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
• • 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
  • F01D11/005—Sealing means between non relatively rotating elements
  • F01D11/006—Sealing the gap between rotor blades or blades and rotor
  • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
• • 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
  • F01D11/005—Sealing means between non relatively rotating elements
  • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

• the invention relates to a turbomachine, in particular a gas turbine with a sealing system for a rotor, which extends along the axis of rotation, the rotor having a first rotor blade and a second rotor blade adjacent to the first rotor blade in the circumferential direction of the rotor.
• Rotatable blades of turbomachines are in different configurations over the full circumference on the circumferential surface of a rotor shaft, which e.g. is formed by a pulley attached.
• a rotor blade usually has an airfoil, a blade platform and a blade root with a fastening structure which is suitably received on the peripheral surface of the rotor shaft by a correspondingly complementary recess, which is produced, for example, as a circumferential groove or axial groove, and in this way the rotor blade fixed.
• gaps are formed by the respectively adjacent areas, which give rise to leakage flows of coolant or a hot action fluid driving the rotor during operation of a turbine.
• gaps occur, for example, between two adjacent blade platforms of rotor blades adjacent in the circumferential direction and between the peripheral surface of the rotor shaft and a blade platform radially adjacent to the peripheral surface.
• coolant e.g. Limiting cooling air
• Sealing concepts sought that are resistant to the occurring temperatures and the mechanical load due to the considerable centrifugal forces on the rotating system.
• a sealing concept for a rotor blade of a gas turbine is described in US Pat. No. 5,599,170.
• An essentially radially extending gap and an essentially axially extending gap are formed by two adjacent adjacent rotor blades, which are fastened in a rotor disk that can be rotated about an axis on the peripheral surface of the rotor disk.
• a sealing element seals the radial and at the same time the axial gap.
• the sealing element is inserted into a cavity which is formed by the blade platforms of the moving blades.
• the sealing element has a first and a second sealing surface, which adjoins the axial or radial gap.
• the sealing element also has a thrust surface that extends obliquely to the radial direction.
• the thrust surface is directly adjacent to a reaction surface which is formed as a partial surface of a movable reaction element arranged in the cavity.
• the sealing effect is achieved by the centrifugal forces acting on the movable reaction element as a result of the rotation of the running disk.
• the reaction element ment transmits a force to the oblique thrust surface whose radially directed force component on the sealing element causes the first sealing surface to seal the axial gap, while the axially directed force component on the sealing element leads to the second sealing surface sealing the radial gap.
• sealing elements are generally inserted into the blade platform on the side of the blade platform of the moving blade facing the action fluid flow.
• EP 0 761 930 AI and GB 905,582 each show a turbomachine with a turbine runner.
• the turbine rotor is designed in a disk design and is composed of individual rotor disks arranged axially adjacent to one another.
• rotor blades are arranged, each of which is fastened with its respective n blade root in an axial groove in the rotor disk, for example an axial fir tree groove or a hammer head groove.
• the rotor blades are axially fixed in the blade root and groove area by means of mounting plates permanently attached to the front of the rotor disks.
• the fastening plates are primarily used to axially fix the rotor blades.
• the object of the invention is to provide a highly efficient one for a turbomachine with a rotor extending along an axis of rotation, which has a first rotor blade and a second rotor blade adjoining the first rotor blade in the circumferential direction of the rotor
• the sealing system should, in particular, ensure an effective limitation of the possible leakage flows through gap areas and spaces between the rotors, and should be resistant to the thermal and mechanical loads that occur.
• the sealing system should be designed so that it can be manufactured as easily as possible and can be used with different rotors.
• a turbomachine in particular a gas turbine, with a rotor extending along an axis of rotation, comprising a circumferential surface which is defined by the outer radial boundary surface of the rotor, and a receiving structure, as well as a first rotor blade and a second Laufschaufei, each with a shovel foot and one to the
• the invention is based on the consideration that, when a turbomachine is in operation, the rotor supports a flowing hot actuator. tion fluid is exposed. As a result of the expansion, the hot action fluid does work on the rotor blades and sets them in rotation about the axis of rotation. For this reason, the rotor with the rotor blades is subjected to very high thermal and mechanical loads, in particular as a result of the centrifugal forces that occur as a result of the rotation.
• a coolant for example cooling air, is used to cool the rotor and, in particular, the rotor blades, which is usually supplied to the rotor by suitable coolant feeds.
• An intermediate space is formed here by the circumferential surface, which is defined here by the outer radial boundary surface of the rotor, and by the respective platform, arranged radially outward of the circumferential surface, of rotor blades arranged adjacent in the circumferential direction of the rotor.
• These leakage flows have a very disadvantageous effect on the cooling efficiency and the mechanical installation strength (smooth running and creep resistance) of the moving blades in the receiving structure of the peripheral surface.
• Leakage flows which are oriented along the axis of rotation (axial leakage flows), for example along the circumferential surface, are of particular importance in this context.
• leakage flows perpendicular to the axis of rotation (radial leakage flows), which are directed along a radial direction and thus essentially perpendicular to the circumferential surface, must also be taken into account.
• the invention shows a new way to effectively seal a rotor with a first rotor blade and with a second rotor blade adjacent to the first rotor blade in the circumferential direction of the rotor against possible leakage currents in a turbomachine. Both axial and radial leakage flows are taken into account.
• This is achieved in that the sealing system having a labyrinth sealing system in the intermediate space on the peripheral surface through the radially outer boundary surface of the rotor of the rotor is arranged. Due to the specified configuration, the sealing system seals the intermediate space that is formed between the blade platforms and the peripheral surface. The space extends in the radial and axial directions and in the circumferential direction of the rotor.
• the axial extent of the gap is generally dominant here, and its extent in the circumferential direction is greater than the radial dimension.
• the exact geometry of the intermediate space is determined by the special design of the adjoining blade platforms and the peripheral surface.
• the specified sealing system which has a labyrinth sealing system, can be individually adapted in its design to the respective geometry and the requirements with regard to the leakage flows to be limited, the provision of a labyrinth sealing system being particularly effective for sealing the interstices.
