EP4168655A1 - Couronne directrice modulaire pour un étage de turbine d'une turbomachine - Google Patents

Couronne directrice modulaire pour un étage de turbine d'une turbomachine

Info

Publication number
EP4168655A1
EP4168655A1 EP21734335.9A EP21734335A EP4168655A1 EP 4168655 A1 EP4168655 A1 EP 4168655A1 EP 21734335 A EP21734335 A EP 21734335A EP 4168655 A1 EP4168655 A1 EP 4168655A1
Authority
EP
European Patent Office
Prior art keywords
ring
blade
module
nozzle ring
modular nozzle
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.)
Withdrawn
Application number
EP21734335.9A
Other languages
German (de)
English (en)
Inventor
Joel Schlienger
Martin Thiele
Rene Mettler
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.)
Turbo Systems Switzerland Ltd
Original Assignee
Turbo Systems Switzerland Ltd
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 Turbo Systems Switzerland Ltd filed Critical Turbo Systems Switzerland Ltd
Publication of EP4168655A1 publication Critical patent/EP4168655A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F01D11/06Control thereof
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04Antivibration arrangements
    • F01D25/06Antivibration arrangements for preventing blade vibration
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24Casings; Casing parts, e.g. diaphragms, casing fastenings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/10Anti- vibration means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00Application
    • F05D2220/40Application in turbochargers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/60Assembly methods
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/30Retaining components in desired mutual position
    • F05D2260/36Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/30Retaining components in desired mutual position
    • F05D2260/38Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/96Preventing, counteracting or reducing vibration or noise
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/12Improving ICE efficiencies

