EP0937864A2 - Guidevane assembly for an axial turbomachine - Google Patents
Guidevane assembly for an axial turbomachine Download PDFInfo
- Publication number
- EP0937864A2 EP0937864A2 EP99103156A EP99103156A EP0937864A2 EP 0937864 A2 EP0937864 A2 EP 0937864A2 EP 99103156 A EP99103156 A EP 99103156A EP 99103156 A EP99103156 A EP 99103156A EP 0937864 A2 EP0937864 A2 EP 0937864A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- housing
- guide vane
- vane ring
- shroud
- reinforcement
- 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.)
- Granted
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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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
- F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
- F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
Definitions
- the invention relates to a fluid flow machine with a rotor and stator in fluidic terms single or multi-stage design, according to the preamble of the claim 1.
- Such a turbomachine is known for example from DE-PS 27 45 130, this document specifically relates to axial turbines with labyrinth seals.
- the flow channel of the working medium alternately leads through guide vanes and rotating vane rings, the static components protruding radially from the outside and the rotating ones radially from the inside.
- Figure 1 of this document clearly shows, there are both radially inside seals between the rotor and the vane rings ( Inner Airseal ”) as well as seals arranged radially on the outside between the rotor blades and the stator ( Outer Airseal ").
- the sealing fins are the Inner Airseal "is attached to the rotor (item 4), so that their dimensions or dimensional deviations depend on the conditions on the rotor (temperature, speed).
- the associated sealing lining (item 7), on the other hand, is on the inner cover band (item 20)
- the guide vane segments are mounted on the housing (pos. 13, 14), so that the dimensions or dimensional deviations of the sealing layer are ultimately determined by the conditions on the outside of the housing on the other hand, the housing often does not change conformingly at the same time, so that there are gap-changing relative movements between the sealing elements (item 7.8) Outer Airseal "(item 11, 12).
- each segment of a guide vane ring is a mechanical unit on - in the longitudinal section hook-shaped housing elements (item 14 At the upstream end of the outer shroud, each guide vane segment has an edge bead with a groove which engages around the hook-shaped housing element (item 14, 22) in a claw-like manner (see FIG. 3).
- each guide vane segment there is an angled section in longitudinal section with a radially outwardly facing contact surface, which during operation is caused by a flow-induced tilting moment around the upstream one Claw bearing "is pressed against the corresponding hook-shaped housing element (see FIG. 1).
- the hook-shaped housing elements also as Hook rings “identifiable -flows of high density heat flow to the colder housing, the "Hook rings” especially in the area of Claw bearings "can be increasingly plastically deformed by crawling. The only remedy here is permanent cooling of the Hook rings ".
- DE-PS 35 40 943 describes such a gap control system especially for one Dual-flow engine.
- the secondary air duct extends at least up to to the end of the turbine area and has openings (item 11) in its inner wall on, through the secondary air from the outside targeted to areas of the turbine housing can be blown.
- This simplified ACC system may have the problem that the low excess pressure of the secondary air flow is not sufficient to in locally narrow housing zones due to correspondingly small flow cross sections To generate cooling air flows with sufficient mass flow.
- an ACC compressor air from the booster or low pressure compressor branched off as coolant, routed in separate channels and via valves specifically blown out.
- guide vane rings In the case of smaller gas turbine engines, it is known to design guide vane rings as self-supporting, integral components with closed shrouds and to center them in the housing. This is for manufacturing and strength reasons (thermal stresses) monolithic "solution limited to blade rings with relatively small dimensions.
- DE-OS 33 36 420 describes a mechanism for protection against overtightening of a gas turbine rotor in the event of a shaft break.
- the mechanism works in the Way that the guide vane segments axially at least one vane ring pivoted and brought into contact / engagement with adjacent blades become. The mutual mechanical blade friction and destruction slows down the rotor quickly and effectively.
- the vane segments belonging to the mechanism each have a pivot bearing on the outer shroud segment and are on their inner circumference by means of a form-fitting, ring-like reinforcement element connected so that the segments together form a rigid, self-supporting Form the guide vane ring.
- the swivel bearings (positions 36, 56, 58 and 64) provide spoke centering for the intrinsically stable guide vane ring, which contributes to precise positioning / centering reduced thermal voltages.
- a disadvantage is the heat transfer from Hot gas area to the housing (item 34), which also affects the bearing elements are. The resulting high temperatures and temperature gradients in the components this area can significantly reduce the service life.
- the US-PS 3,588,267 protects a guide vane ring construction in plastic construction, in which the blades are attached to a closed, inner torus and form a self-supporting wreath with it.
- the outer blade tips are designed without a cover tape and directly in the recesses of a metallic one Glued housing, the elasticity of the bond small relative shifts balances / absorbs. It is obvious that this design is for higher temperatures is completely unusable and at best in the fan or low pressure compressor area Can be used.
