EP0894941B1 - Rotor of a turbomachine - Google Patents
Rotor of a turbomachine Download PDFInfo
- Publication number
- EP0894941B1 EP0894941B1 EP19970810536 EP97810536A EP0894941B1 EP 0894941 B1 EP0894941 B1 EP 0894941B1 EP 19970810536 EP19970810536 EP 19970810536 EP 97810536 A EP97810536 A EP 97810536A EP 0894941 B1 EP0894941 B1 EP 0894941B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- shaft
- feed
- rotor according
- root
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
Definitions
- the invention relates to a rotor of a turbomachine, which on a Surface of its rotor shaft in one or more rows of blades and / or other parts, for example.
- Heat shields or heat accumulation segments each protrude into the rotor shaft through a surface for attachment, the rotor shaft on at least a portion of its surface near a foot a, has a recess in the rotor shaft projecting shaft part the recess is spaced radially from the surface of the rotor shaft,
- a cooling system for a turbine is known from GB-A-2 224 082. Connect cooling channels a rotor disk with an associated turbine blade. To avoid leaks there are seals in the gap.
- the Invention as characterized in the claims, the task, the rotor with simple means and in particular the surface areas of the rotor shaft of a turbomachine and the blades arranged radially on it as directly as possible, but using a gentle cooling medium, preferably air.
- a gentle cooling medium preferably air.
- the measures according to the invention should also be retrofitted to turbomachines that are already in use can be.
- the idea underlying the invention is based on the consideration that the heat acting on the surface of the rotor shaft together with rotor blades hot gases flowing around the rotor, as close as possible to the peripheral peripheral edge the rotor shaft is to be discharged directly by a suitable supply of cooling air lower the temperature of the rotor material and that of the rotor blades.
- recesses are provided in the peripheral peripheral edge of the rotor shaft have and thus overhanging shaft parts, so-called outstanding Provide sections with radial and / or oblique feed-through channels provided so that the peripheral peripheral edge heated by the hot gases along with Blades from the underside of the overhanging shaft part or protruding Section can be cooled.
- FIG. 2 A rotor shaft contour known per se, which is used to carry out the inventive Measures is suitable in FIG. 2 as a representation of the prior art shown.
- the highly schematic cross-sectional drawing according to FIG. 2 represents the represents the upper section of a rotor shaft 1 which rotates about the rotor shaft axis A. At the peripheral peripheral edge of the rotor shaft 1 are radial to the rotor shaft axis A blades 2 arranged. Between the blades 2 are only completeness for the sake of the guide vanes 3, which are fixedly attached to the stator and in the spaces protrude between two successive blades. The The arrow shown above the blade breaks represents the flow direction of the Hot gas through the turbines.
- the idea of the invention basically provides for the overhanging shaft parts to be closed perforate so that there is an exchange of air between the top of the overhanging Wave part 4 and the underlying air volume 5 can take place.
- the overhanging shaft part must be provided with such a perforation, so that the cooling air present in area 5 is the blade root area Blades can cool directly.
- FIG. 1 The cross-sectional view shown in Fig. 1, which is only a section shows the rotor cross-section corresponds to the end of a designed according to the invention Rotors, with the aid of the representation according to FIG. 2 in place It is to be thought that corresponds to the circle delimited by E in FIG. 2.
- the circle includes preferably all those blade roots which are provided with the "perforation" according to the invention can be recorded.
- the constant heat flow Q through the hot gases flowing around the rotor acts on the surface 6 of the rotor shaft 1.
- an additional heat flow Q s penetrates into the rotor shaft 1 via the blade root 7 of a rotor blade (not shown in FIG. 1), which otherwise rises radially above the surface 6 of the rotor shaft 1.
- the blade root 7 of a moving blade which in a circumferential groove 8 is fixed within the rotor shaft 1, with the aid of a feed-through channel 9 to be charged directly with cooling air.
- This will be the blade load-bearing, overhanging shaft part 4 with a through channel 9 such enforces that the feed-through channel 9 is largely radial to the shaft axis A extends from the recess 5 to the blade root 7.
- the circumferential groove 8, in which the blade root 7 is attached also has a cavity 10 in which the Cooling air present in the recess 5 pass through the duct 9 can.
- the circumferential groove 8 runs completely angularly around the rotor shaft 1, in which one A large number of blades are arranged one behind the other.
- the individual cavities 10 under each blade root of a moving blade together form a circumferential channel 10 'through which the cooling air introduced through the duct 9 can circulate. In this way, the blade feet are cooling, integral Cooling system can be implemented within the rotor shaft.
- feed-through channels 9 ' are also provided, which overhang the Push shaft part 4 through completely. In this way, the one on the peripheral Circumferential edge 6 acting heat flow Q directly through the through channels 9 'in the direction of the recess 5, in which cooling air is provided.