Definitions

  • the present disclosure relates to a modular nozzle ring for a
  • Turbine stage of a flow machine a blade module for a modular nozzle ring of a turbine stage, and the use of a carrier system for a modular nozzle ring,
  • exhaust gas turbochargers with a compressor upstream of the engine, a common shaft and the associated turbine are used in the exhaust gas tract of the internal combustion engine as standard nowadays.
  • the exhaust gas turbocharger used for this consists of a standard rotor, comprising a compressor wheel, a turbine wheel and a connecting shaft as well as the bearing, the flow-guiding housing parts (e.g. the compressor housing and turbine housing) and the bearing housing in between.
  • Turbocharger's important power is first transferred to the rotating shaft via a turbine wheel and then to the connected compressor wheel. In this way, air can be sucked in from the vicinity of the compressor, compressed and pressed into the cylinders of the engine with a high discharge pressure and filling level.
  • the power from the hot engine exhaust gas is obtained in terms of flow technology through targeted swirl extraction in the turbine wheel and transferred to the shaft.
  • nozzle rings are often used between the turbine volute casing and the turbine wheel to generate this swirl.
  • the nozzle ring is usually composed of several flow profiles, so-called nozzle ring blades, and generates an operationally dependent swirl flow on the rotating turbine wheel located downstream through the fixed setting of a profile angle.
  • the essential property of the nozzle ring is to adjust the inlet swirl into the turbine wheel by selecting the blade angle so that ideal operation is made possible for the engine.
  • the area of the flow channels and the specification of the nozzle ring as well as the flow velocities at the outlet of the nozzle ring therefore also change.
  • the swirl extraction in the rotating turbine wheel therefore also changes for a given inlet mass flow and operating point of the engine.
  • the nozzle rings are used at high exhaust gas temperatures of up to 700 ° C, in erosive media and at high flow velocities. High-quality and usually expensive base materials must be used in order to ensure that the nozzle ring is robust during operation.
  • the nozzle rings are usually made of cast steel and then machined to finished size. In some cases, the nozzle rings are also milled to measure from the solid for a desired specification, provided the geometry allows it.
  • Nozzle ring for a turbine stage of a turbo machine according to claim 1. Furthermore, the object is achieved by a blade module for a modular nozzle ring of a turbine stage according to claim 15, and by using a carrier system for a modular nozzle ring according to claim 16. Further embodiments, modifications and improvements result based on the following description and the appended claims.
  • the modular nozzle ring has a carrier system having an adjusting ring, and a vane module having an airfoil.
  • the shovel module is detachably connected to the carrier system.
  • the unchangeable setting angle of the airfoil is determined by the carrier system, in particular by the setting ring spaced from a flow channel.
  • the blade module is also set up to be releasably pressed, in particular by the adjusting ring, onto a turbine housing part on the flow side,
  • the modular nozzle ring can also be referred to as a modular fixed geometry nozzle ring.
  • the modular nozzle ring enables the use of a large number of
  • vane module or nozzle ring vane module disclosed herein is provided as a common part.
  • Components of the carrier system, typically only the setting ring, are individually manufactured for the setting angle desired for the respective application.
  • the modular nozzle ring disclosed herein enables the definition of the
  • the variety of specifications that is often required with regard to different setting angles can be implemented by storing an assortment of setting rings specific to the setting angle required in each case. High storage costs can be reduced considerably since, according to the present disclosure, only identical parts and a set of specifically manufactured adjustment rings are stored. Usually up to 20 different blade pitch angles are required for a certain size of a turbine stage.
  • Embodiments reduce model costs for the nozzle ring, since only the setting ring is varied specifically for the required angle. In the prior art, there is a very high investment outlay for the model costs for the enormous number of different variants of nozzle rings.
  • the modular nozzle ring is designed to be releasably attached to the turbine stage.
  • the carrier system can, for example, be inserted or braced in a housing part of the turbine stage.
  • the shovel module is detachably connected to the carrier system.
  • the blade module is designed to be releasably pressed against a turbine housing part on the flow side.
  • the modular nozzle ring disclosed herein is thus demountable. For example, in the event of possible wear of the blade module, the modular nozzle ring can be removed from the turbine stage, the worn blade module can be replaced and the turbine stage can then be reassembled.
  • a damaged blade module can easily be replaced with a new blade module in the event of service, and the existing nozzle ring and all other components of the turbine stage can continue to be used.
  • the existing nozzle ring and all other components of the turbine stage can continue to be used.
  • a complete replacement of the nozzle ring is necessary in the event of wear.
  • the blade module defines a longitudinal axis starting from one end of the
  • flow side indicates a direction along the longitudinal axis and is to be understood as a direction facing a flow channel or, in the case of several, the primary flow channel.
  • bearing side indicates a direction along the longitudinal axis that is essentially opposite to the flow-side space.
  • the blade module has at a flow-side end section that
  • the blade module has the footplate.
  • the footplate is typically cylindrical and flat (ie has a small extension along the longitudinal axis).
  • the base plate can be set up to form a closure, or in other words a housing wall section, of the (primary) flow channel.
  • the blade module can have a seal connected to the footplate or integrated into the footplate, for example lamellar sealing rings. The seal can seal the base plate radially around the (primary) flow channel! to be sealed from the bearing-side end of the footplate.
  • the blade module has on the bearing side from the