- the invention thus lies in the thermal decoupling of the housing and guide vanes by means of a special design and storage / centering of at least one guide vane ring and by means of air cooling of the housing.
- the - at least one - guide vane ring is designed as a self-supporting component with a reinforcement on the inner shroud, which stiffens it against slipping axial deformation. Starting from an approximately flat, radial alignment of the blade axes in the unloaded state, these are offset by the static pressure difference in front of / behind the guide blade ring during deflection Zero "axially deflected towards the middle of the rim and possibly also curved.
- the guide vane rim is therefore mechanically comparable to a disc spring, the inner edge (hole edge) of which forms the inner cover band and the outer edge of which forms the outer cover band.
- the inner cover band is both axially displaced as well as twisted / inverted due to the blade-induced moments, which means that the material cross-sections of the shroud visible in radial-axial sections are rotated more or less around imaginary axes perpendicular to the cutting surface depending on the rigidity / reinforcement.
- the inventive reinforcement of the inner shroud against said inversion also reduces the axial deflection of the blade axes and thus the overall deformation of the guide vane ring under load. This improves the dimensional stability of the static component Inner Airseal ".
- the at least triple bearing which allows radial movements ( Spoke centering ") of the shroud segments practically does not hinder thermal expansion / contraction and thus also contributes to minimizing tension. In addition, exact centering in the housing is achieved.
- the combination of the guide vane ring construction and bearing arrangement and cooling air ducting according to the invention has the result that the deformation behavior of the ring is mainly determined by the conditions / temperatures in the hot gas, which are also decisive for the rotor behavior. Since the static components of the Inner "- and Outer Airseal "are carried by the guide vane rings and behave in conformity with them, the best possible adaptation of the deformations of the static and rotary sealing components with regard to time course, size and direction is achieved with changing operating conditions (unsteady operation). Thus, the machine can consistently with approximately constant, minimal gaps or leakage losses and thus high efficiency can be achieved, especially in the guide vane area there is no risk of premature component fatigue. The use of brush seals is promoted or even made possible by the conformal behavior of the seal carrier (slight gap change, low eccentricity etc.).
- the present invention is generally for turbomachines with a rotor and stator, i.e. suitable for compressors and turbines, which at least in sections in Axial design, i.e. with predominantly axial flow.
- Axial design i.e. with predominantly axial flow.
- Thermodynamic and due to their size, low-pressure turbines are likely to be medium to large Gas turbine engines are preferred applications, which is why the figure Example from this area shows.
- the first two stages are from the low-pressure turbine 1 and from this in turn the relevant elements of the top half are shown, with the turbine / engine axis would run horizontally below the representation.
- the flow direction of the working gas runs from left to right, i.e. first through the guide vane ring 14, then through the area of the blades 3, then through the guide vane ring 15 and through the area of the moving blades 4, whereby further stages (leading, running) can follow.
- the outer engine casing forms the housing 13 in which the guide vane rings 14, 15 are radially centered and are axially fixed. Both the blades 3,4 and the vane rings 14, 15 are designed with inner and outer cover bands 5 to 8 and 16 to 19, the inner and outer blade shrouds between each the blades have gaps, including damaged blades can be replaced individually are.
- the guide vane rings 14, 15 are designed as self-supporting components, their mechanical stability being achieved predominantly in the area of the inner shrouds 16, 17. There are closed in the circumferential direction, ie circumferential ", reinforcements 20, 21 arranged, which also decisively influence the thermal behavior (changes in shape and shape) of the guide vane rings 14, 15.
- the gas forces during operation cause, among other things, an inverting axial deformation of the guide vane rings, ie an axial deflection increasing from the outer to the inner shroud with some twisting of the shrouds plate spring-like "deformation can be significantly reduced by the reinforcements on the inner cover bands.
- the reinforcements shown are, for example, the toroidal hollow bodies shown, axially spaced rings, combinations of hollow and solid profiles, etc., the space conditions also playing a role.
- the reinforcements should play a role.
- the reinforcements should in any case - in the axial / radial section - have as large a moment of inertia as possible about a radial axis, for example through the center of gravity, which can be achieved by sufficient, axially spaced area portions.
- the area portions of the shroud are to be taken into account here.
- the determination of the stresses and deformations in the Stülpen is possible using relevant calculation methods.
- the reinforcement 20 is positively connected to the shroud 16, the Guide vane ring 14 can consist of several segments, which on the reinforcement be held together.
- the reinforcement 21, however, is in the shroud 17 integrated, i.e. integrally joined with this.
- Guide vane segments are the starting parts, which by welding or Solder in the area of the inner shroud / reinforcement.
- outer shrouds 18, 19 should still be segmented in the installed state be, i.e. have several joints on the circumference to prevent thermal stress minimize.
