EP0916812B1 - Final stage for an axial turbine - Google Patents
Final stage for an axial turbine Download PDFInfo
- Publication number
- EP0916812B1 EP0916812B1 EP97810873A EP97810873A EP0916812B1 EP 0916812 B1 EP0916812 B1 EP 0916812B1 EP 97810873 A EP97810873 A EP 97810873A EP 97810873 A EP97810873 A EP 97810873A EP 0916812 B1 EP0916812 B1 EP 0916812B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- vane
- blade
- rotor
- sweep
- side end
- 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.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
Definitions
- the invention relates to the final stage of a turbine with a large axial flow Channel divergence with a series of curved guide vanes and a series of tapered, twisted blades.
- Curved guide vanes are used in particular to reduce secondary losses reduce by redirecting the boundary layers in the Guide vanes are created.
- Turbines with guide blades curved in the axial direction and in the circumferential direction are known, for example, from DE-A-42 28 879.
- a fixed guide grid is arranged upstream of the playpen. Its blades are fluidically optimized for full load with regard to the number and their ratio of chord to pitch. They give the flow the swirl required to enter the playpen.
- the curvature of the blades is perpendicular to the chord, which is achieved by moving the profile cuts both in the circumferential direction and in the axial direction.
- the curvature of the guide vanes is directed against the pressure side of the guide vane which is adjacent in the circumferential direction. This curvature is formed by a continuous arc, which forms an acute angle with the blade carrier and with the hub.
- the blade area projected in the radial direction is larger than in the known curvature in the circumferential direction. This increases the radial force on the flow medium; this is pressed against the channel walls, whereby the boundary layer thickness is reduced there.
- a blade grille for an axially flow-through turbomachine the blade leading edges of which are swept in the area of the blade root and in the area of the blade tip with respect to the direction of flow, is shown in more detail in EP-A-0661413.
- the airfoil essentially consists of a radially oriented middle part of the blade , which takes up about 50% of the blade height and the two swept end sections, which can take up to 10% of the blade height. These rectilinear sections are connected via curved transition regions.
- the trailing edge of the blade follows a course analogous to the leading edge in accordance with the tapering depth of the blade.
- the present invention has for its object in an axially flow Turbine of the type mentioned, especially one with small hub ratio to create a measure by which the detachment the flow from the hub can be avoided and with the more even Pressure distribution over the blading height can be achieved.
- FIG. 1 In the steam turbine shown schematically in FIG. 1, these are the flow through Wall 1 delimiting walls on the one hand the channel limitation on the rotor side 3 and on the other hand the stator-side channel limitation 5.
- the output stage exists from a row of guide vanes 10 and a row of moving blades 20.
- the guide vanes 10 are fixed in a manner not shown in the stator 4, the Blade carrier itself is suspended in a suitable manner in an outer housing.
- the blades 20 are fastened in the rotor 2 in a manner not shown.
- the The blade airfoil is tapered in its longitudinal extension and strongly twisted (Twisted). The airfoil seals against the stator-side channel boundary 5 with its top.
- the channel boundary 3 on the rotor side runs in the entire blading area cylindrical while due to the volume increase of the expanding working medium the stator-side channel boundary 5 is conical and at highly loaded machines can have an opening angle of up to 60 °. It goes without saying that the inner channel contour 3 is also conical can.
- the guide vanes 10 are on their in the axial direction rotor on the rotor end positive and negative arrow on its stator end.
- the Arrow which both the leading edge 11 and the The guide vane trailing edge 12 relates here to the cylindrical Course of the rotor-side channel boundary 3.
- the arrow angle A is selected so that the guide vane trailing edge 12 is at least approximately parallel to the leading edge 21 of the blade 20 runs. This positive sweep extends to approx. 2/3 of the bucket height. It causes a channel limitation radially to the rotor side 3 acting force on the flow, as evidenced by the course of the Meridian streamlines 6 can be seen.
- the selected contour which is adapted to the shape of the blade leading edge 21 the guide vane trailing edge 12 also allows in the lower 2/3 of the flowed channel the setting of the radially variable optimal length of the blade-free axial diffuser between the guide and barrel rows.
