EP1574667B1 - Diffuser for compressor - Google Patents
Diffuser for compressor Download PDFInfo
- Publication number
- EP1574667B1 EP1574667B1 EP20040004895 EP04004895A EP1574667B1 EP 1574667 B1 EP1574667 B1 EP 1574667B1 EP 20040004895 EP20040004895 EP 20040004895 EP 04004895 A EP04004895 A EP 04004895A EP 1574667 B1 EP1574667 B1 EP 1574667B1
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- European Patent Office
- Prior art keywords
- constriction
- diffuser
- gas turbine
- wall
- compressor
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- 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.)
- Expired - Lifetime
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- 230000007423 decrease Effects 0.000 claims description 9
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000011084 recovery Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000011002 quantification Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
Definitions
- the invention relates to a gas turbine with a compressor diffuser and there a measure for optimizing a radial mass flow distribution at the inlet of the compressor diffuser.
- the invention also relates to a diffuser itself.
- a diffuser is known in its most general form, a component of a pipeline in which the cross-section grows gradually. This increase in cross-section causes a decrease in the velocity of the medium flowing through it, while the static pressure increases simultaneously.
- a diffuser is usually arranged at the outlet of the gas turbine, in particular immediately after the turbine, and / or at the outlet of the compressor.
- the invention is concerned with the mass flow or total pressure distribution required for optimum operation of the diffuser.
- the compressor outlet diffuser shown there is designed as an axial diffuser and thus comprises an annular channel.
- the inner, hub-side contour of the annular channel is cylindrical and the outer wall is conical, so that the cross-sectional enlargement of the diffuser along its axial extent is formed mainly by the increase of the radius of the outer wall.
- Immediately upstream of the diffuser freestanding vanes are placed as a Nachleitrad, the free ends of the inner wall of the diffuser are facing gap formation.
- a use of freestanding guide vanes leads, in particular in the case of larger radial gaps, to a considerable drop in the velocity of the flowing working medium, that is to say of the heated gas, in the hub region of a turbine shaft at the outlet of a secondary guide wheel.
- the speed drop is accompanied by a total pressure drop.
- the velocity and pressure distribution is especially unfavorable when a cross-sectional widening takes place within the diffuser exclusively via a reduction of the hub radius of the hub-side inner contour of the diffuser.
- a weakened velocity profile in the region of the hub-side inner contour then leads to lossy flow separations on the inner contour of the diffuser. This significantly limits the pressure recovery of the diffuser and thus its overall efficiency.
- a turbine outlet diffuser with a provided on its outer wall constriction known.
- the constriction of the diffuser channel is located immediately downstream of the trailing edge of the last turbine stage blade, on the diffuser outer wall.
- the EP 1 227 217 treats such a constriction downstream of the last blade of the turbine.
- the invention is therefore based on the object of specifying a gas turbine optimized with a view to avoiding or reducing the abovementioned disadvantages with a diffuser.
- the advantage of the invention is that a modification of the mass flow in the direction of the hub of the turbine rotor is caused by the modification of the inner contour of the diffuser housing just in a compressor diffuser through the constriction. In the area of the hub thus increases the speed level.
- the speed drop caused by the hub-side radial gaps, that is to say by the distance between the upstream of the diffuser and the stationary rotor vanes and the hub of the turbine rotor, is thus largely compensated.
- the constriction is located on the inside of the outer wall of the diffuser housing.
- the constriction can be caused by material being deposited on the inside of the outer wall of the diffuser housing. Another possibility of forming such a constriction is that an adapted, the constriction-containing shaping of the outer wall of the diffuser housing is selected.
- the constriction in the interior of the diffuser gradually decreases in the direction of flow of the medium flowing through, so that the constriction does not influence the intended mode of operation of the diffuser (speed reduction and pressure increase for the medium flowing through) negligibly or negligibly.
- the constriction at the inlet of the diffuser is not abrupt but continuous and in a manner in which in the direction of the medium flowing through an increase of the constriction up to a maximum constriction is such that the increase in constriction to the maximum constriction significantly larger is as the decrease in the constriction following the maximum constriction.
- a gas turbine has a compressor for combustion air, a combustion chamber and a turbine for driving both the compressor and a working machine, for.
- a generator on.
- the turbine and the compressor are arranged on a common, also referred to as a turbine rotor turbine shaft, with which the machine is connected, and which is rotatably mounted about its longitudinal axis.
