EP0000754A1 - Admission system for a gas turbine compressor - Google Patents

Admission system for a gas turbine compressor Download PDF

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Publication number
EP0000754A1
EP0000754A1 EP78100542A EP78100542A EP0000754A1 EP 0000754 A1 EP0000754 A1 EP 0000754A1 EP 78100542 A EP78100542 A EP 78100542A EP 78100542 A EP78100542 A EP 78100542A EP 0000754 A1 EP0000754 A1 EP 0000754A1
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Prior art keywords
section
cross
intake
compressor
transition part
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EP78100542A
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German (de)
French (fr)
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EP0000754B1 (en
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Konrad Goebel
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Kraftwerk Union AG
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Kraftwerk Union AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L41/00—Branching pipes; Joining pipes to walls
    • F16L41/02—Branch units, e.g. made in one piece, welded, riveted
    • F16L41/023—Y- pieces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants

Definitions

  • the invention relates to an intake system for the compressor of a gas turbine which is arranged on the same shaft in addition to a power machine and has intake ducts which run laterally next to the power machine parallel to the shaft and which has a transition part with a hollow cylindrical cross section, which is provided with an inner and outer conical jacket and leads to the shaft , axial inlet opening of the compressor are connected.
  • Beer is a generator as a utility machine, which is surrounded by a hollow cylindrical annulus.
  • the intake air flows vertically from above through silencers and filters into this cavity. into it, where it is deflected by 90 ° in the direction of the turbine axis and the intake cross-section of the compressor is fed via a hollow-cone-shaped transition part.
  • this known solution cannot prevent a flow obstruction in the duct part below the generator foundation due to the foundation supports located there on the compressor side.
  • Abandonment of the Invention is to provide an intake system, the instabilities in the air flow, as before largely avoided by deflections and by discontinuous changes in cross-section, particularly with large mass flows, without it being necessary to arrange the power machine at the exhaust-side end of the turbine.
  • this object is achieved in that there are only two suction ducts separated from one another next to the power machine, that between the inner cone shell and the outer cone shell of the transition part, in the direction of flow, there are converging baffles with a vertical plate plane which come into contact with the compressor inlet opening and end there, and that the cross section of each intake duct is adapted, at least on the side facing the transition part, to the input cross section of the transition part which is delimited by the inner and outer conical jacket and the vertical guide plate.
  • FIG. 2 shows the flow cross section of the intake ducts according to FIG. 1.
  • FIGS. 3 to 5 show a transition part in three views and in FIGS. 6 to 9 a transfer duct part for adapting the cross sections of the intake ducts to the input cross section of the transition part.
  • 6 and 7 show two mutually perpendicular views of the transfer duct part and
  • FIGS. 8 and 9 show views corresponding to arrows VIII and IX.
  • a power machine and the compressor 6 of a gas turbine are arranged side by side on a shaft.
  • the shaft axis is designated 1b.
  • the intake channels 1 run parallel to shaft axis 1b. At their lower end they can be connected, for example, to the outlet of a silencer (not shown) and an air filter.
  • a transfer duct part 2 adjoins the upper ends of the intake ducts 1 and adjusts the cross section of the two intake ducts to the entrance of a transition part 3.
  • the transition part 3 has a hollow cylindrical outlet cross section and is placed directly on the suction opening of the compressor 6.
  • the cone shells 7 and 8 enclose a hollow cone-shaped cross section, which is divided by the guide plates 5 into two channel halves 25 with the cross-sectional contours shown in FIG.
  • the cross-sectional contours consist of the leading edges 15 of the vertical guide plates 5, the pitch circle 17 of the inner cone shell 7 and the pitch circle 16 of the outer.
  • Cone jacket 8 ..
  • the guide plates 5 are only one-dimensionally curved.
  • the curvature of the guide plates 5 is chosen so that the cross sections the channel halves 25 starting from the inlet cross-section 9 of the transition part 3 to decrease steadily in the direction of the outlet cross-section.
  • the mass flow of the flowing gas experiences an at least constant, but preferably increasing acceleration, without an abrupt change in speed occurring.
  • a transfer duct part 2 is arranged between the intake ducts 1 and the transition part 3, which is shown in elevation in FIG. 6 and in plan view in FIG.
  • FIG. 6 shows the shape of the outlet cross section 10 of the transfer duct part 2, which adjoins the inlet cross section 9 of the transition part 3.
  • the size of the cross sections is selected so that the cross section 1 a of both intake ducts 1 is the same size or larger than the outlet cross sections 10 of the transfer duct part 2. This also prevents a sudden deceleration in the speed of the mass flow in the region of the transfer duct part.
  • the outlet cross section 10 of the transfer duct part 2 is formed by the outline contours 18, 19, 20, 21 and 22.
  • the triangular surface 12 adjoins the duct ceiling and duct underside of the intake duct 1.
  • the triangular surface 11 adjoins the angled outer channel wall 23 at the top and bottom and the triangular surfaces 13 and 14 convert the likewise angled inner channel wall 24 (FIGS. 7 and 9) into the contour contours 19 and 22 of the outlet cross section 10.
  • the described design of the intake system avoids unsteady changes in speed and right-angled deflections of the flowing air. You get one particularly uniform potential field at the inlet of the compressor 6, so that compressors with transonic blading can be used without further ado, which are particularly sensitive to an irregular velocity distribution of the gas before entering the first compressor stage.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Bei Gasturbinentriebwerken wird der erste Verdichter oft unmittelbar an die Nutzleistungsmaschine gekuppelt. Zur Schaffung eines Ansaugsystems für die zu verdichtende Luft ohne Umlenkungen und ohne unstetige Querschnittsänderungen sind zwei voneinander getrennte Ansaugkanäle (1) zu beiden Seiten der Nutzleistungsmaschine (4) angeordnet. Für die Verbindung zum Ansaugquerschnitt des Verdichters (6) ist ein Übergangsteil (3) mit senkrechten dachförmig zueinander verlaufenden Leitblechen (5) vorgesehen, die eine stetige Verminderung des Einströmquerschnittes gewährleisten.In gas turbine engines, the first compressor is often coupled directly to the power machine. To create an intake system for the air to be compressed without deflections and without discontinuous changes in cross-section, two separate intake ducts (1) are arranged on both sides of the power machine (4). For the connection to the intake cross-section of the compressor (6), a transition part (3) is provided with vertical baffles (5) which run in a roof-shaped manner and which ensure a constant reduction in the inflow cross-section.