- the Inner Airseal is - at least predominantly - designed with brush seals, brushes 22, 23 fastened in the area of the guide vane ring reinforcements running against rings 11, 12 connected to the rotor 2, which form axial stops for the rotor blades 3, 4.
- the honeycomb carriers 28, 29 are in turn mounted on the guide vane rings 14, 15 and are therefore adapted to the deformation behavior thereof.
- air cooling is used for the housing and the bearing units the guide vane rings provided, which is not so constructively is complex, like an ACC system.
- an air guide shell 30 is arranged at a radial distance, so that between this and the housing cooling air can flow in the longitudinal direction of the engine.
- the admission the cooling air, which is usually branched off from the compressor, is carried out via bores 35 into a first chamber 33.
- the air guide shell has in the area of the bearing journals 26 and 27 30 deliberately gas-permeable openings 31,32, so that part of the cooling air along the journals 26, 27 in the area of the outer shrouds 18, 19 of the guide vane rings 14.15 can flow, a corresponding pressure drop (Cooling air overpressure) provided.
- This cools the bearings and Heat flows from the vane rings to the housing are minimized.
- the wall element 37 has - not shown - restrictors or forms itself with corresponding ones Throttle columns a restrictor for the cooling air, so that this in the subsequent Chamber 34 enters with reduced pressure. It is sufficient if the cooling air only a moderate overpressure in relation to the working gas in the adjacent one Has flow channel.
- the pressure of the working gas decreases axially, it makes sense to also to reduce the cooling air pressure at least in a few stages, which is here is achieved by the chamber design mentioned with restrictors. High pressures the cooling air would also have a high compressive strength of the air guide shell 30 require, i.e. larger wall thicknesses and more weight.
- Wall elements 36, 38 There are more between the flow channel of the working gas and the cooling air channel Wall elements 36, 38 arranged, which secondary gas flows, i.e. -losses, to prevent through these passages. For cooling reasons, these are also Wall elements 36, 38 deliberately designed or fastened somewhat gas-permeable.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Die Erfindung betrifft eine Strömungsmaschine mit Rotor und Stator in strömungstechnisch ein- oder mehrstufiger Ausführung, gemäß dem Oberbegriff des Patentanspruches 1.The invention relates to a fluid flow machine with a rotor and stator in fluidic terms single or multi-stage design, according to the preamble of the claim 1.
Eine derartige Strömungsmaschine ist beispielsweise aus der DE-PS 27 45 130 bekannt,
wobei diese Schrift sich speziell auf Axialturbinen mit Labyrinthdichtungen
bezieht. Der Strömungskanal des Arbeitsmediums führt abwechselnd durch Leit- und
Laufschaufelkränze wobei die statischen Bauteile radial von außen, die rotierenden
radial von innen in diesen hineinragen. Wie Figur 1 dieser Schrift deutlich zeigt, gibt
es sowohl radial innen angeordnete Dichtungen zwischen dem Rotor und den Leitschaufelkränzen
(Inner Airseal") als auch radial außen angeordnete Dichtungen zwischen
den Laufschaufeln und dem Stator (
Bei der Axialturbine gemäß der DE-PS sind die Dichtfins (Pos.8) der
Am stromabwärtigen Ende des äußeren Deckbandes jedes Leitschaufelsegmentes
ist eine -im Längsschnitt- abgewinkelteAnlagestufe mit einer radial nach außen weisenden
Anlagefläche vorhanden, welche im Betrieb infolge eines strömungsinduzierten
Kippmomentes um das stromaufwärtige
Die DE-PS 35 40 943 beschreibt ein solches Spaltkontrollsystem speziell für ein Zweistromtriebwerk. Bei diesem erstreckt sich der Sekundärluftkanal zumindest bis zum Ende des Turbinenbereiches und weist Öffnungen (Pos. 11) in seiner Innenwand auf, durch die Sekundärluft von außen gezielt auf Bereiche des Turbinengehäuses geblasen werden kann. Bei diesem vereinfachten ACC-System besteht ggf. das Problem, daß der geringe Überdruck des Sekundärluftstromes nicht ausreicht, um in örtlich eng begrenzten Gehäusezonen durch entsprechend kleine Strömungsquerschnitte Kühlluftströme mit ausreichendem Massendurchsatz zu erzeugen. Üblicherweise wird bei einem ACC Verdichterluft aus dem Booster bzw. Niederdruckverdichter als Kühlmittel abgezweigt, in separaten Kanälen geführt und über Ventile gezielt ausgeblasen.DE-PS 35 40 943 describes such a gap control system especially for one Dual-flow engine. In this, the secondary air duct extends at least up to to the end of the turbine area and has openings (item 11) in its inner wall on, through the secondary air from the outside targeted to areas of the turbine housing can be blown. This simplified ACC system may have the problem that the low excess pressure of the secondary air flow is not sufficient to in locally narrow housing zones due to correspondingly small flow cross sections To generate cooling air flows with sufficient mass flow. Usually with an ACC compressor air from the booster or low pressure compressor branched off as coolant, routed in separate channels and via valves specifically blown out.