  • Base plate has an axially (along the longitudinal axis) extended blade shaft.
  • the blade shaft is arranged essentially axially in the center and typically extends over part of the cross section of the footplate,
  • the adjustment ring of the carrier system can have a blade shaft opening.
  • the blade shaft opening has an extension that corresponds at least to the cross section of the blade shaft.
  • the blade shaft opening of the adjustment ring is designed to pass through the blade shaft of the blade module.
  • a bearing-side end section of the blade shaft can be arranged at least partially in the blade shaft opening of the adjusting ring. Typically, one end of the blade shaft on the bearing side protrudes from the setting ring,
  • the shovel shaft can enable the shovel module to be secured on the setting ring in such a way that the end of the shovel shaft on the bearing side, which protrudes from the shovel shaft opening of the setting ring on the bearing side, is held by the setting ring on the bearing side and is prevented from passing through the shovel shaft opening of the setting ring,
  • the modular nozzle ring and in particular the carrier system, can be a
  • the securing element can be detachably connected to the end of the blade shaft on the bearing side.
  • a cross section of the securing element can be larger than a cross section of the blade shaft opening of the setting ring or, alternatively, can have a geometry that prevents the securing element from passing through the vane shaft opening on the flow side. This prevents the blade shaft from “falling out”, and thus the entire blade module, in the flow-side direction.
  • the blade module can be moved axially in the bearing-side direction,
  • the securing element is typically a securing ring, for example a snap ring or retaining ring.
  • the end section of the blade shaft on the bearing side can be cylindrical and / or the blade shaft opening can be circular.
  • the diameter of the locking ring can be larger than the diameter of the blade shaft opening.
  • the securing element can also be, for example, a securing pin or a securing needle.
  • the securing element is a nut, the end of the blade shaft on the bearing side having an axially delimited thread,
  • the end of the blade shaft on the bearing side can have a securing groove.
  • the securing element in particular the securing ring, can be in the securing groove be arranged.
  • the securing element, in particular the securing ring can be detachably connected to the securing groove in a form-fitting manner.
  • the securing element is a screw.
  • the end of the blade shaft on the bearing side can have an internal thread.
  • the vane shaft typically does not point out of the setting ring on the bearing side.
  • the screw can be screwed into the blade shaft with axial play in such a way that the blade module and the setting ring can be clamped / pressed on by a clamping element described below.
  • the shovel shaft is used in addition to securing the shovel module by means of the
  • Securing element also guiding and stabilizing, and thus holding together various components of the modular nozzle ring (such as a tensioning element described below).
  • the blade module has on the bearing side of the
  • Base plate an axially (along the longitudinal axis) extended support structure.
  • the support structure is arranged at a radial end section of the blade module and can extend as far as the radial end of the blade module.
  • the stump structure can extend over a partial circumference or over the entire circumference of the blade module.
  • the support structure can have several support struts. In one embodiment, the support structure has two support struts. In the case of two support struts, the support struts can be arranged at approximately 180 ° to one another, i.e. at approximately opposite radial end sections of the vane module. However, other angles are also possible.
  • the outer surface (s) of the support structure i.e. at the radial end of the
  • Blade module can be designed cylindrical.
  • the outer surface (s) of the support structure can have essentially the same shape as the footplate, but in some embodiments is tapered compared to the footplate.
  • a cross section of the outer surface of the support structure can thus be smaller than the cross section of the footplate.
  • the inner surface (s) of the support structure is preferably arranged at a distance from the blade shaft.
  • a gap or cavity, which preferably extends over the entire circumference of the blade shaft, is arranged between the support structure and the blade shaft
  • the blade module has at least one, typically at least two, connecting elements at an end on the bearing side.
  • the at least one connecting element is arranged on the bearing-side end of the support structure.
  • the support structure can have the corresponding number of support struts, wherein one of the connecting elements can be arranged at the bearing-side end of one of the support struts,
  • the adjusting ring also has at least one groove, preferably at least two
  • the at least one groove can have the shape of a notch. However, the groove is preferably an axially continuous opening.
  • the setting angle of the airfoil is set on the setting ring by a releasable connection between the at least one connecting element and the at least one groove. In relation to the setting angle, i.e. the degree of freedom of rotation, the connection can be viewed as form-fitting.
  • the groove can be dimensioned according to the connecting element.
  • the groove can have a shape corresponding to the cross section of the connecting element and / or have a slightly larger cross section than the connecting element. This minimizes "play" with regard to the setting angle.
  • the connecting element has the shape of a cam.
  • the blade module has a first and a second connecting element.
  • the adjustment ring has a first and a second groove per vane module.
  • the connecting elements and / or the grooves are arranged or designed in such a way that only a predefined connection or installation position and thus a predefined setting angle is possible.
  • the connecting elements and the grooves of the respective support structures are not arranged opposite one another (i.e. at an angle other than 180 °, for example 130 °).
  • Groove and / or the first and second connecting elements have different cross-sections (cross-sectional sizes) and / or different cross-sectional shapes (circular, square, etc.).
  • the first connecting element can be dimensioned corresponding to the first groove
