EP2435665A2 - Systeme de controle de jeu, turbomachine et procede de reglage d'un jeu fonctionnel entre un rotor et une enveloppe d'une turbomachine - Google Patents

Systeme de controle de jeu, turbomachine et procede de reglage d'un jeu fonctionnel entre un rotor et une enveloppe d'une turbomachine

Info

Publication number
EP2435665A2
EP2435665A2 EP10730046A EP10730046A EP2435665A2 EP 2435665 A2 EP2435665 A2 EP 2435665A2 EP 10730046 A EP10730046 A EP 10730046A EP 10730046 A EP10730046 A EP 10730046A EP 2435665 A2 EP2435665 A2 EP 2435665A2
Authority
EP
European Patent Office
Prior art keywords
control system
rotor
adjusting
gap
turbomachine
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.)
Granted
Application number
EP10730046A
Other languages
German (de)
English (en)
Other versions
EP2435665B1 (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 GmbH
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 GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2435665A2 publication Critical patent/EP2435665A2/fr
Application granted granted Critical
Publication of EP2435665B1 publication Critical patent/EP2435665B1/fr
Active 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

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, in the preamble of
  • Claim 23 specified type and a method for adjusting a running gap between a rotor blades comprehensive rotor of a turbomachine, in particular a gas turbine, and a surrounding this at least partially surrounding, 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 shows a schematic line diagram of a time- and load-dependent gap change between a rotor disk and a jacket of a turbomachine surrounding it, 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 ⁇ i 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 op t.
  • the optimum size ⁇ r op t 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 ).
  • the running gap L reaches in the area B 4 its maximum value ⁇ r ma ⁇ - eg mm - over which the required adjustment range of the sheathing or the segments of the sheath marked with arrow I is defined.
  • the running gap L becomes smaller again and reaches its minimum value ⁇ r min , since the jacket cools faster than the rotor.
  • the turbomachine cools down, the initial size ⁇ ri of the nip L returns after a certain time. From Fig. 1 it can be seen that the required Verstellhub the Sheath is relatively small and less than 1.0 mm. To achieve a significant improvement, therefore, gap control systems with adjusting devices are required, which work as precisely as possible.
  • thermally active gap control systems in which the running gap is optimized by targeted cooling or heating of the relevant components.
  • Examples of this are the gap control system of the CFM56 engine family, in which the rotor temperature is controlled, or known from US 4,329,114 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. 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 shroud and on eccentricities, such as occur in Manöverlasten, but these gap control systems can not react or only very limited ,
  • 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.
  • a turbomachine with a segmented casing is also shown, wherein 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.
  • US Pat. No. 5,104,287 describes a gap control system for a segmented jacket of a rotor of a turbine rotor comprising rotor blades.
  • 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.
  • Between the segments and a support housing of the sheath wave-shaped flat springs are arranged, which the segments radially inwardly, d. H. 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.
  • 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 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, according to the invention created by each segment of the shell with at least three adjustment of the
  • 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, can be in the purely radial
  • 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.
  • 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. In addition, this is also at the junction between the
  • Segments and the adjustment reaches a high backlash.
  • 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.
  • Turbomachine can be prevented, whereby a correspondingly high efficiency is ensured.
  • 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. If the casing comprises the at least one vane - z. B. by the vane is fixed to the casing - the guide vane contrast advantageous in the
  • the inner gap of the turbomachine is adjustable.
  • the at least one guide vane is supported in the circumferential and / or axial direction on the support housing.
  • 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.
  • the sensor device is arranged in the region of at least one adjusting device, an additional improvement of the adjustability of the running gap is given because
  • Movements of the casing or of the respective, the adjusting device associated segment can be done by means of the sensor device near the Ankoppelschens the adjustment.
  • Sensor device provided, which are preferably spaced uniformly spaced from each other and / or the outer circumference of the sheath are 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 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.
  • 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. 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.
  • 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.
  • 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 cost-adaptive to the respective requirements Prof ⁇ l the turbomachine adaptable.
  • 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.
  • 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.
  • 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, among all
  • 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 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.
  • Gap control system according to one of the preceding Ausf ⁇ ihrungsbeilly is used.
  • the size of the running gap in the case of a faulty sensor device by means of the control and / or
  • Control unit determined based on the transmitted size of a further sensor device and the at least one actuator is controlled or regulated as a function of the determined size.
  • 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.
  • Fig. 1 is a schematic line diagram of a time and load-dependent
  • FIG. 2 shows a schematic perspective view of a gap control system according to a first exemplary embodiment
  • Fig. 3 is a schematic sectional view of that shown in Fig. 2
  • Gap control system wherein in addition to a change in diameter and a central axis offset additionally an ovalization of the sheath occurs;
  • FIG. 4 is a schematic perspective view of three segments of that shown in FIG.
  • each segment is coupled to a plurality of adjusting devices of the gap control system
  • FIG. 5 several exemplary embodiments of provided with stiffening elements