• the mode of operation of a labyrinth sealing system is based on throttling the hot action fluid and / or the coolant in the sealing system as effectively as possible and thus largely suppressing an axially directed leakage flow (leakage mass flow) through the intermediate space.
• a residual leakage flow through existing sealing gaps, as they generally occur, for example, in the case of labyrinth gap seals, can be calculated taking into account the so-called bridging factor.
• labyrinth gap sealing systems which are also referred to as see-through seals, have a leakage flow that is up to 3.5 times greater than that of so-called comb-groove sealing systems the sealing gap. Due to the remaining sealing gap, labyrinth gap sealing systems have the great advantage over the comb-groove sealing systems that they are suitable even for large thermally and / or mechanically induced relative expansions in the rotor. A major advantage over conventional sealing concepts results from the arrangement of the labyrinth sealing system on the peripheral surface.
• the labyrinth sealing system makes it possible for the labyrinth sealing system to adjoin the circumferential surface directly and to produce a sealing effect.
• This is particularly well suited to preventing leakage currents in the axial direction along the peripheral surface.
• a hot action fluid for example the hot gas in a gas turbine
• the sealing system with the labyrinth sealing system can be dimensioned in the radial direction so that it directly adjoins the adjacent blade platforms and a sealing effect is achieved. In this way, an axial leakage flow is practically completely prevented, but at least significantly suppressed.
• Labyrinth sealing system is provided on the circumferential surface, it is not necessarily coupled to a moving blade. Assembly or repair work on a blade, such as the replacement of a Laufschaufei are thus possible without much effort. The sealing system remains unaffected and can therefore be used several times.
• the rotor in the turbomachine has a running disk which comprises the peripheral surface and the receiving structure, the peripheral surface having a first peripheral surface edge and a second peripheral surface edge opposite the first peripheral surface edge along the axis of rotation, the receiving structure having a first Has disc groove and a second disc groove in the circumferential direction of the disc to the first disc groove, and wherein the blade root of the first blade is inserted in the first disc groove and the blade root of the second blade in the second disc groove.
• the attachment of the rotatable rotor blades is such that they can absorb the blade stresses by flow and centrifugal forces as well as by blade vibrations with high certainty during operation of the turbomachine and can transmit the occurring forces to the rotor disk and finally to the entire rotor.
• the rotor blade can be fastened, for example, by means of axial grooves, each rotor blade being clamped individually into a rotor disc groove which is provided for this purpose and extends essentially in the axial direction.
• simple attachments to the barrel for example with a dovetail or Laval foot, are possible.
• the axial fir tree foot can also be used.
• the axial fir tree attachment is preferably also used for thermally highly loaded blades in gas turbines.
• the peripheral surface has a first peripheral surface edge and a second peripheral surface edge as partial regions.
• the first peripheral surface edge is arranged upstream and the second peripheral surface edge is arranged downstream, for example.
• this geometrical division enables the sealing system to be designed and arranged on different partial areas of the circumferential surface.
• the sealing system is preferably arranged on the first peripheral surface edge and / or on the second peripheral surface edge.
• the labyrinth sealing system can be arranged at least partially on the first and / or on the second peripheral surface edge.
• the arrangement of the sealing system on the first, for example upstream, peripheral surface edge primarily limits the entry of flowing hot action fluid into the intermediate space and thus prevents damage to the rotor blade.
• the arrangement of the sealing system on the second, downstream, peripheral surface edge serves primarily to prevent the escape of coolant, e.g. cooling air under a certain pressure in the intermediate space, in the axial direction along the peripheral surface over the second peripheral surface edge in the
• a peripheral surface central region is preferably formed on the peripheral surface and is bordered in the axial direction by the first peripheral surface edge and the second peripheral surface edge, the sealing system being arranged at least partially on the peripheral surface central region.
• the labyrinth sealing system is preferably arranged on the circumferential surface center area.
• the peripheral surface center region forms a partial region of the peripheral surface.
• the sealing system with the labyrinth sealing system preferably has a sealing element that extends in the circumferential direction.
• the intermediate space extends essentially in the radial and axial directions and in the circumferential direction of the rotor.
• An extending along the circumferential direction of the rotor Sealing element in the intermediate space is particularly well suited to hinder possible axial leakage flows in coolant and / or in hot action fluid with high efficiency.
• an upstream axial leakage flow for example a hot gas from the flow channel of a gas turbine, which spreads along the circumferential surface, is effectively impeded by the sealing element.
• the leakage flow is delayed by the obstacle in the intermediate space and finally come to a standstill on the side of the sealing element facing the leakage flow (simple throttle).
• the side of the sealing element facing away from the leakage flow and the part of the intermediate space adjoining it in the axial direction is already effectively protected by the simple sealing element against exposure to the leakage medium, for example hot action fluid or coolant.
• the mode of operation of the sealing element can thus be similar to that of the labyrinth sealing system, which increases the sealing effect.
• a significant improvement of the simple solution described above with a sealing element extending in the circumferential direction results from the combination of the sealing element with one or more further sealing elements.
• at least one further sealing element is provided, which extends in the circumferential direction and is arranged axially spaced from the sealing element.
• This multiple arrangement of sealing elements significantly reduces possible leakage flows in the intermediate space.
• the intermediate space is very effectively protected in particular from a possible entry of hot action fluid both from the upstream region of higher pressure and from the downstream region of lower pressure of the flow channel.
• the sealed space is usable for one Coolant, e.g. cooling air.
• the coolant is supplied to the intermediate space under pressure and is used primarily for efficient internal cooling of the thermally highly loaded rotor, the blade platform and the blade blade radially adjacent to the blade platform.
• Another advantageous use of the pressurized coolant in the intermediate space is to utilize its blocking effect against the hot action fluid in the flow channel.
• the structural design of the sealing elements and the choice of the pressure of the coolant in the intermediate space ensures that the pressure difference between the coolant and the hot action fluid is sufficiently small but sufficiently high to achieve a blocking effect against the hot action fluid.
