EP2337958B1 - Compressor - Google Patents

Compressor Download PDF

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Publication number
EP2337958B1
EP2337958B1 EP09760465.6A EP09760465A EP2337958B1 EP 2337958 B1 EP2337958 B1 EP 2337958B1 EP 09760465 A EP09760465 A EP 09760465A EP 2337958 B1 EP2337958 B1 EP 2337958B1
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EP
European Patent Office
Prior art keywords
nozzle
nozzles
compressor
compressor according
liner segment
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.)
Not-in-force
Application number
EP09760465.6A
Other languages
German (de)
French (fr)
Other versions
EP2337958A1 (en
Inventor
Gottfried SCHÜTZ
Sven-J. Hiller
Yves Burgold
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 date
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Publication of EP2337958A1 publication Critical patent/EP2337958A1/en
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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
    • 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
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • 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
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/60—Fluid transfer
    • F05B2260/601—Fluid transfer using an ejector or a jet pump
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • F05D2270/102—Compressor surge or stall caused by working fluid flow velocity profile distortion

Definitions

  • the present invention relates to a compressor according to the Oberbe-handle of claim 1.
  • a compressor is for example from the US-A-5340271 known.
  • the present invention relates to an engine with a compressor.
  • Fig. 1 shows a schematic diagram of a compressor with insufflation, as it is known, for example, in the prior art.
  • Such a compressor compresses a compression medium, whereby the pressure of the medium increases.
  • the compressor has multiple stages consisting of alternately arranged rotors and stators.
  • the compressor has an outer housing 18, within which a housing segment 20 is arranged, which in turn - seen in the flow direction - is arranged upstream of a rotor 30 having blades. Between the outer housing 18 and the housing segment 20 is a pressure compensation chamber 12, the so-called. Plenum.
  • Such a compressor further rotors and stators, which in Fig. 1 are not shown.
  • compressor pumping can be counteracted by various measures. It is known that the compressor pumps can be delayed when throttling a compressor by blowing in the housing area.
  • these injection nozzles consist of simple slots which pass through the liner segment in such a way that the discharge end faces the rotor.
  • round and flattened injection nozzles are also used.
  • Channels and nozzles with a large cross-sectional area and strong deflection thus tend to form strong three-dimensional cross flows within the nozzle core flow, which can lead to flow separation.
  • this object is achieved by a compressor with the features of claim 1.
  • the object is achieved by an engine having the features of claim 10.
  • the installation space of the nozzles can be reduced and / or a stronger deflection than in the conventional slot solution can be realized.
  • the compressor according to the invention according to claim 2 allows for a small installation space in the liner segment to form a suitable deflection. Since small individual nozzles (individual channels) are formed, even an even stronger deflection can be selected in comparison to the conventional slot solution, without having to worry about crossflows.
  • the compressor according to the invention according to claim 3 allows for a small installation space an advantageous inflow from the pressure chamber into the individual nozzles, and supports a strong deflection in the nozzle.
  • the compressor according to the invention according to claim 5 leads to a slit-like outflow taking advantage of the individual nozzles. As a result, a flat flow can be effected.
  • the compressor according to the invention according to claim 6 allows a high volume flow by taking advantage of the individual nozzles.
  • the compressor according to the invention according to claim 7 enables an improvement of the flow behavior of the main flow at the rotor on the rotor wall.
  • the compressor according to the invention according to claim 8 allows a flexible desired delivery of air in the compressor.
  • the compressor according to the invention according to claim 9 allows better protection against stall along the circumference of the compressor.
  • the compressor according to the invention according to claim 10 allows a cost-effective production of the compressor.
  • the engine according to the invention according to claim 11 utilizes these advantages of a compressor.
  • Fig. 2 shows a longitudinal section through a compressor according to the invention.
  • the compressor has an outer casing 111 within which is disposed a segment 120 (a so-called liner segment) disposed upstream of a rotor (not shown) having blades.
  • the so-called plenum 112 is located between the outer housing 111 and the liner segment 120.
  • the liner segment 120 engages on the outer housing 111 via a so-called housing hook 116.
  • the housing hook 116 the end portion of the liner segment 120 is defined.
  • a pocket 115 is formed on the outer housing 111 facing the plenum 112 in the region of the end portion of the liner segment 120.
  • Blow-in channels 122 with nozzles 123 (see Fig. 8 ) whose inlet region faces the pocket 115 of the outer housing 111 and whose exit region faces the rotor (in FIG Fig. 2 is the blade of the rotor below the liner segment 120 indicated) faces.
  • the nozzles 123 are provided as a nozzle group in the end portion of the liner segment 120.
  • a respective group of nozzles 123 is formed in the end portion of the liner segment 120 by five nozzles 123 which are aligned adjacent to each other in the circumferential direction of the liner segment 120.
  • Several nozzle groups according to the invention may be provided on the liner segment.
  • FIG. 12 is an illustration of circumferential development of a liner segment 120 as viewed from the annulus on the liner segment according to an embodiment of the present invention as compared with a conventional construction.
  • FIG. The nozzle group of five nozzles 123 of the present embodiment is designed as a so-called fan nozzle. As in Fig. 3 to clearly see, the nozzle group of five nozzles 123 of the present embodiment corresponds to a conventional slot nozzle.
  • an air flow is introduced into the pressure chamber 112 (the so-called plenum) via an air supply tube 110 arranged on the outer housing 111 by means of a flange 113. Air passes through the pocket 115 into the inlet region of the nozzles 123, which is blown in via the nozzle outlet toward the rotor 30.
  • Fig. 4 shows speed profiles.
  • the speed profile previously is shown in dashed lines, wherein the speed decrease of the compressor flow is recognizable on the housing wall.
  • the speed profile afterwards is shown pulled through.
  • the increased speed on the housing wall caused by the fan nozzle according to the invention can be seen.
  • Fig. 5 shows a perspective view in partial section of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzle inlet is shown.
  • the inlet region of the group formed as a fan nozzle nozzles 123 is formed so that it faces the pocket 115 in the housing 111.
  • the five nozzles per nozzle group used in this embodiment have a quadrangular cross section in the entrance area.
  • Fig. 6 shows a perspective view in partial section of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzle exit is shown.
  • the exit region of the group formed as a fan nozzle nozzle 123 is formed so that it faces the rotor.
  • the five nozzles per nozzle group used in this embodiment have a quadrangular cross section continuously from the entrance area to the exit area.
  • Fig. 7 and 8th each show perspective sectional views of the end portion of a liner segment according to the embodiment of the present invention.
  • the nozzles are each shown cut.
  • Fig. 8 shows a representation under consideration from a different direction than in Fig. 7 .
  • the many individual nozzles are arranged close to each other. According to the embodiment, the wall web between two adjacent individual nozzles is even smaller than the width of a single nozzle. The many individual nozzles thus form a compact configuration.
  • nozzles (individual nozzles) 123 formed as a fan nozzle cut open, but also the core of the fan nozzle is shown in perspective by reference numeral 123A.
  • the deflection in the respective nozzle is clearly visible.
  • the nozzle inlet is at an angle to the nozzle exit.
  • the nozzle deflection is designed in the axial direction.
  • Fig. 9 shows a perspective sectional view illustrating the nozzle deflection in the liner segment according to the embodiment of the present invention, wherein the nozzles are shown cut away.
  • the entrance area of the respective nozzle 122 has an entrance twist, which results from the angle of the entry area to the vertical of the tangent at the nozzle entrance.
  • the exit area of the respective nozzle 122 has an exit spin resulting from the angle of the exit area to the perpendicular of the tangent to the nozzle exit. As in Fig. 9 shown, in this embodiment, the entrance twist is smaller than the exit spin.
  • the inlet region and the outlet region meet in the deflection region, in which the injection direction is deflected.
  • the fan nozzle according to the invention makes it possible to produce the liner segment, e.g. as a casting or by so-called rapid prototyping.
  • a group of several small individual nozzles is used, which realize the same or a stronger deflection. Due to the compact configuration of the many individual nozzles, the overall effect is comparable to the effect of a large single nozzle (eg the conventional slot nozzle) near the nozzle.
  • the entrance swirl reduces the required deflection and the installation space of the nozzle.
  • the design with individual channels allows almost any spatial guidance of the individual nozzles, so that there is a high degree of design diversity according to the different technical requirements.
  • a larger deflection angle ie a larger difference between the entrance angle and exit angle can be realized without having to fear a flow separation or a compressor pumps.
  • the fan nozzle according to the invention thus enables a strong radial deflection and / or circumferential deflection in the smallest space. Thus, it is ideally suited for use in liner segments.
  • nozzle outlet openings 125 can be any speed and swirl distributions produce in the housing wall. That is, due to the spatial position (radial and / or axial gradation) of the nozzle outlet openings 125 to each other, a desired speed or swirl profile of the air flow can be adjusted in the vicinity of the nozzle on the housing wall (eg a free jet with a twist). In a radial axial grading with adjusted exit angle of the individual nozzles, a specific desired wall normal velocity profile can be adjusted with flush-mounted insufflation.
  • the fan nozzle according to the invention even allows deflections, which lead to an outlet blowing flow, which is directed approximately flush to the outlet nozzle wall.
  • the flow cross section of the Desicherdusen is formed in the above-described embodiment in a quadrangular shape. According to the invention, it can take a square or a rectangular shape.
  • the rectangular shape facilitates slit-like bubbles.
  • five individual nozzles 123 form a group of nozzles.
  • a nozzle group may also be defined by e.g. three, four or six nozzles 123 are formed. The number is not limited as long as several individual nozzles are used.
  • the nozzle deflection in the axial direction can also be designed in the circumferential direction and / or in the axial direction.
  • the fan nozzle according to the invention is provided with an entrance swirl.
  • the invention is not limited thereto.
  • the fan nozzle according to the invention can also be provided without an entrance swirl.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Description

