EP2242931B1 - Structure d'écoulement pour turbocompresseur - Google Patents

Structure d'écoulement pour turbocompresseur Download PDF

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Publication number
EP2242931B1
EP2242931B1 EP09711862.4A EP09711862A EP2242931B1 EP 2242931 B1 EP2242931 B1 EP 2242931B1 EP 09711862 A EP09711862 A EP 09711862A EP 2242931 B1 EP2242931 B1 EP 2242931B1
Authority
EP
European Patent Office
Prior art keywords
chambers
annular chamber
circulation structure
axial direction
structure according
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.)
Active
Application number
EP09711862.4A
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German (de)
English (en)
Other versions
EP2242931A1 (fr
Inventor
Giovanni Brignole
Carsten Zscherp
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP2242931A1 publication Critical patent/EP2242931A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • Y—GENERAL 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the invention relates to a circulation structure for a turbocompressor according to the preamble of claim 1.
  • a circulation structure is for example from US 6,290,458 known.
  • the invention relates to a turbocompressor and an aircraft engine and a stationary gas turbine.
  • Circulation structures or recirculation structures for turbocompressors are known in the form of so-called “Casing Treatments” and “Hub Treatments.”
  • the "Casing Treatments” and “Hub Treatments” circulation structures have the primary task, the aerodynamically stable operating range of the compressor by optimizing the surge margin An optimized surge margin allows for higher compressor pressures and thus a higher compressor load.
  • the faults responsible for a local stall and ultimately compressor surge occur on the housing-side ends of the blades of one or more compressor stages or on the hub-side radially inner ends of the compressor Since the aerodynamic load in the compressor is highest in these areas, circulation structures stabilize the flow in the area of the blade ends
  • the housing-side ends of the blades are referred to as "Casing Treatments”.
  • Rotor-side circulation structures in the area of the hub-side ends of the guide vanes are referred to as "hub treatments”.
  • the DE 29 24 336 A1 describes a blade tip shroud structure for a gas turbine engine compression stage that includes a circumferentially extending recess in the wall of a housing that surrounds the tips of the blades, with axially tapered grooves and circumferentially extending grooves forming surface discontinuities at the bottom of the recess.
  • a plurality of first recesses are provided in the direction of a fluid pressure gradient on an inner flow surface and second recesses are provided in the circumferential direction for communicating the first recesses in the circumferential direction.
  • the present invention based on the problem to provide a novel circulation structure for a turbocompressor.
  • a plurality of axially permeable chambers are positioned, wherein a radial recess is formed to the main flow channel in the region of the axially permeable chambers.
  • the circulation structure according to the invention therefore combines axially permeable chambers, which have no peripheral connection, with at least one annular chamber, which can be flowed through in the circumferential direction, wherein the or each annular chamber is positioned in the main flow direction downstream of the axially permeable chamber without circumferential connection.
  • a forming recirculation flow uses high-loss fluid to influence the inflow of rotor-side assemblies, the geometric properties of the axially permeable chambers without circumferential connection produce a counter-rotation. Further Strömungsversperrungs whatsoever be relocated in the annular chambers with peripheral connection.
  • the circulation structure according to the invention ensures very low losses due to its simplicity. Loss-producing, three-dimensional flow phenomena can be effectively inhibited. This can have positive effects on the operating stability of the turbocompressor at partial load and full load with an overall positive change in the efficiency, especially at full load, coupled.
  • the simplicity of the circulation structure is associated with low production costs.
  • the invention relates to a circulation structure for a turbocompressor, in particular for a compressor of a gas turbine, which can be designed as a "casing treatment” or as a "stroke treatment.”
