EP1478828A1 - Recirculation structure for turbo chargers - Google Patents

Recirculation structure for turbo chargers

Info

Publication number
EP1478828A1
EP1478828A1 EP03718608A EP03718608A EP1478828A1 EP 1478828 A1 EP1478828 A1 EP 1478828A1 EP 03718608 A EP03718608 A EP 03718608A EP 03718608 A EP03718608 A EP 03718608A EP 1478828 A1 EP1478828 A1 EP 1478828A1
Authority
EP
European Patent Office
Prior art keywords
recirculation
guide elements
structure according
recirculation structure
annular chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP03718608A
Other languages
German (de)
French (fr)
Other versions
EP1478828B1 (en
Inventor
Peter Seitz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1478828A1 publication Critical patent/EP1478828A1/en
Application granted granted Critical
Publication of EP1478828B1 publication Critical patent/EP1478828B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F04D29/66—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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 recirculation structure for turbocompressors, according to the preamble of claim 1, and to an aircraft engine and a stationary gas turbine.
  • DE 33 22 295 C3 protects an axial fan with a generic "casing treatment".
  • Characteristic of this type of "casing treatment” is a closed ring (7), which is approximately aligned with the contour of the main flow channel and separates the rear entry area from the front exit area of the recirculation structure and forms a smooth, closed surface area.
  • a very similar “casing treatment” is known from DE 35 39 604 C1, with an area that is open in the circumferential direction being present in the front and rear area of the ring chamber (7). Also note the radially inner ring 6 here.
  • the object of the invention is to provide a recirculation structure for turbocompressors which enables a significant increase in the surge limit and thus a significant increase in the stable operating range without a relevant deterioration in the compressor efficiency.
  • the essence of the invention is that the annular chamber with the guide elements to the main flow channel is completely open over its axial length and circumference. Ring-like elements with rubbing pads etc. are not required.
  • the above-mentioned patents show that, up to now, experts have tried to make recirculation structures to the main flow channel, ie to the so-called annulus, smooth, with little gap and closed over as large an axial area as possible, in order to extend the contour of the Main flow channel to effect. In contrast, the invention leads to cracks, jagged surfaces, etc. and thus appears to be disadvantageous and inappropriate. However, tests have shown that the recirculation structure according to the invention is superior to known solutions both in terms of raising the surge limit and in terms of efficiency.
  • FIG. 1 shows a partial longitudinal section through an axial-type compressor in the region of a recirculation structure on the housing
  • FIG. 2 shows a comparable partial longitudinal section in the area of a hub-side recirculation structure
  • FIG. 3 shows a partial cross section through the recirculation structure according to FIG. 1
  • FIG. 4 shows a partial view of the recirculation structure according to FIGS. 1 and 3 radially from the inside
  • FIG. 5 shows a partial longitudinal section in the area of a housing-side recirculation structure modified with respect to FIG. 1, and
  • FIG. 6 shows a partial longitudinal section in the area of a housing-side recirculation structure modified with respect to FIG. 1 and FIG. 5.
  • the recirculation structure 1 according to FIG. 1 is integrated into the housing 5 of a turbocompressor and can therefore be referred to as a “casing treatment”.
  • device in the bladed main flow channel 9 is indicated on the left with an arrow, it therefore runs from left to right.
  • the flow first meets a guide vane ring 13, then a moving vane ring 20 and finally again a guide vane ring 14.
  • the radially outer contour 11 of the main flow channel 9 corresponds to the inner contour of the housing 5 and is to the left and right of the actual one for clarification Continuation of dash-dotted lines.
  • the static recirculation structure 1 interacts with the rotor blade ring 20 and lies largely axially in front of the latter, ie upstream.
  • the annular chamber 29 forming the recirculation structure 1 together with the guide elements 37 adjoins the main flow channel 9 radially from the outside and is open towards the latter.
  • the free edges 41 of the guide elements 37 lie on or close to the contour 11 of the main flow channel 9, that is to say they are at least approximately aligned with the housing inner contour.
  • the guide elements 37 can consist of a metal, such as a Ni-based alloy, or of a light metal, such as Al, or of a plastic, such as thermoplastics, thermosets or elastomers.
  • the front wall 33 and the rear wall 34 of the annular chamber 29 are inclined forwards starting from their radially inner edges 35, 36 in order to be aerodynamically favorable for the recirculation indicated by a small arrow.
  • the angle of inclination of the front wall is denoted by ⁇ , it can be the same or different in relation to the angle of the rear wall 34.
  • ⁇ The angle of inclination of the front wall
  • FIG. 2 shows a recirculation structure 2 integrated in a rotating hub 8.
  • a rotor blade ring 21 In the main flow channel 10, a rotor blade ring 21, a guide blade ring 15 with radially inner, free blade ends 26 and a rotor blade ring 22 can be seen from left to right.
  • the arrangement of a recirculation structure would consequently be referred to as "hub treatment”.
  • the recirculation consisting of annular chamber 30 and guide elements 38 ons Vietnamese 2 with front and rear recesses 47, 48 cooperates with a largely downstream guide vane ring 15. Since the "hub treatment” rotates here and the guide vane ring 15 stands, the rotor speed acts fully as the differential speed. The mode of operation does not differ in principle from that of a "casing treatment”.
