EP2329150B1 - Axial turbomachine having asymmetrical compressor inlet guide baffle - Google Patents

Axial turbomachine having asymmetrical compressor inlet guide baffle Download PDF

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Publication number
EP2329150B1
EP2329150B1 EP09737335.1A EP09737335A EP2329150B1 EP 2329150 B1 EP2329150 B1 EP 2329150B1 EP 09737335 A EP09737335 A EP 09737335A EP 2329150 B1 EP2329150 B1 EP 2329150B1
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Prior art keywords
guide
guide vanes
different
attack
inlet
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EP09737335.1A
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German (de)
French (fr)
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EP2329150A1 (en
Inventor
Sergio Elorza Gomez
Alexander Halcoussis
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MTU Aero Engines AG
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MTU Aero Engines AG
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    • 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
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Definitions

  • the invention relates to an axial flow machine with an asymmetrical air inlet and a compressor directly downstream of the air inlet with a guide vanes formed from inlet guide.
  • Such axial flow machine with asymmetric air intake occur, for example, in the core engines of turboprop or helicopter engines.
  • flow problems of the first compressor stage can result, which can lead to a partial detachment of the flow at this blade stage with consequent pumping and loss of efficiency.
  • the invention is therefore based on the object to avoid the disadvantages of the known solutions of the prior art and to provide an improved solution for increasing the stability of an axial flow machine with asymmetric air inlet available.
  • an axial flow machine with an asymmetrical air inlet and a compressor arranged downstream of the air inlet is provided with guide vanes formed exactlysleitgitter in which at least individual guide vanes of successivesleitgitters deviating from the other vanes blade profile and / or have a different angle of attack.
  • the inlet flow angle of the first compressor stage is made uniform in terms of circumference. This takes place in that the different entry angles caused by the asymmetry of the air inlet at different circumferential positions of the inlet guide grid are influenced by targeted profiling and / or targeted change of the angle of attack of individual guide vanes, resulting in a circumferentially symmetrical outflow angle from the inlet guide ring.
  • the peripheral disturbances caused by the asymmetrical air inlet are minimized and thus the first compressor stage largely passes on circumferentially symmetrical inlet conditions, which leads to improved stability and improved efficiency of the compressor.
  • An advantageous embodiment of the invention provides that one or more of the guide gratings following the inlet guide grille have at least individual guide vanes with a blade profile deviating from the remaining guide vanes and / or a different angle of attack.
  • An advantageous embodiment of the invention provides that individual vane groups have a blade profile deviating from the remaining vanes and / or angle of attack. This allows a rational production and corresponding cost savings.
  • the guide vanes may be arranged in several groups of different geometry.
  • a further advantageous embodiment of the invention provides that the guide vanes of the respective vanes groups have mutually differing blade profiles and / or angle of attack.
  • a further advantageous embodiment of the invention provides that all guide vanes are profiled differently and / or have a different angle of attack. That Here, a targeted profiling of each blade or a staggering of the individual blades can be done and thereby made an adjustment to the asymmetric flow
  • a further advantageous embodiment of the invention provides that the guide vanes are designed to be adjustable. By a different adjustment of at least individual blades or blade groups also the desired effect can be achieved, since this can be done quasi a targeted rescaling of individual blades. This has the further advantage that with changed flow conditions, the individual alignment of the guide grid can be traced.
  • a further advantageous embodiment of the invention provides that the guide vanes are formed on the inlet side of a fixed part and the outlet side of a pivotable part.
  • a further advantageous embodiment of the invention provides that an individual control is provided for each or all vanes. This enables individual descendants of each individual blade under changed flow conditions.
  • FIG. 1 shows a schematic representation of a developed constructivesleitgitters according to the present invention with multi-profiles, ie individual profiling of each blade of the ensuresleitgitters.
  • the blades are adapted to the variable circumferentially asymmetrical angle of attack of the inlet guide grille. This unbalanced flow is caused by the asymmetric air inlet.
  • a constant outflow angle is generated over the entire circumference and the first compressor stage passed largely circumferentially symmetrical entry conditions. This leads to improved stability and improved efficiency of the compressor.
  • FIG. 2 Figure 12 is a schematic representation of a prior art unwound inlet guide grate with circumferentially asymmetric flow caused by an asymmetric air inlet.
  • the leftmost and outermost right vane in the plane of the drawing have separations which continue in the subsequent compressor stages and lead to unstable compressor behavior, ie to pumps.
  • FIG. 2 It can be seen that the outflow angle in this case is not constant over the circumference, but changes at each vane, which can also lead to unstable compressor behavior and efficiency losses.

