EP2268902B1 - Strut for an intermediate turbine housing and intermediate turbine housing - Google Patents

Strut for an intermediate turbine housing and intermediate turbine housing Download PDF

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Publication number
EP2268902B1
EP2268902B1 EP09733098.9A EP09733098A EP2268902B1 EP 2268902 B1 EP2268902 B1 EP 2268902B1 EP 09733098 A EP09733098 A EP 09733098A EP 2268902 B1 EP2268902 B1 EP 2268902B1
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EP
European Patent Office
Prior art keywords
strut
flange
turbine
housing
centre frame
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Not-in-force
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EP09733098.9A
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German (de)
French (fr)
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EP2268902A1 (en
Inventor
Alexander Böck
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP2268902A1 publication Critical patent/EP2268902A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention relates to a strut for a turbine intermediate housing of a turbomachine having a first end for placement on an inner structure of the turbine intermediate housing and a first end opposite the first end for attaching the strut to a housing or an inner boundary wall of the turbine intermediate housing, according to the preamble of patent claim 1
  • the invention further relates to a turbine intermediate housing for a turbomachine, in particular a gas turbine.
  • Turbine intermediate housings are arranged in turbomachines, in particular in an aircraft engine turbine, between the high-pressure turbine and the low-pressure turbine.
  • the Turbine Center Frame (TCF) is a structural member and has the function of forming a flow channel between the high pressure turbine and the low pressure turbine and structurally connecting the bearing chamber of at least the high pressure rotor to the housing.
  • the turbine intermediate housing serves to distribute cooling air flows for the low-pressure turbine.
  • profiled struts which hold a bearing chamber for the turbine rotor, cross the gas channel. Therefore, these struts are clad with vane-like components. It has proved to be cost-effective to cast integrally the struts together with the storage chamber or the inner structure of the turbine intermediate.
  • the strut cladding must be mountable radially from the outside over the struts.
  • the free strut ends are mounted to a housing or an inner boundary wall of the turbine intermediate housing, they usually have a thickening or a flange in this area, which defines the width of the strut covering in this type of mounting.
  • Strut coverings are used, which are designed according to wide and not optimized flow. However, this reduces the efficiency of the gas turbine, since relatively high flow losses occur.
  • other known turbine intermediate housings on a one-piece design of the struts with the internal structure that is, for example, an integrally molded bearing star dispensed.
  • a generic strut for a turbine intermediate housing of a turbomachine in particular for a gas turbine, comprises a first end for placement on an inner structure of the turbine intermediate housing and a first end opposite the first end second end for attachment of the strut to a housing or an inner boundary wall of the turbine intermediate housing, wherein at the second end at least one flange-like element with at least one first opening for receiving or passing through a fastening means is detachably arranged.
  • the strut according to the invention is used as part of an integrally cast bearing star whose production is inexpensive to implement.
  • the strut in the region of the second end has at least one groove or recess into which a corresponding projection of the flange-like element can engage.
  • the strut has at least one additional peripheral or non-circumferential flange at the second end.
  • the flange Through the flange, it increases the bearing surface between the strut or the second end of the strut and the housing to be connected therewith or to be connected to the inner boundary wall of the turbine intermediate housing.
  • the flange-like element attaches to the flange of the strut.
  • the strut has at least one second opening for receiving or passing through a fastening means at the second end.
  • the at least one second opening is formed in the at least one flange. The formation of a second opening results in a firm and intimate connection between these elements after the attachment of the strut to the housing or the inner boundary wall of the turbine intermediate housing. It is also conceivable that this connection is made not only with two fasteners, but with even more fasteners.
  • the fastener is a screw.
  • corresponding openings for receiving a clamping pin are formed in the flange at the second end of the strut and the flange-like element.
  • the dowel pin advantageously serves to hold the flange-like element on the strut during attachment, in particular screwing to the housing or the inner boundary wall of the turbine intermediate housing.
  • the strut is formed integrally with the inner structure of the turbine intermediate housing.
  • the strut is at least partially surrounded by a strut cladding, wherein the strut cladding is designed to optimize flow.
  • the strut cladding may consist of a heat-resistant material.