Bei kleineren Gasturbinentriebwerken ist es bekannt, Leitschaufelkränze als selbsttragende,
integrale Bauelemente mit geschlossenen Deckbändern auszuführen und
im Gehäuse zu zentrieren.Aus fertigungstechnischen sowie festigkeitstechnischen
Gründen (Thermospannungen) ist diese
Die DE-OS 33 36 420 beschreibt einen Mechanismus zum Schutz gegen ein Überdrehen eines Gasturbinenrotors bei Wellenbruch. Der Mechanismus wirkt in der Weise daß die Leitschaufelsegmente mindestens eines Leitschaufelkranzes axial verschwenkt und in Berührung/Eingriff mit benachbarten Laufschaufeln gebracht werden. Die wechselseitige mechanische Schaufelreibung und -zerstörung bremst den Rotor schnell und effektiv ab. Die zu dem Mechanismus gehörenden Leitschaufelsegmente weisen je ein Schwenklager am äußeren Deckbandsegment auf und sind an ihrem Innenumfang mittels eines formschlüssigen, ringartigen Verstärkungs-elementes verbunden, so daß die Segmente zusammen einen steifen, selbsttragenden Leitschaufelkranz bilden. Bei der Ausführung gemäß Figur 2 und 3 bilden die Schwenklager (Positionen 36,56,58 und 64) eine Speichenzentrierung für den eigenstabilen Leitschaufelkranz, was eine genaue Positionierung/Zentrierung bei reduzierten Thermospannungen ermöglicht. Nachteilig ist der Wärmeübergang vom Heißgasbereich zum Gehäuse (Pos. 34), von dem auch die Lagerelemente betroffen sind. Die resultierenden hohen Temperaturen und Temperaturgradienten in den Bauteilen dieses Bereiches können die Standzeit/Lebensdauer erheblich reduzieren.DE-OS 33 36 420 describes a mechanism for protection against overtightening of a gas turbine rotor in the event of a shaft break. The mechanism works in the Way that the guide vane segments axially at least one vane ring pivoted and brought into contact / engagement with adjacent blades become. The mutual mechanical blade friction and destruction slows down the rotor quickly and effectively. The vane segments belonging to the mechanism each have a pivot bearing on the outer shroud segment and are on their inner circumference by means of a form-fitting, ring-like reinforcement element connected so that the segments together form a rigid, self-supporting Form the guide vane ring. Form in the embodiment according to Figures 2 and 3 the swivel bearings (positions 36, 56, 58 and 64) provide spoke centering for the intrinsically stable guide vane ring, which contributes to precise positioning / centering reduced thermal voltages. A disadvantage is the heat transfer from Hot gas area to the housing (item 34), which also affects the bearing elements are. The resulting high temperatures and temperature gradients in the components this area can significantly reduce the service life.
Die US-PS 3,588,267 schützt eine Leitschaufelkranzkonstruktion in Kunststoffbauweise, bei welcher die Schaufeln an einem geschlossenen, inneren Torus befestigt sind und mit diesem einen selbsttragenden Kranz bilden. Die äußeren Schaufelspitzen sind deckbandlos ausgeführt und direkt in Aussparungen eines metallischen Gehäuses eingeklebt, wobei die Elastizität der Klebung kleine Relativverschiebungen ausgleicht/aufnimmt. Es ist offensichtlich, daß diese Konstruktion für höhere Temperaturen völlig unbrauchbar ist und bestenfalls im Fan- bzw. Niederdruckverdichterbereich Verwendung finden kann.The US-PS 3,588,267 protects a guide vane ring construction in plastic construction, in which the blades are attached to a closed, inner torus and form a self-supporting wreath with it. The outer blade tips are designed without a cover tape and directly in the recesses of a metallic one Glued housing, the elasticity of the bond small relative shifts balances / absorbs. It is obvious that this design is for higher temperatures is completely unusable and at best in the fan or low pressure compressor area Can be used.
