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
  • F05D2250/00—Geometry
  • F05D2250/60—Structure; Surface texture
  • F05D2250/61—Structure; Surface texture corrugated
• • 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
  • F05D2250/00—Geometry
  • F05D2250/60—Structure; Surface texture
  • F05D2250/61—Structure; Surface texture corrugated
  • F05D2250/611—Structure; Surface texture corrugated undulated

Definitions

• the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1 or 11.
• a turbomachine with a stator and a rotor wherein the rotor blades and the stator has a housing and vanes.
• the rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same.
• the radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining.
• the gap between the shroud of the housing and the radially outer end of the or each blade ring to provide a so-called Active Clearance Control can be adjusted or adjusted by means of adjusting devices in its gap, so to automatically influence the gap and to ensure an optimal gap position over all operating conditions.
• the radially inner housing wall or the outer ring is segmented in the circumferential direction, wherein preferably each segment is assigned a separate actuating device.
• the adjusting devices are preferably designed as electro-mechanical actuators.
• DE 101 17 231 Al discloses a turbomachine with a stator and a rotor, wherein the gap between radially outer ends of the blades and the radially inner housing wall by means of a pneumatic, so compressed air operated, actuator unit of a rotor gap control module can be adjusted.
• the pneumatic actuator unit of the rotor gap control module disclosed therein has an actuator chamber, a pressure chamber and the actuator chamber and the pressure chamber connecting valves, depending on the prevailing pressure in the actuator chamber sealing elements of the rotor gap control module are inflated so as to pneuma - Active Clearance Control tables to adjust or adjust the gap of the gap between radially outer ends of blades and the outer ring of the housing.
• the turbomachine according to DE 29 22 835 C2 has a stator and a rotor, wherein the gap between radially outer ends of the blades and an inner ring or shroud of a housing wall can be adjusted pneumatically.
• the shroud ring is connected via resilient side walls with a support ring, wherein the shroud, the support ring and the side walls form a bellows-like structure.
• the resilient side walls are curved several times.
• the side walls are according to DE 29 22 835 C2 thus seen in the axial direction sections inwardly into the cavity and in sections outwardly arched out of the cavity.
• the present invention is based on the problem to provide a novel turbomachine with a pneumatic Active Clearance Control.
• each wall connecting the shroud ring to the support ring is, as seen in the axial direction, curved inwardly only into the respective cavity.
• FIG. 1 shows a cross section through stator-side modules of a turbomachine according to the invention
• FIG. 2 shows a schematic representation of a bellows-type structure of the turbomachine according to FIG. 1;
• Fig. 3 is a schematic representation of an alternative bellows-like structure of a turbomachine.
• FIG. 1 shows a partial cross-section through a stator of a compressor 10 of a turbomachine, the stator comprising a housing 11 and a plurality of fixed guide vanes 12.
• the stator-side guide vanes 12 form so-called vane rings which, viewed in the axial direction, are arranged one behind the other.
• Fig. 1 a total of four fixed, stator-side vane rings 13, 14, 15 and 16 are shown.
• the compressor 10 comprises a rotor, not shown in Fig. 1, wherein the rotor of a plurality of axially arranged behind one another, not shown rotor disks is formed, each rotor disk in the circumferential direction next to each other several, also not shown blades carries.
• the rotor blades associated, circumferentially juxtaposed blades form so-called blade rings, wherein between each two adjacent Leitschaufelkränzen 13 and 14, 14 and 15 and 15 and 16 are each a non-illustrated blade ring is arranged.
• the housing 11 of the stator of the compressor 10 comprises a radially inner housing wall, wherein the radially inner housing wall in the region of each rotor-side, not shown in Fig. 1 blade ring forms a so-called inner ring or shroud 17 and surrounds the respective blade ring radially outward.
• the housing 11 further comprises a radially outer housing wall 18th
• each non-illustrated, rotor-side blade ring forms the radially inner housing wall in the region of each non-illustrated, rotor-side blade ring a so-called shroud ring 17 which surrounds the blade ring radially outward.
• shroud ring 17 which surrounds the blade ring radially outward.
• the present invention now relates to such details, with the aid of which radial gaps between radially outer ends of blade rings and the respective shroud 17 can be accurately maintained.
• the respective shroud 17, the support ring 20 and the between the respective shroud 17 and the respective support ring 20 extending, curved walls 19 each form a bellows-like structure 21, which has a cavity 22.
• the respective bellows-like structure 21 and thus the cavity 22 surrounds in the circumferential direction completely and thus closed the respective blade ring.
• the gap between the respective shroud 17 and the radially outer end of the respective blade ring is pneumatically adjustable.
• the respective radially inner shroud 17 can be pressed radially inward and the respective radially outer support ring 20 radially outward.
• an opposite deformation of the respective bellows-like structure 21 can be realized.
• the curved, resilient walls 19 of the bellows-like structures 21 seen in the axial direction are curved only inwardly into the respective cavity 22 inwardly.
• a relatively obtuse angle ⁇ of greater than 90 ° This will be described below with reference to FIG. 2, which shows a schematic representation of a bellows-like structure 21.