• the pressure of the coolant in the intermediate space has to be only slightly above the upstream pressure of the hot action fluid. The greater the sealing effect of the sealing elements, the less possible residual leakage flows of coolant into the flow channel.
• At least the labyrinth sealing system is preferably produced in one piece in the sealing system, in particular by removing material from the running disk.
• this is already implemented on the peripheral surface by at least two sealing elements that extend in the circumferential direction of the running disk and are axially spaced apart from one another. These sealing elements can be implemented by throttle plates turned from solid.
• the one-piece production method has the advantage that no additional connecting element between the labyrinth sealing system and the peripheral surface is required. In terms of process engineering, machining of the running disk and the production of the labyrinth sealing system can thus be carried out in one step and on a lathe, which is very inexpensive.
• the sealing element preferably has a sealing tip, in particular a knife edge, at its outer radial end. Residual leakage flows through the gap are decisively influenced by the seal gap width that can be executed, i.e. for example the distance between the outer radial end of the sealing element and the blade platform to be sealed adjacent thereto. In order to make the sealing gap width as small as possible, the outer radial end of the sealing element is sharpened. A sealing gap bridging can also be carried out by producing the sealing tip or the knife edge with a small allowance compared to the radial installation dimension of the blade platform. By rubbing the sealing tip or the knife edge against the blade platform, the sealing gap is inserted into the receiving structure when the rotor blade is inserted, e.g.
• the labyrinth sealing system preferably comprises the sealing element and / or the further sealing element.
• the sealing element and the further sealing element are therefore part of the labyrinth sealing system.
• the labyrinth sealing system is preferably designed as a labyrinth gap sealing system.
• a gap sealing element is provided for sealing an essentially axially extending gap, the gap being formed between the blade platform of the first rotor blade and the blade platform of the second rotor blade and being in flow connection with the intermediate space.
• the gap sealing element prevents leakage current from occurring through the gap.
• Such a leakage flow is directed essentially radially and can be oriented radially inward both from the interspace through the gap radially and through the gap into the interspace.
• the gap sealing element prevents the entry of the action fluid, e.g. the hot gas in a gas turbine, through the gap radially inwards prevents the space. This protects the rotor, in particular the rotor blade, from an oxidizing and / or corrosive attack in the intermediate space.
• the gap sealing element prevents coolant, for example cooling air, from escaping radially outward from the intermediate space through the gap into the flow channel.
• a cavity can also adjoin the gap radially outwards, which is formed by the first and second rotor blades adjoining one another in the circumferential direction (so-called box design of a rotor blade).
• the gap sealing element on the one hand prevents the possible entry of hot action fluid from the intermediate space through the gap radially outward into the cavity.
• the cavity sealed by the gap sealing element can be acted upon with a coolant, for example cooling air. This is pressurized in the cavity and is available, for example, for efficient internal cooling of the thermally highly loaded rotor blade or for other cooling purposes.
• a coolant for example cooling air.
• Fertilizing the pressurized coolant in the cavity consists of utilizing its blocking effect against the hot action fluid in the flow channel.
• the gap sealing element is preferably produced by a gap sealing plate which has a gap sealing edge which engages in the gap under the action of centrifugal force and closes the gap.
• the design of the gap sealing element as a gap sealing sheet is a simple and inexpensive solution.
• a configuration as a thin metal strip which has a longitudinal axis and a transverse axis is possible.
• the gap sealing edge extends essentially centrally on the metal strip along the longitudinal axis and can be produced in a simple manner by folding the metal strip over.
• the gap sealing element is advantageously arranged in the intermediate space. During operation of the flow machine, the gap sealing element is then pressed firmly against the adjacent blade platform as a result of the rotation by the radially outward centrifugal force, the gap sealing edge m engaging the gap and sealing it effectively.
• the gap sealing element is preferably made of a highly heat-resistant material, in particular of a nickel-based or cobalt-based alloy. These alloys also have sufficient elastic deformation properties.
• the material of the gap sealing element is selected to match the material of the rotor, thereby avoiding contamination or diffusion damage. Furthermore, an equal thermal expansion or contraction of the rotor, in particular of the blade platform of the rotor blade, is ensured.
• the gap sealing element preferably borders radially on the sealing system.
• the sealing element engages in a recess, in particular in a groove, in the peripheral surface.
• the sealing element is not necessarily part of the labyrinth system, but it is part of the sealing system. The sealing element is prevented from falling out and / or the sealing element is prevented from being thrown out when centrifugal force acts in a stationary manner
• the sealing element engages in a suitable recess.
• the recess also produces a sealing surface on the peripheral surface, which is expediently designed as a partial surface of the recess.
• this sealing surface is designed, for example, on the groove base.
• the sealing surface is produced with a correspondingly low and well-defined surface roughness.
• the sealing element moves away from the axis of rotation of the rotor in the radial direction under the influence of centrifugal force.
• This property is used in a targeted manner to achieve a significantly improved sealing effect on the blade platform of a moving blade.
• the sealing element comes under centrifugal force into contact with the blade platforms radially spaced from one another in the circumferential direction and is firmly pressed against the blade platforms.
• the radial mobility of the sealing element can be ensured by appropriate dimensioning of the recess and the sealing element.
• Another advantage is that the sealing element for possible maintenance purposes or in the event of a failure of the blade without additional tools and without the risk of caking of the sealing element due to an oxidizing or corrosive attack at high operating temperatures can be easily removed and replaced if necessary.
• a certain tolerance of the sealing element, which engages in the recess, in particular in the groove, is very useful because it allows thermal expansion and thus thermally induced stresses in the rotor are avoided.
• the sealing element preferably comprises a first partial sealing element and a second partial sealing element, the first partial sealing element and the second partial sealing element intermeshing.
• the partial sealing elements can be designed so that they perform a partial sealing function for different areas to be sealed in the space in a special way. Such different areas in the intermediate space are formed, for example, by suitable sealing surfaces on the groove base, on the blade platform of the first rotor blade or on the blade platform of the second rotor blade.
• the partial sealing elements complement each other through their arrangement
• Pair of partial sealing elements to form a sealing element the sealing effect of the pair being greater than that of a partial sealing element mentions.
