EP3176388B1 - Guide blade segment with radial securing - Google Patents

Guide blade segment with radial securing Download PDF

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Publication number
EP3176388B1
EP3176388B1 EP16201368.4A EP16201368A EP3176388B1 EP 3176388 B1 EP3176388 B1 EP 3176388B1 EP 16201368 A EP16201368 A EP 16201368A EP 3176388 B1 EP3176388 B1 EP 3176388B1
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EP
European Patent Office
Prior art keywords
radial
guide vane
securing element
vane segment
shroud
Prior art date
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EP16201368.4A
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German (de)
French (fr)
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EP3176388A1 (en
Inventor
Markus Schlemmer
Manfred Feldmann
Rudolf Stanka
Oliver Thiele
Bernd Kislinger
Manuel Hein
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3176388A1 publication Critical patent/EP3176388A1/en
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
    • B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
    • 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
    • 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
    • F05D2230/10—Manufacture by removing material

Definitions

  • the present invention relates to a stator segment for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud and a radially inner shroud, which extend along a respective arc and together form a ring portion, wherein in the radial direction between the outer shroud and the inner shroud a plurality of stator blades are arranged side by side in the circumferential direction, which are materially connected to the inner shroud and the outer shroud, in particular integrally connected, wherein the outer shroud in an axial longitudinal direction comprises an axially forward end wall element and an axially rear end wall element, such that the outer shroud and the two end walls in longitudinal section form a trough-like profile, wherein at least one radial securing element is provided on the axially rear end wall, which is adapted to the guide vane segment in the radial direction re To secure to a surrounding housing, wherein the radial securing element is formed as a projection having
  • US2015 / 0125289 A1 shows a vane segment with a trough-like outer shroud, on the rear end wall of radial securing elements are arranged.
  • the radial securing elements have bearing portions with bearing surfaces which lie on a cylindrical peripheral surface. To make this curved surface must be milled from the full, resulting in significant overhead and higher cost of the component.
  • Similar vane segments are off EP 2 811 118 A1 and EP 1 431 517 A2 known.
  • vane segments which may also be referred to as vane clusters
  • vane clusters for improved and simplified assembly of vane segments, which may also be referred to as vane clusters, in a gas turbine engine, it has been found that the provision of radial securing elements is an apt alternative to heretofore known hook fuses.
  • stator vane segment In the radial securing of vane segments, which are usually combined in a gas turbine to form a vane ring, it is particularly important to secure the vane segments within the turbine housing in the radial direction against falling out.
  • the stator vane segment In operation of the gas turbine, the stator vane segment is generally acted upon by the flow to which the vane (s) is exposed, typically a moment which is such that the axially rearward end wall member is forced radially outward, whereas the axially forward one End wall element is pulled radially inward. This moment is taken up by the axially rear end wall element, that the radially outer edge of the same is supported on the housing.
  • the turbomachine if the turbomachine is out of operation, the flow acting on the vanes in the gas duct is missing.
  • the radial fail safe or the radial securing element described here is used. In this way, it is prevented that the guide blade segment can fall out, for example due to gravity, when the turbo
  • the object of the invention is to provide a vane segment, the radial securing element enables a simplified manufacturing.
  • the support section has a bearing surface which lies in a first plane whose normal vector has vector components in the circumferential direction and in the axial direction (AR) and / or in the radial direction (RR).
  • the first plane is in space so as to intersect a tangential plane to the circumferential direction in a plane defined by the radial direction and the circumferential direction. If the normal vector has a vector component in the circumferential direction and in the radial direction (or in the axial and radial directions), the first plane has no curvature in the circumferential direction and can be made simpler by this simplified geometry or shaping.
  • the vane segment in the circumferential direction (UR) on the outer shroud has two shroud side surfaces arranged at a distance from one another, which are designed such that they can come into contact with a shroud side surface of an adjacent guide blade segment, wherein the radial securing element is flush with at least one shroud side surface is trained.
  • the guide vane segment in the circumferential direction to each other at a distance arranged comprise two radial securing elements, so that the guide vane segment is supported defined at two points and can not slip out of the intended position, in particular can not rotate about a radially extending axis.
  • the one radial securing element is formed flush with the one side of the shroud, and that the other radial securing element is arranged at a distance to the other shroud side surface.
  • the distance measured in the circumferential direction of the two radial securing element is smaller than the distance measured in the circumferential direction of the two shroud side surfaces.
  • the radial securing element is produced by linear grinding.
  • Linear grinding enables the movement of a corresponding grinding tool along a main direction of the grinding, and along a feed direction orthogonal thereto. Due to the tool geometry and the linear movement process (grinding main direction), a bearing surface whose normal vector has the abovementioned features can be formed in a simple manner by the linear grinding.
  • the support section has a second surface which lies in a second plane whose normal vector has vector components in the circumferential direction and in the radial direction (RR), in particular also in the axial direction (AR).
  • the second surface and the support surface are inclined to each other, wherein the angle formed by the first and the second plane in a sectional plane which is spanned by the radial direction (RR) and the axial direction (AR), in an area between 70 ° and 90 °, preferably 75 ° to 85 °.
  • the vane segment may further comprise a circumferential securing element in the circumferential direction in a central region of the rear end wall.
  • the step of aligning the blank vane segment and the step of abrading may be performed once for each raw radial-securing member when two or more raw radial securing members are provided on the blank vane segment.
  • the step of aligning the blank vane segment relative to the linear sander is performed such that the linear sander can be moved or spaced apart from other components of the blank vane segment as the raw radial securing element is abraded, in particular at a distance to a circumferentially provided in a central region on the rear end wall circumferential securing element or a corresponding raw circumferential securing element.
  • the linear grinding of the radial securing elements can be adapted for different guide blade segments of different turbine stages or different gas turbines, so that the bearing surface of the radial securing element can be produced by appropriate relative orientation of the guide blade segment and the linear grinding tool and can the linear grinding device not be in contact with other components or components, in particular projections and reinforcing ribs of the vane segment comes into contact.
  • the invention also relates to a gas turbine, in particular an aircraft gas turbine comprising at least one turbine stage with a plurality of vane segments arranged side by side in the circumferential direction, so that they form a turbine blade vane ring, wherein the vane segments have at least one of the features described above.
  • the vane segment according to the invention is defined in claim 1.
  • the inventive method for producing a vane segment is defined in claim 12.
  • the gas turbine according to the invention is defined in claim 15.
  • Fig. 1 shows in a simplified perspective view of a vane segment 10 with a radially inner shroud 12 and a radially outer shroud 14 in the radial direction RR extending between the inner shroud 12 and the outer shroud 14 vanes 16, wherein the number of three vanes 16 shown here for a vane segment 10 is purely exemplary; it is also possible for two, four, five or more vanes to be provided in a vane segment 10.
  • the vane segment 10 of Fig. 1 is shown so that the view of the suction sides 18 and the trailing edges 20 of the guide vanes 16 is released.
  • the radially outer shroud 14 comprises an axially front end wall 22 and an axially rear end wall 24.
  • the two end walls 22, 24 are designed inclined to the shroud 14 so that there is a trough-like profile in a longitudinal section.
  • a radial securing element 26 can be seen, which is formed on the rear end wall 24 and protrudes therefrom against the axial direction AR or against the main flow direction in the turbomachine.
  • Fig. 2 shows a simplified longitudinal sectional view through the outer shroud 14 and a portion of a turbine housing connected to the nozzle segment 10 turbine housing 28.
  • the radial securing element 26 can be seen, which is designed as a projection and projecting against the axial direction AR of the rear end wall 24.
  • the radial securing element 26 has an essentially S-shaped support section 27 with a convex and a concave arc, against which straight pieces or surfaces adjoin.
  • counterpart 30 is formed so that between the radial securing element 26 and the counterpart 30 a system is made possible for radial securing of the vane segment 26 on the housing 30th
  • Fig. 3 shows the in Fig. 2 dashed rimmed area III, so that from this the radial securing element 26 with its support portion 27 and the counterpart 30 of the turbine housing 28 are better visible.
  • the radial securing element 26 comprises at its support portion 27 a support surface 32 and a second surface 34.
  • the counterpart 30 has a contact surface 36 which faces the support surface 32 of the radial securing element 26 lies.
  • the support surface 32 and the second surface 34 are formed inclined to each other, and in the plane of the drawing (plane, which is spanned by the axial direction AR and the radial direction RR) include an angle ⁇ , preferably about 70 ° 90 °, in particular about 75 ° to 85 °.
  • the contact surface 36 on the counterpart 30 of the housing 28 has substantially the same inclination, as the support surface 32. The interaction between the contact surface 32 and the abutment surface 36 allows the securing of the vane segment 10 in the radial direction RR.
  • FIG. 4 Figure 3 is a simplified perspective view of a blank vane segment 10a after casting such a workpiece.
  • outer shroud 14 front end wall 22, rear end wall 24, and the guide vanes 16.
  • two raw radial securing elements 26a and 26b can be seen, which act as a kind of thickened projection against the axial direction AR protrude from the rear end wall 24.
  • a circumferential securing element 40 formed from two ribs can be seen, which is also still in its raw form after casting.
  • the linear grinding process is carried out until the radial securing element 26 or its support section 27 has reached its final shape, in particular the support surface 32 and the second surface 34 are formed.
  • Starting from the raw vane segment 10a of Fig. 4 show the Fig. 5 a view in which the linear grinding device 42, the raw radial securing elements 26 b processed, and in Fig. 6 a representation in which the linear grinding device 42, the raw radial securing element 26 a processed. From each other Raw radial securing element 26a or 26b, which may already be present as a finished radial securing element 26, is in Fig. 5 respectively. Fig. 6 only one upper section visible.
  • the guide vane segment 10 in the region of the outer shroud 14 respective shroud side surfaces 46 which are adapted to that adjacent vane segments 10 may abut each other in the mounted state in the gas turbine.
  • the vane segment 10 in each case has two shroud side surfaces 46, wherein each shroud side surface 46 may be assigned a radial securing element 26.
  • the respective radial securing element 26 may be flush with the shroud side surface 46, as exemplified by the Fig. 5 or even the Fig. 1 is apparent.
  • the radial securing element 26 may be disposed to the shroud side surface 46 at a distance AB, as best shown in FIG Fig. 4 is apparent, but also in the Fig. 6 is indicated in the in the Fig. 6 left radial securing element 26 (26 a), which is shown in contact with the linear grinding device 42.
  • the linear grinding device in the contact region with the radial securing element 26 is not guided tangentially to the curvature formed in this contact region (along the circumferential direction UR) of the shroud 14 or the rear end wall 24. Rather, an angle ⁇ is formed between a longitudinal axis LAS representing the grinding direction of the linear grinding device 42 and the tangential direction TR in the region of the radial securing element 26.
  • the support surface 32 or / and the surface 34 formed by means of the linear grinding device 42 have normal vectors which, in addition to at least one vector component in the axial direction AR and / or radial direction RR, also have a vector component in the circumferential direction UR.
  • Such relative positioning of linear grinder 42 and vane segment 10 relative to one another enables material to be removed from the radial securing elements 26 without the linear grinding device coming into contact with other components of the vane segment 10, particularly with the circumferential securing element 40 also along the circumferential direction UR is provided on the rear end wall 24 and protrudes counter to the axial direction AR thereof.
  • Fig. 7 shows a simplified schematic sectional view approximately along the section line VII-VII of Fig. 6 .
  • the linear grinding device 42 is designed in the region of its grinding surfaces 44 in such a way that it has a contour complementary to the radial securing element 26 or its bearing section 27.
  • this complementary grinding contour it is possible that, by means of linear relative movement of the linear grinding device 42 along the longitudinal axis LAS of the linear grinding device, a successive material removal on a raw radial securing element 26a, 26b (FIG. Fig. 4 ) takes place until the finished radial securing element 26 is formed.
  • a rather complex milling of the radial securing element (s) 26 can be dispensed with compared to the linear grinding.
  • Fig. 8 shows in the sub-figures A) and B) two highly simplified schematic sectional views of the support surface 32 of the radial securing element 26 to illustrate the vector components of the normal vector.
  • Fig. 8A is a longitudinal section, as he also from the Fig. 1 it can be seen, wherein only the support surface 32 is shown as a line with the normal vector NV, and the vector components VRR and VAR in the radial or axial direction.
  • Fig. 8B is a section corresponding to the line VIII-VIII of Fig. 3 , wherein the bearing surface 32 is shown hatched as a line and a portion of the cut radial securing element 26.
  • the normal vector NV with the vector components VRR and VUR in the radial direction or circumferential direction which are shown in this illustration, is shown for the bearing surface 32.
  • the radial securing elements should therefore be able to be produced inexpensively, which makes possible by means of linear grinding is, and provide a safeguard against falling out in the radial direction, in particular in the assembly / disassembly of stator segments of a turbine stage of a gas turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die vorliegende Erfindung betrifft ein Leitschaufelsegment für eine Gasturbine, insbesondere Fluggasturbine, umfassend wenigstens ein radial äußeres Deckband und ein radial inneres Deckband, die sich entlang eines jeweiligen Kreisbogens erstrecken und gemeinsam einen Ringabschnitt bilden, wobei in radialer Richtung zwischen dem äußeren Deckband und dem inneren Deckband mehrere Leitschaufeln in Umfangsrichtung nebeneinander angeordnet sind, die mit dem inneren Deckband und dem äußeren Deckband materialschlüssig verbunden, insbesondere einstückig verbunden sind, wobei das äußere Deckband in einer axialen Längsrichtung ein axial vorderes Stirnwandelement und ein axial hinteres Stirnwandelement umfasst, derart, dass das äußere Deckband und die beiden Stirnwände im Längsschnitt ein wannenartiges Profil bilden, wobei an der axial hinteren Stirnwand wenigstens ein Radialsicherungselement vorgesehen ist, das dazu eingerichtet ist, das Leitschaufelsegment in radialer Richtung relativ zu einem umgebenden Gehäuse zu sichern, wobei das Radialsicherungselement als Vorsprung ausgebildet ist mit einem Auflageabschnitt, der dazu eingerichtet ist, an einem korrespondierenden Gegenstück am Gehäuse abgestützt zu werden.The present invention relates to a stator segment for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud and a radially inner shroud, which extend along a respective arc and together form a ring portion, wherein in the radial direction between the outer shroud and the inner shroud a plurality of stator blades are arranged side by side in the circumferential direction, which are materially connected to the inner shroud and the outer shroud, in particular integrally connected, wherein the outer shroud in an axial longitudinal direction comprises an axially forward end wall element and an axially rear end wall element, such that the outer shroud and the two end walls in longitudinal section form a trough-like profile, wherein at least one radial securing element is provided on the axially rear end wall, which is adapted to the guide vane segment in the radial direction re To secure to a surrounding housing, wherein the radial securing element is formed as a projection having a support portion which is adapted to be supported on a corresponding counterpart on the housing.

