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EP2435664B1 - Système de contrôle de jeu pour une turbomachine - Google Patents

Système de contrôle de jeu pour une turbomachine Download PDF

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Publication number
EP2435664B1
EP2435664B1 EP10730045.1A EP10730045A EP2435664B1 EP 2435664 B1 EP2435664 B1 EP 2435664B1 EP 10730045 A EP10730045 A EP 10730045A EP 2435664 B1 EP2435664 B1 EP 2435664B1
Authority
EP
European Patent Office
Prior art keywords
rotor
turbomachine
turbomachine according
segment
adjustment
Prior art date
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.)
Not-in-force
Application number
EP10730045.1A
Other languages
German (de)
English (en)
Other versions
EP2435664A2 (fr
Inventor
Hermann Klingels
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2435664A2 publication Critical patent/EP2435664A2/fr
Application granted granted Critical
Publication of EP2435664B1 publication Critical patent/EP2435664B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • the invention relates to a turbomachine for adjusting a running gap between a rotor blades comprising rotor blades.
  • 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 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 casing of a turbomachine, as typically occurs during operation of a known as high-pressure compressor, known from the prior art turbomachine for an engine of the class 30 klb.
  • 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.
  • 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 controlled. 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 casing as well as 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.
  • the gap control system With diameter changes of the rotor and the jacket, the gap control system thus provides comparatively good results.
  • 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.
  • 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 coupled segments of the casing stir out the same lifting movement.
  • a relatively large number of twelve or more segment groups is required.
  • 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.
  • each segment for adjusting the running gap by a gap control system is movable.
  • the segments are moved between wedge-shaped spring members, wherein a disc spring stack can move the segments radially outwardly with respect to the axis of rotation of the rotor and the gap control system can move the segments radially toward the rotor.
  • a high number of actuators and Sensor devices required, whereby the gap maintenance system is not only expensive and difficult, but also has a relatively high probability of failure.
  • the US 5,104,287 describes a gap maintenance system for a segmented casing of a rotor blades comprising a 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 screws of the gap holding system comprising threaded spindles.
  • the adjusting gear are coupled in pairs with a designed as a ring and concentrically arranged around the rotor adjusting.
  • the adjustment of the running gap is made by turning the ring, whose rotational movement is converted by the adjusting gear in a uniform radial movement of the segments away from the rotor.
  • Shaft-shaped flat springs are arranged between the segments and a supporting housing of the casing, which press the segments radially inward, that is to say 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 adjusting mechanism come into direct contact with the high rotor chamber temperatures during operation of the turbomachine.
  • the temperatures can be so high that the spring action of the flat springs is lost or the carrying capacity of the adjusting is no longer sufficient.
  • the gap maintenance system has a high complexity and a relatively high weight, which in addition to the manufacturing and maintenance costs, especially the default probability 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 in a structurally simple way compensating as many influencing factors and thus a reliable and reliable adjustability of the running gap under different operating conditions of the associated Turbomachine allows.
  • 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.
  • the invention relates to a turbomachine, in particular a gas turbine, comprising a rotor comprising rotor blades, a casing enclosing the same at least in sections, comprising at least two segments, and a gap control system by means of which a running gap between the rotor and the casing can be adjusted.
  • the gap control system which allows in a structurally simple way a compensation of as many influencing factors and thus a reliable and reliable adjustability of the running gap under different operating conditions of the associated turbomachine erfingdungsconce created by the adjusting element for adjusting the running gap axially relative to the axis of rotation of the rotor and slidably / or is pivotable relative to the rotor and that the at least one adjusting mechanism is adapted 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.
  • the gap control system makes it possible, on the one hand, to move the segments uniformly over the circumference of the rotor by axial movement of the adjusting element 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 produced, whereby ovalization of the casing due to maneuvering and compressive forces and any offset between the axis of rotation of the rotor and the Central axis of the sheath can be easily considered and compensated.
  • the adjusting element is at least substantially formed as a ring.
  • the adjusting element comprising a plurality of sub-sections, which are preferably connected to one another in an articulated manner.
  • the adjusting element has additional degrees of freedom of movement, so that an additionally improved adjustability of the running gap during pivoting of the adjusting element is made possible.
  • a buckling of the adjusting element i.
  • an ovalization of the shell due to maneuvers and compressive forces are particularly easy to compensate.