Description

Die Erfindung betrifft ein Ansaugsystem für den neben einer Nutzleistungsmaschine auf gleicher Welle angeordneten Verdichter einer Gasturbine mit Ansaugkanälen, die seitlich neben der Nutzleistungsmaschine parallel zur Welle verlaufen und die über einen mit einem inneren und äußeren Kegelmantel versehenen, zur Welle hinführenden Übergangeteil mit einer im Querschnitt hohlzylindrischen, axialen Einlaßöffnung des Verdichters verbunden sind.The invention relates to an intake system for the compressor of a gas turbine which is arranged on the same shaft in addition to a power machine and has intake ducts which run laterally next to the power machine parallel to the shaft and which has a transition part with a hollow cylindrical cross section, which is provided with an inner and outer conical jacket and leads to the shaft , axial inlet opening of the compressor are connected.

Eine derartige Anordnung ist in dem deutschen Gebrauchsmuster 7 417 306 beschrieben. Bier ist als Nutzleistungsmaschine ein Generator vorgesehen, der von einem hohlzylindrischen Ringraum umgeben ist. Senkrecht von oben strömt die Ansaugluft über Schalldämpfer und Filter in diesen Hohlraum. hinein, wo sie um 90° in Richtung der Turbinenachse umgelenkt und den Ansaugquerschnitt des Verdichters über ein hohlkegelförniges Übergangsteil zugeführt wird. Neben der notwendigen Umlenkung der Gase im Ansaugkanal um 90° ist bei dieser bekannten Lösung eine Strömungsbehinderung im Kanalteil unterhalb des Generatorfundamentes durch die dort notwendigen verdichterseitig gelegenen Fundamentstützen nicht zu vermeiden.Such an arrangement is described in German utility model 7 417 306. Beer is a generator as a utility machine, which is surrounded by a hollow cylindrical annulus. The intake air flows vertically from above through silencers and filters into this cavity. into it, where it is deflected by 90 ° in the direction of the turbine axis and the intake cross-section of the compressor is fed via a hollow-cone-shaped transition part. In addition to the necessary deflection of the gases in the intake duct by 90 °, this known solution cannot prevent a flow obstruction in the duct part below the generator foundation due to the foundation supports located there on the compressor side.