Technisches GebietTechnical area

Die vorliegenden Erfindung betrifft einen Verdichter gemäß dem Oberbe-griff von Anspruch 1. Ein solcher Verdichter ist z.B. aus der US-A-5340271 bekannt. Darüber hinaus betrifft die vorliegende Erfindung ein Triebwerk mit einem Verdichter.The present invention relates to a compressor according to the Oberbe-handle of claim 1. Such a compressor is for example from the US-A-5340271 known. Moreover, the present invention relates to an engine with a compressor.

Technisches ProblemTechnical problem

Zunächst ist der Grundaufbau eines solchen Verdichters erläutert.First, the basic structure of such a compressor will be explained.

Fig. 1 zeigt eine Prinzipsskizze eines Verdichters mit Einblasung, wie er z.B. auch im Stand der Technik bekannt ist. Fig. 1 shows a schematic diagram of a compressor with insufflation, as it is known, for example, in the prior art.

Ein solcher Verdichter verdichtet ein Verdichtungsmedium, wobei sich der Druck des Mediums dabei erhöht. Zum Erreichen von hohen Drücken weist der Verdichter mehrere Stufen auf, die aus abwechselnd angeordneten Rotoren und Statoren bestehen.Such a compressor compresses a compression medium, whereby the pressure of the medium increases. To achieve high pressures, the compressor has multiple stages consisting of alternately arranged rotors and stators.

Der Verdichter weist ein Außengehäuse 18 auf, innerhalb dem ein Gehäusesegment 20 angeordnet ist, das wiederum - in Strömungsrichtung gesehen - stromaufwärtig von einem Rotor 30 angeordnet ist, der Schaufeln aufweist. Zwischen dem Außengehäuse 18 und dem Gehäusesegment 20 befindet sich eine Druckausgleichskammer 12, das sog. Plenum.The compressor has an outer housing 18, within which a housing segment 20 is arranged, which in turn - seen in the flow direction - is arranged upstream of a rotor 30 having blades. Between the outer housing 18 and the housing segment 20 is a pressure compensation chamber 12, the so-called. Plenum.