In der vorliegenden Anmeldung sind Richtungsangaben wie "Axial-" bzw. "axial", "Radial-" bzw. "radial" und "Umfangs-" grundsätzlich auf die Maschinenachse der Gasturbine bezogen zu verstehen, sofern sich aus dem Kontext nicht explizit oder implizit etwas anderes ergibt.In the present application directional information such as "axial" or "axial", "radial" or "radial" and "circumferential" basically to refer to the machine axis of the gas turbine to understand, unless the context explicitly or implicitly something else results.

US2015/0125289 A1 zeigt ein Leitschaufelsegment mit einem wannenartigen Außendeckband, an dessen hinterer Stirnwand Radialsicherungselemente angeordnet sind. Die Radialsicherungselemente weisen Auflageabschnitte mit Auflageflächen auf, die auf einer zylindrischen Umfangsfläche liegen. Zur Herstellung dieser gekrümmten Fläche muss aus dem vollen gefräst werden, was zu erheblichem Mehraufwand und höheren Kosten des Bauteils führt. Ähnliche Leitschaufelsegmente sind aus EP 2 811 118 A1 und EP 1 431 517 A2 bekannt. US2015 / 0125289 A1 shows a vane segment with a trough-like outer shroud, on the rear end wall of radial securing elements are arranged. The radial securing elements have bearing portions with bearing surfaces which lie on a cylindrical peripheral surface. To make this curved surface must be milled from the full, resulting in significant overhead and higher cost of the component. Similar vane segments are off EP 2 811 118 A1 and EP 1 431 517 A2 known.