- the combustion chamber is equipped with at least one burner for the combustion of a liquid or gaseous fuel.
- the compressor as well as the turbine each have a number of rotatable blades connected to the turbine shaft.
- the blades are arranged in a ring on the turbine shaft and thus form a number of blade rows.
- both the compressor and the turbine include a number of stationary vanes which are also annularly mounted to form vanes rows on an inner wall of the housing of the compressor or turbine.
- the blades serve to drive the turbine shaft by momentum transfer from the turbine flowing through the working fluid.
- the guide vanes serve to guide the flow of the working medium between two respective rows of blades or rotor blade rings viewed in the flow direction of the working medium.
- a successive pair of a ring of vanes or a row of vanes and a ring of blades or a blade row is also referred to as a turbine stage or as a compressor stage.
- the compressor or turbine housing Between the blades and the inner contour of the respective surrounding housing, so the compressor or turbine housing remains a radial gap whose size is dimensioned so that during operation of the gas turbine even with thermal expansion of the respective materials stripping of the blades is excluded at the respective inner housing.
- a radial gap remains between the stationary vanes and the turbine shaft. This is also such that a contact between the vanes and the turbine shaft is excluded.
- FIG. 1 shows a sectional view of a gas turbine with a arranged at the output of its compressor diffuser 1 with a diffuser housing 2.
- the diffuser housing 2 has in a connection region 3, ie in the region of the transition from the compressor of the gas turbine to the diffuser 1, a constriction 5 reducing the inner radius of the housing 2 on.
- a portion of the diffuser 1 belonging to the connection region 3 is referred to as the inlet 4 of the diffuser 1.
- the inlet 4 has an annular space contour. The dimensions of the inlet 4 are determined essentially by its inner radius.
- the flow space of the diffuser 1 is bounded radially on the outside by an outer wall of the diffuser housing 2 and radially inward by a hub-side inner contour.
- the constriction 5 decreases gradually within the diffuser 1 in the flow direction of the medium flowing through, ie the compressed air.
- the flow direction runs from left to right.
- At the inlet 4 of the diffuser 1 takes place - also in the direction of the medium flowing through - an increase in the constriction to a maximum constriction 5 such that the increase in constriction to the maximum constriction 5 is significantly greater than the decrease in constriction following the maximum Constriction 5.
- the quantification of an aspect ratio between a distance during which the constriction at the inlet 4 initially increases to the maximum constriction 5 and a distance during which the constriction within the diffuser 1 then decreases again is possible as follows:
- the length of a distance along the Outer contour of the diffuser housing 2 parallel to the flow direction of the medium, during which the constriction increases to the maximum constriction 5, is less than one fifth of the length of a distance during which the constriction decreases from the maximum constriction 5 again.
- the one-sided on the inside of the diffuser housing 2, in particular in the region of the Diffusoreinlasses 4, made radius reduction (constriction 5) causes a redistribution of the mass flow in the direction of the hub of the turbine rotor. This increases the speed level in the hub area (see also FIG. 2 ). Overall, there is a substantially improved velocity and total pressure distribution at the inlet 4 of the diffuser 1. Increasing the near-net velocity level causes the hub boundary layer to run at a substantially higher pressure, thus improving the pressure recovery and overall compressor efficiency.
- FIG. 2 shows a graphical representation of a theoretically calculated speed increase in the region of the hub of a turbine runner.
- the abscissa shows the increase in the axial velocity compared to the unmodified design.
- r * as the radius, the distance from the hub of the turbine rotor is removed. It can be seen the significant increase in speed in the immediate hub area, ie in the area in which so far due to a caused by the radial gap at the outer end of the vanes slit flow a drop in speed was observed.
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- Engineering & Computer Science (AREA)
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Description
Die Erfindung betrifft eine Gasturbine mit einem Verdichterdiffusor und dort eine Maßnahme zur Optimierung einer radialen Massenstromverteilung am Eintritt des Verdichterdiffusors. Die Erfindung betrifft ebenfalls einen Diffusor selbst.The invention relates to a gas turbine with a compressor diffuser and there a measure for optimizing a radial mass flow distribution at the inlet of the compressor diffuser. The invention also relates to a diffuser itself.