Bei diesem Verdichter wird ein Luftstrom über ein am Außengehäuse 18 angeordnetes Luftzuführrohr 10 in die Druckausgleichskammer 12 eingebracht, womit sich ein hoher Druck in dieser Kammer 12 aufbaut. Durch im Gehäusesegment 20 angebrachte Düsen wird Luft zum Rotor 30 hin eingeblasen. Im Rotorraum herrscht dabei ein relativ niedriger Druck. Die Rotorlaufrichtung ist in Fig. 1 anhand eines Pfeils angedeutet.In this compressor, an air flow is introduced via a arranged on the outer housing 18 Luftzuführrohr 10 in the pressure compensation chamber 12, whereby a high pressure builds up in this chamber 12. By mounted in the housing segment 20 nozzles air is blown to the rotor 30 out. In the rotor chamber there is a relatively low pressure. The rotor running direction is in Fig. 1 indicated by an arrow.

Darüber hinaus weist ein solcher Verdichter weitere Rotoren und Statoren auf, die in Fig. 1 nicht dargestellt sind.In addition, such a compressor further rotors and stators, which in Fig. 1 are not shown.

Für die Strömung im Verdichter besteht bei einem solchen Aufbau die Gefahr einer Strömungsablösung, da die Strömung des Verdichtungsmediums gegen einen ansteigenden Druck laufen muss. Tritt ein Strömungsabriss in einer oder in mehreren Stufen des Verdichters auf, ergibt sich ein massiver Leistungsabfall im Verdichter. Der Verdichter neigt dann zu einem sog. Pumpen, da die Strömung an der Wandung keine ausreichende kinetische Energie mehr besitzt, um den Druckanstieg zu bewältigen.For the flow in the compressor in such a construction there is a risk of flow separation, since the flow of the compression medium must run against an increasing pressure. If a stall occurs in one or more stages of the compressor, there is a massive performance drop in the compressor. The compressor then tends to a so-called. Pumping, since the flow on the wall no longer has enough kinetic energy to cope with the pressure increase.

Dem Einsetzen dieses sog. Verdichterpumpens kann durch verschiedene Maßnahmen begegnet werden. Es ist bekannt, dass das Verdichterpumpen beim Androsseln eines Verdichters durch Einblasung im Gehäusebereich verzögert werden kann.The onset of this so-called compressor pumping can be counteracted by various measures. It is known that the compressor pumps can be delayed when throttling a compressor by blowing in the housing area.

Eine Maßnahme ist dabei die Gestaltung von umlenkenden Düsen, den sog. Einblasdüsen, am Gehäuserandbereich (in den Linersegmenten), die zur Rotorwand einen zugeführten Luftstrom hin blasen, dessen Blasrichtung zur Rotorwand hin (wandparallel) - mit Drallerzeugung - umgelenkt wird. Diese Umlenkung des Luftstroms in den Düsen erfolgt in Achsrichtung und in Umfangsrichtung des Verdichters. Durch ein spezifisches Gestalten der Einblasdüsen kann das Einsetzen des Verdichterpumpens im Vergleich zu anderen herkömmlichen Lösungen deutlich verzögert werden.One measure is the design of deflecting nozzles, the so-called. Injection nozzles, on the housing edge region (in the liner segments), which blow the supplied airflow to the rotor wall, the blowing direction to the rotor wall (wall parallel) - with swirl generation - is deflected. This deflection of the air flow in the nozzles takes place in the axial direction and in the circumferential direction of the compressor. By a specific design of the injection nozzles, the onset of the compressor pumping can be significantly delayed compared to other conventional solutions.

In der Regel bestehen diese Einblasdüsen aus einfachen Schlitzen, die das Linersegment so durchlaufen, dass das Ausblasende dem Rotor zugewandt ist. Darüber hinaus werden auch runde und abgeflachte Einblasdüsen angewendet.As a rule, these injection nozzles consist of simple slots which pass through the liner segment in such a way that the discharge end faces the rotor. In addition, round and flattened injection nozzles are also used.

Der Einbauraum dieser umlenkenden Einblasdüsen, d.h. im Linersegment, ist dabei sehr beschränkt, somit ergibt ein hoher Umlenkgrad (starke Umlenkung). Der Einbauraum bleibt auch in dem Fall, in dem in den darüber befindlichen Ringraum (Druckraum) hineingebaut wird, sehr beschränkt. Außerdem wird dadurch eine zusätzliche Versperrung bewirkt und die Umlenkung bleibt hoch.The installation space of these deflecting injection nozzles, i. in the liner segment, is very limited, thus resulting in a high degree of deflection (strong deflection). The installation space remains very limited even in the case in which it is built into the annular space located above (pressure chamber). It also causes an additional obstruction and the deflection remains high.

Bei herkömmlichen Konfigurationen ergeben sich dabei Freistrahlen, deren Ausbreitungsverhalten (d.h. die Richtung, die Geschwindigkeits- und Drallverteilung) gar nicht oder nur schwer beeinflussbar ist.In conventional configurations, this results in free jets whose propagation behavior (i.e., the direction, the velocity and twist distribution) is not at all or only with difficulty influenced.

Kanäle und Düsen mit großer Querschnittsfläche und starker Umlenkung neigen somit zur Ausbildung starker dreidimensionaler Querströmungen innerhalb der Düsenkemströmung, die bis zur Strömungsablösung führen kann.Channels and nozzles with a large cross-sectional area and strong deflection thus tend to form strong three-dimensional cross flows within the nozzle core flow, which can lead to flow separation.

Somit tritt jedoch in diesen herkömmlichen Einblasdüsen das Problem auf, dass eine starke räumliche Umlenkung, d.h. ein großer Unterschied zwischen dem Eintrittswinkel und dem Austrittswinkel der Einblasdüse kaum realisierbar ist, da sich dann starke Querströmungen ergeben, die wiederum zu Strömungsablösungen innerhalb der Düse führen.Thus, however, the problem arises in these conventional injection nozzles that a strong spatial deflection, i. a large difference between the entry angle and the exit angle of the injection nozzle is hardly feasible, since then strong cross flows arise, which in turn lead to flow separation within the nozzle.