In DE 60 2004 003 757 T2 wird vorgeschlagen, Masse an einem Deckband eines Leitschaufelsegments durch eine Reduzierung der Dicke abzutragen. Hierzu wird vorgeschlagen bekannte industrielle Verfahren wie manuelle oder CNC-Hochgeschwindigkeitsbearbeitung, automatisches oder manuelles Schleifen, Elektroerodieren oder Wasserstrahlbearbeitung zu verwenden.In DE 60 2004 003 757 T2 It is proposed to remove mass from a shroud of a vane segment by reducing the thickness. For this purpose it is proposed known industrial processes such as manual or high-speed CNC machining, automatic or manual grinding, electro-erosion or water-jet machining.

In EP 2 878 769 A1 wird vorschlagen die Flanken von Nuten, die zwischen zwei Dichtrippen eines Schaufeldeckbandes vorgesehen sind, in Umfangsrichtung linear auszuführen. Bei diesen Flächen handelt es sich nicht um Auflageflächen.In EP 2 878 769 A1 will suggest the flanks of grooves, which are provided between two sealing ribs of a blade shroud, perform linearly in the circumferential direction. These surfaces are not bearing surfaces.

Für eine verbesserte und vereinfachte Montage von Leitschaufelsegmenten, die auch als Leitschaufelcluster bezeichnet werden können, in einer Gasturbine, hat es sich gezeigt, dass das Vorsehen von Radialsicherungselementen eine passende Alternative zu bisher bekannten Hakensicherungen darstellen.For improved and simplified assembly of vane segments, which may also be referred to as vane clusters, in a gas turbine engine, it has been found that the provision of radial securing elements is an apt alternative to heretofore known hook fuses.

Bei der radialen Sicherung von Leitschaufelsegmenten, die in einer Gasturbine in der Regel zu einem Leitschaufelring zusammengesetzt sind, geht es insbesondere darum, die Leitschaufelsegmente innerhalb des Turbinengehäuses in radialer Richtung gegen ein Herausfallen zu sichern. Im Betrieb der Gasturbine wirkt auf das Leitschaufelsegment durch die Strömung, denen die Leitschaufel(n) ausgesetzt ist bzw. sind, in der Regel ein Moment, welches derartiger Natur ist, dass das axial hintere Stirnwandelement nach radial außen gedrückt wird, wohingegen das axial vordere Stirnwandelement nach radial innen gezogen wird. Dieses Moment wird am axial hinteren Stirnwandelement dadurch aufgenommen, dass sich der radial äußere Rand desselben am Gehäuse abstützt. Ist die Strömungsmaschine jedoch außer Betrieb, so fehlt die auf die Leitschaufeln wirkende Strömung im Gaskanal. Vor allem für diesen Fall dient die hier beschriebene radiale Ausfallsicherung bzw. das Radialsicherungselement. Auf diese Weise wird verhindert, dass das Leitschaufelsegment bei Stillstand der Strömungsmaschine zum Beispiel schwerkraftbedingt herausfallen kann.In the radial securing of vane segments, which are usually combined in a gas turbine to form a vane ring, it is particularly important to secure the vane segments within the turbine housing in the radial direction against falling out. In operation of the gas turbine, the stator vane segment is generally acted upon by the flow to which the vane (s) is exposed, typically a moment which is such that the axially rearward end wall member is forced radially outward, whereas the axially forward one End wall element is pulled radially inward. This moment is taken up by the axially rear end wall element, that the radially outer edge of the same is supported on the housing. However, if the turbomachine is out of operation, the flow acting on the vanes in the gas duct is missing. Especially for this case, the radial fail safe or the radial securing element described here is used. In this way, it is prevented that the guide blade segment can fall out, for example due to gravity, when the turbomachine is at a standstill.

In radialer Richtung sind im Betrieb der Gasturbine geringere Kräfte abzustützen. Ein Abstützen von in Radialrichtung wirkenden Kräften kann in der Regel dann optimal erfolgen, wenn eine Auflagefläche einen Normalenvektor aufweist, der nur Vektorkomponenten in Radialrichtung oder/und Axialrichtung aufweist. Es hat sich allerdings gezeigt, dass derartige Auflageflächen in der Herstellung eher aufwändig sind, wenn die Auflagefläche in Umfangsrichtung entsprechend dem auf die Maschinenachse bezogenen Radius gekrümmt sein soll, oder wenn die Auflagefläche in einer Tangentialebene zum Umfang im Bereich des äußeren Deckbandes liegt.In the radial direction, lower forces are to be supported during operation of the gas turbine. A support of forces acting in the radial direction can usually be optimally carried out when a support surface has a normal vector having only vector components in the radial direction and / or axial direction. However, it has been found that such bearing surfaces are rather expensive to manufacture if the bearing surface should be curved in the circumferential direction in accordance with the radius related to the machine axis, or if the bearing surface lies in a tangential plane to the circumference in the region of the outer shroud.

Aufgabe der Erfindung ist es, ein Leitschaufelsegment bereitzustellen, dessen Radialsicherungselement eine vereinfachte Fertigung ermöglicht.The object of the invention is to provide a vane segment, the radial securing element enables a simplified manufacturing.

Zur Lösung dieser Aufgabe wird vorgeschlagen, dass der Auflageabschnitt eine Auflagefläche aufweist, die in einer ersten Ebene liegt, deren Normalenvektor Vektorkomponenten in Umfangrichtung sowie in Axialrichtung (AR) oder/und in Radialrichtung (RR) aufweist. Anders ausgedrückt, liegt die erste Ebene so im Raum, dass sie eine Tangentialebene bzw. Tangentialrichtung zur Umfangsrichtung in einer Ebene schneidet, die durch die Radialrichtung und die Umfangrichtung aufgespannt ist. Weist der Normalenvektor eine Vektorkomponente in Umfangsrichtung und in Radialrichtung (oder in Axial- und Radialrichtung) auf, weist die erste Ebene keine Krümmung in Umfangsrichtung auf und kann durch diese vereinfachte Geometrie bzw. Formgebung einfacher hergestellt werden.To solve this problem, it is proposed that the support section has a bearing surface which lies in a first plane whose normal vector has vector components in the circumferential direction and in the axial direction (AR) and / or in the radial direction (RR). In other words, the first plane is in space so as to intersect a tangential plane to the circumferential direction in a plane defined by the radial direction and the circumferential direction. If the normal vector has a vector component in the circumferential direction and in the radial direction (or in the axial and radial directions), the first plane has no curvature in the circumferential direction and can be made simpler by this simplified geometry or shaping.

Weiterbildend wird vorgeschlagen, dass das Leitschaufelsegment in Umfangsrichtung (UR) am äußeren Deckband zwei voneinander in einem Abstand angeordnete Deckbandseitenflächen aufweist, die derart ausgebildet sind, dass sie mit einer Deckbandseitenfläche eines benachbarten Leitschaufelsegments in Kontakt kommen können, wobei das Radialsicherungselement mit wenigstens einer Deckbandseitenfläche bündig ausgebildet ist.In a further development, it is proposed that the vane segment in the circumferential direction (UR) on the outer shroud has two shroud side surfaces arranged at a distance from one another, which are designed such that they can come into contact with a shroud side surface of an adjacent guide blade segment, wherein the radial securing element is flush with at least one shroud side surface is trained.

Dabei kann das Leitschaufelsegment in Umfangsrichtung zueinander in einem Abstand angeordnet zwei Radialsicherungselemente umfassen, so dass das Leitschaufelsegment an zwei Punkten definiert abgestützt wird und nicht aus der vorgesehenen Lage verrutschen kann, sich insbesondere nicht um eine radial verlaufende Achse verdrehen kann..In this case, the guide vane segment in the circumferential direction to each other at a distance arranged comprise two radial securing elements, so that the guide vane segment is supported defined at two points and can not slip out of the intended position, in particular can not rotate about a radially extending axis.

Hierzu wird vorgeschlagen, dass das eine Radialsicherungselement bündig mit der einen Deckbandseitenfläche ausgebildet ist, und dass das andere Radialsicherungselement zur anderen Deckbandseitenfläche mit einem Abstand angeordnet ist.For this purpose, it is proposed that the one radial securing element is formed flush with the one side of the shroud, and that the other radial securing element is arranged at a distance to the other shroud side surface.