  • a turbine intermediate housing according to the invention for a turbomachine in particular a gas turbine, comprises a plurality of struts arranged radially on an inner structure for connection to a housing or an inner boundary wall of the turbine intermediate housing, wherein the struts are formed as described above.
  • the turbomachine can be a gas turbine of an aircraft engine.
  • the turbine intermediate housing according to the invention has a higher efficiency compared to known turbine intermediate housings, since the struts used are provided with flow-optimized strut coverings. Due to the slim and flow-optimized strut cladding flow losses are reduced and thus a higher efficiency of the gas turbine, in particular the aircraft engine, possible.
  • FIG. 1 shows a schematic representation of a strut 10 for a turbine intermediate housing of a turbomachine, in particular a gas turbine for an aircraft engine.
  • the strut 10 is integrally formed with an inner structure of the turbine intermediate housing (not shown).
  • a plurality of struts 10 together with the inner structure form a so-called integrally molded bearing star.
  • the bearing star serves for the storage of waves or rotors of a gas turbine.
  • FIG. 1 is shown in a top portion of the strut 10 in a plan view and in a lower portion in a corresponding sectional view. It is clear that the strut 10 is formed profiled.
  • the strut 10 has a first end for location on the internal structure of the turbine hub (not shown) and a second end 12 opposite the first end for attachment of the strut 10 to a housing 42 (see FIG FIG. 2 ) or an inner boundary wall of the turbine intermediate housing.
  • the flange-like element 14 is elongated in the illustrated embodiment, wherein the maximum of the longitudinal extent along the longitudinal axis of the strut 10 extends.
  • the flange-like element 14 has a projection 34 which engages in a groove 32 formed on the strut 10.
  • the flange-like element 14 also has a shoulder 36 which is supported on a support surface 38 of a flange 16 of the strut 10.
  • the flange 16 is formed partially circumferential in the illustrated embodiment, the second end 12 of the strut 10.
  • a second opening 22 is formed for receiving a second fastening means.
  • both the first opening 18 and the second opening 22 each have an internal thread 20, 24 for insertion and attachment of a screw with a corresponding external thread.
  • the second opening 22 is formed in the flange 16.
  • corresponding openings 26, 28 are formed for receiving a clamping pin 30.
  • a simple and secure attachment of the flange-like element 14 to the strut 10 in the region of the second end 12 is possible.
  • a flow-optimized, slim strut cover is pushed over the strut 10 from the outside.
  • the flange-like element 14 is fastened by means of the clamping pin 30 on the strut 10, so that in a further step, the screwing of the second end 12 of the strut 10 with the housing 42 can be carried out.
  • the strut 10 is hollow and has a gas channel 40.
  • FIG. 2 shows a schematic representation of a strut 10 according to a second embodiment. Also in FIG. 2 is in the upper area a plan view of the strut 10th and in a lower region, a corresponding sectional view of the strut 10 is shown.
  • the strut 10 according to the second embodiment basically has one with the strut 10 according to the in FIG. 1 described first embodiment comparable structure. Same reference numerals in the FIGS. 1 and 2 denote therefore in each case the same elements of the struts 10.
  • the flange-like element 14 is not arranged approximately parallel to the longitudinal axis of the strut 10 in its longitudinal direction.
  • the longitudinal axis of the likewise elongated flange-like element 14 extends approximately perpendicular to the longitudinal axis of the strut 10. It can be seen that at the end facing away from the strut 10 of the flange-like element 14, a support surface 44 for supporting the housing 42 is formed. At the end opposite the support surface 44, the flange-like element 14 in turn has a projection 34 which engages in a corresponding groove or recess 32 in the region of the second end 12 of the strut 10. In this case, the recess 32 and the projection 34 are formed such that form parallel surfaces, which prevent rotation of the flange-like element 14 relative to the strut 10 during assembly.
  • the flange-like element 14 is in turn held by means of a clamping pin 30 on the strut 10.
  • the flange 16 of the second end 12 of the strut 10 in turn has an opening 26 which corresponds to an opening 28 in the flange-like element 14.
  • the opening 28 is formed in the illustrated embodiment in the projection 34.
  • the opening 26 extends on both sides of the walls 32 surrounding the recess 32 of the flange 16th
  • the housing 42 For fixing the housing 42 to the strut 10, the housing 42 also has two openings 46, 48, which correspond to the first opening 20 and the second opening 22 of the flange-like element 14 and the flange 16.
  • the connection of the housing 42 with the strut 10 takes place by means of a screw connection.
  • the strut 10 with a corresponding strut cladding, which is designed to optimize flow provided, as has already been described with the presented in Figure 1 embodiment.
  • Strut 10 is integrally formed with an inner structure of the turbine intermediate housing (not shown).

