EP2435665B1 - Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine - Google Patents
Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine Download PDFInfo
- Publication number
- EP2435665B1 EP2435665B1 EP10730046A EP10730046A EP2435665B1 EP 2435665 B1 EP2435665 B1 EP 2435665B1 EP 10730046 A EP10730046 A EP 10730046A EP 10730046 A EP10730046 A EP 10730046A EP 2435665 B1 EP2435665 B1 EP 2435665B1
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- European Patent Office
- Prior art keywords
- rotor
- control system
- adjusting
- turbomachine
- clearance
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
Definitions
- the invention relates to a gap control system for adjusting a nip between a rotor blades comprising a rotor blades of a turbomachine, in particular a gas turbine, and a surrounding this at least partially surrounding, at least two segments comprising sheath.
- the invention further relates to a turbomachine, in particular a gas turbine, the type specified in the preamble of claim 11 and a method for adjusting a running gap between a rotor blades comprehensive rotor of a turbomachine, in particular a gas turbine, and at least partially surrounding this, at least two segments comprising sheath ,
- the efficiency of a turbomachine depends essentially on the size of the radial running gap between a rotor and static components of the turbomachine.
- the position of the surge limit-that is to say the limit up to which stable operation of the turbomachine is possible- is also determined essentially by the size of the running gap.
- the realization of the smallest possible, over the operating life of the turbomachine constant radial clearance gaps is therefore a primary design goal. This is even more important the smaller the dimensions of the rotor blades of the rotor. This is the case, for example, in the rear stages of a high-pressure compressor or a turbomachine designed as a high-pressure turbine.
- Fig. 1 a schematic line diagram of a time and load-dependent gap change between a rotor disk and a surrounding this surrounding a turbomachine, such as it typically occurs during the operation of a high pressure compressor, known from the prior art turbomachine for an engine of the 30 klb thrust class.
- the solid line ⁇ 1 describes a radius of the rotor disk and the solid line ⁇ 2 describes a radius of the casing, whereas the dashed line ⁇ 3 describes the radius of the casing required for setting a running gap L with an optimum size ⁇ r opt .
- the optimum size ⁇ r opt of the nip L should be able to be adjusted by means of a gap control system of the turbomachine.
- the sheath with its lower mass compared to the rotor, generally reacts thermally much faster (range B 3 ).
- thermally active gap control systems in which the running gap is optimized by targeted cooling or heating of the relevant components.
- Examples include the gap control system of the CFM56 engine family, in which the rotor temperature is controlled, or from the US 4,329,114 known Gap control system, by means of which the housing temperature of the turbomachine is regulated. Since these gap control systems only act by influencing the component temperatures, they react relatively slowly and can therefore only significantly improve the stationary clearance gaps. On rapid changes of the nip - as described above in transient operating conditions arise - on an offset between a rotational axis of the rotor and a central axis of the sheath and on eccentricities, such as occur in Manöverlasten, these gap control systems can not or only very limited react.
- the sheathing of the rotor should be able to adapt as well as possible to its diameter and relative position at all times.
- the sheath is often segmented.
- the GB 2108591 A shows, for example, a gap control system for such a segmented jacket of a turbomachine. Each three segments are coupled together by a lever mechanism. These coupled segments are adjusted uniformly, each with an actuator in response to measurement signals of multiple sensor devices.
- the running gap in each of these coupled segment groups can hereby be set over the circumferential extent of the segment group to a middle running gap. With diameter changes of the rotor and the jacket, the gap control system thus provides comparatively good results compared to thermally active gap control systems.
- each segment for adjusting the running gap by a gap control system is movable.
- the segments are moved between wedge-shaped guide elements, wherein a disc spring stack, the segments with respect to the axis of rotation of the rotor radially outward and the gap control system can move the segments radially towards the rotor.
- a high number of actuators and sensor devices are required, whereby the gap maintenance system is not only expensive and difficult, but also has a relatively high failure probability.
- the US 5,104,287 describes a gap control system for a segmented jacket of a rotor blades comprising rotor of a turbomachine.
- Each segment of the casing can be moved radially with respect to the axis of rotation of the rotor by means of two associated adjusting devices of the gap holding system comprising threaded spindles.
- the adjusting devices designed as adjusting gears are coupled in pairs with a control element designed as a ring and arranged concentrically around the rotor.
- the adjustment of the running gap is made by turning the ring, the rotational movement of which is converted by the adjusting devices into a uniform radial movement of the segments away from the rotor.
- Wavy flat springs are arranged between the segments and a support housing of the casing, which press the segments radially inwards, ie in the direction of the rotor.
- a disadvantage is the fact that the segments of the shell can only be moved radially together, so that only a few of the above influencing variables can be counteracted. In particular, ovalizations of the casing or an offset between the axis of rotation of the rotor and the central axis of the casing can not be compensated. Furthermore, it is disadvantageous that the Flat springs and the adjustment during the operation of the turbomachine directly with the high rotor chamber temperatures come into contact. In modern, designed as a gas turbine turbomachinery with high overall pressure ratios, however, the temperatures can be so high that the spring action of the flat springs is lost or the carrying capacity of the adjustment is no longer sufficient. In addition, the gap maintenance system has a high complexity and a relatively high weight, which in addition to the manufacturing and maintenance costs and the probability of failure of the entire gap maintenance system is increased.
- Object of the present invention is therefore to provide a gap control system of the type mentioned, which allows a structurally simple way a compensation of as many influencing factors and thus reliable and reliable adjustability of the running gap under different operating conditions of the associated turbomachine.
- Another object is to provide a turbomachine with such a gap control system and a corresponding method for adjusting a running gap of a turbomachine.
- a gap control system which enables a compensation of as many influencing variables as possible and thus a reliable and reliable adjustability of the running gap under different operating conditions of the associated turbomachine is inventively created in that each segment of the jacket is coupled to at least three adjustment of the gap control system.
- the adjusting devices can basically individual elements such as adjusting, actuators, control rods and the like or include or consist of any combination of these elements. This makes it possible, in contrast to the prior art, to force the segments operating state independently on a circular path and thus to ensure a steady and constant curvature of the segments. Since the segments of the sheath are designed for a certain diameter, crescent-shaped running gaps can result in the purely radial movement of the segments, as described in the prior art.
- each segment is coupled to at least three circumferential locations with one of the adjusting devices and can thus be easily forced onto a circular path with the current rotor diameter plus the desired running gap.
- the adjusting devices are arranged uniformly spaced from each other to ensure a correspondingly uniform force distribution over the segment and a good setting of the circular arc shape.
- the running gap can be adjusted optimally with the help of the gap control system according to the invention, regardless of the operating state of the associated turbomachine, whereby the efficiency of the turbomachine is increased and their fuel consumption is reduced accordingly. Due to the structurally simple construction of the gap control system according to the invention also result in comparison to known gap control systems also significant cost and weight savings and advantageously increased reliability and ease of maintenance.
- the gap control system is basically suitable both for a single stage and for several stages of a turbomachine.
- two adjusting devices are arranged on opposite edge regions of their associated segment and / or an adjusting device is arranged in the middle of its associated segment.
- a particularly weight and space-saving arrangement is given in another embodiment in that at least two adjacent segments are coupled to a common adjusting device.
- a high tightness of the casing and a correspondingly high efficiency of the turbomachine are also ensured.
- adjacent edge regions of two segments can advantageously be moved radially together. In this way, a steady transition from one segment to the adjacent segment is ensured, so that the emergence of crescent-shaped running gaps is particularly reliably prevented.
- a high backlash is thereby achieved at the junction between the segments and the adjustment.
- all adjacent segments are each coupled to one or more common adjustment devices in order to obtain an optimized arrangement.
- an adjusting element which can be arranged around the rotor is provided, which is coupled to at least one adjusting device and is movable relative thereto for actuating the adjusting device.
- This allows a structurally simple, cost-effective and space-saving arrangement of the adjusting element in the region of the rotor or the sheathing.
- forces occurring when moving or pivoting of the adjustment can be well distributed, whereby the mechanical stability and life of the adjustment is extended accordingly.
- the adjusting element may preferably be formed at least substantially as a ring.
- the adjusting element comprising a plurality of subsections which are preferably connected to one another in an articulated manner.
- This has the Adjustment additional freedom of movement, so that an additional improved adjustability of the running gap is made possible during pivoting of the adjusting element.
- a buckling of the adjustment ie by a relative movement of the sections to each other, a ovalization of the shell due to maneuvering and compressive forces are particularly easy to compensate.
- the adjusting element for adjusting the running gap is axially displaceable relative to the axis of rotation of the rotor and / or is pivotable relative to the rotor.
- the gap control system according to the invention makes it possible, by moving the adjusting element axially, to move the segments uniformly over the circumference of the rotor and to achieve a correspondingly uniform change of the running gap.
- a non-uniform movement of the segments over the circumference of the rotor can be generated, so that ovalization of the casing due to maneuvering and pressure forces and any offset between the axis of rotation of the rotor and the center axis of the sheath can be considered easily.
- At least one of the adjusting devices is designed to convert an at least predominantly axial movement of the adjusting element into an at least predominantly radial movement of the associated segment of the casing. With the aid of the adjusting device, large movements of the adjusting element can thus advantageously be converted into small movements of the associated segment and vice versa, whereby a particularly precise adjustability of the running gap is provided. It is preferably provided that all adjusting devices are designed in this way.
- At least one adjusting device is fixed to a support housing.
- the support housing may be formed, for example, as an outer housing of the turbomachine or be arrangeable within a separate outer housing.
- the support housing is annular and / or the outer circumference of the sheath and / or can be arranged concentrically to the axis of rotation of the rotor.
- the casing comprises at least one vane and / or is preferably supported by means of a push rod relative to the support housing.
- the guide vanes are usually fastened to the support housing, so that no influence can be exerted on the inner running gap.
- the casing comprises the at least one vane - z.
- the vane can advantageously be moved when setting the running gap of the rotor, whereby the inner gap of the turbomachine is adjustable.
- At least one sensor device by means of which a size of the running gap can be determined. This allows a particularly simple, fast and precise determination of the size of the running gap, whereby a correspondingly improved adjustment of the running gap is made possible.
- the sensor device can fundamentally operate according to different physical principles, for example capacitive, inductive, optical, with microwaves or with eddy current.
- a plurality of sensor device are provided which, preferably uniformly, are arranged spaced from each other and / or the outer circumference of the sheathing can be arranged.
- the running gap can thus be determined particularly precisely and spatially resolved, so that correspondingly different adjustment movements of the segments can be carried out and a uniform running gap can be generated.
- At least one actuator coupled to the adjusting element is provided, by means of which the adjusting element is axially displaceable relative to the axis of rotation of the rotor or pivotable relative to the rotor.
- the adjusting element can be moved in a particularly simple and precise manner.
- large movements of the at least one actuator can advantageously be converted into small movements of the segments or vice versa.
- the actuator can basically function according to different physical principles, for example hydraulically, pneumatically, electrically, piezoelectrically or magnetically.
- the at least one actuator is arranged in the region of at least one adjusting device.
- the actuator is arranged in the region of a sensor device.
- a simplified and particularly precise adjustability of the running gap is ensured due to the small spatial distance between the sensor device and the actuator.
- a further improvement of the adjustability of the nip is given in a further embodiment in that at least one control and / or regulating unit is provided, which is coupled to at least one sensor device and at least one actuator and is designed to at least one actuator in dependence of the To control or regulate at least one sensor device determined size of the running gap.
- At least two adjusting devices are arranged axially with respect to the axis of rotation of the rotor and actuated jointly by means of the adjusting element. Since the rotors of several stages of a turbomachine designed as a high-pressure compressor exhibit a similar expansion behavior over time - especially if the coefficients of thermal expansion of the materials used are similar - then the running gaps of several stages can be adjusted with the same movement of the adjusting element. It may optionally be provided that - for example, by different lever lengths on the adjustment - different Hubzien on the segments of the multi-part casing of different levels can be achieved. In addition, if required, a different gap size can be generated at each stage.
- At least one adjusting an actuating lever and / or a thrust bearing and / or a ball screw and / or a spindle drive and / or an eccentric shaft and / or a bending spring and / or a spring element and / or a Knee lever and / or a grid includes.
- the at least one adjusting device thereby makes it possible, in a structurally simple way, for an at least predominantly axial movement of the adjusting element to be converted into a smaller radial movement of the segment of the sheathing.
- At least one adjusting device comprising a sealing element, which is preferably designed as a clamping band and / or bellows seal and / or piston ring and / or C-seal.
- a sealing element which is preferably designed as a clamping band and / or bellows seal and / or piston ring and / or C-seal.
- At least one adjusting device comprises a tension bolt coupled to at least one segment and a pressure bolt coupled to the at least one segment, wherein the tension bolt and the pressure bolt are movable relative to each other and subjected to force.
- the entire adjusting device is prestressed in itself and thus free of play, so that a particularly precise gap adjustment can be realized.
- the application of force between train and Pressure pin can be accomplished, for example, with the aid of a spring element, in principle, any desired spring designs such as coil springs, cup spring pack or the like can be provided.
- Another aspect of the invention relates to a turbomachine, in particular a gas turbine rotor having a rotor blades, at least partially surrounding it, at least two segments comprising sheath, and a gap control system by means of which a running gap between the rotor and the sheath is adjustable.
- a gap control system is designed according to one of the preceding embodiments.
- the gap control system is accommodated in a housing and / or forms at least a part of the housing.
- the inclusion in a housing of the turbomachine allows a mechanically stable, reliable and space-saving arrangement of the gap control system.
- the gap control system itself forms at least a part of the housing.
- the casing comprising at least one vane. If the at least one guide vane is provided on the casing or on a segment, advantageously also the running gaps on the annular space inner contour, that is the gap between the rotor and the at least one vane, are set by the gap control system. The forces generated by the at least one vane during operation of the turbomachine then act on the segments.
- the at least two segments of the casing are coupled together.
- a high tightness of the casing and a correspondingly high efficiency of the turbomachine are ensured.
- adjacent regions of two segments can advantageously be moved radially together. In this way, moreover, a steady transition from one segment to the adjacent segment is ensured so that the emergence of crescent-shaped running gaps is particularly reliably prevented.
- a high backlash is thereby achieved at the junction between the segments and the adjustment.
