibration of at least one of the plurality of blades by impinging pressurized damping fluid onto the surface of at least one of the blades in opposition to the vibratory movement of the plurality of blades during operation of the turbine.

[0011] Exemplary aspects of this disclosure are designed to address the problems described herein and / or other problems not discussed herein. Attached Figure Description

[0012] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the present disclosure in conjunction with the accompanying drawings depicting various embodiments thereof, wherein:

[0013] Figure 1 A schematic diagram of an exemplary turbine in the form of a gas turbine system is shown;

[0014] Figure 2 A partial schematic cross-sectional view of an exemplary turbine including a blade damping system according to an embodiment of the present disclosure is shown;

[0015] Figure 3 A perspective view of a turbine rotor blade of a type that may employ embodiments of this disclosure is shown;

[0016] Figure 4 A blade vibration damping system in a housing according to an embodiment of the present disclosure is shown along... Figure 2 A partial schematic cross-sectional view taken from line 4-4 in the diagram;

[0017] Figure 5 A perspective view of a blade damping system in a housing according to other embodiments of this disclosure is shown; and

[0018] Figure 6 A cross-sectional view of a fluid injection nozzle according to an alternative embodiment of the present disclosure is shown.

[0019] It should be noted that the accompanying drawings of this disclosure are not necessarily drawn to scale. The drawings are intended to depict only typical aspects of this disclosure and should therefore not be considered as limiting the scope of this disclosure. In the drawings, similar numbers denote similar elements between figures. Detailed Implementation

[0020] As an initial consideration, in order to clearly describe this technology, it will be necessary to select certain terms when referring to and describing related machine components within a turbine. To the extent possible, common industry terms will be used and adopted in a manner consistent with their accepted meaning. Unless otherwise stated, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will understand that several different or overlapping terms may generally be used to refer to a particular component. An object that can be described herein as a single part may include multiple components and is referred to in another context as being composed of multiple components. Alternatively, an object that can be described herein as comprising multiple components may elsewhere be referred to as a single part.

[0021] In addition, several descriptive terms may be used periodically throughout this document, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise stated, these terms and their definitions are as follows. As used herein, “downstream” and “upstream” are terms indicating the direction of fluid flow, such as through the working fluid of a turbine engine, or, for example, through the airflow of a combustor or through the coolant of one of the turbine's component systems. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” refers to the direction opposite to the flow. Without any other particularity, the terms “front” and “rear” refer to directions, where “front” refers to the front end of the engine or the compressor end, and “rear” refers to the rear end of the engine or the turbine end.

[0022] It is often necessary to describe parts positioned at different radial locations relative to the central axis. The term "radial" refers to movement or position perpendicular to the axis. For example, if a first part is closer to the axis than a second part, this document will describe the first part as "radially inward" or "inner" of the second part. On the other hand, if the first part resides further away from the axis than the second part, this document may describe the first part as "radially outward" or "outer" of the second part. The term "axial" refers to movement or position parallel to the axis. Finally, the term "circumferential" refers to movement or position about the axis. It should be understood that such terms can be applied relative to the central axis of the turbine.

[0023] In addition, several descriptive terms may be used regularly in this document, as described below. The terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of a single component.

[0024] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that, when used in the specification, the terms “comprising” and / or “including” specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. “Optional” or “optionally” means that an event or condition subsequently described may or may not occur, and the description includes instances where the event occurs and instances where the event does not occur.

[0025] When an element or layer is referred to as “on,” “joined to,” “connected to,” or “linked to” another element or layer, it may be directly on, joined to, connected to, or linked to another element or layer, or an intermediary element or layer may be present. In contrast, when an element is referred to as “directly on another element or layer,” “directly joined to another element or layer,” “directly connected to another element or layer,” or “directly linked to another element or layer,” an intermediary element or layer may not be present. Other terms used to describe relationships between elements should be interpreted in a similar manner (e.g., “between” vs. “directly between,” “adjacent” vs. “directly adjacent,” etc.). As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items.