  • a circulation structure for a turbocompressor in particular for a compressor of a gas turbine, which can be designed as a "casing treatment” or as a "stroke treatment.”
  • the invention will be described below with reference to FIG Fig. 1 to 19 described on a trained as a "Casing Treatment” circulation structure, which is introduced into a stator-side housing which defines a main flow channel of the turbo compressor radially outward and connects to free blade ends of blades of a rotor-side blade ring.
  • circulation structure according to the invention can also be used analogously as a "stroke treatment", wherein the same is then introduced into a rotor-side hub which radially inwardly delimits the main flow channel of the turbocompressor and adjoins free blade ends of stator vanes of a stator vane ring.
  • Fig. 1 to 4 show different views of a "Casing Treatment" trained, housing-side circulation structure 20, which in stator-side housing 21 of a compressor of a gas turbine is introduced, according to an example that facilitates the understanding of the invention.
  • the housing 21 defines radially outwardly a main flow channel 22, wherein in the main flow channel 22 rotor-side blades 23 of a blade ring 24 rotate. Radially inside the main flow channel 22 is bounded by a hub 25 of the rotor.
  • the circulation structure 20 includes a circumferentially permeable annular chamber 26 disposed concentric with an axis of the compressor in the region of free blade ends of the blades 23 of the blade ring 24.
  • the annular chamber 26 adjoins radially to the main flow channel 22.
  • the annular chamber 26 allows a flow in the circumferential direction and therefore has a peripheral connection.
  • the annular chamber 26 is formed as a circumferential groove, wherein 26 may be positioned to guide the flow within the annular chamber.
  • the annular chamber 26 extends in the axial direction completely in the region of the free blade ends of the blades 23 of the blade ring 24.
  • the axial extent of the annular chamber 26 is in accordance with Fig. 2 characterized by the parameter b.
  • the radial extent of the annular chamber 26 is characterized by the parameter t.
  • An edge of the annular chamber 26 positioned upstream as viewed in the main flow direction is according to FIG Fig. 4 by ek and a downstream positioned edge of the annular chamber 26 indicated by ak.
  • a plurality of axially permeable chambers 27 are positioned.
  • the chambers 27 which can be flowed through in the axial direction are in the form of slots or axial grooves and are not connected to one another in the circumferential direction; the chambers 27 which can be flowed through in the axial direction therefore have no peripheral connection.
  • An upstream edge of the chambers 27 positioned in the main flow direction of the main flow passage 22 is shown in FIG Fig. 4 labeled vk
  • a downstream edge of the chambers 27 seen in the main flow direction of the main flow passage 22 is in FIG Fig. 4 marked with hk.
  • a suction-side edge of the chambers 27 is in Fig. 4 with sk and a pressure-sided edge marked dk, where 3 and 4 a suction side 28 and a pressure side 29 of a blade 23 of the blade ring 24 show.
  • the chambers 27, which can be flowed through in the axial direction, are positioned in sections in the region of the free blade ends of the rotor blades 24 of the rotor blade ring 24 viewed in the axial direction. So shows Fig. 2 with the parameter o, the portion of the axially permeable chambers 27, which extends in the region of the free blade ends of the blades 23 and thus overlaps the blade ring 24.
  • the parameter v shows the portion of the axially permeable chambers 27, which extends completely upstream of the blade ring 24.
  • Fig. 2 illustrates with the parameter h, the radial extent or depth of the traversable in the axial direction brackets 27.
  • a subsequent to the upstream edge vk contour of the chambers 27 is according to Fig. 2 slanted by the angle ⁇ relative to the radially outer contour of the main flow channel 22.
  • a contour of the chambers 27 adjoining the downstream edge hk is inclined at an angle ⁇ with respect to the radially outer contouring of the main flow channel 22. Furthermore, according to Fig. 3 the axially permeable chambers 27 are inclined relative to the radial direction by the angle ⁇ . Viewed in the circumferential direction, the chambers 27, which can be flowed through in the axial direction, have the width c, wherein immediately adjacent chambers 27 have the spacing s in the circumferential direction.