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

Description

Die Erfindung betrifft eine axiale Strömungsmaschine mit asymmetrischem Lufteinlass und einem dem Lufteinlass unmittelbar nachgeordnetem Verdichter mit einem aus Leitschaufeln gebildetem Eintrittsleitgitter.The invention relates to an axial flow machine with an asymmetrical air inlet and a compressor directly downstream of the air inlet with a guide vanes formed from inlet guide.

Derartige axiale Strömungsmaschine mit asymmetrischem Lufteinlass kommen beispielsweise bei Kerntriebwerken von Turboprop- oder Hubschraubertriebwerken vor. Als Folge der unsymmetrischen Anströmung können sich Anströmungsprobleme der ersten Verdichterstufe ergeben, die zu einem teilweisen Ablösen der Strömung an dieser Schaufelstufe mit daraus resultierendem Pumpen und Wirkungsgradverlust führen kann.Such axial flow machine with asymmetric air intake occur, for example, in the core engines of turboprop or helicopter engines. As a result of the asymmetrical flow, flow problems of the first compressor stage can result, which can lead to a partial detachment of the flow at this blade stage with consequent pumping and loss of efficiency.

Für stationäre Gasturbinen lehrt die EP 1 508 669 A1 , dass durch Ausbildung unterschiedlicher Profilkrümmungen von mindestens zwei Vorleitschaufeln der Wirkungsgrad einer stationären Gasturbine erhöht werden kann. Die Wirkungsgraderhöhung wird durch eine Verringerung der Strömungsverluste am Eintrittsleitgitter erreicht.For stationary gas turbines teaches the EP 1 508 669 A1 in that the efficiency of a stationary gas turbine can be increased by forming different profile curvatures of at least two pilot vanes. The increase in efficiency is achieved by reducing the flow losses at Eintrittsleitgitter.

Der Erfindung liegt daher die Aufgabe zugrunde, die Nachteile der bekannten Lösungen des Standes der Technik zu vermeiden und eine verbesserte Lösung zur Erhöhung der Stabilität einer axialen Strömungsmaschine mit asymmetrischem Lufteinlass zur Verfügung zu stellen.The invention is therefore based on the object to avoid the disadvantages of the known solutions of the prior art and to provide an improved solution for increasing the stability of an axial flow machine with asymmetric air inlet available.

Diese Aufgabe wird erfindungsgemäß durch eine axiale Strömungsmaschine mit asymmetrischem Lufteinlass und einem dem Lufteinlass nachgeordnetem Verdichter mit einem aus Leitschaufeln gebildetem Eintrittsleitgitter mit den Merkmalen des Patentanspruchs 1 gelöst. Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung sind in den abhängigen Ansprüchen angegeben.This object is achieved by an axial flow machine with asymmetric air inlet and a downstream of the air inlet compressor with a guide vanes formed Eintrittsleitgitter with the features of claim 1. Advantageous embodiments and further developments of the invention are specified in the dependent claims.