[0026] Among other things, embodiments of this disclosure include a blade damping system, a housing for a turbine including the damping system, and related methods. The blade damping system impinges pressurized damping fluid onto the surface of at least one of the turbine's blades in opposition to the vibrating movement of a plurality of turbine blades, to dampen vibrations of the blades during turbine operation. The system includes a fluid injection nozzle located in a stationary section adjacent to the plurality of blades. A valve selectively allows pressurized damping fluid from a pressurized damping fluid source into the fluid injection nozzle, and a control system controls the valve to operate the fluid injection nozzle in response to operating parameters exceeding a threshold during turbine operation. Operating parameters may include, for example, amplitude and phase of vibration. The pressurized damping fluid may be injected in a pulsed flow, for example, pulsed at 180° out of phase with the blade vibration, to counteract and dampen the vibration. The fluid injection nozzle may be positioned in a stationary section defining at least a portion of a working fluid path to guide the working fluid through a blade stage including a plurality of blades operatively coupled to a rotor. The teachings of this disclosure contrast with current testing systems that use fluid injection to determine resonant frequency vibrations but are not used to dampen vibrations during actual turbine operation.

[0027] Refer to the attached diagram. Figure 1 This is a schematic diagram of an exemplary machine that includes a turbine to which the teachings of this disclosure can be applied. Figure 1 The image shows a turbine 90 in the form of a combustion turbine or gas turbine (GT) system 100 (hereinafter referred to as "GT system 100"). GT system 100 includes a compressor 102 and a combustor 104. Combustor 104 includes a combustion zone 105 and a fuel nozzle portion 106. GT system 100 also includes a turbine 108 and a conventional compressor / turbine shaft 110 (hereinafter referred to as "rotor 110").

[0028] In one embodiment, the GT system 100 is a 7HA.03 engine, commercially available from General Electric Company (Greenville, SC). This disclosure is not limited to any particular GT system and can be implemented with other engines, including, for example, General Electric Company's HA, F, B, LM, GT, TM, and E-class engine models, as well as engine models from other companies. More importantly, the teachings of this disclosure are not necessarily limited to turbines in GT systems and can be applied to virtually any type of turbine, such as steam turbines, jet engines, compressors (e.g.,...). Figure 1 (as shown), turbofan, turbocharger, etc. Therefore, reference to the turbocharger 108 of the GT system 100 is for descriptive purposes only and not for limitation.

[0029] Figure 2 A partial cross-sectional schematic diagram of an exemplary portion of a turbine 108 according to an embodiment of the present disclosure is shown. The turbine includes a blade damping system 118 and a housing 126 that includes a portion of the system. In the example shown, the turbine 108 includes components compatible with… Figure 1 The GT system 100 uses four stages L0-L3. These four stages are referred to as L0, L1, L2, and L3. Stage L0 is the first stage and the smallest of the four stages (in the radial direction). Stage L1 is the second stage and the next stage in the axial direction. Stage L2 is the third stage and the next stage in the axial direction. Stage L3 is the fourth (last) stage and the largest (in the radial direction). It should be understood that the four stages are shown only as an example, and each turbine may have more or fewer than four stages.

[0030] Multiple stationary blades or nozzles 112 may mate with multiple turbine blades 114 (hereinafter referred to as "blades 114") to form each stage L0-L3 of turbine 108 and define a portion of the working fluid path (WFP) through turbine 108. The blades 114 in each stage are coupled to rotor 110, for example, by corresponding rotor wheels 116 that circumferentially connect them to rotor 110. That is, the blades 114 are mechanically coupled to rotor 110, for example, by rotor wheels 116 in a circumferentially spaced manner. Where provided, the stationary nozzle portion 115 includes a plurality of stationary nozzles 112 circumferentially spaced around rotor 110. Each nozzle 112 may include at least one endwall (or platform) 120, 122 connected to airfoil 124. In the example shown, nozzle 112 includes a radially outer endwall 120 and a radially inner endwall 122. The radially outer endwall 120 connects nozzle 112 to housing 126 of turbine 108. In some forms of turbines, nozzle 112 may be omitted.