• FIG. 2 shows that the wall sections of the respective wall 19 enclose an obtuse angle ⁇ in the region of a vertex 29 of the curvature.
• curved walls 19 are superimposed at an increase in pressure in the corresponding cavity 22 of the respective bellows-like structure 21, two effects.
• the respective shroud 17 and the respective support ring 20 are pressed apart as viewed directly in the radial direction.
• this radial disengagement of the respective shroud 17 and support ring 20 is supported by a toggle-like effect of the curved walls 19 or at least not hindered.
• the curved walls 19 are exposed to essentially exclusively compressive forces.
• the respective bellows-like structure 21 has a greater radial extent than axial extent.
• the walls 19 of the respective bellows-type structure 21 have a greater radial extent than axial extent.
• each bellows-like structures 21 have an approximately constant wall thickness in the radial direction.
• the curved walls 19 seen in the radial direction have a variable wall thickness.
• each bellows-like structure 21 has a smaller wall thickness than the respective radially outer support ring 20.
• the support ring 20 of each bellows-like structure 21 is therefore designed with a thicker wall thickness than the respective shroud 17. This ensures that deformations of the bellows-like structure 21 caused by changing the pressure prevailing in the respective cavity 22 act primarily on the shroud 17.
• each bellows-like structure 21 has a contour 23 curved radially outward and projecting into the respective cavity 22 in a central region viewed in the axial direction.
• Each bellows-like structure 21 is in each case assigned at least one compressed-air line 24 in order to either introduce compressed air into the respective cavity 22 of the respective bellows-like structure 21 or to discharge it from the same compressed air.
• a compressed air line 24 exclusively for the bellows-like structure 21 positioned between the two guide blade rings 13 and 14, as shown in the axial direction.
• Each bellows-like structure 21 is assigned at least one such compressed air line 24. The more such compressed air lines 24 per bellows-like structure 21 are present, the faster compressed air can be introduced into the respective cavity 24 or derived from the same.
• a bellows-like structure 21 is arranged between the two guide blade rings 13 and 14 and between the two guide blade rings 15 and 16, between the two Leitschaufelkränzen 14 and 15, however, no such bellows-like structure is present. Rather, as shown in FIG. 1 between the two vane rings 14 and 15 and thus in the region of a rotor blade ring arranged between the same, a sensor unit 25 is arranged.
• the sensor unit 25 With the sensor unit 25, at least the radial dimension of the gap between the corresponding blade ring and the shell ring 17 surrounding this blade ring can be measured. Via a signal line 26, the sensor unit 25 transmits a corresponding actual value to a control device, not shown, wherein the control device compares the actual value with a desired value and depending on the pressure prevailing in the cavities 22 of the bellows structures 21 set pressure such that the actual value approaches the target value ,
• the compressed air supply into the cavities 22 and the compressed air discharge from the cavities 22 of the bellows-like structures 21 is adjustable via individual valves, so as to adjust the pressure prevailing in the cavities 22 of the two bellows-like structures 21 pressure individually and so each Dimension of the radial gap between the shroud 17 and the corresponding blade ring depending on the respective radial extent of the blade ring individually set.
• it can be provided to adjust the compressed air supply into the cavities 22 of the bellows-like structures 21 or the compressed air discharge from the same via a common valve.
• the two bellows-like structures 21 are each divided by axially extending parting planes in the axial direction, wherein during manufacture, the two axial halves of the bellows-like structures 21 are welded together. Alternatively, it is also possible to divide the bellows-like structures in the radial direction.
• each wall 19 is curved in the axial direction into the respective cavity 22, viewed in the axial direction.
• each arched, resilient wall 19 is curved in the axial direction outwardly out of the respective cavity 22. 3 close in the region of a vertex 29 of the curvature wall portions of the respective wall 19 a relatively acute angle ß of less than 90 °.
• the wall sections enclosing the angle ⁇ of the walls 19 extend essentially in the axial direction.
• the same as the shroud 17 and the support ring 21 are acted upon by the pressure prevailing in the cavity 22 and thereby support a radial disengagement of the shroud 17 and support ring 20 at a pressure increase in the cavity 22.
• a in this variant negative-acting toggle-like effect is due to the tips Angle ß almost completely eliminated.
• the bellows-type structure 30 according to FIG. 3 has a greater axial extent than radial extent, in particular the walls 19 of the bellows-type structure 30 have a greater axial extent than radial extent.

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

Applications Claiming Priority (2)

Publications (3)

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Family Applications (1)

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Family Cites Families (17)

• 2006
  • 2006-11-09 DE DE102006052786A patent/DE102006052786B4/de not_active Expired - Fee Related
• 2007
  • 2007-10-30 DE DE502007006392T patent/DE502007006392D1/de active Active
  • 2007-10-30 WO PCT/DE2007/001946 patent/WO2008055474A1/fr active Application Filing
  • 2007-10-30 CA CA002666200A patent/CA2666200A1/fr not_active Abandoned
  • 2007-10-30 AT AT07846281T patent/ATE497088T1/de active
  • 2007-10-30 EP EP07846281A patent/EP2087208B9/fr not_active Not-in-force
  • 2007-10-30 US US12/514,283 patent/US8608435B2/en not_active Expired - Fee Related

Non-Patent Citations (1)

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