  • the second connecting element can be dimensioned corresponding to the second groove. “Correspondingly dimensioned” means that the groove and connecting element have a comparable cross-section and / or a comparable cross-sectional shape (circular, square, etc.).
  • the first and second connecting elements can have different cross-sections and / or the first and second groove can have different cross-sections.
  • the vane module has the first and second connecting elements.
  • the first and second connecting elements are arranged approximately opposite one another and each have the shape of a cam.
  • the first cam has a greater extent along one side than the second cam.
  • the first and second grooves are designed corresponding to the first and second cams.
  • connecting elements and grooves are arranged or designed in such a way that only a predefined connection or installation position and thus a predefined setting angle is possible.
  • the provision of two or more connecting elements increases the mechanical stability of the modular nozzle ring.
  • the adjustment ring can be specific for the desired adjustment angle of the
  • the adjusting ring has a flat, cylindrical shape.
  • the setting ring can have a vane shaft opening and at least one, preferably at least two, grooves per vane module spaced apart from the vane shaft opening.
  • the desired setting angle of the airfoil can be achieved by the
  • Positioning of the at least one groove can be predetermined.
  • Modular nozzle rings according to the present disclosure enable the nozzle ring specification to be determined only on the day of assembly, with only an assortment of adjustment rings in stock being required for commonly used blade adjustment angles.
  • the connection between the groove and the connecting element is usually not permanently established (e.g. by means of a material connection). In the event of maintenance, a damaged blade module can therefore easily be removed and replaced with a new blade module.
  • the blade module is set up to be releasably pressed against a turbine housing part on the flow side by the carrier system, in particular the adjusting ring.
  • the blade module is preferably set up to be resiliently pressed against the turbine housing part on the flow side.
  • the modular nozzle ring comprises a
  • the tensioning element can be, for example, a tensioning spring or a plate spring.
  • the tensioning element is set up to act against the carrier system, in particular the adjusting ring. A resilient pressing of the blade module against the flow-side
  • the turbine housing part can take place in that the clamping element acts against the carrier system and the carrier system presses the blade module against the turbine housing part on the flow side (through an indirect action of the clamping element on the blade module).
  • the clamping element is preferably set up to act against the carrier system, in particular the adjusting ring, and the blade module. In this way, a force can be transmitted from the carrier system, in particular the adjusting ring, to the clamping element and from the clamping element to the blade module.
  • the tensioning element can be arranged between the adjusting ring and the footplate and / or be arranged within the gap or cavity formed between the support structure and the blade shaft.
  • the clamping element can be arranged concentrically around the blade shaft and / or concentrically within the support structure.
  • the blade shaft and / or the support structure prevent the clamping element from slipping.
  • the clamping element can be supported against the bearing-side end of the footplate of the shovel module.
  • an intermediate part can also be arranged between the tensioning element and the base plate.
  • the tensioning element is set up for this purpose
  • the blade module is axially pressed against the turbine housing part on the flow side, in particular by supporting the clamping element against the footplate of the blade module.
  • the pressing can take place against a support surface or a channel contour of the turbine housing part on the flow side.
  • the flow-side end of the airfoil can be braced axially on contact with the channel contour of the turbine housing part.
  • the tensioning element thus functions as a compression spring.
  • the clamping element is set up to press the blade module against the turbine housing part on the flow side without any gaps. This avoids a gap between the flow-side end of the airfoil and the channel contour of the turbine housing part, which can lead to an improvement in the efficiency of the turbine stage.
  • the clamping element can also be configured to axially press the setting ring against a housing part of the turbo machine on the bearing side.
  • the tensioning element can be supported against a support surface of the adjusting ring on the flow side.
  • the support surface can be arranged between the blade shaft opening and the at least one groove.
  • an intermediate part can also be used between the clamping element and the support surface of the adjusting ring be arranged.
  • the end of the setting ring on the bearing side can be clamped axially in contact with a bearing surface or a mating contour of the housing part on the bearing side.
  • Turbine housing part and in particular the pretension between the tensioning element and adjusting ring and tensioning element and base plate, the components of the modular nozzle ring are axially tensioned and are thus secured against vibration forces during operation.
  • This pretensioning of the components reduces the risk of frictional wear at the connecting surfaces between the components of the nozzle ring and the housing, thereby enabling a long service life and avoiding possible failure of the nozzle ring construction.
  • the carrier system can also have a carrier ring.
  • the carrier ring is set up to accommodate the adjustment ring.
  • the carrier ring can have a circular recess or notch in which the adjusting ring is inserted.
  • the adjusting ring is thus arranged on the bearing side of the carrier ring.
  • the carrier ring can be set up to prevent the adjustment ring from moving in the flow-side direction.
  • the carrier ring is typically not designed to prevent movement of the adjustment ring on the bearing side.
  • the carrier ring can also have a heat shield or a heat layer.
  • the carrier ring may have an axially expanded opening into which the
  • the bucket module is partially inserted.
  • the opening of the carrier ring serves as a receptacle for the support structure and / or the blade shaft.
  • the opening of the carrier ring can also serve to guide the support structure.
