EP0591565B1 - Stator blade fastening for axial through-flow turbomachines - Google Patents
Stator blade fastening for axial through-flow turbomachines Download PDFInfo
- Publication number
- EP0591565B1 EP0591565B1 EP92116970A EP92116970A EP0591565B1 EP 0591565 B1 EP0591565 B1 EP 0591565B1 EP 92116970 A EP92116970 A EP 92116970A EP 92116970 A EP92116970 A EP 92116970A EP 0591565 B1 EP0591565 B1 EP 0591565B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- vane
- segments
- axial
- collar
- guide
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000001816 cooling Methods 0.000 claims description 11
- 239000000969 carrier Substances 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 230000002093 peripheral effect Effects 0.000 claims 1
- 238000007789 sealing Methods 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000009304 pastoral farming Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
Definitions
- the invention relates to an axially flow-through turbomachine, in particular a gas turbine according to the preamble of claim 1.
- a turbomachine is e.g. known from GB-A-647 384.
- Turbomachines with axial flow are generally equipped with a blade carrier for the guide vanes, which is coaxially suspended in a housing, both the housing and the blade carrier being provided with a horizontal parting plane in which the upper and lower halves are screwed together.
- Another measure consists in dispensing with the blade carrier designed as a screwed-together half-shell and in hanging the guide blades in blade carrier segments of the type mentioned above. These blade carrier segments are in turn suspended in radial ribs of the housing. With this solution, it is assumed that the thermal deformation of the outer housing is less than that of a half-shell blade carrier.
- the guide blades are held with their feet in the blade support segments, the foot of each guide blade engaging in two blade support segments that are adjacent in the axial direction.
- the disadvantage here is that the end faces of the blade carrier segments form the flow-limiting walls of the turbomachine and as such are exposed to the high temperatures prevailing in the flow channel.
- the segments must therefore be made of a high quality material.
- the invention tries to avoid this disadvantage.
- the annular space delimited by the blade carrier segments and the collar of the blade roots is expediently connected to a cooling air space via a bore arranged in the blade carrier segments. Since the other free surfaces of the segments also protrude into axially adjacent cooling air spaces, in which the air for cooling the guide vanes is provided, the segments are thus cooled relatively evenly all round.
- the blade carrier segments are provided with interlocking teeth in the circumferential direction.
- a blade carrier segment receives at least three blade roots of the same guide row and is positioned in the turbine housing in a stationary manner by means of a screw. If the screw is arranged in the middle of the segment, this ensures that each segment is stretched on both sides in the circumferential direction, the segment ends growing into the toothings, which are equipped for this purpose with appropriate play.
- the gas turbine of which the exhaust side and the last four axially flowed stages are shown only in FIG. 1 above the machine axis 13, essentially consists of the rotor 1 bladed with rotor blades and the blade carrier segments 2 equipped with guide blades. These segments 2 are via hammer head grooves (Fig.2) in corresponding receptacles in the machine housing 3, here a turbine housing 3. The suspension takes place in radial ribs 22 which are cast integrally with the housing.
- the exhaust housing 5 is flanged to the turbine housing, which essentially consists of a hub-side, annular inner part 6 and an annular outer part 7, which delimit the diffuser 9.
- Both elements 6 and 7 can Half shells with an axial parting plane or one-piece pot housing. They are connected to one another by a plurality of welded-on radial flow ribs 8, which are arranged evenly distributed over the circumference.
- the annular outer part 7 is provided on the turbine side with an annular sealing strip 10 which is flush with the cylinder-side contour of the turbine channel through which the flow passes.
- the outlet-side mounting of the turbomachine is arranged in the cavity within the inner part 6, the rotor 1 being located in a support bearing 4.
- the turbine housing 3 with the radial ribs 22 is provided with a horizontal parting plane (not shown) lying in the machine axis 13.
- the upper and lower halves of the turbine housing, which are generally provided with flanges, are screwed together.
- each guide vane 11 is guided with their feet 14 in the segments 2.