- the perforation according to the invention of an overhanging shaft part of a rotor shaft 1, as stated above, is preferably carried out at the end of a rotor, especially since cooling air is supplied there in the area of the recess 5 can.
- Perforation achieve that a desired rotor temperature even with warmer cooling air is achievable, which is already cheaper from a thermodynamic point of view is.
- Fig. 1 which preferably for Cooling of the blades is provided at the rotor end, can be different Be designed so that the cooling air for removal of the to Shovel feet serve existing heat.
- the cooling air located near the blade root in the cavity 10 is heated due to the large heat input Q s and experiences so much lift in the presence of the centrifugal field generated by the rotation of the rotor that the warmer air climbs radially inward through the duct and in this way the flowing cold air makes room so that it is able to cool the hot blade feet.
- This convection flow which forms in the centrifugal field, arises automatically due to the temperature gradient.
- the feed-through channels must be of a correspondingly large size so that a countercurrent system of the above-mentioned type can form within a channel.
- cooling flows can also be specifically initiated in the cooling system. Since the openings 12 of the lead-through channels facing the rotor shaft are due to the rotational movement of the rotor relative to that in the recess 5 Rotating the cooling medium can be done by specifically designing the opening geometry the flow direction within each channel for each duct be specified.
- Fig. 1b is the sectional view according to the section A entered in Fig. 1a - A is shown.
- the cross-sectional view shown in the angular direction to the axis of rotation 1b shows two adjacent feed-through channels 9, which each have openings 11, 11 'facing the rotor shaft and are different have large inlet curvatures R and r.
- R and r By the of the direction of rotation specified for the rotation of the rotor (see the large arrow direction) cause smaller or sharper opening radii r to create and guide a radially outward cooling flow into the cooling system. Make it up in this way lead-through channels through which the cooling air flows.
- the cooling flow then passes through the immediately adjacent feedthrough channels off again, especially since the individual feed-through channels via the circulation groove 10 ', which is composed of the totality of all cavities 10, are connected.
- each with differently dimensioned opening radii R, r have, which alternate between adjacent through-channels it is also possible to design the opening area of a through channel in such a way that an opening has two different radii R and r. So it is for the above described flow direction specification necessary, the opening areas two adjacent passageways, which are closest to each other form the same radii of curvature. (see Figure 1c)
- the direct cooling of the blade feet of the moving blades by a targeted below the cooling medium introduced, preferably cooling air, is also the blade roots for reasons of possible contamination by dust particles within the Cooling system an advantage.
- dust particles get through the feed-through channels in the circumferential grooves of the mounting rails, so these can in principle also to blockages of the circumferential grooves and thus to a considerable one Reduce the cooling effect.
- so-called dust holes such as those in cooled blades are used, on the other hand, it is easy for maintenance work Effort possible by removing the blades from the mounting rail to easily remove contaminants deposited in the circumferential grooves.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Applications Or Details Of Rotary Compressors (AREA)
Description
Die Erfindung bezieht sich auf einen Rotor einer Strömungsmaschine, der an einer Oberfläche seiner Rotorwelle in einer oder mehreren Reihen Laufschaufeln und/oder andere Teile, bspw. Hitzeschilder oder Wärmestausegmente vorsieht, die jeweils über einen Fuß zur Befestigung durch die Oberfläche in die Rotorwelle hineinragen, wobei die Rotorwelle an wenigstens einem Bereich ihrer Oberfläche nahe eines Fußes ein, eine Ausnehmung in der Rotorwelle überragendes Wellenteil aufweist, das die Ausnehmung radial zur Oberfläche der Rotorwelle beabstandet,The invention relates to a rotor of a turbomachine, which on a Surface of its rotor shaft in one or more rows of blades and / or other parts, for example. Heat shields or heat accumulation segments, each protrude into the rotor shaft through a surface for attachment, the rotor shaft on at least a portion of its surface near a foot a, has a recess in the rotor shaft projecting shaft part the recess is spaced radially from the surface of the rotor shaft,
In Hinblick auf die Leistungs- und Lebensdauersteigerung von modernen Gasturbinen, deren einzelne Komponenten sehr großen thermischen Belastungen ausgesetzt sind, spielt die Kühlung von den thermisch hoch belasteten Aggregaten eine immer wichtigere Rolle. Insbesondere wird an dieser Stelle an die Kühlung der Rotorwelle und der Laufschaufeln einer Gasturbine gedacht, die dem von der Brennkammer kommenden Heißgasen unmittelbar ausgesetzt sind und somit eine große Kühlintensität benötigt.With regard to the increase in performance and service life of modern gas turbines, the individual components of which are exposed to very high thermal loads cooling from the thermally highly stressed units plays a role increasingly important role. In particular, at this point the cooling of the rotor shaft and the blades of a gas turbine thought to match that of the combustion chamber coming hot gases are exposed immediately and thus a high cooling intensity needed.