  • the opening can advantageously have a slightly larger cross section than the outer surface of the support structure.
  • the carrier ring can also serve at least partially as a receptacle for the footplate.
  • the opening can be cylindrical.
  • the opening of the carrier ring can have a cross-sectional shape that corresponds to the footplate.
  • One side of the carrier ring can face the (primary) flow channel.
  • a section of the side facing the flow channel can, in particular together with the footplate, form a closure, or in other words a housing wall section, of the (primary) flow channel.
  • the seal connected to the footplate or integrated into the footplate is set up to seal the footplate at the bearing-side end or at a radial end against the carrier ring.
  • the adjusting ring is arranged at a distance from the flow channel or is not or substantially not exposed to the primary flow.
  • the tensioning element, the support structure and the blade shaft are not or substantially not exposed to the main flow.
  • the carrier ring can be designed to be axially braced between the bearing-side housing part and the flow-side turbine housing part will.
  • the carrier ring can be manufactured as an identical part, regardless of a desired one
  • the opening of the carrier ring has a first cross section at the flow-side end of the opening which is at least as large or slightly larger than the cross section of the footplate.
  • the opening On the bearing side from the flow-side end of the opening, i.e. from a flow-side end section of the opening to a bearing-side end of the opening, the opening has a second cross section.
  • the opening tapers from the first cross section to the second cross section in a stepped manner or, in other words, the opening can have a shoulder.
  • the second cross section of the opening can be smaller than the cross section of the footplate.
  • the second cross section can be slightly larger than the cross section of the outer surface of the support structure.
  • the opening of the carrier ring and the base plate each have a cylindrical shape.
  • the opening tapers in steps from a first diameter at the flow-side end to a smaller second diameter on the bearing side from the flow-side end.
  • the second diameter is smaller than the diameter of the footplate.
  • the opening can thus serve as a receptacle and for guiding the support structure.
  • the second cross section restricts the freedom of movement of the footplate in the bearing-side direction.
  • the carrier ring can be set up to be axially braced between the bearing-side housing part and the flow-side turbine housing part, and to limit the movement of the adjustment ring in the flow-side direction and optionally to limit the movement of the footplate, and thus of the blade module, in the bearing-side direction.
  • the combination of setting ring and vane module thus has a certain "axial play" between the housing parts in the assembled state, but can be limited by the carrier ring. This advantageously increases safety and simplifies the assembly of the modular carrier ring
  • the use of a tensioning element can also be used to prevent the vane module from "falling out" of the setting ring on the flow side by using the securing element connected to the vane shaft.
  • the opening of the carrier ring can also be a continuous opening with a constant cross section or diameter in the axial direction, in particular without a shoulder.
  • the blade can have a larger cross section or a larger width than the opening and / or the footplate.
  • the shovel module can be used in an identical form for all setting angles and can thus be placed as a common part.
  • the airfoil, the blade shaft, the footplate and the support structure can be formed integrally or in one piece.
  • the entire blade module can be formed integrally.
  • the vane module can be obtained by a metal injection molding process.
  • no reworking is required on the blade module following a metal powder injection molding process.
  • a vane module suitable for an application can be obtained directly by a metal powder injection molding process.
  • the manufacturing and component costs for the modular nozzle ring can be kept very low.
  • the adjusting ring can be prepared as a blank, for example from a highly heat-resistant and heat-resistant sheet metal as a ring, executed with a predetermined thickness and placed in stock in an unprocessed state and at low cost.
  • the at least one groove can be worked into the blank after setting an adjustment angle.
  • an assortment of setting rings for a large number of setting angles can be prepared for later assembly and stored in stock.
  • the grooves of the setting ring can be obtained, for example, by laser cutting or water jet cutting. In particular, the water jet method can be implemented easily and inexpensively.
  • the tensioning element in particular the tensioning spring, is made of a heat-resistant material.
  • the securing element in particular the securing ring, is also made from a heat-resistant material.
  • the modular nozzle ring has a plurality or a combination of vane modules.
  • Each of the blade modules is detachably connected to the carrier system, in particular the adjusting ring.
  • the adjustment ring can have a blade shaft opening and at least one groove per blade module.
  • the modular nozzle ring has a clamping element for each blade module.
  • the tensioning element acts against the carrier system, in particular the adjusting ring.
  • the carrier ring can each have an opening for each of the blade modules.
  • a turbine stage is a
  • the turbine stage has a modular nozzle ring according to any of those disclosed herein Embodiments on.
  • the turbine stage also has a turbine wheel and a turbine housing or volute.
  • the turbine stage optionally has an outlet diffuser in an outlet area.
  • the modular nozzle ring can be arranged between the turbine housing (spiral) and the turbine wheel.
  • the blade shaft and / or the blade is oriented in the direction of the rotor axis of the turbine wheel.
  • the components of the turbine stage can be manufactured as identical parts, regardless of a desired setting angle (with the exception of the adjustment ring mentioned above), in particular the turbine housing and a turbine wheel can be designed as identical parts.
  • the turbine stage can have the bearing-side housing part and / or the flow-side turbine housing part.
  • the housing part on the bearing side, together with the base plate and / or the carrier ring, can form a first flow wall or flow wall on the hub side for the (primary) flow channel.