Dabei ist es bevorzugt, dass der in Umfangsrichtung gemessene Abstand der beiden Radialsicherungselement kleiner ist als der in Umfangsrichtung gemessene Abstand der beiden Deckbandseitenflächen.It is preferred that the distance measured in the circumferential direction of the two radial securing element is smaller than the distance measured in the circumferential direction of the two shroud side surfaces.

Es wird weiter vorgeschlagen, dass das Radialsicherungselement durch Linearschleifen hergestellt ist. Linearschleifen ermöglicht das Bewegen eines entsprechenden Schleifwerkzeugs entlang einer Schleifhauptrichtung, und entlang einer hierzu orthogonalen Vorschubrichtung. Durch das lineare Schleifen kann aufgrund der Werkzeuggeometrie und des linearen Bewegungsvorgangs (Schleifhauptrichtung) in einfacher Weise eine Auflagefläche ausgebildet werden, deren Normalenvektor die oben genannten Merkmale aufweist.It is further proposed that the radial securing element is produced by linear grinding. Linear grinding enables the movement of a corresponding grinding tool along a main direction of the grinding, and along a feed direction orthogonal thereto. Due to the tool geometry and the linear movement process (grinding main direction), a bearing surface whose normal vector has the abovementioned features can be formed in a simple manner by the linear grinding.

Weiter wird vorgeschlagen, dass der Auflageabschnitt eine zweite Fläche aufweist, die in einer zweiten Ebene liegt, deren Normalenvektor Vektorkomponenten in Umfangrichtung und in Radialrichtung (RR), insbesondere auch in Axialrichtung (AR), aufweist.It is further proposed that the support section has a second surface which lies in a second plane whose normal vector has vector components in the circumferential direction and in the radial direction (RR), in particular also in the axial direction (AR).

Dabei ist es bevorzugt, dass die zweite Fläche und die Auflagefläche zueinander geneigt sind, wobei der von der ersten und der zweiten Ebene gebildete Winkel in einer Schnittebene, die durch die Radialrichtung (RR) und die Axialrichtung (AR) aufgespannt ist, in einem Bereich zwischen 70° und 90°, vorzugsweise 75° bis 85° liegt.In this case, it is preferable that the second surface and the support surface are inclined to each other, wherein the angle formed by the first and the second plane in a sectional plane which is spanned by the radial direction (RR) and the axial direction (AR), in an area between 70 ° and 90 °, preferably 75 ° to 85 °.

Das Leitschaufelsegment kann ferner in Umfangsrichtung in einem zentralen Bereich der hinteren Stirnwand ein Umfangssicherungselement umfassen.The vane segment may further comprise a circumferential securing element in the circumferential direction in a central region of the rear end wall.

Die der Erfindung zu Grunde liegende Aufgabe wird auch gelöst durch ein Verfahren zur Herstellung eines Leitschaufelsegments für eine Gasturbine, insbesondere Fluggasturbine, umfassend folgende Schritte:

  • Bereitstellen eines Roh-Leitschaufelsegments (10a) mit wenigstens einem radial äußeren Deckband (14) und einem radial inneren Deckband (12), die sich entlang eines jeweiligen Kreisbogens erstrecken und gemeinsam einen Ringabschnitt bilden, wobei in radialer Richtung (RR) zwischen dem äußeren Deckband (14) und dem inneren Deckband (12) mehrere Leitschaufeln (16) in Umfangsrichtung (UR) nebeneinander angeordnet sind, die mit dem inneren Deckband (12) und dem äußeren Deckband (14) materialschlüssig verbunden, insbesondere einstückig verbunden sind, wobei das äußere Deckband (14) in einer axialen Längsrichtung (AR) ein axial vorderes Stirnwandelement (22) und ein axial hinteres Stirnwandelement (24) umfasst, derart dass das äußere Deckband (14) und die beiden Stirnwände (22, 24) im Längsschnitt ein wannenartiges Profil bilden, und mit wenigstens einem Roh-Radialsicherungselement;
  • Ausrichten des Roh-Leitschaufelsegments relativ zu einer Linearschleifvorrichtung, derart dass mittels der Linearschleifvorrichtung Material des Roh-Radialsicherungselements abgetragen werden kann;
  • Abschleifen des Roh-Radialsicherungselements mittels der Linearschleifvorrichtung bis das Roh-Radialsicherungselement die Form eines Radialsicherungselements mit einem Auflageabschnitt angenommen hat, der eine Auflagefläche aufweist, die in einer ersten Ebene liegt, deren Normalenvektor Vektorkomponenten in Umfangrichtung und in Radialrichtung (RR), insbesondere auch in Axialrichtung (AR), aufweist.
The object underlying the invention is also achieved by a method for producing a guide blade segment for a gas turbine, in particular an aircraft gas turbine, comprising the following steps:
  • Providing a raw vane segment (10a) having at least one radially outer shroud (14) and a radially inner shroud (12) extending along a respective arc and forming together a ring portion, in the radial direction (RR) between the outer shroud (14) and the inner shroud (12) a plurality of guide vanes (16) in the circumferential direction (UR) are arranged side by side, which are materially connected to the inner shroud (12) and the outer shroud (14), in particular integrally connected, wherein the outer Shroud (14) in an axial longitudinal direction (AR) an axially front end wall element (22) and an axially rear end wall element (24), such that the outer shroud (14) and the two end walls (22, 24) in longitudinal section form a trough-like profile, and at least one raw radial fuse element;
  • Aligning the raw Leitschaufelsegments relative to a linear grinding device, such that by means of the linear grinding material of the Rohunialicherungselements can be removed;
  • Grinding the raw radial securing element by means of the linear grinding device until the raw radial securing element has taken the form of a radial securing element with a support section having a support surface lying in a first plane, the normal vector vector components in the circumferential direction and in the radial direction (RR), in particular also in FIG Axial direction (AR).

Dabei können der Schritt des Ausrichtens des Roh-Leitschaufelsegments und der Schritt des Abschleifens je einmal durchgeführt werden für ein jeweiliges Roh-Radialsicherungselement, wenn am Roh-Leitschaufelsegment zwei oder mehr Roh-Radialsicherungselemente vorgesehen sind.Incidentally, the step of aligning the blank vane segment and the step of abrading may be performed once for each raw radial-securing member when two or more raw radial securing members are provided on the blank vane segment.

Ferner wird vorgeschlagen, dass der Schritt des Ausrichtens des Roh-Leitschaufelsegments relativ zur Linearschleifvorrichtung derart ausgeführt wird, dass die Linearschleifvorrichtung beim Abschleifen des Roh-Radialsicherungselements mit einem Abstand zu anderen Komponenten des Roh-Leitschaufelsegments geführt bzw. bewegt werden kann, insbesondere mit einem Abstand zu einem in Umfangsrichtung in einem zentralen Bereich an der hinteren Stirnwand vorgesehen Umfangssicherungselement bzw. einem entsprechenden Roh-Umfangssicherungselement.Further, it is proposed that the step of aligning the blank vane segment relative to the linear sander is performed such that the linear sander can be moved or spaced apart from other components of the blank vane segment as the raw radial securing element is abraded, in particular at a distance to a circumferentially provided in a central region on the rear end wall circumferential securing element or a corresponding raw circumferential securing element.

Das Linearschleifen der Radialsicherungselemente kann für unterschiedliche Leitschaufelsegmente unterschiedlicher Turbinenstufen bzw. unterschiedlicher Gasturbinen angepasst werden, so dass durch entsprechende relative Ausrichtung von Leitschaufelsegment und Linearschleifwerkzeug die Auflagefläche des Radialsicherungselements hergestellt werden und kann dass die Linearschleifvorrichtung nicht in Kontakt mit anderen Komponenten bzw. Bauteilen, insbesondere Vorsprüngen und Verstärkungsrippen, des Leitschaufelsegments in Berührung kommt.The linear grinding of the radial securing elements can be adapted for different guide blade segments of different turbine stages or different gas turbines, so that the bearing surface of the radial securing element can be produced by appropriate relative orientation of the guide blade segment and the linear grinding tool and can the linear grinding device not be in contact with other components or components, in particular projections and reinforcing ribs of the vane segment comes into contact.

Schließlich betrifft die Erfindung auch eine Gasturbine, insbesondere Fluggasturbine umfassend wenigstens eine Turbinenstufe mit mehreren Leitschaufelsegmenten, die in Umfangsrichtung nebeneinander angeordnet, so dass sie einen Leitschaufelring der Turbinenstufe bilden, wobei die Leitschaufelsegmente wenigstens eines der oben beschriebenen Merkmale aufweisen.Finally, the invention also relates to a gas turbine, in particular an aircraft gas turbine comprising at least one turbine stage with a plurality of vane segments arranged side by side in the circumferential direction, so that they form a turbine blade vane ring, wherein the vane segments have at least one of the features described above.