  • “Casing treatment” and “hub treatment” can also be combined in a turbo compressor
  • the radial inner contour 12 of the main flow channel corresponds here to the outer contour of the hub 8.
  • FIG. 3 shows a detail from FIG. 1 in cross section.
  • the guide elements 37 are inclined at an angle ⁇ to the radial such that the blade ends 25 of the rotor blade ring 20 convey the recirculation flow into the annular chamber 29 without major losses, the direction of rotation (see arrow) to be noted.
  • the angle of inclination ⁇ can decrease from radially inside to outside to the value “zero” with appropriately curved guide elements.
  • FIG. 4 for FIG. 3 shows the blade profiling of the rotor blade ring 20 in connection with its direction of rotation (arrow) and gives a good idea of the aerodynamic profiling and curvature of the guide elements 37.
  • the person skilled in the art can recognize that the recirculation outlet in the area of the upstream Edge 35 of the annular chamber 29 in relation to the blade ring 20 is to take place here with counter-swirl. With 36 the downstream edge of the annular chamber is designated.
  • the guide elements 37 can also consist of flat or curved “sheets” in simpler versions.
  • the recirculation structure 3 according to FIG. 5 is a "casing treatment" with an annular chamber 31 integrated into a housing 6.
  • the guide elements 39 extend here to the front wall of the annular chamber 31, recesses 49 are provided in the rear area, in the immediate vicinity of the blade ends 27 of the Blade ring 23.
  • the free edges 43 of the guide elements 39 do not extend into the rotation region of the blade ends 27. With 16 and 17, guide blade rings are designated.
  • the recirculation structure 4 in FIG. 6 with the annular chamber 32 and guide elements 40 is likewise a “casing treatment”, which is integrated in a housing 7 and interacts with a moving blade ring 24.
  • the guide elements 40 extend to the rear wall of the annular chamber 32.
  • Recesses 50 are provided in the front area here, since the free edges 44 of the guide elements 40 extend into the rotation area of the blade ends 28, they are offset radially outward in the rear area in order to reliably avoid contact with the blades the edges are also offset accordingly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Catalysts (AREA)
  • Immobilizing And Processing Of Enzymes And Microorganisms (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Recirculation structure for turbocompressors, having a ring chamber which is arranged in the area of the free blade ends of a blade ring largely upstream of the latter and adjoins the main flow duct. A plurality of guiding elements are arranged in the ring chamber distributed over its circumference and are arranged and shaped in a fluidically advantageous manner with respect to the recirculation flow, with recesses provided in the leading and/or trailing area of the ring chamber. The side of the ring chamber which adjoins the contour of the main flow duct is open along its axial length as well as along its entire circumference, the free edges of the guiding elements being situated on the or close to the contour of the main flow duct.

Description

Rezirkulationsstruktur für Turboverdichter Recirculation structure for turbocompressors
Die Erfindung betrifft eine Rezirkulationsstruktur für Turboverdichter, gemäß dem Oberbegriff des Patentanspruches 1 , sowie ein Flugtriebwerk und eine stationäre Gasturbine.The invention relates to a recirculation structure for turbocompressors, according to the preamble of claim 1, and to an aircraft engine and a stationary gas turbine.
Rezirkulationsstrukturen für Turboverdichter sind seit geraumer Zeit bekannt und werden in der Fachwelt in der Regel als „Casing Treatments" bezeichnet. Diese haben primär die Aufgabe, den aerodynamisch stabilen Betriebsbereich des Verdichters zu erhöhen, wobei die sogenannte Pumpgrenze zu höheren Verdichterdrücken, d.h. zu einer höheren Verdichterbelastung hin, verschoben wird. Die für einen örtlichen Strömungsabriss und letztlich für das Pumpen des Verdichters verantwortlichen Störungen treten gehäuseseitig an den Laufschaufelenden einer bzw. mehrerer Verdichterstufen, nabenseitig an den radial innenliegenden Leitschaufelenden auf, da in diesen Bereichen die aerodynamische Belastung am höchsten ist. Durch Rezirkula- tion der zwischen den Schaufelspitzen mit Schaufeldrehzahl umlaufenden, eine reduzierte Energie aufweisenden „Luftteilchen" in den Hauptstrom unter Energiezunahme wird die Strömung im Bereich der Schaufelenden wieder stabilisiert. Da Strömungsstörungen in der Regel nicht gleichmäßig über den Stufenumfang auftreten, sollte strömungstechnisch auch ein Ausgleich in Umfangsrichtung, zusätzlich zur im wesentlichen axialen Rezirkulation, möglich sein. Der Hauptnachteil der bekannten „Casing Treatments" liegt darin, dass sie zwar die Pumpgrenze erhöhen, aber gleichseitig den Verdichterwirkungsgrad reduzieren.Recirculation structures for turbocompressors have been known for some time and are generally referred to in the specialist world as "casing treatments". The primary purpose of these is to increase the aerodynamically stable operating range of the compressor, the so-called surge limit leading to higher compressor pressures, ie to a higher one The disturbances responsible for a local stall and ultimately for the pumping of the compressor occur on the housing side at the blade ends of one or more compressor stages, on the hub side at the radially inner guide blade ends, since the aerodynamic load is highest in these areas. The flow in the area of the blade ends is stabilized again by recirculation of the “air particles” circulating between the blade tips at blade speed and having a reduced energy and increasing energy. Since flow disturbances generally do not occur evenly over the circumference of the step, flow-related compensation should also be possible in the circumferential direction, in addition to the essentially axial recirculation. The main disadvantage of the known "casing treatments" is that although they increase the surge limit, they simultaneously reduce the compressor efficiency.