  • Connections or mouth openings 30 of the chambers 27 which can be flowed through in the axial direction into the main flow channel 22 are axially spaced or axially separated from a connection or mouth opening 31 of the annular chamber 26, according to FIG Fig. 2 the axial distance between these mouth openings 30 and 31 is characterized by the parameter a.
  • edges ak and ek of the annular chamber 26 as well as the edges vk, hk, dk and sk of the chambers 27 which can be flowed through in the axial direction and thus the entry surfaces thereof can be described by any curves or splines.
  • Edge surfaces of the annular chamber 26 adjoining these edges and of the chambers 27 which can be flowed through in the axial direction can be defined by generic Nurbs surfaces.
  • the geometry of each individual chamber 27 may differ from the other chambers 27. This applies in particular to the inclination angle ⁇ of the chambers 27, the circumferential distance s of the chambers 27 and the circumferential width c of the chambers 27.
  • Fig. 1 to 4 are at the edges ak and ek of the annular chamber 26 and at the edges vk, hk, dk and sk of the chambers 27 adjacent edge surfaces or outer surfaces generated by rotation of continuously differentiable curves.
  • edge surfaces or outer surfaces of a Polyline in Fig. 6 from a straight line and circle segments and in Fig. 7 generated by simple geometric shapes, such as an ellipse and a rectangle.
  • FIG. 8 shows an embodiment of the invention with a contouring of the housing 21 to form a radial recess to the main flow channel 22 in the region of the axially permeable chambers 27th
  • the parameters ⁇ , ⁇ , h, t and b can assume any value.
  • the parameters o, v and a can assume an arbitrary value, the parameters o and v having to assume a value of greater than zero, in particular in order to ensure an overlap of the axially flow-through chambers 27 with the free blade ends of the rotor blades 24 of the rotor blade ring 24.
  • a pre-stretching of the chambers 27 which can be flowed through in the axial direction can thereby be realized upstream of an inlet edge of the reed blades 23.
  • the parameter a must assume a value greater than zero.
  • Fig. 1 to 4 extend the edges sk and dk of the axially permeable chambers 27 straight in the axial direction of the turbocompressor.
  • Fig. 9 to 15 a different contouring of the suction-side edges sk and the pressure-side edges dk of the chambers 27 which can be flowed through in the axial direction.
  • edges sk and dk of the axially permeable chambers 27 are inclined relative to the axial direction.
  • the edges sk and dk of the axially permeable chambers 27 are bent in the circumferential direction, wherein Fig. 15 the edges sk and dk of the chambers 27 in the region of the downstream edge hk extend approximately tangentially to the suction side and pressure side of the rotor blades 23.
  • Fig. 16 shows an embodiment of the invention with two annular chambers 26, both seen in the main flow direction of the flow channel 22, are positioned downstream of the axially permeable chambers 27.
  • Fig. 17 shows an embodiment of the invention in which the axially permeable chambers 27 are connected to the downstream thereof positioned annular chamber 26 via discrete connections 33. These discrete connections 33 can be actively closed and opened via corresponding control elements so as to set an active regulation of a flow passage between the annular chamber 26 and the chambers 27 which can be flowed through in the axial direction.
  • Fig. 18 shows an embodiment of the invention in which the downstream edge ak of the annular chamber 26 discrete projections 34 so as to increase the axial extent of the mouth opening 31 of the annular chamber 26 in sections.
  • Fig. 19 shows Fig. 19 a contouring of an edge surface or lateral surface nw of the annular chamber 26 with discrete radial projections 35 which reduce the radial extent t of the annular chamber 26 in sections.
  • the invention can also be used when the turbocompressor has a tandem rotor with two directly successive blade rings and / or two directly successive guide blade rings.
  • the circulation structure according to the invention is used in turbocompressors, in particular compressors of a gas turbine designed as an aircraft engine or a stationary gas turbine.