Neben bekannten Kühlmaßnahme, bspw. einen Teil der vorverdichteten Luft zu Kühlzwecken abzuzweigen - was jedoch aufgrund des nur beschränkten Lufthaushaltes in einer modernen Gasturbine unweigerlich mit einem gewissen Wirkungsgradverlust verbunden ist -, wird alternativ vorgeschlagen, die Kühlung der thermisch belasteten Aggregate einer Gasturbine mit anderen Kühlmedien zu bewerkstelligen, beispielsweise mit Kühlwasser zu beaufschlagen, das in einem rotorinternen kühlkreislauf, zur Kühlung aller heißen Regionen, geleitet wird.In addition to known cooling measures, for example part of the pre-compressed air To branch off cooling purposes - which, however, due to the limited air balance in a modern gas turbine with inevitable loss of efficiency is connected, it is alternatively proposed to cool the thermally to carry out loaded units of a gas turbine with other cooling media, to apply cooling water, for example, to the cooling circuit inside the rotor, for cooling all hot regions.
Aus der Schrift GB-A-2 224 082 ist ein Kühlsystem einer Turbine bekannt. Kühlkanäle verbinden eine Rotorscheibe mit einer zugehörigen Turbinenschaufel. Um Leckagen zu vermeiden sind im Zwischenraum Dichtungen vorhanden.A cooling system for a turbine is known from GB-A-2 224 082. Connect cooling channels a rotor disk with an associated turbine blade. To avoid leaks there are seals in the gap.
Ergänzend oder alternativ zu den vorstehend genannten Kühleinrichtungen liegt der Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, die Aufgabe zugrunde, mit möglichst einfachen Mitteln den Rotor und insbesondere die Oberflächenbereiche der Rotorwelle einer Strömungsmaschine sowie die radial an ihr angeordneten Laufschaufeln möglichst direkt, aber unter Einsatz eines schonenden Kühlmediums, vorzugsweise Luft zu kühlen. Insbesondere sollen die ohnehin bei bekannten Rotoren vorhandenen Konturen zu Kühlzwecken genutzt werden, so daß die Kühlmaßnahmen mit geringem konstruktivem sowie auch finanziellem Einsatz durchgeführt werden können. Die erfindungsgemäßen Maßnahmen sollten auch bei bereits im Einsatz befindlichen Strömungsmaschinen nachgerüstet werden können. In addition or as an alternative to the cooling devices mentioned above, the Invention, as characterized in the claims, the task, the rotor with simple means and in particular the surface areas of the rotor shaft of a turbomachine and the blades arranged radially on it as directly as possible, but using a gentle cooling medium, preferably air. In particular, should the contours that are already present in known rotors are used for cooling purposes are, so that the cooling measures with little constructive as well as financial Use can be carried out. The measures according to the invention should also be retrofitted to turbomachines that are already in use can be.
Die der Erfindung zugrunde liegende Idee geht dabei von der Überlegung aus, daß die auf die Oberfläche der Rotorwelle nebst Laufschaufeln einwirkende Wärme der den Rotor umströmenden Heißgase, so nah wie möglich am peripheren Umfangsrand der Rotorwelle durch geeignete Kühlluftzufuhr direkt abgeführt werden soll, um die Temperatur des Rotormaterials sowie die der Laufschaufeln abzusenken.The idea underlying the invention is based on the consideration that the heat acting on the surface of the rotor shaft together with rotor blades hot gases flowing around the rotor, as close as possible to the peripheral peripheral edge the rotor shaft is to be discharged directly by a suitable supply of cooling air lower the temperature of the rotor material and that of the rotor blades.
Hierzu werden bei Rotoren, die im peripheren Umfangsrand der Rotorwelle Ausnehmungen aufweisen und somit überhängende Wellenteile, sogenannte überragende Abschnitte vorsehen, mit radialen und/oder schrägradialen Durchführungskanälen versehen, so daß der durch die Heißgase erhitzte periphere Umfangsrand nebst Laufschaufeln von der Unterseite des überhängenden Wellenteils respektive überragenden Abschnitts gekühlt werden kann.For rotors, recesses are provided in the peripheral peripheral edge of the rotor shaft have and thus overhanging shaft parts, so-called outstanding Provide sections with radial and / or oblique feed-through channels provided so that the peripheral peripheral edge heated by the hot gases along with Blades from the underside of the overhanging shaft part or protruding Section can be cooled.
Eine an sich bekannte Rotorwellenkontur, die zur Durchführung der erfindungsgemäßen Maßnahmen geeignet ist, ist in Fig. 2 als Darstellung zum Stand der Technik gezeigt.A rotor shaft contour known per se, which is used to carry out the inventive Measures is suitable in FIG. 2 as a representation of the prior art shown.