• a particularly adapted design of the partial sealing elements to the areas to be sealed in the intermediate space means that the sealing effect of the paired partial sealing elements is greater than can be achieved, for example, with a one-piece sealing element.
• the first partial sealing element and the second partial sealing element are preferably movable in the circumferential direction relative to one another.
• This provides an adapted system of partial sealing elements.
• the relative movement of the partial sealing elements in the circumferential direction enables an adapted meshing of the partial sealing elements, depending on the thermal and / or mechanical loading of the rotor.
• the adapted system of partial sealing elements can be designed so that it is under the action of external forces, e.g. the centrifugal force as well as the normal and bearing forces, to a certain extent self-adjusted to develop its sealing effect. Furthermore, possible thermally or mechanically induced stresses are compensated for much better by the movable pair of partial sealing elements.
• first partial sealing element and the second partial sealing element each have a disk sealing edge adjacent to the peripheral surface and a platform sealing edge adjacent to the blade platform.
• the respective platform sealing edge can further be functionally subdivided into platform part sealing edges.
• a first platform partial sealing edge and a second platform partial sealing edge can be provided, the first platform partial sealing edge being adjacent to the blade platform of the first rotor blade and the second platform part sealing edge being adjacent to the blade platform of the second rotor blade.
• This functional subdivision makes it easy to adapt the partial sealing elements to the respective installation geometry of the first and second rotor blades in the receiving structure.
• the partial sealing element it is sufficient that the disk sealing edge seals against the peripheral surface and the platform sealing edge seals against the blade platform of the moving blade, the best possible form fit being produced.
• a particularly effective seal is achieved with the paired arrangement of the first and second partial sealing elements to form a sealing element.
• the first and the second partial sealing elements preferably overlap, the platform sealing edge and the disc sealing edge of the first partial sealing element being adjacent to the platform sealing edge or disc sealing edge of the second partial sealing element.
• the sealing element is preferably made of a heat-resistant material, in particular of a nickel-based or cobalt-based alloy. These alloys also have sufficient elastic deformation properties. It is thus achieved that the material of the sealing element is selected to match the material of the rotor in order to avoid contamination or diffusion damage and to ensure a uniform thermal expansion of the rotor, in particular the blade platform of the rotor blade.
• the receiving structure is produced in the turbomachine with the rotor extending along an axis of rotation by means of a circumferential groove, the circumferential surface having a first circumferential surface and a second circumferential surface lying opposite the first circumferential surface along the axis of rotation, each of which axially adjoins the circumferential groove abuts, the sealing system being provided on the first and / or on the second peripheral surface in the intermediate space.
• the fastening of the rotor blades must absorb the blade stresses by flow and centrifugal forces as well as by blade vibrations with a high degree of certainty and must transmit the forces which occur to the rotor disk and finally to the entire rotor.
• the blade fastening mechanism in a circumferential groove is widespread, especially in the case of low and medium loads.
• Various configurations are known after use (cf. I. Kosmorowski and G. Schramm, “Turbo Machines ⁇ ISBN 3-7785-1642-6, edition of Dr. Alfred Huthig Verlag, Heidelberg, 1989, p.113- 117)
• the so-called hammer head connection which is easy to manufacture, is used.
• the flow machine is preferably a gas turbine.
• 1 shows a half section through a gas turbine with a compressor, combustion chamber and turbine, 1 shows a perspective view of a section of a rotor disk,
• FIG. 1 shows a perspective view of a section of a running disk with inserted moving blade
• FIG. 4 different views of a second partial sealing element of a sealing element shown in FIG. 4,
• FIG. 3 shows an axial top view of a section of a rotor with an alternative configuration of the sealing element to FIG. 7,
• FIG. 3 shows a side view of a rotor blade with an alternative configuration of the labyrinth sealing system compared to FIG. 9, a perspective view of a section of a rotor disk with an inserted rotor blade and with a gap sealing element,
• FIG. 11 shows a detail of a view of the arrangement shown in FIG. 11 along the section line XII-XII, 13 shows a perspective view of a rotor shaft with circumferential grooves,
• FIG. 14 shows a sectional view of a section of a rotor with a circumferential groove and with an inserted rotor blade
• FIG. 15 shows a sectional view of a section of a rotor with an alternative embodiment of the blade attachment to FIG. 14.
• the gas turbine 1 shows a half section through a gas turbine 1.
• the gas turbine 1 has a compressor 3 for combustion air, a combustion chamber 5 with burners 7 for a liquid or gaseous fuel, and a turbine 9 for driving the compressor 3 and a generator (not shown in FIG. 1).
• stationary guide vanes 11 and rotatable rotor blades 13 are arranged on respective radially extending rings, not shown in half section, along the axis of rotation 15 of the gas turbine 1.
• a successive pair along the axis of rotation 15 is made up of a ring of guide vanes 11 (guide blade ring) and a ring of rotor blades 13
• Each guide blade 11 has a blade platform 17 which is arranged to fix the relevant guide blade 11 to the inner turbine housing 19.
• the blade platform 17 represents a wall element in the turbine 9.
• the blade platform 17 is a thermally highly stressed component which forms the outer boundary of the flow channel 21 in the turbine 9.
• the rotor blade 13 is fastened on the turbine rotor 23 arranged along the axis of rotation 15 of the gas turbine 1 via a corresponding blade platform 17.
• the turbine rotor 23 can, for example, consist of a plurality of rotor blades 13, not shown in FIG Be assembled disks that are held together by a tie rod, not shown, and are centered on the axis of rotation 15 in a way that is tolerant of thermal expansion by means of serration teeth.
• the turbine rotor 23 forms, together with the rotor blades 13, the rotor 25 of the turbomachine 1, in particular the gas turbine 1.
• air L is sucked in from the surroundings.
• the air L is compressed in the compressor 3 and thereby preheated at the same time.
• the combustion chamber 5 the air L is brought together with the liquid or gaseous fuel and burned.
• a portion of the air L previously extracted from the compressor 3 from suitable withdrawals 27 serves as cooling air K for cooling the turbine stages, the first turbine stage, for example, being subjected to a turbine inlet temperature of approximately 750 ° C. to 1200 ° C.