[0031] Figure 3A perspective view of a blade 114 of a type that may employ embodiments of the present disclosure is shown. Each of the plurality of blades 114 includes a root 130 through which the blade 114 is attached to the rotor 110. Figure 1 The root 130 may include a dovetail tenon 132, which is configured to be mounted on the rotor 110. Figure 1 ) rotor wheel 116 ( Figure 2 The root 130 may also include a shank 134 extending between the dovetail tenon 132 and the platform 136, the platform being positioned at the junction of the airfoil 138 and the root 130, and defining the working fluid path (WFP) through the turbine 108. Figure 2 Part of the inner boundary of the rotor 110. It should be understood that the airfoil 138 is the moving part of the blade 114, which intercepts the flow of the working fluid and causes the rotor 110 to rotate. As can be seen, the airfoil 138 of the blade 114 includes a concave pressure side (PS) outer wall 140 and circumferentially or laterally opposed convex suction side (SS) outer walls 142, which extend axially between opposing leading edges 144 and trailing edges 146, respectively. The side walls 140 and 142 also extend radially from the platform 136 to the outer tip 148. Although an exemplary blade 114 has been described, it should be understood that the blade can vary structurally across different types of turbines.

[0032] return Figure 2 The housing 126 may include a stationary member 160 that defines at least a portion of a working fluid path (WFP) to guide working fluid (WF) through a blade stage (e.g., L0-L3) comprising a plurality of blades 114 operatively coupled to the rotor 110. As noted, for the GT system 100 ( Figure 1 The working fluid WF is the fuel to be burned. Other turbines may use other working fluids, such as, but not limited to, steam, water, air, fuel, or a fuel / air mixture. The stationary component 160 may include any portion of the turbine housing that forms the working fluid path (WFP). In a non-limiting example, the stationary component 160 may include the outer tip 148 surrounding the blade 114. Figure 3 The tip guard of the blades 114. In other embodiments, the stationary component 160 may include a portion of a nozzle portion 115 extending circumferentially around the plurality of blades 114, such as the outer end wall 120 of the upstream or downstream nozzle portion 115.

[0033] refer to Figure 1 and Figure 2During operation, air flows through compressor 102, and pressurized air is supplied to burner 104. Specifically, pressurized air is supplied to fuel nozzle portion 106, which is integral with burner 104. Fuel nozzle portion 106 is in fluid communication with combustion zone 105. Fuel nozzle portion 106 is also in communication with fuel source ( Figure 1 A combustor 104 (not shown) is in fluid communication with a turbine 108, within which fuel and air are directed to a combustion zone 105. The combustor 104 is ignited and the fuel is burned. The combustor 104 is in fluid communication with a turbine 108, within which the thermal energy of the gas flow is converted into mechanical rotational energy by directing the burned fuel (e.g., working fluid) into a working fluid path (WFP) to rotate the blades 114. The turbine 108 is rotatably coupled to and drives a rotor 110. A compressor 102 is rotatably coupled to the rotor 110. At least one end of the rotor 110 may extend axially away from the turbine 108 and may be attached to a load or machinery (not shown), such as, but not limited to, a generator, a load compressor, and / or another turbine.

[0034] As noted, during turbine operation, blades 114 can be excited into vibration by a number of different force applications. For example, changes in the temperature, pressure, and / or density of the working fluid can excite vibrations throughout the rotor assembly, particularly within the blade surfaces and / or tips. Gas exiting the turbine and / or compressor section upstream in a periodic or “pulsating” manner can also excite undesired vibrations. Other common causes of turbine blade vibration include, but are not limited to, excitation from upstream nozzles, low circumferential flow distortion per revolution from the combustor canister, structural excitation from the generator, and turbine blade flutter.

[0035] Figure 2 and Figure 4 A blade damping system 118 (hereinafter referred to as "System 118") for a turbine 108 is shown according to an embodiment of the present disclosure. Figure 4 A partial schematic cross-sectional view of the system 118 and housing 126 of the turbine 108 is shown (along... Figure 2(Line 4-4 is cut off). System 118 may also optionally include a sensor system 170 operatively associated with a plurality of blades 114 in turbine 108. Sensor system 170 may be configured, for example, to determine the amplitude and phase of vibration, or another operating parameter of at least one of the plurality of blades 114. Sensor system 170 may include one or more sensors 172, which are coupled to stationary housing 126 at any location adjacent to the outer tip 148 of blade 114 for accurate vibration measurement. Any number of circumferentially spaced sensors 172 may be used. Connections from sensor 172 to control system 190 described elsewhere herein are well known and are not shown. Sensor 172 may be any of a variety of suitable sensors, such as electromagnetic probes.