Die Rückwirkung einer quer gerichteten Außenströmung am Düsenaustritt auf die Düsenkernströmung ist sehr stark, wenn das Verhältnis aus Länge zu Durchmesser gering ist (ca. 1/d < 3 ... 5).The reaction of a transversely directed external flow at the nozzle outlet to the nozzle core flow is very strong when the ratio of length to diameter is low (about 1 / d <3 ... 5).

Außerdem ist es bei kleinen Düsenquerschnitten nahezu unmöglich, Drallerzeuger in die Düse zu integrieren.In addition, with small nozzle cross-sections, it is almost impossible to integrate swirl generators in the nozzle.

Aufgabe der ErfindungObject of the invention

Somit ist es die Aufgabe der vorliegenden Erfindung, einen verbesserten Verdichter, bei dem die Einblasung vorteilhaft gestaltet ist, und ein verbessertes Triebwerk zu schaffen.Thus, it is the object of the present invention to provide an improved compressor in which the injection is advantageously designed and an improved engine.

Im Hinblick auf den Verdichter ist diese Aufgabe durch einen Verdichter mit den Merkmalen von Anspruch 1 gelöst. Im Hinblick auf das Triebwerk ist die Aufgabe durch ein Triebwerk mit den Merkmalen von Anspruch 10 gelöst.With regard to the compressor, this object is achieved by a compressor with the features of claim 1. With regard to the engine, the object is achieved by an engine having the features of claim 10.

Vorteilhafte Weiterbildungen der Erfindung sind Gegenstand der weiteren Ansprüche.Advantageous developments of the invention are the subject of the other claims.

Gemäß dem erfindungsgemäßen Verdichter nach Anspruch 1 ergibt sich eine sog. Fächerdüse mit einer Vielzahl an kleinen Einzeldüsen. In diesem Aufbau realisieren im Vergleich zur herkömmlichen Schlitzlösung mehrere kleine Einzeldüsen, die den Schlitz ersetzen, das Einblasen in den Rotorraum. In den kleinen Einzeldüsen ist das Vermeiden von störenden Querströmungen viel besser realisierbar. Die Einzeldüsen sind weitgehend frei von Querströmungen. Dadurch wird eine starke radiale Umlenkung und/oder Umfangsumlenkung möglich, ohne dass sich frühzeitig Strömungsablösungen ergeben.According to the compressor according to the invention according to claim 1 results in a so-called. Fächerdüse with a large number of small individual nozzles. In this structure, as compared with the conventional slit solution, a plurality of small individual nozzles replacing the slit realize the blowing into the rotor space. In the small individual nozzles, the avoidance of disturbing cross flows is much easier to realize. The individual nozzles are largely free of cross flows. As a result, a strong radial deflection and / or circumferential deflection is possible without early flow separation results.

Dadurch kann wiederum der Einbauraum der Düsen verkleinert und/oder eine stärkere Umlenkung als bei der herkömmlichen Schlitzlösung verwirklicht werden.As a result, in turn, the installation space of the nozzles can be reduced and / or a stronger deflection than in the conventional slot solution can be realized.

Der erfindungsgemäße Verdichter nach Anspruch 2 ermöglicht bei kleinem Einbauraum im Linersegment das Ausbilden einer geeigneten Umlenkung. Da kleine Einzeldüsen (Einzelkanäle) ausgebildet sind, kann im Vergleich zur herkömmlichen Schlitzlösung sogar eine noch stärkere Umlenkung gewählt werden, ohne Querströmungen befürchten zu müssen.The compressor according to the invention according to claim 2 allows for a small installation space in the liner segment to form a suitable deflection. Since small individual nozzles (individual channels) are formed, even an even stronger deflection can be selected in comparison to the conventional slot solution, without having to worry about crossflows.

Der erfindungsgemäße Verdichter nach Anspruch 3 ermöglicht bei kleinem Einbauraum ein vorteilhaftes Einströmen vom Druckraum in die Einzeldüsen, und unterstützt eine starke Umlenkung in der Düse.The compressor according to the invention according to claim 3 allows for a small installation space an advantageous inflow from the pressure chamber into the individual nozzles, and supports a strong deflection in the nozzle.

Bei dem erfindungsgemäßen Verdichter nach Anspruch 4 ist die Flexibilität des Einsatzortes erhöht.In the compressor according to the invention according to claim 4, the flexibility of the site is increased.

Der erfindungsgemäße Verdichter nach Anspruch 5 führt zu einem schlitzähnlichen Ausströmen unter Ausnutzen des Vorteils der Einzeldüsen. Dadurch kann eine flächige Strömung bewirkt werden.The compressor according to the invention according to claim 5 leads to a slit-like outflow taking advantage of the individual nozzles. As a result, a flat flow can be effected.

Der erfindungsgemäße Verdichter nach Anspruch 6 ermöglicht einen hohen Volumenstrom unter Ausnutzen des Vorteils der Einzeldüsen.The compressor according to the invention according to claim 6 allows a high volume flow by taking advantage of the individual nozzles.

Der erfindungsgemäße Verdichter nach Anspruch 7 ermöglicht eine Verbesserung des Strömungsverhaltens der Hauptströmung beim Rotor an der Rotorwand.The compressor according to the invention according to claim 7 enables an improvement of the flow behavior of the main flow at the rotor on the rotor wall.

Der erfindungsgemäße Verdichter nach Anspruch 8 ermöglicht eine flexible wunschgemäße Luftabgabe im Verdichter.The compressor according to the invention according to claim 8 allows a flexible desired delivery of air in the compressor.

Der erfindungsgemäße Verdichter nach Anspruch 9 ermöglicht einen besseren Schutz gegenüber einem Strömungsabriss entlang des Umfangs des Verdichters.The compressor according to the invention according to claim 9 allows better protection against stall along the circumference of the compressor.

Der erfindungsgemäße Verdichter nach Anspruch 10 ermöglicht ein kostengünstiges Herstellen des Verdichters.The compressor according to the invention according to claim 10 allows a cost-effective production of the compressor.

Das erfindungsgemäße Triebwerk nach Anspruch 11 nutzt diese Vorteile eines Verdichters.The engine according to the invention according to claim 11 utilizes these advantages of a compressor.