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

Claims (13)

  1. Structure d'écoulement pour un turbocompresseur, notamment pour un compresseur d'une turbine à gaz comprenant au moins une chambre annulaire (26) pouvant être traversée par le fluide dans une direction circonférentielle, qui est disposée de manière concentrique par rapport un axe du turbocompresseur dans la zone des extrémités libres des aubes d'une couronne d'aubes (24) et qui est radialement adjacente un canal d'écoulement principal (22), vu de la direction d'un écoulement principal du canal d'écoulement principal (22), plusieurs chambres (27) pouvant être traversées par le fluide dans une direction axiale étant positionnées en amont de la ou de chaque chambre annulaire (26), caractérisé en ce qu'une échancrure radiale vers le canal d'écoulement principal (22) est façonnée dans la section de la chambre (27) pouvant être traversée par le fluide en direction axiale.
  2. Structure d'écoulement selon la revendication 1, caractérisée en ce que les chambres (27) positionnées en amont de la ou de chaque chambre annulaire (26) sont façonnées en tant qu'interstice ou rainures axiales qui ne sont pas reliées entre elles en direction circonférentielle,
  3. Structure d'écoulement selon la revendication 1 ou 2, caractérisée en ce que la ou chaque chambre annulaire (26) est façonnée en tant que rainure circonférentielle, des éléments de conduite étant préférablement positionnés dans au moins une chambre annulaire.
  4. Structure d'écoulement selon l'une des revendications 1 à 3, caractérisée en ce que les connexions ou embouchures (30) des chambres (27) pouvant être traversées par le fluide en direction axiale dans le canal d'écoulement principal (22) sont écartées axialement et ainsi séparées par une connexion ou une embouchure (31) de la ou de chaque chambre annulaire (26) dans le canal d'écoulement principal.
  5. Structure d'écoulement selon l'une des revendications 1 à 4, caractérisée en ce que les chambres (27) pouvant être traversées par le fluide en direction axiale sont séparées de sorte à ce qu'aucune connexion n'existe entre les chambres (27) pouvant être traversées par le fluide en direction axiale et la chambre annulaire (26) positionnée en aval des chambres (27).
  6. Structure d'écoulement selon l'une des revendications 1 à 4, caractérisée en ce que les chambres (27) pouvant être traversées par le fluide en direction axiale sont connectées à la chambre annulaire (26) positionnée en aval des chambres (27) par l'intermédiaire de connexions discrètes (33).
  7. Structure d'écoulement selon l'une des revendications 6, caractérisée en ce que les connexions discrètes (33) peuvent être fermées et ouvertes activement via les éléments de commande.
  8. Structure d'écoulement selon l'une des revendications 1 à 7, caractérisée en ce que les chambres (27) pouvant être traversées par le fluide en direction axiale, vues en direction axiale, s'étendent par sections dans la zone des extrémités libres des aubes d'une couronne d'aubes (24).
  9. Structure d'écoulement selon l'une des revendications 1 à 8, caractérisée en ce que les chambres (27) pouvant être traversées par le fluide en direction axiale, vues en direction d'écoulement principal du canal d'écoulement principal (22), sont avancées en amont des bords d'entrée des aubes de la couronne d'aubes (24).
  10. Structure d'écoulement selon l'une des revendications 1 à 9, caractérisée en ce que les chambres (27) pouvant être traversées par le fluide en direction axiale, vues en direction d'écoulement principal du canal d'écoulement principal (22), sont avancées en amont des bords d'entrée des aubes de la couronne d'aubes (24).
  11. Turbocompresseur doté d'au moins une structure d'écoulement selon une ou plusieurs des revendications 1 à 10.
  12. Réacteur d'avion doté d'un turbocompresseur selon la revendication 11.
  13. Turbine à gaz stationnaire dotée d'un turbocompresseur selon la revendication 11.
EP09711862.4A 2008-02-21 2009-02-19 Structure d'écoulement pour turbocompresseur Active EP2242931B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008010283A DE102008010283A1 (de) 2008-02-21 2008-02-21 Zirkulationsstruktur für einen Turboverdichter
PCT/DE2009/000230 WO2009103278A1 (fr) 2008-02-21 2009-02-19 Structure d'écoulement pour turbocompresseur

Publications (2)

Publication Number Publication Date
EP2242931A1 EP2242931A1 (fr) 2010-10-27
EP2242931B1 true EP2242931B1 (fr) 2016-11-02

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EP09711862.4A Active EP2242931B1 (fr) 2008-02-21 2009-02-19 Structure d'écoulement pour turbocompresseur

Country Status (6)

Country Link
US (1) US8915699B2 (fr)
EP (1) EP2242931B1 (fr)
CN (1) CN101946094A (fr)
CA (1) CA2716417A1 (fr)
DE (1) DE102008010283A1 (fr)
WO (1) WO2009103278A1 (fr)

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Also Published As

Publication number Publication date
CA2716417A1 (fr) 2009-08-27
WO2009103278A1 (fr) 2009-08-27
CN101946094A (zh) 2011-01-12
US20100329852A1 (en) 2010-12-30
US8915699B2 (en) 2014-12-23
DE102008010283A1 (de) 2009-08-27
EP2242931A1 (fr) 2010-10-27

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