Die DE 33 22 295 C3 schützt einen Axialventilator mit einem gattungsgemäßen „Casing Treatment". Man erkennt dort eine Ringkammer (8), in der Leitelemente (9) fest angeordnet sind. Im stromabwärtigen Bereich über den Laufschaufelenden befindet sich ein in Umfangsrichtung offener Bereich, in den sich die Leitelemente nicht erstrecken. Charakteristisch für diese Art „Casing Treatment" ist ein etwa mit der Kontur des Hauptströmungskanales fluchtender, geschlossener Ring (7), der den hinteren Eintrittsbereich vom vorderen Austrittsbereich der Rezirkulationsstruktur trennt und einen glatten, geschlossenen Oberflächenbereich bildet. Ein ganz ähnliches „Casing Treatment" ist aus der DE 35 39 604 C1 bekannt, wobei hier im vorderen und hinteren Bereich der Ringkammer (7) ein in Umfangsrichtung offener Bereich vorhanden ist. Man beachte auch hier den radial innenliegenden Ring 6.DE 33 22 295 C3 protects an axial fan with a generic "casing treatment". There is an annular chamber (8) in which guide elements (9) are fixedly arranged. In the downstream area above the blade ends there is an area which is open in the circumferential direction, In which the guiding elements do not extend. Characteristic of this type of "casing treatment" is a closed ring (7), which is approximately aligned with the contour of the main flow channel and separates the rear entry area from the front exit area of the recirculation structure and forms a smooth, closed surface area. A very similar “casing treatment” is known from DE 35 39 604 C1, with an area that is open in the circumferential direction being present in the front and rear area of the ring chamber (7). Also note the radially inner ring 6 here.
Ein neueres „Casing Treatment" ist aus der US 5,282,718 A bekannt. Hier sind die Ringkammer (18, 28) und die Leitelemente (24) strömungstechnisch verfeinert. Auch hier sind Ein- und Austritt der Rezirkulationsströmung durch einen massiven, zu den Schaufeln hin glatten und geschlossenen Ring getrennt. Derartige Ringe im Schaufelbereich müssen für den Fall der Berührung mit den Schaufelspitzen in der Regel mit einem Anstreif- bzw. Einlaufbelag versehen werden.A newer "casing treatment" is known from US Pat. No. 5,282,718 A. Here, the annular chamber (18, 28) and the guide elements (24) are refined in terms of flow technology. Here too, the entry and exit of the recirculation flow are smooth towards the blades and closed ring separately, such rings in the area of the blade must be provided with a brush or run-in covering in the event of contact with the blade tips.
Es gibt weitere „Casing Treatments" mit axialen bzw. axial schrägen Nuten, wie z.B. in der US 5, 137,419 A offenbart. Diese bleiben hier deshalb außer Betracht, da mangels Verbindung der Nuten untereinander bei diesen Versionen kein Strömungsausgleich in Umfangsrichtung möglich ist.There are further "casing treatments" with axial or axially inclined grooves, as disclosed, for example, in US Pat. No. 5,137,419 A. These are not taken into consideration here, since the lack of connection of the grooves with one another in these versions means that flow compensation in the circumferential direction is not possible.
Angesichts der Nachteile der Lösungen nach dem Stand der Technik besteht die Aufgabe der Erfindung darin, eine Rezirkulationsstruktur für Turboverdichter bereitzustellen, die eine deutliche Erhöhung der Pumpgrenze und somit eine deutliche Vergrößerung des stabilen Betriebsbereiches ohne relevante Verschlechterung des Verdichterwirkungsgrades ermöglicht.In view of the disadvantages of the solutions according to the prior art, the object of the invention is to provide a recirculation structure for turbocompressors which enables a significant increase in the surge limit and thus a significant increase in the stable operating range without a relevant deterioration in the compressor efficiency.
Diese Aufgabe wird durch die in Patentanspruch 1 gekennzeichneten Merkmale gelöst, in Verbindung mit den gattungsbildenden Merkmalen in dessen Oberbegriff.This object is achieved by the features characterized in claim 1, in conjunction with the generic features in the preamble.