Gasturbinen mit Verdichterdiffusor, im Folgenden kurz als Diffusor bezeichnet, sind allgemein bekannt. Ein Diffusor ist in seiner allgemeinsten Form bekanntlich ein Bauteil einer Rohrleitung, in dem der Querschnitt allmählich wächst. Dies Zunahme des Querschnitts bedingt eine Abnahme der Geschwindigkeit des hindurch strömenden Mediums, während der statische Druck gleichzeitig ansteigt. Bei einer Gasturbine mit einem Verdichter, einer Brennkammer und einer Turbine ist ein Diffusor üblicherweise am Ausgang der Gasturbine, insbesondere unmittelbar im Anschluss an die Turbine, und/oder am Ausgang des Verdichters angeordnet.Gas turbines with compressor diffuser, hereinafter referred to as a diffuser, are well known. A diffuser is known in its most general form, a component of a pipeline in which the cross-section grows gradually. This increase in cross-section causes a decrease in the velocity of the medium flowing through it, while the static pressure increases simultaneously. In a gas turbine with a compressor, a combustion chamber and a turbine, a diffuser is usually arranged at the outlet of the gas turbine, in particular immediately after the turbine, and / or at the outlet of the compressor.
Die Erfindung befasst sich mit der Massenstrom- oder Totaldruckverteilung, die für eine optimale Wirkungsweise des Diffusors erforderlich ist.The invention is concerned with the mass flow or total pressure distribution required for optimum operation of the diffuser.
Eine vorgenannte Gasturbine ist beispielsweise aus der japanischen Patentanmeldung
Eine Verwendung freistehender Leitschaufeln führt insbesondere bei größeren Radialspalten zu einem erheblichen Geschwindigkeitseinbruch des strömenden Arbeitsmediums, also des erwärmten Gases, im Nabenbereich einer Turbinenwelle am Austritt eines Nachleitrades. Der Geschwindigkeitseinbruch geht mit einem Totaldruckeinbruch einher.A use of freestanding guide vanes leads, in particular in the case of larger radial gaps, to a considerable drop in the velocity of the flowing working medium, that is to say of the heated gas, in the hub region of a turbine shaft at the outlet of a secondary guide wheel. The speed drop is accompanied by a total pressure drop.
Die Geschwindigkeits- und Druckverteilung ist vor allem dann ungünstig, wenn eine Querschnittserweiterung innerhalb des Diffusors ausschließlich über eine Reduktion des Nabenradius der nabenseitigen Innenkontur des Diffusors erfolgt. Ein geschwächtes Geschwindigkeitsprofil im Bereich der nabenseitigen Innenkontur führt dann zu Verlust behafteten Strömungsablösungen an der Innenkontur des Diffusors. Dies begrenzt signifikant den Druckrückgewinn des Diffusors und damit dessen Gesamtwirkungsgrad.The velocity and pressure distribution is especially unfavorable when a cross-sectional widening takes place within the diffuser exclusively via a reduction of the hub radius of the hub-side inner contour of the diffuser. A weakened velocity profile in the region of the hub-side inner contour then leads to lossy flow separations on the inner contour of the diffuser. This significantly limits the pressure recovery of the diffuser and thus its overall efficiency.
Zur Lösung dieses Problems ist bisher nur eine spezielle Formgebung der unmittelbar stromauf des Diffusors gelegenen Leitschaufeln in Betracht gezogen worden. Diese Maßnahme bewirkt allerdings nur sehr begrenzt eine Kompensation des durch die Spaltströmung bedingten Geschwindigkeitseinbruchs, so dass bisher die Querschnittserweiterung des Diffusors und damit der erreichbare Druckrückgewinn auf einen der ungünstigen Zuströmung entsprechenden Wert begrenzt bleiben musste. Dies ist insbesondere dann ungünstig, wenn ausreichend axialer Bauraum für große Querschnittserweiterungen bei erträglichen Verzögerungen zur Verfügung steht.To solve this problem, only a special shape of the vanes immediately upstream of the diffuser has been considered. However, this measure causes only a very limited compensation of the speed drop caused by the slit flow, so that so far the cross-sectional widening of the diffuser and thus the achievable pressure recovery had to remain limited to a value corresponding to the unfavorable inflow. This is particularly unfavorable if sufficient axial space for large cross-sectional expansions with tolerable delays available.
Ferner ist aus der
Der Erfindung liegt daher die Aufgabe zugrunde, eine im Hinblick auf eine Vermeidung oder Reduzierung der oben genannten Nachteile optimierte Gasturbine mit einem Diffusor anzugeben.The invention is therefore based on the object of specifying a gas turbine optimized with a view to avoiding or reducing the abovementioned disadvantages with a diffuser.