Das erfindungsgemäße Leitschaufelsegment ist in Anspruch 1 definiert. Das erfindungsgemäße Verfahren zur Herstellung eines Leitschaufelsegments ist in Anspruch 12 definiert. Die erfindungsgemäße Gasturbine ist in Anspruch 15 definiert.The vane segment according to the invention is defined in claim 1. The inventive method for producing a vane segment is defined in claim 12. The gas turbine according to the invention is defined in claim 15.

Nachfolgend wird die Erfindung unter Bezugnahme auf die anliegenden Figuren beispielhaft und nicht einschränkend beschrieben.

  • Fig. 1 zeigt in einer vereinfachten perspektivischen Darstellung ein Leitschaufelsegment.
  • Fig. 2 zeigt eine stark vereinfachte Längsschnittdarstellung eines Übergangsbereichs zwischen Leitschaufelsegment und Turbinengehäuse.
  • Fig. 3 zeigt eine Vergrößerung des in Figur 2 gestrichelt umrandeten Bereichs III mit einem Radialsicherungselement und einem gehäuseseitigen Gegenstück.
  • Fig. 4 zeigt in einer vereinfachten perspektivischen Darstellung ein Roh-Leitschaufelsegment.
  • Fig. 5 zeigt in einer vereinfachten perspektivischen Prinzipdarstellung eine Linearschleifvorrichtung in relativer Positionierung zum Leitschaufelsegment.
  • Fig. 6 zeigt in einer anderen vereinfachten perspektivischen Prinzipdarstellung die Linearschleifvorrichtung in relativer Positionierung zum Leitschaufelsegment.
  • Fig. 7 zeigt eine vergrößerte Teilschnittdarstellung etwa entlang der Schnittlinie VII-VII der Fig. 6.
  • Fig. 8 zeigt in den Teilfiguren A) und B) in schematischen und vereinfachten Prinzipdarstellungen die Neigung einer Auflagefläche eines Radialsicherungselements.
The invention will be described below by way of example and not limitation with reference to the attached figures.
  • Fig. 1 shows in a simplified perspective view of a vane segment.
  • Fig. 2 shows a highly simplified longitudinal sectional view of a transition region between the vane segment and turbine housing.
  • Fig. 3 shows an enlargement of the in FIG. 2 dashed rimmed area III with a radial securing element and a housing-side counterpart.
  • Fig. 4 shows in a simplified perspective view of a raw vane segment.
  • Fig. 5 shows in a simplified perspective schematic representation of a linear grinding device in relative positioning to the vane segment.
  • Fig. 6 shows in another simplified perspective schematic representation of the linear grinding device in relative positioning to the vane segment.
  • Fig. 7 shows an enlarged partial sectional view approximately along the section line VII-VII of Fig. 6 ,
  • Fig. 8 shows in the sub-figures A) and B) in schematic and simplified schematic diagrams of the inclination of a bearing surface of a radial securing element.

Fig. 1 zeigt in einer vereinfachten perspektivischen Darstellung ein Leitschaufelsegment 10 mit einem radial inneren Deckband 12 und einem radial äußeren Deckband 14. In Radialrichtung RR erstrecken sich zwischen dem inneren Deckband 12 und dem äußeren Deckband 14 Leitschaufeln 16, wobei die hier dargestellte Anzahl von drei Leitschaufeln 16 für ein Leitschaufelsegment 10 rein beispielhaft ist; es können auch zwei, vier, fünf oder mehr Leitschaufeln in einem Leitschaufelsegment 10 vorgesehen sein. Fig. 1 shows in a simplified perspective view of a vane segment 10 with a radially inner shroud 12 and a radially outer shroud 14 in the radial direction RR extending between the inner shroud 12 and the outer shroud 14 vanes 16, wherein the number of three vanes 16 shown here for a vane segment 10 is purely exemplary; it is also possible for two, four, five or more vanes to be provided in a vane segment 10.

Das Leitschaufelsegment 10 der Fig. 1 ist so dargestellt, dass der Blick auf die Saugseiten 18 und die Hinterkanten 20 der Leitschaufeln 16 freigegeben ist. Das radial äußere Deckband 14 umfasst eine axial vordere Stirnwand 22 und eine axial hintere Stirnwand 24. Die beiden Stirnwände 22, 24 sind zum Deckband 14 geneigt ausgeführt, so dass sich in einem Längsschnitt ein wannenartige Profil ergibt. In der Fig. 1 ist ferner ein Radialsicherungselement 26 ersichtlich, das an der hinteren Stirnwand 24 ausgebildet ist und von dieser entgegen der Axialrichtung AR bzw. gegen die Hauptströmungsrichtung in der Strömungsmaschine vorsteht.
Fig. 2 zeigt eine vereinfachte Längsschnittdarstellung durch das äußere Deckband 14 und einen Teil eines mit dem Leitschaufelsegment 10 verbundenen Turbinengehäuses 28. Ebenfalls ersichtlich sind aus der Fig. 2 die vordere Stirnwand 22 und die hintere Stirnwand 24, die zusammen mit dem Deckband 14 das wannenartige Profil in der Schnittdarstellung bilden. An der hinteren Stirnwand 24 ist das Radialsicherungselement 26 ersichtlich, das als Vorsprung ausgebildet ist und entgegen der axialen Richtung AR von der hinteren Stirnwand 24 vorsteht. Das Radialsicherungselement 26 weist einen im Schnitt im Wesentlichen S-förmigen Auflageabschnitt 27 auf mit einem konvexen und einem konkaven Bogen, an die gerade Stücke bzw. Flächen angrenzen. Am Gehäuse 28 ist ein zum Radialsicherungselement 26 komplementär ausgebildetes Gegenstück 30 ausgebildet, so dass zwischen dem Radialsicherungselement 26 und dem Gegenstück 30 eine Anlage ermöglicht wird zur radialen Sicherung des Leitschaufelsegments 26 am Gehäuse 30.The vane segment 10 of Fig. 1 is shown so that the view of the suction sides 18 and the trailing edges 20 of the guide vanes 16 is released. The radially outer shroud 14 comprises an axially front end wall 22 and an axially rear end wall 24. The two end walls 22, 24 are designed inclined to the shroud 14 so that there is a trough-like profile in a longitudinal section. In the Fig. 1 Furthermore, a radial securing element 26 can be seen, which is formed on the rear end wall 24 and protrudes therefrom against the axial direction AR or against the main flow direction in the turbomachine.
Fig. 2 shows a simplified longitudinal sectional view through the outer shroud 14 and a portion of a turbine housing connected to the nozzle segment 10 turbine housing 28. Also can be seen from the Fig. 2 the front end wall 22 and the rear end wall 24, which together with the shroud 14 form the trough-like profile in the sectional view. At the rear end wall 24, the radial securing element 26 can be seen, which is designed as a projection and projecting against the axial direction AR of the rear end wall 24. The radial securing element 26 has an essentially S-shaped support section 27 with a convex and a concave arc, against which straight pieces or surfaces adjoin. On the housing 28 a complementary to the radial securing element 26 formed counterpart 30 is formed so that between the radial securing element 26 and the counterpart 30 a system is made possible for radial securing of the vane segment 26 on the housing 30th