- At least one segment comprises a stiffening element, by means of which a curvature of the segment is adjustable as a function of the size of the running gap.
- a stiffening element by means of which a curvature of the segment is adjustable as a function of the size of the running gap.
- the stiffness distribution of the segment of the casing can be selected such that a constant curvature can be generated under all operating conditions of the turbomachine.
- the stiffening element can be designed as a rib with variable radial height or by ribs with decreasing width to the segment edges out, whereby the stiffness distribution is structurally simple and inexpensive adaptable to the respective requirement profile of the turbomachine.
- the gap control system is arranged in the region of a low-pressure compressor stage and / or a high-pressure compressor stage and / or a low-pressure turbine stage and / or a high-pressure turbine stage of the turbomachine.
- sheath comprising two segments formed as half-rings and / or at most eight, more preferably at most six segments.
- the number of components and thus the potential leakage points is kept small.
- the ease of assembly and maintenance is considerably improved.
- each segment of the casing is coupled to at least three spaced adjustment of the gap control system.
- the representation of a contant curvature of each segment is ensured particularly reliable.
- the adjustability of a constant curvature is promoted by a corresponding geometric design and / or a stiffness distribution of the segments.
- a cross-sectional contour of each segment can be chosen so that the second derivative of the bending line results in a constant value and, accordingly, a constant curvature can be generated under all operating conditions of the turbomachine.
- Another aspect of the invention relates to a method for adjusting a running gap between a rotor comprising a rotor blades of a turbomachine, in particular a gas turbine, and a surrounding this at least partially surrounding, at least two segments comprising sheath.
- the method comprises according to the invention at least the steps of determining a size of the running gap by means of at least one Sensor device and transmitting the size of a control and / or regulating unit, controlling or regulating at least one actuator by means of the control and / or regulating unit in dependence of the determined size of the running gap, axial displacement and / or pivoting with respect to a rotational axis of the rotor of order the adjusting element arranged by means of the at least one actuator, actuation of at least one adjusting device by means of the adjusting element and radial movement relative to the axis of rotation of the rotor of at least one segment of the casing by means of the at least one adjusting device.
- the size of the running gap is determined by means of the control and / or regulating unit on the basis of the transmitted size of a further sensor device and the at least one actuator is controlled or regulated as a function of the determined variable ,
- the at least one actuator is controlled or regulated as a function of the determined variable
- Fig. 1 shows a schematic line diagram of a time- and load-dependent radius change of a rotor and a surrounding casing of a turbomachine and has already been explained above.
- ⁇ r opt the actual radius of the jacket of the rotor characterized by the line .phi.2
- a gap control system to measure the actual radius of the jacket of the rotor characterized by the line .phi.2 by means of a gap control system to the line shown by the dashed line ⁇ 3 characterized SollRadius adapt.
- Fig. 2 shows a schematic perspective view of a gap control system according to a first embodiment.
- the gap control system serves to set the running gap L between a rotor blades 10 (s. Fig. 10 ) comprehensive rotor 12 (s. Fig. 3 ) of a turbomachine 14 (s. Fig. 10 ), in particular a gas turbine, and a surrounding this at least partially sheathing 18.
- a turbomachine 14 s. Fig. 10
- the sheath 18 in the present embodiment four segments 16a-d (liner), which are at least largely independently movable.
- the gap control system comprises eight adjusting devices 20 designed as adjusting gears, which are each coupled to at least one segment 16 of the casing 18.
- the adjusting devices 20 are designed as actuators, control rods or the like or comprise actuators, control rods or equivalent elements.
- the gap control system comprises an adjusting element 22 which can be arranged around the rotor 12 and which in the present case is designed essentially as a ring and comprises two half rings connected to one another in an articulated manner as partial sections 22a, 22b.
- the adjusting element 22 is coupled to the adjusting devices 20 and can be displaced axially relative to the axis of rotation D of the rotor 12 or pivoted relative to the rotor 12 in order to actuate the adjusting devices 20 and thus to adjust the running gap L.
- the adjusting devices 20 are designed to convert an at least predominantly axial movement of the adjusting element 22 into an at least predominantly radial movement of the respectively associated segments 16a-d of the casing 18.
- the segments 16a-d are arranged within a ring-shaped support housing 24 arranged concentrically with the axis of rotation D of the rotor 12.
- the support housing 24 may be formed as an outer housing of the turbomachine 14 or lie within a separate outer housing.
- the adjusting devices 20 - and thus indirectly the adjusting element 22 - are fixed to the support housing 24.
- a total of four sensor devices 26a-d are uniformly spaced from one another on the supporting housing 24, by means of which a size of the running gap L at different circumferential positions can be determined.
- Between the support housing 24 and the radially displaceable segments 16a-d sealing elements are arranged.
- the sealing elements may be formed as sealing flakes (so-called “leaf seals”), wherein other types of seals, such as brush seals or C-rings, may be provided.
- the sealing elements 40 prevent a carrying-housing-side flow around the segments 16a-d in the axial direction.
- the gap control system further comprises four actuators 28a-d coupled to the adjusting element 22, by means of which the adjusting element 22 is displaceable axially relative to the axis of rotation D of the rotor 12 or pivotable relative to the rotor 12.
- the actuators 28a-d are uniformly spaced from each other outside the Sheath 18 and each arranged in the region of an adjusting device 20.
- the gap control system has control and / or regulating unit 30, which is coupled to the sensor devices 26a-d and the actuators 28a-d.
- the control and / or regulating unit 30 is designed to control or regulate the actuators 28a-d as a function of the size ⁇ r of the running gap L determined by means of the sensor devices 26a-d.
- the control signals supplied by the sensor devices 26a-d are processed in the control and / or regulating unit 30.
- the respective actuator 26a-d associated with the relevant sensor device 26a-d normally receives a signal to move the adjusting element axially until the optimum size ⁇ r opt of the sensor device 26a-d in question Run gap L can be determined. The same happens at the other sensor positions. This makes it possible to perform different strokes of the segments 16a-d at different circumferential positions.
- the sensor devices 26a-d can operate according to various physical principles, for example, capacitively, inductively, optically, with microwaves or with eddy current.
- the same applies to the actuators 28a-d which can be operated, for example, hydraulically, pneumatically, electrically, piezoelectrically or magnetically.
- the actuator 26a-d whose normally assigned sensor device 26a-d has failed, can still be activated via a corresponding error logic by the preferably redundantly designed control and / or regulating unit 30.
- a corresponding control signal can be derived from the signals of the remaining functional sensor device 26a-d.
- the adjusting element 22 of all actuators 28a-d axially with respect to the axis of rotation D of the rotor 12 is moved.
- the adjusting element 22 With an offset of the center axis M of the support housing 24 with respect to the axis of rotation D, the adjusting element 22, however, is moved differently in the axial direction at the individual actuator positions.
- the adjusting element 22 thereby performs a spatial pivoting movement relative to the rotor 12 and its axis of rotation D. (Wobble) off.
- a constant running gap L over the entire circumference of the sheath 18 can be adjusted.
- a particular advantage of the adjusting devices 20 lies in the fact that they can convert comparatively large movements of the actuators 28a-d into comparatively small movements of the segments 16a-d, as a result of which the running gap L can be set particularly precisely.
- a point on a tip of a rotor blade 10 describes an ideal circular path.
- a circle is uniquely determined when three points in space are known that lie at different circumferential positions in the circle plane. If one neglects first the case of an ovalization of the sheath 18, a total of three sensor devices 26 and three actuators 28 are connected to a one-piece adjusting element 22 in order to set a running gap L constant over the circumference of the sheath 18 in different operating states of the turbomachine.
- Fig. 3 shows a schematic sectional view of the in Fig. 2 shown gap control system, wherein in addition to a change in the diameter ⁇ and the radius of the rotor 12 in addition an offset between the central axis M and the axis of rotation D and an ovalization of the sheath 18 occurs.
- the casing 18 in turn has a minimum diameter ⁇ min and a maximum diameter ⁇ max , whereby the running gap L varies over the circumference and has different sizes ⁇ r ad .
- the ovalization are perfectly balanced when the articulated connection of the sections 22a, 22b of the adjusting element 22 in a through the engine axis T and a major axis H of the resulting Cross-sectional ellipse formed plane lie.
- the ovalization is only partially compensated. If the ovalization is to be at least approximately completely compensated even in any position of the cross-sectional ellipses, then a further subdivision of the adjusting element 22, for example into three subsections or the use of six actuators 28, has proven to be advantageous.
- the gap control system according to the invention is able to adjust the running gap L over the circumference of the sheath 18 with different adjustment paths. As a result, it is possible to react both to changes in the diameter ⁇ or the radius r of the rotor 12 and to an offset between the center axis M of the casing 18 and the axis of rotation D of the rotor 12 and also to an ovalization of the casing 18.
- Fig. 4 shows a schematic perspective view of three segments 16a-c of in Fig. 2 shown sheath 18, wherein each segment 16a-c is coupled to a plurality of adjusting devices 20 of the gap control system.
- the segments 16a-c are usually made for a certain diameter. If the relatively large segments 16a-d were simply displaced to a different radius, crescent-shaped running gaps L would result due to their curvature. Moreover, in unsteady operating states of the turbomachine, a radial temperature gradient which changes the curvature uncontrollably and deformations by mechanical stress ( eg by gas loads).
- each segment 16a-d is coupled at three peripheral locations with an adjusting device 20 and forced by this on a circular path with the current rotor diameter plus the desired running gap L.
- an adjusting device 20 is assigned to two segments 16.
- the segments 16a-d are positively connected in the radial direction with their respective adjacent segments 16 at the segment edges.
- the positive connection is generated by a tension bolt 31 and a spring-loaded pressure plate 33 of the adjusting device 20. This is achieved at the junction of the segments 16a-d with the respective adjustment 20 backlash.
- the segments 16a-d are mutually displaceable, which is necessary on the one hand because of the occurring during operation different temperatures between the segments 16a-d and the support housing 24 and on the other hand due to the ability to move the segments 16a-d radially (a radial displacement of all Segments 16a-d, for example, 0.5 mm results in a change in the circumferential length of 3.14 mm).
- the stiffness distribution is selected such that a constant curvature is present under all operating conditions.
- Fig. 5 shows for this purpose several embodiments of each provided with stiffening elements 32 segments 16. With the help of the stiffening elements 32 is maintained at a variation of the radial position of the segments 16a-d almost an ideal circular shape.
- the stiffening elements 32 may be formed integrally with the segments 16. Possible embodiments of the stiffening elements 32 include, for example, variation of the radial height of the segment 16 or ribs of decreasing width towards the segment edges. In this way, the stiffness distribution of the segments 16 can be optimally adapted.
- Fig. 6 shows a schematic perspective view of a plurality of vanes 34 comprising segment 16, which is indirectly supported by means of a hinged at its ends push rod 36 relative to the support housing 24 (not shown) of the turbomachine.
- a fastening element of the adjusting device 20 simultaneously acts as a support element for the push rod 36, so that occurring forces are introduced into the support housing.
- the vanes 34 may be formed as separate components or as an integral part of the segments 16. Alternatively or additionally, the guide vanes 34 may be fixed to the support housing 24.
- the vanes 34 are fastened to the segments 16 as shown, the running gaps on the annular space inner contour, that is the running gap between the rotor, also become fixed 12 and the vanes 34, adjusted by the gap control system.
- the forces generated by the vane 34 then act on the segment 16. So that the gap control system is not adversely affected by these forces, it makes sense to derive the forces by means of the push rod 36 and distribute.
- Fig. 7 shows an embodiment of the adjusting device 20 in a schematic perspective and side view.
- the adjusting device 20 also allows the conversion of a predominantly axial movement of the adjusting element 22 in a small radial movement of the associated segment 16.
- the adjusting device 20 includes a bending spring 38 which is mounted on the support housing 24 and deformed by a coupled to the adjusting element 22 toggle mechanism 42 can be.
- a traverse 44 attached to the bending spring 38 transmits the movement to the segment 16.
- FIG. 8 Another embodiment of the adjusting device 20 is in a schematic perspective and side view in Fig. 8 shown.
- the radial movement of the cross member 44 and thus of the segment 16 is generated by rotating eccentric shafts 46 coupled to the adjusting element 22.
- Fig. 9 shows a schematic perspective view of the gap control system according to a second embodiment.
- the present gap control system comprises a plurality of groups of three, via a coupling rod 48 coupled to each other adjusting means 20 which are each arranged axially relative to the axis of rotation D of the rotor 12 and actuated jointly by means of the adjusting element 22.
- the sheath 18 comprises a plurality of groups of segments 16, which are also arranged along the axis of rotation D of the rotor 12.
- the gap maintenance system is therefore particularly suitable for multi-stage turbomachinery.
- the rotor expansions of the stages in a high pressure compressor show a similar temporal behavior - especially if the coefficients of thermal expansion of the materials used are chosen similarly - it is possible in conjunction with an optimization of the temporal expansion behavior of the support housing 24 (geometric design, mass distribution, insulation and the like), the Cleavage behavior of the stages as far as possible to match each other.
- Different lever lengths on the adjusting devices 20 make it possible to achieve different lifting movements on the segments 16 of the various stages with the same axial movement of the adjusting element 22.
- a different running gap L can be set at each stage. This makes it possible to set the run column L of the other stages with the same actuator movement by the running gap size determination at one stage.
- Fig. 10 shows a schematic and partial sectional side view of a with the in Fig. 9
- the flow machine 14 or the gap control system will be described below in conjunction with Fig. 11 and Fig. 12 be explained.
- Fig. 11 shows a schematic and partially sectioned perspective view of a Fig. 10 shown adjusting device 20, while in Fig. 12
- a schematic lateral sectional view of the adjusting device 20 is shown according to a further embodiment.
- the general structure of the turbomachine 14 is known from the prior art.
- the three in Fig. 10 recognizable adjusting devices 20 are arranged along the axis of rotation D of the rotor 12 and fixed to a support housing 24 of the turbomachine 14. Due to a comparable expansion behavior, the three adjusting devices 20 are jointly controlled and actuated.
- the adjusting devices 20 are actuated or controlled in a controlled manner individually or in groups.