  • the turbine housing part on the flow side, which is arranged for the releasable contact pressure of the blade module, forms a second flow wall for the (primary) flow channel.
  • the second flow wall is arranged opposite the first flow wall.
  • the turbine stage can also be set up for a bearing-side
  • the gas inflow on the bearing side enables gas to flow in from the base plate on the bearing side. In this way, a gas pressure similar to or higher than the (primary) flow channel can also be achieved on the bearing side of the footplate.
  • the gas inflow on the bearing side enables mechanical relief and thus an increase in the service life of the components of the modular nozzle ring, in particular of the clamping element.
  • the housing part on the bearing side can have an opening which is connected to a gas connection.
  • the gas inflow on the bearing side can be provided by means of sealing air on the compressor side from the compressor stage or by means of sealing air to be connected externally.
  • the blade module is further configured to be releasably pressed against a turbine housing part on the flow side by means of sealing air.
  • the turbine stage can be assembled by inserting the modular
  • Nozzle ring and the turbine wheel in the bearing-side housing part then placing the flow-side turbine housing part and axially bracing the housing parts.
  • the turbine stage is set up to axially compress the modular nozzle ring by axially bracing the bearing-side housing part and the flow-side turbine housing part.
  • the axial compression in combination with the clamping element enables the blade module to be pressed against the turbine housing part on the flow side without any gaps.
  • the vane module can have any of the features of the vane module disclosed above in connection with the modular nozzle ring. Some of the aspects are summarized below.
  • the blade module has a blade and at least one connecting element, in particular a cam, arranged at an end on the bearing side.
  • the connecting element is set up to set an adjustment angle of the airfoil through a connection between the connecting element and a groove of a carrier system, in particular an adjusting ring of the carrier system, of the modular nozzle ring,
  • the shovel module in particular the shovel blade, can be detached
  • the blade is preferably set up for resilient pressing against a turbine housing part on the flow side.
  • the blade module has on the bearing side of one
  • Footplate of the blade module has an axially extended blade shaft.
  • the blade shaft is arranged essentially axially in the center and typically extends over part of the cross section of the footplate.
  • An end section of the blade shaft on the bearing side can be configured at least partially into a blade shaft opening of the setting ring and / or an end of the blade shaft on the bearing side can be configured to protrude from the setting ring on the bearing side,
  • the blade shaft can be designed to be secured on the setting ring, in particular by means of a securing element.
  • the end of the blade shaft on the bearing side can have a securing groove for receiving and / or fixing a securing element.
  • the blade module has on the bearing side of the
  • Base plate an axially (along the longitudinal axis) extended support structure.
  • the support structure is arranged on a radial end section of the blade module and can extend as far as the radial end of the blade module.
  • the support structure can extend over a partial circumference or also over the entire circumference of the blade module.
  • the support structure can have several support struts.
  • the support structure typically has two support struts. In the case of two support struts, the support struts are preferably arranged at approximately 180 ° to one another, ie approximately at opposite radial end sections of the vane module. However, other angles are also possible.
  • An inner surface (s) of the support structure is preferably spaced from the
  • Blade shaft arranged.
  • a gap or cavity preferably extending over the entire circumference of the blade shaft, is arranged between the support structure and the blade shaft.
  • the gap or cavity can be designed to accommodate a clamping element.
  • the at least one connecting element is at the end of the bearing
  • the support structure can have the corresponding number of support struts, one of the connection elements being able to be arranged at the bearing-side end of one of the support struts.
  • the use of a carrier system for a modular nozzle ring is provided.
  • the carrier system can have any of the features of the carrier system disclosed above in connection with the modular nozzle ring.
  • the carrier system has an adjusting ring, and in particular a carrier ring.
  • FIG. 1 shows part of a modular nozzle ring according to a
  • Figure 2 shows part of a modular nozzle ring according to a
  • FIG. 3 shows a blade module for a modular nozzle ring according to one
  • FIG. 4 shows part of a carrier system according to one embodiment.
  • FIG. 5 shows part of a modular nozzle ring according to one
  • FIG. 6 shows part of a modular nozzle ring according to a
  • FIG. 7 shows part of a modular nozzle ring according to one
  • FIG. 8 shows part of a carrier system according to one embodiment.
  • FIG. 9 shows part of a modular nozzle ring according to a
  • FIG. 10 shows part of a modular nozzle ring according to a
  • FIG. 11 shows part of a modular nozzle ring according to a
  • FIG. 12 shows part of a modular nozzle ring according to one
  • FIG. 1 shows part of a modular nozzle ring 100 for a turbine stage of a turbomachine.
  • the modular nozzle ring is shown installed in a turbine stage.
  • the modular nozzle ring 100 has a blade module 300 and a carrier system 200.
  • the blade module 300 has the airfoil 326 at an end section on the flow side.
  • the blade module 300 On the bearing side of the blade 326, the blade module 300 has a base plate 309.
  • the footplate 309 is typically set up to form a closure, or in other words a housing wall section, of the (primary) flow channel 120.
  • the blade module 300 On the bearing side of the base plate 309, the blade module 300 has a lateral, axially extended support structure 313.
  • the support structure 313 can have a plurality of support struts 317, 318.
  • the blade module 300 shown in FIG. 3 has, for example two support struts 317, 318 which are arranged at approximately 180 ° to one another, ie approximately at opposite radial end sections of the blade module 300.
  • Support struts 317, 318, two connecting elements 330, 331 are arranged.
  • the connecting elements shown in Figure 3 have the shape of a cam.