Fig. 3 zeigt den in Fig. 2 gestrichelt umrandeten Bereich III, so dass hieraus das Radialsicherungselement 26 mit seinem Auflageabschnitt 27 und das Gegenstück 30 des Turbinengehäuses 28 besser ersichtlich sind. Das Radialsicherungselement 26 umfasst an seinem Auflageabschnitt 27 eine Auflagefläche 32 und eine zweite Fläche 34. Das Gegenstück 30 weist eine Anlagefläche 36 auf, die der Auflagefläche 32 des Radialsicherungselements 26 gegenüber liegt. Wie aus der Schnittdarstellung ersichtlich, sind die Auflagefläche 32 und die zweite Fläche 34 geneigt zueinander ausgebildet, wobei sie in der Zeichnungsebene (Ebene, die durch die Axialrichtung AR und die Radialrichtung RR aufgespannt wird) einen Winkel β einschließen, der vorzugsweise etwa 70° bis 90°, insbesondere etwa 75° bis 85° beträgt. Die Anlagefläche 36 am Gegenstück 30 des Gehäuses 28 weist im Wesentlichen die gleiche Neigung auf, wie die Auflagefläche 32. Das Zusammenwirken zwischen der Anlagefläche 32 und der Anlagefläche 36 ermöglich die Sicherung des Leitschaufelsegments 10 in radialer Richtung RR. Fig. 3 shows the in Fig. 2 dashed rimmed area III, so that from this the radial securing element 26 with its support portion 27 and the counterpart 30 of the turbine housing 28 are better visible. The radial securing element 26 comprises at its support portion 27 a support surface 32 and a second surface 34. The counterpart 30 has a contact surface 36 which faces the support surface 32 of the radial securing element 26 lies. As seen from the sectional view, the support surface 32 and the second surface 34 are formed inclined to each other, and in the plane of the drawing (plane, which is spanned by the axial direction AR and the radial direction RR) include an angle β, preferably about 70 ° 90 °, in particular about 75 ° to 85 °. The contact surface 36 on the counterpart 30 of the housing 28 has substantially the same inclination, as the support surface 32. The interaction between the contact surface 32 and the abutment surface 36 allows the securing of the vane segment 10 in the radial direction RR.

Fig. 4 ist eine vereinfachte perspektivische Darstellung eines Roh-Leitschaufelsegments 10a nach dem Gießen eines solchen Werkstücks. Es sind die bereits erwähnten Komponenten ersichtlich: äußeres Deckband 14, vordere Stirnwand 22, hintere Stirnwand 24, sowie die Leitschaufeln 16. An der hinteren Stirnwand 24 sind zwei Roh-Radialsicherungselemente 26a und 26b ersichtlich, die als eine Art dreickiger Vorsprung entgegen der Axialrichtung AR von der hinteren Stirnwand 24 abstehen. In einem in Umfangsrichtung UR zentralen Bereich der hinteren Stirnwand 24 ist ein aus zwei Rippen gebildetes Umfangssicherungselement 40 ersichtlich, das ebenfalls noch in seiner Rohform nach dem Gießen vorliegt. Fig. 4 Figure 3 is a simplified perspective view of a blank vane segment 10a after casting such a workpiece. The above-mentioned components can be seen: outer shroud 14, front end wall 22, rear end wall 24, and the guide vanes 16. At the rear end wall 24, two raw radial securing elements 26a and 26b can be seen, which act as a kind of thickened projection against the axial direction AR protrude from the rear end wall 24. In an area of the rear end wall 24 that is central in the circumferential direction UR, a circumferential securing element 40 formed from two ribs can be seen, which is also still in its raw form after casting.

Um aus den Roh-Radialsicherungselementen 26a und 26b die fertig geformten Radialsicherungselemente 26 zu bilden, wie sie unter Bezugnahme auf die Fig. 1 bis 3 bisher beschrieben worden sind, wird an den Roh-Radialsicherungselementen 26a, 26b Material abgetragen, wobei dies durch lineares Schleifen erfolgt. Hierzu zeigen die Fig. 5 und 6 beispielhaft das (Roh-)Leitschaufelsegment 10 (10a) und eine vereinfacht und schematisch dargestellte Linearschleifvorrichtung 42 in unterschiedlichen Perspektiven und relativen Anordnungen zueinander. Die Linearschleifvorrichtung 42 und das Leitschaufelsegment 10 werden so zueinander ausgerichtet, dass die Linearschleifvorrichtung 42 mit ihren Schleifflächen 44 in Kontakt mit einem der Roh-Radialsicherungselemente 26a, 26b kommt. Der lineare Schleifvorgang wird solange durchgeführt, bis das Radialsicherungselement 26 bzw. dessen Auflageabschnitt 27 seine endgültige Form erreicht hat, insbesondere die Auflagefläche 32 und die zweite Fläche 34 ausgebildet sind. Ausgehend von dem Roh-Leitschaufelsegment 10a der Fig. 4 zeigt die Fig. 5 eine Darstellung, bei der die Linearschleifvorrichtung 42 das Roh-Radialsicherungselemente 26b bearbeitet, und in Fig. 6 eine Darstellung, bei der die Linearschleifvorrichtung 42 das Roh-Radialsicherungselement 26a bearbeitet. Vom jeweils anderen Roh-Radialsicherungselement 26a bzw. 26b, das auch schon als fertig bearbeitetes Radialsicherungselement 26 vorliegen kann, ist in Fig. 5 bzw. Fig. 6 jeweils nur ein oberer Abschnitt erkennbar.To form the finished molded radial securing elements 26 from the raw radial securing elements 26a and 26b as described with reference to FIGS Fig. 1 to 3 heretofore described, material is removed from the raw radial securing elements 26a, 26b, this being done by linear grinding. To show the FIGS. 5 and 6 For example, the (raw) vane segment 10 (10a) and a simplified and schematically illustrated linear grinding device 42 in different perspectives and relative arrangements to each other. The linear grinder 42 and the vane segment 10 are aligned with each other so that the linear grinder 42 with its grinding surfaces 44 comes into contact with one of the raw radial securing elements 26a, 26b. The linear grinding process is carried out until the radial securing element 26 or its support section 27 has reached its final shape, in particular the support surface 32 and the second surface 34 are formed. Starting from the raw vane segment 10a of Fig. 4 show the Fig. 5 a view in which the linear grinding device 42, the raw radial securing elements 26 b processed, and in Fig. 6 a representation in which the linear grinding device 42, the raw radial securing element 26 a processed. From each other Raw radial securing element 26a or 26b, which may already be present as a finished radial securing element 26, is in Fig. 5 respectively. Fig. 6 only one upper section visible.

Wie aus der Zusammenschau der Fig. 4 bis 6 ersichtlich ist, weist das Leitschaufelsegment 10 im Bereich des äußeren Deckbandes 14 jeweilige Deckbandseitenflächen 46 auf, die dazu eingerichtet sind, dass benachbarte Leitschaufelsegmente 10 aneinander anliegen können im montierten Zustand in der Gasturbine. Das Leitschaufelsegment 10 weist jeweils zwei Deckbandseitenflächen 46 auf, wobei jeder Deckbandseitenfläche 46 ein Radialsicherungselement 26 zugeordnet sein kann. Dabei kann das betreffende Radialsicherungselement 26 mit der Deckbandseitenfläche 46 bündig ausgeführt sein, wie dies beispielshaft aus der Fig. 5 oder auch der Fig. 1 ersichtlich ist. Alternativ kann das Radialsicherungselement 26 zur Deckbandseitenfläche 46 in einem Abstand AB angeordnet sein, wie dies am besten aus der Fig. 4 ersichtlich ist, aber auch in der Fig. 6 angedeutet ist bei dem in der Fig. 6 linken Radialsicherungselement 26 (26a), das in Kontakt mit der Linearschleifvorrichtung 42 dargestellt ist.As from the synopsis of 4 to 6 it can be seen, the guide vane segment 10 in the region of the outer shroud 14 respective shroud side surfaces 46 which are adapted to that adjacent vane segments 10 may abut each other in the mounted state in the gas turbine. The vane segment 10 in each case has two shroud side surfaces 46, wherein each shroud side surface 46 may be assigned a radial securing element 26. In this case, the respective radial securing element 26 may be flush with the shroud side surface 46, as exemplified by the Fig. 5 or even the Fig. 1 is apparent. Alternatively, the radial securing element 26 may be disposed to the shroud side surface 46 at a distance AB, as best shown in FIG Fig. 4 is apparent, but also in the Fig. 6 is indicated in the in the Fig. 6 left radial securing element 26 (26 a), which is shown in contact with the linear grinding device 42.