• the turbine 9 there is a relaxation and cooling of the hot action fluid A, hereinafter referred to as hot gas A, which flows through the turbine stages and thereby sets the rotor 25 in rotation.
• FIG. 2 shows a perspective view of a section of a rotor 29 of a rotor 25.
• the rotor 29 is centered along the axis of rotation 15 of the rotor 25.
• the rotor disk 29 has a receiving structure 33 for fastening rotor blades 13 of the gas turbine 1.
• the receiving structure 33 is produced by recesses 35, in particular by grooves, in the running disk 29.
• the recess 35 is designed as an axial disk groove 37, in particular as an axial fir tree groove.
• the running disk 29 has a peripheral surface 31 which is arranged at the outer radial end of the running disk 29.
• a first peripheral surface edge 39A and a second peripheral surface edge 39B are formed on the peripheral surface 31.
• the first peripheral surface edge 39A lies along the axis of rotation 15 opposite the second peripheral surface edge 39B on the peripheral surface 31.
• a peripheral surface center region 41 is formed on the peripheral surface 31 and is bordered in the axial direction by the first peripheral surface edge 39A and the second peripheral surface edge 39B.
• a perspective view of a section of a running disk 29 with inserted moving blade 13A is shown in FIG. 3. Over its full circumference, the running disk 29 has running disk grooves 37A, 37B which are open towards its peripheral surface 31 and which run essentially parallel to the axis of rotation 15 of the rotor 25, but can also be set at an angle thereto.
• the disk grooves 37A, 37B are equipped with undercuts 59.
• a blade 13A with its blade root 43A is inserted into a disk groove 37A along the direction of use 57 of the disk groove 37A.
• the blade root 43A is supported with longitudinal ribs 61 on the undercuts 59 of the disk groove 37A.
• the rotor blade 13A is held securely against the centrifugal forces occurring in the direction of the longitudinal axis 47 of the rotor blade 13A when the rotor disk 29 rotates about the axis of rotation 15.
• the blade platform 17A has a disk-side base 63 and an outer side 65 opposite the disk-side base 63.
• the airfoil 45 of the moving blade 13A On the outside 65 of the blade platform 17A there is an airfoil 45 of the moving blade 13A.
• the hot gas A required to operate the rotor 25 flows past the airfoil 45 and thereby generates a torque on the rotor 29.
• the airfoil 45 of the rotor 13A requires an internal cooling system, which is not shown in FIG.
• a coolant K for example cooling air K
• a feed line (not shown) through the running disk 29 into the blade root 43A of the moving blade 13A and from there to suitable supply lines of the internal cooling system, likewise not shown in FIG. 3.
• a sealing system 51 is provided.
• the sealing system 51 is on the circumferential surface 31 arranged on the second peripheral surface edge 39B.
• the sealing system 51 has a sealing element 53 which extends in the circumferential direction of the running disk 29.
• a further sealing element 55 is provided and extends axially spaced from the sealing element 53 in the circumferential direction of the running disk 29.
• the sealing element 53 and the further sealing element 55 each engage in a recess 35, in particular in a groove, in the peripheral surface 31.
• the sealing system 51 seals the intermediate space 49, which is inserted between the blade platform 17A of the rotor blade 13A and a blade platform 17B of a second rotor blade 13B, which is shown in broken lines and into a second rotor disk groove 37B, which is spaced apart in the circumferential direction of the rotor disk 29 from the first rotor disk groove 37A and the peripheral surface 31 is formed.
• This largely prevents the hot gas A from reaching the intermediate space 49 axially via the second peripheral surface edge 39B and damaging the rotor blades 13A, 13B in the region of the blade root 43A, 43B or the blade platform 17A, 17B.
• an escape of coolant K from the intermediate space 49 is prevented axially along the peripheral surface 31 via the second peripheral surface edge 39B.
• FIG. 4 shows a side view of a rotor blade 13 with a sealing system 51.
• the sealing system 51 is illustrated as a partial section in FIG. 4.
• the sealing system 51 is arranged on the first peripheral surface edge 39A and on the second peripheral surface edge 39B in the intermediate space 49.
• the first peripheral surface edge 39A is located upstream on the peripheral surface 31 of the running disk 29 and the second peripheral surface edge 39B is located downstream.
• the arrangement of the sealing system 51 on the first, upstream, peripheral surface edge 39A primarily limits the entry of flowing hot gas A into the intermediate space 49. This prevents damage to the rotor blade 13 and the running disk 29 in the region of the peripheral surface 31.
• the arrangement of the sealing system 51 on the second, downstream, peripheral surface edge 39B serves primarily to prevent the exit of a coolant K, for example cooling air K under a certain pressure in the intermediate space 49, in the axial direction along the peripheral surface 31 via the second peripheral surface edge 39B in the FIGS
• the hot gas A expands in the direction of flow.
• the pressure of the hot gas A is continuously reduced in the direction of flow.
• a coolant K under a certain pressure in the intermediate space 49 will therefore emerge from the intermediate space 49 in the direction of the lower ambient pressure, that is to say at the second peripheral surface edge 49B arranged downstream.
• the sealing system 51 on the first peripheral surface edge 39A and on the second peripheral surface edge 39B seals the intermediate space 49 in both directions.
• This configuration therefore offers great security both against the entry of hot gas A into the intermediate space 49 and against the exit of coolant K from the intermediate space 49.
• the sealing system 51 On the first peripheral surface edge 39A, the sealing system 51 has a sealing element 53 which extends in the circumferential direction of the running disk 29.
• the sealing element 53 engages in a recess 35, in particular in a groove, which is incorporated in the peripheral surface 31.
• the sealing system 51 At the second peripheral surface edge 39B, the sealing system 51 has a sealing element 53 which extends in the peripheral direction.
• Another sealing member 55 is provided on the second peripheral surface edge 39B.
• the further sealing element 55 extends in the circumferential direction of the running disk 29 and is arranged axially spaced from the sealing element 53.