Das Wesen der Erfindung liegt darin, dass die Ringkammer mit den Leitelementen zum Hauptströmungskanal hin über ihre axiale Länge und ihren Umfang vollkommen offen ist. Ringartige Elemente mit Anstreifbelägen etc. entfallen dabei. Die obengenannten Patentschriften zeigen, dass die Fachwelt bis dato versucht hat, Rezirkulati- onsstrukturen zum Hauptströmungskanal, d.h. zum sog. Ringraum hin über einen möglichst großen axialen Bereich glatt, spaltarm und geschlossen auszuführen, um eine möglichst strömungsgünstige und verlustarme Verlängerung der Kontur des Hauptströmungskanales zu bewirken. Die Erfindung führt demgegenüber zu Spalten, zerklüfteten Oberflächen etc. und erscheint somit nachteilig und unzweckmäßig zu sein. Versuche haben jedoch gezeigt, dass die erfindungsgemäße Rezirkulationsstruktur bekannten Lösungen sowohl hinsichtlich Pumpgrenzanhebung als auch hinsichtlich Wirkungsgrad überlegen ist. Dies ist aerodynamisch dadurch zu erklären, dass die freie, ungezwungene Ausbildung der Rezirkulationsströmung in der offenen Ringkammer mit freistehenden Leitelementen und Strömungsverbindungen in Umfangsrichtung wichtiger ist, als eine möglichst spaltfreie Verlängerung der Kontur des Hauptströmungskanales. Das Fehlen eines geschlossenen Rings hat die weiteren Vorteile, dass kein Anstreif- bzw. Einlaufbelag für die Leitelemente erforderlich ist und radialer Bauraum sowie Gewicht eingespart wird, was zu strukturmechanischen Vorteilen führt.The essence of the invention is that the annular chamber with the guide elements to the main flow channel is completely open over its axial length and circumference. Ring-like elements with rubbing pads etc. are not required. The above-mentioned patents show that, up to now, experts have tried to make recirculation structures to the main flow channel, ie to the so-called annulus, smooth, with little gap and closed over as large an axial area as possible, in order to extend the contour of the Main flow channel to effect. In contrast, the invention leads to cracks, jagged surfaces, etc. and thus appears to be disadvantageous and inappropriate. However, tests have shown that the recirculation structure according to the invention is superior to known solutions both in terms of raising the surge limit and in terms of efficiency. This can be explained aerodynamically by the fact that the free, informal formation of the recirculation flow in the open annular chamber with free-standing guide elements and flow connections in the circumferential direction is more important than a gap-free extension of the contour of the main flow channel. The absence of a closed ring has the further advantages that no rubbing or running-in covering is required for the guide elements and that radial installation space and weight are saved, which leads to structural mechanical advantages.
In den Unteransprüche sind bevorzugte Ausgestaltungen der Rezirkulationsstruktur nach dem Hauptanspruch gekennzeichnet.Preferred embodiments of the recirculation structure according to the main claim are characterized in the subclaims.
Die Erfindung wird anschließend anhand er Zeichnungen noch näher erläutert. Dabei zeigen in vereinfachter, nicht maßstäblicher Darstellung:The invention is explained in more detail with reference to drawings. Simplified, not to scale, show:
Figur 1 einen Teillängsschnitt durch einen Verdichter in Axialbauart im Bereich einer gehäuseseitigen Rezirkulationsstruktur,FIG. 1 shows a partial longitudinal section through an axial-type compressor in the region of a recirculation structure on the housing,
Figur 2 einen vergleichbaren Teillängsschnitt im Bereich einer nabenseitigen Rezirkulationsstruktur,FIG. 2 shows a comparable partial longitudinal section in the area of a hub-side recirculation structure,
Figur 3 einen Teilquerschnitt durch die Rezirkulationsstruktur gemäß Figur 1, Figur 4 eine Teilansicht der Rezirkulationsstruktur gemäß Figur 1 und 3 radial von Innen,3 shows a partial cross section through the recirculation structure according to FIG. 1, FIG. 4 shows a partial view of the recirculation structure according to FIGS. 1 and 3 radially from the inside,
Figur 5 einen Teillängsschnitt im Bereich einer gehäuseseitigen, gegenüber Figur 1 modifizierten Rezirkulationsstruktur, und5 shows a partial longitudinal section in the area of a housing-side recirculation structure modified with respect to FIG. 1, and
Figur 6 einen Teillängsschnitt im Bereich einer gehäuseseitigen, gegenüber Figur 1 und Figur 5 modifizierten Rezirkulationsstruktur.6 shows a partial longitudinal section in the area of a housing-side recirculation structure modified with respect to FIG. 1 and FIG. 5.