Die vorliegende Erfindung ist nachstehend anhand von Ausführungsbeispielen genauer erläutert. Zur besseren Veranschaulichung einiger Aspekte der Ausführungsbeispiele sind Zeichnungen beigefügt.The present invention is explained in more detail below with reference to embodiments. To better illustrate some aspects of the embodiments drawings are attached.

Kurzbeschreibung der ZeichnungenBrief description of the drawings

  • Fig. 1 zeigt eine Prinzipsskizze eines Verdichters mit Einblasung, wie er z.B. auch im Stand der Technik bekannt ist. Fig. 1 shows a schematic diagram of a compressor with insufflation, as it is known, for example, in the prior art.
  • Fig. 2 zeigt einen Längsschnitt durch einen erfindungsgemäßen Verdichter. Fig. 2 shows a longitudinal section through a compressor according to the invention.
  • Fig. 3 zeigt eine Darstellung einer Umfangsabwicklung eines Linersegments gemäß einem Ausführungsbeispiel der vorliegenden Erfindung im Vergleich zu einem herkömmlichen Aufbau. Fig. 3 FIG. 12 is an illustration of a circumferential development of a liner segment according to an embodiment of the present invention as compared with a conventional structure. FIG.
  • Fig. 4 zeigt Geschwindigkeitsprofile. Fig. 4 shows speed profiles.
  • Fig. 5 zeigt eine perspektivische Darstellung im Teilschnitt eines Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei der Düseneintritt dargestellt ist. Fig. 5 shows a perspective view in partial section of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzle inlet is shown.
  • Fig. 6 zeigt eine perspektivische Darstellung im Teilschnitt eines Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei der Düsenaustritt dargestellt ist. Fig. 6 shows a perspective view in partial section of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzle exit is shown.
  • Fig. 7 zeigt eine perspektivische Schnittdarstellung eines Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei die Düsen aufgeschnitten dargestellt sind. Fig. 7 shows a perspective sectional view of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzles are shown cut away.
  • Fig. 8 zeigt eine perspektivische Schnittdarstellung eines Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei die Düsen aufgeschnitten dargestellt sind, unter Betrachtung aus einer anderen Richtung als in Fig. 7. Fig. 8 FIG. 12 is a perspective sectional view of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzles are shown cut away as viewed from a direction other than in FIG Fig. 7 ,
  • Fig. 9 zeigt eine perspektivische Schnittdarstellung zur Veranschaulichung der Düsenumlenkung im Linersegment gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei die Düsen aufgeschnitten dargestellt sind. Fig. 9 shows a perspective sectional view illustrating the nozzle deflection in the liner segment according to the embodiment of the present invention, wherein the nozzles are shown cut away.

Ausführliche Beschreibung eines bevorzugten AusführungsbeispielsDetailed description of a preferred embodiment

Nachstehend ist ein Ausführungsbeispiel der vorliegenden Erfindung unter Bezugnahme auf die Zeichnungen beschrieben.Hereinafter, an embodiment of the present invention will be described with reference to the drawings.

Fig. 2 zeigt einen Längsschnitt durch einen erfindungsgemäßen Verdichter. Fig. 2 shows a longitudinal section through a compressor according to the invention.

Zunächst ist der allgemeine Aufbau des erfindungsgemäßen Verdichters beschrieben.First, the general structure of the compressor according to the invention will be described.

Der Verdichter weist ein Außengehäuse 111 auf, innerhalb dem ein Segment 120 (ein sog. Linersegment) angeordnet ist, das stromaufwärtig von einem (nicht dargestelltem) Rotor angeordnet ist, der Laufschaufeln aufweist. Zwischen dem Außengehäuse 111 und dem Linersegment 120 befindet sich das sog. Plenum 112. Über einen sog. Gehäusehaken 116 ist das Linersegment 120 am Außengehäuse 111 in Eingriff. Am Gehäusehaken 116 ist der Endabschnitt des Linersegments 120 definiert. Am Außengehäuse 111 ist dem Plenum 112 zugewandt im Bereich des Endabschnitts des Linersegments 120 eine Tasche 115 ausgebildet.The compressor has an outer casing 111 within which is disposed a segment 120 (a so-called liner segment) disposed upstream of a rotor (not shown) having blades. The so-called plenum 112 is located between the outer housing 111 and the liner segment 120. The liner segment 120 engages on the outer housing 111 via a so-called housing hook 116. At the housing hook 116, the end portion of the liner segment 120 is defined. On the outer housing 111 facing the plenum 112 in the region of the end portion of the liner segment 120, a pocket 115 is formed.

Im Endabschnitt des Linersegments 120 sind sog. Einblaskanäle 122 mit Düsen 123 (siehe Fig. 8) ausgebildet, deren Eintrittsbereich der Tasche 115 des Außengehäuses 111 zugewandt ist und deren Austrittsbereich dem Rotor (in Fig. 2 ist die Laufschaufel des Rotors unterhalb des Linersegments 120 angedeutet) zugewandt ist.In the end portion of the liner segment 120 are so-called. Blow-in channels 122 with nozzles 123 (see Fig. 8 ) whose inlet region faces the pocket 115 of the outer housing 111 and whose exit region faces the rotor (in FIG Fig. 2 is the blade of the rotor below the liner segment 120 indicated) faces.

Die Düsen 123 sind als Düsengruppe im Endabschnitt des Linersegments 120 vorgesehen. Im vorliegenden Ausführungsbeispiel ist eine jeweilige Gruppe an Düsen 123 im Endabschnitt des Linersegments 120 durch fünf Düsen 123 gebildet, die nahe beieinander benachbart in Umfangsrichtung des Linersegments 120 ausgerichtet sind. Es können mehrere erfindungsgemäße Düsengruppen am Linersegment vorgesehen sein.The nozzles 123 are provided as a nozzle group in the end portion of the liner segment 120. In the present embodiment, a respective group of nozzles 123 is formed in the end portion of the liner segment 120 by five nozzles 123 which are aligned adjacent to each other in the circumferential direction of the liner segment 120. Several nozzle groups according to the invention may be provided on the liner segment.

