EP0040267A1 - Cooled turbine stator - Google Patents

Cooled turbine stator Download PDF

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Publication number
EP0040267A1
EP0040267A1 EP80200461A EP80200461A EP0040267A1 EP 0040267 A1 EP0040267 A1 EP 0040267A1 EP 80200461 A EP80200461 A EP 80200461A EP 80200461 A EP80200461 A EP 80200461A EP 0040267 A1 EP0040267 A1 EP 0040267A1
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EP
European Patent Office
Prior art keywords
guide vane
vane carrier
carrier according
guide
channels
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
Application number
EP80200461A
Other languages
German (de)
French (fr)
Other versions
EP0040267B1 (en
Inventor
Wolfgang Beckershoff
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Priority to AT80200461T priority Critical patent/ATE16035T1/en
Priority to EP80200461A priority patent/EP0040267B1/en
Priority to DE8080200461T priority patent/DE3071161D1/en
Priority to JP6351181A priority patent/JPS5710707A/en
Priority to US06/260,336 priority patent/US4386885A/en
Publication of EP0040267A1 publication Critical patent/EP0040267A1/en
Application granted granted Critical
Publication of EP0040267B1 publication Critical patent/EP0040267B1/en
Expired legal-status Critical Current

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    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor

Definitions

  • the present invention relates to a guide vane carrier for a gas turbine, which is designed in two parts and is provided with cooling channels and carries cooled guide vanes and is conical in relation to the longitudinal axis of the turbine.
  • the guide vane carriers in gas turbines take on the Guide vanes acting aerodynamic forces and forward them to the housing, whereby the guide vane carriers are exposed to the typical boiler tensions as the machine housing at a relatively high intrinsic temperature.
  • guide vane supports were formed as separate parts, which made it possible for them to expand freely due to their own temperature. They are arranged housing in known manner in the overall 'that they are advantageously fixed in the downstream cooler parts and sealed.
  • the conical design of the guide vane carrier enables the arrangement of coolant channels in its walls, the curvature and kink-free design of its longitudinal section profile reducing the bending moment on the partial flange due to residual thermal stresses in the wall to a minimum.
  • the tapping holes branching off from the coolant channels to the individual guide vanes enable a uniform and adjustable coolant flow.
  • the arrangement according to the invention of preferably obliquely axial bores or channels in the wall line of gravity avoids expansion differences which can lead to bending moments and the resulting flange stresses.
  • the design of the coolant guides as oblique-axial channels or pipes cast into the guide vane carrier wall, which alternately have coolant supply lines and discharge lines over the circumference of the guide vane carrier, with radial or radial-axial feed bores from or to the components to be cooled being arranged at suitable locations can, by means of this arrangement alternating over the circumference in the wall, on average compensate for the locally different temperature influences.
  • the arrangement of the coolant channels in the neutral phase of the guide vane carrier wall results in the advantages that the inevitable weakening of the guide vane carrier wall when bending moments and tensile forces occur, and for other uneven temperature distributions due to different residual wall thicknesses and resulting deformations can be avoided.
  • the arrangement of a cylindrically shaped part on the high-pressure side end of the guide vane carrier simplifies the fastening of the components to be connected at this end, for example the inlet segments, the hot gas housing and the intermediate jacket.
  • the guide vane carriers preferably have a separating surface in the horizontal plane, a partial surface screw connection must be provided, which must be designed in such a way that it does not diverge during operation as a result of the bending moments that occur as a result of thermal stresses.
  • the inventive comb profile-like design of the flange screw connection of the guide vane carrier wherein the comb profiles can be formed by welding individual sheets, enables the partial surface flange to be screwed together by means of screws which are located in slots which are open on one side.
  • the flange material delimiting the screw slots forms rib-like projections which, in connection with the. Wall of the guide vane carrier form the comb profile. Since each slot only has to have the width of the screw shaft, for example the expansion shaft of an expansion screw, the comb section can be kept much smaller.
  • the open slots of the air flowing around the guide vane carrier and coming out of the compressor allow these parts to flow freely, whereby both the flange material and the fastening screws are heated evenly, so that the otherwise usual thermal stresses in the flange zone and the expansion of the screw shafts beyond the yield point be avoided.
  • the section modulus and the overall cross-section are reinforced by the comb profiles, the slots can be made so deep that they affect the sealing strip provided.
  • the groove base of the slots is semicircular, whereby the notch effect is largely eliminated, which is particularly the case with Comb profiles welded together from sheet metal parts have an advantageous effect as a wall transition which is largely defused in terms of the notch effect, and the removal of the penetration which occurs during welding is facilitated.
  • the expansion bolts are held in nut supports, each of which bridges a slot, these nut supports with their preferred and formed boundary surface lying in a groove provided in parallel with the flange surface and having a semicircular cross section.
  • the outer contour of the comb-like flange plates advantageously runs almost rectilinearly and the comb part, which is based on a smooth wall, results in a thickness distribution in which, compared to the known flange contours, material accumulations are much smaller. This applies to both the cross-section itself and 'die existing moments of resistance. The rugged cross-sectional transitions are also missing in such a design.
  • the inlet sections can be locked in the axial direction, in such a way that massive projections of the inlet section engage behind resiliently resilient lugs on the guide vane carrier.
  • the connecting elements to the coolant channels are simultaneously brought into an elastic, form-fitting connection with the guide vane carrier.
  • 1 and 2 denotes a guide vane carrier which has a conically shaped section 2 and a cylindrical section 3, the conical section 2 having the same angle of inclination essentially over its entire length.
  • guide lugs 4 are arranged which guide the guide vane carrier 1 in the machine housing (not shown).
  • the guide lugs 4 'additionally serve to limit displacements of a hot gas housing 5 with an intermediate jacket 6 and a rib 7 is used as a spacer between these two components 10 is arranged in the cylindrical portion 3 and in a nose 11 of a locking element 12. Hollow inlet segments 13 are also attached to the locking element 12.
  • the locking element 12 also serves to guide and seal the connection of the hot gas housing 5, as well as to guide the intermediate jacket 6 and a cooling medium passage 14 for introducing the inlet segment cooling medium, the holder of the inlet segments 13, the holder of the first guide vane / row 10 5 and the guide of cooling medium connecting elements 15, which are arranged between the cooling medium passage 14 and the cooling channel system of the inlet segments 13.
  • Cooling channels 16 are arranged in the guide vane carrier 1 and are supplied with coolant via inlet openings 17 or from which the heated coolant flows out via outlet openings 18.
  • the inlet openings 17 and outlet openings 18 are arranged alternately lying next to one another over the circumference (see also FIGS. 4 and 5).
  • the cooling channels 16 are connected to the cooling channel system of the guide vanes 9, 10 via connecting channels 19. Between the connecting channels 19 and the inlet openings in the guide vanes 9, 10 there are sealing elements 20 provided with passages, which prevent cooling medium from escaping into the spaces between the guide vane feet 21.
  • the cooling channels 16 can be closed at the high-pressure end of the guide vane carrier 1 when no inlet segments 3 need to be cooled.
  • cooling channels 16 alternately supply the guide vanes 9, 10 alone and the inlet segments 13 with cooling medium alternately over the circumference of the guide vane carrier 1, the cooling channel 16 is therefore also alternately closed in pairs or is free to the coolant passage 14 .
  • the arrows drawn in FIGS. 1 and 2 show the direction of flow of the cooling medium.
  • the inlet segment 13 can be, for example, an end piece of an annular combustion chamber.
  • the cross section through the guide vane carrier 1 according to FIG. 4 illustrates the alternating arrangement of the supply and discharge lines of the cooling channels 16, 16 '.
  • two guide vanes 9 are fastened to a common base plate 22, distribution channels 29 being arranged in each base plate in such a way that they communicate with the connecting channels 19.
  • Comb profile-like screw connections 24 are provided in the partial surface area of the guide vane carrier 1.
  • the cylindrical section 3 of the guide vane carrier 1 has slots 25 which cancel out the stiffening effect of the kink between the conical section 2 and the cylindrical section 3, as well as the associated bending moments on the flange screw connection in the event of temperature differences.
  • FIGS. 6, 7 and 8 show details of the partial surface screw connection, again with 1 the wall of the guide vane carrier is designated, on which a flange 26 is arranged, which is tightened with fastening screws 27, preferably with expansion screws.
  • the flanges 26 are designed in such a way that the wall of the guide vane carrier 1 is designed in the manner of a comb profile in the region between the contact surfaces of the fastening screws 27, the slots (according to FIGS. 9 and 10) not being wider than the shaft diameter of the fastening screws 27 requires, while the remaining wall thickness of the guide vane carrier 1 is completely the same thickness is held.
  • the outer contour of the comb profiles 24 runs approximately in a straight line.
  • 27 nut supports 28 are provided under the nuts of the expansion screws, which have a cylindrical underside, which in turn is in a Corresponding grooves with a semicircular cross section is mounted on the flange, which at the same time form the notch-free transition from the flange combs to the general wall and secure the screws 27 together with nuts and nut supports 28 in the screwed state against slipping out of the slot 25 laterally. Since the cylindrical bearing surfaces permit rotary movements about their cylinder axes, this configuration is insensitive to an inclined position of the screws 27 and at least in one plane. thus the approval of coarser manufacturing tolerances.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)