Die Rezirkulationsstruktur 1 gemäß Figur 1 ist in das Gehäuse 5 eines Turboverdichters integriert und somit als „Casing Treatment" zu bezeichnen. Die Strömungsrich- tung im beschaufelten Hauptströmungskanal 9 ist links mit einem Pfeil angedeutet, sie verläuft also von links nach rechts. Die Strömung trifft im gezeigten Bereich zunächst auf einen Leitschaufelkranz 13, dann auf einen Laufschaufelkranz 20 und schließlich wieder auf einen Leitschaufelkranz 14. Die radial äußere Kontur 1 1 des Hauptströmungskanals 9 entspricht der inneren Kontur des Gehäuses 5 und ist zur Verdeutlichung links und rechts der eigentlichen Darstellung strichpunktiert fortgesetzt. Die statische Rezirkulationsstruktur 1 wirkt mit dem Laufschaufelkranz 20 zusammen und liegt großteils axial vor diesem, d.h. stromaufwärts. Die zusammen mit den Leitelementen 37 die Rezirkulationsstruktur 1 bildende Ringkammer 29 grenzt radial von außen an den Hauptströmungskanal 9 an und ist zu diesem hin offen. Die freien Kanten 41 der Leitelemente 37 liegen auf oder nahe bei der Kontur 1 1 des Hauptströmungskanales 9, d.h. sie fluchten zumindest annähernd mit der Gehäuseinnenkontur. Die Leitelemente 37 können aus einem Metall, wie einer Ni- Basislegierung, oder aus einem Leichtmetall, wie AI, oder aus einem Kunststoff, wie Thermoplaste, Duroplaste oder Elastomere, bestehen. Die vordere Wand 33 und die hintere Wand 34 der Ringkammer 29 sind ausgehend von ihren radial inneren Kanten 35, 36 nach vorne geneigt, um für die mit einem kleinen Pfeil angedeutete Rezirkula- tion strömungsgünstig zu sein.The recirculation structure 1 according to FIG. 1 is integrated into the housing 5 of a turbocompressor and can therefore be referred to as a “casing treatment”. device in the bladed main flow channel 9 is indicated on the left with an arrow, it therefore runs from left to right. In the region shown, the flow first meets a guide vane ring 13, then a moving vane ring 20 and finally again a guide vane ring 14. The radially outer contour 11 of the main flow channel 9 corresponds to the inner contour of the housing 5 and is to the left and right of the actual one for clarification Continuation of dash-dotted lines. The static recirculation structure 1 interacts with the rotor blade ring 20 and lies largely axially in front of the latter, ie upstream. The annular chamber 29 forming the recirculation structure 1 together with the guide elements 37 adjoins the main flow channel 9 radially from the outside and is open towards the latter. The free edges 41 of the guide elements 37 lie on or close to the contour 11 of the main flow channel 9, that is to say they are at least approximately aligned with the housing inner contour. The guide elements 37 can consist of a metal, such as a Ni-based alloy, or of a light metal, such as Al, or of a plastic, such as thermoplastics, thermosets or elastomers. The front wall 33 and the rear wall 34 of the annular chamber 29 are inclined forwards starting from their radially inner edges 35, 36 in order to be aerodynamically favorable for the recirculation indicated by a small arrow.
Der Neigungswinkel der vorderen Wand ist mit α bezeichnet, er kann gleich oder unterschiedlich in Relation zum Winkel der hinteren Wand 34 sein. Zwischen der vorderen Wand 33, den Leitelementen 37 und der hinteren Wand 34 sind Aussparungen 45, 46 vorhanden, die Strömungsvorgänge innerhalb der Ringkammer in Umfangsrichtung zulassen, zusätzlich zur vorwiegend axial verlaufenden Rezirkulation. Mit 25 sind die freien Schaufelenden des Laufschaufelkranzes 20 bezeichnet, in deren Bereich Strömungsstörungen am ehesten auftreten.The angle of inclination of the front wall is denoted by α, it can be the same or different in relation to the angle of the rear wall 34. There are recesses 45, 46 between the front wall 33, the guide elements 37 and the rear wall 34, which allow flow processes within the annular chamber in the circumferential direction, in addition to the predominantly axial recirculation. With 25 the free blade ends of the moving blade ring 20 are designated, in the area of which flow disturbances are most likely to occur.
Im Unterschied zu Figur 1 zeigt Figur 2 eine in eine rotierende Nabe 8 integrierte Rezirkulationsstruktur 2. Man erkennt im Hauptströmungskanal 10 von links nach rechts einen Laufschaufelkranz 21 , einen Leitschaufelkranz 15 mit radial inneren, freien Schaufelenden 26 und einen Laufschaufelkranz 22. Eine solche, neue Anordnung einer Rezirkulationsstruktur wäre konsequenterweise als „Hub Treatment" zu bezeichnen. Die aus Ringkammer 30 und Leitelementen 38 bestehende Rezirkulati- onsstruktur 2 mit vorderen und hinteren Aussparungen 47, 48 wirkt mit einem großteils stromabwärts liegenden Leitschaufelkranz 15 zusammen. Da hier das „Hub Treatment" rotiert und der Leitschaufelkranz 15 steht, wirkt die Rotordrehzahl voll als Differenzdrehzahl. Die Wirkungsweise unterschiedet sich prinzipiell nicht von der eines „Casing Treatments" In einem Turboverdichter können "Casing Treatment" und „Hub Treatment" auch kombiniert werden und in mehreren Stufen zur Anwendung kommen. Die radial innere Kontur 12 des Hauptströmungskanals entspricht hier der Außenkontur der Nabe 8.In contrast to FIG. 1, FIG. 2 shows a recirculation structure 2 integrated in a rotating hub 8. In the main flow channel 10, a rotor blade ring 21, a guide blade ring 15 with radially inner, free blade ends 26 and a rotor blade ring 22 can be seen from left to right. Such a new one The arrangement of a recirculation structure would consequently be referred to as "hub treatment". The recirculation consisting of annular chamber 30 and guide elements 38 onsstruktur 2 with front and rear recesses 47, 48 cooperates with a largely downstream guide vane ring 15. Since the "hub treatment" rotates here and the guide vane ring 15 stands, the rotor speed acts fully as the differential speed. The mode of operation does not differ in principle from that of a "casing treatment". "Casing treatment" and "hub treatment" can also be combined in a turbo compressor The radial inner contour 12 of the main flow channel corresponds here to the outer contour of the hub 8.