  • the gap control system comprises a support housing (24) and at least one adjusting gear is fixed to the 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 concentric with the axis of rotation of the rotor can be arranged.
  • 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 comprising the at least one vane-for example by the vane being fixed to the casing-the vane can advantageously be moved during the adjustment of the rotor's nip, whereby the internal gap of the turbomachine can also be adjusted.
  • the at least one guide vane is supported in the circumferential and / or axial direction on the support housing.
  • the at least one adjusting is supported by means of the push rod relative to the support housing.
  • the sensor device can basically operate according to different physical principles, for example capacitive, inductive, optical, with microwaves or with eddy current.
  • a plurality of sensor devices are provided which, preferably uniformly, are arranged at a distance from one another and / or can be arranged on the outer circumference of the sheathing.
  • the running gap can thus be determined in a particularly precise and spatially resolved manner, so that correspondingly different stroke movements of the segments can be executed 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.
  • the actuator can 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 variable transmission.
  • 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.
  • a plurality of adjusting gears are provided, which are arranged axially with respect to the axis of rotation of the rotor and together can be actuated by means of the adjusting element. Since the rotors of several stages of a turbomachine designed as a high-pressure compressor show a similar expansion behavior over time - especially if the coefficients of thermal expansion of the materials used are similar - running columns of several stages can be set with the same movement of the adjusting element. It may optionally be provided that - for example, by different lever lengths on the adjusting - different strokes on the segments of the multi-part casing of different levels can be achieved. In addition, if required, a different gap size can be created or set at each stage.
  • At least one adjusting gear coupled to the adjusting element actuating lever and / or a thrust bearing and / or a recirculating 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 toggle lever and / or a toggle pin which can be coupled to at least one segment of the casing and / or a grid.
  • a backlash-free power transmission from the adjusting element to the at least one adjusting mechanism can be ensured in a particularly simple manner, and a likewise backlash-free and optionally rastered movement of the respective segment can be generated.
  • the at least one adjusting mechanism thereby makes it possible, in a structurally simple way, to convert an at least predominantly axial movement of the adjusting element into a small radial movement of the segment of the casing.
  • At least one adjusting mechanism 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 gear coupled to at least one segment Draw bolt and a coupled to the at least one segment pressure pin comprises, wherein the tension bolt and the pressure pin are movable relative to each other and subjected to a force.
  • the application of force between the tension bolt and the pressure bolt can be generated, for example, with the aid of a spring element, with basically any desired spring designs, such as helical springs, cup spring packs or the like, being able to 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 comprises at least one vane. If the at least one vane is provided on the casing or on a segment, the running gaps on the casing are advantageously also provided Ring space inner contour, that is, the gap between the rotor and the at least one vane, 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 coupling by means of at least one adjusting gear adjacent regions of two segments can advantageously be moved radially together.
  • 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.
  • thereby a high backlash is achieved at the junction between the segments and the at least one adjusting.
  • At least one segment of the casing comprises a stiffening element, by means of which a curvature of the segment is adjustable in dependence on the size of the running gap.
  • a stiffening element by means of which a curvature of the segment is adjustable in dependence on the size of the running gap.
  • the gap control system 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 is arranged.
  • Such an arrangement allows a particularly variable embodiment of the turbomachine and a particularly high, at least largely wholesomesstandsunabphaserigigen efficiency.
  • 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 two and preferably three spaced-apart adjusting the gap control system. Since the segments are designed for a certain diameter, crescent-shaped running gaps can generally result from the radial movement of the segments due to the occurrence of curvatures. In addition, in unsteady operating states of the fluid machine with a radial temperature gradient, which could change the curvature uncontrolled, as well as with mechanical stress (for example, by gas loads) must be expected. In order for the segments to have the desired constant curvature independent of the operating state, each segment is coupled to at least two and preferably to three circumferential locations, each with one adjusting gear and thus forced to a circular path with the current rotor diameter plus the adjustable running gap. If a segment is coupled to only two variable speed drives, it has been found to be advantageous if the two variable speed drives engage the segment edges of the segment to force it to the desired circular segment path.
  • a cross-sectional contour of each segment can be selected so that the second derivative of the bending line results in a constant value and accordingly there is a constant curvature.
  • a further aspect 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 casing which surrounds the latter at least in sections, comprising at least two segments.