Description

Die vorliegende Erfindung betrifft eine Strebe für ein Turbinenzwischengehäuse einer Strömungsmaschine mit einem ersten Ende zur Anordnung an einer Innenstruktur des Turbinenzwischengehäuses und einem dem ersten Ende gegenüberliegenden zweiten Ende zur Befestigung der Strebe an einem Gehäuse oder einer inneren Begrenzungswand des Turbinenzwischengehäuses, gemäß dem Oberbegriff des Patentanspruchs 1. Die Erfindung betrifft weiterhin ein Turbinenzwischengehäuse für eine Strömungsmaschine, insbesondere eine Gasturbine.The present invention relates to a strut for a turbine intermediate housing of a turbomachine having a first end for placement on an inner structure of the turbine intermediate housing and a first end opposite the first end for attaching the strut to a housing or an inner boundary wall of the turbine intermediate housing, according to the preamble of patent claim 1 The invention further relates to a turbine intermediate housing for a turbomachine, in particular a gas turbine.

Turbinenzwischengehäuse sind bei Strömungsmaschinen, insbesondere bei einer Turbine eines Flugtriebwerks, zwischen der Hochdruckturbine und der Niederdruckturbine angeordnet. Das Turbinenzwischengehäuse (auch "Turbine Center Frame", TCF) ist ein Strukturbauteil und hat die Funktion, einen Strömungskanal zwischen der Hochdruckturbine und der Niederdruckturbine auszubilden und die Lagerkammer zumindest des Hochdruckrotors mit dem Gehäuse strukturell zu verbinden. Des Weiteren dient das Turbinenzwischengehäuse zur Verteilung von Kühlluftströmen für die Niederdruckturbine. Dabei kreuzen profilierte Streben, welche eine Lagerkammer für den Turbinenrotor halten, den Gaskanal. Deshalb werden diese Streben mit Leitschaufel-ähnlichen Bauteilen verkleidet. Dabei hat es sich als kostengünstig erwiesen, die Streben zusammen mit der Lagerkammer beziehungsweise der Innenstruktur des Turbinenzwischengebäuses integral zu gießen. In diesem Fall müssen aber die Strebenverkleidungen radial von außen über die Streben montierbar sein. Da aber die freien Strebenenden an ein Gehäuse oder eine innere Begrenzungswand des Turbinenzwischengehäuses montiert werden, besitzen diese in diesem Bereich üblicherweise eine Verdickung oder einen Flansch, der bei dieser Montageart die Breite der Strebenverkleidung definiert. Nachteiligerweise können daher bei derartigen Streben nur Strebenverkleidungen verwendet werden, die entsprechend breit und nicht strömungsoptimiert ausgebildet sind. Dies verringert allerdings den Wirkungsgrad der Gasturbine, da relativ hohe Strömungsverluste auftreten. Um dies zu vermeiden, wird bei anderen bekannten Turbinenzwischengehäusen auf eine einstückige Ausbildung der Streben mit der Innenstruktur, d. h. zum Beispiel auf einen integral gegossenen Lagerstern, verzichtet. Dadurch erhöhen sich jedoch wiederum die Kosten der Herstellung des Turbinenzwischengehäuses. Aus dem Dokument US-A- 5 292 227 ist eine Strebe für ein Turbinenzwischengehäuse bekannt, welche am zweiten Ende ein lösbares, flanschartiges Element mit Öffnungen zur Aufnahme bzw. Hindurchführung von Befestigungsmitteln aufweist.Turbine intermediate housings are arranged in turbomachines, in particular in an aircraft engine turbine, between the high-pressure turbine and the low-pressure turbine. The Turbine Center Frame (TCF) is a structural member and has the function of forming a flow channel between the high pressure turbine and the low pressure turbine and structurally connecting the bearing chamber of at least the high pressure rotor to the housing. Furthermore, the turbine intermediate housing serves to distribute cooling air flows for the low-pressure turbine. In this case, profiled struts, which hold a bearing chamber for the turbine rotor, cross the gas channel. Therefore, these struts are clad with vane-like components. It has proved to be cost-effective to cast integrally the struts together with the storage chamber or the inner structure of the turbine intermediate. In this case, however, the strut cladding must be mountable radially from the outside over the struts. However, since the free strut ends are mounted to a housing or an inner boundary wall of the turbine intermediate housing, they usually have a thickening or a flange in this area, which defines the width of the strut covering in this type of mounting. Disadvantageously, therefore, in such struts only Strut coverings are used, which are designed according to wide and not optimized flow. However, this reduces the efficiency of the gas turbine, since relatively high flow losses occur. To avoid this, in other known turbine intermediate housings on a one-piece design of the struts with the internal structure, that is, for example, an integrally molded bearing star dispensed. However, this in turn increases the cost of manufacturing the turbine hub. From the document US-A-5,292,227 a strut for a turbine intermediate housing is known, which has at the second end a detachable, flange-like element with openings for receiving or passing through fastening means.