Figur 3 zeigt im Querschnitt ein Detail aus Fig. 1. Die Leitelemente 37 sind um einen Winkel ß so zur Radialen geneigt, dass die Schaufelenden 25 des Laufschaufelkranzes 20 die Rezirkulationsströmung ohne größere Verluste in die Ringkammer 29 hineinfördern, wobei die Drehrichtung (siehe Pfeil) zu beachten ist. Der Neigungswinkel ß kann von radial Innen nach Außen bis auf den Wert „Null" abnehmen bei entsprechend gekrümmten Leitelementen.FIG. 3 shows a detail from FIG. 1 in cross section. The guide elements 37 are inclined at an angle β to the radial such that the blade ends 25 of the rotor blade ring 20 convey the recirculation flow into the annular chamber 29 without major losses, the direction of rotation (see arrow) to be noted. The angle of inclination β can decrease from radially inside to outside to the value “zero” with appropriately curved guide elements.
Eine radiale Anordnung der Leitelemente, d.h. ß = 0° ist möglich, dürfte aber weniger strömungsgünstig sein.A radial arrangement of the guide elements, i.e. ß = 0 ° is possible, but should be less aerodynamic.
Die Ansicht gemäß Figur 4 zu Figur 3 zeigt die Schaufelprofilierung des Laufschaufelkranzes 20 in Verbindung mit seiner Drehrichtung (Pfeil) und vermittelt eine gute Vorstellung von der strömungsgünstigen Profilierung und Krümmung der Leitelemente 37. Der Fachmann vermag zu erkennen, dass der Rezirkulationsaustritt im Bereich der stromaufwärtigen Kante 35 der Ringkammer 29 in Relation zum Laufschaufelkranz 20 hier mit Gegendrall erfolgen soll. Mit 36 ist die stromabwärtige Kante der Ringkammer bezeichnet. Es sei daran erinnert, dass die Leitelemente 37 in einfacheren Ausführungen auch aus ebenen oder gekrümmten „Blechen" bestehen können.The view according to FIG. 4 for FIG. 3 shows the blade profiling of the rotor blade ring 20 in connection with its direction of rotation (arrow) and gives a good idea of the aerodynamic profiling and curvature of the guide elements 37. The person skilled in the art can recognize that the recirculation outlet in the area of the upstream Edge 35 of the annular chamber 29 in relation to the blade ring 20 is to take place here with counter-swirl. With 36 the downstream edge of the annular chamber is designated. It should be remembered that the guide elements 37 can also consist of flat or curved “sheets” in simpler versions.
Die Rezirkulationsstruktur 3 gemäß Figur 5 ist ein „Casing Treatment" mit einer in ein Gehäuse 6 integrierten Ringkammer 31. Die Leitelemente 39 reichen hier bis zur vorderen Wand der Ringkammer 31, im hinteren Bereich sind Aussparungen 49 vorhanden, in unmittelbarer Nähe der Schaufelenden 27 des Laufschaufelkranzes 23. Die freien Kanten 43 der Leitelemente 39 reichen nicht bis in den Rotationsbereich der Schaufelenden 27. Mit 16 und 17 sind Leitschaufelkränze bezeichnet.The recirculation structure 3 according to FIG. 5 is a "casing treatment" with an annular chamber 31 integrated into a housing 6. The guide elements 39 extend here to the front wall of the annular chamber 31, recesses 49 are provided in the rear area, in the immediate vicinity of the blade ends 27 of the Blade ring 23. The free edges 43 of the guide elements 39 do not extend into the rotation region of the blade ends 27. With 16 and 17, guide blade rings are designated.
Die Rezirkulationsstruktur 4 in Figur 6 mit Ringkammer 32 und Leitelementen 40 ist ebenfalls ein „Casing Treatment", das in ein Gehäuse 7 integriert ist und mit einem Laufschaufelkranz 24 zusammenwirkt. Im Unterschied zu Figur 5 reichen hier die Leitelemente 40 bis zur hinteren Wand der Ringkammer 32. Aussparungen 50 sind hier im vorderen Bereich vorgesehen. Da die freien Kanten 44 der Leitelemente 40 bis in den Rotationsbereich der Schaufelenden 28 reichen, sind sie im hinteren Bereich radial nach außen versetzt, um eine Berührung mit den Schaufeln sicher zu vermeiden. Natürlich können die Kanten auch im ganzen entsprechen versetzt sein.The recirculation structure 4 in FIG. 6 with the annular chamber 32 and guide elements 40 is likewise a “casing treatment”, which is integrated in a housing 7 and interacts with a moving blade ring 24. In contrast to FIG. 5, the guide elements 40 extend to the rear wall of the annular chamber 32. Recesses 50 are provided in the front area here, since the free edges 44 of the guide elements 40 extend into the rotation area of the blade ends 28, they are offset radially outward in the rear area in order to reliably avoid contact with the blades the edges are also offset accordingly.
Für alle Ausgestaltungen der Rezirkulationsstruktur gilt, dass die freien Kanten 41 bis 44 der Leitelemente 37 bis 40 nicht radial nach außen versetzt sein müssen, wenn die Leitelemente aus einem weichen Leichtmetall oder einem Kunststoff hergestellt sind, weil eine Berührung mit den Schaufelenden 25 bis 28 zugelassen werden kann, ohne dass die Schaufeln beschädigt werden. It applies to all configurations of the recirculation structure that the free edges 41 to 44 of the guide elements 37 to 40 do not have to be offset radially outward if the guide elements are made of a soft light metal or a plastic, because contact with the blade ends 25 to 28 is permitted can be damaged without damaging the blades.