[0036] System 118 may also include a fluid injection nozzle 174 located in a stationary component 160 adjacent to the plurality of blades 114. The fluid injection nozzle 174 is configured to impinge pressurized damping fluid 176 onto the surface 178 of at least one of the blades in opposition to the vibratory movement of the plurality of blades 114, to damping the vibration of at least one of the blades 114 during turbine operation. As used herein, “damping” refers to the reduction of the amplitude of an oscillation or vibration (e.g., the resonant frequency of a blade) by dissipating energy from an object such as a blade.

[0037] In many, but perhaps not all, cases, the optimal positioning of the fluid injection nozzle 174 for damping vibrations ensures that the pressurized damping fluid 176 is injected in a direction perpendicular to the surface 178. For this purpose, the fluid injection nozzle 174 can be angled within the stationary component 160 in any manner to ensure that the pressurized damping fluid 176 impacts the desired surface at the desired angle of the associated blade 114. Figure 4 In one example shown, the fluid injection nozzle 174 may be angled α relative to the radial axis R to guide pressurized damping fluid 176 perpendicular to the surface 178 of the blade 114. Here, the fluid injection nozzle 174 is in or parallel to the radial plane 192, i.e., the page plane perpendicular to the axis of the rotor 110. Figure 1 ).

[0038] exist Figure 5 In another example shown in the perspective view, the fluid injection nozzle 174 is at an angle α relative to the radial axis R and relative to the radial plane 192 (i.e., the plane perpendicular to the axis of the rotor 110). Figure 1 An angle β is formed to guide the pressurized damping fluid 176 on the surface 178 perpendicular to the blade 114.

[0039] In one example, the fluid injection nozzle 174 is aligned with the surface 178 of the outer tip 148 of at least one of the plurality of blades 114. In this configuration, a pressurized damping fluid 176 may also be used to at least partially reduce over-tip leakage of the working fluid. In another example, the surface 178 of the blade 114 may be the surface of its airfoil 138, i.e., the surface away from the outer tip 148. However, the surface 178 may be any surface of the blade 114, such as… Figure 2 As shown, the outer wall 140 on the pressure side or the outer wall 142 on the suction side of the wing surface 138.

[0040] exist Figure 4 In the example shown, blade 114 rotates clockwise. In this case, pressurized damping fluid 176 is directed onto the suction-side outer wall 142 of airfoil 138, opposite to the rotation. However, it should be emphasized that pressurized damping fluid 176 can be directed in any direction, including the direction of rotation, and impinge on any blade surface to dampen vibrations. Pressurized damping fluid 176 may include, for example, pressurized air, water, steam, or combinations thereof. Although the impact angle has been described herein as vertical, other impact angles may also be used.

[0041] The fluid injection nozzle 174 can have any size commensurate with the size of the turbine 108 and the desired damping effect. For example... Figure 4 and Figure 5 As shown, the fluid injection nozzle 176 may include, for example, a nozzle insert 186 (fixed) in an opening 188 in a stationary member 160. Alternatively, as Figure 6 As shown in the enlarged partial cross-sectional view, the fluid injection nozzle 174 can be integrally formed in the stationary component 160, for example, by casting, additive manufacturing, or machining therein. In any case, the nozzle 174 can be configured to provide any shape and / or form to the pressurized damped fluid 176 as it exits the stationary component 160. Furthermore, the system 118 can be implemented on a new turbine 108, and advantageously, can be retrofitted to an older turbine 108, for example, by drilling an opening 188 in its stationary component 160 and using a nozzle insert 186.

[0042] Fluid injection nozzle 174 and sensor 172 (if provided) are available in radial plane 192 ( Figure 4 and Figure 6 ) Central axis aligned (see Figure 2 Levels L0, L2, and L3 in the middle), or they can be axially offset (see Figure 2 (Level L1 in the middle).