  • the two cams 330, 331 have a similar cross-sectional shape, but have a different cross-section (or cross-sectional size ⁇ 314, 315.
  • the different cross-sections 314, 315 enable a setting angle ⁇ of the blade 326 to be clearly defined and, for example, prevent the blade module from turning Rotated 180 ° can be fixed on the carrier system 200 and thereby the blade profile angle is set incorrectly, or the blade is aligned the wrong way round to the direction of flow,
  • Adjustment surfaces 316 are located to the side of the ends 314, 315 of the cams on the bearing side
  • the adjustment surfaces 316 are configured to contact the grooves (described below) of the adjustment ring to establish a setting angle.
  • the vane module 300 furthermore has a vane shaft 310.
  • the blade shaft 310 extends from the base plate 309 to a bearing-side end of the blade module 300.
  • the blade shaft 310 is essentially axial and can also be arranged centrally.
  • a securing groove 325 is arranged on an end section of the blade shaft 310 on the bearing side. The securing groove 325 is not labeled in FIG. 3 and can best be seen in FIG.
  • the carrier system comprises an adjustment ring 203. A portion of the
  • Adjustment ring 203 is shown separately in FIG. 8 (not built into the modular nozzle ring 100).
  • the adjusting ring 203 has a blade shaft for each blade module 300
  • the shovel module 300 can be secured to the shovel shaft 310 on the bearing side.
  • the modular nozzle ring 100 has a securing element 208.
  • the securing element 208 can be, for example, a securing ring 208, as can be seen clearly in FIGS. 7 and 9.
  • the securing element 208 prevents the vane module 300 from “slipping out” of the adjusting ring 203 on the flow side.
  • the adjusting ring 203 has at least one groove for each blade module 300
  • the setting angle ⁇ is determined by a connection between the precise cam 330, 331 of the blade module and the corresponding and precisely dimensioned groove 220, 222 of the setting ring 203.
  • the setting surfaces 316 of the cams 330, 331 each enter with the grooves 220, 222 on both sides Contact.
  • the correct installation position of the blade module 300 is ensured by the cams 330, 331 and grooves 220, 222 each having different cross sections, and only one installation position is therefore possible.
  • the carrier system can have a carrier ring 202, which is shown in FIG.
  • FIG. 2 shows a larger view of the modular nozzle ring 100 from FIG. 1.
  • the carrier ring 202 is set up to receive the setting ring 203.
  • the carrier ring 202 has a circular recess into which the adjusting ring 203 is inserted.
  • the end of the carrier ring 202 on the bearing side and the circular recess are visible in FIG. 4, for example.
  • the setting ring 203 can be inserted into the carrier ring 202 without being attached to the carrier ring 202.
  • the carrier ring 202 has a multiplicity of openings 210 which serve to receive the blade modules 300 (only one of the openings 210 is labeled in FIG. 4). In this case, the blade can be securely guided through cylindrical outer surfaces of the support structure 313 in the opening 210 of the carrier ring 202 and within a remaining radial residual gap.
  • the carrier ring 202 has a central opening for receiving a
  • the carrier ring 202 is fixed by a housing part 104 on the bearing side.
  • the carrier ring 202 can also be axially braced between the housing part 104 on the bearing side and a turbine housing part 112 on the flow side.
  • the modular nozzle ring can further comprise a tensioning element 106.
  • FIGS. 1 and 2 show a tension spring 106 as embodiments of the tensioning element.
  • the tensioning element 106 is set up to act against the setting ring 203 and the blade module 300. In this way, power can be transmitted from the carrier system 200, in particular the setting ring 203, to the clamping element 106 and from the clamping element 106 to the shovel module 300.
  • the tensioning element 106 is between the adjusting ring 203 and the footplate
  • the tensioning element 106 is supported against the the end of the footplate 309 of the shovel module 300 on the bearing side.
  • the tensioning element 106 is also supported against a support surface of the adjusting ring 203 on the flow side.
  • Figure 5 shows the combination of setting ring 203 and a variety
  • Shovel modules 300 The shovel modules 300 are fixed in the setting angles a by the connection with the grooves and secured by means of the securing elements 208.
  • the tensioning element 106 leads to tension in the assembly of adjusting ring 203 and vane modules 300.
  • FIG. 6 shows a combination of FIGS. 4 and 5, i.e. the combination of carrier ring 202, adjustment ring 203 and a large number of blade modules 300.
  • a section of this assembly is shown in FIGS. 9 and 10 for a blade module 300
  • FIG. 7 shows a detail from FIG. 6 as an exploded drawing.
  • the narrow dash-dotted line illustrates the longitudinal axis, and the two arrows marked in bold indicate the bearing-side direction along the longitudinal axis.
  • Figure 8 shows the adjusting ring 203 and the grooves 220, 222 contained therein and the blade shaft opening 221.
  • Figure 8 indicates two different angular positions of the setting angle ⁇ by the two dash-dot lines.
  • the blade shaft opening 221 can be made the same for all setting angles ⁇ .
  • the position of the grooves 220, 222 requires an adaptation to the respectively desired setting angle ⁇ .
  • FIG. 11 also indicates the changes at different setting angles in the middle blade module shown, and in particular the differently arranged blade 326.
  • FIG. 12 shows a section of a rear view from FIG. 11. The positions of the grooves 220, 222 for two different setting angles ⁇ are shown as an example .
  • Nozzle ring 100 installed between the flow-side turbine housing part 112 and the bearing-side housing part 104 of the turbomachine.
  • the housing part 104 on the bearing side can have a recess for receiving the blade shaft 310 protruding from the setting ring 203 on the bearing side.
  • the axial distance between the flow-side turbine housing part 112 and the bearing-side housing part 104 is made shorter than the axial distance between the bearing-side end of the adjustment ring 203 and the flow-side end 327 of the blade 326.
  • the modular nozzle ring 100 is axially through the assembly compressed, whereby the securing elements 208 are axially relieved and the setting ring 203 and the blade 326 are each pressed against the housing part.
  • the bearing-side end of the adjustment ring 203 is set up to the
  • the modular nozzle ring 100 is thus designed axially within the scope of