- the gap control system can in principle be arranged both in compressor and in turbine stages. Particular advantages arise when the gap control system is arranged in the region of the rear stages of the turbomachine, because in these due to the small blades, the ratio between running gap and blade size is particularly relevant.
- Each adjusting device 20 is sealed with sealing elements 52.
- Two liner segments 16a, 16b are pressed radially inwards in the direction of the rotor 12 by a spring element 54 (eg helical spring, disc spring package etc.) via a pressure sleeve 80 and the pressure plate 33. So that no segment 16 is moved into the rotor 12, each segment 16 via a thread 58, which in the in Fig. 11 shown embodiment as a ball screw and im in Fig. 12 shown embodiment as Movement thread is formed, are moved radially away from the rotor 12.
- the power transmission takes place in each case via a thrust bearing 60 on an anchor plate 62 and the tie bolt 31.
- This is positively connected to the segment 16 and the segments 16a, 16b, wherein in Fig. 12 a sliding between the segment 16b and the tie bolt 31 is exemplified by arrow XII.
- the arrangement described has the advantage that the entire adjusting device 20 is braced by the spring elements 54 and thus free of play.
- the thread 58 in combination with the thrust bearing 60 has the advantage that the adjusting device 20 has a low wear and a low internal friction.
- the spring elements 54 are presently integrated in the adjusting device 20 and outside of the outer housing 50 and thus arranged in the comparatively cold region of the turbomachine 14. Between the outer housing 50 and the adjusting device 20 and within the adjusting device 20 a plurality of sealing elements 52 are arranged. These give the components the necessary movement possibilities (lifting movement and thermal expansion) and at the same time seal spaces with different pressures against each other.
- sealing elements 52 designed as piston rings, C-seals, bellows or the like may also be provided.
- actuating lever 66 of the adjusting device 20 can be seen, which is coupled on the one hand with the adjusting element 22 and on the other hand rotatably connected to the thread 58 in order to convert the at least substantially axial movement of the adjusting element 22 in a smaller radial movement.
- a basically optional screening facilitates the desired adjustability of the running gap L in some applications.
- the adjusting device 20 functions according to the embodiment shown in the manner of a spindle drive.
- the adjusting device 20 is attached to the support housing 24 of the turbomachine by screws, welding or the like.
- connection sleeve 82 can be seen.
- the spring element 54 (coil spring, cup spring package, etc.) presses the segments 16a, 16b over one Pressure pin 80 and the pressure plate 33 at the segment edges or in the middle of the segment (not shown) radially in the direction of the engine axis, wherein the spring element 54 is supported on the bolt part of the thread 58.
- the nut part 58a of the thread 58 acts on the armature plate 62 via a thrust bearing and on the segments 16a, 16b via the tension bolt 31 or on a single segment 16 in the middle of a segment.
- the tension bolt 31 counteracts the pressure pin 80, as a result the entire adjustment 20 is biased in and thus free of play.
- the rotation of the nut member 58a causes a radial displacement of the armature plate 62 and the indirectly connected thereto segments 16a, 16b.
- Various sliding elements 52 are provided on the sliding points (arrow XII) between adjusting device 20 and housings (outer housing 50 or supporting housing 24) and within the adjusting device 20.
- the connecting sleeve 82, the thread 58 and the anchor plate 62 form an adjusting device housing 90 in the present case.
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Description
Die Erfindung betrifft ein Spaltkontrollsystem zum Einstellen eines Laufspalts zwischen einem Rotorschaufeln umfassenden Rotor einer Strömungsmaschine, insbesondere einer Gasturbine, und einer diesen zumindest abschnittsweise umgebenden, wenigstens zwei Segmente umfassenden Ummantelung. Die Erfindung betrifft weiterhin eine Strömungsmaschine, insbesondere eine Gasturbine, der im Oberbegriff des Patentanspruchs 11 angegebenen Art sowie ein Verfahren zum Einstellen eines Laufspalts zwischen einem Rotorschaufeln umfassenden Rotor einer Strömungsmaschine, insbesondere einer Gasturbine, und einer diesen zumindest abschnittsweise umgebenden, wenigstens zwei Segmente umfassenden Ummantelung.The invention relates to a gap control system for adjusting a nip between a rotor blades comprising a rotor blades of a turbomachine, in particular a gas turbine, and a surrounding this at least partially surrounding, at least two segments comprising sheath. The invention further relates to a turbomachine, in particular a gas turbine, the type specified in the preamble of claim 11 and a method for adjusting a running gap between a rotor blades comprehensive rotor of a turbomachine, in particular a gas turbine, and at least partially surrounding this, at least two segments comprising sheath ,
Der Wirkungsgrad einer Strömungsmaschine, beispielsweise eines Verdichters oder einer Turbine, hängt wesentlich von der Größe des radialen Laufspalts zwischen einem Rotor und statischen Bauteilen der Strömungsmaschine ab. Bei Verdichtern wird zusätzlich die Lage der Pumpgrenze - das heißt die Grenze, bis zu der ein stabiler Betrieb der Strömungsmaschine möglich ist - wesentlich durch die Größe des Laufspalts bestimmt. Die Verwirklichung von möglichst kleinen, über die Betriebsdauer der Strömungsmaschine konstant bleibenden radialen Laufspalten ist daher ein vorrangiges Auslegungsziel. Dies ist umso wichtiger, je kleiner die Abmessungen der Rotorschaufeln des Rotors sind. Dies ist beispielsweise in hinteren Stufen eines Hochdruckverdichters bzw. einer als Hochdruckturbine ausgebildeten Strömungsmaschine der Fall.The efficiency of a turbomachine, for example a compressor or a turbine, depends essentially on the size of the radial running gap between a rotor and static components of the turbomachine. In the case of compressors, the position of the surge limit-that is to say the limit up to which stable operation of the turbomachine is possible-is also determined essentially by the size of the running gap. The realization of the smallest possible, over the operating life of the turbomachine constant radial clearance gaps is therefore a primary design goal. This is even more important the smaller the dimensions of the rotor blades of the rotor. This is the case, for example, in the rear stages of a high-pressure compressor or a turbomachine designed as a high-pressure turbine.
Betrachtet man das Laufspaltverhalten einer Strömungsmaschine, so stellt man fest, dass der Laufspalt aufgrund unterschiedlicher zeitlicher Dehnverhalten des Rotors und seiner Ummantelung, welche beispielsweise als Gehäuse oder Gehäuseteil ausgebildet sein kann, relativ stark variiert. Zur näheren Erläuterung zeigt
Die optimale Größe Δropt des Laufspalts L soll dabei mit Hilfe eines Spaltkontrollsystems der Strömungsmaschine eingestellt werden können. Im gezeigten Ausführungsbeispiel wird ein zumindest annähernd konstanter Laufspalt L mit der Größe Δropt=0,1-0,2 mm angestrebt. Beim Beschleunigen (Phase Ib) aus einer Leerlaufphase Ia, in welcher der Laufspalt L die Anfangsgröße Δr1 besitzt, erfährt der Radius des Rotors bzw. der Rotorscheibe im Bereich B1 - proportional zur Drehzahländerung - eine Radiusänderung aufgrund der wirkenden Fliehkräfte. Demgegenüber erfolgt eine thermisch bedingte Dehnung der Rotorscheibe aufgrund ihrer vergleichsweise großen radialen Erstreckung und großen Masse deutlich langsamer (Bereich B2). Die Ummantelung mit ihrer im Vergleich zum Rotor geringeren Masse reagiert in der Regel thermisch wesentlich schneller (Bereich B3). Beim Beschleunigen gemäß Phase Ib verringert sich daher der ursprünglich vorhandene Laufspalt L=Δr1 zunächst wegen der sehr schnell wirkenden Fliehkraftdehnung des Rotors und wird dann deutlich größer, weil die Ummantelung thermisch schneller reagiert. Der Laufspalt L erreicht im Bereich B4 seinen Maximalwert Δrmax - z.B. Δrmax=0,8 mm - über welchen der mit Pfeil I markierte geforderte Verstellbereich der Ummantelung bzw. der Segmente der Ummantelung definiert ist.The optimum size Δr opt of the nip L should be able to be adjusted by means of a gap control system of the turbomachine. In the embodiment shown, an at least approximately constant running gap L with the size Δr opt = 0.1-0.2 mm is desired. When accelerating (phase Ib) from an idling phase Ia, in which the running gap L has the initial size .DELTA.r 1 , the radius of the rotor or the rotor disk in the region B 1 - proportional to the speed change - undergoes a change in radius due to the centrifugal forces. In contrast, a thermally induced elongation of the rotor disk due to their relatively large radial extent and large mass is much slower (range B 2 ). The sheath, with its lower mass compared to the rotor, generally reacts thermally much faster (range B 3 ). When accelerating according to phase Ib, therefore, the originally existing running gap L = Δr 1 initially decreases because of the very fast acting centrifugal force expansion of the rotor and then becomes significantly larger because the jacket reacts thermally faster. The running gap L reaches its maximum value Δr max in the area B 4 - eg Δr max = 0.8 mm - over which the required adjustment range of the sheathing or of the segments of the sheathing marked with arrow I is defined.
Nachdem auch der Rotor durchgeheizt ist, wird in Phase Ic die stationäre Laufspaltgröße Δrstat - z.B. Δrstat=0,4 mm - erreicht. Beim Verzögern in Phase Id vergrößert sich zunächst der Laufspalt L wegen der geringer werdenden Fliehkraftbelastung des Rotors. Anschließend wird der Laufspalt L wieder kleiner und erreicht seinen Minimalwert Δrmin, da die Ummantelung schneller abkühlt als der Rotor. Beim Abkühlen der Strömungsmaschine stellt sich nach einer gewissen Zeit wieder die Anfangsgröße Δr1 des Laufspalts L ein. Aus
Das beschriebene transiente Spaltverhalten eines rein passiven Spaltkontrollsystems und die Forderung, dass ein "hartes" Anstreifen der Rotorschaufeln an der Ummantelung unbedingt zu vermeiden ist, führt insbesondere im Hochdruckbereich von modernen Strömungsmaschinen zu stationären Laufspaltgrößen Δrstat im Bereich von etwa 2-3% der Höhe der Rotorschaufeln. Die maximalen Laufspaltgrößen Δrmax, die während des transienten Betriebes auftreten, können dabei jedoch mehr als die doppelten Werte erreichen. Die Größe des Laufspalts einer Strömungsmaschine hängt zusammenfassend von verschiedenen Einflussgrößen ab:
- Dehnungen des Rotors aufgrund von Fliehkraftwirkungen;
- Thermische Dehnungen des Rotors und der Ummantelung;
- Dehnungen und Ovalisierung der Ummantelung aufgrund von Manöverlasten und Druckkräften;
- Versatz zwischen der Drehachse des Rotors und der Mittelachse der Ummantelung aufgrund von Manöverlasten; sowie
- Fertigungstoleranzen, beispielsweise Unrundheiten oder Exzentrizitäten.
- Strains of the rotor due to centrifugal forces;
- Thermal expansions of the rotor and the cladding;
- Stretching and ovalization of the sheath due to maneuvering and compressive forces;
- Misalignment between the axis of rotation of the rotor and the central axis of the casing due to maneuvering loads; such as
- Manufacturing tolerances, such as discontinuities or eccentricities.
Bei den aus dem Stand der Technik bekannten passiven Spaltkontrollsystemen wird versucht, anhand der Masse des Rotors und der Ummantelung bzw. deren Masseverteilung, durch geeignete Führung von Sekundärluftströmen sowie durch Beeinflussung des Wärmeflusses mithilfe geometrisch optimierter Gestaltung und Wärmedämmschichten das Dehnverhalten der Strömungsmaschinenbauteile derart zu optimieren, dass geringstmögliche Diferenzdehnungen zwischen dem Rotor und dem Stator bzw. der Ummantelung erzielt werden.In the passive gap control systems known from the prior art, it is attempted, on the basis of the mass of the rotor and the sheathing or their mass distribution, to optimize the expansion behavior of the turbomachinery components by suitable guidance of secondary air flows and by influencing the heat flow with the aid of geometrically optimized design and thermal barrier coatings. that the smallest possible Diferenzdehnungen between the rotor and the stator or the sheath are achieved.
Alternativen stellen thermisch aktive Spaltkontrollsysteme dar, bei denen der Laufspalt durch gezieltes Kühlen bzw. Aufheizen der relevanten Bauteile optimiert wird. Beispiele hierfür sind das Spaltkontrollsystem der CFM56-Triebwerksfamilie, bei der die Rotortemperatur geregelt wird, oder das aus der
Als weitere Alternative sind mechanisch aktive Spaltkontrollsysteme bekannt. Um einen möglichst kleinen Laufspalt unter Berücksichtigung der genannten Einflussgrößen erzielen zu können, sollte sich die Ummantelung des Rotors zu jedem Zeitpunkt möglichst gut an dessen Durchmesser und relative Lage anpassen können. Zu diesem Zweck wird die Ummantelung häufig segmentiert. Die
Ein Versatz zwischen der Drehachse des Rotors und der Mittelachse der Ummantelung sowie Ovalisierungen der Ummantelung können jedoch nicht oder nicht zufrieden stellend ausgeglichen werden. Da die Segmente der Segmentgruppe in Umfangsrichtung ortsfest gelagert sind, entstehen bei einem Versatz der Drehachse des Rotors gegenüber der Mittelachse der Ummantelung sichelförmige Laufspalte, da alle gekoppelten Segmente der Ummantelung die gleiche Hubbewegung ausführen. Um eine im Vergleich zu einem passiven Spaltkontrollsystem verbesserte Einstellbarkeit des Laufspalts erreichen zu können, ist zudem eine relativ große Anzahl von zwölf oder mehr Segmentgruppen erforderlich. Gleichzeitig wird auch eine entsprechende Anzahl von Aktuatoren und Sensoreinrichtungen benötigt, wodurch neben den Herstellungskosten auch der Bauraumbedarf und die Fehleranfälligkeit steigen.However, an offset between the axis of rotation of the rotor and the central axis of the casing as well as ovalizations of the casing can not be compensated satisfactorily or not. Since the segments of the segment group are mounted stationarily in the circumferential direction, crescent-shaped running gaps arise in the case of a displacement of the axis of rotation of the rotor relative to the central axis of the casing, since all the coupled segments of the casing execute the same lifting movement. Moreover, in order to be able to achieve an improved adjustability of the running gap compared to a passive gap control system, a relatively large number of twelve or more segment groups is required required. At the same time a corresponding number of actuators and sensor devices is required, which in addition to the manufacturing costs and the space requirement and susceptibility to errors increase.