[0043] System 118 may also include valve 182 for selectively allowing pressurized damping fluid 176 to enter fluid injection nozzle 174 from pressurized damping fluid source 184 (hereinafter referred to as "source 184"). Source 184 may be any supply device now known or later developed suitable for pressurized damping fluid 176. In a non-limiting example, source 184 may be at least one of: a pressurized storage tank (e.g., water or air), compressor 102 ( Figure 1 The device includes an exhaust system (air), a cooling fluid supply system 185 (e.g., air) leading to the nozzle section 115 upstream of the relevant blade stage, a heat recovery steam generator (HRSG) for steam, etc. Valve 182 can be any suitable valve for the pressurized damping fluid 176 used, such as an electronically controlled ball valve for air.

[0044] System 118 may also include a control system 190 for controlling valve 182 to operate fluid injection nozzle 174 in response to operating parameters of turbine 108 exceeding a threshold during turbine 108 operation. Operating parameters may be parameters now known or developed later that indicate the need to address blade vibration. In a non-limiting example, with sensor system 170 provided, the operating parameters may be the amplitude and phase of the vibration of at least one of the plurality of blades 114, as measured by sensor 172. Here, control system 190 may operate valve 182 in response to at least one of the amplitude and phase of the vibration of at least one of the plurality of blades exceeding a threshold during turbine operation. Specifically, the phase of the vibration may be used to cause valve 182 to open precisely and at the right time to provide counterflow to dampen the vibration, for example, by pulses 180° out of phase with the blade vibration to counteract and dampen the vibration. In other non-limiting examples, the operating parameters can be any other parameters measured in turbine 108, such as, but not limited to: working fluid temperature, pressure, and / or density; and / or determining, in a pulsating manner, the upstream of gas exiting the turbine 108 section and / or the compressor 102 section. The operating parameters can also be a combination of measurable parameters, such as working fluid temperature and density exceeding corresponding thresholds, working fluid pressure, and the amplitude of one or more blades 114 as measured by sensor system 170.

[0045] In one embodiment, the fluid injection nozzle 174 may be configured to continuously impinge pressurized damping fluid 176 onto the surface 178 of the blade 114 of the blade stage to alter the flow field (e.g., volume, velocity, direction, etc.) around the blade stage, thereby reducing the total dynamic excitation of the blade 114 during operation of the turbine 108. In this case, valve 182 would be in a continuously open position. However, in other embodiments, the control system 190 may operate valve 182 to provide pressurized damping fluid 176 in any desired selective manner. For example, in one embodiment, pressurized damping fluid 176 may be injected at a substantially constant flow rate, e.g., with some short closing periods, such as during turbine 108 startup. A constant flow rate means that it is constant compared to a conventional test system that pulsates the flow to produce the desired vibrations for testing and design purposes. In other embodiments, pressurized damping fluid 176 may be injected intermittently or in a pulsed manner to counteract the phase of the vibrational movement of at least one of the plurality of blades of the blade stage. For example, it may be pulsed 180° out of phase with the blade vibration. The duration of any type of flow may also be controlled. Control system 190 can be any digital controller now known or developed later, and can be a standalone controller or integrated into a larger control system, such as for turbine 108 or turbine 90. Figure 1 Overall control.

[0046] like Figure 4 As shown, embodiments of this disclosure may optionally include a plurality of fluid injection nozzles 174 circumferentially spaced in the stationary component 160. In this case, each fluid injection nozzle 174 may include a corresponding valve 182 for selectively allowing pressurized damping fluid 176 to enter the nozzle from the pressurized damping fluid source 184 under the control of the control system 190. However, it is possible that one valve 182 may control the flow to more than one nozzle 174. In any case, the control system 190 opens at least one valve 182 to operate at least one corresponding fluid injection nozzle 174 in response to an operating parameter (e.g., the amplitude of at least one of the plurality of blades) exceeding a threshold as described herein during turbine operation. Any number of fluid injection nozzles 174 may be employed as part of system 118.

[0047] like Figure 2 As shown, rotor 110 may include multiple blade stages L0-L3. Although each blade stage is shown as including system 118, this arrangement may not always be necessary. For example, only selected blade stages may include system 118. In one example, as... Figure 4 and Figure 5 As shown, blade 114 is adjacent to the housing end wall 196 of housing 126, and therefore can be part of the last (maximum) stage of blade stages L0-L3.