Es ist daher Aufgabe der vorliegenden Erfindung, eine konstruktiv weiter verbesserte bzw. vereinfachte, gattungsgemäße Strebe für ein Turbinenzwischengehäuse bereitzustellen, die eine einfache Verkleidung mit einer strömungsoptimierten und schlank ausgebildeten Strebenverkleidung ermöglicht.It is therefore an object of the present invention to provide a structurally further improved or simplified, generic strut for a turbine intermediate housing, which allows a simple panel with a flow-optimized and slender strut cladding.

Es ist weiterhin Aufgabe der vorliegenden Erfindung, ein gattungsgemäßes Turbinenzwischengehäuse mit einem im Vergleich zu bekannten Turbinenzwischengehäusen höheren Wirkungsgrad und verbesserter Konstruktion bereitzustellen.It is another object of the present invention to provide a generic turbine intermediate housing with a higher efficiency and improved construction compared to known turbine intermediate housings.

Gelöst werden diese Aufgaben durch eine Strebe und ein Turbinenzwischengehäuse gemäß den Merkmalen des unabhängigen Anspruchs 1.These objects are achieved by a strut and a turbine intermediate housing according to the features of independent claim 1.

Vorteilhafte Ausgestaltungen der Erfindung sind in den jeweiligen Unteransprüchen beschrieben.Advantageous embodiments of the invention are described in the respective subclaims.

Eine gattungsgemäße Strebe für ein Turbinenzwischengehäuse einer Strömungsmaschine, insbesondere für eine Gasturbine, umfasst ein erstes Ende zur Anordnung an einer Innenstruktur des Turbinenzwischengehäuses und ein dem ersten Ende gegenüberliegendes zweites Ende zur Befestigung der Strebe an einem Gehäuse oder einer inneren Begrenzungswand des Turbinenzwischengehäuses, wobei an dem zweiten Ende mindestens ein flanschartige Element mit mindestens einer ersten Öffnung zur Aufnahme oder Hindurchführung eines Befestigungsmittels lösbar angeordnet ist. Durch die lösbare Anordnung des flanschartigen Elements ist es möglich, zunächst eine strömungsoptimierte Strebenverkleidung radial von außen über die Strebe zu schieben und erst anschließend das flanschartige Element an dem zweiten Ende anzuordnen und die Strebe mittels des flanschartigen Elements an dem Gehäuse oder der inneren Begrenzungswand des Turbinenzwischengehäuses zu befestigen. Durch die Möglichkeit der Montage von schlankeren, strömungsoptimierten Strebenverkleidungen werden die Strömungsverluste innerhalb des Turbinenzwischengehäuses signifikant reduziert, wodurch sich wiederum ein höherer Wirkungsgrad der Strömungsmaschine ergibt. Des Weiteren ist es dabei möglich, dass die erfindungsgemäße Strebe als Teil eines integral gegossenen Lagersterns, dessen Herstellung kostengünstig zu realisieren ist, verwendet wird. Erfindungsgemäß weist die Strebe im Bereich des zweiten Endes mindestens eine Nut oder Ausnehmung auf, in die ein entsprechender Vorsprung des flanschartigen Elements eingreifen kann. Dadurch ist eine einfache Montage des flanschartigen Elements an der Strebe im Bereich des zweiten Endes der Strebe möglich.A generic strut for a turbine intermediate housing of a turbomachine, in particular for a gas turbine, comprises a first end for placement on an inner structure of the turbine intermediate housing and a first end opposite the first end second end for attachment of the strut to a housing or an inner boundary wall of the turbine intermediate housing, wherein at the second end at least one flange-like element with at least one first opening for receiving or passing through a fastening means is detachably arranged. Due to the detachable arrangement of the flange-like element, it is possible to first push a flow-optimized strut trim radially from the outside over the strut and only then to arrange the flange-like element at the second end and the strut by means of the flange-like element on the housing or the inner boundary wall of the turbine intermediate housing to fix. Due to the possibility of mounting slimmer, flow-optimized strut cladding, the flow losses within the turbine intermediate housing are significantly reduced, which in turn results in a higher efficiency of the turbomachine. Furthermore, it is possible that the strut according to the invention is used as part of an integrally cast bearing star whose production is inexpensive to implement. According to the invention, the strut in the region of the second end has at least one groove or recess into which a corresponding projection of the flange-like element can engage. As a result, a simple mounting of the flange-like element on the strut in the region of the second end of the strut is possible.

Weiterhin weist die Strebe erfindungsgemäß am zweiten Ende mindestens einen zusätzlichen umlaufenden oder nicht-umlaufenden Flansch auf. Durch den Flansch vergrößert sie die Auflagefläche zwischen der Strebe beziehungsweise dem zweiten Ende der Strebe und dem damit zu verbindenden Gehäuse oder der damit zu verbindenden inneren Begrenzungswand des Turbinenzwischengehäuses. Das flanschartige Element setzt dabei an dem Flansch der Strebe an.Furthermore, according to the invention, the strut has at least one additional peripheral or non-circumferential flange at the second end. Through the flange, it increases the bearing surface between the strut or the second end of the strut and the housing to be connected therewith or to be connected to the inner boundary wall of the turbine intermediate housing. The flange-like element attaches to the flange of the strut.