- the foot 14 of each guide vane is provided on its side facing away from the flow channel with brackets which engage in corresponding grooves in the segments 2.
- Each foot is guided over such a bracket in two axially adjacent blade carrier segments 2, 2 '.
- the feet 14 of the guide blades 11 are provided with a collar 15 which is flush with the flow-limiting surface of the blade root.
- the collar extends in the axial direction up to the entry plane 16 of the upstream rotor blade 12. In this plane the collar seals against the foot 14 'of the preceding guide blade 11'.
- the annular space 19 delimited by a segment 2, the opposite collar 15, and the lateral brackets of two adjacent feet 14, 14 ' is connected to a cooling air space 21 via a bore 20 arranged in the blade carrier segment.
- a blade carrier segment 2 comprises three blade feet 11 of the same guide row after blading.
- Each segment is in the turbine housing, i.e. screwed to its corresponding radial rib 22 with a stud 18. These screws are advantageously arranged in the middle of the segment, as seen in the circumferential direction.
- the blade carrier segments 2 are provided with interlocking teeth 17 at their ends on both sides, as can be seen in FIG. 4.
- This toothing 17 has the play S in the circumferential direction in order to allow free expansion of the segments.
Description
Die Erfindung betrifft eine axialdurchströmte Turbomaschine, insbesondere eine Gasturbine gemäß dem Oberbegriff von Anspruch 1. Eine derartige Turbomaschine ist z.B. aus GB-A- 647 384 bekannt.The invention relates to an axially flow-through turbomachine, in particular a gas turbine according to the preamble of claim 1. Such a turbomachine is e.g. known from GB-A-647 384.
Axial durchströmte Turbomaschinen sind in der Regel mit einem in einem Gehäuse koaxial eingehängten Schaufelträger für die Leitschaufeln ausgerüstet, wobei sowohl das Gehäuse als auch der Schaufelträger mit einer horizontalen Trennnebene versehen sind, in welcher die jeweils oberen und unteren Hälften miteinander verschraubt sind.Turbomachines with axial flow are generally equipped with a blade carrier for the guide vanes, which is coaxially suspended in a housing, both the housing and the blade carrier being provided with a horizontal parting plane in which the upper and lower halves are screwed together.
Im instationären Betrieb, wie er bei Kraftwerks-Gasturbinen zur Spitzenlastdeckung häufig vorkommt, treten an den Gehäusen Wärmespannungen und Differenzdehnungen auf, die zu Deformationen an den Gehäusen und Spieländerungen zwischen Gehäuse und Läufer führen. So ist beispielsweise bei derartigen thermischen Turbomaschinen das Problem des Ovalwerdens der beteiligten axial geteilten Gehäuse so alt wie diese Maschinen selbst. Die Ursachen dieser unerwünschten Verformungen sind hauptsächlich im Vorhandensein von Temperaturgradienten über der Wanddicke zu sehen, welche ein unterschiedliches Kriechen zwischen den Aussen- beziehungsweise Innenfasern erzeugen, sowie in der infolge der Trennebenen verursachten Asymmetrie.In transient operation, as is often the case in power plant gas turbines for peak load coverage, thermal stresses and differential expansions occur on the casings, which lead to deformations of the casings and changes in play between the casing and the rotor. For example, in the case of such thermal turbomachines, the problem of the axially divided housings involved becoming oval is as old as these machines themselves. The causes of these undesirable deformations are mainly to be seen in the presence of temperature gradients over the wall thickness, which cause a different creep between the outer and inner fibers generate, as well as in the asymmetry caused by the parting planes.
Bei hochbelasteten Gasturbinen, bei denen die Schaufelträger trotz Kühlung während des Betriebes Temperaturen von 400 bis 450°C annehmen, könnte möglicherweise eine Änderung der Kühlung die Ovalisation beinflussen. Allerdings könnte dadurch die radiale Dehnung des Schaufelträgers so beeinflusst werden, dass die Schaufelspiele dadurch verkleinert würden, was zu einer erhöhten Streifgefahr führen würde.In the case of highly loaded gas turbines, in which the blade carriers reach temperatures of 400 to 450 ° C during operation, a change in the cooling could possibly influence the ovalization. However, this could influence the radial expansion of the blade carrier in such a way that the blade clearances would be reduced, which would lead to an increased risk of grazing.