Aus der
Die
Als nachteilig ist dabei der Umstand anzusehen, dass die Segmente der Ummantelung nur gemeinsam radial bewegt werden können, so dass nur wenigen der oben genannten Einflussgrößen entgegengewirkt werden kann. Insbesondere Ovalisierungen der Ummantelung oder ein Versatz zwischen der Drehachse des Rotors und der Mittelachse der Ummantelung können nicht ausgeglichen werden. Weiterhin ist nachteilig, dass die Flachfedern und die Verstelleinrichtungen während des Betriebs der Strömungsmaschine unmittelbar mit den hohen Rotorraumtemperaturen in Kontakt treten. Bei modernen, als Gasturbinen ausgebildeten Strömungsmaschinen mit hohen Gesamtdruckverhältnissen können die Temperaturen jedoch so hoch werden, dass die Federwirkung der Flachfedern verloren geht oder die Tragfähigkeit der Verstelleinrichtungen nicht mehr ausreicht. Zudem besitzt das Spalthaltungssystem eine hohe Komplexität sowie ein vergleichsweise hohes Gewicht, wodurch neben den Herstellungs- und Wartungskosten auch die Ausfallwahrscheinlichkeit des gesamten Spalthaltungssystems erhöht ist.A disadvantage is the fact that the segments of the shell can only be moved radially together, so that only a few of the above influencing variables can be counteracted. In particular, ovalizations of the casing or an offset between the axis of rotation of the rotor and the central axis of the casing can not be compensated. Furthermore, it is disadvantageous that the Flat springs and the adjustment during the operation of the turbomachine directly with the high rotor chamber temperatures come into contact. In modern, designed as a gas turbine turbomachinery with high overall pressure ratios, however, the temperatures can be so high that the spring action of the flat springs is lost or the carrying capacity of the adjustment is no longer sufficient. In addition, the gap maintenance system has a high complexity and a relatively high weight, which in addition to the manufacturing and maintenance costs and the probability of failure of the entire gap maintenance system is increased.
Aufgabe der vorliegenden Erfindung ist es daher ein Spaltkontrollsystem der eingangs genannten Art zu schaffen, welches auf konstruktiv einfache Weise eine Kompensierung möglichst vieler Einflussgrößen und damit eine zuverlässige und betriebssichere Einstellbarkeit des Laufspalts unter verschiedenen Betriebszuständen der zugeordneten Strömungsmaschine ermöglicht. Eine weitere Aufgabe besteht darin, eine Strömungsmaschine mit einem derartigen Spaltkontrollsystem sowie ein entsprechendes Verfahren zum Einstellen eines Laufspalts einer Strömungsmaschine zu schaffen.Object of the present invention is therefore to provide a gap control system of the type mentioned, which allows a structurally simple way a compensation of as many influencing factors and thus reliable and reliable adjustability of the running gap under different operating conditions of the associated turbomachine. Another object is to provide a turbomachine with such a gap control system and a corresponding method for adjusting a running gap of a turbomachine.
Die Aufgaben werden erfindungsgemäß durch ein Spaltkontrollsystem mit den Merkmalen des Patentanspruchs 1, durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 11 sowie durch ein Verfahren zum Einstellen eines Laufspalts gemäß Patentanspruch 15 gelöst. Vorteilhafte Ausgestaltungen mit zweckmäßigen Weiterbildungen der Erfindung sind in den jeweiligen Unteransprüchen angegeben, wobei vorteilhafte Ausgestaltungen des Spaltkontrollsystems als vorteilhafte Ausgestaltungen der Strömungsmaschine bzw. des Verfahrens und umgekehrt anzusehen sind.The objects are achieved by a gap control system with the features of claim 1, by a turbomachine with the features of claim 11 and by a method for adjusting a running gap according to claim 15. Advantageous embodiments with expedient developments of the invention are specified in the respective subclaims, wherein advantageous embodiments of the gap control system are to be regarded as advantageous embodiments of the turbomachine or of the method and vice versa.
Ein Spaltkontrollsystem, welches auf konstruktiv einfache Weise eine Kompensierung möglichst vieler Einflussgrößen und damit eine zuverlässige und betriebssichere Einstellbarkeit des Laufspalts unter verschiedenen Betriebszuständen der zugeordneten Strömungsmaschine ermöglicht, ist erfindungsgemäß dadurch geschaffen, dass jedes Segment der Ummantelung mit wenigstens drei Verstelleinrichtungen des Spaltkontrollsystems gekoppelt ist. Die Verstelleinrichtungen können dabei grundsätzlich einzelne Elemente wie Verstellgetriebe, Aktuatoren, Steuerstangen und dergleichen oder beliebige Kombination dieser Elemente umfassen bzw. aus diesen bestehen. Hierdurch ist es im Unterschied zum Stand der Technik möglich, die Segmente betriebszustandsunabhängig auf eine Kreisbahn zu zwingen und somit eine stetige und konstante Krümmung der Segmente zu gewährleisten. Da die Segmente der Ummantelung auf einen bestimmten Durchmesser ausgelegt sind, können sich beim rein radialen Bewegen der Segmente - wie im Stand der Technik beschrieben - sichelförmige Laufspalte ergeben. Zudem muss bei instationären Betriebszuständen der Strömungsmaschine mit einem radialen Temperaturgradienten, der die Krümmung unkontrolliert verändern könnte, sowie mit Verformungen durch mechanische Beanspruchung (z.B. durch Gaslasten) gerechnet werden. Damit die Segmente betriebszustandsunabhängig die gewünschte konstante Krümmung aufweisen, wird jedes Segment mindestens an drei Umfangsstellen mit jeweils einer der Verstelleinrichtungen gekoppelt und kann somit einfach auf eine Kreisbahn mit dem aktuellen Rotordurchmesser zuzüglich des gewünschten Laufspalts gezwungen werden. In der Regel hat es sich dabei als vorteilhaft gezeigt, wenn die Verstelleinrichtungen gleichmäßig beabstandet voneinander angeordnet sind, um eine entsprechend gleichmäßige Kraftverteilung über das Segment und eine gute Einstellung der Kreisbogenform sicherzustellen. Der Laufspalt kann mit Hilfe des erfindungsgemäßen Spaltkontrollsystems unabhängig vom Betriebszustand der zugeordneten Strömungsmaschine optimal eingestellt werden, wodurch der Wirkungsgrad der Strömungsmaschine erhöht und deren Kraftstoffbedarf entsprechend gesenkt wird. Aufgrund des konstruktiv einfachen Aufbaus des erfindungsgemäßen Spaltkontrollsystems ergeben sich im Vergleich zu bekannten Spaltkontrollsystemen zudem erhebliche Kosten- und Gewichtseinsparungen sowie eine vorteilhaft gesteigerte Zuverlässigkeit und Wartungsfreundlichkeit. Das Spaltkontrollsystem eignet sich grundsätzlich sowohl für eine Einzelstufe als auch für mehrere Stufen einer Strömungsmaschine.A gap control system which enables a compensation of as many influencing variables as possible and thus a reliable and reliable adjustability of the running gap under different operating conditions of the associated turbomachine is inventively created in that each segment of the jacket is coupled to at least three adjustment of the gap control system. The adjusting devices can basically individual elements such as adjusting, actuators, control rods and the like or include or consist of any combination of these elements. This makes it possible, in contrast to the prior art, to force the segments operating state independently on a circular path and thus to ensure a steady and constant curvature of the segments. Since the segments of the sheath are designed for a certain diameter, crescent-shaped running gaps can result in the purely radial movement of the segments, as described in the prior art. In addition, in unsteady operating states of the turbomachine with a radial temperature gradient, which could change the curvature uncontrolled, as well as with deformations due to mechanical stress (eg by gas loads) can be expected. In order for the segments to have the desired constant curvature independently of the operating state, each segment is coupled to at least three circumferential locations with one of the adjusting devices and can thus be easily forced onto a circular path with the current rotor diameter plus the desired running gap. In general, it has been found to be advantageous if the adjusting devices are arranged uniformly spaced from each other to ensure a correspondingly uniform force distribution over the segment and a good setting of the circular arc shape. The running gap can be adjusted optimally with the help of the gap control system according to the invention, regardless of the operating state of the associated turbomachine, whereby the efficiency of the turbomachine is increased and their fuel consumption is reduced accordingly. Due to the structurally simple construction of the gap control system according to the invention also result in comparison to known gap control systems also significant cost and weight savings and advantageously increased reliability and ease of maintenance. The gap control system is basically suitable both for a single stage and for several stages of a turbomachine.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass zwei Verstelleinrichtungen an entgegengesetzten Randbereichen ihres zugeordneten Segments angeordnet sind und/oder eine Verstelleinrichtung in der Mitte ihres zugeordneten Segments angeordnet ist. Indem zwei Verstelleinrichtungen an den Segmenträndern des Segments angreifen, kann die gewünschte Kreissegmentbahn unter Einhaltung der erforderlichen Tangentenbedingungen unter allen Betriebsbedingungen besonders zuverlässig eingehalten werden. Indem eine Verstelleinrichtung in der Mitte ihres zugeordneten Segments angeordnet ist kann alternativ oder zusätzlich ebenfalls eine vorteilhafte Krafteinleitung in das Segment erzielt werden. Eine betriebszustandsunabhängige Erzeugung der konstanten, kreisbahnförmigen Krümmung des Segments ist somit besonders einfach zu verwirklichen.In an advantageous embodiment of the invention it is provided that two adjusting devices are arranged on opposite edge regions of their associated segment and / or an adjusting device is arranged in the middle of its associated segment. By two adjusting devices acting on the segment edges of the segment, the desired circular segment track, while maintaining the required tangent conditions under all operating conditions especially be reliably adhered to. By an adjusting device is arranged in the middle of its associated segment can alternatively or additionally also an advantageous force introduction into the segment can be achieved. An operating state-independent generation of the constant, circular path-shaped curvature of the segment is thus particularly easy to implement.
Eine besonders gewichts- und bauraumsparende Anordnung ist in weiterer Ausgestaltung dadurch gegeben, dass wenigstens zwei benachbarte Segmente mit einer gemeinsamen Verstelleinrichtung gekoppelt sind. Auf diese Weise werden zudem eine hohe Dichtigkeit der Ummantelung und ein entsprechend hoher Wirkungsgrad der Strömungsmaschine sichergestellt. Durch eine Kopplung mittels der Verstelleinrichtung können benachbarte Randbereiche zweier Segmente vorteilhaft gemeinsam radial bewegt werden. Auf diese Weise wird ein stetiger Übergang vom einen Segment zum benachbarten Segment sichergestellt, so dass das Entstehen sichelförmiger Laufspalte besonders zuverlässig verhindert wird. Zudem wird hierdurch auch an der Verbindungsstelle zwischen den Segmenten und der Verstelleinrichtung eine hohe Spielfreiheit erreicht. Vorteilhafterweise kann vorgesehen sein, dass alle benachbarten Segmente jeweils mit einer oder mehreren gemeinsamen Verstelleinrichtungen gekoppelt sind, um eine optimierte Anordnung zu erhalten.A particularly weight and space-saving arrangement is given in another embodiment in that at least two adjacent segments are coupled to a common adjusting device. In this way, a high tightness of the casing and a correspondingly high efficiency of the turbomachine are also ensured. By means of a coupling by means of the adjusting device, adjacent edge regions of two segments can advantageously be moved radially together. In this way, a steady transition from one segment to the adjacent segment is ensured, so that the emergence of crescent-shaped running gaps is particularly reliably prevented. In addition, a high backlash is thereby achieved at the junction between the segments and the adjustment. Advantageously, it can be provided that all adjacent segments are each coupled to one or more common adjustment devices in order to obtain an optimized arrangement.
In einer vorteilhaften Ausgestaltung der Erfindung ist ein um den Rotor anordenbares Verstellelement vorgesehen ist, welches mit wenigstens einer Verstelleinrichtung gekoppelt und zum Betätigen der Verstelleinrichtung relativ zu dieser bewegbar ist. Hierdurch ist eine konstruktiv einfache, kostengünstige und bauraumsparende Anordnung des Verstellelements im Bereich des Rotors bzw. der Ummantelung ermöglicht. Zudem können beim Bewegen bzw. Verschwenken des Verstellelements auftretende Kräfte gut verteilt werden, wodurch die mechanische Stabilität und Lebensdauer des Verstellelements entsprechend verlängert wird. Das Verstellelement kann dabei vorzugsweise zumindest im Wesentlichen als Ring ausgebildet sein.In an advantageous embodiment of the invention, an adjusting element which can be arranged around the rotor is provided, which is coupled to at least one adjusting device and is movable relative thereto for actuating the adjusting device. This allows a structurally simple, cost-effective and space-saving arrangement of the adjusting element in the region of the rotor or the sheathing. In addition, forces occurring when moving or pivoting of the adjustment can be well distributed, whereby the mechanical stability and life of the adjustment is extended accordingly. The adjusting element may preferably be formed at least substantially as a ring.
Weitere Vorteile ergeben sich, indem das Verstellelement mehrere Teilabschnitte umfasst, die vorzugsweise gelenkig miteinander verbunden sind. Hierdurch besitzt das Verstellelement zusätzliche Bewegungsfreiheitsgrade, so dass eine zusätzlich verbesserte Einstellbarkeit des Laufspalts beim Verschwenken des Verstellelements ermöglicht ist. So kann beispielsweise durch ein Verknicken des Verstellelements, d.h. durch ein relatives Bewegen der Teilabschnitte zueinander, eine Ovalisierung der Ummantelung aufgrund von Manöverlasten und Druckkräften besonders einfach ausgeglichen werden.Further advantages result from the adjusting element comprising a plurality of subsections which are preferably connected to one another in an articulated manner. This has the Adjustment additional freedom of movement, so that an additional improved adjustability of the running gap is made possible during pivoting of the adjusting element. Thus, for example, by a buckling of the adjustment, ie by a relative movement of the sections to each other, a ovalization of the shell due to maneuvering and compressive forces are particularly easy to compensate.