  • the method comprises at least the steps of determining a size of the running gap by means of at least one sensor device and transmitting the variable to a control and / or to compensate for as many influencing factors as possible and thus a reliable and reliable adjustment of the running gap under different operating conditions of the turbomachine Control unit, controlling or regulating at least one actuator by means of the control and / or regulating unit as a function of the determined size of the running gap, axial displacement and / or pivoting with respect to a rotational axis of the rotor of an adjusting element arranged around the rotor by means of the at least one actuator, actuating at least an adjusting mechanism 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 gear.
  • 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 as a function of the determined variable or is regulated.
  • 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 here comprises eight adjusting gear 20, which are each coupled to at least one segment 16 of the casing 18.
  • the segments 16a-d for adjusting the running gap can be moved radially relative to a rotational axis D of the rotor 12.
  • 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 gear 20 and can be moved axially relative to the axis of rotation D of the rotor 12 or pivoted relative to the rotor 12 for actuating the adjusting gear 20 and thus for adjusting the running gap L.
  • the adjusting gear 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 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 support housing 24 in the vicinity of each second adjusting gear 20, by means of which a size of the running gap L at different circumferential positions can be determined.
  • 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 arranged uniformly spaced from each other on the outer circumference of the casing 18 and in each case in the region of an adjusting gear 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 actuator 26a-d whose normally assigned sensor device 26a-d has failed, can nevertheless 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 to the individual Aktuatorpositioneri in the axial direction.
  • the adjusting element 22 thereby performs a spatial pivotal movement relative to the rotor 12 and its axis of rotation D (wobble). In this way, a constant running gap L over the entire circumference of the sheath 18 can be adjusted.
  • a particular advantage of the adjusting mechanism 20 lies in the fact that they can convert relatively 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 casing 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 which is constant over the circumference of the casing 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 can also be completely compensated by "bending" of the adjustment element 22, ie by relative pivoting of the sections 22a, 22b, when the articulated connection of the sections 22a, 22b of the adjustment 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 Verstellgetrieben 20 of the gap control system.
  • the segments 16a-c are usually made for a certain diameter. If the relatively large segments 16a-d simply shifted to a different radius, would arise due to their curvature, crescent-shaped running column L.
  • in unsteady operating conditions of the turbomachine with a radial temperature gradient which changes the curvature uncontrolled, as well as with mechanical stress (eg by gas loads) can be expected.
  • each segment 16a-d is coupled at three circumferential points with an adjusting gear 20 and forced by this on a circular path with the current rotor diameter plus the desired running gap L.
  • an adjusting 20 20 two segments 16 is assigned.
  • 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 20. This is achieved at the junction of the segments 16a-d with the respective adjustment gears 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 gear 20 simultaneously acts as a support element for the push rod 36, so that occurring forces are introduced into the support housing.
  • the LeitSufeln 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.
  • Fig. 7 shows an embodiment of the variable speed 20 in a schematic perspective and side view.
  • the adjusting mechanism 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 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.
  • variable speed transmission 20 is shown in schematic perspective and side view in FIG 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 each, via a Coupling rod 48 coupled to each other adjusting gears 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.
  • 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 cutaway perspective view of an in Fig. 10 shown adjusting gear 20, while in Fig. 12
  • a schematic side sectional view of the variable speed according to a further exemplary embodiment is shown.
  • the general structure of the turbomachine 14 is known from the prior art.
  • the three in Fig. 10 Recognizable adjusting gear 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 20 are controlled or regulated together.
  • the adjusting gears 20 are controlled or regulated individually or in groups.
  • the gap control system can in principle be arranged both in compressor and in turbine stages. Special benefits arise When the gap control system is arranged in the region of the rear stages of the turbomachine, because of the small blades, the ratio between running gap and blade size is particularly relevant.
  • Each adjusting gear 20 is sealed with sealing elements 52: Two liner segments 16a, 16b are pressed by a spring element 54 (eg helical spring, disc spring package, etc.) via a pressure sleeve 80 and the pressure plate 33 radially inwards in the direction of the rotor 12. 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 is designed as a movement thread, are moved radially away from the rotor 12. The power transmission takes place in each case via a thrust bearing 60 to an armature plate 62 and the tension bolt 31.
  • a spring element 54 eg helical spring, disc spring package, etc.
  • This tension bolt 31 is positively connected to the segment 16 or 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 described arrangement has the advantage that the entire adjusting mechanism 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 gear 20 has a low wear and a low internal friction.