Die stark schematisiert dargestellte Querschnittzeichnung gemäß Fig. 2 stellt den
oberen Abschnitt einer Rotorwelle 1 dar, die um die Rotorwellenachse A rotiert. Am
peripheren Umfangsrand der Rotorwelle 1 sind radial zur Rotorwellenachse A Laufschaufeln
2 angeordnet. Zwischen den Laufschaufeln 2 sind nur der Vollständigkeit
halber die Leitschaufeln 3 gezeigt, die fest am Stator angebracht sind und in die Zwischenräume
zwischen zwei aufeinander folgenden Laufschaufeln hineinragen. Der
über den Schaufelabrissen dargestellt Pfeil stellt die Durchströmungsrichtung der
Heißgases durch die Turbinen dar.The highly schematic cross-sectional drawing according to FIG. 2 represents the
represents the upper section of a
Ein besonderes Augenmerk soll jedoch auf das in der Fig. 2 dargestellten überhängenden
Wellenteil 4 gelegt werden, das in der Nähe eines Schaufelfußes einer Leitschaufel
2 am peripheren Umfangsrand der Rotorwelle 1 vorgesehen ist. Natürlich
sind auch alle anderen vergleichbar ausgestalteten überhängenden Wellenteile für
die erfindungsgemäße "Perforierung" geeignet, nur befindet sich am strömungsabtriebsseitigen
Ende der Strömungsmaschine kühlere Luft bzw. die Zufuhr von Kühlluft
kann an diesen Bereich ungehindert erfolgen.However, special attention should be paid to the overhang shown in FIG. 2
Shaft part 4 are placed in the vicinity of a blade root of a guide blade
2 is provided on the peripheral peripheral edge of the
Der Erfindungsgedanke sieht grundsätzlich vor, die überhängenden Wellenteile zu
perforieren, so daß ein Luftaustausch zwischen der Oberseite des überhängenden
Wellenteiles 4 und dem darunter befindlichen Luftvolumens 5 stattfinden kann. Insbesondere
ist der überhängende Wellenteil mit einer derartigen Perforierung zu versehen,
so daß die im Bereich 5 vorhandene Kühlluft den Schaufelfußbereich der
Laufschaufeln direkt kühlen kann.The idea of the invention basically provides for the overhanging shaft parts to be closed
perforate so that there is an exchange of air between the top of the overhanging
Wave part 4 and the
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand eines Ausführungsbeispieles unter Bezugnahme auf die Zeichnung exemplarisch beschrieben, auf die im übrigen hinsichtlich der Offenbarung aller im Text nicht näher erläuterten erfindungsgemäßen Einzelheiten ausdrücklich verwiesen wird. Es zeigen:
- Fig. 1a
- Teilquerschnittsdarstellung durch einen Teil des peripheren Umfangsrandes einer Rotorwelle mit überhängendem Wellenteil,
- Fig. 1b
- Schnittdarstellung gemäß Schnittlinie A - A in Fig. 1a,
- Fig. 1c
- alternative Schnittdarstellung zur Figur 1b und
- Fig. 2
- Prinzipquerschnittsdarstellung durch eine an sich bekannte Rotoranordnung.
- Fig. 1a
- Partial cross-sectional view through a part of the peripheral peripheral edge of a rotor shaft with an overhanging shaft part,
- Fig. 1b
- Sectional view along section line A - A in Fig. 1a,
- Fig. 1c
- alternative sectional view to Figure 1b and
- Fig. 2
- Principle cross-sectional representation through a rotor arrangement known per se.
Die in Fig. 1 dargestellte Querschnittsdarstellung, die lediglich einen Ausschnitt aus dem Rotorquerschnitt zeigt, entspricht dem Ende eines erfindungsgemäß ausgestalteten Rotors, das unter zu Hilfenahme der Darstellung gemäß Fig. 2 an die Stelle zu denken ist, die in Fig. 2 dem mit E eingegrenzten Kreis entspricht. Der Kreis umfasst vorzugsweise all jene Laufschaufelfüsse, die mit der erfindungsgemäßen "Perforierung" erfasst werden können. The cross-sectional view shown in Fig. 1, which is only a section shows the rotor cross-section corresponds to the end of a designed according to the invention Rotors, with the aid of the representation according to FIG. 2 in place It is to be thought that corresponds to the circle delimited by E in FIG. 2. The circle includes preferably all those blade roots which are provided with the "perforation" according to the invention can be recorded.