Weitere Vorteile ergeben sich, wenn das Verstellelement zum Einstellen des Laufspalts axial bezüglich der Drehachse des Rotors verschiebbar und/oder gegenüber dem Rotor verschwenkbar ist. Im Unterschied zum Stand der Technik ermöglicht das erfindungsgemäße Spaltkontrollsystem durch axiales Bewegen des Verstellelements eine über den Umfang des Rotors gleichmäßige Bewegung der Segmente und eine entsprechend gleichmäßige Veränderung des Laufspalts. Alternativ oder zusätzlich kann durch Verschwenken bzw. Verkippen des Verstellelements gegenüber der Drehachse des Rotors eine über den Umfang des Rotors ungleichmäßige Bewegung der Segmente erzeugt werden, so dass auch Ovalisierung der Ummantelung aufgrund von Manöverlasten und Druckkräften sowie ein etwaiger Versatz zwischen der Drehachse des Rotors und der Mittelachse der Ummantelung problemlos berücksichtigt werden können.Further advantages result if the adjusting element for adjusting the running gap is axially displaceable relative to the axis of rotation of the rotor and / or is pivotable relative to the rotor. In contrast to the prior art, the gap control system according to the invention makes it possible, by moving the adjusting element axially, to move the segments uniformly over the circumference of the rotor and to achieve a correspondingly uniform change of the running gap. Alternatively or additionally, by pivoting or tilting the adjusting element relative to the axis of rotation of the rotor, a non-uniform movement of the segments over the circumference of the rotor can be generated, so that ovalization of the casing due to maneuvering and pressure forces and any offset between the axis of rotation of the rotor and the center axis of the sheath can be considered easily.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens eine der Verstelleinrichtungen ausgebildet ist, eine zumindest überwiegend axiale Bewegung des Verstellelements in eine zumindest überwiegend radiale Bewegung des zugeordneten Segments der Ummantelung umzuwandeln. Mit Hilfe der Verstelleinrichtung können somit große Bewegungen des Verstellelements vorteilhaft in kleine Bewegungen des zugeordneten Segments und umgekehrt umgewandelt werden, wodurch eine besonders präzise Einstellbarkeit des Laufspalts gegeben ist. Vorzugsweise ist vorgesehen, dass alle Verstelleinrichtungen derartig ausgebildet sind.In a further advantageous embodiment of the invention, it is provided that at least one of the adjusting devices is designed to convert an at least predominantly axial movement of the adjusting element into an at least predominantly radial movement of the associated segment of the casing. With the aid of the adjusting device, large movements of the adjusting element can thus advantageously be converted into small movements of the associated segment and vice versa, whereby a particularly precise adjustability of the running gap is provided. It is preferably provided that all adjusting devices are designed in this way.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens eine Verstelleinrichtung an einem Traggehäuse festgelegt ist. Hierdurch ergibt sich eine besonders stabile und betriebssichere Anordnung der Verstelleinrichtung. Das Traggehäuse kann dabei beispielsweise als Außengehäuse der Strömungsmaschine ausgebildet sein oder innerhalb eines separaten Außengehäuses anordenbar sein.In a further advantageous embodiment of the invention it is provided that at least one adjusting device is fixed to a support housing. This results in a particularly stable and reliable arrangement of the adjustment. The support housing may be formed, for example, as an outer housing of the turbomachine or be arrangeable within a separate outer housing.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass das Traggehäuse ringförmig ausgebildet ist und/oder außenumfänglich der Ummantelung und/oder konzentrisch zur Drehachse des Rotors anordenbar ist. Hierdurch können die mechanischen und konstruktiven Eigenschaften des Traggehäuses optimal an die Anforderungen der Strömungsmaschine angepasst werden.In a further advantageous embodiment of the invention it is provided that the support housing is annular and / or the outer circumference of the sheath and / or can be arranged concentrically to the axis of rotation of the rotor. As a result, the mechanical and structural properties of the support housing can be optimally adapted to the requirements of the turbomachine.
Weitere Vorteile ergeben sich, indem wenigstens ein Dichtelement vorgesehen ist, mittels welchem das Traggehäuse gegenüber der Ummantelung abzudichten ist. Hierdurch kann ein unerwünschtes Entweichen oder Rückströmen des Arbeitsmediums der Strömungsmaschine verhindert werden, wodurch ein entsprechend hoher Wirkungsgrad sichergestellt ist.Further advantages are obtained by providing at least one sealing element by means of which the support housing is to be sealed off from the shell. In this way, an undesirable escape or return flow of the working medium of the turbomachine can be prevented, whereby a correspondingly high efficiency is ensured.
In weiterer Ausgestaltung hat es sich als vorteilhaft gezeigt, wenn die Ummantelung wenigstens eine Leitschaufel umfasst und/oder vorzugsweise mittels einer Schubstange gegenüber dem Traggehäuse abgestützt ist. Bei bekannten Spaltkontrollsystemen und Strömungsmaschinen sind die Leitschaufeln üblicherweise am Traggehäuse befestigt, so dass auf den inneren Laufspalt kein Einfluss genommen werden kann. Wenn die Ummantelung die wenigstens eine Leitschaufel umfasst - z. B. indem die Leitschaufel an der Ummantelung festgelegt ist - kann die Leitschaufel demgegenüber vorteilhaft beim Einstellen des Laufspalts des Rotors mitbewegt werden, wodurch auch der innere Spalt der Strömungsmaschine einstellbar ist. Durch eine Anordnung der wenigstens einen Leitschaufel an der Ummantelung werden zudem während des Betriebs der Strömungsmaschine auftretende Kräfte besonders gut abgeleitet und verteilt. Vorteilhaft kann vorgesehen sein, dass die wenigstens eine Leitschaufel in Umfangs- und/oder Axialrichtung am Traggehäuse abgestützt ist.In a further embodiment, it has proven to be advantageous if the casing comprises at least one vane and / or is preferably supported by means of a push rod relative to the support housing. In known gap control systems and turbomachines, the guide vanes are usually fastened to the support housing, so that no influence can be exerted on the inner running gap. If the casing comprises the at least one vane - z. For example, by the vane is fixed to the casing - the vane can advantageously be moved when setting the running gap of the rotor, whereby the inner gap of the turbomachine is adjustable. By arranging the at least one guide vane on the casing, forces occurring during operation of the turbomachine are also dissipated and distributed particularly well. Advantageously, it can be provided that the at least one guide vane is supported in the circumferential and / or axial direction on the support housing.
Weitere Vorteile ergeben sich, indem wenigstens eine Sensoreinrichtung vorgesehen ist, mittels welcher eine Größe des Laufspalts ermittelbar ist. Dies erlaubt eine besonders einfache, schnelle und präzise Ermittlung der Größe des Laufspalts, wodurch eine entsprechend verbesserte Einstellung des Laufspalts ermöglicht ist. Die Sensoreinrichtung kann grundsätzlich nach unterschiedlichen physikalischen Prinzipen arbeiten, beispielsweise kapazitiv, induktiv, optisch, mit Mikrowellen oder mit Wirbelstrom.Further advantages result by providing at least one sensor device by means of which a size of the running gap can be determined. This allows a particularly simple, fast and precise determination of the size of the running gap, whereby a correspondingly improved adjustment of the running gap is made possible. The sensor device can fundamentally operate according to different physical principles, for example capacitive, inductive, optical, with microwaves or with eddy current.
Indem die Sensoreinrichtung im Bereich wenigstens einer Verstelleinrichtung angeordnet ist, ist eine zusätzliche Verbesserung der Einstellbarkeit des Laufspalts gegeben, da Bewegungen der Ummantelung bzw. des jeweiligen, der Verstelleinrichtung zugeordneten Segments mittels der Sensoreinrichtung nahe des Ankoppelbereichs der Verstelleinrichtung erfolgen können.By arranging the sensor device in the region of at least one adjusting device, an additional improvement of the adjustability of the running gap is provided since movements of the sheathing or of the respective segment associated with the adjusting device can take place by means of the sensor device close to the coupling region of the adjusting device.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung sind mehrere Sensoreinrichtung vorgesehen, welche, vorzugsweise gleichmäßig, voneinander beabstandet angeordnet sind und/oder außenumfänglich der Ummantelung anordenbar sind. Auf diese Weise ist es möglich, den Laufspalt mittels der mehreren Sensoreinrichtungen an verschiedenen Umfangspositionen des Rotors zu ermitteln. Der Laufspalt kann somit besonders präzise und ortsaufgelöst ermittelt werden, so dass gezielt entsprechend unterschiedliche Einstellbewegungen der Segmente ausführbar sind und ein gleichmäßiger Laufspalt erzeugbar ist.In a further advantageous embodiment of the invention, a plurality of sensor device are provided which, preferably uniformly, are arranged spaced from each other and / or the outer circumference of the sheathing can be arranged. In this way it is possible to determine the running gap by means of the plurality of sensor devices at different circumferential positions of the rotor. The running gap can thus be determined particularly precisely and spatially resolved, so that correspondingly different adjustment movements of the segments can be carried out and a uniform running gap can be generated.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens ein mit dem Verstellelement gekoppelter Aktuator vorgesehen ist, mittels welchem das Verstellelement axial bezüglich der Drehachse des Rotors verschiebbar oder gegenüber dem Rotor verschwenkbar ist. Mit Hilfe wenigstens eines Aktuators kann das Verstellelement besonders einfach und präzise bewegt werden. Zusammen mit den Verstelleinrichtungen können dabei vorteilhafterweise große Bewegungen des wenigstens einen Aktuators in kleine Bewegungen der Segmente oder umgekehrt umgewandelt werden. Der Aktuator kann grundsätzlich nach unterschiedlichen physikalischen Prinzipien funktionieren, beispielsweise hydraulisch, pneumatisch, elektrisch, piezoelektrisch oder magnetisch.In a further advantageous embodiment of the invention it is provided that at least one actuator coupled to the adjusting element is provided, by means of which the adjusting element is axially displaceable relative to the axis of rotation of the rotor or pivotable relative to the rotor. With the help of at least one actuator, the adjusting element can be moved in a particularly simple and precise manner. Along with the adjusting devices, large movements of the at least one actuator can advantageously be converted into small movements of the segments or vice versa. The actuator can basically function according to different physical principles, for example hydraulically, pneumatically, electrically, piezoelectrically or magnetically.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass der wenigstens eine Aktuator im Bereich wenigstens einer Verstelleinrichtung angeordnet ist. Hierdurch ist ein besonders kurzer Kraftübertragungsweg und eine entsprechend präzise Einstellbarkeit des Laufspalts gegeben. Alternativ oder zusätzlich kann vorgesehen sein, dass der Aktuator im Bereich einer Sensoreinrichtung angeordnet ist. Hierdurch wird aufgrund der geringen räumlichen Distanz zwischen der Sensoreinrichtung und dem Aktuator eine vereinfachte und besonders präzise Einstellbarkeit des Laufspalts sichergestellt.In a further advantageous embodiment of the invention, it is provided that the at least one actuator is arranged in the region of at least one adjusting device. As a result, a particularly short power transmission path and a correspondingly precise Adjustability of the running gap given. Alternatively or additionally, it can be provided that the actuator is arranged in the region of a sensor device. As a result, a simplified and particularly precise adjustability of the running gap is ensured due to the small spatial distance between the sensor device and the actuator.
Weitere Vorteile ergeben sich, indem mehrere Aktuatoren vorgesehen sind, welche, vorzugsweise gleichmäßig, voneinander beabstandet angeordnet sind und/oder außenumfänglich der Ummantelung anordenbar sind. Mit Hilfe mehrerer Aktuatoren an verschiedenen Umfangspositionen kann das Verstellelement besonders einfach axial bewegt oder verschwenkt werden, wodurch gezielt gleiche oder unterschiedliche Hubbewegungen der Segmente zum Einstellen des Laufspalts ausgeführt werden können. Indem die Aktuatoren im Bereich jeweils zugeordneter Sensoreinrichtungen angeordnet sind, können weiterhin etwaige gegenseitige Beeinflussungen mehrerer Aktuatoren und Sensoreinrichtungen vorteilhaft unterdrückt bzw. verunmöglicht werden.Further advantages result from the provision of a plurality of actuators which, preferably uniformly, are arranged at a distance from one another and / or can be arranged on the outer circumference of the sheathing. With the aid of a plurality of actuators at different circumferential positions, the adjusting element can be moved or swiveled in a particularly simple manner, as a result of which identical or different lifting movements of the segments for setting the running gap can be carried out in a targeted manner. By arranging the actuators in the region of respectively associated sensor devices, furthermore, any mutual influences of a plurality of actuators and sensor devices can be advantageously suppressed or rendered impossible.