Aufgabe der rorliegenden. Erfindung ist es, ein Ansaugsystem anzugeben, das Instabilitäten in der Luftströmung, wie sie vor allem durch Umlenkungen und durch unstetige Querschnittsveränderungen insbesondere bei großen Massenströmen vorkommen, weitgehend vermeidet, ohne daß es notwendig wird, die Nutzleistungsmaschine an das abgasseitige Ende der Turbine anzuordnen.Abandonment of the Invention is to provide an intake system, the instabilities in the air flow, as before largely avoided by deflections and by discontinuous changes in cross-section, particularly with large mass flows, without it being necessary to arrange the power machine at the exhaust-side end of the turbine.

Erfindungsgemäß wird diese Aufgabe dadurch gelöst, daß nur seitlich neben der Nutzleistungsmaschine zwei voneinander getrennte Ansaugkanäle vorhanden sind, daß sich zwischen dem inneren Kegelmantel und dem äußeren Kegelmantel des Übergangsteils in Strömungsrichtung aufeinander zulaufende Leitbleche mit senkrechter Blechebene befinden, die sich vor der Einlaßöffnung des Verdichters berühren und dort enden, und daB der Querschnitt jedes Ansaugkanals mindestens an der dem Übergangsteil zugewandtem Seite an den durch den inneren und äußeren Kegelmantel und das senkrechte Leitblech begrenzten Eingangsquerschnitt des Übergangsteils angepaßt ist.According to the invention, this object is achieved in that there are only two suction ducts separated from one another next to the power machine, that between the inner cone shell and the outer cone shell of the transition part, in the direction of flow, there are converging baffles with a vertical plate plane which come into contact with the compressor inlet opening and end there, and that the cross section of each intake duct is adapted, at least on the side facing the transition part, to the input cross section of the transition part which is delimited by the inner and outer conical jacket and the vertical guide plate.

Ein Ausführungsbeispiel ist in Figur 1 schematisch im Grundriß dargestellt.An embodiment is shown schematically in Figure 1 in plan.

Figur 2 zeigt den Strömungsquerschnitt der Ansaugkanäle nach Figur 1. In den Figuren 3 bis 5 ist ein Übergangsteil in drei Ansichten und in den Figuren 6 bis 9 ein Überleitkanslteil zur Anpassung der Querschnitte der Ansaugkanäle an den Eingangsquerschnitt des Übergangsteils dargestellt. Hierbei zeigen die Figuren 6 und 7 zwei zueinander senkrechte Ansichten des Überleitkanalteils und die Figuren 8 und 9 Ansichten entsprechend der Pfeile VIII und IX.FIG. 2 shows the flow cross section of the intake ducts according to FIG. 1. FIGS. 3 to 5 show a transition part in three views and in FIGS. 6 to 9 a transfer duct part for adapting the cross sections of the intake ducts to the input cross section of the transition part. 6 and 7 show two mutually perpendicular views of the transfer duct part and FIGS. 8 and 9 show views corresponding to arrows VIII and IX.

In Figur 1 ist eine Nutzleistungsmaschine und der Verdichter 6 einer im einzelnen nicht dargestellten Gasturbine gemeinsam auf einer Welle nebeneinander angeordnet. Die Wellenachse ist mit 1b bezeichnet. In Höhe und zu beiden Seiten der Wellenachse 1b befinden sich zwei Ansaugkanäle 1 mit rechteckigem Querschnitt 1a. Die Ansaugkanäle 1 laufen dabei parallel zur wellenachse 1b. Sie können an ihrem unteren Ende beispielsweise mit dem Ausgang eines nicht dargestellten Schalldämpfers sowie eines Luftfilters verbunden sein. An die oberen Enden der Ansaugkanäle 1 grenzt ein Überleitkanalteil 2 an, das den Querschnitt der beiden Ansaugkanäle an den Eingang eines Übergangsteils 3 anpaßt. Das Übergangsteil 3 hat einen hohlzylindrischen Ausgangsquerschnitt und ist unmittelbar auf die Ansaugöffnung des Verdichters 6 aufgesetzt.In FIG. 1, a power machine and the compressor 6 of a gas turbine (not shown in detail) are arranged side by side on a shaft. The shaft axis is designated 1b. At the height and on both sides of the shaft axis 1b there are two suction channels 1 with a rectangular cross-section 1a. The intake channels 1 run parallel to shaft axis 1b. At their lower end they can be connected, for example, to the outlet of a silencer (not shown) and an air filter. A transfer duct part 2 adjoins the upper ends of the intake ducts 1 and adjusts the cross section of the two intake ducts to the entrance of a transition part 3. The transition part 3 has a hollow cylindrical outlet cross section and is placed directly on the suction opening of the compressor 6.