Auf die Oberfläche 6 der Rotorwelle 1 wirkt der stete Wärmefluß Q durch die den
Rotor umströmenden Heißgase ein. Zusätzlich dringt über den Schaufelfuß 7 einer
nicht in der Fig. 1 dargestellten Laufschaufel, die sich im Übrigen radial über die
Oberfläche 6 der Rotorwelle 1 erhebt, ein zusätzlicher Wärmefluß Qs in die Rotorwelle
1 ein.The constant heat flow Q through the hot gases flowing around the rotor acts on the surface 6 of the
Um die in die Rotorwelle 1 eingebrachte Wärme möglichst rasch abzuführen ist zum
einen erfindungsgemäß vorgesehen, den Schaufelfuß 7 einer Laufschaufel, der in
einer Umlaufnut 8 innerhalb der Rotorwelle 1 fixiert ist, mit Hilfe eines Durchführungskanales
9 direkt mit Kühlluft zu beaufschlagen. Hierzu wird das die Laufschaufel
tragende, überhängende Wellenteil 4 mit einem Durchführungskanal 9 derart
durchsetzt, daß sich der Durchführungskanal 9 weitgehend radial zur Wellenachse
A von der Ausnehmung 5 hin zum Schaufelfuß 7 erstreckt. Die Umfangsnut 8, in
der der Schaufelfuß 7 befestigt ist, weist überdies einen Hohlraum 10 auf, in dem die
in der Ausnehmung 5 vorhandene Kühlluft über den Durchführungskanal 9 gelangen
kann.In order to dissipate the heat introduced into the
Die Umfangsnut 8 verläuft vollständig um die Rotorwelle 1 angulär um, in der eine
Vielzahl von Laufschaufeln hintereinander angeordnet sind. Die einzelnen Hohlräume
10 unter jedem Schaufelfuß einer Laufschaufel ergeben zusammen einen Umfangskanal
10' durch den die über die Durchführungskanäle 9 eingeleitete Kühlluft
zirkulieren kann. Auf diese Weise ist ein die Schaufelfüße kühlendes, integrales
Kühlsystem innerhalb der Rotorwelle realisierbar.The
In Ergänzung zu den, die Schaufelfüße 9 unmittelbar kühlenden Durchführungskanälen
sind auch weitere Durchführungskanäle 9' vorgesehen, die das überhängende
Wellenteil 4 vollständig durchsetzen. Auf diese Weise wird der auf den peripheren
Umfangsrand 6 einwirkende Wärmefluß Q unmittelbar durch die Durchführungskanäle
9' in Richtung der Ausnehmung 5, in der Kühlluft vorgesehen ist, abgeleitet. In addition to the feed channels that cool the
Neben den in radialer Erstreckung orientierten Durchführungskanälen 9, 9' können
alternativ oder in Ergänzung auch schrägradiale Durchführungskanäle in das überhängende
Wellenteil 4 eingebracht werden.In addition to the feed-
Die erfindungsgemäße Perforierung eines überhängenden Wellenteils einer Rotorwelle
1 ist wie vorstehend dargelegt vorzugsweise am Ende eines Rotors durchzuführen,
zumal dort gezielt Kühlluft in den Bereich der Ausnehmung 5 zugeführt werden
kann. Falls dies jedoch nicht nötig ist, kann man mit der erfindungsgemäßen
Perforierung erreichen, daß auch mit wärmerer Kühlluft eine gewünschte Rotortemperatur
erreichbar ist, was bereits aus thermodynamischen Gesichtspunkten günstiger
ist.The perforation according to the invention of an overhanging shaft part of a
Für das in Fig. 1 dargestellte erfindungsgemäße Kühlsystem, das vorzugsweise zum Kühlen der Laufschaufeln jeweils am Rotorende vorgesehen ist, kann in unterschiedlicher Weise ausgestaltet werden, so daß die Kühlluft zum Abtransport der an den Schaufelfüßen vorhandenen Wärme dient.For the cooling system according to the invention shown in Fig. 1, which preferably for Cooling of the blades is provided at the rotor end, can be different Be designed so that the cooling air for removal of the to Shovel feet serve existing heat.
Grundsätzlich wird die nahe dem Schaufelfuß im Hohlraum 10 befindliche Kühlluft
aufgrund des großen Wärmeeintrages Qs erwärmt und erfährt in Gegenwart des
durch die Rotation des Rotors erzeugten Zentrifugalfeldes so viel Auftrieb, daß die
wärmere Luft radial nach innen gerichtet den Durchführungskanal durchsteigt und
auf diese Weise der nachströmenden kälteren Luft Platz macht, so daß diese die
heißen Schaufelfüße zu kühlen vermag. Diese, in dem Zentrifugalfeld sich ausbildende
Konvektionsströmung entsteht aufgrund des Temperaturgefälles automatisch.
Die Durchführungskanäle müssen jedoch entsprechend groß ausgebildet sein, so
daß sich innerhalb eines Kanales ein Gegenstromsystem der vorstehend genannten
Weise ausbilden kann.Basically, the cooling air located near the blade root in the
Neben den sich selbständig ausbildenden Kühlströmungen, die sich innerhalb eines
Durchführungskanals, vergleichsweise in Art eines sogenannten "Thermosyphons"
ausbilden, können jedoch auch gezielt in das Kühlsystem Kühlströme initiiert werden.