Eine weitere Verbesserung der Einstellbarkeit des Laufspalts ist in weiterer Ausgestaltung dadurch gegeben, dass wenigstens eine Steuer- und/oder Regeleinheit vorgesehen ist, welche mit wenigstens einer Sensoreinrichtung und wenigstens einem Aktuator gekoppelt ist und ausgelegt ist, den wenigstens einen Aktuator in Abhängigkeit der mittels der wenigstens einen Sensoreinrichtung ermittelten Größe des Laufspalts zu steuern bzw. zu regeln.A further improvement of the adjustability of the nip is given in a further embodiment in that at least one control and / or regulating unit is provided, which is coupled to at least one sensor device and at least one actuator and is designed to at least one actuator in dependence of the To control or regulate at least one sensor device determined size of the running gap.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens zwei Verstelleinrichtungen axial bezüglich der Drehachse des Rotors angeordnet und gemeinsam mittels des Verstellelements betätigbar sind. Da die Rotoren mehrerer Stufen einer als Hochdruckverdichter ausgebildeten Strömungsmaschine ein ähnliches zeitliches Dehnungsverhalten zeigen - speziell wenn die Wärmeausdehnungskoeffizienten der verwendeten Werkstoffe ähnlich sind -, können hierdurch die Laufspalte mehrerer Stufen mit der gleichen Bewegung des Verstellelements eingestellt werden. Dabei kann gegebenenfalls vorgesehen sein, dass - beispielsweise durch unterschiedliche Hebellängen an den Verstelleinrichtungen - unterschiedliche Hubbewegungen an den Segmenten der mehrteiligen Ummantelung verschiedener Stufen erzielbar ist. Zudem kann bei Bedarf an jeder Stufe eine unterschiedliche Laufspaltgröße erzeugt werden.In a further advantageous embodiment of the invention it is provided that at least two adjusting devices are arranged axially with respect to the axis of rotation of the rotor and actuated jointly by means of the adjusting element. Since the rotors of several stages of a turbomachine designed as a high-pressure compressor exhibit a similar expansion behavior over time - especially if the coefficients of thermal expansion of the materials used are similar - then the running gaps of several stages can be adjusted with the same movement of the adjusting element. It may optionally be provided that - for example, by different lever lengths on the adjustment - different Hubbewegungen on the segments of the multi-part casing of different levels can be achieved. In addition, if required, a different gap size can be generated at each stage.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens eine Verstelleinrichtung einen Betätigungshebel und/oder ein Drucklager und/oder ein Kugelumlaufgewinde und/oder einen Spindeltrieb und/oder eine Exzenterwelle und/oder eine Biegefeder und/oder ein Federelement und/oder einen Kniehebel und/oder eine Rasterung umfasst. Auf diese Weise kann besonders einfach eine variable Anbindung an das Verstellelement und eine spielfreie Kraftübertragung vom Verstellelement auf die Verstelleinrichtung sichergestellt werden. Dies ermöglicht in weiterer Folge eine ebensolche spielfreie und gegebenenfalls gerasterte Bewegung des jeweils zugeordneten Segments. Zudem ermöglicht die wenigstens eine Verstelleinrichtung hierdurch auf konstruktiv einfache Weise, dass eine zumindest überwiegend axiale Bewegung des Verstellelements in eine kleinere radiale Bewegung des Segments der Ummantelung umgesetzt wird.In a further advantageous embodiment of the invention it is provided that at least one adjusting an actuating lever and / or a thrust bearing and / or a ball screw and / or a spindle drive and / or an eccentric shaft and / or a bending spring and / or a spring element and / or a Knee lever and / or a grid includes. In this way, it is particularly easy to ensure a variable connection to the adjusting element and a play-free power transmission from the adjusting element to the adjusting device. This subsequently enables a likewise play-free and optionally rastered movement of the respectively assigned segment. In addition, the at least one adjusting device thereby makes it possible, in a structurally simple way, for an at least predominantly axial movement of the adjusting element to be converted into a smaller radial movement of the segment of the sheathing.
Weitere Vorteile ergeben sich, indem wenigstens eine Verstelleinrichtung ein Dichtelement umfasst, welches vorzugsweise als Spannband und/oder Balgdichtung und/oder Kolbenring und/oder C-Dichtung ausgebildet ist. Mit Hilfe eines derartigen Dichtelements kann einerseits die erforderliche Bewegungsmöglichkeit, beispielsweise eine Hubbewegung oder thermische Differenzdehnung, bereitgestellt werden, andererseits können zugleich Räume mit unterschiedlichen Drücken gegeneinander abgedichtet werden.Further advantages result from at least one adjusting device comprising a sealing element, which is preferably designed as a clamping band and / or bellows seal and / or piston ring and / or C-seal. With the help of such a sealing element, on the one hand, the required movement possibility, for example, a lifting movement or thermal expansion difference can be provided, on the other hand, at the same time rooms with different pressures can be sealed against each other.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens eine Verstelleinrichtung einen mit zumindest einem Segment gekoppelten Zugbolzen und einen mit dem zumindest einen Segment gekoppelten Druckbolzen umfasst, wobei der Zugbolzen und der Druckbolzen relativ zueinander bewegbar und gegeneinander kraftbeaufschlagt sind. Hierdurch wird vorteilhaft erreicht, dass die gesamte Verstelleinrichtung in sich vorgespannt und damit spielfrei ist, so dass eine besonders präzise Spalteinstellung realisierbar ist. Die Kraftbeaufschlagung zwischen Zug- und Druckbolzen kann beispielsweise mit Hilfe eines Federelements bewerkstelligt sein, wobei grundsätzlich beliebige Federbauformen wie Schraubenfedern, Tellerfederpackete oder dergleichen vorgesehen sein können.In a further advantageous embodiment of the invention, it is provided that at least one adjusting device comprises a tension bolt coupled to at least one segment and a pressure bolt coupled to the at least one segment, wherein the tension bolt and the pressure bolt are movable relative to each other and subjected to force. In this way, it is advantageously achieved that the entire adjusting device is prestressed in itself and thus free of play, so that a particularly precise gap adjustment can be realized. The application of force between train and Pressure pin can be accomplished, for example, with the aid of a spring element, in principle, any desired spring designs such as coil springs, cup spring pack or the like can be provided.
Ein weiterer Aspekt der Erfindung betrifft eine Strömungsmaschine, insbesondere eine Gasturbine, mit einem Rotorschaufeln umfassenden Rotor, einer diesen zumindest abschnittsweise umgebenden, wenigstens zwei Segmente umfassenden Ummantelung, und einem Spaltkontrollsystem, mittels welchem ein Laufspalt zwischen dem Rotor und der Ummantelung einstellbar ist. Um auf konstruktiv einfache Weise eine Kompensierung möglichst vieler Einflussgrößen und damit eine zuverlässige und betriebssichere Einstellbarkeit des Laufspalts unter verschiedenen Betriebszuständen der Strömungsmaschine zu ermöglichen, ist erfindungsgemäß vorgesehen, dass das Spaltkontrollsystem gemäß einem der vorhergehenden Ausführungsbeispiele ausgebildet ist. Die sich hieraus ergebenden Vorteile sind aus den entsprechenden Beschreibungen zu entnehmen und als Vorteile der Strömungsmaschine anzusehen.Another aspect of the invention relates to a turbomachine, in particular a gas turbine rotor having a rotor blades, at least partially surrounding it, at least two segments comprising sheath, and a gap control system by means of which a running gap between the rotor and the sheath is adjustable. In order to enable a compensation of as many influencing variables as possible in a structurally simple manner and thus a reliable and reliable adjustment of the running gap under different operating conditions of the turbomachine, it is provided according to the invention that the gap control system is designed according to one of the preceding embodiments. The resulting advantages can be taken from the corresponding descriptions and regarded as advantages of the turbomachine.
In weiterer Ausgestaltung ist vorgesehen, dass das Spaltkontrollsystem in einem Gehäuse aufgenommen ist und/oder zumindest einen Teil des Gehäuses bildet. Die Aufnahme in einem Gehäuse der Strömungsmaschine erlaubt eine mechanisch stabile, betriebssichere und bauraumsparende Anordnung des Spaltkontrollsystems. Alternativ oder zusätzlich kann dabei vorgesehen sein, dass das Spaltkontrollsystem selbst zumindest einen Teil des Gehäuses bildet. Hierdurch werden aufgrund von Synergieeffekten erhebliche Kosten- und Gewichtssenkungen erzielt.In a further embodiment, it is provided that the gap control system is accommodated in a housing and / or forms at least a part of the housing. The inclusion in a housing of the turbomachine allows a mechanically stable, reliable and space-saving arrangement of the gap control system. Alternatively or additionally, it may be provided that the gap control system itself forms at least a part of the housing. As a result, significant cost and weight reductions are achieved due to synergy effects.
Weitere Vorteile ergeben sich, indem die Ummantelung wenigstens eine Leitschaufel umfasst. Wenn die wenigstens eine Leitschaufel an der Ummantelung bzw. an einem Segment vorgesehen ist, werden vorteilhaft auch die Laufspalte an der Ringrauminnenkontur, das heißt dem Spalt zwischen dem Rotor und der wenigstens einen Leitschaufel, durch das Spaltkontrollsystem eingestellt. Die während des Betriebs der Strömungsmaschine von der wenigstens einen Leitschaufel erzeugten Kräfte wirken dann auf die Segmente.Further advantages result from the casing comprising at least one vane. If the at least one guide vane is provided on the casing or on a segment, advantageously also the running gaps on the annular space inner contour, that is the gap between the rotor and the at least one vane, are set by the gap control system. The forces generated by the at least one vane during operation of the turbomachine then act on the segments.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die wenigstens zwei Segmente der Ummantelung, vorzugsweise mittels wenigstens einer Verstelleinrichtung des Spaltkontrollsystems, miteinander gekoppelt sind. Auf diese Weise werden eine hohe Dichtigkeit der Ummantelung und ein entsprechend hoher Wirkungsgrad der Strömungsmaschine sichergestellt. Durch eine Kopplung mittels wenigstens einer gemeinsamen Verstelleinrichtung können benachbarte Bereiche zweier Segmente vorteilhaft gemeinsam radial bewegt werden. Auf diese Weise wird zudem ein stetiger Übergang von einem Segment zum benachbarten Segment sichergestellt, so dass das Entstehen sichelförmiger Laufspalte besonders zuverlässig verhindert wird. Zudem wird hierdurch auch an der Verbindungsstelle zwischen den Segmenten und der Verstelleinrichtung eine hohe Spielfreiheit erreicht.In a further advantageous embodiment of the invention, it is provided that the at least two segments of the casing, preferably by means of at least one adjustment of the gap control system, are coupled together. In this way, a high tightness of the casing and a correspondingly high efficiency of the turbomachine are ensured. By means of a coupling by means of at least one common adjusting device, adjacent regions of two segments can advantageously be moved radially together. In this way, moreover, a steady transition from one segment to the adjacent segment is ensured so that the emergence of crescent-shaped running gaps is particularly reliably prevented. In addition, a high backlash is thereby achieved at the junction between the segments and the adjustment.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens ein Segment ein Versteifungselement umfasst, mittels welchem eine Krümmung des Segments in Abhängigkeit der Größe des Laufspalts einstellbar ist. Mit Hilfe eines derartigen Versteifungselements kann die Steifigkeitsverteilung des Segments der Ummantelung so gewählt werden, dass unter allen Betriebzuständen der Strömungsmaschine eine konstante Krümmung erzeugbar ist. Damit wird bei der Einstellung der Radialposition des Segments zumindest nahezu eine ideale Kreisform beibehalten. Das Versteifungselement kann dabei als Rippe mit variabler radialer Bauhöhe oder durch Rippen mit abnehmender Breite zu den Segmenträndern hin ausgebildet sein, wodurch die Steifigkeitsverteilung konstruktiv einfach und kostengünstig an das jeweilige Anforderungsprofil der Strömungsmaschine anpassbar ist.In a further advantageous embodiment of the invention, it is provided that at least one segment comprises a stiffening element, by means of which a curvature of the segment is adjustable as a function of the size of the running gap. With the aid of such a stiffening element, the stiffness distribution of the segment of the casing can be selected such that a constant curvature can be generated under all operating conditions of the turbomachine. Thus, when setting the radial position of the segment is maintained at least almost an ideal circular shape. The stiffening element can be designed as a rib with variable radial height or by ribs with decreasing width to the segment edges out, whereby the stiffness distribution is structurally simple and inexpensive adaptable to the respective requirement profile of the turbomachine.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass das Spaltkontrollsystem im Bereich einer Niederdruckverdichterstufe und/oder einer Hochdruckverdichterstufe und/oder einer Niederdruckturbinenstufe und/oder einer Hochdruckturbinenstufe der Strömungsmaschine angeordnet ist. Eine derartige Anordnung erlaubt eine besonders variable Ausgestaltung der Strömungsmaschine sowie einen besonders hohen, zumindest weitgehend betriebzustandsunabhängigen Wirkungsgrad.In a further advantageous embodiment of the invention, it is provided that the gap control system is arranged in the region of a low-pressure compressor stage and / or a high-pressure compressor stage and / or a low-pressure turbine stage and / or a high-pressure turbine stage of the turbomachine. Such an arrangement allows a particularly variable embodiment of the turbomachine and a particularly high, at least largely operating state independent efficiency.
Weitere Vorteile ergeben sich, indem die Ummantelung zwei als Halbringe ausgebildete Segmente und/oder höchstens acht, besonders bevorzugt höchstens sechs Segmente umfasst. Auf diese Weise wird im Gegensatz zum Stand der Technik die Anzahl der Bauteile und dadurch der potenziellen Leckagestellen klein gehalten. Neben einer Verringerung der Herstellungskosten der Strömungsmaschine wird hierdurch auch die Montage- und Wartungsfreundlichkeit erheblich verbessert.Further advantages result from the sheath comprising two segments formed as half-rings and / or at most eight, more preferably at most six segments. In this way, in contrast to the prior art, the number of components and thus the potential leakage points is kept small. In addition to a reduction in the manufacturing cost of the turbomachine and thus the ease of assembly and maintenance is considerably improved.
In weiterer Ausgestaltung ist vorgesehen, dass jedes Segment der Ummantelung mit wenigstens drei voneinander beabstandeten Verstelleinrichtungen des Spaltkontrollsystems gekoppelt ist. Hierdurch wird die Darstellung einer kontanten Krümmung jedes Segments besonders zuverlässig sichergestellt. Dabei kann vorgesehen sein, dass die Einstellbarkeit einer konstanten Krümmung durch eine entsprechende geometrische Gestaltung und/oder eine Steifigkeitsverteilung der Segmente gefördert wird. Hierzu kann beispielsweise eine Querschnittskontur jedes Segments so gewählt sein, dass die zweite Ableitung der Biegelinie einen konstanten Wert ergibt und dementsprechend unter allen Betriebszuständen der Strömungsmaschine eine konstante Krümmung erzeugbar ist.In a further embodiment, it is provided that each segment of the casing is coupled to at least three spaced adjustment of the gap control system. As a result, the representation of a contant curvature of each segment is ensured particularly reliable. It can be provided that the adjustability of a constant curvature is promoted by a corresponding geometric design and / or a stiffness distribution of the segments. For this purpose, for example, a cross-sectional contour of each segment can be chosen so that the second derivative of the bending line results in a constant value and, accordingly, a constant curvature can be generated under all operating conditions of the turbomachine.