Diese Aufgabe wird erfindungsgemäß mit einer Gasturbine mit den Merkmalen des Anspruchs 1 gelöst.This object is achieved with a gas turbine having the features of
Der Vorteil der Erfindung besteht darin, dass durch die Modifikation der Innenkontur des Diffusorgehäuses gerade bei einem Verdichterdiffuser durch die Einschnürung eine Umverteilung des Massenstromes in Richtung der Nabe des Turbinenläufers hervorgerufen wird. Im Bereich der Nabe steigt damit das Geschwindigkeitsniveau. Der durch die nabenseitigen Radialspalte, also durch den Abstand zwischen den stromauf des Diffusors liegenden, feststehenden Leitschaufeln und der Nabe des Turbinenläufers bedingte Geschwindigkeitseinbruch wird auf diese Weise zu einem großen Teil kompensiert. Die Einschnürung befindet sich dazu am Innern der Außenwand des Diffusorgehäuses.The advantage of the invention is that a modification of the mass flow in the direction of the hub of the turbine rotor is caused by the modification of the inner contour of the diffuser housing just in a compressor diffuser through the constriction. In the area of the hub thus increases the speed level. The speed drop caused by the hub-side radial gaps, that is to say by the distance between the upstream of the diffuser and the stationary rotor vanes and the hub of the turbine rotor, is thus largely compensated. The constriction is located on the inside of the outer wall of the diffuser housing.
Vorteilhafte Ausgestaltungen der Erfindung sind Gegenstand der Unteransprüche.Advantageous embodiments of the invention are the subject of the dependent claims.
Die Einschnürung kann dadurch hervorgerufen werden, dass Material auf der Innenseite der Außenwand des Diffusorgehäuses angelagert ist. Eine andere Möglichkeit der Ausbildung einer solchen Einschnürung besteht darin, dass eine angepasste, die Einschnürung beinhaltende Formgebung der Außenwand des Diffusorgehäuses gewählt wird.The constriction can be caused by material being deposited on the inside of the outer wall of the diffuser housing. Another possibility of forming such a constriction is that an adapted, the constriction-containing shaping of the outer wall of the diffuser housing is selected.
Vorteilhaft nimmt die Einschnürung im Innern des Diffusors in Strömungsrichtung des durchströmenden Mediums allmählich ab, so dass die Einschnürung die beabsichtigte Wirkungsweise des Diffusors (Geschwindigkeitsreduktion und Druckerhöhung für das durchströmende Medium) nicht oder nur unwesentlich negativ beeinflusst.Advantageously, the constriction in the interior of the diffuser gradually decreases in the direction of flow of the medium flowing through, so that the constriction does not influence the intended mode of operation of the diffuser (speed reduction and pressure increase for the medium flowing through) negligibly or negligibly.
Vorteilhaft erfolgt die Einschnürung am Einlass des Diffusors nicht abrupt sondern kontinuierlich und zwar in einer Art und Weise, bei der in Richtung des durchströmenden Mediums eine Zunahme der Einschnürung bis zu einer maximalen Einschnürung derart erfolgt, dass die Zunahme der Einschnürung bis zur maximalen Einschnürung deutlich größer ist als die Abnahme der Einschnürung im Anschluss an die maximale Einschnürung.Advantageously, the constriction at the inlet of the diffuser is not abrupt but continuous and in a manner in which in the direction of the medium flowing through an increase of the constriction up to a maximum constriction is such that the increase in constriction to the maximum constriction significantly larger is as the decrease in the constriction following the maximum constriction.
Nachfolgend wird ein Ausführungsbeispiel der Erfindung anhand der Zeichnung näher erläutert. Einander entsprechende Gegenstände oder Elemente sind in allen Figuren mit den gleichen Bezugszeichen versehen.An embodiment of the invention will be explained in more detail with reference to the drawing. Corresponding objects or elements are provided in all figures with the same reference numerals.
Darin zeigen:
- FIG 1
- eine schematische Darstellung einer Ringraumkontur am Einlass eines Diffusors, und
- FIG 2
- eine graphische Darstellung eines theoretisch berechneten Geschwindigkeitsanstiegs im Bereich der Nabe eines Turbinenläufers.
- FIG. 1
- a schematic representation of an annular space contour at the inlet of a diffuser, and
- FIG. 2
- a graphical representation of a theoretically calculated speed increase in the region of the hub of a turbine runner.