Abstract

In order to improve cooling of an at least two-part guide vane support or carrier for gas turbines, at which deformations do not occur during any operating state and whose parting surface-connection flanges and connection elements are constructed such that they can withstand, essentially free of deformation, all bending moments resulting from the thermal stresses, it is proposed to design the cooling agent channels arranged within the wall of the guide vane support alternately over the circumference thereof as infeed lines or openings and/or outfeed lines or openings and containing connection channels leading to the individual guide vanes or blades. The guide vane support possesses an essentially conical configuration over its axial extent. At the guide vane support there are provided substantially comb-like slotted elements defining the parting surface-connection flanges and the individual comb-like slotted elements may comprise individual sheet metal members which are fixed, as by welding, to the guide vane support.

Description

Die vorliegende Erfindung betrifft einen Leitschaufelträger für eine Gasturbine, welcher.zweiteilig ausgebildet und mit Kühlkanälen versehen ist und gekühlte Leitschaufeln trägt und konzentrisch zur Turbinenlängsachse konisch ausgebildet ist.The present invention relates to a guide vane carrier for a gas turbine, which is designed in two parts and is provided with cooling channels and carries cooled guide vanes and is conical in relation to the longitudinal axis of the turbine.

Bei Maschinen, welche mit einem Arbeitsmittel mit hohem Druck und hoher Temperatur betrieben werden, beispielsweise Gasturbinen, ergeben sich die am häufigsten auftretenden Probleme an jenen Bauteilen, die den heissen Prozessgasen direkt ausgesetzt sind. Derartige Probleme sind im wesentlichen in der verminderten Festigkeit der Werkstoffe bei 'hohen Betriebstemperaturen und in erhöhter Korrosionsan-. fälligkeit dieser Teile zu sehen. Des weiteren treten hohe stationäre und instationäre Wärmespannungen an diesen Bauteilen auf, wodurch die Abdichtung unvermeidlicher Dehnungsspalte, welche je nach dem Betriebszustand, d.h. zwischen Anfahren und Abstellen der Gasturbine variieren können, schwierig und eine leckagefreie Zu- und Abfuhr.von Kühlmitteln problematisch wird.In machines which are operated with a working medium at high pressure and high temperature, for example gas turbines, the most frequently occurring problems arise on those components which are directly exposed to the hot process gases. Such problems are essentially in the reduced strength of the materials at high operating temperatures and in increased corrosion. due dates of these parts. Furthermore, high stationary and unsteady thermal stresses occur on these components, whereby the sealing of unavoidable expansion gaps, which, depending on the operating state, i.e. can vary between starting and stopping the gas turbine, difficult and a leak-free supply and discharge of coolants becomes problematic.

Die Leitschaufelträger in Gasturbinen übernehmen die auf die Leitschaufeln einwirkenden aerodynamischen Kräfte und leiten.sie an das Gehäuse weiter, wobei die Leitschaufelträger bei relativ hoher Eigentemperatur aber nicht den typischen Kesselspannungen wie das Maschinengehäuse.ausgesetzt werden. Ferner wurden derartige Leitschaufelträger als separate Teile ausgebildet, wodurch ermöglicht wurde, dass sie sich aufgrund ihrer Eigentemperatur frei ausdehnen konnten. Sie werden in bekannter Weise so im Ge- 'häuse angeordnet, dass sie vorteilhafterweise in den stromabwärts liegenden kühleren Partien fixiert und abgedichtet werden.The guide vane carriers in gas turbines take on the Guide vanes acting aerodynamic forces and forward them to the housing, whereby the guide vane carriers are exposed to the typical boiler tensions as the machine housing at a relatively high intrinsic temperature. Furthermore, such guide vane supports were formed as separate parts, which made it possible for them to expand freely due to their own temperature. They are arranged housing in known manner in the overall 'that they are advantageously fixed in the downstream cooler parts and sealed.

Die ständige Erhöhung der Leistungen und Wirkungsgrade bei Gasturbinen wurde durch Steigerung der Betriebstemperaturen und Betriebsdrücke erreicht, wodurch die Kühlung immer schwieriger wurde, weil aufgrund des hohen Verdichterenddruckes aus die Verdichteraustrittstemperatur zur Kühlung der gefährdeten Teile bereits zu hoch ist, um noch als Kühlmittel wirksam zu sein.The constant increase in performance and efficiency in gas turbines was achieved by increasing the operating temperatures and operating pressures, which made cooling more and more difficult because, due to the high compressor end pressure, the compressor outlet temperature for cooling the endangered parts is already too high to still be effective as a coolant .