Claims

Patentansprücheclaims
Rezirkulationsstruktur für Turboverdichter, mit einer konzentrisch zur Verdichterachse im Bereich der freien Schaufelenden eines Schaufelkranzes angeordneten Ringkammer, deren axiale Mitte stromaufwärts der axialen Mitte der freien Schaufelenden liegt, und die radial an die Kontur des Hauptströmungskanales, des sogenannten Ringraumes, angrenzt, und mit einer Vielzahl von in der Ringkammer angeordneten, über deren Umfang verteilten Leitelementen, die in der Weise angeordnet und geformt sind, dass im axial hinteren Bereich der Ringkammer der Eintritt der Rezirkulationsströmung strömungsgünstig erfolgt, und im axial vorderen Bereich der Ringkammer der Austritt der Rezirkulationsströmung relativ zum stromabwärtigen Schaufelkranz mit definierter Richtung und ggf. definiertem Drall erfolgt, wobei die Leitelemente im vorderen und/oder im hinteren Bereich der Ringkammer Aussparungen für einen Strömungsdurchtritt in Umfangsrichtung aufweisen, dadurch gekennzeichnet, dass die an die Kontur (1 1, 12) des Hauptströmungskanales (9, 10) angrenzende Seite der Ringkammer (29 bis 32) über ihre axiale Länge, d.h. vom Eintritt bis zum Austritt der Rezirkulationsströmung, sowie über ihren gesamten Umfang zum Hauptströmungskanal (9, 10) hin offen ist, wobei die freien Kanten (41 bis 44) der Leitelemente (37 bis 40) auf oder nahe bei der Kontur ( 1 1, 12) des Hauptströmungskanales (9, 10) liegen.Recirculation structure for turbocompressors, with an annular chamber arranged concentrically to the compressor axis in the area of the free blade ends of a blade ring, the axial center of which lies upstream of the axial center of the free blade ends, and which adjoins the contour of the main flow channel, the so-called annular space, and with a large number of guide elements arranged in the annular chamber, distributed over the circumference thereof, which are arranged and shaped in such a way that the entry of the recirculation flow takes place in the axially rearward region of the annular chamber, and in the axially front region of the annular chamber the exit of the recirculation flow relative to the downstream blade ring takes place with a defined direction and, if necessary, defined swirl, the guide elements in the front and / or in the rear region of the annular chamber having cutouts for a flow passage in the circumferential direction, characterized in that the to the K ontur (1 1, 12) of the main flow channel (9, 10) adjacent side of the annular chamber (29 to 32) over its axial length, i.e. from the entrance to the exit of the recirculation flow, as well as over its entire circumference to the main flow channel (9, 10), the free edges (41 to 44) of the guide elements (37 to 40) being on or close to the contour (1 1, 12) of the main flow channel (9, 10).
Rezirkulationsstruktur nach Anspruch 1, dadurch gekennzeichnet, dass sie ein- oder mehrfach gehäusefest, d.h. statisch, im Bereich eines oder mehrerer Laufschaufelkränze (20, 23, 24) und/oder ein- oder mehrfach nabenfest, d.h. rotierend, im Bereich eines oder mehrerer Leitschaufelkränze (15) angeordnet ist.Recirculation structure according to claim 1, characterized in that it is fixed to the housing one or more times, i.e. static, in the area of one or more rotor blades (20, 23, 24) and / or one or more hub-fixed, i.e. rotating, is arranged in the region of one or more guide vane rings (15).
Rezirkulationsstruktur nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass sie in einem ein- oder mehrstufigen Turboverdichter in Axial-, Diagonal- oder Radialbauweise angeordnet ist.Recirculation structure according to claim 1 or 2, characterized in that it is arranged in a single or multi-stage turbocompressor in axial, diagonal or radial construction.
Rezirkulationsstruktur nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die axial vordere Wand (33) und die axial hintere Wand (34) der Ringkammer (29) ausgehend von ihren Kanten (35,36) auf der Kontur ( 1 1 ) des Hauptströmungskanales (9) um den gleichen oder einen unterschiedlichen Winkel α stromaufwärts, d.h. schräg nach vorne, geneigt sind.Recirculation structure according to one of the preceding claims, characterized in that the axially front wall (33) and the axially rear wall (34) of the annular chamber (29), starting from their edges (35, 36) on the contour (11) of the main flow channel (9), are inclined by the same or a different angle α upstream, ie obliquely to the front.
Rezirkulationsstruktur nach Anspruch 4, dadurch gekennzeichnet, dass der Neigungswinkel α der axial vorderen und der axial hinteren Wand der Ringkammer ausgehend von der Radialrichtung einen Wert im Bereich von 30° bis 60° aufweist.Recirculation structure according to claim 4, characterized in that the angle of inclination α of the axially front and the axially rear wall of the annular chamber has a value in the range from 30 ° to 60 °, starting from the radial direction.