- This axial diffuser that occurs in the blade-free space due to the strong channel divergence, has a width C in the example. The narrower this axial diffuser is is, the cheaper this affects the design of the following Blade from. The less the fluid in this area in his Axial component is delayed, the greater the stagger angle of the subsequent blade profile can be selected. About the considered bucket height has the consequence that the airfoil is less twisted overall (twisted) must be.
- FIG. 2 A further measure is shown in FIG. 2, which advantageously affects the displacement the flow affects the rotor-side channel boundary.
- the guide vanes 10 over a large part of their radial extent in the circumferential direction inclined in such a way that the inclination towards the suction side 13 which is directed in the circumferential direction adjacent vane 10 '.
- On the end of the rotor is directed radially. From about 15% of the radial extension it inclines in the circumferential direction and returns on its stator side End back in the radial R. It has been shown that a Tilt angle B to the radial R in the range of 10-17 °, preferably 12-15 ° a sufficiently large force acting radially towards the rotor on the flow generated and pushes them against the rotor.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die Erfindung betrifft die Endstufe einer axialdurchströmten Turbine mit grosser Kanaldivergenz mit einer Reihe gekrümmter Leitschaufeln und einer Reihe verjüngter, verdrehter Laufschaufeln.The invention relates to the final stage of a turbine with a large axial flow Channel divergence with a series of curved guide vanes and a series of tapered, twisted blades.
Gekrümmte Leitschaufeln werden insbesondere eingesetzt, um die Sekundärverluste zu verringern, die durch die Umlenkung der Grenzschichten in den Leitschaufeln entstehen.Curved guide vanes are used in particular to reduce secondary losses reduce by redirecting the boundary layers in the Guide vanes are created.
Es sind Turbinen mit nur in Umfangsrichtung gekrümmten Leitschaufeln beispielsweise aus der DE-A-37 43 738 bekannt. Dort sind Schaufeln gezeigt und beschrieben, deren Krümmung über der Schaufelhöhe gegen die Druckseite der jeweils in Umfangsrichtung benachbarten Leitschaufel gerichtet ist. Es sind auch aus dieser Schrift Schaufeln bekannt, deren Krümmung über der Schaufelhöhe gegen die Saugseite der jeweils in Umfangsrichtung benachbarten Leitschaufel gerichtet ist. Damit sollen auf wirksame Weise sowohl radiale als auch in Umfangsrichtung verlaufende Grenzschicht-Druckgradienten verringert werden und damit die aerodynamischen Schaufelverluste verkleinert werden. Unabhängig davon, gegen welche Seite der benachbarten Schaufel die Krümmung dieser bekannten Schaufel gerichtet ist, verläuft sie in jedem Fall genau in Umfangsrichtung. Dies bedeutet, dass bei den dargestellten zylindrischen Schaufeln zumindest deren Vorderkanten über der Schaufelhöhe in der gleichen Axialebene liegen.They are turbines with guide vanes that are only curved in the circumferential direction known for example from DE-A-37 43 738. Shovels are shown there and described, the curvature of the blade height against the pressure side which is directed in the circumferential direction adjacent vane. There are also known from this document blades, their curvature above the blade height against the suction side of the adjacent guide vane in the circumferential direction is directed. This is designed to effectively both radial and boundary layer pressure gradients running in the circumferential direction can be reduced and thus the aerodynamic blade losses are reduced. Independently of which side of the neighboring blade the curvature of this Known blade is directed, it runs exactly in the circumferential direction in any case. This means that in the cylindrical blades shown at least their front edges above the blade height in the same axial plane lie.