In dem Übergangsteil 3 werden die Halbströme des Gases aus den Ansaugkanälen 1 zusammengeführt, ohne daB unstetige Querschnittsveränderungen auftreten. Dieser Übergangsteil ist in den Figuren 3, 4 und 5 im einzelnen dargestellt. Er setzt sich aus drei Bauteilen zusaamen:

  • Dem inneren Kegelmantel 7, durch welchen die Welle mit der Wellenachse 1b zur Verbindung der Nutzleistungsmaschine 4 mit dem Verdichter 6 geführt ist;
  • dem äußeren Kegelmantel 8 mit einem Neigungswinkel gegen die Turboachse von weniger als 30° und
  • den beide Kegelmäntel 7, 8 in der Vertikalebene verbindenden Leitblechen 5, deren Eintrittskanten 15 in Figur 4 sichtbar sind.
In the transition part 3, the half flows of the gas from the intake channels 1 are brought together without inconsistent cross-sectional changes occurring. This transition part is shown in Figures 3, 4 and 5 in detail. It is composed of three components:
  • The inner cone jacket 7 through which the shaft is guided with the shaft axis 1b for connecting the power machine 4 to the compressor 6;
  • the outer cone shell 8 with an angle of inclination against the turbo axis of less than 30 ° and
  • the baffles 5 connecting the two cone shells 7, 8 in the vertical plane, the leading edges 15 of which are visible in FIG.

Die Kegelmäntel 7 und 8 schließen einen hohlkegelförmigen Querschnitt ein, der durch die Leitbleche 5 in zwei Kanalhälften 25 mit den in Figur 4 gezeigten Querschnittskonturen aufgeteilt ist. Die Querschnittskonturen bestehen aus den Eintrittskanten 15 der senkrechten Leitbleche 5, dem Teilkreis 17 des inneren Kegelmantels 7 und dem Teilkreis 16 des äuBeren. Kegelmantels 8..The cone shells 7 and 8 enclose a hollow cone-shaped cross section, which is divided by the guide plates 5 into two channel halves 25 with the cross-sectional contours shown in FIG. The cross-sectional contours consist of the leading edges 15 of the vertical guide plates 5, the pitch circle 17 of the inner cone shell 7 and the pitch circle 16 of the outer. Cone jacket 8 ..

Die Leitbleche 5 sind lediglich eindimensional gekrümmt. Die Krümmung der Leitbleche 5 ist so gewählt, daß die Querschnitte der Kanalhälften 25 beginnend vom Eintrittsquerschnitt 9 des. Übergangsteils 3 sich in Richtung zum Austrittsquerschnitt stetig verkleinern. Hierdurch erfährt der Massenstrom des strömenden Gases eine zumindest konstante, vorzugsweise aber zunehmende Beschleunigung, ohne daB eine sprunghafte Geschwindigkeite- änderung auftritt.The guide plates 5 are only one-dimensionally curved. The curvature of the guide plates 5 is chosen so that the cross sections the channel halves 25 starting from the inlet cross-section 9 of the transition part 3 to decrease steadily in the direction of the outlet cross-section. As a result, the mass flow of the flowing gas experiences an at least constant, but preferably increasing acceleration, without an abrupt change in speed occurring.

Zur Anpassung der Querschnitte der Ansaugkanäle 1 an den Eintrittsquerschnitt 9 des Übergangsteils 3 ist zwischen den Ansaugkanälen 1 und dem Übergangsteil 3 ein Überleitkanalteil 2 angeordnet, das in Figur 6 in Aufriß und in Figur 7 im Grundriß dargestellt ist.In order to adapt the cross sections of the intake ducts 1 to the inlet cross section 9 of the transition part 3, a transfer duct part 2 is arranged between the intake ducts 1 and the transition part 3, which is shown in elevation in FIG. 6 and in plan view in FIG.