Es ist daher Aufgabe der vorliegenden Erfindung, einen gekühlten Leitschaufelträger zu schaffen, bei welchem in keinem Betriebszustand Deformationen auftreten und dessen Teilflächenflansche und Verschraubungen so ausgebildet sind, dass sie allen aus den Wärmespannungen resultierenden Biegemomenten verformungsfrei standhalten können. Weiterhin soll dabei eine vollständig druckdichte, leckagefreie Kühlmittelverbindung zu und von den zu kühlenden Einzelteilen vorgesehen werden.It is therefore an object of the present invention to provide a cooled guide vane carrier in which deformations do not occur in any operating state and the partial surface flanges and screw connections of which are designed so that they can withstand all bending moments resulting from the thermal stresses without deformation. Furthermore, a completely pressure-tight, leak-free coolant connection to and from the individual parts to be cooled should be provided.

Die vorgenannte Aufgabe wird erfindungsgemäss bei einem Leitschaufelträger der eingangs genannten Art nach dem Kennzeichen des Patentanspruches 1 gelöst.The above object is achieved according to the invention in a guide vane carrier of the type mentioned in the characterizing part of patent claim 1.

Weitere mögliche Ausbildungsformen des Erfindungsgegenstandes gehen aus den abhängigen Unteransprüchen hervor.Further possible forms of training of the subject matter of the invention emerge from the dependent subclaims.

Die konische Ausbildung des Leitschaufelträgers ermöglicht die Anordnung von Kühlmittelkanälen in dessen Wandungen, wobei die krümmungs- und knickfreie Ausbildung dessen Längsschnittprofils das Biegemoment am Teilfächenflansch infolge Restwärmespannungen in der Wand auf ein Minimum reduziert.The conical design of the guide vane carrier enables the arrangement of coolant channels in its walls, the curvature and kink-free design of its longitudinal section profile reducing the bending moment on the partial flange due to residual thermal stresses in the wall to a minimum.

Die von den Kühlmittelkanälen abzweigenden Anzapfbohrungen zu den einzelnen Leitschaufeln ermöglichen eine gleichmässige und einstellbare Kühlmittelströmung. Durch die erfindungsgemässe Anordnung von vorzugsweise schrägaxialen Bohrungen bzw. Kanälen in der Wandschwerlinie werden Dehnungsdifferenzen, welche zu Biegemomenten und daraus resultierenden Flanschbeanspruchungen führen können, vermieden.The tapping holes branching off from the coolant channels to the individual guide vanes enable a uniform and adjustable coolant flow. The arrangement according to the invention of preferably obliquely axial bores or channels in the wall line of gravity avoids expansion differences which can lead to bending moments and the resulting flange stresses.

Die Ausbildung der Kühlmittelführungen als schrägaxiale Kanäle oder in die Leitschaufelträgerwand eingegossene Rohre, welche abwechselnd über den Umfang des-Leitschaufelträgers Kühlmittelzuleitungen und -Ableitungen aufweisen, wobei wiederum an geeigneten Stellen radiale oder radial-axiale,Anspeisebohrungen von bzw. zu den zu kühlenden Bauteilen angeordnet sein können, ermöglicht durch diese über den Umfang alternierende Anordnung in der Wand im Mittel einen Ausgleich der örtlich unterschiedlichen Temperatureinflüsse.The design of the coolant guides as oblique-axial channels or pipes cast into the guide vane carrier wall, which alternately have coolant supply lines and discharge lines over the circumference of the guide vane carrier, with radial or radial-axial feed bores from or to the components to be cooled being arranged at suitable locations can, by means of this arrangement alternating over the circumference in the wall, on average compensate for the locally different temperature influences.

Die Anordnung der Kühlmittelkanäle in der neutralen Phase der Leitschaufelträgerwand ergibt die Vorteile, dass einmal die unvermeidliche Schwächung der Leitschaufelträgerwand bei Auftreten von Biegemomenten und Zugkräften und zum anderen ungleichmässige Temperaturverteilungen infolge unterschiedlicher Restwandstärken und daraus resultierenden Deformationen vermieden werden.The arrangement of the coolant channels in the neutral phase of the guide vane carrier wall results in the advantages that the inevitable weakening of the guide vane carrier wall when bending moments and tensile forces occur, and for other uneven temperature distributions due to different residual wall thicknesses and resulting deformations can be avoided.

Die Anordnung eines zylindrisch ausgebildeten Teiles am hochdruckseitigen Ende des Leitschaufelträgers vereinfacht die Befestigung der an diesem Ende anzuschliessenden Komponenten, beispielsweise der Einlaufsegmente, des Heissgasgehäuses und des Zwischenmantels.The arrangement of a cylindrically shaped part on the high-pressure side end of the guide vane carrier simplifies the fastening of the components to be connected at this end, for example the inlet segments, the hot gas housing and the intermediate jacket.

Da die Leitschaufelträger vorzugsweise in der Horizontalebene eine Trennfläche aufweisen, muss eine Teilflächenverschraubung vorgesehen werden, die so ausgebildet werden muss, dass ein Auseinanderklaffen während des Betriebes als Folge der auftretenden Biegemömente, die aus Wärmespannungen resultieren, verhindert wird.Since the guide vane carriers preferably have a separating surface in the horizontal plane, a partial surface screw connection must be provided, which must be designed in such a way that it does not diverge during operation as a result of the bending moments that occur as a result of thermal stresses.