Turbinen mit in Axialrichtung und in Umfangsrichtung gekrümmten Leitschaufeln sind beispielsweise aus der DE-A-42 28 879 bekannt. Stromaufwärts des Laufgitters ist ein festes Leitgitter angeordnet. Dessen Schaufeln sind hinsichtlich Anzahl sowie bezüglich ihres Verhältnisses Sehne zu Teilung strömungstechnisch für Vollast optimiert. Sie verleihen der Strömung den für den Eintritt in das Laufgitter erforderlichen Drall. Die Krümmung der Schaufeln verläuft senkrecht zur Sehne, was durch eine Verschiebung der Profilschnitte sowohl in Umfangsrichtung als auch in Axialrichtung erreicht wird. Die Krümmung der Leitschaufeln ist gegen die Druckseite der jeweils in Umfangsrichtung benachbarten Leitschaufel gerichtet. Diese Krümmung wird durch einen kontinuierlichen Bogen gebildet, der mit dem Schaufelträger und mit der Nabe einen spitzen Winkel bildet. Infolge der Krümmung senkrecht zur Schaufelsehne ist die in Radialrichtung projizierte Schaufelfläche grösser als bei der bekannten Krümmung in Umfangsrichtung. Dadurch erhöht sich die Radialkraft auf das Strömungsmittel; dieses wird an die Kanalwandungen gedrückt, wodurch dort die Grenzschichtdicke reduziert wird.Turbines with guide blades curved in the axial direction and in the circumferential direction are known, for example, from DE-A-42 28 879. A fixed guide grid is arranged upstream of the playpen. Its blades are fluidically optimized for full load with regard to the number and their ratio of chord to pitch. They give the flow the swirl required to enter the playpen. The curvature of the blades is perpendicular to the chord, which is achieved by moving the profile cuts both in the circumferential direction and in the axial direction. The curvature of the guide vanes is directed against the pressure side of the guide vane which is adjacent in the circumferential direction. This curvature is formed by a continuous arc, which forms an acute angle with the blade carrier and with the hub. As a result of the curvature perpendicular to the blade chord, the blade area projected in the radial direction is larger than in the known curvature in the circumferential direction. This increases the radial force on the flow medium; this is pressed against the channel walls, whereby the boundary layer thickness is reduced there.
Ein Schaufelgitter für eine axial durchströmte Strömungsmaschine, dessen Schaufelvorderkanten im Bereich des Schaufelfusses und im Bereich der Schaufelspitze gegenüber der Strömungsrichtung einen gepfeilten Verlauf einnehmen, ist in EP-A-0661413 näher dargestellt. Das Schaufelblatt besteht im wesentlichen aus einem radial ausgerichteten Blattmittelteil, das etwa 50% der Schaufelhöhe einnimmt sowie den zwei gepfeilten Endabschnitten, die bis zu 10% der Schaufelhöhe einnehmen können. Diese geradlinig verlaufenden Abschnitte sind über gekrümmt ausgebildete Übergangsbereiche verbunden. Die Schaufelhinterkante nimmt einen der Vorderkante analogen Verlauf nach Massgabe der sich verjüngenden Schaufelblatttiefe. Aufgrund des geradlinigen, gepfeilten Verlaufs der Schaufelkanten im Bereich des Schaufelfusses und der Schaufelspitze ergibt sich eine positive Beeinflussung der Sekundärströmung des Strömungsmittels dergestalt, dass der radiale Druckgradient im begrenzungsnahen Bereich sich in einer Weise ändert, die die verlustbringende Ausbildung von Hufeisenwirbeln weitgehend vermindert. Die verminderten Verluste führen zu einer entsprechenden Erhöhung des Stufenwirkungsgrades. Mit zunehmendem Strömungsquerschnitt gehen jedoch die anteiligen Auswirkungen der begrenzungsnahen Druckfelder auf den Stufenwirkungsgrad zugunsten des Einflusses der radialen Druckverteilung über die Schaufelhöhe deutlich zurück. Insbesondere in mit grosser Divergenz verlaufenden Strömungskanälen, wie sie für die Niederdruckstufen von Dampfturbinen charakteristisch sind, liegt daher der Schwerpunkt der Bemühungen in der Beherrschung eines gleichmässigen radialen Druckgradienten über die Schaufelhöhe. A blade grille for an axially flow-through turbomachine, the blade leading edges of which are swept in the area of the blade root and in the area of the blade tip with respect to the direction of flow, is shown in more detail in EP-A-0661413. The airfoil essentially consists of a radially oriented middle part of the blade , which takes up about 50% of the blade height and the two swept end sections, which can take up to 10% of the blade height. These rectilinear sections are connected via curved transition regions. The trailing edge of the blade follows a course analogous to the leading edge in accordance with the tapering depth of the blade. Due to the straight, arrow-shaped course of the blade edges in the area of the blade root and the blade tip , there is a positive influence on the secondary flow of the fluid in such a way that the radial pressure gradient in the area near the boundary changes in a way that largely reduces the loss-making formation of horseshoe vertebrae. The reduced losses lead to a corresponding increase in the stage efficiency. However, as the flow cross-section increases, the proportional effects of the pressure fields close to the boundary on the step efficiency decrease significantly in favor of the influence of the radial pressure distribution over the blade height. In particular, in flow channels with a large divergence, as are characteristic of the low-pressure stages of steam turbines, the focus of the efforts lies in the control of a uniform radial pressure gradient across the blade height.