Figur 6 zeigt die Form des Austrittsquerschnitts 10 des Überleitkanalteils 2, der an den Eintrittsquerschnitt 9 des Übergangsteils 3 anschließt. Die Größe der Querschnitte ist so gewählt, daB der Querschnitt 1a beider Ansaugkanäle 1 gleich groß oder größer ist als die Austrittsquerschnitte 10 des Überleitkanalteils 2. Hierdurch wird auch im Bereich des Überleitkanalteils eine sprunghafte Verzögerung der Geschwindigkeit des Massenstromes vermieden. Der Austrittsquerschnitt 10 des Überleitkanalteils 2 wird von den Umrißkonturen 18, 19, 20, 21 und 22 gebildet.FIG. 6 shows the shape of the outlet cross section 10 of the transfer duct part 2, which adjoins the inlet cross section 9 of the transition part 3. The size of the cross sections is selected so that the cross section 1 a of both intake ducts 1 is the same size or larger than the outlet cross sections 10 of the transfer duct part 2. This also prevents a sudden deceleration in the speed of the mass flow in the region of the transfer duct part. The outlet cross section 10 of the transfer duct part 2 is formed by the outline contours 18, 19, 20, 21 and 22.

Diese Umrißkonturen sind mit dem Querschnitt 1a der Ansaugkanäle 1 durch ebene Dreiecifläehen 11, 12, 13 und 14 verbunden. Die Dreieckfläche 12 schließt an die Kanaldecke und Kanalunterseite des Ansaugkanals 1 an. Die Dreieckfläche 11 (Figur 8) schließt oben-und unten an die angewinkelte AuBenkanalwand 23 an und durch die Dreieckflächen 13 und 14 wird die ebenfalls angewinkelte Innenkanalwand 24 (Figur 7 und 9) in die Umrißkonturen 19 und 22 des Austrittsquerschnittes 10 überführt.These outline contours are connected to the cross section 1a of the intake ducts 1 by flat triangular surfaces 11, 12, 13 and 14. The triangular surface 12 adjoins the duct ceiling and duct underside of the intake duct 1. The triangular surface 11 (FIG. 8) adjoins the angled outer channel wall 23 at the top and bottom and the triangular surfaces 13 and 14 convert the likewise angled inner channel wall 24 (FIGS. 7 and 9) into the contour contours 19 and 22 of the outlet cross section 10.

Durch die geschilderte Ausbildung des Ansaugsystems werden damit unstetige Geschwindigkeitsänderungen und rechtwinkelige Umlenkungen der strömenden Luft vermieden. Man erhält dadurch ein besonders gleichmäßiges Potentialfeld am Eintritt des Verdichters 6, so daß ohne weiteres Verdichter mit transsonischen Beschaufelungen zur Anwendung kommen können, die in besonderem MaBe empfindlich gegen eine unregelmäßige Geschwindigkeitsverteilung des Gases vor Eintritt in die erste Verdichterstufe sind.The described design of the intake system avoids unsteady changes in speed and right-angled deflections of the flowing air. You get one particularly uniform potential field at the inlet of the compressor 6, so that compressors with transonic blading can be used without further ado, which are particularly sensitive to an irregular velocity distribution of the gas before entering the first compressor stage.

BezuRezeichenlisteRegarding the list of characters

  • 1 Ansaugkanäle1 suction channels
  • 1a rechteckiger Querschnitt1a rectangular cross section
  • 1b Wellenachse1b shaft axis
  • 2 Überleitkanalteil2 transfer duct part
  • 3 Übergangsteil3 transition part
  • 4 Nutzleistungsmaschine4 utility machine
  • 5 Leitbleche5 baffles
  • 6 Verdichter6 compressors
  • 7 innerer Kegelmantel7 inner cone jacket
  • 8 äußerer Kegelmantel8 outer cone jacket
  • 9 Eintrittsquerschnitt9 inlet cross-section
  • 10 Austrittsquerschnitt10 outlet cross section
  • 11 )11)
  • 12) Dreieckflächen 12) triangular surfaces
  • 13 )13)
  • 14 )14)
  • 15 Eintrittskanten15 leading edges
  • 16 Teilkreis16 pitch circle
  • 17 Teilkreis17 pitch circle
  • 18 UmriBkonturen18 outline contours
  • 19 UmriBkonturen19 outline contours
  • 20 UmriBkonturen20 outline contours
  • 21 UmriBkonturen21 outline contours
  • 22 UmriBkonturen22 outline contours
  • 23 AuBenkanalwand23 outer channel wall
  • 24 Innenkanalwand24 inner channel wall

Claims (4)