Da die rotorwellenseitig zugewandten Öffnungen 12 der Durchführungskanäle aufgrund
der Rotationsbewegung des Rotors relativ zu dem in der Ausnehmung 5 vorhandenem
Kühlmedium rotieren, kann durch gezielte Ausbildung der Öffnungsgeometrie
zu jedem Durchführungskanal die Strömungsrichtung innerhalb des Kanals
vorgegeben werden.In addition to the independently developing cooling flows that occur within a
Feed-through channel, comparatively in the manner of a so-called "thermosiphon"
training, however, cooling flows can also be specifically initiated in the cooling system.
Since the openings 12 of the lead-through channels facing the rotor shaft are due to
the rotational movement of the rotor relative to that in the
In Fig. 1b ist die Schnittdarstellung gemäß dem in Fig. 1a eingetragenen Schnittes A
- A dargestellt. Die in angulärer Richtung zur Rotationsachse gezeigte Querschnittsdarstellung
in Fig. 1b gibt zwei benachbarte Durchführungskanäle 9 wieder,
die jeweils rotorwellenseitig zugewandte Öffnungen 11, 11' aufweisen und über unterschiedlich
groß dimensionierte Einlaßrundungen R und r verfügen. Durch die von
der Rotation des Rotors vorgegebene Umlaufrichtung (siehe die große Pfeilrichtung)
bewirken kleinere bzw. schärfere Öffnungsradien r eine Schöpfwirkung und leiten
eine radial nach außen gerichtete Kühlströmung in das Kühlsystem ein. Es bilden
sich auf diese Weise Durchführungskanäle aus, durch die die Kühlluft einströmt.
Durch die unmittelbar benachbarten Durchführungskanäle tritt sodann die Kühlströmung
wieder aus, zumal die einzelnen Durchführungskanäle über die Umlaufnut 10',
die sich aus der Gesamtheit aller Hohlräume 10 zusammensetzt, verbunden sind.In Fig. 1b is the sectional view according to the section A entered in Fig. 1a
- A is shown. The cross-sectional view shown in the angular direction to the axis of rotation
1b shows two adjacent feed-through
Alternativ zu der in Figur 1b dargestellten Ausbildung der Öffnungen der Durchführungskanäle, die jeweils über unterschiedlich dimensionierte Öffnungsradien R, r verfügen, die sich jeweils zwischen benachbarten Durchgangskanälen abwechseln ist es auch möglich den Öffnungsbereich eines Durchgangskanal derart auszubilden, daß eine Öffnung zwei unterschiedliche Radien R und r aufweist. So ist es zur vorstehend beschriebenen Strömungsrichtungsvorgabe notwendig, die Öffnungsbereiche zweier benachbarter Durchgangskanäle, die sich jeweils am nächsten liegen mit gleichen Krümmungsradien auszubilden. (siehe hierzu Figur 1c)As an alternative to the configuration of the openings of the feed-through channels shown in FIG. 1b, each with differently dimensioned opening radii R, r have, which alternate between adjacent through-channels it is also possible to design the opening area of a through channel in such a way that an opening has two different radii R and r. So it is for the above described flow direction specification necessary, the opening areas two adjacent passageways, which are closest to each other form the same radii of curvature. (see Figure 1c)
Damit das Kühlsystem, wie in der Fig. 1b und 1c ausschnittsweise dargestellt, arbeiten kann, muß die Anzahl der Durchführungskanäle eine natürliche gerade Zahl annehmen, so daß einem Einströmkanal jeweils ein Auströmkanal zugeordnet ist. So that the cooling system, as shown in Figs. 1b and 1c, work the number of feed-through channels must assume a natural even number, so that an outflow channel is assigned to an inflow channel.
Alternativ oder ergänzend zu den Fig. 1b und 1c dargestellten Öffnungskonturen, können regelrechte Schöpfkanten an die jeweiligen Stellen der Öffnungen der Durchgangskanäle vorgesehen werden. Dies jedoch ist mit einem zusätzlichen konstruktiven Aufwand verbunden, der durch die Funktionsweise des vorstehend beschriebenen "Thermosyphons" nicht zwingend erforderlich ist.As an alternative or in addition to the opening contours shown in FIGS. 1b and 1c, can real scooping edges at the respective points of the openings of the Through channels are provided. However, this is with an additional constructive Effort associated with the operation of the above "Thermosyphons" is not absolutely necessary.