Der vorliegenden Erfindung liegt die Aufgabe zugrunde, bei einer axial durchströmten Turbine der eingangs genannten Art, insbesondere einer solchen mit kleinem Nabenverhältnis, eine Massnahme zu schaffen, mit welcher das Ablösen der Strömung von der Nabe vermieden werden kann und mit der eine gleichmässigere Druckverteilung über die Beschaufelungshöhe erzielt werden kann. The present invention has for its object in an axially flow Turbine of the type mentioned, especially one with small hub ratio to create a measure by which the detachment the flow from the hub can be avoided and with the more even Pressure distribution over the blading height can be achieved.
Erfindungsgemäss wird dies mit den kennzeichnenden Merkmalen der Patentanprüche erreicht.According to the invention, this is done with the characterizing features of the patent claims reached.
Der Vorteil der Erfindung ist unter anderem darin zu sehen, dass infolge der verbesserten Zuströmung eine wesentlich verwindungsärmere Laufschaufelkonstruktion zur Anwendung gelangen kann.The advantage of the invention can be seen, inter alia, in the fact that as a result of the improved Inflow a significantly less torsional blade construction can be used.
In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand der letzten
Niederdruckstufe einer Dampfturbine dargestellt.
Es zeigen:
- Fig. 1
- einen Teillängsschnitt der Turbine;
- Fig. 2
- einen Teilquerschnitt der Turbine.
Show it:
- Fig. 1
- a partial longitudinal section of the turbine;
- Fig. 2
- a partial cross section of the turbine.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Nicht dargestellt sind beispielsweise die Schaufelfüsse, mit denen die Schaufeln in ihren tragenden Partien eingehängt sind sowie eventuelle Schaufel-Deckplatten zur Verbesserung der Dichtwirkung. Die Strömungsrichtung des Strömungsmittels ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. Not shown are, for example, the blade feet with which the blades are suspended in their load-bearing parts, and any blade cover plates to improve the sealing effect. The direction of flow of the flow is indicated by arrows.
In der in Fig.1 schematisch gezeigten Dampfturbine sind die den durchströmten
Kanal 1 begrenzenden Wandungen zum einen die rotorseitige Kanalbegrenzung
3 und zum andern die statorseitige Kanalbegrenzung 5. Die Endstufe besteht
aus einer Reihe Leitschaufen 10 und einer Reihe Laufschaufeln 20. Die Leitschaufeln
10 sind auf nicht dargestellte Weise im Stator 4 befestigt, wobei der
Schaufelträger selbst auf geeignete Art in einem Aussengehäuse eingehängt ist. In the steam turbine shown schematically in FIG. 1, these are the flow through
Wall 1 delimiting walls on the one hand the channel limitation on the
Die Laufschaufeln 20 sind auf nicht dargestellte Weise im Rotor 2 befestigt. Das
Laufschaufelblatt ist in seiner Längserstreckung verjüngt und stark verdreht
(twisted). Gegen die statorseitige Kanalbegrenzung 5 dichtet das Schaufelblatt
mit seiner Spitze.The
Im ganzen Beschaufelungsbereich verläuft die rotorseitige Kanalbegrenzung 3
zylindrisch, während infolge der Volumenzunahme des expandierenden Arbeitsmittels
die statorseitige Kanalbegrenzung 5 konisch ausgebildet ist und bei
hochbelasteten Maschinen einen Öffnungswinkel von bis zu 60° aufweisen kann.