Eine Gasturbine und deren Arbeitsweise ist allgemein bekannt. Demnach weist eine Gasturbine einen Verdichter für Verbrennungsluft, eine Brennkammer sowie eine Turbine zum Antrieb sowohl des Verdichters wie auch einer Arbeitsmaschine, z. B. eines Generators, auf. Dazu sind die Turbine und der Verdichter auf einer gemeinsamen, auch als Turbinenläufer bezeichneten Turbinenwelle angeordnet, mit der auch die Arbeitsmaschine verbunden ist, und die um ihre Längsachse drehbar gelagert ist. Die Brennkammer ist mit mindestens einem Brenner zur Verbrennung eines flüssigen oder gasförmigen Brennstoffs bestückt.A gas turbine and its operation is well known. Accordingly, a gas turbine has a compressor for combustion air, a combustion chamber and a turbine for driving both the compressor and a working machine, for. As a generator, on. For this purpose, the turbine and the compressor are arranged on a common, also referred to as a turbine rotor turbine shaft, with which the machine is connected, and which is rotatably mounted about its longitudinal axis. The combustion chamber is equipped with at least one burner for the combustion of a liquid or gaseous fuel.
Der Verdichter wie auch die Turbine weisen jeweils eine Anzahl von mit der Turbinenwelle verbundenen, rotierbaren Laufschaufeln auf. Die Laufschaufeln sind kranzförmig an der Turbinenwelle angeordnet und bilden somit eine Anzahl von Laufschaufelreihen. Weiterhin umfasst sowohl der Verdichter als auch die Turbine eine Anzahl von feststehenden Leitschaufeln, die ebenfalls kranzförmig unter der Bildung von Leitschaufelreihen an einer Innenwand des Gehäuses von Verdichter bzw. Turbine befestigt sind. In der Turbine dienen die Laufschaufeln zum Antrieb der Turbinenwelle durch Impulsübertrag vom die Turbine durchströmenden Arbeitsmedium. Die Leitschaufeln dienen hingegen zur Strömungsführung des Arbeitsmediums zwischen jeweils zwei in Strömungsrichtung des Arbeitsmediums gesehen aufeinanderfolgenden Laufschaufelreihen oder Laufschaufelkränzen. Ein aufeinanderfolgendes Paar aus einem Kranz von Leitschaufeln oder einer Leitschaufelreihe und aus einem Kranz von Laufschaufeln oder einer Laufschaufelreihe wird dabei auch als Turbinenstufe bzw. als Verdichterstufe bezeichnet. Zwischen den Laufschaufeln und der Innenkontur des jeweils umgebenden Gehäuses, also des Verdichter- oder Turbinengehäuses verbleibt ein Radialspalt, dessen Größe so bemessen ist, dass beim Betrieb der Gasturbine auch bei Temperaturdehnungen der jeweiligen Materialien ein Anstreifen der Laufschaufeln am jeweiligen Innengehäuse ausgeschlossen ist. Ebenso verbleibt zwischen den feststehenden Leitschaufeln und der Turbinenwelle ein Radialspalt. Auch dieser ist so bemessen, dass ein Kontakt zwischen den Leitschaufeln und der Turbinenwelle ausgeschlossen ist.The compressor as well as the turbine each have a number of rotatable blades connected to the turbine shaft. The blades are arranged in a ring on the turbine shaft and thus form a number of blade rows. Furthermore, both the compressor and the turbine include a number of stationary vanes which are also annularly mounted to form vanes rows on an inner wall of the housing of the compressor or turbine. In the turbine, the blades serve to drive the turbine shaft by momentum transfer from the turbine flowing through the working fluid. By contrast, the guide vanes serve to guide the flow of the working medium between two respective rows of blades or rotor blade rings viewed in the flow direction of the working medium. A successive pair of a ring of vanes or a row of vanes and a ring of blades or a blade row is also referred to as a turbine stage or as a compressor stage. Between the blades and the inner contour of the respective surrounding housing, so the compressor or turbine housing remains a radial gap whose size is dimensioned so that during operation of the gas turbine even with thermal expansion of the respective materials stripping of the blades is excluded at the respective inner housing. Likewise, a radial gap remains between the stationary vanes and the turbine shaft. This is also such that a contact between the vanes and the turbine shaft is excluded.