Fig. 3 zeigt eine Darstellung einer Umfangsabwicklung eines Linersegments 120 unter Betrachtung vom Ringraum auf das Linersegment gemäß einem Ausführungsbeispiel der vorliegenden Erfindung im Vergleich zu einem herkömmlichen Aufbau. Die Düsengruppe aus fünf Düsen 123 des vorliegenden Ausführungsbeispiels ist dabei als sog. Fächerdüse ausgebildet. Wie in Fig. 3 deutlich zu sehen, entspricht die Düsengruppe aus fünf Düsen 123 des vorliegenden Ausführungsbeispiels einer herkömmlichen Schlitzdüse. Fig. 3 FIG. 12 is an illustration of circumferential development of a liner segment 120 as viewed from the annulus on the liner segment according to an embodiment of the present invention as compared with a conventional construction. FIG. The nozzle group of five nozzles 123 of the present embodiment is designed as a so-called fan nozzle. As in Fig. 3 to clearly see, the nozzle group of five nozzles 123 of the present embodiment corresponds to a conventional slot nozzle.

Nachstehend ist die Funktionsweise des erfindungsgemäßen Verdichters beschrieben.The operation of the compressor according to the invention is described below.

Bei diesem Verdichter wird ein Luftstrom über ein am Außengehäuse 111 mittels Flansch 113 angeordnetes Luftzuführrohr 110 in die Druckkammer 112 (das sog. Plenum) eingebracht. Über die Tasche 115 gelangt Luft in den Eintrittsbereich der Düsen 123, die über den Düsenaustritt zum Rotor 30 hin eingeblasen wird.In this compressor, an air flow is introduced into the pressure chamber 112 (the so-called plenum) via an air supply tube 110 arranged on the outer housing 111 by means of a flange 113. Air passes through the pocket 115 into the inlet region of the nozzles 123, which is blown in via the nozzle outlet toward the rotor 30.

Fig. 4 zeigt Geschwindigkeitsprofile. Fig. 4 shows speed profiles.

Das Geschwindigkeitsprofil vorher ist gestrichelt dargestellt, wobei die Geschwindigkeitsabnahme der Verdichterströmung an der Gehäusewand erkennbar ist. Das Geschwindigkeitsprofile nachher ist durchgezogen gezeigt. Die von der erfindungsgemäßen Fächerdüse bewirkte erhöhte Geschwindigkeit an der Gehäusewand ist erkennbar.The speed profile previously is shown in dashed lines, wherein the speed decrease of the compressor flow is recognizable on the housing wall. The speed profile afterwards is shown pulled through. The increased speed on the housing wall caused by the fan nozzle according to the invention can be seen.

Details des AusführungsbeispielsDetails of the embodiment

Fig. 5 zeigt eine perspektivische Darstellung im Teilschnitt eines Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei der Düseneintritt dargestellt ist. Fig. 5 shows a perspective view in partial section of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzle inlet is shown.

An der Oberseite des schmalen Linersegments, die dem Plenum 112 zugewandt ist, ist der Eintrittsbereich der als Fächerdüse ausgebildete Gruppe an Düsen 123 so ausgebildet, dass er der Tasche 115 im Gehäuse 111 zugewandt ist. Die bei diesem Ausführungsbeispiel verwendeten fünf Düsen pro Düsengruppe haben einen viereckigen Querschnitt im Eintrittsbereich.At the top of the narrow liner segment, which faces the plenum 112, the inlet region of the group formed as a fan nozzle nozzles 123 is formed so that it faces the pocket 115 in the housing 111. The five nozzles per nozzle group used in this embodiment have a quadrangular cross section in the entrance area.

Fig. 6 zeigt eine perspektivische Darstellung im Teilschnitt eines Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei der Düsenaustritt dargestellt ist. Fig. 6 shows a perspective view in partial section of an end portion of a liner segment according to the embodiment of the present invention, wherein the nozzle exit is shown.

An der Unterseite des Linersegments, die dem Plenum 112 abgewandt ist, ist der Austrittsbereich der als Fächerdüse ausgebildete Gruppe an Düsen 123 so ausgebildet, dass er dem Rotor zugewandt ist. Die bei diesem Ausführungsbeispiel verwendeten fünf Düsen pro Düsengruppe haben einen viereckigen Querschnitt durchgehend vom Eintrittsbereich bis zum Austrittsbereich.On the underside of the liner segment, which faces away from the plenum 112, the exit region of the group formed as a fan nozzle nozzle 123 is formed so that it faces the rotor. The five nozzles per nozzle group used in this embodiment have a quadrangular cross section continuously from the entrance area to the exit area.

Die Fig. 7 und 8 zeigen jeweils perspektivische Schnittdarstellungen des Endabschnitts eines Linersegments gemäß dem Ausführungsbeispiel der vorliegenden Erfindung. Die Düsen sind jeweils aufgeschnitten dargestellt.The Fig. 7 and 8th each show perspective sectional views of the end portion of a liner segment according to the embodiment of the present invention. The nozzles are each shown cut.

Fig. 8 zeigt dabei eine Darstellung unter Betrachtung aus einer anderen Richtung als in Fig. 7. Fig. 8 shows a representation under consideration from a different direction than in Fig. 7 ,

Die vielen Einzeldüsen sind nahe beieinander angeordnet. Gemäß dem Ausführungsbeispiel ist der Wandsteg zwischen zwei benachbarten Einzeldüsen sogar kleiner als die Breite einer Einzeldüse. Die vielen Einzeldüsen bilden somit eine kompakte Konfiguration.The many individual nozzles are arranged close to each other. According to the embodiment, the wall web between two adjacent individual nozzles is even smaller than the width of a single nozzle. The many individual nozzles thus form a compact configuration.

In den Fig. 7 und 8 ist nicht nur die als Fächerdüse ausgebildete Gruppe an Düsen (Einzeldüsen) 123 aufgeschnitten gezeigt, sondern auch der Kern der Fächerdüse perspektivisch mit dem Bezugszeichen 123A dargestellt. Die Umlenkung in der jeweiligen Düse ist hierbei deutlich zu sehen. Der Düseneintritt steht winklig zum Düsenaustritt. In Fig. 8 ist die Düsenumlenkung in Achsrichtung gestaltet.In the Fig. 7 and 8th Not only is the group of nozzles (individual nozzles) 123 formed as a fan nozzle cut open, but also the core of the fan nozzle is shown in perspective by reference numeral 123A. The deflection in the respective nozzle is clearly visible. The nozzle inlet is at an angle to the nozzle exit. In Fig. 8 the nozzle deflection is designed in the axial direction.