Es versteht sich, dass auch die innere Kanalkontur 3 konisch ausgebildet sein
kann.The
Gemäss der Erfindung sind die Leitschaufeln 10 in axialer Richtung an ihrem
rotorseitigen Ende positiv und an ihrem statorseitigen Ende negativ gepfeilt. Die
Pfeilung, welche sowohl die Leitschaufelvorderkante 11 als auch die
Leitschaufelhinterkante 12 betrifft, bezieht sich hierbei auf den zylindrischen
Verlauf der rotorseitigen Kanalbegrenzung 3. Der Pfeilwinkel A ist so gewählt,
dass die Leitschaufelhinterkante 12 zumindest annähernd parallel zur Vorderkante
21 der Laufschaufel 20 verläuft. Diese positive Pfeilung erstreckt sich bis
ca. 2/3 der Schaufelhöhe. Sie bewirkt eine radial zur rotorseitigen Kanalbegrenzung
3 hin wirkende Kraft auf die Strömung, wie dies aus dem Verlauf der
Meridianstromlinien 6 erkennbar ist.According to the invention, the
Bezogen auf die rotorseitige Kanalkontur 3 geht ab ca. 2/3 der Schaufelhöhe die
positive Pfeilung in eine negative Pfeilung über. Diese ist so gewählt, dass am
statorseitigen Ende die Leitschaufelhinterkante 12 und die Leitschaufelvorderkante
11 zumindest annähernd senkrecht zur strömungsbegrenzenden Wand 5
gerichtet sind. Mit dieser Massnahme wird erreicht, dass die Stromlinien 6 im
Bereich des Stators senkrecht auf die Leitschaufelvorderkante 11 auftreffen. Based on the rotor-
Es ist somit erkennbar, dass die nicht geradlinigen und nicht radial verlaufenden Eintritts- und Austrittskanten der Leitschaufeln es ermöglichen, eine aerodynamisch optimale Schaufelbreite zu verwirklichen.It can thus be seen that the non-linear and non-radial ones Leading and trailing edges of the guide vanes allow an aerodynamic to realize optimal bucket width.
Die gewählte, an den Verlauf der Laufschaufelvorderkante 21 angepasste Kontur
der Leitschaufelhinterkante 12 ermöglicht zudem in den unteren 2/3 des
durchströmten Kanals die Einstellung der radial veränderlichen optimalen Länge
des schaufelfreien Axialdiffusors zwischen Leit- und Laufreihe. Dieser Axialdiffusor,
der im schaufelfreien Raum infolge der starken Kanaldivergenz entsteht,
weist im Beispielsfall eine Breite C auf. Je schmäler dieser Axialdiffusor ausgebildet
ist, umso günstiger wirkt sich dies auf die Gestaltung der nachfolgenden
Laufschaufel aus. Je weniger das Strömungmittel in diesem Bereich in seiner
Axialkomponente verzögert wird, umso grösser muss der Staffelungswinkel des
nachfolgenden Schaufelprofils gewählt werden. Über die betrachtete Schaufelhöhe
hat dies zur Folge, dass das Schaufelblatt insgesamt weniger stark verwunden
(twisted) werden muss.The selected contour, which is adapted to the shape of the
Genau die gegenteilige Folge ergibt sich im Bereich der statorseitigen Kanalbegrenzung, wo eine negative Pfeilung vorherrscht. Hier entsteht im letzten Drittel der Schaufelhöhe zwischen Leit- und Laufschaufeln ein sich gegen die Wandung stetig verbreitender Axialdiffusor mit zunehmender Verzögerung der Axialkomponente des Strömungsmittels. Dies bewirkt, dass der Staffelungswinkel des nachfolgenden Schaufelprofils zunehmend kleiner gewählt werden muss. Über die betrachtete Schaufelhöhe hat dies wiederum zur Folge, dass das Schaufelblatt insgesamt weniger stark verwunden werden muss.The exact opposite results in the area of the stator-side channel limitation, where there is a negative arrow. Here arises in the last third the blade height between the guide and rotor blades is against the Wall of continuously widening axial diffuser with increasing deceleration of the Axial component of the fluid. This causes the stagger angle of the subsequent blade profile must be chosen increasingly smaller. With the blade height under consideration, this in turn means that Airfoil needs to be wound less overall.