Die erfindungsgemässe kammprofilartige Ausbildung der Flanschverschraubung des Leitschaufelträgers, wobei die Kammprofile durch Anschweissen einzelner Bleche gebildet sein können, ermöglicht es, dass der Teilflächenflansch mittels Schrauben, welche in einseitig offenen Schlitzen liegen, verschraubt werden kann.' Das die Schraubenschlitze begrenzende Flanschmaterial bildet rippenartige Vorsprünge, welche in Verbindung mit der. Wand des Leitschaufelträgers das Kammprofil bilden. Da jeder Schlitz nur jeweils die Breite des Schraubenschaftes, beispielsweise des Dehn- schaftes einer Dehnschraube, aufzuweisen braucht, kann die Kammteilurig wesentlich kleiner gehalten werden. Des weiteren ermöglichen die offenen Schlitze der den Leitschaufelträger umströmenden, aus dem Verdichter kommenden Luft ein freies Umströmen dieser Teile, wodurch sowohl das Flanschmaterial als auch die Befestigungsschrauben gleichmässig aufgeheizt werden, so dass die sonst üblichen Wärmespannungen in der Flanschzone und die Ueberdehnung der Schraubenschäfte über die Streckgrenze hinaus vermieden werden. Da im Bereich der Schlitze das Widerstandsmoment und der Gesamtquerschnitt durch die Kammprofile verstärkt werden, können die Schlitze so tief ausgebildet werden, dass sie die vorgesehene Dichtleiste tangieren..Der Nutengrund der Schlitze ist halbkreisförmig ausgebildet, wodurch die Kerbwirkung weitgehend eliminiert wird, was insbesondere bei aus Blechteilen zusammengeschweisster Kammprofile sich vorteilhaft als bezüglich der Kerbwirkung weitgehend entschärfter Wandübergang auswirkt, sowie die Beseitigung des beim Schweissen entstehenden Einbrandes erleichtert wird.The inventive comb profile-like design of the flange screw connection of the guide vane carrier, wherein the comb profiles can be formed by welding individual sheets, enables the partial surface flange to be screwed together by means of screws which are located in slots which are open on one side. ' The flange material delimiting the screw slots forms rib-like projections which, in connection with the. Wall of the guide vane carrier form the comb profile. Since each slot only has to have the width of the screw shaft, for example the expansion shaft of an expansion screw, the comb section can be kept much smaller. Furthermore The open slots of the air flowing around the guide vane carrier and coming out of the compressor allow these parts to flow freely, whereby both the flange material and the fastening screws are heated evenly, so that the otherwise usual thermal stresses in the flange zone and the expansion of the screw shafts beyond the yield point be avoided. Since in the area of the slots the section modulus and the overall cross-section are reinforced by the comb profiles, the slots can be made so deep that they affect the sealing strip provided. The groove base of the slots is semicircular, whereby the notch effect is largely eliminated, which is particularly the case with Comb profiles welded together from sheet metal parts have an advantageous effect as a wall transition which is largely defused in terms of the notch effect, and the removal of the penetration which occurs during welding is facilitated.

Die Dehnschrauben werden in Mutternauflagen gehalten, welche jeweils einen Schlitz überbrücken, wobei diese Mutternauflagen mit deren vorzugsweiserund ausgebildeter Begrenzungsfläche in einer zur Flanschfläche parallel vorgesehenen, einen halbkreisförmigen Querschnitt aufweisenden Nut liegen.The expansion bolts are held in nut supports, each of which bridges a slot, these nut supports with their preferred and formed boundary surface lying in a groove provided in parallel with the flange surface and having a semicircular cross section.

Vorteilhafterweise verläuft bei einer Dimensionierung gleicher Festigkeit die Aussenkontur der kammartig ausgebildeten Flanschbleche fast geradlinig und die auf eine glatte Wand bezogene Kammpartie ergibt eine Dickenvertei- lung, bei welcher-gegenüber den bekannten Flanschkonturen sich wesentlich geringere Materialanhäufungen ergeben. Dies gilt sowohl für den Querschnitt selbst, als auch für'die vorhandenen Widerstandsmomente. Auch fehlen bei einer derartigen Ausbildung die schroffen Querschnittsübergänge.When dimensioning the same strength, the outer contour of the comb-like flange plates advantageously runs almost rectilinearly and the comb part, which is based on a smooth wall, results in a thickness distribution in which, compared to the known flange contours, material accumulations are much smaller. This applies to both the cross-section itself and 'die existing moments of resistance. The rugged cross-sectional transitions are also missing in such a design.

Gemäss der erfindungsgemässen Ausbildung der Leitschaufelträger sind an diesen die Einlaufpartien in axialer Richtung verriegelbar, und zwar in der Weise, dass massive Vorsprünge der Einlaufpartie hinter elastisch federnde Nasen am Leitschaufelträger einrasten. Beim axialen Aufschieben der Segmente werden gleichzeitig die Verbindungselemente zu den Kühlmittelkanälen in eine elastische, formschlüssige Verbindung mit dem Leitschaufelträger gebracht. Durch diese Ausbildung ist gleichzeitig eine axiale Montage und Demontage der ersten Leitschaufelreihe der Gasturbine ohne Abdecken der Maschine möglich.According to the design of the guide vane carrier according to the invention, the inlet sections can be locked in the axial direction, in such a way that massive projections of the inlet section engage behind resiliently resilient lugs on the guide vane carrier. When the segments are pushed on axially, the connecting elements to the coolant channels are simultaneously brought into an elastic, form-fitting connection with the guide vane carrier. This design enables axial assembly and disassembly of the first row of guide vanes of the gas turbine at the same time without covering the machine.

In der Zeichnung ist ein Ausführungsbeispiel des Erfindungsgegenstandes vereinfacht dargestellt. In den einzelnen Figuren sind gleiche Teile mit denselben Bezugszahlen versehen.In the drawing, an embodiment of the subject matter of the invention is shown in simplified form. In the individual figures, the same parts are provided with the same reference numbers.

Es zeigen:

  • Fig. 1 einen Längsschnitt durch einen Leitschaufelträger mit Kühlmedium-Einführung zu den Leitschaufeln und zur Einlaufpartie,
  • Fig. 2 einen Längsschnitt durch einen Leitschaufelträger mit Kühlmediumaustritt aus den Leitschaufeln und der Einlaufpartie,
  • Fig. 3 einen Längsschnitt durch einen konisch aus- 'gebildeten Leitschaufelträger, ohne zylindri- schen Teil,
  • Fig. 4 einen Querschnitt durch den Leitschaufelträger entlang der Schnittlinie A-A in Fig. 1,
  • Fig. 5 eine Draufsicht auf einen Leitschaufelträger mit Ein- und Austrittsöffnungen für das Kühlmedium,
  • Fig. 6 einen Querschnitt durch eine Teilflächen-Flanschverschraubung,
  • Fig. 7 ein Detail einer Schraubenanordnung in der Teilflächen-Flanschverschraubung gemäss Fig. 6,
  • Fig. 8 eine perspektivische Ansicht einer Mutternauflage für die Schraubenanordnung gemäss Fig. 6,
  • Fig. 9 eine Seitenansicht einer kammprofilartigen Teilflächen-Flanschverschraubung,
  • Fig. 10 eine Draufsicht auf die Anordnung gemäss Fig. 9.
Show it:
  • 1 shows a longitudinal section through a guide vane carrier with cooling medium introduction to the guide vanes and to the inlet section,
  • 2 shows a longitudinal section through a guide vane carrier with cooling medium outlet from the guide vanes and the inlet section,
  • 3 shows a longitudinal section through a conical vane carrier without a cylindrical part,
  • 4 shows a cross section through the guide vane carrier along the section line AA in FIG. 1,
  • 5 is a plan view of a guide vane carrier with inlet and outlet openings for the cooling medium,
  • 6 shows a cross section through a partial surface flange screw connection,
  • 7 shows a detail of a screw arrangement in the partial surface flange screw connection according to FIG. 6,
  • 8 is a perspective view of a nut rest for the screw arrangement according to FIG. 6,
  • 9 is a side view of a comb-shaped partial surface flange screw connection,
  • 10 is a plan view of the arrangement according to FIG. 9.