Rezirkulationsstruktur nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Leitelemente (37 bis 40) blechartig, eben oder gekrümmt, mit konstanter Dicke, oder schaufelartig, räumlich gekrümmt, mit variierender Dicke und mit definierten Profilschnitten ausgeführt sind.Recirculation structure according to one of the preceding claims, characterized in that the guide elements (37 to 40) are sheet-like, flat or curved, with constant thickness, or blade-like, spatially curved, with varying thickness and with defined profile cuts.
Rezirkulationsstruktur nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Leitelemente (37 bis 40) - bei axialer Blickrichtung - radial, in Umfangsrichtung geneigt oder in Umfangsrichtung gekrümmt angeordnet sind, wobei im Falle einer Neigung oder Krümmung die Winkel ß so gewählt sind, dass der Eintritt der Rezirkulationsströmung in die Ringkammer (29 bis 32) strömungstechnisch erleichtert wird, d.h. strömungsgünstig erfolgt.Recirculation structure according to one of the preceding claims, characterized in that the guide elements (37 to 40) - in the axial direction of view - are arranged radially, inclined in the circumferential direction or curved in the circumferential direction, the angles β being chosen in the case of an inclination or curvature such that the entry of the recirculation flow into the annular chamber (29 to 32) is fluidically facilitated, ie streamlined.
Rezirkulationsstruktur nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Verhältnis des Gesamtströmungsvolumens zum Gesamtvolumen der Leitelemente (37 bis 40) innerhalb der Rezirkulationsstruktur (1 bis 4) möglichst groß gewählt ist, d.h. die Leitelemente (37 bis 40) möglichst dünnwandig bzw. dünn profiliert ausgeführt sind.Recirculation structure according to one of the preceding claims, characterized in that the ratio of the total flow volume to the total volume of the guide elements (37 to 40) within the recirculation structure (1 to 4) is chosen to be as large as possible, i.e. the guide elements (37 to 40) are made as thin-walled or thinly profiled as possible.
Rezirkulationsstruktur nach eine der vorhergehenden Ansprüche, bei der sich die Leitelemente axial bis in den Bereich der freien Schaufelenden erstrecken, dadurch gekennzeichnet, dass die freien Kanten (44) der Leitelemente (40) zumindest im Bereich der freien Schaufelenden (28) radial so weit zurückgesetzt sind, dass im Normalbetrieb des Turboverdichters keine Berührung zwischen den Schaufelenden (28) und den Leitelementen (40) erfolgt. Rezirkulationsstruktur nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Leitelemente (37 bis 40) aus einem Metall, wie Stahl oder einer Ni- oder einer Co-Basislegierung, einem Leichtmetall, wie AI, oder einem Kunststoff, wie Thermoplaste, Duroplaste oder Elastomere, bestehen.Recirculation structure according to one of the preceding claims, in which the guide elements extend axially into the region of the free blade ends, characterized in that the free edges (44) of the guide elements (40) are set back radially so far at least in the region of the free blade ends (28) are that during normal operation of the turbocompressor there is no contact between the blade ends (28) and the guide elements (40). Recirculation structure according to one of the preceding claims, characterized in that the guide elements (37 to 40) made of a metal, such as steel or a Ni or a Co-based alloy, a light metal, such as Al, or a plastic, such as thermoplastics, thermosets or elastomers , consist.
Rezirkulationsstruktur nach Anspruch 10, dadurch gekennzeichnet, dass sich die freien Kanten (41 bis 44) der Leitelemente (37 bis 40) im Fall von Leichtmetall oder Kunststoff bis in den Bereich der freien Schaufelenden (25 bis 28) erstrecken und eine Berührung möglich ist.Recirculation structure according to claim 10, characterized in that the free edges (41 to 44) of the guide elements (37 to 40) in the case of light metal or plastic extend into the area of the free blade ends (25 to 28) and contact is possible.
Flugtriebwerk, umfassend einen Turboverdichter mit wenigstens einer Rezirkulationsstruktur nach einem oder mehreren der vorhergehenden Ansprüche.Aircraft engine, comprising a turbocompressor with at least one recirculation structure according to one or more of the preceding claims.
Stationäre Gasturbine, umfassend einen Turboverdichter mit wenigstens einer Rezirkulationsstruktur nach einem oder mehreren der Ansprüche 1 bis 1 1. Stationary gas turbine comprising a turbocompressor with at least one recirculation structure according to one or more of claims 1 to 11.
EP03718608A 2002-02-28 2003-02-26 Recirculation structure for turbo chargers Expired - Lifetime EP1478828B1 (en)

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CA2495186A1 (en) 2003-09-04
ATE348943T1 (en) 2007-01-15
RU2293221C2 (en) 2007-02-10
DE50306028D1 (en) 2007-02-01
CA2495186C (en) 2010-04-27
EP1478828B1 (en) 2006-12-20
US6935833B2 (en) 2005-08-30
UA76596C2 (en) 2006-08-15
JP2006505730A (en) 2006-02-16
JP4527403B2 (en) 2010-08-18
US20040156714A1 (en) 2004-08-12
RU2004129277A (en) 2005-08-27
DE10390754D2 (en) 2005-05-12
CN100395432C (en) 2008-06-18
WO2003072910A1 (en) 2003-09-04
AU2003222718A1 (en) 2003-09-09
CN1646790A (en) 2005-07-27

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