  • FIG. 6 is a schematic perspective view of a segment comprising a plurality of guide vanes, which is supported by a push rod in relation to a support housing;
  • Fig. 7 shows an exemplary embodiment of the adjusting in a schematic
  • Fig. 8 shows a further exemplary embodiment of the adjusting in a schematic
  • FIG. 9 is a schematic perspective view of the gap control system according to a second exemplary embodiment; 10 shows a schematic and partially sectional side view of a turbomachine provided with the gap control system shown in FIG. 9; FIG.
  • Fig. 11 is a schematic and partially sectioned perspective view of an adjusting device shown in Fig. 9;
  • Fig. 12 is a schematic sectional side view of the adjusting device according to another exemplary embodiment.
  • FIG. 1 shows a schematic line diagram of a time- and load-dependent change in the radius of a rotor and a surrounding casing of a turbomachine surrounding it and has already been explained above. Regardless of the operating condition of the turbomachine always the optimum running gap size ⁇ r opt and thus
  • 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 nip L between a rotor 12 (see Fig. 3) comprising a rotor blades 10 (see Fig. 3) of a turbomachine 14 (see Fig. 10), in particular a gas turbine, and at least partially surrounding sheath 18.
  • the sheathing 18 above the rotor 12 it is necessary for the sheathing 18 above the rotor 12 to be able to adapt to the diameter or radius and position of the rotor 12 or its axis of rotation D at all times.
  • the sheath 18 in the present embodiment four segments 16a-d (liner), which at least largely
  • 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 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 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.
  • 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.
  • the sealing elements can be designed as sealing flakes (so-called “leaf seals”), whereby other types of seals, for example brush seals or C-rings, can 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 apart from each other on the outside 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 assigned to the relevant sensor device 26a-d normally receives a signal which
  • 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 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 gap control system shown in Fig. 2, wherein in addition to a change in the diameter ⁇ or 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 sheath 18 thus has in turn to a minimum diameter ⁇ m i n and a maximum diameter ⁇ max, whereby the running clearance L varies over the circumference and having different sizes .DELTA.R a- d.
  • the gap control system already explained in FIG. 2 comprises the four actuators 28a-d and the four sensor devices 26a-d.
  • Each of the actuators 28a-d moves the adjusting element 22 differently far along the axis of rotation D, whereby a pivoting movement is generated. This is made possible by the multi-part and articulated construction of the adjusting element 22.
  • a linear displacement of the adjusting element 22 along the central axis M or the axis of rotation D By a linear displacement of the adjusting element 22 along the central axis M or the axis of rotation D, a uniform change in the radius of the casing 18 can be achieved.
  • a center line offset can be compensated.
  • 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 In any position of the major axes H of the cross-sectional ellipses, the ovalization is only partially compensated.Although the ovalization is to be at least approximately completely compensated for any position of the cross-sectional ellipses, a further subdivision of the adjusting element 22 into three subsections or However, since the ovalization of the shroud 18 is normally small compared to the offset between the center axis M and the axis of rotation D, a gap control system with four actuators 28 has usually been found to be perfect Enough shown.
  • the gap control system 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 the sheath 18 shown in FIG. 2, each segment 16a-c being 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
  • each segment 16a-d is coupled at three circumferential points with an adjusting device 20 and through this to a
  • 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 different temperatures occurring between the segments 16a-d and the support housing 24 in the operation 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). Between the attack points of the
  • the stiffness distribution is selected so that there is a constant curvature under all operating conditions.
  • FIG. 5 shows several exemplary embodiments of segments 16 each provided with stiffening elements 32.
  • 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 indirectly by means of a hinged at their ends mounted push rod 36 relative to the support housing 24 (not shown) of the
  • 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 by a with the
  • Adjustment 22 coupled toggle mechanism 42 can be deformed.
  • 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 shown in schematic perspective and side view in Fig. 8.
  • 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 exemplary embodiment.
  • the basic structure is already out of the
  • 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 partially sectional side view of a multi-stage turbomachine 14 provided with the gap control system shown in FIG. 9.
  • the turbomachine 14 or the gap control system will be explained below in conjunction with FIGS. 11 and 12.
  • FIG. 11 shows a schematic and partially sectioned perspective view of an adjusting device 20 shown in FIG. 10, while FIG. 12 finally shows a schematic lateral sectional view of the adjusting device 20 according to a further exemplary embodiment.
  • the general structure of the turbomachine 14 is known from the prior art.
  • the three adjusting devices 20, which can be seen in FIG. 10, are arranged along the axis of rotation D of the rotor 12 and fixed on a supporting 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 embodiment shown in FIG. 11 as recirculating ball screw and in the embodiment shown in FIG 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 armature 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 draw bolt 31 by way of example Arrow XII is marked.
  • 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 in the present case are integrated in the adjusting device 20 and are arranged outside the outer housing 50 and thus 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.
  • an 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 exemplary 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.
  • a connection sleeve 82 is further recognizable.
  • 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 at the sliding points (arrow XII) between the 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.