1. Ansaugsystem für den neben einer Nutzleistungsmaschine auf gleicher Welle angeordneten Verdichter einer Gasturbine mit Ansaugkanälen, die seitlich neben der Nutzleistungsmaschine parallel zur Welle verlaufen und die über einen mit einem inneren und äußeren Kegelmantel versehenen, zur Welle hinführenden Übergangsteil mit einer im Querschnitt hohlzylindrischen, axialen Einlaßöffnung des Verdichters verbunden sind, dadurch gekennzeichnet , daB nur seitlich neben der Nutzleistungsmaschine (4) zwei voneinander getrennte Ansaugkanäle (1) vorhanden sind, daß sich zwischen dem inneren Kegelmantel (7) und dem äußeren Kegelmantel (8) des Übergangsteils (3) in Strömungsrichtung aufeinander zulaufende Leitbleche (5) mit senkrechter Blechebene befinden, die sich vor der Einlaßöffnung des Verdichters (6) berühren und dort enden, und daß der Querschnitt jedes Ansaugkanals (1) mindestens an der dem Übergangeteil (3) zugewandten Seite an den durch den inneren und äußeren Kegelmantel (7,8) und das senkrechte Leitblech (5) begrenzten Eingangsquerschnitt (9) des Übergangsteils (3) angepaßt ist.1.Intake system for the compressor of a gas turbine arranged on the same shaft next to a power machine with suction channels, which run parallel to the shaft next to the power machine and which have an internal and external conical jacket and lead to the shaft with a hollow cylindrical axial section in cross section Inlet opening of the compressor are connected, characterized in that there are only two suction ducts (1) separated from each other next to the power machine (4), that between the inner cone jacket (7) and the outer cone jacket (8) of the transition part (3) in Direction of flow towards each other baffles (5) with a vertical plane of the plate, which touch and end there in front of the inlet opening of the compressor (6), and that the cross section of each intake duct (1) at least on the side facing the transition part (3) on the through the inner and outer cone jacket (7,8) and the se Right guide plate (5) limited input cross-section (9) of the transition part (3) is adapted. 2. Ansaugsystem nach Anspruch 1, dadurch gekennzeichnet, daB die Ansaugkanäle (1) jeweils einen rechteckigen Querschnitt (1a) besitzen und daß ein Überleitkanalteil (2) zur Anpassung des Querschnittes zwischen den Ansaugkanälen (1) und dem Übergangskanalteil (3) vorgesehen ist.2. Intake system according to claim 1, characterized in that the intake ducts (1) each have a rectangular cross section (1a) and that a transfer duct part (2) is provided for adapting the cross section between the intake ducts (1) and the transition duct part (3). 3. Ansaugsystem nach Anspruch 1, dadurch gekennzeichnet, daB die Leitbleche (5) so gekrümmt sind, daB im Bereich des Übergangsteils ein sich stetig Vermindernder Querschnitt in Strömungsrichtung vorhanden ist.3. Intake system according to claim 1, characterized in that the baffles (5) are curved in such a way that there is a continuously decreasing cross-section in the flow direction in the region of the transition part. 4. Ansaugsystem nach Anspruch 2, dadurch gekennzeichnet, daB der Überleitkanalteil (2) aus Blechen zusammengeschweißt ist, die jeweils ebene Dreieckflächen aufweisen.4. Intake system according to claim 2, characterized in that the transfer duct part (2) is welded together from sheet metal, each of which has flat triangular surfaces.
EP78100542A 1977-08-10 1978-07-28 Admission system for a gas turbine compressor Expired EP0000754B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE2736074 1977-08-10
DE19772736074 DE2736074A1 (en) 1977-08-10 1977-08-10 INTAKE SYSTEM FOR THE COMPRESSOR OF A GAS TURBINE

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Publication Number Publication Date
EP0000754A1 true EP0000754A1 (en) 1979-02-21
EP0000754B1 EP0000754B1 (en) 1981-01-07

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EP78100542A Expired EP0000754B1 (en) 1977-08-10 1978-07-28 Admission system for a gas turbine compressor

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EP (1) EP0000754B1 (en)
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CH671753A5 (en) * 1987-02-17 1989-09-29 Johann Arnold
US5297930A (en) * 1991-12-31 1994-03-29 Cornell Research Foundation, Inc. Rotating stall suppression
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DE2860416D1 (en) 1981-02-26
DE2736074A1 (en) 1979-02-15
EP0000754B1 (en) 1981-01-07
US4255082A (en) 1981-03-10

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