Erfindungsgemäß weist die Strebe am zweiten Ende mindestens eine zweite Öffnung zur Aufnahme oder Hindurchführung eines Befestigungsmittels auf. Dabei ist die mindestens eine zweite Öffnung in dem mindestens einen Flansch ausgebildet. Durch die Ausbildung einer zweiten Öffnung ergibt sich nach der Befestigung der Strebe an dem Gehäuse oder der inneren Begrenzungswand des Turbinenzwischengehäuses eine feste und innige Verbindung zwischen diesen Elementen. Es ist auch denkbar, dass diese Verbindung nicht nur mit zwei Befestigungsmitteln, sondern mit noch mehr Befestigungsmitteln erfolgt.According to the invention, the strut has at least one second opening for receiving or passing through a fastening means at the second end. In this case, the at least one second opening is formed in the at least one flange. The formation of a second opening results in a firm and intimate connection between these elements after the attachment of the strut to the housing or the inner boundary wall of the turbine intermediate housing. It is also conceivable that this connection is made not only with two fasteners, but with even more fasteners.

Üblicherweise ist das Befestigungsmittel eine Schraube.Usually, the fastener is a screw.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung sind im Flansch am zweiten Ende der Strebe und dem flanschartigen Element korrespondierende Öffnungen zur Aufnahme eines Spannstiftes ausgebildet. Der Spannstift dient dabei vorteilhafterweise zum Halten des flanschartigen Elements an der Strebe während der Befestigung, insbesondere Verschraubung an dem Gehäuse oder der inneren Begrenzungswand des Turbinenzwischengehäuses.In a further advantageous embodiment of the invention corresponding openings for receiving a clamping pin are formed in the flange at the second end of the strut and the flange-like element. The dowel pin advantageously serves to hold the flange-like element on the strut during attachment, in particular screwing to the housing or the inner boundary wall of the turbine intermediate housing.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist die Strebe mit der Innenstruktur des Turbinenzwischengehäuses einstückig ausgebildet. Zudem ist die Strebe zumindest teilweise von einer Strebenverkleidung umgeben, wobei die Strebenverkleidung strömungsoptimiert ausgebildet ist. Zudem kann die Strebenverkleidung aus einem hitzebeständigen Material bestehen.In a further advantageous embodiment of the invention, the strut is formed integrally with the inner structure of the turbine intermediate housing. In addition, the strut is at least partially surrounded by a strut cladding, wherein the strut cladding is designed to optimize flow. In addition, the strut cladding may consist of a heat-resistant material.

Ein erfindungsgemäßes Turbinenzwischengehäuse für eine Strömungsmaschine, insbesondere eine Gasturbine, umfasst mehrere an einer Innenstruktur radial angeordnete Streben zur Verbindung mit einem Gehäuse oder einer inneren Begrenzungswand des Turbinenzwischengehäuses, wobei die Streben wie im Vorhergehenden beschrieben ausgebildet sind. Die Strömungsmaschine kann dabei eine Gasturbine eines Flugtriebwerks sein. Das erfindungsgemäße Turbinenzwischengehäuse weist einen im Vergleich zu bekannten Turbinenzwischengehäusen höheren Wirkungsgrad auf, da die verwendeten Streben mit strömungsoptimierten Strebenverkleidungen versehen sind. Durch die schlanken und strömungsoptimierten Strebenverkleidungen werden Strömungsverluste reduziert und somit ein höherer Wirkungsgrad der Gasturbine, insbesondere des Flugtriebwerks, möglich.A turbine intermediate housing according to the invention for a turbomachine, in particular a gas turbine, comprises a plurality of struts arranged radially on an inner structure for connection to a housing or an inner boundary wall of the turbine intermediate housing, wherein the struts are formed as described above. The turbomachine can be a gas turbine of an aircraft engine. The turbine intermediate housing according to the invention has a higher efficiency compared to known turbine intermediate housings, since the struts used are provided with flow-optimized strut coverings. Due to the slim and flow-optimized strut cladding flow losses are reduced and thus a higher efficiency of the gas turbine, in particular the aircraft engine, possible.