[0048] Embodiments of this disclosure may also include a housing 126 for the turbine 108, the housing including a fluid injection nozzle 174 in its stationary portion 160. Furthermore, the housing 126 may include a valve 182 (coupled to or externally thereto) for selectively allowing pressurized damping fluid 176 from a pressurized damping fluid source 184 into the fluid injection nozzle 174. The housing 126 may also include a control system 190 (coupled to or externally thereto) that opens the valve 182 to operate the fluid injection nozzle 174 in response to turbine operating parameters exceeding thresholds as described herein.

[0049] In operation, the method according to embodiments of this disclosure includes operating turbine 108. Compared to a test system, embodiments of this disclosure are applied to turbine 108 during actual active operation, during which turbine 108 generates its design output (e.g., rotational power, compressed air, compressed air / fuel mixture, etc.). Turbine 108 can operate at any load and / or speed, where blade vibration may be a problem. Turbine 108 can be operated by transferring working fluid through a working fluid path (WFP) defined between the stationary component 160 of housing 126 and rotor 110. Figure 2 And it is operated through a plurality of blades 114 operatively coupled to rotor 110. As described herein, the method also includes damping the vibration of at least one blade of blade 114 during operation of turbine 108 by impinging pressurized damping fluid 176 onto the surface 178 of at least one blade of blade 114 in opposition to the vibratory movement of the blades. As described herein, this damping may include selectively operating valve 182 during operation of turbine 108, the valve being configured to selectively allow pressurized damping fluid 176 from source 184 into fluid injection nozzle 174, the fluid injection nozzle being configured to impinge pressurized damping fluid 176 onto the surface 178 of at least one blade of blade 114. During operation of turbine 108, any number of blades 114 can simultaneously dampen their vibration by impinging pressurized damping fluid 176 onto the surface 178 of each of the plurality of blades.

[0050] The embodiments of this disclosure provide systems and methods for selectively damping vibrations in one or more turbine blades during turbine operation. These teachings are applicable to any type of turbine in a variety of applications: jet engines, steam or gas turbines, compressors, turbochargers, etc. Damping turbine stages and / or blades in this manner helps extend blade life, allows for the use of larger blades, generates more power, and improves efficiency. Furthermore, damping turbine stages and / or blades can allow the elimination of tip span and mid-span shrouds originally used to reduce vibration. The embodiments of this disclosure also do not add any mass to the blades, unlike other blade dampers that add fixed loads to the blades and have durability problems due to exposure to high temperatures, centrifugal loads, and blade vibrations.

[0051] As used throughout the specification and claims, approximate language can be used to modify any quantitative expression that allows for variation without causing a change in its underlying function. Therefore, values ​​modified by one or more terms (such as “about,” “approximately,” and “substantially”) are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value. Range limitations may be combined and / or interchanged herein and throughout the specification and claims. Unless otherwise specified by context or language, these ranges are identified and include all subranges contained therein. The term “about” applied to a specific value within a range applies to both terminating values ​​and may indicate + / - 10% of said value unless otherwise dependent on the precision of the instrument used to measure the value.

[0052] All means or steps plus functional elements in the following claims are intended to include any structure, material, action, and equivalent for performing a function in conjunction with other claimed elements of a particular claim. This disclosure has been described for purposes of illustration and description, but it is not intended to be exhaustive or to limit the disclosure to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of this disclosure. Embodiments have been selected and described to best explain the principles and practical application of this disclosure and to enable others skilled in the art to understand various embodiments of this disclosure with various modifications suitable for the intended particular use.