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)

Abstract

L'invention concerne un système de contrôle de jeu permettant de régler un jeu fonctionnel (L) entre un rotor (12) à aubes (10) d'une turbomachine (14), en particulier d'une turbine à gaz, et une enveloppe (18) entourant au moins partiellement ledit rotor et pourvue d'au moins deux segments (16a-d). Le système de contrôle de jeu comprend au moins un dispositif d'ajustement (20), qui peut être accouplé à au moins un segment (16a-d) de l'enveloppe (18) et au moyen duquel le ou les segments (16a-d) peuvent être déplacés radialement par rapport à un axe de rotation (D) du rotor (12) pour permettre le réglage du jeu fonctionnel (L), chaque segment (16a-d) de l'enveloppe (18) étant accouplé à au moins trois dispositifs d'ajustement (20) du système de contrôle de jeu. L'invention concerne également une turbomachine (14), en particulier une turbine à gaz, ainsi qu'un procédé de réglage d'un jeu fonctionnel (L).
EP10730046A 2009-05-28 2010-05-19 Système de contrôle de jeu, turbomachine et procédé de réglage d'un jeu fonctionnel entre un rotor et une enveloppe d'une turbomachine Active EP2435665B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009023061A DE102009023061A1 (de) 2009-05-28 2009-05-28 Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
PCT/DE2010/000570 WO2010136018A2 (fr) 2009-05-28 2010-05-19 Système de contrôle de jeu, turbomachine et procédé de réglage d'un jeu fonctionnel entre un rotor et une enveloppe d'une turbomachine

Publications (2)

Publication Number Publication Date
EP2435665A2 true EP2435665A2 (fr) 2012-04-04
EP2435665B1 EP2435665B1 (fr) 2013-02-13

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EP10730046A Active EP2435665B1 (fr) 2009-05-28 2010-05-19 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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US (1) US8678742B2 (fr)
EP (1) EP2435665B1 (fr)
DE (1) DE102009023061A1 (fr)
WO (1) WO2010136018A2 (fr)

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Also Published As

Publication number Publication date
DE102009023061A1 (de) 2010-12-02
EP2435665B1 (fr) 2013-02-13
WO2010136018A3 (fr) 2011-02-24
WO2010136018A2 (fr) 2010-12-02
US20120063884A1 (en) 2012-03-15
US8678742B2 (en) 2014-03-25

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