Weitere Vorteile ergeben sich, indem mehrere Ummantelungen unter Ausbildung mehrerer Laufspalte entlang der Drehachse des Rotors angeordnet und die Laufspalte mittels des Spaltkontrollsystems zwischen dem Rotor und den Ummantelungen gemeinsam einstellbar sind. Hierdurch können die Laufspalte mehrerer Stufen der Strömungsmaschine vorteilhaft gemeinsam mittels des Spaltkontrollsystems eingestellt werden, wodurch signifikante Kosten- und Gewichtseinsparungen gegeben sind.Further advantages result from the fact that several casings are arranged along the axis of rotation of the rotor with the formation of a plurality of flow gaps and the running gaps are jointly adjustable by means of the gap control system between the rotor and the casings. As a result, the running gaps of several stages of the turbomachine can advantageously be set jointly by means of the gap control system, which results in significant cost and weight savings.
Ein weiterer Aspekt der Erfindung betrifft ein Verfahren zum Einstellen eines Laufspalts zwischen einem Rotorschaufeln umfassenden Rotor einer Strömungsmaschine, insbesondere einer Gasturbine, und einer diesen zumindest abschnittsweise umgebenden, wenigstens zwei Segmente umfassenden Ummantelung. Um eine Kompensierung möglichst vieler Einflussgrößen und damit eine zuverlässige und betriebssichere Einstellbarkeit des Laufspalts unter verschiedenen Betriebszuständen der Strömungsmaschine zu ermöglichen, umfasst das Verfahren erfindungsgemäß zumindest die Schritte Ermitteln einer Größe des Laufspalts mittels wenigstens einer Sensoreinrichtung und Übermitteln der Größe an eine Steuer- und/oder Regeleinheit, Steuern bzw. Regeln wenigstens eines Aktuators mittels der Steuer- und/oder Regeleinheit in Abhängigkeit der ermittelten Größe des Laufspalts, axiales Verschieben und/oder Verschwenken bezüglich einer Drehachse des Rotors eines um den Rotor angeordneten Verstellelements mittels des wenigstens einen Aktuators, Betätigen wenigstens einer Verstelleinrichtung mittels des Verstellelements und radiales Bewegen bezüglich der Drehachse des Rotors wenigstens eines Segments der Ummantelung mittels der wenigstens einen Verstelleinrichtung. Die sich hieraus ergebenden Vorteile sind bereits aus den vorhergehenden Beschreibungen des Spaltkontrollsystems bzw. der Strömungsmaschine zu entnehmen Dabei kann vorgesehen sein, dass eine Strömungsmaschine bzw. ein Spaltkontrollsystem gemäß einem der vorhergehenden Ausführungsbeispiele verwendet wird.Another aspect of the invention relates to a method for adjusting a running gap between a rotor comprising a rotor blades of a turbomachine, in particular a gas turbine, and a surrounding this at least partially surrounding, at least two segments comprising sheath. In order to enable a compensation of as many influencing variables as possible and thus a reliable and reliable adjustability of the running gap under different operating conditions of the turbomachine, the method comprises according to the invention at least the steps of determining a size of the running gap by means of at least one Sensor device and transmitting the size of a control and / or regulating unit, controlling or regulating at least one actuator by means of the control and / or regulating unit in dependence of the determined size of the running gap, axial displacement and / or pivoting with respect to a rotational axis of the rotor of order the adjusting element arranged by means of the at least one actuator, actuation of at least one adjusting device by means of the adjusting element and radial movement relative to the axis of rotation of the rotor of at least one segment of the casing by means of the at least one adjusting device. The resulting advantages can already be seen from the preceding descriptions of the gap control system or the turbomachine. It can be provided that a turbomachine or a gap control system according to one of the preceding embodiments is used.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Größe des Laufspalts im Fall einer fehlerhaften Sensoreinrichtung mittels der Steuer- und/oder Regeleinheit anhand der übermittelten Größe einer weiteren Sensoreinrichtung ermittelt und der wenigstens eine Aktuator in Abhängigkeit der ermittelten Größe gesteuert bzw. geregelt wird. Hierdurch kann durch eine entsprechende Steuer- bzw. Regellogik eine erhöhte Ausfallsicherheit erzielt werden, indem der wenigstens eine Aktuator in Abhängigkeit der Messsignale der weiteren, intakten Sensoreinrichtung gesteuert wird.In an advantageous embodiment of the invention, it is provided that, in the case of a faulty sensor device, the size of the running gap is determined by means of the control and / or regulating unit on the basis of the transmitted size of a further sensor device and the at least one actuator is controlled or regulated as a function of the determined variable , As a result, an increased reliability can be achieved by a corresponding control or regulating logic by controlling the at least one actuator as a function of the measuring signals of the further, intact sensor device.
Die vorstehend in der Beschreibung genannten Merkmale und Merkmalskombinationen sowie die nachfolgend in den Ausführungsbeispielen genannten Merkmale und Merkmalskombinationen sind nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen oder in Alleinstellung verwendbar, ohne den Rahmen der Erfindung zu verlassen. Weitere Vorteile, Merkmale und Einzelheiten der Erfindung ergeben sich anhand der nachfolgenden Beschreibung von Ausführungsbeispielen sowie anhand der Zeichnungen, in welchen gleiche oder funktionsgleiche Elemente mit identischen Bezugszeichen versehen sind. Dabei zeigen:
- Fig. 1
- ein schematisches Liniendiagramm einer zeit- und lastabhängigen Radiusänderung eines Rotors und einer diesen umgebenden Ummantelung einer Strömungsmaschine;
- Fig. 2
- eine schematische Perspektivansicht eines Spaltkontrollsystems gemäß einem ersten Ausführungsbeispiel;
- Fig. 3
- eine schematische Schnittansicht des in
Fig. 2 gezeigten Spaltkontrollsystems, wobei neben einer Durchmesseränderung und einem Mittelachsenversatz zusätzlich eine Ovalisierung der Ummantelung auftritt; - Fig. 4
- eine schematische Perspektivansicht dreier Segmente der in
Fig. 2 gezeigten Ummantelung, wobei jedes Segment mit mehreren Verstelleinrichtungen des Spaltkontrollsystems gekoppelt ist; - Fig. 5
- mehrere Ausführungsbeispiele von mit Versteifungselementen versehenen Segmenten der Ummantelung;
- Fig. 6
- eine schematische Perspektivansicht eines mehrere Leitschaufeln umfassenden Segments, welches mittels einer Schubstange gegenüber einem Traggehäuse abgestützt ist;
- Fig. 7
- ein Ausführungsbeispiel der Verstelleinrichtung in schematischer Perspektiv- und Seitenansicht;
- Fig. 8
- ein weiteres Ausführungsbeispiel der Verstelleinrichtung in schematischer Perspektiv- und Seitenansicht;
- Fig. 9
- eine schematische Perspektivansicht des Spaltkontrollsystems gemäß einem zweiten Ausführungsbeispiel;
- Fig. 10
- eine schematische und ausschnittsweise seitliche Schnittansicht einer mit dem in
Fig. 9 gezeigten Spaltkontrollsystem versehenen Strömungsmaschine; - Fig. 11
- eine schematische und teilgeschnittene Perspektivansicht einer in
Fig. 9 gezeigten Verstelleinrichtung; und - Fig. 12
- eine schematische seitliche Schnittansicht der Verstelleinrichtung gemäß einem weiteren Ausführungsbeispiel.
- Fig. 1
- a schematic line diagram of a time and load-dependent radius change of a rotor and a surrounding casing of a turbomachine;
- Fig. 2
- a schematic perspective view of a gap control system according to a first embodiment;
- Fig. 3
- a schematic sectional view of the in
Fig. 2 shown gap control system, wherein in addition to a change in diameter and a central axis offset additionally ovalization of the sheath occurs; - Fig. 4
- a schematic perspective view of three segments of in
Fig. 2 Sheath shown, wherein each segment is coupled to a plurality of adjusting devices of the gap control system; - Fig. 5
- several embodiments of provided with stiffening elements segments of the casing;
- Fig. 6
- a schematic perspective view of a plurality of vanes comprising segment which is supported by a push rod relative to a support housing;
- Fig. 7
- an embodiment of the adjustment in a schematic perspective and side view;
- Fig. 8
- a further embodiment of the adjusting device in a schematic perspective and side view;
- Fig. 9
- a schematic perspective view of the gap control system according to a second embodiment;
- Fig. 10
- a schematic and partial sectional side view of a with the in
Fig. 9 shown gap control system provided turbomachine; - Fig. 11
- a schematic and partially sectioned perspective view of an in
Fig. 9 shown adjusting device; and - Fig. 12
- a schematic sectional side view of the adjusting device according to another embodiment.
Das Spaltkontrollsystem umfasst weiterhin vier mit dem Verstellelement 22 gekoppelte Aktuatoren 28a-d, mittels welchem das Verstellelement 22 axial bezüglich der Drehachse D des Rotors 12 verschiebbar oder gegenüber dem Rotor 12 verschwenkbar ist. Die Aktuatoren 28a-d sind dabei gleichmäßig voneinander beabstandet außenumfänglich der Ummantelung 18 sowie jeweils im Bereich einer Verstelleinrichtung 20 angeordnet. Das Spaltkontrollsystem weist Steuer- und/oder Regeleinheit 30 auf, welche mit den Sensoreinrichtungen 26a-d und den Aktuatoren 28a-d gekoppelt ist. Die Steuer- und/oder Regeleinheit 30 ist ausgelegt, die Aktuatoren 28a-d in Abhängigkeit der mittels der Sensoreinrichtungen 26a-d ermittelten Größe Δr des Laufspalts L zu steuern bzw. zu regeln. Die von den Sensoreinrichtungen 26a-d gelieferten Steuersignale werden hierzu in der Steuer- und/oder Regeleinheit 30 verarbeitet.The gap control system further comprises four
Von der Steuer- und/oder Regeleinheit 30 erhält der jeweilige, der betreffenden Sensoreinrichtung 26a-d zugeordnete Aktuator 26a-d im Normalfall ein Signal, das Verstellelement solange axial zu bewegen, bis durch die betreffende Sensoreinrichtung 26a-d die optimale Größe Δropt des Laufspalts L ermittelt werden kann. Das Gleiche geschieht an den anderen Sensorpositionen. Dadurch wird es möglich, an verschiedenen Umfangspositionen unterschiedliche Hubbewegungen der Segmente 16a-d auszuführen. Die Sensoreinrichtungen 26a-d können nach verschieden physikalischen Prinzipen arbeiten, beispielsweise kapazitiv, induktiv, optisch, mit Mikrowellen oder mit Wirbelstrom. Gleiches gilt für die Aktuatoren 28a-d, die beispielsweise hydraulisch, pneumatisch, elektrisch, piezoelektrisch oder magnetisch betreibbar sein können.From the control and / or regulating
Im Fehlerfall, z.B. beim Ausfall einer Sensoreinrichtung 26a-d, kann über eine entsprechende Fehlerlogik durch die vorzugsweise redundant ausgebildete Steuer- und/oder Regeleinheit 30 derjenige Aktuator 26a-d, dessen normalerweise zugeordnete Sensoreinrichtung 26a-d ausgefallen ist, dennoch angesteuert werden. Hierzu kann beispielsweise aus den Signalen der verbliebenen funktionsfähigen Sensoreinrichtung 26a-d ein entsprechendes Steuersignal abgeleitet werden.In case of error, e.g. If a
Bei einer über den Umfang gleichmäßigen Änderung des Laufspalts wird das Verstellelement 22 von allen Aktuatoren 28a-d axial bezüglich der Drehachse D des Rotors 12 verschoben. Bei einem Versatz der Mittelachse M des Traggehäuses 24 gegenüber der Drehachse D wird das Verstellelement 22 hingegen an den einzelnen Aktuatorpositionen unterschiedlich in axialer Richtung bewegt. Das Verstellelement 22 führt dadurch eine räumliche Schwenkbewegung gegenüber dem Rotor 12 bzw. seiner Drehachse D (Taumelbewegung) aus. Hierdurch kann ein konstanter Laufspalt L über den ganzen Umfang der Ummantelung 18 eingestellt werden. Ein besonderer Vorteil der Verstelleinrichtungen 20 liegt dabei darin, dass sie vergleichsweise große Bewegungen der Aktuatoren 28a-d in vergleichsweise kleine Bewegungen der Segmente 16a-d umwandeln können, wodurch der Laufspalt L besonders präzise einstellbar ist.In a uniform over the circumference change of the running gap, the adjusting
Grundsätzlich gilt, dass bei einer Rotation des Rotors 12 ein Punkt auf einer Spitze einer Rotorschaufel 10 eine ideale Kreisbahn beschreibt. Ein Kreis ist eindeutig bestimmt, wenn drei Raumpunkte bekannt sind, die auf unterschiedlichen Umfangspositionen in der Kreisebene liegen. Wenn man zunächst den Fall einer Ovalisierung der Ummantelung 18 vernachlässigt, genügen insgesamt drei Sensoreinrichtungen 26 und drei Aktuatoren 28, die mit einem einteiligen Verstellelement 22 verbunden sind, um in unterschiedlichen Betriebszuständen der Strömungsmaschine einen über den Umfang der Ummantelung 18 konstanten Laufspalt L einzustellen.In principle, during a rotation of the
Zum Einstellen eines konstanten Laufspalts L umfasst das bereits in
Die Segmente 16a-d sind in radialer Richtung mit ihren jeweils benachbarten Segmenten 16 an den Segmenträndern formschlüssig verbunden. Der Formschluss wird durch einen Zugbolzen 31 und eine federbelastete Druckplatte 33 der Verstelleinrichtung 20 erzeugt. Damit wird auch an der Verbindungsstelle der Segmente 16a-d mit den jeweiligen Verstelleinrichtungen 20 Spielfreiheit erreicht. In Umfangsrichtung sind die Segmente 16a-d zueinander verschiebbar, was einerseits wegen der im Betrieb auftretenden unterschiedlichen Temperaturen zwischen den Segmenten 16a-d und dem Traggehäuse 24 und anderseits aufgrund der Möglichkeit die Segmente 16a-d radial zu verschieben notwendig ist (eine radiale Verschiebung aller Segmente 16a-d um z.B. 0,5 mm ergibt eine Änderung der Umfangslänge von 3,14 mm). Zwischen den Angriffspunkten der Verstelleinrichtungen 20 an den Segmenten 16a-d ist die Steifigkeitsverteilung so gewählt, dass unter allen Betriebzuständen eine konstante Krümmung vorliegt.The
Ein weiteres Ausführungsbeispiel der Verstelleinrichtung 20 ist in schematischer Perspektiv- und Seitenansicht in
Jede Verstelleinrichtung 20 ist mit Dichtelementen 52 abgedichtet. Zwei Liner-Segmente 16a, 16b werden von einem Federelement 54 (z.B. Schraubenfeder, Tellerfederpacket etc.) über eine Druckhülse 80 und die Druckplatte 33 radial nach innen in Richtung Rotor 12 gedrückt. Damit kein Segment 16 in den Rotor 12 bewegt wird, kann jedes Segment 16 über ein Gewinde 58, welches im in
Das Gewinde 58 bietet in Kombination mit dem Drucklager 60 den Vorteil, dass die Verstelleinrichtung 20 einen geringen Verschleiß und eine geringe innere Reibung besitzt. Im Gegensatz zum aus der
In
In
Die in den Unterlagen angegebenen Parameterwerte zur Definition von Prozess- und Messbedingungen für die Charakterisierung von spezifischen Eigenschaften des Erfindungsgegenstands sind auch im Rahmen von Abweichungen - beispielsweise aufgrund von Messfehlern, Systemfehlern, Einwaagefehlern, DIN-Toleranzen und dergleichen - als vom Rahmen der Erfindung mitumfasst anzusehen.The parameter values given in the documents for the definition of process and measurement conditions for the characterization of specific properties of the subject invention are also within the scope of deviations - for example due to measurement errors, system errors, Einwaagefehlern, DIN tolerances and the like - as included in the scope of the invention ,
Claims (15)
- A clearance control system for adjusting a running clearance (L) between a rotor (12), comprising rotor blades (10), of a turbomachine (14), in particular a gas turbine, and a casing (18) that surrounds the rotor at least in sections and comprises at least two segments (16a-d), having at least one adjusting device (20) which can be coupled to at least one segment (16a-d) of the casing (18) and by means of which the at least one segment (16a-d) for the adjustment of the running clearance (L) can be moved radially in relation to a rotational axis (D) of the rotor (12), characterised in that each segment (16a-d) of the casing (18) is coupled to at least three of the adjusting devices (20) of the clearance control system.