Eine andere Massnahme besteht darin, auf den als zusammengeschraubte Halbschalen ausgebildeten Schaufelträger zu verzichten und die Leitschaufeln in Schaufelträgersegmente der oben genannten Art einzuhängen. Diese Schaufelträgersegmente sind dabei ihrerseits in radialen Rippen des Gehäuses eingehängt. Bei dieser Lösung wird davon ausgegangen, dass die thermische Verformung des Ausssengehäuses geringer ist als jene eines halbschaligen Schaufelträgers. Die Leitschaufeln sind dabei mit ihren Füssen in den Schaufelträgersegmenten gehalten, wobei der Fuss jeder Leitschaufel in je zwei in axialer Richtung benachbartete Schaufelträgersegmente eingreift. Von Nachteil ist hierbei, dass die Stirnseiten der Schaufelträgersegmente die strömungsbegrenzenden Wandungen der Turbomaschine bilden und als solche den im Strömungskanal herrschenden hohen Temperaturen ausgesetzt sind. Die Segmente müssen somit aus einem hochwertigen Werkstoff gefertigt sein.Another measure consists in dispensing with the blade carrier designed as a screwed-together half-shell and in hanging the guide blades in blade carrier segments of the type mentioned above. These blade carrier segments are in turn suspended in radial ribs of the housing. With this solution, it is assumed that the thermal deformation of the outer housing is less than that of a half-shell blade carrier. The guide blades are held with their feet in the blade support segments, the foot of each guide blade engaging in two blade support segments that are adjacent in the axial direction. The disadvantage here is that the end faces of the blade carrier segments form the flow-limiting walls of the turbomachine and as such are exposed to the high temperatures prevailing in the flow channel. The segments must therefore be made of a high quality material.
Die Erfindung versucht diesen Nachteil zu vermeiden.The invention tries to avoid this disadvantage.
Bei einer axial durchströmten Turbomaschine der eingangs genannten Art wird dies erfindungsgemäss durch die Merkmale des Anspruchs 1 erreicht. Der Kragen bildet dabei die strömungsbegrenzende Wandung in der Ebene der Laufschaufel und schützt die Segmente vor unzulässiger Erwärmung.In the case of an axially flow-through turbomachine of the type mentioned at the outset, this is achieved according to the invention by the features of claim 1. The collar forms the flow-limiting wall in the plane of the rotor blade and protects the segments against inadmissible heating.
Zweckmässigerweise wird der von den Schaufelträgersegmenten und den Kragen der Schaufelfüsse begrenzte Ringraum über eine in den Schaufelträgersegmenten angeordnete Bohrung mit einem Kühlluftraum in Verbindung gebracht. Da auch die andern freien Flächen der Segmente in axial benachbarte Kühl lufträume, in welchen auch die Luft für die Kühlung der Leitschaufeln bereitgestellt wird, hineinragen, werden die Segmente somit rundum relativ gleichmässig gekühlt.The annular space delimited by the blade carrier segments and the collar of the blade roots is expediently connected to a cooling air space via a bore arranged in the blade carrier segments. Since the other free surfaces of the segments also protrude into axially adjacent cooling air spaces, in which the air for cooling the guide vanes is provided, the segments are thus cooled relatively evenly all round.
Zur Abdichtung dieser benachbarten Kühllufträume in Axialrichtung sind die Schaufelträgersegmente in Umfangsrichtung mit einer ineinandergreifenden Verzahnung versehen.To seal these adjacent cooling air spaces in the axial direction, the blade carrier segments are provided with interlocking teeth in the circumferential direction.