Wie aus den Fig. 5 und 6 ersichtlich ist, wird die Linearschleifvorrichtung im Kontaktbereich mit dem Radialsicherungselement 26 nicht tangential zu der in diesem Kontaktbereich ausgebildeten Krümmung (entlang der Umfangsrichtung UR) des Deckbandes 14 bzw. der hinteren Stirnwand 24 geführt. Vielmehr wird zwischen einer die Schleifrichtung repräsentierenden Längsachse LAS der Linearschleifvorrichtung 42 und der Tangentialrichtung TR im Bereich des Radialsicherungselements 26 ein Winkel γ gebildet. Dies führt dazu, dass die mittels der Linearschleifvorrichtung 42 ausgebildete Auflagefläche 32 oder/und die Fläche 34 Normalenvektoren aufweisen, der neben wenigstens einer Vektorkomponente in Axialrichtung AR oder/und Radialrichtung RR auch eine Vektorkomponente in Umfangsrichtung UR aufweisen. Eine derartige relative Positionierung von Linearschleifvorrichtung 42 und Leitschaufelsegment 10 zueinander ermöglicht das Abtragen von Material an den Radialsicherungselementen 26, ohne dass die Linearschleifvorrichtung mit anderen Komponenten bzw. Bauteilen des Leitschaufelsegments 10 in Kontakt kommt, insbesondere nicht mit dem Umfangssicherungselement 40, das ebenfalls entlang der Umfangsrichtung UR an der hinteren Stirnwand 24 vorgesehen ist und entgegen der axialen Richtung AR von dieser vorsteht.Like from the FIGS. 5 and 6 it can be seen, the linear grinding device in the contact region with the radial securing element 26 is not guided tangentially to the curvature formed in this contact region (along the circumferential direction UR) of the shroud 14 or the rear end wall 24. Rather, an angle γ is formed between a longitudinal axis LAS representing the grinding direction of the linear grinding device 42 and the tangential direction TR in the region of the radial securing element 26. As a result, the support surface 32 or / and the surface 34 formed by means of the linear grinding device 42 have normal vectors which, in addition to at least one vector component in the axial direction AR and / or radial direction RR, also have a vector component in the circumferential direction UR. Such relative positioning of linear grinder 42 and vane segment 10 relative to one another enables material to be removed from the radial securing elements 26 without the linear grinding device coming into contact with other components of the vane segment 10, particularly with the circumferential securing element 40 also along the circumferential direction UR is provided on the rear end wall 24 and protrudes counter to the axial direction AR thereof.

Fig. 7 zeigt eine vereinfachte schematische Schnittdarstellung etwa entlang der Schnittlinie VII-VII der Fig. 6. Aus dieser Darstellung ist ersichtlich, dass die Linearschleifvorrichtung 42 im Bereich ihrer Schleifflächen 44 so ausgestaltet ist, dass sie eine zum Radialsicherungselement 26 bzw. dessen Auflageabschnitt 27 komplementäre Kontur aufweist. Durch diese komplementäre Schleifkontur ist es möglich, dass mittels linearer Relativbewegung der Linearschleifvorrichtung 42 entlang der Längsachse LAS der Linearschleifvorrichtung ein sukzessiver Materialabtrag an einem Roh-Radialsicherungselement 26a, 26b (Fig. 4) erfolgt bis das fertige Radialsicherungselement 26 ausgebildet ist. Somit kann auf ein verglichen mit dem Linearschleifen eher aufwändiges Fräsen des bzw. der Radialsicherungselemente(s) 26 verzichtet werden. Fig. 7 shows a simplified schematic sectional view approximately along the section line VII-VII of Fig. 6 , From this representation, it can be seen that the linear grinding device 42 is designed in the region of its grinding surfaces 44 in such a way that it has a contour complementary to the radial securing element 26 or its bearing section 27. By means of this complementary grinding contour, it is possible that, by means of linear relative movement of the linear grinding device 42 along the longitudinal axis LAS of the linear grinding device, a successive material removal on a raw radial securing element 26a, 26b (FIG. Fig. 4 ) takes place until the finished radial securing element 26 is formed. Thus, a rather complex milling of the radial securing element (s) 26 can be dispensed with compared to the linear grinding.

Fig. 8 zeigt in den Teilfiguren A) und B) zwei stark vereinfachte prinzipielle Schnittdarstellungen der Auflagefläche 32 des Radialsicherungselements 26, um die Vektorkomponenten des Normalenvektors zu illustrieren. Fig. 8A) ist ein Längsschnitt, wie er auch aus der Fig. 1 ersichtlich ist, wobei lediglich die Auflagefläche 32 als Linie dargestellt ist mit dem Normalenvektor NV, und den Vektorkomponenten VRR und VAR in radialer bzw. axialer Richtung. Fig. 8B) ist ein Schnitt entsprechend der Linie VIII-VIII der Fig. 3, wobei die Auflagefläche 32 als Linie und ein Teil des geschnittenen Radialsicherungselements 26 schraffiert dargestellt ist. Auch in Fig 8B) ist für die Auflagefläche 32 der Normalenvektor NV mit den in dieser Darstellung ersichtlichen Vektorkomponenten VRR und VUR in Radialrichtung bzw. Umfangsrichtung gezeigt. Fig. 8 shows in the sub-figures A) and B) two highly simplified schematic sectional views of the support surface 32 of the radial securing element 26 to illustrate the vector components of the normal vector. Fig. 8A ) is a longitudinal section, as he also from the Fig. 1 it can be seen, wherein only the support surface 32 is shown as a line with the normal vector NV, and the vector components VRR and VAR in the radial or axial direction. Fig. 8B ) is a section corresponding to the line VIII-VIII of Fig. 3 , wherein the bearing surface 32 is shown hatched as a line and a portion of the cut radial securing element 26. Also in Fig. 8B ), the normal vector NV with the vector components VRR and VUR in the radial direction or circumferential direction, which are shown in this illustration, is shown for the bearing surface 32.

Wenn die Auflagefläche 32 des Radialsicherungselements 26 in der beschriebenen Art geneigt ist, wobei deren Normalenvektor eine Vektorkomponente VUR in Umfangsrichtung aufweist, kann dies dazu führen, dass die Auflagefläche 32 nicht flächig in Kontakt kommt mit der Anlagefläche 36 des Gegenstücks 30, sondern dass nur eine Berührung zwischen diesen beiden Auflageflächen 32, 36 entlang einer Linie vorliegt. Eine nicht vollflächige Anlage von Radialsicherungselement 26 und Gegenstück 30 wird allerdings nicht als nachteilig erachtet, weil über die Radialsicherungselemente 26 im Stillstand einer Gasturbine keine großen Kräfte abzustützen sind, wobei im Betrieb derselben in der Regel gar keine Kräfte über die Radialsicherungselemente 26 abgestützt werden. Die Radialsicherungselemente sollen daher kostengünstig hergestellt werden können, was mittels des Linearschleifens ermöglicht ist, und eine Sicherung gegen Herausfallen in radialer Richtung bieten, insbesondere bei der Montage/Demontage von Leitschaufelsegmenten einer Turbinenstufe einer Gasturbine.If the bearing surface 32 of the radial securing element 26 is inclined in the manner described, with its normal vector having a vector component VUR in the circumferential direction, this can lead to the bearing surface 32 not coming into contact with the abutment surface 36 of the counterpart 30, but only one There is contact between these two bearing surfaces 32, 36 along a line. However, not a full-surface system of radial securing element 26 and counterpart 30 is not considered disadvantageous, because no large forces are to support on the radial securing elements 26 at standstill of a gas turbine, in the operation of the same usually no forces on the radial securing elements 26 are supported. The radial securing elements should therefore be able to be produced inexpensively, which makes possible by means of linear grinding is, and provide a safeguard against falling out in the radial direction, in particular in the assembly / disassembly of stator segments of a turbine stage of a gas turbine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

1010
Leitschaufelsegmentvane segment
10a10a
Roh-LeitschaufelsegmentRaw vane segment
1212
inneres Deckbandinner shroud
1414
äußeres Deckbandouter shroud
1616
Leitschaufelvane
1818
Saugseitesuction
2020
Hinterkantetrailing edge
2222
vordere Stirnwandfront end wall
2424
hintere Stirnwandrear end wall
2626
RadialsicherungselementRadial fuse element
26a26a
Roh-RadialsicherungselementCrude radial securing element
26b26b
Roh-RadialsicherungselementCrude radial securing element
2727
Auflageabschnittbearing section
2828
Gehäusecasing
3030
Gegenstückcounterpart
3232
Auflageflächebearing surface
3434
Flächearea
3636
Anlageflächecontact surface
4040
UmfangssicherungselementPerimeter security element
4242
LinearschleifvorrichtungLinear grinding device
4444
Schleifflächegrinding surface
4646
DeckbandseitenflächeShroud side face
ABFROM
Abstanddistance
ARAR
axiale Richtungaxial direction
LASREAD
Längsachse (Linearschleifvorrichtung 42)Longitudinal axis (linear grinding device 42)
NVNV
Normalenvektornormal vector
RRRR
radiale Richtungradial direction
TRTR
Tangentialrichtungtangential
URUR
Umfangsrichtungcircumferentially
VARVAR
Vektorkomponente in AxialrichtungVector component in the axial direction
VRRVRR
Vektorkomponente in RadialrichtungVector component in the radial direction
VURVUR
Vektorkomponente in UmfangsrichtungVector component in the circumferential direction