Erfindungsgemäß ist eine axiale Strömungsmaschine mit asymmetrischem Lufteinlass und einem dem Lufteinlass nachgeordnetem Verdichter mit einem aus Leitschaufeln gebildetem Eintrittsleitgitter vorgesehen, bei welcher zumindest einzelne Leitschaufeln des Eintrittsleitgitters ein von den übrigen Leitschaufeln abweichendes Schaufelprofil und/oder einen abweichenden Anstellwinkel aufweisen. Hierdurch wird der Eintrittsströmungswinkel der ersten Verdichterstufe umfangssymmetrisch vergleichmäßigt. Dies erfolgt dadurch, dass die durch die Asymmetrie des Lufteinlasses verursachten unterschiedlichen Eintrittswinkel an verschiedenen Umfangspositionen des Eintrittsleitgitters durch gezielte Profilierung und/oder gezielte Veränderung des Anströmwinkels einzelner Leitschaufeln derart beeinflusst wird, dass hieraus ein umfangssymmetrischer Abströmwinkel aus dem Eintrittsleitkranz resultiert. Dadurch werden die durch den asymmetrischen Lufteinlass verursachten Umfangsstörungen minimiert und damit der ersten Verdichterstufe weitgehend umfangssymmetrische Eintrittsbedingungen weitergegeben, was zu einer verbesserten Stabilität und einem verbesserten Wirkungsgrad des Verdichters führt. Beispielsweise kann es in dem Leitgitter eine Leitschaufel-Hauptgruppe geben, die nur einige Einzelschaufeln aufweist, die sich von der Gruppe unterscheiden.According to the invention, an axial flow machine with an asymmetrical air inlet and a compressor arranged downstream of the air inlet is provided with guide vanes formed Eintrittsleitgitter in which at least individual guide vanes of Eintrittsleitgitters deviating from the other vanes blade profile and / or have a different angle of attack. As a result, the inlet flow angle of the first compressor stage is made uniform in terms of circumference. This takes place in that the different entry angles caused by the asymmetry of the air inlet at different circumferential positions of the inlet guide grid are influenced by targeted profiling and / or targeted change of the angle of attack of individual guide vanes, resulting in a circumferentially symmetrical outflow angle from the inlet guide ring. As a result, the peripheral disturbances caused by the asymmetrical air inlet are minimized and thus the first compressor stage largely passes on circumferentially symmetrical inlet conditions, which leads to improved stability and improved efficiency of the compressor. For example, there may be one vane main group in the baffle that has only a few individual blades that are different from the group.

Eine vorteilhafte Ausführungsform der Erfindung sieht vor, dass einzelne oder mehrere der auf das Eintrittsleitgitter folgenden Leitgitter zumindest einzelne Leitschaufeln mit einem von den übrigen Leitschaufeln abweichendes Schaufelprofil und/oder einen abweichenden Anstellwinkel aufweisen. Durch die asymmetrische Profilierung der auf das Eintrittsleitgitter folgenden Zwischenleitgitter können ggf. noch vorhandene Restasymmetrien der Strömung nach der ersten Stufe weiter abgebaut werden.An advantageous embodiment of the invention provides that one or more of the guide gratings following the inlet guide grille have at least individual guide vanes with a blade profile deviating from the remaining guide vanes and / or a different angle of attack. As a result of the asymmetrical profiling of the intermediate guide grids following the inlet guide grid, any remaining residual asymmetries of the flow after the first step may possibly be further reduced.

Eine vorteilhafte Ausführungsform der Erfindung sieht vor, dass einzelne Leitschaufelgruppen ein von den übrigen Leitschaufeln abweichendes Schaufelprofil und/oder Anstellwinkel aufweisen. Dies ermöglicht eine rationelle Fertigung und entsprechende Kosteneinsparungen. Beispielsweise können die Leitschaufeln in mehreren Gruppen unterschiedlicher Geometrie angeordnet sein.An advantageous embodiment of the invention provides that individual vane groups have a blade profile deviating from the remaining vanes and / or angle of attack. This allows a rational production and corresponding cost savings. For example, the guide vanes may be arranged in several groups of different geometry.

Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass die Leitschaufeln der jeweiligen Leitschaufelgruppen voneinander abweichende Schaufelprofile und/oder Anstellwinkel aufweisen.A further advantageous embodiment of the invention provides that the guide vanes of the respective vanes groups have mutually differing blade profiles and / or angle of attack.

Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass alle Leitschaufeln unterschiedlich profiliert sind und/oder einen unterschiedlichen Anstellwinkel aufweisen. D.h. hier kann eine gezielte Profilierung jeder einzelnen Schaufel oder eine Umstaffelung der einzelnen Schaufeln erfolgen und dadurch eine Anpassung an die asymmetrische Anströmung vorgenommen werdenA further advantageous embodiment of the invention provides that all guide vanes are profiled differently and / or have a different angle of attack. That Here, a targeted profiling of each blade or a staggering of the individual blades can be done and thereby made an adjustment to the asymmetric flow

Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass die Leitschaufeln verstellbar ausgebildet sind. Durch eine unterschiedliche Verstellung von zumindest einzelnen Schaufeln oder Schaufelgruppen kann ebenfalls der gewünschte Effekt erzielt werden, da hierdurch quasi eine gezielte Umstaffelung einzelner Schaufeln erfolgen kann. Dies hat weiterhin der Vorteil, dass bei veränderten Strömungsverhältnissen die individuelle Ausrichtung des Leitgitters nachgefahren werden kann.A further advantageous embodiment of the invention provides that the guide vanes are designed to be adjustable. By a different adjustment of at least individual blades or blade groups also the desired effect can be achieved, since this can be done quasi a targeted rescaling of individual blades. This has the further advantage that with changed flow conditions, the individual alignment of the guide grid can be traced.

Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass die Leitschaufeln eintrittsseitig aus einem feststehenden Teil und austrittsseitig aus einem schwenkbaren Teil gebildet sind. Hierdurch lassen sich auch individuell verschiedene Profilierungen einzelner Schaufeln des Leitschaufelgitters erstellen, wenn die entsprechende Verstellung für einzelne oder alle Schaufeln individuell verschieden erfolgt.A further advantageous embodiment of the invention provides that the guide vanes are formed on the inlet side of a fixed part and the outlet side of a pivotable part. As a result, individually different profiles of individual blades of the vane grille can also be created if the corresponding adjustment for individual or all blades takes place individually differently.

Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass für einzelne oder alle Leitschaufeln jeweils eine individuelle Regelung vorgesehen ist. Dies ermöglicht ein individuelles Nachfahren jeder einzelnen Schaufel bei veränderten Strömungsbedingungen.A further advantageous embodiment of the invention provides that an individual control is provided for each or all vanes. This enables individual descendants of each individual blade under changed flow conditions.

Weitere die Erfindung verbessernde Maßnahmen werden nachstehend gemeinsam mit der Beschreibung eines bevorzugten Ausführungsbeispiels der Erfindung anhand der Figuren näher dargestellt. Es zeigen:

Fig. 1
einen schematischen Darstellung eines Eintrittsleitgitters gemäß der vorliegenden Erfindung;
Fig. 2
ein schematischer Darstellung eines Eintrittsleitgitters vom Stand der Technik;
Further measures improving the invention will be described in more detail below together with the description of a preferred embodiment of the invention with reference to FIGS. Show it:
Fig. 1
a schematic representation of a Eintrittsleitgitters according to the present invention;
Fig. 2
a schematic representation of a Eintrittsleitgitters of the prior art;

Figur 1 zeigt einen schematischen Darstellung eines abgewickelten Eintrittsleitgitters gemäß der vorliegenden Erfindung mit Multiprofilen, d.h. individueller Profilierung jeder einzelnen Schaufel des Eintrittsleitgitters. Dadurch sind die Schaufeln an den variablen umfangsunsymmetrischen Anströmwinkel des Eintrittsleitgitters angepasst. Diese unsymmetrische Anströmung wird durch den asymmetrischen Lufteinlass verursacht. Durch das erfindungsgemäße Eintrittsleitgitter wird über den ganzen Umfang ein konstanter Abströmwinkel erzeugt und der ersten Verdichterstufe weitgehend umfangssymmetrische Eintrittsbedingungen weitergegeben. Dies führt zu einer verbesserten Stabilität und einem verbesserten Wirkungsgrad des Verdichters. FIG. 1 shows a schematic representation of a developed Eintrittsleitgitters according to the present invention with multi-profiles, ie individual profiling of each blade of the Eintrittsleitgitters. As a result, the blades are adapted to the variable circumferentially asymmetrical angle of attack of the inlet guide grille. This unbalanced flow is caused by the asymmetric air inlet. By Eintrittsleitgitter invention a constant outflow angle is generated over the entire circumference and the first compressor stage passed largely circumferentially symmetrical entry conditions. This leads to improved stability and improved efficiency of the compressor.