Gemäss den Fig. 1 und 2 ist mit 1 ein Leitschaufelträger bezeichnet, welcher eine konisch ausgebildete Partie 2 und eine zylindrische Partie 3 aufweist, wobei die konische Partie 2 im wesentlichen über ihre gesamte Länge denselben Neigungswinkel aufweist. An beiden Partien 2, 3 des Leitschaufelträgers 1 sind Führungsnasen 4 angeordnet, welche den Leitschaufelträger 1 im (nicht dargestellten) Maschinengehäuse führen. Die Führungsnasen 4' dienen noch zusätzlich zur Begrenzung von Verschiebungen eines Heissgasgehäuses 5 mit einem Zwischenmantel 6 und als Abstandshalterung zwischen diesen beiden Komponenten dient eine Rippe 7. Am Leitschaufelträger 1 sind in Verhängungen 8 der konischen Partie 2 Leitschaufeln 9 eingehängt, während eine erste hochdruckseitige Leitschaufelreihe 10 in der zylindrischen Partie 3 und in einer Nase 11 eines Verriegelungselementes 12 angeordnet ist. Am Verriegelungselement 12 sind weiterhin hohl ausgebildete Einlaufsegmente 13 befestigt. Das Verriegelungselement 12 dient ferner zur Führung und Abdichtung des Anschlusses des Heissgasgehäuses 5, sowie zur Führung des Zwischenmantels 6 und einen Kühlmemediumdurchtritt 14 zur Einleitung des Einlaufsegment-Kühlmediums, der Halterung der Einlaufsegmente 13, der Halterung der ersten Leitschaufel/reihe 105 sowie der Führung von Kühlmediumsverbindungselementen 15, welche zwischen dem Kühlmediumsdurchtritt 14 und dem Kühlkanalsystem der Einlaufsegmente 13 angeordnet sind.1 and 2, 1 denotes a guide vane carrier which has a conically shaped section 2 and a cylindrical section 3, the conical section 2 having the same angle of inclination essentially over its entire length. On both lots 2, 3 of the guide vane carrier 1, guide lugs 4 are arranged which guide the guide vane carrier 1 in the machine housing (not shown). The guide lugs 4 'additionally serve to limit displacements of a hot gas housing 5 with an intermediate jacket 6 and a rib 7 is used as a spacer between these two components 10 is arranged in the cylindrical portion 3 and in a nose 11 of a locking element 12. Hollow inlet segments 13 are also attached to the locking element 12. The locking element 12 also serves to guide and seal the connection of the hot gas housing 5, as well as to guide the intermediate jacket 6 and a cooling medium passage 14 for introducing the inlet segment cooling medium, the holder of the inlet segments 13, the holder of the first guide vane / row 10 5 and the guide of cooling medium connecting elements 15, which are arranged between the cooling medium passage 14 and the cooling channel system of the inlet segments 13.

Im Leitschaufelträger 1 sind Kühlkanäle 16 angeordnet, welche über Eintrittsöffnungen 17 mit Kühlmittel beschickt werden, bzw. aus welchem über Austrittsöfffnungen 18 das aufgeheizte Kühlmittel abfliesst. Dabei sind die Eintritts-17 und Austrittsöffnungen 18 alternierend über den Umfang nebeneinander liegend angeordnet (siehe ebenfalls Fig. 4 und 5). Die Kühlkanäle 16 sind über Verbindungskanäle 19 mit dem Kühlkanalsystem der Leitschaufeln 9, 10 verbunden. Zwischen den Verbindungskanälen 19 und den-Eintrittsöffnungen in den Leitschaufeln 9, 10 sind mit Durchtritten versehene Dichtelemente 20 angeordnet, welche ein Austreten von Kühlmedium in die Räume zwischen den Leitschaufelfüssen 21 verhindern. Die Kühlkanäle 16 können am Hochdruckende des Leitschaufelträgers 1 dann verschlossen werden, wenn keine Einlaufsegementel3 gekühltwerden müssen. Da die Kühlkanäle 16 über den Umfang des Leitschaufelträgers 1 alternierend einmal die Leitschaufeln 9, 10 allein und zum anderen daneben'noch die Einlaufsegmente 13 mit Kühlmedium versorgen, ist daher ebenfalls paarweise alternierend einmal der Kühlkanal 16 verschlossen, bzw. ist dieser zum Kühlmitteldurchtritt 14 frei. Die in den Fig. 1 und 2 eingezeichneten Pfeile geben die Strömungsrichtung des Kühlmediums wieder.Cooling channels 16 are arranged in the guide vane carrier 1 and are supplied with coolant via inlet openings 17 or from which the heated coolant flows out via outlet openings 18. In this case, the inlet openings 17 and outlet openings 18 are arranged alternately lying next to one another over the circumference (see also FIGS. 4 and 5). The cooling channels 16 are connected to the cooling channel system of the guide vanes 9, 10 via connecting channels 19. Between the connecting channels 19 and the inlet openings in the guide vanes 9, 10 there are sealing elements 20 provided with passages, which prevent cooling medium from escaping into the spaces between the guide vane feet 21. The cooling channels 16 can be closed at the high-pressure end of the guide vane carrier 1 when no inlet segments 3 need to be cooled. Since the cooling channels 16 alternately supply the guide vanes 9, 10 alone and the inlet segments 13 with cooling medium alternately over the circumference of the guide vane carrier 1, the cooling channel 16 is therefore also alternately closed in pairs or is free to the coolant passage 14 . The arrows drawn in FIGS. 1 and 2 show the direction of flow of the cooling medium.

In der Fig. 3 ist ein Leitschaufelträger 1 ohne die zylindrische Partie 3 (aus Fig. 1 und 2) gezeigt, wobei gleiche Teile mit denselben Bezugszahlen versehen sind. Bei dieser Ausbildung kann das Einlaufsegment 13 beispielsweise ein Abschluss-Stück einer Ringbrennkammer sein.3 shows a guide vane carrier 1 without the cylindrical part 3 (from FIGS. 1 and 2), the same parts being provided with the same reference numbers. In this embodiment, the inlet segment 13 can be, for example, an end piece of an annular combustion chamber.

Der Querschnitt durch den Leitschaufelträger 1 gemäss Fig.4 verdeutlicht die alternierende Anordnung der Zu- und Ableitungen der Kühlkanäle 16, 16'. Jeweils vorzugsweise zwei Leitschaufeln 9 sind an einer gemeinsamen Fussplatte 22 befestigt, wobei in jeder Fussplatte 22 Verteilkanäle 29 so angeordnet sind, dass diese mit den Verbindungskanälen 19 kommunizieren.The cross section through the guide vane carrier 1 according to FIG. 4 illustrates the alternating arrangement of the supply and discharge lines of the cooling channels 16, 16 '. In each case preferably two guide vanes 9 are fastened to a common base plate 22, distribution channels 29 being arranged in each base plate in such a way that they communicate with the connecting channels 19.