Weitere Vorteile, Merkmale und Einzelheiten der Erfindung ergeben sich aus der nachfolgenden Beschreibung zweier zeichnerisch dargestellter Ausführungsbeispiele. Es zeigen

Figur 1
eine schematische Darstellung einer erfindungsgemäßen Strebe für ein Turbinenzwischengehäuse gemäß einer ersten Ausführungsform; und
Figur 2
eine schematische Darstellung einer erfindungsgemäßen Strebe für ein Turbinenzwischengehäuse gemäß einer zweiten Ausführungsform.
Further advantages, features and details of the invention will become apparent from the following description of two drawings illustrated embodiments. Show it
FIG. 1
a schematic representation of a strut according to the invention for a turbine intermediate housing according to a first embodiment; and
FIG. 2
a schematic representation of a strut according to the invention for a turbine intermediate housing according to a second embodiment.

Figur 1 zeigt eine schematische Darstellung einer Strebe 10 für ein Turbinenzwischengehäuse einer Strömungsmaschine, insbesondere einer Gasturbine für ein Flugtriebwerk. Die Strebe 10 ist dabei mit einer Innenstruktur des Turbinenzwischengehäuses einstückig ausgebildet (nicht dargestellt). Insbesondere bilden mehrere Streben 10 zusammen mit der Innenstruktur einen so genannten integral gegossenen Lagerstern. Der Lagerstern dient dabei zur Lagerung von Wellen beziehungsweise Rotoren einer Gasturbine. In der Figur 1 ist in einem oberen Bereich die Strebe 10 in einer Aufsicht und in einem unteren Bereich in einer entsprechenden Schnittdarstellung gezeigt. Dabei wird deutlich, dass die Strebe 10 profiliert ausgebildet ist. Des Weiteren erkennt man, dass die Strebe 10 ein erstes Ende zur Anordnung an der Innenstruktur des Turbinenzwischengehäuses (nicht dargestellt) und ein dem ersten Ende gegenüberliegendes zweites Ende 12 zur Befestigung der Strebe 10 an einem Gehäuse 42 (vergleiche Figur 2) oder einer inneren Begrenzungswand des Turbinenzwischengehäuses aufweist. An dem zweiten Ende 12 ist dabei ein flanschartiges Element 14 mit einer ersten Öffnung 18 zur Aufnahme eines Befestigungsmittels, insbesondere einer Schraube (nicht dargestellt), lösbar angeordnet. FIG. 1 shows a schematic representation of a strut 10 for a turbine intermediate housing of a turbomachine, in particular a gas turbine for an aircraft engine. The strut 10 is integrally formed with an inner structure of the turbine intermediate housing (not shown). In particular, a plurality of struts 10 together with the inner structure form a so-called integrally molded bearing star. The bearing star serves for the storage of waves or rotors of a gas turbine. In the FIG. 1 is shown in a top portion of the strut 10 in a plan view and in a lower portion in a corresponding sectional view. It is clear that the strut 10 is formed profiled. Furthermore, it can be seen that the strut 10 has a first end for location on the internal structure of the turbine hub (not shown) and a second end 12 opposite the first end for attachment of the strut 10 to a housing 42 (see FIG FIG. 2 ) or an inner boundary wall of the turbine intermediate housing. At the second end 12, a flange-like element 14 with a first opening 18 for receiving a fastening means, in particular a screw (not shown), detachably arranged.

Das flanschartige Element 14 ist in dem dargestellten Ausführungsbeispiel länglich ausgebildet, wobei das Maximum der Längserstreckung entlang der Längsachse der Strebe 10 verläuft. Das flanschartige Element 14 weist dabei einen Vorsprung 34 auf, der in eine an der Strebe 10 ausgebildete Nut 32 eingreift. An dem dem Vorsprung 34 gegenüberliegenden Ende weist das flanschartige Element 14 zudem eine Schulter 36 auf, die an einer Abstützfläche 38 eines Flansches 16 der Strebe 10 abgestützt ist. Der Flansch 16 ist in dem dargestellten Ausführungsbeispiel am zweiten Ende 12 der Strebe 10 teilweise umlaufend ausgebildet.The flange-like element 14 is elongated in the illustrated embodiment, wherein the maximum of the longitudinal extent along the longitudinal axis of the strut 10 extends. The flange-like element 14 has a projection 34 which engages in a groove 32 formed on the strut 10. At the opposite end of the projection 34, the flange-like element 14 also has a shoulder 36 which is supported on a support surface 38 of a flange 16 of the strut 10. The flange 16 is formed partially circumferential in the illustrated embodiment, the second end 12 of the strut 10.