Figur 2 zeigt ein schematischer Darstellung eines abgewickelten Eintrittsleitgitters vom Stand der Technik mit umfangsunsymmetrischer Anströmung, die durch einen asymmetrischen Lufteinlass verursacht wird. Hier weisen die in der Zeichnungsebene äußerste linke und äußerste rechte Leitschaufel Ablösungen auf, die sich in den nachfolgenden Verdichterstufen fortsetzen und zu instabilem Verdichterverhalten, d.h. zu Pumpen führen. Ferner lässt sich aus Figur 2 entnehmen, dass der Abströmwinkel in diesem Fall nicht über den Umfang konstant ist, sondern sich an jeder Leitschaufel ändert, was ebenfalls zu instabilem Verdichterverhalten und Wirkungsgradverlusten führen kann. FIG. 2 Figure 12 is a schematic representation of a prior art unwound inlet guide grate with circumferentially asymmetric flow caused by an asymmetric air inlet. Here, the leftmost and outermost right vane in the plane of the drawing have separations which continue in the subsequent compressor stages and lead to unstable compressor behavior, ie to pumps. It also turns out FIG. 2 It can be seen that the outflow angle in this case is not constant over the circumference, but changes at each vane, which can also lead to unstable compressor behavior and efficiency losses.

Die Erfindung beschränkt sich in ihrer Ausführung nicht auf das vorstehend angegebene bevorzugte Ausführungsbeispiel. Vielmehr ist eine Anzahl von Varianten denkbar, welche von der in den Patentansprüchen beanspruchten Lösung auch bei anders gearteten Ausführungen Gebrauch macht.The invention is not limited in its execution to the above-mentioned preferred embodiment. Rather, a number of variants are conceivable which makes use of the claimed in the claims solution even in other types.

Claims (8)

  1. Turboprop engine or helicopter engine comprising an asymmetrical air intake and a compressor arranged downstream of the air intake, which compressor has an inlet guide baffle formed of guide vanes, characterized in that at least some guide vanes of the inlet guide baffle have a different vane profile and/or a different angle of attack from the rest of the guide vanes, such that a constant outflow angle is created by the inlet guide baffle over the entire circumference.
  2. Turboprop engine or helicopter engine according to claim 1, characterized in that single or multiple guide baffles following the inlet guide baffle comprise at least some guide vanes that have a different vane profile and/or a different angle of attack from the rest of the guide vanes.
  3. Turboprop engine or helicopter engine according to either claim 1 or claim 2, characterized in that some guide vane groups have a different vane profile and/or a different angle of attack from the rest of the guide vanes.
  4. Turboprop engine or helicopter engine according to claim 3, characterized in that the guide vanes in each guide vane group have different vane profiles and/or different angles of attack from one another.
  5. Turboprop engine or helicopter engine according to any of claims 1 to 4, characterized in that all the guide vanes have different profiles and/or a different angle of attack.
  6. Turboprop engine or helicopter engine according to any of claims 1 to 5, characterized in that the guide vanes are designed to be adjustable.
  7. Turboprop engine or helicopter engine according to any of claims 1 to 6, characterized in that the guide vanes are formed of a stationary part on the inlet side and a pivotable part on the outlet side.
  8. Turboprop engine or helicopter engine according to either claim 6 or claim 7, characterized in that an individual control system is provided for some or all of the guide vanes.
EP09737335.1A 2008-09-29 2009-09-09 Axial turbomachine having asymmetrical compressor inlet guide baffle Active EP2329150B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008049358A DE102008049358A1 (en) 2008-09-29 2008-09-29 Axial flow machine with asymmetric compressor inlet guide
PCT/DE2009/001281 WO2010034285A1 (en) 2008-09-29 2009-09-09 Axial turbomachine having asymmetrical compressor inlet guide baffle

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EP2329150A1 EP2329150A1 (en) 2011-06-08
EP2329150B1 true EP2329150B1 (en) 2018-03-21

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US (1) US20110164967A1 (en)
EP (1) EP2329150B1 (en)
CN (1) CN102165198A (en)
CA (1) CA2738201A1 (en)
DE (1) DE102008049358A1 (en)
WO (1) WO2010034285A1 (en)

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WO2010034285A1 (en) 2010-04-01
DE102008049358A1 (en) 2010-04-01
CA2738201A1 (en) 2010-04-01
CN102165198A (en) 2011-08-24
EP2329150A1 (en) 2011-06-08
US20110164967A1 (en) 2011-07-07

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