In der Fig. 5 sind gleiche Teile mit denselben Bezugszeichen versehen, wie iri den Fig. l'bis 4. Aus der Draufsicht auf den Leitschaufelträger 1 ist die Anordnung der in den und aus dem Leitschaufelträger 1 führenden Eintrittsöffnungen 17 und Austrittsöffnungen 18, die in die Kühlkanäle 16 (nicht sichtbar) führen, deutlich erkennbar. Zwischen den Eintritts- 17 und Austrittsöffnungen l8 sind die Führungsnasen 4 angeordnet. Am in der Figur unteren Teil sind die zylindrische Partie 3 mit den Nasen 4' und durch Pfeile 23 angedeutete Kühlmediumsübertritte zum, bzw. vom (nicht dargestellten) Einlaufsegment 13 gezeigt.5 are the same parts with the same reference numerals provided as iri Figs. l 'to 4. From the top view of the guide vane 1, the arrangement of the leading in and out of the guide vane 1 inlet openings 17 and outlet openings 18 (not visible) lead into the cooling channels 16, clearly visible . The guide lugs 4 are arranged between the inlet openings 17 and outlet openings 18. At the lower part in the figure, the cylindrical section 3 with the lugs 4 'and coolant transfers indicated by arrows 23 to and from the (not shown) inlet segment 13 are shown.

Im Teilflächenbereich des.Leitschaufelträgers l sind kammprofilartige Verschraubungen 24 vorgesehen. Die zylindrische Partie 3 des Leitschaufelträgers 1 weist Schlitze 25 auf, welche die versteifende Wirkung des Knicks zwischen der konischen Partie 2 und der zylindrischen Partie 3 aufhebt, sowie die dazugehörigen Biegemomente an der Flanschverschraubung bei Temperaturdifferenzen.Comb profile-like screw connections 24 are provided in the partial surface area of the guide vane carrier 1. The cylindrical section 3 of the guide vane carrier 1 has slots 25 which cancel out the stiffening effect of the kink between the conical section 2 and the cylindrical section 3, as well as the associated bending moments on the flange screw connection in the event of temperature differences.

Die Details der Fig. 6, 7 und 8 zeigen Einzelheiten der Teilflächenverschraubung, wobei wiederum mit 1 die Wand des Leitschaufelträgers bezeichnet ist, an welcher ein Flansch 26 angeordnet ist, der mit Befestigungsschrauben 27, vorzugsweise mit Dehnschrauben, zusammengezogen ist. Die Flansche 26 sind so ausgebildet, dass die Wand des Leitschaufelträgers 1 im Bereich zwischen den Auflageflächen der Befestigungsschrauben 27 kammprofilartig ausgebildet ist, wobei die Schlitze (gemäss Fig. 9 und 10) nicht breiter ausgebildet sind, als der Schaftdurchmesser der Befestigungsschrauben 27 erfordert, während die übrige Wandstärke des Leitschaufelträgers 1 vollständig gleich stark gehalten ist. Die Aussenkontur der Kammprofile 24 verläuft annähernd geradlinig. Zur Vermeidung angesenkter ebener Mutternauflageflächen, bei welchen am Uebergang zur Wand relativ grosse Materialanhäufungen und scharfkantige Querschnittsübergänge in Kauf genommen werden müssten, werden unter den Muttern der Dehnschrauben 27 Mutternauflagen 28 (Fig. 8) vorgesehen, welche eine zylindrische Unterseite aufweisen, die ihrerseits in einer korrespondierenden Nute mit Halbkreisquerschnitt am Flansch gelagert ist, die gleichzeitig den kerbfreien Uebergang von den Flanschkämmen zur allgemeinen Wand bilden und die Schrauben 27 samt Muttern und Mutternauflagen 28 im verschraubten Zustand gegen seitliches Herausrutschen aus dem Schlitz 25 sichern. Da die zylindrischen Lagerflächen Drehbewegungen um ihre Zylinderachsen erlauben, wird diese Ausbildung mindestens in einer Ebene unempfindlich gegen eine Schräglage der Schrauben 27 und erlaubt. somit die Zulassung gröberer Herstellungstoleranzen.The details of FIGS. 6, 7 and 8 show details of the partial surface screw connection, again with 1 the wall of the guide vane carrier is designated, on which a flange 26 is arranged, which is tightened with fastening screws 27, preferably with expansion screws. The flanges 26 are designed in such a way that the wall of the guide vane carrier 1 is designed in the manner of a comb profile in the region between the contact surfaces of the fastening screws 27, the slots (according to FIGS. 9 and 10) not being wider than the shaft diameter of the fastening screws 27 requires, while the remaining wall thickness of the guide vane carrier 1 is completely the same thickness is held. The outer contour of the comb profiles 24 runs approximately in a straight line. To avoid countersunk flat nut contact surfaces, in which relatively large material accumulations and sharp-edged cross-sectional transitions would have to be accepted at the transition to the wall, 27 nut supports 28 (FIG. 8) are provided under the nuts of the expansion screws, which have a cylindrical underside, which in turn is in a Corresponding grooves with a semicircular cross section is mounted on the flange, which at the same time form the notch-free transition from the flange combs to the general wall and secure the screws 27 together with nuts and nut supports 28 in the screwed state against slipping out of the slot 25 laterally. Since the cylindrical bearing surfaces permit rotary movements about their cylinder axes, this configuration is insensitive to an inclined position of the screws 27 and at least in one plane. thus the approval of coarser manufacturing tolerances.

BezeichnungslisteLabel list

  • 1 = Leitschaufelträger1 = guide vane carrier
  • 2 = konische Partie2 = conical section
  • 3 = zylindrische Partie3 = cylindrical section
  • 4, 4' = Führungsnasen4, 4 '= guide lugs
  • 5 Heissgasgehäuse5 hot gas housing
  • 6 = Zwischenmantel6 = intermediate sheath
  • 7 = Rippen7 = ribs
  • 8 = Verhängungen .8 = impositions.
  • 9 = Leitschaufeln9 = guide vanes
  • 10 = erste Leitschaufelreihe10 = first row of guide vanes
  • 11 = Nase11 = nose
  • 12 Verriegelungselement12 locking element
  • 13 = Einlaufsegmente13 = inlet segments
  • 14 = Kühlmediumdurchtritt14 = coolant passage
  • 15 = Kühlmediumverbindungselemente15 = cooling medium connecting elements
  • 16, 16' = Kühlkanäle (Zu- und Rücklauf)16, 16 '= cooling channels (supply and return)
  • 17 = Eintrittsöffnungen17 = entry openings
  • 18 = Austrittsöffnungen18 = outlet openings
  • 19 = Verbindungskanäle19 = connecting channels
  • 20 = Dichtelement20 = sealing element
  • 21 = Leitschaufelfüsse21 = guide vane feet
  • 22 = Fussplatte22 = base plate
  • 23 = Pfeile23 = arrows
  • 24 = Kammprofile24 = comb profiles
  • 25 = Schlitze25 = slots
  • 26 = Flansch26 = flange
  • 27 = Verschraubungselemente27 = screw connection elements
  • 28 = Mutternauflagen28 = nut supports
  • 29 = Verteilkanäle29 = distribution channels