Positiver und negativer Pfeilwinkel der Leitschaufel zusammen ergeben somit eine nachfolgende Laufschaufel mit einer radial optimalen Verwindungsverteilung, was sich auch auf die Festigkeit der Laufschaufel günstig auswirkt.The positive and negative arrow angles of the guide vane together thus result a subsequent rotor blade with a radially optimal torsion distribution, which also has a favorable effect on the strength of the rotor blade.
In Fig. 2 ist eine weitere Massnahme gezeigt, die sich vorteilhaft auf das Abdrängen
der Strömung zur rotorseitigen Kanalbegrenzung hin auswirkt. Hierzu
sind die Leitschaufeln 10 über einen Grossteil ihrer radialen Erstreckung in Umfangsrichtung
geneigt und zwar derart, dass die Neigung gegen die Saugseite 13
der jeweils in Umfangsrichtung benachbarten Leitschaufel 10' gerichtet ist. An
ihrem rotorseitigen Ende ist die Leitschaufel radial gerichtet. Ab ca. 15% der
radialen Erstreckung neigt sie sich in Umfangsrichtung und kehrt an ihrem statorseitigen
Ende wieder zurück in die Radiale R. Es hat sich gezeigt, dass ein
Neigungswinkel B zur Radialen R im Bereich von 10-17°, vorzugsweise 12-15°
eine hinreichend grosse radial zum Rotor hin wirkende Kraft auf die Strömung
erzeugt und diese gegen den Rotor drückt. A further measure is shown in FIG. 2, which advantageously affects the displacement
the flow affects the rotor-side channel boundary. For this
are the
- 11
- Kanalchannel
- 22
- Rotorrotor
- 33
- rotorseitige Kanalbegrenzungchannel limitation on the rotor side
- 44
- Stator, Schaufelträger (vane carrier)Stator, vane carrier
- 55
- statorseitige Kanalbegrenzungstator-side channel limitation
- 66
- MeridianstromlinienMeridional flow lines
- 1010
- Leitschaufel (vane)Vane (vane)
- 1111
- Leitschaufelvorderkante (leading edge)Leading edge
- 1212
- Leitschaufelhinterkante (trailing edge)Trailing edge
- 1313
- Leitschaufel-Saugseite (suction side)Vane suction side
- 1414
- Leitschaufel-Druckseite (pressure side)Guide vane pressure side
- 2020
- Laufschaufel (blade)Blade (blade)
- 2121
- LaufschaufelvorderkanteBlade leading edge
- RR
- Radialeradial
- AA
- Pfeilungswinkel (sweep angle)Sweep angle
- BB
- Neigungswinkel (lean angle)Lean angle
- CC
- Breite des Axialdiffusors zwischen 10 und 20Width of the axial diffuser between 10 and 20
Claims (4)
- Output stage of an axial-flow turbine having high channel divergence, of up to 60°, with a row of curved vanes (10) and with a row of narrowed twisted blades (20), the vanes (10) having, in the axial direction, a positive sweep at their rotor-side end and a negative sweep at their stator-side end, with respect to the run of the rotor-side channel boundary (3), characterized in that the positive sweep of the vane (10) extends over 2/3 of the vane height and then merges into the negative sweep, the vane trailing edge (12) running parallel to the blade leading edge (21) in the region of the positive sweep and an axial diffuser widening continuously towards the wall (5), and with an increase in delay of the axial component of the flow medium, being formed between the vanes (10) and blades (20) in the region of the negative sweep.
- Output stage according to Claim 1, characterized in that the negative sweep at the stator-side end is selected in such a way that the vane trailing edge (12) and/or the vane leading edge (11) is directed at least approximately perpendicularly to the flow-limiting wall (5).
- Output stage according to Claim 1, characterized in that the vane (10) is directed radially at its rotor-side end, leans in the circumferential direction from approximately 15% of the radial extent towards the suction side (13) of the neighbouring vane (10') and leans back again at least approximately into the radial (R) at its stator-side end.
- Output stage according to Claim 3, characterized in that the lean angle (B) relative to the radial (R) is approximately 12-15°.