  • the spring elements 54 are presently integrated in the adjusting 20 and outside of the outer housing 50 and thus arranged in the relatively cold region of the turbomachine 14. Between the outer housing 50 and the adjusting gear 20, and within the adjusting gear 20 different 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.
  • Fig. 12 is an actuating lever 66 of the adjusting 20 recognizable, which coupled on the one hand with the adjusting element 22 and on the other hand rotationally fixed to the Thread 58 is connected to convert the at least substantially axial movement of the adjusting element 22 in a smaller radial movement.
  • the adjusting mechanism 20 functions according to the embodiment shown in the manner of a spindle drive.
  • the adjusting mechanism 20 is fastened to the supporting housing 24 of the turbomachine by screwing, 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 via a 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 on the bolt part of the thread 58 supported.
  • 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 adjusting 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.
  • different sealing elements 52 are provided at the sliding points (arrow XII) between the adjusting gear 20 and housings (outer housing 50 and the support housing 24) and within the variable transmission 20 different sealing elements 52 (piston rings, C-rings, bellows, etc.) are provided.
  • the connecting sleeve 82, the thread 58 and the anchor plate 62 form a Verstellgetriebegephinuse 90 here.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (17)

  1. Turbomachine (14), en particulier turbine à gaz, équipée d'un rotor (10) comportant des aubes de rotor (12), une enveloppe (18) entourant ledit rotor au moins partiellement et comportant au moins deux segments (16a-d), et un système de commande d'écartement permettant de régler un écartement de passage (L) ménagé entre le rotor (12) et l'enveloppe (18), ladite turbomachine comprenant ;
    - au moins un mécanisme de réglage (20) qui peut être accouplé à au moins un segment (16a-d) de l'enveloppe (18) et au moyen duquel l'au moins un segment (16a-d) peut être déplacé radialement par rapport à un axe de rotation (D) du rotor (12) pour régler l'écartement de passage (L) ; et
    - un élément de réglage (22) qui peut être disposé autour du rotor (12), qui est accouplé d'au moins un mécanisme de réglage (20) et qui peut être déplacé par rapport au mécanisme de réglage (20) pour actionner celui-ci,
    l'élément de réglage (22) pouvant coulisser axialement par rapport à l'axe de rotation (D) du rotor (12) et/ou pivoter par rapport au rotor (12) pour régler l'écartement de passage (L) et l'au moins un mécanisme de réglage (20) étant configuré pour convertir un mouvement essentiellement axial de l'élément de réglage (22) en un mouvement essentiellement radial du segment (16a-d) associé de l'enveloppe (18), caractérisée en ce que l'élément de réglage (22) est conformé sensiblement en anneau.
  2. Turbomachine selon la revendication 1, caractérisée en ce que l'élément de réglage (22) comprend une pluralité de sections (22a, 22b) qui sont reliées entre elles de manière articulée.
  3. Turbomachine selon l'une des revendications 1 à 2, caractérisée en ce que le système de commande d'écartement comprend un boîtier de support (24) et au moins un mécanisme de réglage (20) est fixé au boîtier de support (24).
  4. Turbomachine selon la revendication 3, caractérisée en ce que le boîtier de support (24) aune conformation annulaire et/ou peut être disposé sur la circonférence extérieure de l'enveloppe (18) et/ou concentriquement à l'axe de rotation (D) du rotor (12).
  5. Turbomachine selon la revendication 3 ou 4, caractérisé en ce qu'il est prévu au moins un élément d'étanchéité (40) au moyen duquel le boîtier de support (24) peut être rendu étanche par rapport à l'enveloppe (18).
  6. Turbomachine selon l'une des revendications 3 à 5, caractérisée en ce que l'enveloppe (18) comprend au moins une aube directrice (34) et/ou est supporté au moyen d'une tige de poussée (36) par rapport au boîtier de support (24).
  7. Turbomachine selon l'une des revendications 1 à 6, caractérisée en ce qu'il est prévu au moins un dispositif de détection (26) permettant de déterminer la dimension (Δr) de l'écartement de passage (L)
  8. Turbomachine selon la revendication 7, caractérisée en ce que le dispositif de détection (26) est disposé dans la zone d'au moins un mécanisme de réglage (20).