• the configuration of the sealing system 51 by means of one or more sealing elements 53, 55 is particularly well suited to hinder possible axial leakage flows of coolant K and / or hot gas A in the intermediate space 49 with increased efficiency. So the entry of an upstream becomes axial leakage flow, for example of the hot gas A from the flow channel of a gas turbine 1, which flows into the intermediate space 49 via the first peripheral surface edge 39A along the peripheral surface 31, effectively hampered by the sealing system 51 arranged on the first peripheral surface edge 39. At the same time, the occurrence of an axial leakage flow, which is directed out of the intermediate space 49 along the second peripheral surface edge 39B, is reliably prevented by the obstacle in the form of the sealing elements 53, 55.
• the sealed space 49 is thus well usable for a coolant K, e.g. Cooling air K.
• a coolant K e.g. Cooling air K.
• This can be pressurized and then used for efficient internal cooling of the thermally highly loaded rotor 25, in particular of the blade platform 17 and of the blade blade 45 adjoining the blade platform along the longitudinal axis 47.
• a further advantageous use of the pressurized coolant K in the intermediate space 49 is in the blocking effect with respect to the hot gas A in the flow channel. This blocking effect of the coolant K largely prevents the entry of hot gas A into the intermediate space 49.
• the sealing elements 53, 55 are each arranged to be movable in the radial direction in the recess 35, so that, when the rotor 25 is in operation, the sealing effect 53, 55 is improved compared to conventional designs due to the action of the centrifugal force. Under the action of the centrifugal force, the sealing elements 53, 55 will move radially outward parallel to the longitudinal axis 47. In this case, the disk-side base 63 of the blade platform 17 is sealed very effectively against possible axial leakage flows out of the intermediate space 49 or into the intermediate space 49. The radial mobility of the sealing elements 53, 55 can be ensured by appropriate design of the recess 35 and the sealing element 53, 55.
• sealing elements 53, 55 also for possible maintenance purposes or in the event of a failure of the rotor blade 13 without additional tools and without the risk of caking of the sealing element 53 due to an oxidizing or corrosive attack at high operating temperatures, and can be replaced if necessary.
• the sealing element 53, 55 has a first partial sealing element 67A and a second partial sealing element 67B.
• the first partial sealing element 67A and the second partial sealing element 67B engage in one another.
• 67A, 67B complement each other through their paired arrangement to form a sealing element 53, 55 in a special way, the achieved sealing effect of the paired partial sealing elements 67A, 67B being greater than that of an individual partial sealing element 67A, 67B.
• a particularly advantageous embodiment of the partial sealing elements 67A, 67B on the regions to be sealed in the intermediate space 49 ensures that the sealing effect achieved by the paired arrangement is greater than would be possible, for example, with a one-piece sealing element 53.
• a possible, particularly advantageous embodiment of the partial sealing elements 67A, 67B is presented below with reference to FIGS. 5A to 5D and FIGS. 6A to 6D.
• the sealing element 53, 55 shown in FIG. 4 is composed of two interlocking partial sealing elements 67A, 67B.
• the first partial sealing element 57A is shown in different views in FIGS. 5A to 5D:
• FIG. 5A shows a perspective view of the first partial sealing element 67A.
• the first partial sealing element 67A has a pane sealing edge 69 and one of the pane sealing edge 69 opposite platform sealing edge 71.
• the disk sealing edge 69 borders on the peripheral surface 31, and the platform sealing edge 71 on the disk-side base 63 of the blade platform 17.
• FIG. 5B shows a view of the disk sealing edge 71 of the first partial sealing element 67A
• FIG 5C shows a top view of the first partial sealing element 67A
• FIG. 5D shows a side view.
• the platform sealing edge 71 has a first platform part sealing edge 71A and a second platform part sealing edge 71B.
• This subdivision of the platform sealing edge 71 into two platform part sealing edges 71A, 71B enables a simple constructional adaptation of the first part sealing element 67A to the respective installation geometry of a rotor blade 13 and a further rotor blade 13B in a rotor disk 29 (see FIGS. 3 and 4).
• the second partial sealing element 67B is configured in a corresponding manner.
• FIGS. 6A to 6D show different views of the second partial sealing element 67B of a sealing element 53 shown in FIG. 4.
• the second partial sealing element 67B has a pane sealing edge 69 and a platform sealing edge 71 opposite the pane sealing edge 69.
• the platform sealing edge 71 is further functionally subdivided into platform part sealing edges 71A, 71B.
• a first platform part sealing edge 71A and a second platform part sealing edge 71B are provided.
• Each of the partial sealing elements 67A, 67B is designed such that its respective center of mass is arranged adjacent to exactly one of the platform partial sealing edges 71A, 71B assigned to the relevant partial sealing element 67A, 67B. This is achieved by a stepped constructional design of each of the partial sealing elements 67A, 67B with an area of smaller material thickness and with an area of greater material thickness, each area being associated with exactly one platform part sealing edge 71A, 71B.
• the first partial sealing element 67A and the second partial sealing element 67B are arranged in pairs to form a sealing element 53. This ensures a very efficient seal.
• the partial sealing elements 67A, 67B are designed such that they engage and overlap in the installed state, the platform sealing edge 71 and the disc sealing edge 69 of the first partial sealing element 67A adjoining the platform sealing edge 71 and disc sealing edge 69 of the second partial sealing element 67B.
• the partial sealing elements 67A, 67B are designed, for example, as metallic sealing sheets.
• a material is selected that is highly heat-resistant and has sufficient elastic deformation properties.
• a suitable material is, for example, a nickel-based or cobalt-based alloy. This ensures that the material of the partial sealing elements 67A, 67B is selected to match the material of the rotor 25. Contamination or diffusion damage are thereby avoided and a uniform, largely stress-free thermal expansion of the rotor 25 is possible.
• FIG. 7 shows an axial top view of a section of a rotor 25 with a sealing element 53.
• the rotor 25 has a running disk 29.
• the running disk 29 has a first one Disc groove 37A and a second disc groove 37B spaced in the circumferential direction of the disc 29 from the first disc groove 37A.