- A clearance control system according to claim 1, characterised in that two adjusting devices (20) are arranged at opposite edge regions of their associated segment (16a-d), and/or one adjusting device (20) is arranged in the centre of its associated segment (16a-d).
- A clearance control system according to claim 1 or 2, characterised in that at least two adjacent segments (16a-d) are coupled to a common adjusting device (20).
- A clearance control system according to one of claims 1 to 3, characterised in that an adjusting element (22) is provided that can be arranged around the rotor (12), is coupled to at least one adjusting device (20) and, in order to actuate the adjusting device (20), can be moved relatively to it.
- A clearance control system according to claim 3, characterised in that the adjusting element (22) comprises a plurality of subsections (22a, 22b) which are preferably connected together in an articulated manner.
- A clearance control system according to claim 4 or 5, characterised in that in order to adjust the running clearance (L) the adjusting element (22) can be shifted axially in relation to the rotational axis (D) of the rotor (12) and/or can be pivoted with respect to the rotor (12).
- A clearance control system according to one of claims 1 to 6, characterised in that the casing (18) comprises at least one guide vane (34) and/or is supported with respect to a support housing (24) preferably by means of a thrust rod (36).
- A clearance control system according to one of claims 1 to 7, characterised in that at least one sensor device (26) is provided by means of which a magnitude (Δr) of the running clearance (L) can be determined.
- A clearance control system according to one of claims 4 to 8, characterised in that at least one actuator (28) is provided that is coupled to the adjusting element (22) and by means of which the adjusting element (22) can be shifted axially in relation to the rotational axis (D) of the rotor (12) or can be pivoted with respect to the rotor (12).
- A clearance control system according to claim 8 or 9, characterised in that at least one control and/or regulating unit (30) is provided which is coupled to at least one sensor device (26a-d) and at least one actuator (28a-d) and is designed to control or to regulate the at least one actuator (28a-d) as a function of the magnitude (Δr) of the running clearance (L) determined by means of the at least one sensor device (26a-d).
- A turbomachine (14), in particular a gas turbine, having a rotor (12) comprising rotor blades (10), a casing (18) surrounding the rotor at least in sections and comprising at least two segments (16a-d), and a clearance control system by means of which a running clearance (L) can be adjusted between the rotor (12) and the casing (18), characterised in that the clearance control system is formed in accordance with one of claims 1 to 10.
- A turbomachine (14) according to claim 11, characterised in that the clearance control system is arranged in the region of a low-pressure compressor stage and/or a high-pressure compressor stage and/or a low-pressure turbine stage and/or a high-pressure turbine stage of the turbomachine (14).
- A turbomachine (14) according to claim 11 or 12, characterised in that the casing (18) comprises two segments (16) formed as half-rings or at most eight, preferably at most six, segments (16).
- A turbomachine (14) according to one of claims 11 to 13, characterised in that a plurality of casings (18) are arranged along the rotational axis (D) of the rotor (12) with the formation of a plurality of running clearances (L), and the running clearances (L) can be adjusted jointly by means of the clearance control system between the rotor (12) and the casings (18).
- Method for adjusting a running clearance (L) between a rotor (12), comprising rotor blades (10), of a turbomachine (14), in particular a gas turbine, and a casing (18) that surrounds the rotor at least in sections and comprises at least two segments (16a-d), comprising the following steps:- determination of a magnitude (Δr) of the running clearance (L) by means of at least one sensor device (26a-d) and transmission of the magnitude (Δr) to a control and/or regulating unit (30);- control or regulation of at least one actuator (28a-d) by means of the control and/or regulating unit (30) as a function of the magnitude (Δr) of the running clearance (L) determined;- axial shifting and/or pivoting in relation to a rotational axis (D) of the rotor (12) of an adjusting element (22), arranged around the rotor (12), by means of the at least one actuator (28a-d); characterised by- actuation of at least one of three adjusting device (20), coupled to each segment (16a-d), by means of the adjusting element (22); and- radial movement in relation to the rotational axis (D) of the rotor (12) of at least one segment (16a-d) of the casing (18) by means of at least one of the three adjusting devices (20), and the magnitude (Δr) of the running clearance (L) is determined in the case of a defective sensor device (26a-d) by means of the control and/or regulating unit (30) on the basis of the transmitted magnitude (Δr) of a further sensor device (26a-d), and the at least one actuator (28a-d) is controlled or regulated as a function of the magnitude (Δr) hereby determined.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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DE102009023061A DE102009023061A1 (en) | 2009-05-28 | 2009-05-28 | Gap control system, turbomachine and method for adjusting a running gap between a rotor and a casing of a turbomachine |
PCT/DE2010/000570 WO2010136018A2 (en) | 2009-05-28 | 2010-05-19 | Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine |
Publications (2)
Publication Number | Publication Date |
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EP2435665A2 EP2435665A2 (en) | 2012-04-04 |
EP2435665B1 true EP2435665B1 (en) | 2013-02-13 |
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Application Number | Title | Priority Date | Filing Date |
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EP10730046A Active EP2435665B1 (en) | 2009-05-28 | 2010-05-19 | Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine |
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US (1) | US8678742B2 (en) |
EP (1) | EP2435665B1 (en) |
DE (1) | DE102009023061A1 (en) |
WO (1) | WO2010136018A2 (en) |
Families Citing this family (24)
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GB0910070D0 (en) * | 2009-06-12 | 2009-07-22 | Rolls Royce Plc | System and method for adjusting rotor-stator clearance |
ITMI20111430A1 (en) * | 2011-07-28 | 2013-01-29 | Ansaldo Energia Spa | PLANT FOR THE PRODUCTION OF ELECTRIC TURBINE ENERGY AND METHOD TO OPERATE THE PLANT |
US9039346B2 (en) | 2011-10-17 | 2015-05-26 | General Electric Company | Rotor support thermal control system |
US9228447B2 (en) | 2012-02-14 | 2016-01-05 | United Technologies Corporation | Adjustable blade outer air seal apparatus |
US9371738B2 (en) * | 2012-12-20 | 2016-06-21 | United Technologies Corporation | Variable outer air seal support |
US9957830B2 (en) | 2013-03-07 | 2018-05-01 | United Technologies Corporation | Hybrid passive and active tip clearance system |
US9976436B2 (en) * | 2013-03-28 | 2018-05-22 | United Technologies Corporation | Movable air seal for gas turbine engine |
EP2789809A1 (en) * | 2013-04-12 | 2014-10-15 | Alstom Technology Ltd | Method for automatic positioning of a gas turbine rotor |
WO2015067394A1 (en) * | 2013-11-06 | 2015-05-14 | Voith Patent Gmbh | Stator device for a turbomachine, in particular a water turbine |
US9593589B2 (en) * | 2014-02-28 | 2017-03-14 | General Electric Company | System and method for thrust bearing actuation to actively control clearance in a turbo machine |
US9784117B2 (en) | 2015-06-04 | 2017-10-10 | United Technologies Corporation | Turbine engine tip clearance control system with rocker arms |
US9752450B2 (en) | 2015-06-04 | 2017-09-05 | United Technologies Corporation | Turbine engine tip clearance control system with later translatable slide block |
ITUB20152155A1 (en) * | 2015-07-14 | 2017-01-14 | Nuovo Pignone Tecnologie Srl | Method for stabilizing the transverse oscillations of a rotor. |
US10822972B2 (en) | 2015-12-08 | 2020-11-03 | General Electric Company | Compliant shroud for gas turbine engine clearance control |
US10458429B2 (en) | 2016-05-26 | 2019-10-29 | Rolls-Royce Corporation | Impeller shroud with slidable coupling for clearance control in a centrifugal compressor |
US10851712B2 (en) | 2017-06-27 | 2020-12-01 | General Electric Company | Clearance control device |
US10704408B2 (en) * | 2018-05-03 | 2020-07-07 | Rolls-Royce North American Technologies Inc. | Dual response blade track system |
US11156455B2 (en) | 2018-09-26 | 2021-10-26 | General Electric Company | System and method for measuring clearance gaps between rotating and stationary components of a turbomachine |
US11008882B2 (en) * | 2019-04-18 | 2021-05-18 | Rolls-Royce North American Technologies Inc. | Blade tip clearance assembly |
KR102316629B1 (en) * | 2020-06-23 | 2021-10-25 | 두산중공업 주식회사 | Turbine blade tip clearance control apparatus and gas turbine comprising the same |
CN113090339B (en) * | 2021-04-08 | 2022-08-02 | 沈阳航空航天大学 | Active clearance control brush type sealing structure based on magnetic attraction effect |
CN113107615B (en) * | 2021-04-08 | 2022-08-26 | 沈阳航空航天大学 | Active clearance control labyrinth seal structure based on eccentric damping action |
US12012859B2 (en) * | 2022-07-11 | 2024-06-18 | General Electric Company | Variable flowpath casings for blade tip clearance control |
US12006829B1 (en) | 2023-02-16 | 2024-06-11 | General Electric Company | Seal member support system for a gas turbine engine |
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CH524087A (en) * | 1970-11-18 | 1972-06-15 | Bbc Brown Boveri & Cie | Cylinder ring seal |
US4332523A (en) * | 1979-05-25 | 1982-06-01 | Teledyne Industries, Inc. | Turbine shroud assembly |
GB2050524B (en) * | 1979-06-06 | 1982-10-20 | Rolls Royce | Turbine stator shroud assembly |
US4329114A (en) | 1979-07-25 | 1982-05-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Active clearance control system for a turbomachine |
JPS5726211A (en) * | 1980-07-23 | 1982-02-12 | Hitachi Ltd | Rotary blade top edge clearance adjusting device for hydraulic turbine |
GB2099515B (en) | 1981-05-29 | 1984-09-19 | Rolls Royce | Shroud clearance control in a gas turbine engine |
GB2108591A (en) | 1981-11-03 | 1983-05-18 | Rolls Royce | Casing of a gas turbine engine rotor |
FR2591674B1 (en) * | 1985-12-18 | 1988-02-19 | Snecma | DEVICE FOR ADJUSTING THE RADIAL CLEARANCES BETWEEN ROTOR AND STATOR OF A COMPRESSOR |
US5096375A (en) | 1989-09-08 | 1992-03-17 | General Electric Company | Radial adjustment mechanism for blade tip clearance control apparatus |
US5104287A (en) * | 1989-09-08 | 1992-04-14 | General Electric Company | Blade tip clearance control apparatus for a gas turbine engine |
US5054997A (en) * | 1989-11-22 | 1991-10-08 | General Electric Company | Blade tip clearance control apparatus using bellcrank mechanism |
US5049033A (en) * | 1990-02-20 | 1991-09-17 | General Electric Company | Blade tip clearance control apparatus using cam-actuated shroud segment positioning mechanism |
DE102004037955A1 (en) * | 2004-08-05 | 2006-03-16 | Mtu Aero Engines Gmbh | Turbomachine, in particular gas turbine |
EP1655455A1 (en) * | 2004-11-05 | 2006-05-10 | Siemens Aktiengesellschaft | Turbomachine having a guide vane support with adjustable radial clearance |
GB0513654D0 (en) * | 2005-07-02 | 2005-08-10 | Rolls Royce Plc | Variable displacement turbine liner |
GB2440744B (en) * | 2006-08-09 | 2008-09-10 | Rolls Royce Plc | A blade clearance arrangement |
US8292571B2 (en) | 2007-10-12 | 2012-10-23 | General Electric Company | Apparatus and method for clearance control of turbine blade tip |
-
2009
- 2009-05-28 DE DE102009023061A patent/DE102009023061A1/en not_active Withdrawn
-
2010
- 2010-05-19 WO PCT/DE2010/000570 patent/WO2010136018A2/en active Application Filing
- 2010-05-19 EP EP10730046A patent/EP2435665B1/en active Active
- 2010-05-19 US US13/266,268 patent/US8678742B2/en active Active
Also Published As
Publication number | Publication date |
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EP2435665A2 (en) | 2012-04-04 |
US20120063884A1 (en) | 2012-03-15 |
WO2010136018A2 (en) | 2010-12-02 |
DE102009023061A1 (en) | 2010-12-02 |
US8678742B2 (en) | 2014-03-25 |
WO2010136018A3 (en) | 2011-02-24 |
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