Angesichts dieser bekannten Lösungen und ihrer Nachteile besteht die Aufgabe der Erfindung darin, eine Strömungsmaschine mit Rotor und Stator sowie mit mindestens einem, je ein äußeres und ein inneres Deckband aufweisenden Leitschaufelkranz zu schaffen, welche sich in allen Betriebszuständen durch eine optimale Spalthaltung, d.h. durch besonders niedrige, wenig variierende und rechnerisch gut erfaßbare Leckageverluste, somit einen hohen Wirkungsgrad, sowie durch eine relativ einfache, kosten- und gewichtsgünstige, langlebige und wartungsfreundliche Konstruktion ohne die Erfordernis eines aktiven Spaltkontrollsystems (ACC's) auszeichnet und auch mit großen Leistungen und Abmessungen ausführbar sowie funktionstüchtig ist.In view of these known solutions and their disadvantages, there is the task of Invention in a turbomachine with rotor and stator and at least one, each having an outer and an inner cover band guide vane ring to create, which is in all operating conditions by an optimal gap, i.e. due to particularly low, little varying and computationally easy to understand Leakage losses, thus a high efficiency, as well as by a relative simple, cost-effective, low-weight, durable and maintenance-friendly construction without the need for an active gap control system (ACC's) and can also be carried out with large capacities and dimensions and is functional is.
Diese Aufgabe wird durch die im Anspruch 1 gekennzeichnete Kombination der Merkmale A bis D gelöst, in Verbindung mit den gattungsbildenden Merkmalen in dessen Oberbegriff.This object is achieved by the combination of Features A to D solved, in connection with the generic features in its generic term.
Die Erfindung liegt somit in der thermischen Entkoppelung von Gehäuse und Leitschaufeln
mittels einer speziellen Ausführung und Lagerung/Zentrierung mindestens
eines Leitschaufelkranzes sowie mittels Luftkühlung des Gehäuses. Der - mindestens
eine - Leitschaufelkranz ist als selbsttragendes Bauteil mit einer Verstärkung
am inneren Deckband ausgeführt, welche ihn gegen stülpende Axialverformung versteift.
Ausgehend von einer etwa ebenen, radialen Ausrichtung der Schaufelachsen
im unbelasteten Zustand werden diese durch die statische Druckdifferenz vor/hinter
dem Leitschaufelkranz bei Auslenkung
Die erfindungsgemäße Verstärkung des inneren Deckbandes gegen besagte Verstülpung
reduziert auch die axiale Auslenkung der Schaufelachsen und somit die gesamte
Verformung des Leitschaufelkranzes unter Last. Dies verbessert die Maßhaltigkeit
der statischen Komponente der
Durch die wenigen, kleinen Wärmebrücken/Lagereinheiten zwischen äußerem Deckband und Gehäuse sowie durch die Kühlluftführung in diesem Bereich wird ein Wärmetransport vom Gaskanal in das Gehäuse weitestgehend vermieden, wodurch sich u. a. geringe Temperaturgradienten im äußeren Deckband einstellen, was in Kombination mit der Segmentierung des äußeren Deckbandes die Thermospannungen im Leitkranz verringert. Das luftgekühlte Gehäuse bleibt auf einem niedrigen Temperaturniveau, wogegen der Leitkranz insgesamt etwa die Heißgastemperatur annimmt.Due to the few, small thermal bridges / storage units between the outside Cover band and housing as well as through the cooling air duct in this area Heat transfer from the gas duct into the housing is largely avoided, which means yourself u. a. set low temperature gradients in the outer shroud, which in Combined with the segmentation of the outer shroud the thermal stresses reduced in the wreath. The air-cooled case remains low Temperature level, whereas the lead ring as a whole is about the hot gas temperature assumes.
Die mindestens dreifache, jeweils radiale Bewegungen zulassende Lagerung
(
Die erfindungsgemäße Kombination aus Leitschaufelkranzkonstruktion und -lagerung
sowie Kühlluftführung hat zur Folge, daß das Verformungsverhalten des Kranzes
überwiegend durch die Verhältnisse/Temperaturen im Heißgas, welche auch für das
Rotorverhalten maßgeblich sind, bestimmt wird. Da die statischen Komponenten der
In den Unteransprüchen sind bevorzugte Ausgestaltungen der Strömungsmaschine nach dem Hauptanspruch gekennzeichnet.Preferred embodiments of the turbomachine are in the subclaims marked according to the main claim.
Die Erfindung wird anschließend anhand der Figur noch näher erläutert. Diese zeigt einen Teillängsschnitt durch die Niederdruckturbine eines Turboluftstrahltriebwerkes. The invention is explained in more detail with reference to the figure. This shows a partial longitudinal section through the low pressure turbine of a turbo air jet engine.
Die vorliegende Erfindung ist generell für Strömungsmaschinen mit Rotor und Stator, d.h. für Verdichter und Turbinen, geeignet, welche zumindest abschnittsweise in Axialbauart, d.h. mit vorwiegend axialer Durchströmung, ausgeführt sind. Thermodynamisch und abmessungsbedingt dürften Niederdruckturbinen mittlerer bis großer Gasturbinentriebwerke bevorzugte Anwendungsfälle darstellen, weshalb die Figur ein Beispiel aus diesem Bereich zeigt.The present invention is generally for turbomachines with a rotor and stator, i.e. suitable for compressors and turbines, which at least in sections in Axial design, i.e. with predominantly axial flow. Thermodynamic and due to their size, low-pressure turbines are likely to be medium to large Gas turbine engines are preferred applications, which is why the figure Example from this area shows.