Von Vorteil ist es, wenn ein Schaufelträgersegment mindestens drei Schaufelfüsse der gleichen Leitreihe aufnimmt und im Turbinengehäuse mittels einer Schraube ortsfest positioniert ist. Sofern die Schraube in der Segmentmitte angeordnet ist, ist in Umfangsrichtung dadurch eine beidseitige Dehnung jedes Segmentes gewährleistet, wobei die Segmentenden in die Verzahnungen hineinwachsen, die hierzu mit entsprechenden Spiel ausgerüstet sind.It is advantageous if a blade carrier segment receives at least three blade roots of the same guide row and is positioned in the turbine housing in a stationary manner by means of a screw. If the screw is arranged in the middle of the segment, this ensures that each segment is stretched on both sides in the circumferential direction, the segment ends growing into the toothings, which are equipped for this purpose with appropriate play.
In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand einer axialdurchströmten Gasturbine dargestellt. Es. zeigen:
- Fig. 1 einen Teillängsschnitt der Gasturbine;
- Fig. 2 eine vergrösserte Ansicht des Details X in Fig. 1:
- Fig. 3 einen Teilquerschnitt der Gasturbine;
- Fig. 4 einen Unteransicht eines Schaufelträgersegmentes;
- Fig. 5 eine axiale Dichtung zwischen zwei benachbarten Schaufelfüssen.
- 1 shows a partial longitudinal section of the gas turbine;
- FIG. 2 shows an enlarged view of the detail X in FIG. 1:
- 3 shows a partial cross section of the gas turbine;
- 4 shows a bottom view of a blade carrier segment;
- Fig. 5 is an axial seal between two adjacent blade feet.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Nicht dargestellt sind von der Anlage beispielsweise der Verdichterteil, die Brennkammer sowie das vollständige Abgasrohr und der Kamin. Die Strömungsrichtung des Arbeitsmittels ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. The system does not show, for example, the compressor section, the combustion chamber and the complete exhaust pipe and chimney. The direction of flow of the working fluid is indicated by arrows.
Die Gasturbine, von der in Fig. 1 nur oberhalb der Maschinenachse 13 die Abgasseite und die vier letzten, axialdurchströmten Stufen dargestellt sind, besteht im wesentlichen aus dem mit Laufschaufeln beschaufelten Rotor 1 und den mit Leitschaufeln bestückten Schaufelträgersegmenten 2. Diese Segmente 2 sind über Hammerkopfnuten (Fig.2) in entsprechenden Aufnahmen im Maschinengehäuse 3, hier ein Turbinengehäuse 3 eingehängt. Die Einhängung erfolgt in radialen Rippen 22, die integral mit dem Gehäuse vergossen sind.The gas turbine, of which the exhaust side and the last four axially flowed stages are shown only in FIG. 1 above the
An das Turbinengehäuse ist das Abgasgehäuse 5 angeflanscht, welches im wesentlichen aus einem nabenseitigen, ringförmigen Innenteil 6 und einem ringförmigen Aussenteil 7 besteht, welche den Diffusor 9 begrenzen. Beide Elemente 6 und 7 können Halbschalen mit axialer Trennebene oder einteilige Topfgehäuse sein. Sie sind miteinander verbunden durch mehrere angeschweisste radiale Strömungsrippen 8, die gleichmässig verteilt über den Umfang angeordnet sind. Der ringförmige Aussenteil 7 ist turbinenseitig mit einer ringförmigen Dichtleiste 10 versehen, welche bündig ist mit der zylinderseitigen Kontur des durchströmten Turbinenkanals. Im Hohlraum innerhalb des Innenteils 6 ist die austrittsseitige Lagerung der Turbomaschine angeordnet, wobei der Rotor 1 in einem Traglager 4 einliegt.The
Das Turbinengehäuse 3 mit dem radialen Rippen 22 ist mit einer in der Maschinenachse 13 liegenden, nicht dargestellten, horizontalen Trennebene versehen. Darin sind die in der Regel mit Flanschen versehenen oberen und unteren Hälften des Turbinengehäuses miteinander verschraubt.The turbine housing 3 with the