Fig. 9 zeigt eine perspektivische Schnittdarstellung zur Veranschaulichung der Düsenumlenkung im Linersegment gemäß dem Ausführungsbeispiel der vorliegenden Erfindung, wobei die Düsen aufgeschnitten dargestellt sind. Fig. 9 shows a perspective sectional view illustrating the nozzle deflection in the liner segment according to the embodiment of the present invention, wherein the nozzles are shown cut away.

Der Eintrittsbereich der jeweiligen Düse 122 hat einen Eintrittsdrall, der sich aus dem Winkel des Eintrittsbereichs zur Senkrechten der Tangente am Düseneingang ergibt. Der Austrittsbereich der jeweiligen Düse 122 hat einen Austrittsdrall, der sich aus dem Winkel des Austrittsbereichs zur Senkrechten der Tangente am Düsenausgang ergibt. Wie in Fig. 9 dargestellt, ist bei diesem Ausführungsbeispiel der Eintrittsdrall kleiner als der Austrittsdrall. In der Düse 122 treffen der Eintrittsbereich und der Austrittsbereich im Umlenkbereich aufeinander, in welchem die Einblasrichtung umgelenkt wird.The entrance area of the respective nozzle 122 has an entrance twist, which results from the angle of the entry area to the vertical of the tangent at the nozzle entrance. The exit area of the respective nozzle 122 has an exit spin resulting from the angle of the exit area to the perpendicular of the tangent to the nozzle exit. As in Fig. 9 shown, in this embodiment, the entrance twist is smaller than the exit spin. In the nozzle 122, the inlet region and the outlet region meet in the deflection region, in which the injection direction is deflected.

Die erfindungsgemäße Fächerdüse ermöglicht eine Herstellung des Linersegments z.B. als Gussteil oder auch per sog. Rapid Prototyping.The fan nozzle according to the invention makes it possible to produce the liner segment, e.g. as a casting or by so-called rapid prototyping.

Vorteile der ErfindungAdvantages of the invention

Statt einer einzelnen stark umlenkenden Einzeldüse wird eine Gruppe an mehreren kleinen Einzeldüsen eingesetzt, die die selbe oder eine stärkere Umlenkung verwirklichen. Durch die kompakte Konfiguration der vielen Einzeldüsen ist die Gesamtwirkung vergleichbar mit der Wirkung einer großen Einzeldüse (z. B. die herkömmliche Schlitzdüse) in Düsennähe. Der Eintrittsdrall reduziert die erforderliche Umlenkung und den Bauraum der Düse.Instead of a single strongly deflecting individual nozzle, a group of several small individual nozzles is used, which realize the same or a stronger deflection. Due to the compact configuration of the many individual nozzles, the overall effect is comparable to the effect of a large single nozzle (eg the conventional slot nozzle) near the nozzle. The entrance swirl reduces the required deflection and the installation space of the nozzle.

Aufgrund des großen Verhältnisses zwischen Länge und Querschnitt der erfindungsgemäßen kleindurchmessrigen Einzeldüsen sind diese weitgehend frei von störenden Querströmungen.Due to the large ratio between the length and cross section of the small diameter single nozzles according to the invention, they are largely free from disturbing cross flows.

Die Bauweise mit Einzelkanälen ermöglicht eine nahezu beliebige räumliche Führung der Einzeldüsen, so dass sich eine hohe Gestaltungsvielfalt entsprechend den unterschiedlichsten technischen Anforderungen ergibt.The design with individual channels allows almost any spatial guidance of the individual nozzles, so that there is a high degree of design diversity according to the different technical requirements.

Somit kann im Gegensatz zu einer Gestaltung mit einer konventionellen Schlitzdüse (siehe Vergleich in Fig. 3) bei der Lösung nach dem vorliegenden Ausführungsbeispiel ein größere Umlenkwinkel d.h. eine größere Differenz zwischen Eintrittswinkel und Austrittswinkel realisiert werden, ohne eine Strömungsablösung oder ein Verdichterpumpen befürchten zu müssen.Thus, in contrast to a design with a conventional slot nozzle (see comparison in FIG Fig. 3 ) In the solution according to the present embodiment, a larger deflection angle ie a larger difference between the entrance angle and exit angle can be realized without having to fear a flow separation or a compressor pumps.

Der zusätzliche Druckverlust durch die größere Wandreibung (größere benetzte Fläche) kann in vielen Fällen toleriert werden.The additional pressure loss due to the greater wall friction (larger wetted area) can be tolerated in many cases.

Die erfindungsgemäße Fächerdüse ermöglicht somit eine starke radiale Umlenkung und/oder Umfangsumlenkung auf kleinstem Raum. Somit ist sie für den Einsatz in Linersegmenten bestens geeignet.The fan nozzle according to the invention thus enables a strong radial deflection and / or circumferential deflection in the smallest space. Thus, it is ideally suited for use in liner segments.

Durch eine spezielle Gestaltung der Düsenaustrittsöffnungen 125 (radialer Versatz, axialer Versatz und/oder Umfangsversatz) lassen sich beliebige Geschwindigkeits- und Drallverteilungen in Gehäusewandnähe erzeugen. D.h. aufgrund der räumlichen Lage (radiale und/oder axiale Stufung) der Düsenaustrittsöffnungen 125 zueinander kann ein gewünschtes Geschwindigkeits- oder Drallprofil des Luftstroms in Düsennähe an der Gehäusewand eingestellt werden (z.B. ein Freistrahl mit Drall). Bei einer radialenaxialen Stufung mit angepasstem Austrittswinkel der Einzeldüsen kann ein spezielles erwünschtes wandnormales Geschwindigkeitsprofil bei wandbündiger Einblasung eingestellt werden.By a special design of the nozzle outlet openings 125 (radial offset, axial offset and / or circumferential offset) can be any speed and swirl distributions produce in the housing wall. That is, due to the spatial position (radial and / or axial gradation) of the nozzle outlet openings 125 to each other, a desired speed or swirl profile of the air flow can be adjusted in the vicinity of the nozzle on the housing wall (eg a free jet with a twist). In a radial axial grading with adjusted exit angle of the individual nozzles, a specific desired wall normal velocity profile can be adjusted with flush-mounted insufflation.