Claims (11)

1. Leitschaufelträger für eine Gasturbine, welcher zweiteilig ausgebildet und mit Kühlkanälen versehen ist und gekühlte Leitschaufeln trägt und konzentrisch zur Turbinenlängsachse konisch ausgebildet ist, dadurch gekennzeichnet, dass die in der Leitschaufelträgerwand angeordneten Kühlmittelkanäle (16) über den Umfang abwechselnd als Zu- und/oder Ableitungen (17, 18) für das Kühlmittel ausgebildet und mit Verbindungskanälen (19) zu den einzelnen Leitschaufeln (9, 10) versehensind, und dass der Leitschaufelträger (1) über seine axiale Erstreckung im wesentlichen konisch ist.1. guide vane carrier for a gas turbine, which is formed in two parts and is provided with cooling channels and carries cooled guide vanes and is conical in relation to the longitudinal axis of the turbine, characterized in that the coolant channels (16) arranged in the guide vane carrier wall alternate over the circumference as adapters and / or Leads (17, 18) for the coolant are formed and are provided with connecting channels (19) to the individual guide vanes (9, 10), and that the guide vane carrier (1) is essentially conical over its axial extent. 2. Leitschaufelträger nach Anspruch 1, dadurch gekennzeichnet, dass der Leitschaufelträger (1) in axialer Erstreckung einteilig ausgebildet ist.2. guide vane carrier according to claim 1, characterized in that the guide vane carrier (1) is integrally formed in the axial extent. 3. Leitschaufelträger nach Anspruch 1, dadurch gekennzeichnet, dass die Kühlmittelkanäle (16) als schrägaxiale Bohrungen ausgebildet sind.3. guide vane carrier according to claim 1, characterized in that the coolant channels (16) are designed as obliquely axial bores. 4. Leitschaufelträger nach.Anspruch 1, dadurch gekennzeichnet, dass die Kühlmittelkänäle (16) im Leitschaufelträger (1) eingegossene Rohre sind.4. Guide vane carrier according to claim 1, characterized net that the coolant channels (16) in the guide vane carrier (1) are cast pipes. 5. Leitschaufelträger nach Anspruch 1 und 3, dadurch gekennzeichnet, dass die.Kühlmittelkanäle (16) in der neutralen Fase der Leitschaufelträgerwand angeordnet sind.5. Guide vane carrier according to claim 1 and 3, characterized in that the coolant channels (16) are arranged in the neutral chamfer of the guide vane carrier wall. . 6. Leitschaufelträger nach Anspruch 1, dadurch gekennzeichnet, dass an der Einlaufseite des Leitschaufelträgers (1)'eine zylindrische Partie (3) vorgesehen ist, an welcher eine Einlaufpartie angeordnet ist.. 6. guide vane carrier according to claim 1, characterized in that on the inlet side of the guide vane carrier (1) ' a cylindrical section (3) is provided, on which an inlet section is arranged. 7. Leitschaufelträger nach Anspruch 1, dadurch gekennzeichnet, dass der Leitschaufelträger (1) mit einer kammprofilartigen Teilflächen-Flanschverschraubung versehen ist.7. guide vane carrier according to claim 1, characterized in that the guide vane carrier (1) is provided with a comb-shaped partial surface flange screw connection. 8. Leitschaufelträger nach Anspruch 1 und 7, dadurch gekennzeichnet, dass die Kammprofile (24) der Teilflä- . chen-Flanschverschraubung aus einzelnen angeschweissten Blechen gebildet sind.8. guide vane carrier according to claim 1 and 7, characterized in that the comb profiles (24) of the Teilflä-. Chen flange screw connection are formed from individual welded sheets. 9. Leitschaufelträger nach Anspruch 1 und 7, dadurch gekennzeichnet, dass die Schlitzbreite der einzelnen Kammprofile (24) dem Schaftdurchmesser der Verschraubungselemente (27) entspricht.9. guide vane carrier according to claim 1 and 7, characterized in that the slot width of the individual comb profiles (24) corresponds to the shaft diameter of the screw elements (27). 10. Gekühlter Leitschaufelträger nach Anspruch 9, dadurch gekennzeichnet, dass die Verschraubungselemente (27) Dehnschrauben sind.10. Cooled guide vane carrier according to claim 9, characterized in that the screw elements (27) are expansion screws. 11. Leitschaufelträger nach Anspruch 1, dadurch gekennzeichnet, dass die Einlaufpartie (13) in axialer Richtung mittels elastisch federnder Nasen (4') des Leitschaufelträgers (1) in Vorsprüngen an der Einlaufpartie verriegelbar ist.11. guide vane carrier according to claim 1, characterized in that the inlet section (13) in the axial direction by means of elastically resilient lugs (4 ') of the guide vane carrier (1) can be locked in projections on the inlet section.
EP80200461A 1980-05-19 1980-05-19 Cooled turbine stator Expired EP0040267B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT80200461T ATE16035T1 (en) 1980-05-19 1980-05-19 COOLED VANE CARRIER.
EP80200461A EP0040267B1 (en) 1980-05-19 1980-05-19 Cooled turbine stator
DE8080200461T DE3071161D1 (en) 1980-05-19 1980-05-19 Cooled turbine stator
JP6351181A JPS5710707A (en) 1980-05-19 1981-04-28 Cooled guide blade holding body
US06/260,336 US4386885A (en) 1980-05-19 1981-05-04 Cooled guide support vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP80200461A EP0040267B1 (en) 1980-05-19 1980-05-19 Cooled turbine stator

Publications (2)

Publication Number Publication Date
EP0040267A1 true EP0040267A1 (en) 1981-11-25
EP0040267B1 EP0040267B1 (en) 1985-10-09

Family

ID=8186999

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80200461A Expired EP0040267B1 (en) 1980-05-19 1980-05-19 Cooled turbine stator

Country Status (5)