Des Weiteren erkennt man, dass in dem dem flanschartigen Element 14 beziehungsweise der ersten Öffnung 18 gegenüberliegenden Ende der Strebe 10 eine zweite Öffnung 22 zur Aufnahme eines zweiten Befestigungsmittels ausgebildet ist. Dabei weisen sowohl die erste Öffnung 18 wie auch die zweite Öffnung 22 jeweils ein Innengewinde 20, 24 zur Einführung und Befestigung einer Schraube mit einem entsprechenden Außengewinde auf. Die zweite Öffnung 22 ist dabei im Flansch 16 ausgebildet.Furthermore, it can be seen that in the flange-like element 14 and the first opening 18 opposite end of the strut 10, a second opening 22 is formed for receiving a second fastening means. In this case, both the first opening 18 and the second opening 22 each have an internal thread 20, 24 for insertion and attachment of a screw with a corresponding external thread. The second opening 22 is formed in the flange 16.

Des Weiteren sind im Flansch 16 und dem flanschartigen Element 14 korrespondierende Öffnungen 26, 28 zur Aufnahme eines Spannstiftes 30 ausgebildet. Dadurch ist eine einfache und sichere Befestigung des flanschartigen Elementes 14 an der Strebe 10 im Bereich des zweiten Endes 12 möglich. Vor einer Befestigung des flanschartigen Elements 14 an der Strebe 10 wird über die Strebe 10 von außen eine strömungsoptimierte, schlanke Strebenverkleidung geschoben. Anschließend wird das flanschartige Element 14 mithilfe des Spannstiftes 30 an der Strebe 10 befestigt, so dass in einem weiteren Schritt die Verschraubung des zweiten Endes 12 der Strebe 10 mit dem Gehäuse 42 erfolgen kann.Furthermore, in the flange 16 and the flange-like element 14 corresponding openings 26, 28 are formed for receiving a clamping pin 30. As a result, a simple and secure attachment of the flange-like element 14 to the strut 10 in the region of the second end 12 is possible. Before attachment of the flange-like element 14 to the strut 10, a flow-optimized, slim strut cover is pushed over the strut 10 from the outside. Subsequently, the flange-like element 14 is fastened by means of the clamping pin 30 on the strut 10, so that in a further step, the screwing of the second end 12 of the strut 10 with the housing 42 can be carried out.

Des Weiteren erkennt man, dass die Strebe 10 hohlförmig ausgebildet ist und einen Gaskanal 40 aufweist.Furthermore, it can be seen that the strut 10 is hollow and has a gas channel 40.

Figur 2 zeigt eine schematische Darstellung einer Strebe 10 gemäß einem zweiten Ausführungsbeispiel. Auch in Figur 2 ist in dem oberen Bereich eine Aufsicht auf die Strebe 10 und in einem unteren Bereich eine entsprechende Schnittzeichnung der Strebe 10 dargestellt Die Strebe 10 gemäß der zweiten Ausführungsform weist grundsätzlich einen mit der Strebe 10 gemäß der in Figur 1 beschriebenen ersten Ausführungsform vergleichbaren Aufbau auf. Gleiche Bezugszeichen in den Figuren 1 und 2 bezeichnen daher jeweils gleiche Elemente der Streben 10. Im Gegensatz zu dem in Figur 1 dargestellten Ausführungsbeispiel ist hier jedoch das flanschartige Element 14 nicht in seiner Längsrichtung ungefähr parallel zur Längsachse der Strebe 10 angeordnet. Vielmehr verläuft die Längsachse des ebenfalls länglich ausgebildeten flanschartigen Elements 14 ungefähr senkrecht zur Längsachse der Strebe 10. Man erkennt, dass an dem der Strebe 10 abgewandten Ende des flanschartigen Elements 14 eine Stützfläche 44 zur Abstützung des Gehäuses 42 ausgebildet ist. An dem der Stützfläche 44 gegenüberliegenden Ende weist das flanschartige Element 14 wiederum einen Vorsprung 34 auf, der in eine entsprechende Nut beziehungsweise Ausnehmung 32 im Bereich des zweiten Endes 12 der Strebe 10 eingreift. Dabei sind die Ausnehmung 32 und der Vorsprung 34 derart ausgebildet, dass sich parallele Flächen ausbilden, die ein Verdrehen des flanschartigen Elements 14 relativ zur Strebe 10 während der Montage verhindern. FIG. 2 shows a schematic representation of a strut 10 according to a second embodiment. Also in FIG. 2 is in the upper area a plan view of the strut 10th and in a lower region, a corresponding sectional view of the strut 10 is shown. The strut 10 according to the second embodiment basically has one with the strut 10 according to the in FIG. 1 described first embodiment comparable structure. Same reference numerals in the FIGS. 1 and 2 denote therefore in each case the same elements of the struts 10. In contrast to the in FIG. 1 illustrated embodiment, however, the flange-like element 14 is not arranged approximately parallel to the longitudinal axis of the strut 10 in its longitudinal direction. Rather, the longitudinal axis of the likewise elongated flange-like element 14 extends approximately perpendicular to the longitudinal axis of the strut 10. It can be seen that at the end facing away from the strut 10 of the flange-like element 14, a support surface 44 for supporting the housing 42 is formed. At the end opposite the support surface 44, the flange-like element 14 in turn has a projection 34 which engages in a corresponding groove or recess 32 in the region of the second end 12 of the strut 10. In this case, the recess 32 and the projection 34 are formed such that form parallel surfaces, which prevent rotation of the flange-like element 14 relative to the strut 10 during assembly.