Bei einer Umfangsspreizung der Verteilung der Düsenaustrittsöffnungen 125 der Einzeldüsen 123 lassen sich somit schlitzförmige Geschwindigkeitsverteilungen oder eine Vergleichmäßigung der Strahlgeschwindigkeiten in Umfangsrichtung erzielen.With a circumferential spread of the distribution of the nozzle outlet openings 125 of the individual nozzles 123, slot-shaped velocity distributions or equalization of the jet velocities in the circumferential direction can thus be achieved.

Die erfindungsgemäße Fächerdüse ermöglicht sogar Umlenkungen, die zu einer Austrittsblasströmung führen, die annähernd bündig zur Austrittsdüsenwand gerichtet ist.The fan nozzle according to the invention even allows deflections, which lead to an outlet blowing flow, which is directed approximately flush to the outlet nozzle wall.

Bei der erfindungsgemäßen Fächerdüse ist daher das vorstehend genannte Problem der Strömungsablösung minimiert.In the fan nozzle according to the invention, therefore, the aforementioned problem of flow separation is minimized.

Der Strömungsquerschnitt der Fächerdusen ist im vorstehend beschriebenen Ausführungsbeispiel in viereckiger Form ausgebildet. Gemäß der Erfindung kann er eine quadratische oder eine rechteckige Form einnehmen. Die rechteckige Form erleichtert ein schlitzähnliches Blasen.The flow cross section of the Fächerdusen is formed in the above-described embodiment in a quadrangular shape. According to the invention, it can take a square or a rectangular shape. The rectangular shape facilitates slit-like bubbles.

Im vorstehend beschriebenen Ausführungsbeispiel bilden fünf Einzeldüsen 123 eine Gruppe an Düsen. Eine Düsengruppe kann auch durch z.B. drei, vier oder sechs Düsen 123 gebildet werden. Die Zahl ist nicht beschränkt, solange mehrere Einzeldüsen angewendet werden.In the embodiment described above, five individual nozzles 123 form a group of nozzles. A nozzle group may also be defined by e.g. three, four or six nozzles 123 are formed. The number is not limited as long as several individual nozzles are used.

Im vorstehend beschriebenen Ausführungsbeispiel ist, wie in Fig. 8 besonders gut dargestellt, die Düsenumlenkung in Achsrichtung gestaltet. Die Düsenumlenkung kann auch in Umfangsrichtung und/oder in Achsrichtung gestaltet sein.In the embodiment described above, as in FIG Fig. 8 shown particularly well, designed the nozzle deflection in the axial direction. The nozzle deflection can also be designed in the circumferential direction and / or in the axial direction.

Im vorstehend beschriebenen Ausführungsbeispiel ist die erfindungsgemäße Fächerdüse mit einem Eintrittsdrall versehen. Die Erfindung ist darauf nicht beschränkt. Die erfindungsgemäße Fächerdüse kann auch ohne einen Eintrittsdrall vorgesehen sein.In the embodiment described above, the fan nozzle according to the invention is provided with an entrance swirl. The invention is not limited thereto. The fan nozzle according to the invention can also be provided without an entrance swirl.

Claims (11)

  1. A compressor with an inflow channel (110), which guides a compression medium into a pressure chamber (112) formed within a compressor housing (111), and
    a liner segment (120) provided with nozzles (123), that transmit the compression medium from the pressure chamber (112) to a rotor, wherein the nozzles (123) are formed in the liner segment (120) as a plurality of individual nozzles arranged in a group in a fan-like manner,
    characterized in that
    the individual nozzles are shaped in a square or rectangular manner.
  2. A compressor according to claim 1,
    characterized in that
    each nozzle (123) has an entry section (124) and an outlet section (125), which are at an angle to each other.
  3. A compressor according to claim 1 or 2,
    characterized in that
    each nozzle (123) has an entry section (124) with an entry swirl.
  4. A compressor according to one of claims 1 or 2,
    characterized in that
    each nozzle (123) has an entry section (124) without an entry swirl.
  5. A compressor according to claim 1 to 4,
    characterized in that
    a wall web between two adjacent individual nozzles (123) is smaller than the width of an individual nozzle.
  6. A compressor according to claim 1 to 5,
    characterized in that
    in each case five nozzles (123) form a group of nozzles.
  7. A compressor according to claim 2 to 6,
    characterized in that
    the outlet section (125) is designed, such that the deflection between entry section (124) and an outlet section (125) leads to an outlet blow flow, which is directed approximately flush to the outlet nozzle wall.
  8. A compressor according to one of claims 2 to 7,
    characterized in that
    nozzle deflection occurs in the axial direction and/or circumferential direction to the compressor.
  9. A compressor according to one of claims 1 to 8,
    characterized in that
    several groups of individual nozzles (123) are designed in the liner segment (120) along the circumference of the liner segment (120).
  10. A compressor according to one of claims 1 to 9,
    characterized in that
    the liner segment (120) is produced with the individual nozzles as a cast part.
  11. An engine with a compressor according to one of claims 1 to 10.
EP09760465.6A 2008-10-20 2009-10-16 Compressor Not-in-force EP2337958B1 (en)

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DE102008052372A DE102008052372A1 (en) 2008-10-20 2008-10-20 compressor
PCT/DE2009/001437 WO2010045923A1 (en) 2008-10-20 2009-10-16 Compressor

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DE102012100339A1 (en) * 2012-01-16 2013-07-18 Universität der Bundeswehr München Method and device for stabilizing a compressor flow

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US20110200470A1 (en) 2011-08-18
CA2740992A1 (en) 2010-04-29
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WO2010045923A1 (en) 2010-04-29
EP2337958A1 (en) 2011-06-29

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