Claims (15)

  1. Guide vane segment (10) for a gas turbine, in particular an aircraft gas turbine, comprising
    at least one radially outer shroud (14) and one radially inner shroud (12), which extend along a particular circular arc and together form a ring portion,
    a plurality of guide vanes (16) being arranged, in the radial direction (RR) between the outer shroud (14) and the inner shroud (12), side by side in the circumferential direction (UR), which guide vanes are integrally joined, in particular as one part, with the inner shroud (12) and the outer shroud (14),
    the outer shroud (14) comprising an axially front end-wall element (22) and an axially rear end-wall element (24) in an axial longitudinal direction (AR) such that the outer shroud (14) and the two end walls (22, 24) form a trough-like profile in longitudinal cross section,
    at least one radial securing element (26) being provided on the axially rear end wall (24), which securing element is designed to secure the guide vane segment (10) in the radial direction (RR) relative to a surrounding housing (28, 30),
    the radial securing element (26) being in the form of a projection comprising a support portion (27) which is designed to be supported on a corresponding counter member (30) on the housing (28),
    characterized in that
    the support portion (27) has a support surface (32) which lies in a plane of which the normal vector has a vector component (VUR) in the circumferential direction (UR) and in the radial direction (RR).
  2. Guide vane segment according to claim 1, characterized in that the support portion (27) has a support surface (32) which lies in a plane of which the normal vector has a vector component (VAR) in the axial direction (AR).
  3. Guide vane segment according to either claim 1 or claim 2, characterized in that it has, in the circumferential direction (UR) on the outer shroud (14), two shroud side surfaces (46) which are arranged at a distance from each other and are designed to be able to come into contact with a shroud side surface of an adjacent guide vane segment, the radial securing element (26) being flush with at least one shroud side surface (46).
  4. Guide vane segment according to claim 3, characterized in that it comprises two radial securing elements (26) arranged at a distance from each other in the circumferential direction.
  5. Guide vane segment according to claim 4, characterized in that one radial securing element (26) is flush with one of the shroud side surfaces (46) and in that the other radial securing element (26) is arranged at a distance (AB) from the other shroud side surface (46).
  6. Guide vane segment according to either claim 4 or claim 5, characterized in that the distance, measured in the circumferential direction, between the two radial securing elements (26) is smaller than the distance, measured in the circumferential direction, between the two shroud side surfaces (46).
  7. Guide vane segment according to any of the preceding claims, characterized in that the radial securing element (26) is produced by linear grinding.
  8. Guide vane segment according to any of the preceding claims, characterized in that the support portion (27) has a second surface (34) which lies in a second plane of which the normal vector has vector components in the circumferential direction and in the radial direction (RR).
  9. Guide vane segment according to claim 8, characterized in that the normal vector of the second plane has vector components in the axial direction (AR).
  10. Guide vane segment according to either claim 8 or claim 9, characterized in that the second surface (34) and the support surface (32) are inclined towards each other, the angle (β) formed by the first and the second plane, in a cutting plane which is spanned by the radial direction (RR) and the axial direction (AR), being in a range of between 70° and 90°, preferably 75° and 85°.
  11. Guide vane segment according to any of the preceding claims, characterized in that it comprises a circumferential securing element (40) in the circumferential direction (UR) in a central region of the rear end wall (24).
  12. Method for producing a guide vane segment (10) for a gas turbine, in particular an aircraft gas turbine, comprising the following steps:
    providing a blank guide vane segment (10a) comprising at least one radially outer shroud (14) and one radially inner shroud (12), which extend along a particular circular arc and together form a ring portion, a plurality of guide vanes (16) being arranged, in the radial direction (RR) between the outer shroud (14) and the inner shroud (12), side by side in the circumferential direction (UR), which guide vanes are integrally joined, in particular as one part, with the inner shroud (12) and the outer shroud (14), the outer shroud (14) comprising an axially front end-wall element (22) and an axially rear end-wall element (24) in an axial longitudinal direction (AR) such that the outer shroud (14) and the two end walls (22, 24) form a trough-like profile in longitudinal cross section, and comprising at least one blank radial securing element (26a, 26b);
    orienting the blank guide vane segment relative to a linear grinding apparatus (42) such that material of the blank radial securing element (26a, 26b) can be removed by means of the linear grinding apparatus (42);
    grinding off the blank radial securing element (26a, 26b) by means of the linear grinding apparatus (42) until the blank radial securing element (26a, 26b) has assumed the shape of a radial securing element (26) comprising a support portion (27) having a support surface (32) which lies in a first plane of which the normal vector has vector components in the circumferential direction and in the radial direction (RR), in particular also in the axial direction (AR).
  13. Method according to claim 12, wherein the step of orienting the blank guide vane segment (26a, 26b) and the step of grinding off are carried out once per blank radial securing element (26a, 26b) if two or more blank radial securing elements (26a, 26b) are provided on the blank guide vane segment (10a).
  14. Method according to either claim 12 or claim 13, wherein the step of orienting the blank guide vane segment (10a) relative to the linear grinding apparatus (42) is carried out such that the linear grinding apparatus (42) can be guided or moved, during the grinding of the blank radial securing element (26a, 26b), at a distance from the other components of the blank guide vane segment (10a), in particular at a distance from a circumferential securing element (40) provided on the rear end wall (24) in a central region in the circumferential direction (UR) or at a distance from a corresponding blank circumferential securing element.
  15. Gas turbine, in particular aircraft gas turbine, comprising at least one turbine stage having a plurality of guide vane segments (10) according to any of claims 1 to 11, which vane segments are arranged side by side in the circumferential direction such that they form a guide vane ring of the turbine stage.
EP16201368.4A 2015-12-04 2016-11-30 Guide blade segment with radial securing Active EP3176388B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015224378.8A DE102015224378A1 (en) 2015-12-04 2015-12-04 Guide vane segment with radial lock

Publications (2)

Publication Number Publication Date
EP3176388A1 EP3176388A1 (en) 2017-06-07
EP3176388B1 true EP3176388B1 (en) 2018-11-14

Family

ID=57471672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16201368.4A Active EP3176388B1 (en) 2015-12-04 2016-11-30 Guide blade segment with radial securing

Country Status (4)

Country Link
US (1) US10370989B2 (en)
EP (1) EP3176388B1 (en)
DE (1) DE102015224378A1 (en)
ES (1) ES2700953T3 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016202519A1 (en) * 2016-02-18 2017-08-24 MTU Aero Engines AG Guide vane segment for a turbomachine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6893217B2 (en) * 2002-12-20 2005-05-17 General Electric Company Methods and apparatus for assembling gas turbine nozzles
EP1508668B1 (en) * 2003-07-23 2006-12-20 Alstom Technology Ltd Method of reconditioning and method of fabricating a turbine blade
EP2615243B1 (en) 2012-01-11 2017-08-30 MTU Aero Engines AG Blade ring segment for a fluid flow engine and method for producing the same
FR2990719B1 (en) * 2012-05-16 2016-07-22 Snecma TURBOMACHINE DISPENSER AND METHOD OF MANUFACTURE
JP5962915B2 (en) * 2012-10-29 2016-08-03 株式会社Ihi Turbine nozzle fixing part structure and turbine using the same
EP2811118B1 (en) * 2013-06-06 2018-03-14 MTU Aero Engines GmbH Guide blade segment of a turboengine and turbine
US9835038B2 (en) * 2013-08-07 2017-12-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
DE102013224199A1 (en) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gas turbine blade
GB201417150D0 (en) * 2014-09-29 2014-11-12 Rolls Royce Plc Carriers for turbine components

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US20170159466A1 (en) 2017-06-08
DE102015224378A1 (en) 2017-06-08
EP3176388A1 (en) 2017-06-07
ES2700953T3 (en) 2019-02-20
US10370989B2 (en) 2019-08-06

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