Die Einschnürung 5 befindet sich am Innern einer Außenwand des Gehäuses 2. Sie ergibt sich aus der Differenz einer konventionellen Ringraumkontur 6 des Diffusorgehäuses 2 und einer die Einschnürung hervorrufenden, modifizierten Ringraumkontur 7. Die Einschnürung 5 ist entweder Materialanlagerung auf der Innenseite der Außenwand oder durch eine angepasste Formgebung der Außenwand hervorgerufen.It results from the difference between a conventional annular space contour 6 of the
Die Einschnürung 5 nimmt innerhalb des Diffusors 1 in Strömungsrichtung des durchströmenden Mediums, also der verdichteten Luft, allmählich ab. In der Darstellung in
Die einseitig an der Innenseite des Diffusorgehäuses 2, insbesondere im Bereich des Diffusoreinlasses 4, vorgenommene Radienreduktion (Einschnürung 5) bewirkt eine Umverteilung des Massenstroms in Richtung auf die Nabe des Turbinenläufers. Damit steigt das Geschwindigkeitsniveau im Nabenbereich (vgl. auch
Claims (6)
- Gas turbine having a diffuser (1) which is arranged at the outlet of its compressor with a diffuser housing (2), the diffuser housing (2) delimiting an annular-space contour (6) with an outer wall which lies radially on the outside and an inner contour which is arranged radially on the inside and having a connection region (3) in the region of the transition from the compressor to the diffuser (1), having guide blades (8) which are arranged in a ring immediately upstream of the diffuser (1) and the respective free end of which lies opposite the inner contour in each case with the formation of a radial gap, characterized in that a circumferential constriction (5) which is situated on the interior of the outer wall is provided in the connection region (3), in order to bring about a redistribution of the mass flow in the direction of the inner contour and, as a result, to compensate to a great extent for the drop in speed which is caused by the radial gaps in the region of the inner contour.
- Gas turbine according to Claim 1, the constriction (5) being brought about by the accretion of material on the inner side of the outer wall.
- Gas turbine according to Claim 1 or 2, the constriction (5) being brought about by an adapted shape of the outer wall.
- Gas turbine according to one of the preceding claims, the constriction (5) decreasing gradually in the flow direction of the medium which is flowing through.
- Gas turbine according to Claim 4, an increase in the constriction up to a maximum constriction (5) being effected at the inlet (4) of the diffuser (1) in the direction of the medium which is flowing through, in such a way that the increase in the constriction up to the maximum constriction (5) is considerably greater than the decrease in the constriction following the maximum constriction (5).
- Gas turbine according to Claim 5, the length of a section along the outer contour of the diffuser housing (2) parallel to the flow direction of the medium, during which section the constriction increases up to the maximum constriction (5), being less than a fifth of the length of a section during which, starting from the maximum constriction (5), the constriction decreases again.
Priority Applications (1)
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EP20040004895 EP1574667B1 (en) | 2004-03-02 | 2004-03-02 | Diffuser for compressor |
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EP20040004895 EP1574667B1 (en) | 2004-03-02 | 2004-03-02 | Diffuser for compressor |
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EP1574667A1 EP1574667A1 (en) | 2005-09-14 |
EP1574667B1 true EP1574667B1 (en) | 2013-07-17 |
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Publication number | Priority date | Publication date | Assignee | Title |
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EP2194231A1 (en) * | 2008-12-05 | 2010-06-09 | Siemens Aktiengesellschaft | Ring diffuser for an axial turbo engine |
DE102012215412A1 (en) | 2012-08-30 | 2014-03-06 | Rolls-Royce Deutschland Ltd & Co Kg | Assembly of an axial turbomachine and method for producing such an assembly |
CN115962154A (en) * | 2023-03-17 | 2023-04-14 | 潍柴动力股份有限公司 | Compressor with transition section meridian flow channel narrowed at casing side, engine and automobile |
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US6442939B1 (en) * | 2000-12-22 | 2002-09-03 | Pratt & Whitney Canada Corp. | Diffusion mixer |
JP3912989B2 (en) * | 2001-01-25 | 2007-05-09 | 三菱重工業株式会社 | gas turbine |
JP3564420B2 (en) * | 2001-04-27 | 2004-09-08 | 三菱重工業株式会社 | gas turbine |
-
2004
- 2004-03-02 EP EP20040004895 patent/EP1574667B1/en not_active Expired - Lifetime
Also Published As
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EP1574667A1 (en) | 2005-09-14 |
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