Wie in der Detailansicht in Fig. 2 erkennbar, sind die Leitschaufeln 11 mit ihren Füssen 14 in den Segmenten 2 geführt. Der Fuss 14 jeder Leitschaufel ist hierzu an seiner dem Strömungskanal abgekehrten Seite mit Bügeln versehen, welche in entsprechende Nuten der Segmente 2 eingreifen. Jeder Fuss ist über einen solchen Bügel in zwei in axialer Richtung benachbarteten Schaufelträgersegmenten 2, 2' geführt.As can be seen in the detailed view in FIG. 2, the guide vanes 11 are guided with their
Die Füsse 14 der Leitschaufeln 11 sind mit einem Kragen 15 versehen, der bündig ist mit der strömungsbegrenzenden Fläche des Schaufelfusses. Der Kragen erstreckt sich in Axialrichtung bis zur Eintrittsebene 16 der stromaufwärts angeordneten Laufschaufel 12. In dieser Ebene dichtet der Kragen gegen den Fuss 14' der vorangehenden Leitschaufel 11'.The
Der von einem Segment 2, dem gegenüberliegenden Kragen 15, sowie den seitlichen Bügeln zweier benachbarter Füsse 14, 14' begrenzte Ringraum 19 steht über eine im Schaufelträgersegment angeordnete Bohrung 20 mit einem Kühlluftraum 21 in Verbindung. Die durch diese Bohrung 20 eindringende Luft entweicht aus dem Ringraum 19 über die Dichtung zwischen Kragen 15 und Fuss 14'.The
Fig. 5 zeigt ein Beispiel einer solchen Dichtung. Es handelt sich dabei um zwei in iher Mitte zusammengeheftete Federbleche 23, die in Nuten des Fusses 14' und des Kragens 15 anliegen und somit bei guter Abdichtung die freie Warmebeweglichkeit der beteiligten Elemente gewährleisten. In Umfangsrichtung wird man zweckmässigerweise pro Schaufelfuss ein solches Dichtelement anbringen. An ihren Stosstellen in Umfangsrichtung kann die obengenannte Kühlluft in den Strömungskanal entweichen5 shows an example of such a seal. These are two
Wie in Fig. 3 gezeigt, umfasst ein Schaufelträgersegment 2 nach dem Beschaufeln drei Schaufelfüsse 11 der gleichen Leitreihe. Jedes Segment ist im Turbinengehäuse, d.h. an dessen entsprechender radialer Rippe 22 mit einer Stiftschraube 18 ortsfest verschraubt. Diese Schrauben sind mit Vorteil jeweils in der Segmentmitte - in Umfangsrichtung gesehen - angeordnet.As shown in FIG. 3, a
Zur gegenseitigen Abdichtung von benachbarten Kühllufträumen 21, in denen möglicherweise die Kühlluft unterschiedliche Zustände aufweist, sind die Schaufelträgersegmente 2 an ihren beidseitigen Enden mit einer ineinandergreifenden Verzahnung 17 versehen, wie dies in Fig. 4 erkennbar ist. Diese Verzahnung 17 weist in Umfangsrichtung das Spiel S auf, um eine freie Ausdehnung der Segmente zu erlauben.For mutual sealing of adjacent
- 11
- Rotorrotor
- 2, 2'2, 2 '
- SchaufelträgersegmentBlade carrier segment
- 33rd
- TurbinengehäuseTurbine casing
- 44th
- TraglagerSupport bearing
- 55
- AbgasgehäuseExhaust housing
- 66
- Innenteilinner part
- 77
- AussenteilOutside part
- 88th
- StrömungsrippenFlow ribs
- 99
- DiffusorDiffuser
- 1010th
- StrömungsleisteFlow bar
- 11, 11'11, 11 '
- Leitschaufelvane
- 1212th
- LaufschaufelBlade
- 1313
- MaschinenachseMachine axis
- 14, 14'14, 14 '
- LeitschaufelfussGuide blade root
- 1515
- Kragencollar
- 1616
- Eintrittsebene der LaufachaufelnEntry level of the moving blades
- 1717th
- VerzahnungGearing
- 1818th
- Schraubescrew
- 1919th
- Raumroom
- 2020th
- Bohrungdrilling
- 2121
- kühlluftraumcooling air room
- 2222
- Ripperib
- 2323
- FederblechSpring plate
- SS
- Spiel zwischen 17Game between 17
Claims (5)
- Axial-flow turbomachine, particularly a gas turbine, having a plurality of vane carriers (2, 2') which are suspended coaxially in a machine casing (3) and in which the guide vanes (11, 11') are held by their roots (14, 14'), the roots (14) of the guide vanes (11) being provided with a collar (15) which extends in the axial direction at least to the inlet plane (16) of the rotor blade (12) lying upstream or to the outlet plane of the rotor blade (12) lying downstream, characterized in that the vane carriers are constructed as segments, in that the root (14) of each guide vane engages in each case in two vane carrier segments (2, 2') adjoining one another in the axial direction, and in that the collar (15), at its axial free end, makes a seal against the root (14') of another guide vane (11').