Claims

1. A housing (126) for a turbine (108), comprising: A stationary component (160) defines at least a portion of the working fluid path to guide the working fluid through a blade (114) stage, the blade stage including a plurality of blades (114) operatively coupled to a rotor (110). A fluid injection nozzle (174) located in the stationary component (160) is configured to impinge pressurized damping fluid (176) onto the surface (178) of at least one of the plurality of blades (114) in the blade (114) stage in opposition to the vibratory movement of the blades (114) of the blade (114) stage, so as to cause damping of the vibration of at least one of the plurality of blades (114) during operation of the turbine (108); Valve (182), the valve being used to selectively allow the pressurized damping fluid (176) to enter the fluid injection nozzle (174) from the pressurized damping fluid source (184); and A control system (190) is used to control the valve (182). The control system (190) opens the valve (182) to operate the fluid injection nozzle (174) in response to the operating parameters of the turbine (108). The fluid injection nozzle (174) comprises a plurality of circumferentially spaced fluid injection nozzles (174) in the stationary component (160), each fluid injection nozzle (174) comprising a corresponding valve (182) for selectively allowing the pressurized damping fluid (176) from the pressurized damping fluid source (184) into the fluid injection nozzle (174) under the control of the control system (190), and the housing further comprises: A sensor system (170), operatively associated with the plurality of blades (114), is used to determine the amplitude of at least one of the plurality of blades (114), and The control system (190) opens at least one valve (182) to operate at least one corresponding fluid injection nozzle (174) in response to the amplitude of at least one of the plurality of blades (114) exceeding a threshold during operation of the turbine (108). The surface (178) of at least one of the plurality of blades (114) is the surface of its airfoil (124, 138), and the fluid injection nozzle (174) is positioned to inject the pressurized damping fluid (176) in a direction perpendicular to the surface (178).

2. The housing (126) according to claim 1, wherein the pressurized damping fluid (176) is injected at a substantially constant flow rate.

3. The housing (126) according to claim 1, wherein the stationary component (160) includes a tip guard extending circumferentially around the plurality of blades (114).

4. The housing (126) according to claim 1, wherein the stationary component (160) includes a portion of a nozzle (174) portion extending circumferentially around the plurality of blades (114).

5. The housing (126) according to claim 1, wherein the pressurized damping fluid (176) comprises at least one of pressurized air, water, steam, or a combination thereof.

6. The housing (126) according to claim 1, wherein the rotor (110) comprises a plurality of blade (114) stages, and wherein at least one of the plurality of blades (114) is part of the final stage of the plurality of blades (114) stages.

7. The housing (126) according to claim 1, wherein the fluid injection nozzle (174) includes a nozzle (174) insert in an opening (188) in the stationary member (160).

8. The housing (126) according to claim 1, wherein the fluid injection nozzle (174) is integrally formed in the stationary part (160).

9. The housing (126) according to claim 1, wherein the pressurized damping fluid (176) originates from at least one of the following: a cooling fluid supply device (185) leading to a nozzle (174) portion upstream of the blade (114) stage, and a compressor (102) discharge device.

10. A blade (114) vibration damping system (118) for a turbine (108), the system (118) comprising: A fluid injection nozzle (174) located in a stationary component (160) adjacent to a plurality of blades (114) in the turbine (108) is configured to impinge pressurized damping fluid (176) onto the surface (178) of at least one of the blades in the plurality of blades (114) in the opposite direction to the vibratory movement of the plurality of blades (114) to damping the vibration of at least one of the blades (114) during operation of the turbine (108); Valve (182), the valve being used to selectively allow the pressurized damping fluid (176) to enter the fluid injection nozzle (174) from the pressurized damping fluid source (184). and A control system (190) is configured to control the valve (182) to operate the fluid injection nozzle (174) in response to an operating parameter exceeding a threshold during operation of the turbine (108). The fluid injection nozzle (174) comprises a plurality of circumferentially spaced fluid injection nozzles (174) in the stationary component (160), each fluid injection nozzle (174) comprising a corresponding valve (182) for selectively allowing the pressurized damping fluid (176) from the pressurized damping fluid source (184) into the fluid injection nozzle (174) under the control of the control system (190), and the system (118) further comprises: A sensor system (170), operatively associated with the plurality of blades (114), is used to determine the amplitude of at least one of the plurality of blades (114), and The control system (190) opens at least one valve (182) to operate at least one corresponding fluid injection nozzle (174) in response to the amplitude of at least one of the plurality of blades (114) exceeding a threshold during operation of the turbine (108). The surface (178) of at least one of the plurality of blades (114) is the surface of its airfoil (124, 138), and the fluid injection nozzle (174) is positioned to inject the pressurized damping fluid (176) in a direction perpendicular to the surface (178).

11. The system (118) of claim 10, wherein the pressurized damping fluid (176) is injected at a substantially constant flow rate.

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