• a first rotor blade 13A and a second rotor blade 13B are inserted into the rotor disk 29, the blade root 43A of the first rotor blade 13A being inserted into the rotor disk groove 37A and the blade root 43B of the second rotor blade 13B engaging in the second rotor disk groove 37B.
• the blade platform 17A of the first rotor blade 13A adjoins the blade platform 17B of the second rotor blade 13B and an intermediate space 49 is formed between the blade platforms 17A, 17B and the peripheral surface 31.
• a sealing element 53 is provided on the peripheral surface 31 in the intermediate space 49.
• the sealing element 53 has a pane sealing edge 69 as well as a first platform part sealing edge 71A opposite the pane sealing edge 69 and a second platform part sealing edge 71B.
• the sealing element 53 is inserted into a recess 35, in particular into a groove in the peripheral surface 31.
• the disk sealing edge 69 adjoins the peripheral surface 31.
• the first platform part sealing edge 71A adjoins the disc-side base 63 of the first blade platform 17A
• the second platform part sealing edge 71B adjoins the disc-side base 63 of the second blade platform 17B.
• the sealing element 53 can be formed by two interlocking, paired partial sealing elements 67A, which are movable in the radial direction and in the circumferential direction,
• FIGS. 5A-5D and 6A-6D comes under centrifugal force into contact with the blade platforms 17A, which are radially spaced from the peripheral surface 31 and are adjacent to one another in the peripheral direction , 17B and is firmly pressed onto the disk-side base 63 thereof.
• Adequate radial mobility is ensured by appropriate dimensioning of the recess 35, in particular the groove, and the sealing element 53.
• mobility of the sealing element 53 in the circumferential direction of the running disk 29 is provided.
• the sealing element 53 in particular each of the partial sealing elements 67A, 67B not shown in FIG. 7 (cf. FIGS. 5A-5D and FIGS. 6A-6D), will then under the action of all external forces, such as the centrifugal force, as well as the normal and / or adjust the bearing forces yourself to develop its sealing effect.
• the inclination of the platform part sealing edges 71A, 71B in relation to the longitudinal axis 47 corresponds to the inclination of the disc-side base 63 of the blade platforms 17A, 17B.
• a gap 73 can be formed.
• This gap 73 is in flow connection with the intermediate space 49 and can optionally be sealed by a simple gap sealing element (cf. FIG. 11 and the relevant description of the figures).
• FIG. 7 An axial plan view of a section of a rotor 25 with an alternative configuration to the sealing element 53 compared to FIG. 7 is shown in FIG.
• the blade platform 17A of the first rotor blade 13A is offset in the radial direction with respect to the adjacent blade platform 17B of the second rotor blade 13B.
• Such one Offset ⁇ between vane platforms 17A, 17B which adjoin one another in the circumferential direction generally occurs when the rotor disk grooves 37A, 37B are inclined with respect to the axis of rotation 15 of the rotor 25.
• the sealing element 53, or each of the partial sealing elements 67A, 67B, which are not shown in FIG. 7 and are arranged in pairs with the sealing element 53 (cf. FIGS. 5A-5D and FIGS. 6A-6D), is equipped with an offset sealing edge 75 which compensates for the offset ⁇ form-fitting seal.
• the specified sealing concept can thus be flexibly applied to different rotor geometries and installation dimensions by designing the
• FIG. 9 shows a side view of a rotor blade 13 which is inserted in a rotor disk 29, the sealing system 51 being arranged in the intermediate space 49 on the peripheral surface center region 41 of the peripheral surface 31.
• the sealing system 51 is designed as a labyrinth sealing system 5LA, in particular a labyrinth gap sealing system 5LA.
• the labyrinth gap sealing system 51A is implemented by a plurality of sealing elements 53 which extend in the circumferential direction of the running disk 29 and are axially spaced apart from one another on the circumferential surface center region 41.
• the individual sealing elements 53 are each embodied by a throttle plate 77A-77E that is caulked into the peripheral surface 41.
• the mode of operation of the labyrinth gap sealing system 51A produced by the various throttling plates 77A-77E is based on the most effective throttling of a flowing hot gas A and / or a coolant K in the sealing system 51A and an extensive reduction of an axially directed one which is thereby effected
• the outer radial end 79 of a throttle plate 77A is spaced from the disk-side base 63 of the blade platform 17 by a sealing gap 81.
• a residual leakage flow can occur in the intermediate space 49 through the sealing gap 81, as is generally the case with labyrinth gap seals 51A.
• the throttle sheets 77A - 77E of the labyrinth gap sealing system s 51A the residual leakage flow is limited to a specified level.
• the labyrinth gap sealing system 51A has the advantage over other possible labyrinth sealing systems that a tolerance with respect to thermally and / or mechanically induced relative expansions in the rotor 25 is achieved by the sealing gaps 81.
• the sealing system 51 is also designed as a labyrinth gap sealing system 51A, this being produced in one piece, in particular by removing material from the running disk 29.
• the labyrinth gap sealing system 51A is arranged on the circumferential surface center region 41 of the running disk 29.
• the labyrinth gap sealing system 51A has a plurality of sealing elements 53 which extend in the circumferential direction of the running disk 29 and are axially spaced from one another.
• the sealing elements 53 are produced by four throttle plates 77A-77D turned from the solid of the running disk 29. With this manufacturing method, no additional connecting element between the labyrinth gap sealing system 51A and the peripheral surface 31 is required.
• a sealing gap bridging can also be carried out by producing the sealing tip 83 or the knife edge with a small allowance compared to the radial installation dimension of the blade platform 17.
• the sealing gap 81 is then bridged when inserting the blade into the rotor 29. In this way, the sealing gap 81 is practically completely closed, a significantly improved sealing effect is achieved and a possible axial leakage flow, for example due to the flowing hot gas A or a coolant K, in the intermediate space 49 is further reduced.
• FIG. 11 shows a perspective view of a section of a rotor disk 29 with an inserted rotor blade 13A, the blade root 43A of the rotor blade 13A being inserted into a first rotor disk groove 37A.
• a second rotor blade 13B which is shown in dashed lines, is inserted with its blade root 43B into a second rotor disk groove 37B and is arranged adjacent to the rotor blade 13A in the circumferential direction of the rotor disk 29.