- Turbomachine according to Claim 1, characterized in that the annular space (19) bounded by the vane carrier segments (2) and the collar (15) is in communication with a cooling air space (21) by way of a bore (20) provided in each vane carrier segment.
- Turbomachine according to Claim 1, characterized in that the vane carrier segments (2) are provided in the peripheral direction with interengaging toothing (17).
- Turbomachine according to Claim 1, characterized in that a vane carrier segment (2) holds at least three vane roots (14) of the same guide row.
- Turbomachine according to Claim 1, characterized in that the vane carrier segments (2) are secured in position in the machine casing by means of screws (18).
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP92116970A EP0591565B1 (en) | 1992-10-05 | 1992-10-05 | Stator blade fastening for axial through-flow turbomachines |
| DE59205187T DE59205187D1 (en) | 1992-10-05 | 1992-10-05 | Guide blade attachment for axially flow-through turbomachine |
| US08/121,317 US5387082A (en) | 1992-10-05 | 1993-09-15 | Guide wave suspension for an axial-flow turbomachine |
| JP5247687A JPH06193403A (en) | 1992-10-05 | 1993-10-04 | Axial flow type turbomachinery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP92116970A EP0591565B1 (en) | 1992-10-05 | 1992-10-05 | Stator blade fastening for axial through-flow turbomachines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0591565A1 EP0591565A1 (en) | 1994-04-13 |
| EP0591565B1 true EP0591565B1 (en) | 1996-01-24 |
Family
ID=8210100
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP92116970A Expired - Lifetime EP0591565B1 (en) | 1992-10-05 | 1992-10-05 | Stator blade fastening for axial through-flow turbomachines |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US5387082A (en) |
| EP (1) | EP0591565B1 (en) |
| JP (1) | JPH06193403A (en) |
| DE (1) | DE59205187D1 (en) |
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| EP1118806A1 (en) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Thermally charged wall structure and method to seal gaps in such a structure |
| US6893214B2 (en) * | 2002-12-20 | 2005-05-17 | General Electric Company | Shroud segment and assembly with surface recessed seal bridging adjacent members |
| US6808363B2 (en) * | 2002-12-20 | 2004-10-26 | General Electric Company | Shroud segment and assembly with circumferential seal at a planar segment surface |
| EP1443275B1 (en) * | 2003-01-29 | 2008-08-13 | Siemens Aktiengesellschaft | Combustion chamber |
| US7255929B2 (en) * | 2003-12-12 | 2007-08-14 | General Electric Company | Use of spray coatings to achieve non-uniform seal clearances in turbomachinery |
| FR2902843A1 (en) * | 2006-06-23 | 2007-12-28 | Snecma Sa | COMPRESSOR RECTIFIER AREA OR TURBOMACHINE DISTRIBUTOR SECTOR |
| US7762766B2 (en) * | 2006-07-06 | 2010-07-27 | Siemens Energy, Inc. | Cantilevered framework support for turbine vane |
| US8240045B2 (en) * | 2007-05-22 | 2012-08-14 | Siemens Energy, Inc. | Gas turbine transition duct coupling apparatus |
| FR2918444B1 (en) * | 2007-07-05 | 2013-06-28 | Snecma | CHAMBER BOTTOM DEFLECTOR, COMBUSTION CHAMBER COMPRISING SAME, AND GAS TURBINE ENGINE WHERE IT IS EQUIPPED |