  9. Turbomachine selon la revendication 7 ou 8, caractérisée en ce qu'il est prévu une pluralité de dispositifs de détection (26a-d) qui peuvent être disposés à une certaine distance, de préférence uniforme, les uns des autres et/ou qui peuvent être disposés sur la circonférence extérieure de l'enveloppe (18).
  10. Turbomachine selon l'une des revendications 1 à 9, caractérisée en ce qu'il est prévu au moins une actionneur (28) accouplé à l'élément de réglage (22) et permettant de faire coulisser l'élément de réglage (22) axialement par rapport à l'axe de rotation (D) du rotor (12) ou de le faire pivoter par rapport au rotor (12).
  11. Turbomachine selon la revendication 10, caractérisée en ce que l'actionneur (28) est disposé dans la zone d'au moins un mécanisme de réglage (20).
  12. Turbomachine selon la revendication 10 ou 11, caractérisée en ce qu'il est prévu une pluralité d'actionneurs (28a-d) qui sont disposés à une certaine distance, de préférence uniforme, les uns des autres et/ou peuvent être disposés sur la circonférence extérieure de l'enveloppe (18).
  13. Turbomachine selon l'une des revendications 7 à 9 et l'une des revendications 10 à 12, caractérisée en ce qu'il est prévu au moins une unité (30) de commande et/ou de régulation qui est accouplée à au moins un moyen de détection (26a-d) et au moins un actionneur (28a-d) et qui est adaptée pour commander ou réguler l'au moins un actionneur (28a-d) en fonction de la dimension (Δr) de l'écartement de passage (L) déterminée par l'au moins un dispositif de détection (26a-d).
  14. Turbomachine selon l'une des revendications 1 à 13, caractérisée en ce qu'il est prévu une pluralité de mécanismes de réglage (20) qui sont disposés axialement par rapport à l'axe de rotation (D) du rotor (12) et qui peuvent être actionnés ensemble au moyen de l'élément de réglage (22).
  15. Turbomachine selon l'une des revendications 1 à 14, caractérisée en ce qu'au moins un mécanisme de réglage (20) comprend un levier d'actionnement (66) accouplé à l'élément de réglage (22) et/ou un filetage (58) et/ou un palier de butée (60) et/ou un entraînement à broche et/ou un arbre d'excentrique (46) et/ou un ressort de flexion (38) et/ou un élément élastique (54) et/ou un levier à genouillère (42) et/ou un boulon à traction (31) pouvant être accouplé à au moins un segment (16a-d) de l'enveloppe (18) et/ou un crantage.
  16. Turbomachine selon l'une des revendications 1 à 15, caractérisée en ce qu'au moins un mécanisme de réglage (20) comprend un élément d'étanchéité (52) qui est réalisé sous la forme d'une bande de serrage en V et/ou d'une garniture d'étanchéité à soufflet et/ou d'un segment de piston et/ou d'une garniture d'étanchéité en C.
  17. Turbomachine selon l'une des revendications 1 à 16, caractérisée en ce qu'au moins un mécanisme de réglage (20) comprend un boulon de traction (31) accouplé à au moins un segment (16a, 16b) et un boulon à pression (80) accouplé à l'au moins un segment (16a, 16b), le boulon à traction (31) et le boulon à pression (80) étant mobiles l'un par rapport à l'autre et étant forcés l'un contre l'autre.
EP10730045.1A 2009-05-28 2010-05-18 Système de contrôle de jeu pour une turbomachine Not-in-force EP2435664B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009023062A DE102009023062A1 (de) 2009-05-28 2009-05-28 Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
PCT/DE2010/000560 WO2010136014A2 (fr) 2009-05-28 2010-05-18 Système de contrôle de jeu, turbomachine et procédé de réglage d'un jeu fonctionnel entre un rotor et une enveloppe d'une turbomachine

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EP2435664A2 EP2435664A2 (fr) 2012-04-04
EP2435664B1 true EP2435664B1 (fr) 2016-08-17

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EP (1) EP2435664B1 (fr)
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Also Published As

Publication number Publication date
EP2435664A2 (fr) 2012-04-04
US9068471B2 (en) 2015-06-30
WO2010136014A2 (fr) 2010-12-02
DE102009023062A1 (de) 2010-12-02
US20120057958A1 (en) 2012-03-08
WO2010136014A3 (fr) 2011-06-23

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