Von der Niederdruckturbine 1 sind die ersten beiden Stufen und hiervon wiederum
die relevanten Elemente der oberen Hälfte dargestellt, wobei die Turbinen/Triebwerksachse
horizontal unterhalb der Darstellung verlaufen würde. Die Strömungsrichtung
des Arbeitsgases verläuft von links nach rechts, d.h. zunächst durch
den Leitschaufelkranz 14, dann durch den Bereich der Laufschaufeln 3, anschließend
durch den Leitschaufelkranz 15 und durch den Bereich der Laufschaufeln 4,
wobei noch weitere Stufen (Leit-, Lauf-) folgen können. Die äußere Triebwerkshülle
bildet das Gehäuse 13, in welchem die Leitschaufelkränze 14,15 radial zentriert und
axial fixiert gelagert sind. Sowohl die Laufschaufeln 3,4 als auch die Leitschaufelkränze
14,15 sind mit inneren und äußeren Deckbändern 5 bis 8 und 16 bis 19 ausgeführt,
wobei die inneren und äußeren Laufschaufeldeckbänder jeweils zwischen
den Schaufeln Trennfugen aufweisen, u.a. damit beschädigte Schaufeln einzeln auswechselbar
sind.The first two stages are from the low-pressure turbine 1 and from this in turn
the relevant elements of the top half are shown, with the turbine / engine axis
would run horizontally below the representation. The flow direction
of the working gas runs from left to right, i.e. first through
the guide vane ring 14, then through the area of the
Die Leitschaufelkränze 14,15 sind als selbsttragende Bauelemente ausgeführt, wobei
ihre mechanische Stabilität überwiegend im Bereich der inneren Deckbänder
16,17 erzielt wird. Dort sind in Umfangsrichtung geschlossene, d.h.
Die Verstärkung 20 ist mit dem Deckband 16 formschlüssig verbunden, wobei der
Leitschaufelkranz 14 aus mehreren Segmenten bestehen kann, welche über die Verstärkung
zusammengehalten werden. Die Verstärkung 21 ist hingegen in das Deckband
17 integriert, d.h. stoffschlüssig mit diesem zusammengefügt. Auch hier können
Leitschaufelsegmente die Ausgangsteile sein, welche durch Schweißen oder
Löten im Bereich des inneren Deckbandes/ der Verstärkung verbunden werden.The
Die äußeren Deckbänder 18,19 sollen jedoch im Einbauzustand noch segmentiert
sein, d.h. mehrere Trennfugen am Umfang aufweisen, um Thermospannungen zu
minimieren.However, the
Die Zentrierung und Fixierung der Leitschaufelkränze 14,15 im Gehäuse 13 erfolgt
über
26,27 und
ballig, die
aus
sind. All
about
26.27 and
crowned, the
out
are. Alles
Die
Die
Im Sinne der Erfindung ist eine Luftkühlung für das Gehäuse und die Lagereinheiten
der Leitschaufelkränze vorgesehen, welche konstruktiv jedoch bei weitem nicht so
aufwendig ist, wie ein ACC-System. Zu diesem Zweck ist auf der Innenseite des Gehäuses
13 in radialem Abstand eine Luftleitschale 30 angeordnet, so daß zwischen
dieser und dem Gehäuse Kühlluft in Triebwerkslängsrichtung strömen kann. Der Zutritt
der in der Regel vom Verdichter abgezweigten Kühlluft erfolgt über Bohrungen
35 in eine erste Kammer 33. Im Bereich der Lagerzapfen 26 und 27 besitzt die Luftleitschale
30 bewußt gasdurchlässige Öffnungen 31,32, so daß ein Teil der Kühlluft
längs der Lagerzapfen 26,27 in den Bereich der äußeren Deckbänder 18,19 der Leitschaufelkränze
14,15 strömen kann, ein entsprechendes Druckgefälle
(Kühlluftüberdruck) vorausgesetzt. Dadurch werden die Lagerstellen gekühlt und
Wärmeströme von den Leitschaufelkränzen zum Gehäuse minimiert. Das Wandelement
37 weist - nicht dargestellte - Restriktoren auf oder bildet selbst mit entsprechenden
Drosselspalten einen Restriktor für die Kühlluft, so daß diese in die nachfolgende
Kammer 34 mit reduziertem Druck eintritt. Es reicht aus, wenn die Kühlluft
jeweils nur einen mäßigen Überdruck gegenüber dem Arbeitsgas im angrenzenden
Strömungskanal aufweist. Da der Druck des Arbeitsgases axial abnimmt, ist es sinnvoll,
auch den Kühlluftdruck zumindest in wenigen Stufen zu reduzieren, was hier
durch die genannte Kammerbauweise mit Restriktoren erreicht wird. Hohe Überdrücke
der Kühlluft würden auch eine hohe Druckfestigkeit der Luftleitschale 30
erfordern, d.h. größere Wanddicken und mehr Gewicht. For the purposes of the invention, air cooling is used for the housing and the bearing units