Die unmittelbare Kühlung der Schaufelfüße der Laufschaufeln durch ein gezielt unterhalb der Schaufelfüße eingebrachtes Kühlmedium, vorzugsweise Kühlluft, ist auch aus Gründen möglicher Verschmutzungsgefahren durch Staubpartikel innerhalb des Kühlsystems von Vorteil. Gelangen beispielsweise Staubpartikel durch die Durchführungskanäle in die Umfangsnuten der Aufnahmeschienen, so können diese grundsätzlich auch zu Verstopfungen der Umfangsnuten und somit zu einer erheblichen Verminderung des Kühleffektes führen. Zum einen kann man gegen derartige Verschmutzungen sogenannte Staublöcher vorsehen, wie sie in gekühlten Schaufeln eingesetzt werden, zum anderen ist es jedoch bei Wartungsarbeiten ohne weiteren Aufwand möglich, durch Entnahme der Laufschaufeln aus der Aufnahmeschiene, die sich in den Umfangsnuten abgesetzten Verunreinigungen auf leichte Weise zu entfernen. The direct cooling of the blade feet of the moving blades by a targeted below the cooling medium introduced, preferably cooling air, is also the blade roots for reasons of possible contamination by dust particles within the Cooling system an advantage. For example, dust particles get through the feed-through channels in the circumferential grooves of the mounting rails, so these can in principle also to blockages of the circumferential grooves and thus to a considerable one Reduce the cooling effect. On the one hand, one can counteract such contamination Provide so-called dust holes, such as those in cooled blades are used, on the other hand, it is easy for maintenance work Effort possible by removing the blades from the mounting rail to easily remove contaminants deposited in the circumferential grooves.
- 11
- Rotorwellerotor shaft
- 22
- Laufschaufelblade
- 33
- Leitschaufelvane
- 44
- überhängendes Wellenteiloverhanging shaft part
- 55
- Ausnehmung, bzw. von der Ausnehmung begrenztes VolumenRecess, or volume limited by the recess
- 66
- Oberfläche der RotorwelleSurface of the rotor shaft
- 77
- Schaufelfußblade
- 88th
- Umfangsnutcircumferential groove
- 9,9'9.9 '
- DurchführungskanalThrough channel
- 1010
- Hohlraumcavity
- 10'10 '
- Umfangsnutcircumferential groove
- 11,11'11.11 '
- Öffnungen der DurchführungskanäleOpenings in the duct
- AA
- RotorwellenachseRotor shaft axis
- R, rR, r
-
großer und kleiner Krümmungsradius der Öffnungen 11, 11'large and small radius of curvature of the
openings 11, 11 '
Claims (19)
- Rotor of a fluid-flow machine, which has moving blades (2) in at least one row on a surface (6) of its rotor shaft (1), which moving blades (2) project through the surface (6) into the rotor shaft (1) in each case via a root (7) for fastening 1 [sic], that [sic] the rotor shaft (1), in at least one region at the surface (6) close to a root (7), has a shaft part (4) which projects above a recess (5) in the rotor shaft (1) and keeps the recess (5) at a radial distance from the surface (6) of the rotor shaft (1), at least two feed-through passages (9) passing through the projecting shaft part (4) in such a way that the feed-through passages (9), for cooling purposes, connect [sic] the recess (5) to that end of a root (7) which faces the rotor-shaft side characterized in that a circumferential cavity (10') which is continuous over the circumference and into which the feed-through passages (9) open is arranged below the roots (7).
- Rotor according to Claim 1, characterized in that a cooling medium, preferably cooling air, is provided in the recess (5).
- Rotor according to one of Claims 1 to 2, characterized in that the projecting shaft part (4) is attached to the end of the rotor shaft (1), i.e. the end of a part of the fluid-flow machine.
- Rotor according to one of Claims 1 to 3, characterized in that the feed-through passage (9) is arranged radially or obliquely radially relative to the rotor shaft (1).
- Rotor according to one of Claims 1 to 4, characterized in that the root (7) sits in a circumferential slot (8) inside the rotor shaft (1), which circumferential slot (8) provides a cavity (10) radially below the inserted root (7), and this cavity (10) is connected to the feed-through passage (9).
- Rotor according to one of Claims 1 to 5, characterized in that the root (7) sits in an axial slot inside the rotor shaft (1), which axial slot runs axially or obliquely axially at the surface of the rotor shaft and has the circumferential cavity (10') radially below the inserted root (7), and this cavity (10) is connected to the feed-through passage (9).
- Rotor according to Claim 5 or 6, characterized in that the circumferential slot and/or axial slot as well as the root have serrations for mutual fastening.
- Rotor according to one of Claims 1 to 5, characterized in that moving blades (2) are arranged radially next to one another at the surface (6) of the rotor shaft (1), and to the root (7) of one moving blade (2) a feed-through passage (9) is allocated in each case.
- Rotor according to Claim 8, characterized in that a feed-through passage has an opening (11, 11') at that side of the overhanging shaft part (5) which faces the rotor-shaft side, the opening radius of which opening (11, 11') is in each case dimensioned in such a way that the openings of two directly adjacent feed-through passages have different opening radii.