Country Link
US (1) US4386885A (en)
EP (1) EP0040267B1 (en)
JP (1) JPS5710707A (en)
AT (1) ATE16035T1 (en)
DE (1) DE3071161D1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0716159A1 (en) 1994-12-07 1996-06-12 General Electric Company Brazable articles
EP0735243A2 (en) * 1995-03-31 1996-10-02 General Electric Company Inner turbine shell with bucket tip clearance control
DE19546722A1 (en) * 1995-12-14 1997-06-19 Asea Brown Boveri Gas turbine blade carrier with cooling channels
GB2327466A (en) * 1997-03-20 1999-01-27 Snecma A stator for a gas turbine compressor
EP2159384A1 (en) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Stator vane support for a gas turbine
FR3101105A1 (en) * 2019-09-23 2021-03-26 Safran Aircraft Engines Housing for turbomachine and turbomachine equipped with such a housing

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4627233A (en) * 1983-08-01 1986-12-09 United Technologies Corporation Stator assembly for bounding the working medium flow path of a gas turbine engine
JPS61173284U (en) * 1985-04-15 1986-10-28
JPS62157377U (en) * 1986-03-26 1987-10-06
US4907946A (en) * 1988-08-10 1990-03-13 General Electric Company Resiliently mounted outlet guide vane
DE4327376A1 (en) * 1993-08-14 1995-02-16 Abb Management Ag Compressor and method for its operation
CN1106496C (en) * 1996-06-21 2003-04-23 西门子公司 Turbine shaft and process for cooling it
DE19643716A1 (en) 1996-10-23 1998-04-30 Asea Brown Boveri Blade carrier for a compressor
CA2263508C (en) * 1997-06-19 2003-08-19 Mitsubishi Heavy Industries, Ltd. Sealing device for gas turbine stator blades
GB0403198D0 (en) * 2004-02-13 2004-03-17 Rolls Royce Plc Casing arrangement
EP2148045A1 (en) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Casing section for a gas turbine
EP2159381A1 (en) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Turbine lead rotor holder for a gas turbine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE451857C (en) * 1925-01-06 1927-11-02 Bernhard Moll Dipl Ing Steam power plant, in particular steam turbine, with preheating of the boiler feed water
CH148852A (en) * 1930-07-08 1931-08-15 Escher Wyss Maschf Ag Steam or gas turbine, especially for high pressure and high temperature.
US1938688A (en) * 1931-12-19 1933-12-12 Nanna S Brooke Gas turbine
CH202312A (en) * 1937-03-15 1939-01-15 Bbc Brown Boveri & Cie Set up on machines operated with superheated steam for rapid heating of the same.
GB510672A (en) * 1938-03-18 1939-08-04 British Thomson Houston Co Ltd Improvements in and relating to casings for elastic fluid turbines
GB675484A (en) * 1949-02-10 1952-07-09 English Electric Co Ltd Improvements in and relating to the stator cooling of gas turbines
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
CH425341A (en) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gas turbine with cooling of the blade carriers
CH488098A (en) * 1968-04-10 1970-03-31 Licentia Gmbh Device for cooling the flanges on the housing joints of saturated steam or wet steam turbines
DE1601845A1 (en) * 1967-07-12 1971-02-04 Escher Wyss Gmbh Process for operating a steam or gas turbine with heat exchange channels through which the working medium flows in housing parts of larger material thickness, as well as steam or gas turbine for carrying out this process

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2489683A (en) * 1943-11-19 1949-11-29 Edward A Stalker Turbine
US3275294A (en) * 1963-11-14 1966-09-27 Westinghouse Electric Corp Elastic fluid apparatus
GB1126469A (en) * 1964-09-24 1968-09-05 English Electric Co Ltd Improvements in or relating to gas turbines
US3734639A (en) * 1968-01-25 1973-05-22 Gen Motors Corp Turbine cooling
CH488931A (en) * 1968-03-22 1970-04-15 Sulzer Ag Housing for turbo machines, in particular axially separated housing for high-temperature turbines
US3736069A (en) * 1968-10-28 1973-05-29 Gen Motors Corp Turbine stator cooling control
US4184689A (en) * 1978-10-02 1980-01-22 United Technologies Corporation Seal structure for an axial flow rotary machine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE451857C (en) * 1925-01-06 1927-11-02 Bernhard Moll Dipl Ing Steam power plant, in particular steam turbine, with preheating of the boiler feed water
CH148852A (en) * 1930-07-08 1931-08-15 Escher Wyss Maschf Ag Steam or gas turbine, especially for high pressure and high temperature.
US1938688A (en) * 1931-12-19 1933-12-12 Nanna S Brooke Gas turbine
CH202312A (en) * 1937-03-15 1939-01-15 Bbc Brown Boveri & Cie Set up on machines operated with superheated steam for rapid heating of the same.
GB510672A (en) * 1938-03-18 1939-08-04 British Thomson Houston Co Ltd Improvements in and relating to casings for elastic fluid turbines
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
GB675484A (en) * 1949-02-10 1952-07-09 English Electric Co Ltd Improvements in and relating to the stator cooling of gas turbines
CH425341A (en) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gas turbine with cooling of the blade carriers
DE1601845A1 (en) * 1967-07-12 1971-02-04 Escher Wyss Gmbh Process for operating a steam or gas turbine with heat exchange channels through which the working medium flows in housing parts of larger material thickness, as well as steam or gas turbine for carrying out this process
CH488098A (en) * 1968-04-10 1970-03-31 Licentia Gmbh Device for cooling the flanges on the housing joints of saturated steam or wet steam turbines

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0716159A1 (en) 1994-12-07 1996-06-12 General Electric Company Brazable articles
EP0735243A2 (en) * 1995-03-31 1996-10-02 General Electric Company Inner turbine shell with bucket tip clearance control
EP0735243A3 (en) * 1995-03-31 1996-12-04 Gen Electric Inner turbine shell with bucket tip clearance control
US5913658A (en) * 1995-03-31 1999-06-22 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US6079943A (en) * 1995-03-31 2000-06-27 General Electric Co. Removable inner turbine shell and bucket tip clearance control
US6082963A (en) * 1995-03-31 2000-07-04 General Electric Co. Removable inner turbine shell with bucket tip clearance control
DE19546722A1 (en) * 1995-12-14 1997-06-19 Asea Brown Boveri Gas turbine blade carrier with cooling channels
DE19546722B4 (en) * 1995-12-14 2005-03-31 Alstom Guide vane carrier for a gas turbine
GB2327466A (en) * 1997-03-20 1999-01-27 Snecma A stator for a gas turbine compressor
EP2159384A1 (en) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Stator vane support for a gas turbine
FR3101105A1 (en) * 2019-09-23 2021-03-26 Safran Aircraft Engines Housing for turbomachine and turbomachine equipped with such a housing

Also Published As

Publication number Publication date
ATE16035T1 (en) 1985-10-15
EP0040267B1 (en) 1985-10-09
DE3071161D1 (en) 1985-11-14
JPS5710707A (en) 1982-01-20
US4386885A (en) 1983-06-07
JPS648173B2 (en) 1989-02-13

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