the guide vane rings provided, which is not so constructively
is complex, like an ACC system. For this purpose is on the inside of the
Zwischen dem Strömungskanal des Arbeitsgases und dem Kühlluftkanal sind weitere
Wandelemente 36, 38 angeordnet, welche Arbeitsgasnebenströme, d.h. -verluste,
durch diese Passagen verhindern sollen. Aus Kühlungsgründen sind auch diese
Wandelemente 36,38 bewußt etwas gasdurchlässig ausgeführt bzw. befestigt.There are more between the flow channel of the working gas and the cooling air
Claims (6)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19807247A DE19807247C2 (en) | 1998-02-20 | 1998-02-20 | Turbomachine with rotor and stator |
DE19807247 | 1998-02-20 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0937864A2 true EP0937864A2 (en) | 1999-08-25 |
EP0937864A3 EP0937864A3 (en) | 2000-10-25 |
EP0937864B1 EP0937864B1 (en) | 2003-08-13 |
Family
ID=7858458
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99103156A Expired - Lifetime EP0937864B1 (en) | 1998-02-20 | 1999-02-18 | Guidevane assembly for an axial turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US6139263A (en) |
EP (1) | EP0937864B1 (en) |
JP (1) | JP4230040B2 (en) |
DE (2) | DE19807247C2 (en) |
Cited By (5)
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WO2011018072A3 (en) * | 2009-08-14 | 2011-09-15 | Mtu Aero Engines Gmbh | Fastening element for a guide blade ring of a turbomachine |
CN103482219A (en) * | 2013-09-16 | 2014-01-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Axial and radial positioning method for rotator in gas turbine transporting process |
EP2719869A1 (en) * | 2012-10-12 | 2014-04-16 | MTU Aero Engines GmbH | Axial sealing in a housing structure for a turbomachine |
EP2796667A1 (en) * | 2013-04-24 | 2014-10-29 | MTU Aero Engines GmbH | Slip ring seal |
EP2947281A1 (en) * | 2014-05-14 | 2015-11-25 | MTU Aero Engines GmbH | Gas turbine housing assembly |
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IT1318103B1 (en) * | 2000-07-03 | 2003-07-23 | Nuovo Pignone Spa | CONNECTION SYSTEM BETWEEN A LOW PRESSURE NOZZLE AND UNTRANSITION DUCT IN A GAS TURBINE |
DE10037837C2 (en) | 2000-08-03 | 2002-08-01 | Mtu Aero Engines Gmbh | suspension |
JP2002129901A (en) * | 2000-10-30 | 2002-05-09 | Ishikawajima Harima Heavy Ind Co Ltd | Chip shroud structure |
DE10064272A1 (en) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Gas turbine blade has platform at base with end face turned towards gas flow, smaller blade whose surface is parallel to end face being mounted under platform which is at least as wide as projection of blade width on front edge of platform |
DE10122464C1 (en) * | 2001-05-09 | 2002-03-07 | Mtu Aero Engines Gmbh | Mantle ring for low pressure turbine stage of gas turbine uses segments each having seal carrier and relatively spaced security element with minimum contact between them |
US7059821B2 (en) * | 2003-05-07 | 2006-06-13 | General Electric Company | Method and apparatus to facilitate sealing within turbines |
DE10359730A1 (en) | 2003-12-19 | 2005-07-14 | Mtu Aero Engines Gmbh | Turbomachine, in particular gas turbine |
DE102004016222A1 (en) * | 2004-03-26 | 2005-10-06 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for automatic running gap adjustment in a two-stage or multi-stage turbine |
GB2448116B (en) * | 2007-04-05 | 2009-05-27 | Rolls Royce Plc | Means for cooling a bearing assembly |
US8090456B2 (en) * | 2008-11-03 | 2012-01-03 | United Technologies Corporation | System and method for design and control of engineering systems utilizing component-level dynamic mathematical model |
US8668434B2 (en) * | 2009-09-02 | 2014-03-11 | United Technologies Corporation | Robust flow parameter model for component-level dynamic turbine system control |
US8315741B2 (en) * | 2009-09-02 | 2012-11-20 | United Technologies Corporation | High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control |
DE102009042029A1 (en) * | 2009-09-17 | 2011-03-24 | Mtu Aero Engines Gmbh | Blade ring for flow machine, particularly for gas turbine, has hardened reinforcement on inner shroud, where reinforcement is closed in circumferential direction |