• the sealing system 51 which is designed as a labyrinth gap sealing system 51A, is arranged on the peripheral surface 31 on the peripheral surface center region 41.
• the sealing system 51A is produced by a plurality of sealing elements 53 which are spaced apart from one another along the axis of rotation 15 and extend in the circumferential direction of the running disk 29.
• a substantially axially extending gap 73 is formed between the blade platform 17A of the rotor blade 13A and the blade platform 17B of the second rotor blade 13B and is in flow connection with the intermediate space 49.
• a gap sealing element 85 is provided to seal the gap 73.
• the gap sealing element 85 is implemented in a simple manner by means of a suitable gap sealing plate which has a gap sealing edge 87. The gap sealing edge engages in the gap 73 under the action of centrifugal force and seals the gap 73.
• the gap sealing element 85 is arranged in the intermediate space 49 in such a way that it borders radially on the sealing system 51, in particular on the labyrinth gap sealing system 51A.
• the gap sealing element 85 largely prevents leakage current from occurring through the gap 73.
• Such a leakage flow through the gap 73 is essentially lie radially directed and can be oriented radially inward both from the space 49 through the gap 73 and radially inward through the gap 73 into the space 49.
• a cavity 97 is formed by the platforms 17A, 17B of the rotor blades 13A, 13B which adjoin one another in the circumferential direction of the rotor disk 29. This adjoins the gap 73 radially outward (box design of the rotor blades 13A, 13B).
• the gap sealing element 85 on the one hand prevents the possible entry of hot gas A from the intermediate space 49 through the gap 73 radially outwards into the
• Cavity 97 On the other hand, the cavity 97 sealed by the gap sealing element 85 can be filled with a coolant K, e.g. with cooling air K, are applied.
• the coolant K is supplied to the cavity 97 under pressure and is available there for efficient internal cooling of the thermally highly loaded blades 13A, 13B or for other cooling purposes.
• the blocking effect of a pressurized coolant K in the cavity 97 with respect to the hot gas A in the flow channel can be used.
• the gap sealing element 85 is made from a high-temperature-resistant material, in particular from a nickel-based or cobalt-based alloy.
• FIG. 12 shows a section of a view of the arrangement shown in FIG. 11 along the section line XII-XII.
• the gap sealing element 85 is arranged in the intermediate space 49 and adjoins the sealing element 53 radially outwards.
• the gap sealing element 85 becomes firm against the disc-side base 63 of the adjacent platforms as a result of the rotation by the centrifugal force directed radially outwards along the longitudinal axis 47 17A, 17B, the gap sealing edge 87 engaging in the gap 73 and thereby largely closing the gap 73.
• the sealing system 51 essentially reduces the axially directed leakage flows, while the gap sealing element 85 substantially reduces the radially directed leakage flows (cf. FIG. 11).
• the gap sealing element 85 and the sealing system 51 complement each other very effectively in this way.
• FIG. 13 shows a perspective view of a rotor shaft 89 of a rotor 25 which extends along an axis of rotation 15.
• a receiving structure 33 is produced by a plurality of axially spaced circumferential grooves 91 which extend over the full circumference of the rotor shaft 89 and are machined into the circumferential surface 31.
• the peripheral surface 31 has a first peripheral surface 93 and a second peripheral surface 95 lying opposite the first peripheral surface 93 along the axis of rotation 15.
• the first peripheral surface 93 and the second peripheral surface 95 each axially adjoin a peripheral groove 91.
• FIG. 14 shows a sectional view of a section of a rotor 25 with a circumferential groove 91 and with a rotor blade 13 inserted.
• the circumferential groove 91 is produced as a hammer head groove which receives the blade root 43.
• this type of blade attachment is preferably used.
• a sealing element 53 is provided in the intermediate space 49 of the first peripheral surface 93 and on the second peripheral surface 95. The sealing element 53 extends in the circumferential direction of the rotor shaft 89 and engages in a recess 35, in particular in a groove, in the rotor shaft 89.
• Sealing element 53 is arranged to be radially movable in the recess 35.
• the sealing element 53 will move radially outward under the action of centrifugal force along the longitudinal axis 47 of the rotor blade 13 and firmly against the disc-side base
• the sealing element 53 can be composed of two intermeshing partial sealing elements 67A, 67B, which are not shown in FIG. 14 (cf. FIG. 4 and FIGS. 5A-5D and 6A-6D).
• FIG. 15 shows a sectional view of a section of a rotor 25 with an alternative embodiment of the rotor blade attachment to that shown in FIG. 14.
• the circumferential groove 91 is produced by a so-called circumferential fir tree groove.
• the blade root 43 of the rotor blade 13 is accordingly produced as a fir tree root which engages in the circumferential groove 91, in particular in the circumferential fir tree groove.
• This type of attachment of the rotor blade 13 results in a very effective power transmission to the rotor shaft 89 and a particularly secure hold when the rotor 25 rotates about the axis of rotation 15.
• a sealing element 53 for sealing the intermediate space 49 is provided on the first peripheral surface 93 and on the second peripheral surface 95 in the intermediate space 49.
• the specified concept for sealing the intermediate space 49 can in any case be transferred very flexibly to a rotor 25, the rotor blade 13 of which is fastened in a circumferential groove 91.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

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• 2000
  • 2000-05-15 WO PCT/DE2000/001550 patent/WO2000070191A1/de not_active Application Discontinuation
  • 2000-05-15 CN CN00810134A patent/CN1360660A/zh active Pending
  • 2000-05-15 EP EP00938559A patent/EP1180197A1/de not_active Withdrawn
  • 2000-05-15 JP JP2000618586A patent/JP2002544430A/ja not_active Withdrawn
  • 2000-05-15 KR KR1020017014507A patent/KR20020005747A/ko not_active Application Discontinuation
  • 2000-05-15 CA CA002372740A patent/CA2372740A1/en not_active Abandoned
  • 2000-05-15 US US09/979,401 patent/US6682307B1/en not_active Expired - Fee Related

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