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE59709447T DE59709447D1 (en) | 1997-11-17 | 1997-11-17 | Power stage for turbine with axial flow |
| EP97810873A EP0916812B1 (en) | 1997-11-17 | 1997-11-17 | Final stage for an axial turbine |
| US09/190,366 US6099248A (en) | 1997-11-17 | 1998-11-12 | Output stage for an axial-flow turbine |
| KR1019980049088A KR19990045318A (en) | 1997-11-17 | 1998-11-16 | Output terminal of axial turbine |
| CN98123390.2A CN1250863C (en) | 1997-11-17 | 1998-11-17 | Output stage of axial-flow turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP97810873A EP0916812B1 (en) | 1997-11-17 | 1997-11-17 | Final stage for an axial turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0916812A1 EP0916812A1 (en) | 1999-05-19 |
| EP0916812B1 true EP0916812B1 (en) | 2003-03-05 |
Family
ID=8230472
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97810873A Expired - Lifetime EP0916812B1 (en) | 1997-11-17 | 1997-11-17 | Final stage for an axial turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US6099248A (en) |
| EP (1) | EP0916812B1 (en) |
| KR (1) | KR19990045318A (en) |
| CN (1) | CN1250863C (en) |
| DE (1) | DE59709447D1 (en) |
Families Citing this family (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7025576B2 (en) * | 2001-03-30 | 2006-04-11 | Chaffee Robert B | Pump with axial conduit |
| DE60133382T2 (en) | 2000-05-17 | 2009-04-02 | Robert B. Boston Chaffee | INFLATABLE DEVICE WITH INTEGRATED FLOW REGULATOR AND IMPROVED ADJUSTING DEVICE |
| DE10051223A1 (en) | 2000-10-16 | 2002-04-25 | Alstom Switzerland Ltd | Connectable stator elements |
| DE60211696T2 (en) | 2001-07-10 | 2007-05-16 | Robert B. Boston Chaffee | CONFIGURABLE INFLATABLE SUPPORT DEVICE |
| ATE333618T1 (en) | 2002-05-03 | 2006-08-15 | Robert B Chaffee | SELF-CLOSING VALVE WITH ELECTROMECHANICAL DEVICE FOR ACTUATING THE VALVE |
| WO2004045343A1 (en) | 2002-11-18 | 2004-06-03 | Chaffee Robert B | Inflatable device |
| CA2528332A1 (en) * | 2003-06-09 | 2005-01-06 | Aero International Products, Inc. | Reversible inflation system |
| CN100353031C (en) * | 2003-07-09 | 2007-12-05 | 西门子公司 | Turbine blade |
| US7547187B2 (en) * | 2005-03-31 | 2009-06-16 | Hitachi, Ltd. | Axial turbine |
| US7588425B2 (en) * | 2005-03-18 | 2009-09-15 | Aero Products International, Inc. | Reversible inflation system |
| US7510371B2 (en) * | 2005-06-06 | 2009-03-31 | General Electric Company | Forward tilted turbine nozzle |
| JP2009531593A (en) * | 2006-03-31 | 2009-09-03 | アルストム テクノロジー リミテッド | Guide blades for fluid machinery, especially steam turbines |
| US7806653B2 (en) * | 2006-12-22 | 2010-10-05 | General Electric Company | Gas turbine engines including multi-curve stator vanes and methods of assembling the same |
| CA2695474A1 (en) | 2007-04-24 | 2008-10-30 | Alstom Technology Ltd. | Fluid flow engine |
| DE102008055824B4 (en) | 2007-11-09 | 2016-08-11 | Alstom Technology Ltd. | steam turbine |
| ITMI20072441A1 (en) * | 2007-12-28 | 2009-06-29 | Ansaldo Energia Spa | LATEST PRESSURE SECTION STATE STADIUM STAGE OF A STEAM TURBINE |
| DE102008004014A1 (en) * | 2008-01-11 | 2009-07-23 | Continental Automotive Gmbh | Guide vane for a variable turbine geometry |
| WO2009118234A1 (en) * | 2008-03-28 | 2009-10-01 | Alstom Technology Ltd | Blade for a rotating thermal engine |