DE102009052314A1 (en) | 2009-11-07 | 2011-05-12 | Mtu Aero Engines Gmbh | Sealing arrangement for a gas turbine and such a gas turbine |
US20110255959A1 (en) * | 2010-04-15 | 2011-10-20 | General Electric Company | Turbine alignment control system and method |
ES2793725T3 (en) | 2010-11-16 | 2020-11-16 | Mtu Aero Engines Gmbh | Rotor blade assembly for a turbine |
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EP2647795B1 (en) | 2012-04-04 | 2018-11-07 | MTU Aero Engines AG | Seal system for a turbo engine |
ES2552474T3 (en) | 2012-04-04 | 2015-11-30 | Mtu Aero Engines Gmbh | Method for manufacturing a coating |
EP2647796A1 (en) * | 2012-04-04 | 2013-10-09 | MTU Aero Engines GmbH | Seal system for a turbo engine |
KR101480089B1 (en) | 2012-05-10 | 2015-01-08 | 이병화 | Anchor Bolt for Wood |
US10975721B2 (en) * | 2016-01-12 | 2021-04-13 | Pratt & Whitney Canada Corp. | Cooled containment case using internal plenum |
IT201900014724A1 (en) | 2019-08-13 | 2021-02-13 | Ge Avio Srl | Elements for retaining blades for turbomachinery. |
IT201900014736A1 (en) | 2019-08-13 | 2021-02-13 | Ge Avio Srl | Integral sealing elements for blades held in a rotatable annular outer drum rotor in a turbomachinery. |
IT201900014739A1 (en) | 2019-08-13 | 2021-02-13 | Ge Avio Srl | Elements for retaining blades for turbomachinery. |
CN115387906B (en) * | 2022-05-12 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Air inlet bearing frame connecting structure of low inlet hub ratio engine and assembling method |
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1998
- 1998-02-20 DE DE19807247A patent/DE19807247C2/en not_active Expired - Fee Related
-
1999
- 1999-02-18 EP EP99103156A patent/EP0937864B1/en not_active Expired - Lifetime
- 1999-02-18 DE DE59906550T patent/DE59906550D1/en not_active Expired - Lifetime
- 1999-02-19 US US09/252,752 patent/US6139263A/en not_active Expired - Lifetime
- 1999-02-19 JP JP04200599A patent/JP4230040B2/en not_active Expired - Fee Related
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US3588267A (en) | 1968-06-27 | 1971-06-28 | Rolls Royce | Blade assembly for a fluid flow machine |
DE2745130C2 (en) | 1977-10-07 | 1980-01-03 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Sealing device for the free blade ends of axial turbines |
DE3336420A1 (en) | 1982-10-06 | 1984-04-12 | Rolls-Royce Ltd., London | Mechanism to prevent over-revving of the turbine rotor of a gas turbine engine in the event of a broken shaft |
DE3540943C2 (en) | 1985-11-19 | 1992-01-23 | Mtu Muenchen Gmbh |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011018072A3 (en) * | 2009-08-14 | 2011-09-15 | Mtu Aero Engines Gmbh | Fastening element for a guide blade ring of a turbomachine |
EP2719869A1 (en) * | 2012-10-12 | 2014-04-16 | MTU Aero Engines GmbH | Axial sealing in a housing structure for a turbomachine |
US9605551B2 (en) | 2012-10-12 | 2017-03-28 | MTU Aero Engines AG | Axial seal in a casing structure for a fluid flow machine |
EP2796667A1 (en) * | 2013-04-24 | 2014-10-29 | MTU Aero Engines GmbH | Slip ring seal |
US9835039B2 (en) | 2013-04-24 | 2017-12-05 | MTU Aero Engines AG | Slide ring seal |
CN103482219A (en) * | 2013-09-16 | 2014-01-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Axial and radial positioning method for rotator in gas turbine transporting process |
CN103482219B (en) * | 2013-09-16 | 2016-06-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotor is carried out axle, radial localization method by a kind of internal combustion turbine transportation |
EP2947281A1 (en) * | 2014-05-14 | 2015-11-25 | MTU Aero Engines GmbH | Gas turbine housing assembly |
US9816386B2 (en) | 2014-05-14 | 2017-11-14 | MTU Aero Engines AG | Casing arrangement for a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
EP0937864B1 (en) | 2003-08-13 |
JPH11294103A (en) | 1999-10-26 |
US6139263A (en) | 2000-10-31 |
DE19807247C2 (en) | 2000-04-20 |
JP4230040B2 (en) | 2009-02-25 |
DE59906550D1 (en) | 2003-09-18 |
EP0937864A3 (en) | 2000-10-25 |
DE19807247A1 (en) | 1999-09-09 |
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