- Rotor according to Claim 9, characterized in that the openings have either a large (R) or a small (r) opening radius.
- Rotor according to Claim 8, characterized in that the opening (11, 11') of a feed-trough passage (9) which faces the rotor-shaft side has two radii (R, r) of curvature designed to be of different size in such a way that two opening regions of an opening which are nearest to the respectively directly adjacent opening have a different radius of curvature.
- Rotor according to Claim 11, characterized in that the opening regions (11, 11') of two directly adjacent openings have a corresponding radius of curvature.
- Rotor according to one of Claims 5 to 12, characterized in that the cavities (10) under all roots made in a distributed manner around the rotor shaft (1) are connected to one another to form a circumferential passage (10').
- Rotor according to claim 13, characterized in that an even number of radial and/or obliquely radial feed-through passages (9) lead into a circumferential passage (10').
- Rotor according to one of Claims 1 to 14, characterized in that the fluid-flow machine is a turbine, a compressor stage of a gas turbine or of a steam turbine.
- Rotor according to one of Claims 1 to 15, characterized in that a plurality of feed-through passages (9, 9') run radially and/or obliquely radially and have openings (11, 11') which are arranged closer to the rotor-shaft axis than other regions of the feed-through passages (9, 9').
- Rotor according to one of Claims 1 to 16, characterized in that the rotor moves relative to a medium contained in the recess (5).
- Rotor according to one of Claims 1 to 17, characterized in that the root (7) of a moving blade (2) or of a part is arranged radially above the region of a recess (5).
- Rotor according to one of Claims 1 to 18, characterized in that the part is a heat segment or a heat shield.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE59709507T DE59709507D1 (en) | 1997-07-28 | 1997-07-28 | Rotor of a turbomachine |
| EP19970810536 EP0894941B1 (en) | 1997-07-28 | 1997-07-28 | Rotor of a turbomachine |
| JP10210997A JPH1193602A (en) | 1997-07-28 | 1998-07-27 | Rotor for fluid machinery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP19970810536 EP0894941B1 (en) | 1997-07-28 | 1997-07-28 | Rotor of a turbomachine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0894941A1 EP0894941A1 (en) | 1999-02-03 |
| EP0894941B1 true EP0894941B1 (en) | 2003-03-12 |
Family
ID=8230324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP19970810536 Expired - Lifetime EP0894941B1 (en) | 1997-07-28 | 1997-07-28 | Rotor of a turbomachine |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0894941B1 (en) |
| JP (1) | JPH1193602A (en) |
| DE (1) | DE59709507D1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1041246A1 (en) * | 1999-03-29 | 2000-10-04 | Siemens Aktiengesellschaft | Casted gas turbine blade with inner cooling, method and device for manufacturing a manifold of the gas turbine blade |
| JP4981709B2 (en) * | 2008-02-28 | 2012-07-25 | 三菱重工業株式会社 | Gas turbine, disk and method for forming radial passage of disk |
| WO2019008656A1 (en) * | 2017-07-04 | 2019-01-10 | 東芝エネルギーシステムズ株式会社 | Turbine blade and turbine |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH495496A (en) * | 1969-02-26 | 1970-08-31 | Bbc Sulzer Turbomaschinen | Turbomachine with a cooled rotor |
| US3904307A (en) * | 1974-04-10 | 1975-09-09 | United Technologies Corp | Gas generator turbine cooling scheme |
| US3918835A (en) * | 1974-12-19 | 1975-11-11 | United Technologies Corp | Centrifugal cooling air filter |
| US4344738A (en) * | 1979-12-17 | 1982-08-17 | United Technologies Corporation | Rotor disk structure |
| FR2614654B1 (en) * | 1987-04-29 | 1992-02-21 | Snecma | TURBOMACHINE AXIAL COMPRESSOR DISC WITH CENTRIPTED AIR TAKE-OFF |
| GB2224082A (en) * | 1988-10-19 | 1990-04-25 | Rolls Royce Plc | Turbine disc having cooling and sealing arrangements |
| US5318404A (en) * | 1992-12-30 | 1994-06-07 | General Electric Company | Steam transfer arrangement for turbine bucket cooling |
| DE4428207A1 (en) * | 1994-08-09 | 1996-02-15 | Bmw Rolls Royce Gmbh | Mfg. turbine rotor disc with curved cooling air channels |
-
1997
- 1997-07-28 EP EP19970810536 patent/EP0894941B1/en not_active Expired - Lifetime
- 1997-07-28 DE DE59709507T patent/DE59709507D1/en not_active Expired - Lifetime
-
1998
- 1998-07-27 JP JP10210997A patent/JPH1193602A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| JPH1193602A (en) | 1999-04-06 |
| DE59709507D1 (en) | 2003-04-17 |
| EP0894941A1 (en) | 1999-02-03 |
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