| US20100303604A1 (en) * | 2009-05-27 | 2010-12-02 | Dresser-Rand Company | System and method to reduce acoustic signature using profiled stage design |
| EP2434094A3 (en) | 2010-09-28 | 2018-02-21 | Mitsubishi Hitachi Power Systems, Ltd. | Steam turbine stator vane and steam turbine |
| CN102235241A (en) * | 2011-06-28 | 2011-11-09 | 北京动力机械研究所 | Low-pressure turbine structure with big expanding path at inlet |
| GB201115581D0 (en) * | 2011-09-09 | 2011-10-26 | Rolls Royce Plc | A turbine engine stator and method of assembly of the same |
| US9488055B2 (en) | 2012-06-08 | 2016-11-08 | General Electric Company | Turbine engine and aerodynamic element of turbine engine |
| US20160201468A1 (en) * | 2015-01-13 | 2016-07-14 | General Electric Company | Turbine airfoil |
| DE102018202888A1 (en) * | 2018-02-26 | 2019-08-29 | MTU Aero Engines AG | Guide blade for the hot gas duct of a turbomachine |
| JP7061497B2 (en) * | 2018-03-30 | 2022-04-28 | 三菱重工航空エンジン株式会社 | Aircraft gas turbine |
| US11629599B2 (en) | 2019-11-26 | 2023-04-18 | General Electric Company | Turbomachine nozzle with an airfoil having a curvilinear trailing edge |
| US11566530B2 (en) | 2019-11-26 | 2023-01-31 | General Electric Company | Turbomachine nozzle with an airfoil having a circular trailing edge |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2663493A (en) * | 1949-04-26 | 1953-12-22 | A V Roe Canada Ltd | Blading for compressors, turbines, and the like |
| GB1080015A (en) * | 1963-11-13 | 1967-08-23 | English Electric Co Ltd | Steam turbines |
| GB1116580A (en) * | 1965-11-17 | 1968-06-06 | Bristol Siddeley Engines Ltd | Stator blade assemblies for axial-flow turbine engines |
| US4433955A (en) * | 1981-03-26 | 1984-02-28 | General Electric Company | Turbine arrangement |
| FR2505399A1 (en) * | 1981-05-05 | 1982-11-12 | Alsthom Atlantique | DIRECT DRAWING FOR DIVERGENT VEINS OF STEAM TURBINE |
| FR2523642A1 (en) * | 1982-03-19 | 1983-09-23 | Alsthom Atlantique | DIRECT DRAWING FOR DIVERGENT VEINS OF STEAM TURBINE |
| GB2164098B (en) * | 1984-09-07 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for turbine engines |
| FR2603953B1 (en) * | 1986-09-12 | 1991-02-22 | Peugeot Aciers Et Outillage | PROPELLER BLADE AND ITS APPLICATION TO MOTOR FANS |
| US4826400A (en) * | 1986-12-29 | 1989-05-02 | General Electric Company | Curvilinear turbine airfoil |
| JP2753382B2 (en) * | 1990-09-17 | 1998-05-20 | 株式会社日立製作所 | Axial flow turbine vane device and axial flow turbine |
| DE4228879A1 (en) * | 1992-08-29 | 1994-03-03 | Asea Brown Boveri | Turbine with axial flow |
| DE4344189C1 (en) * | 1993-12-23 | 1995-08-03 | Mtu Muenchen Gmbh | Axial vane grille with swept front edges |
-
1997
- 1997-11-17 EP EP97810873A patent/EP0916812B1/en not_active Expired - Lifetime
- 1997-11-17 DE DE59709447T patent/DE59709447D1/en not_active Expired - Lifetime
-
1998
- 1998-11-12 US US09/190,366 patent/US6099248A/en not_active Expired - Lifetime
- 1998-11-16 KR KR1019980049088A patent/KR19990045318A/en not_active Application Discontinuation
- 1998-11-17 CN CN98123390.2A patent/CN1250863C/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| CN1217419A (en) | 1999-05-26 |
| CN1250863C (en) | 2006-04-12 |
| EP0916812A1 (en) | 1999-05-19 |
| US6099248A (en) | 2000-08-08 |
| DE59709447D1 (en) | 2003-04-10 |
| KR19990045318A (en) | 1999-06-25 |
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