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne une couronne directrice modulaire pour un étage de turbine d'une turbomachine. Cette couronne directrice modulaire présente un système de support présentant une bague de réglage, ainsi qu'un module aube présentant une ailette. Le module aube est relié au système de support de manière amovible. En outre, un angle de réglage de l'ailette non modifiable, en particulier pendant le fonctionnement, est fixé par le système de support, en particulier par la bague de réglage espacée d'un canal d'écoulement. Le module aube est conçu pour être plaqué de manière amovible, en particulier par la bague de réglage, contre une partie du carter de turbine côté écoulement. L'invention concerne en outre un module aube pour une couronne directrice modulaire d'un étage de turbine, ainsi que l'utilisation d'un système de support pour une couronne directrice modulaire.
EP21734335.9A 2020-06-23 2021-06-21 Couronne directrice modulaire pour un étage de turbine d'une turbomachine Withdrawn EP4168655A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP20181648.5A EP3929407A1 (fr) 2020-06-23 2020-06-23 Bague de tuyère modulaire pour une étage de turbine d'une turbomachine
PCT/EP2021/066845 WO2021259862A1 (fr) 2020-06-23 2021-06-21 Couronne directrice modulaire pour un étage de turbine d'une turbomachine

Publications (1)

Publication Number Publication Date
EP4168655A1 true EP4168655A1 (fr) 2023-04-26

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ID=71138537

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Application Number Title Priority Date Filing Date
EP20181648.5A Withdrawn EP3929407A1 (fr) 2020-06-23 2020-06-23 Bague de tuyère modulaire pour une étage de turbine d'une turbomachine
EP21734335.9A Withdrawn EP4168655A1 (fr) 2020-06-23 2021-06-21 Couronne directrice modulaire pour un étage de turbine d'une turbomachine

Family Applications Before (1)

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EP20181648.5A Withdrawn EP3929407A1 (fr) 2020-06-23 2020-06-23 Bague de tuyère modulaire pour une étage de turbine d'une turbomachine

Country Status (6)

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US (1) US20230235681A1 (fr)
EP (2) EP3929407A1 (fr)
JP (1) JP2023531220A (fr)
KR (1) KR20230028429A (fr)
CN (1) CN115803510A (fr)
WO (1) WO2021259862A1 (fr)

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CN115803510A (zh) 2023-03-14
KR20230028429A (ko) 2023-02-28
JP2023531220A (ja) 2023-07-21
US20230235681A1 (en) 2023-07-27
WO2021259862A1 (fr) 2021-12-30
EP3929407A1 (fr) 2021-12-29

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