| US8616007B2 (en) * | 2009-01-22 | 2013-12-31 | Siemens Energy, Inc. | Structural attachment system for transition duct outlet |
| US8231338B2 (en) | 2009-05-05 | 2012-07-31 | General Electric Company | Turbine shell with pin support |
| DE102010024289A1 (en) | 2010-04-23 | 2011-10-27 | Carl Freudenberg Kg | Mechanical seal |
| US8651809B2 (en) | 2010-10-13 | 2014-02-18 | General Electric Company | Apparatus and method for aligning a turbine casing |
| EP2700798A1 (en) * | 2012-08-21 | 2014-02-26 | Siemens Aktiengesellschaft | Turbomachine comprising a rotor and a casing |
| DE102014202744A1 (en) * | 2014-02-14 | 2015-08-20 | Siemens Aktiengesellschaft | Protection against erosion and erosion corrosion on webs of cast casings |
| US9631507B2 (en) * | 2014-07-14 | 2017-04-25 | Siemens Energy, Inc. | Gas turbine sealing band arrangement having a locking pin |
| US10030541B2 (en) | 2015-07-01 | 2018-07-24 | Rolls-Royce North American Technologies Inc. | Turbine shroud with clamped flange attachment |
| US11466700B2 (en) * | 2017-02-28 | 2022-10-11 | Unison Industries, Llc | Fan casing and mount bracket for oil cooler |
| DE102018210601A1 (en) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE |
| DE102018210600A1 (en) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | COAT RING ARRANGEMENT FOR A FLOWING MACHINE |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB647384A (en) * | 1948-10-05 | 1950-12-13 | English Electric Co Ltd | Improvements in and relating to gas turbine blading |
| FR1003299A (en) * | 1949-12-13 | 1952-03-17 | Rateau Soc | Further training in gas turbines and other axial turbo-machines |
| GB786689A (en) * | 1955-11-09 | 1957-11-20 | Gen Motors Corp | Improvements relating to elastic-fluid turbines |
| GB904138A (en) * | 1959-01-23 | 1962-08-22 | Bristol Siddeley Engines Ltd | Improvements in or relating to stator structures, for example for axial flow gas turbine engines |
| US3004700A (en) * | 1959-08-18 | 1961-10-17 | Gen Electric | Turbine engine casing |
| US3427000A (en) * | 1966-11-14 | 1969-02-11 | Westinghouse Electric Corp | Axial flow turbine structure |
| US3542483A (en) * | 1968-07-17 | 1970-11-24 | Westinghouse Electric Corp | Turbine stator structure |
| US3892497A (en) * | 1974-05-14 | 1975-07-01 | Westinghouse Electric Corp | Axial flow turbine stationary blade and blade ring locking arrangement |
| CS174516B1 (en) * | 1974-09-26 | 1977-04-29 | ||
| US3981609A (en) * | 1975-06-02 | 1976-09-21 | United Technologies Corporation | Coolable blade tip shroud |
| US5224824A (en) * | 1990-09-12 | 1993-07-06 | United Technologies Corporation | Compressor case construction |
-
1992
- 1992-10-05 EP EP92116970A patent/EP0591565B1/en not_active Expired - Lifetime
- 1992-10-05 DE DE59205187T patent/DE59205187D1/en not_active Expired - Fee Related
-
1993
- 1993-09-15 US US08/121,317 patent/US5387082A/en not_active Expired - Fee Related
- 1993-10-04 JP JP5247687A patent/JPH06193403A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| JPH06193403A (en) | 1994-07-12 |
| DE59205187D1 (en) | 1996-03-07 |
| US5387082A (en) | 1995-02-07 |
| EP0591565A1 (en) | 1994-04-13 |
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