Das flanschartige Element 14 wird wiederum mittels eines Spannstifts 30 an der Strebe 10 gehalten. Zur Aufnahme und Lagerung des Spannstifts 30 weist der Flansch 16 des zweiten Endes 12 der Strebe 10 wiederum eine Öffnung 26 auf, die mit einer Öffnung 28 in dem flanschartigen Element 14 korrespondiert. Die Öffnung 28 ist in dem dargestellten Ausführungsbeispiel dabei in dem Vorsprung 34 ausgebildet. Die Öffnung 26 erstreckt sich auf beiden Seiten der die Ausnehmung 32 umgebenden Wände des Flansches 16.The flange-like element 14 is in turn held by means of a clamping pin 30 on the strut 10. For receiving and supporting the clamping pin 30, the flange 16 of the second end 12 of the strut 10 in turn has an opening 26 which corresponds to an opening 28 in the flange-like element 14. The opening 28 is formed in the illustrated embodiment in the projection 34. The opening 26 extends on both sides of the walls 32 surrounding the recess 32 of the flange 16th

Zur Befestigung des Gehäuses 42 an der Strebe 10 weist das Gehäuse 42 ebenfalls zwei Öffnungen 46, 48 auf, die mit der ersten Öffnung 20 und der zweiten Öffnung 22 des flanschartigen Elements 14 beziehungsweise des Flansches 16 korrespondieren. Die Verbindung des Gehäuses 42 mit der Strebe 10 erfolgt dabei mittels einer Schraubverbindung. Vor dieser Verbindung wird wiederum die Strebe 10 mit einer entsprechenden Strebenverkleidung, die strömungsoptimiert ausgebildet ist, versehen, wie dies bereits mit dem in Figur 1 vorgestellten Ausführungsbeispiel beschrieben worden ist. Auch die in Figur 2 dargestellte Strebe 10 ist einstückig mit einer Innenstruktur des Turbinenzwischengehäuses ausgebildet (nicht dargestellt).For fixing the housing 42 to the strut 10, the housing 42 also has two openings 46, 48, which correspond to the first opening 20 and the second opening 22 of the flange-like element 14 and the flange 16. The connection of the housing 42 with the strut 10 takes place by means of a screw connection. Before this connection, in turn, the strut 10 with a corresponding strut cladding, which is designed to optimize flow, provided, as has already been described with the presented in Figure 1 embodiment. Also in FIG. 2 illustrated Strut 10 is integrally formed with an inner structure of the turbine intermediate housing (not shown).

Claims (9)

  1. A strut for a turbine centre frame of a jet engine having a first end for arrangement on an inner structure of the turbine centre frame and a second end (12) lying opposite the first end for securement of the strut (10) to a housing (42) or an inner boundary wall of the turbine centre frame, wherein detachably arranged at the second end (12) there is at least one flange-like element (14) having at least one first opening (18) for accommodating or guiding through a means of securement, wherein the strut (10) has in the region of the second end (12) at least one groove or recess (32) into which a corresponding projection (34) of the at least one flange-like element (14) engages, and wherein formed at the second end (12) there is at least one circumferential or non-circumferential flange (16), characterised in that the strut (10) has at the second end (12) at least one second opening (22) for accommodating or guiding through a means of securement, and in that the at least one second opening (22) is formed in the at least one flange (16).
  2. A strut according to claim 1, characterised in that the at least one flange (16) forms at least one support surface (38) for support of a shoulder (36) of the flange-like element (14).
  3. A strut according to claim 1 or 2, characterised in that the flange-like element (14) has at least one supporting surface (44) for support on the housing (42) or the inner boundary wall of the turbine centre frame.
  4. A strut according to one of claims 1 to 3, characterised in that formed in the at least one flange (16) and the at least one flange-like element (14) there are corresponding openings (26, 28) for accommodation of at least one dowel pin (30).
  5. A strut according to one of the preceding claims, characterised in that the means of securement is a screw.
  6. A strut according to one of the preceding claims, characterised in that the strut (10) is formed in one piece with the inner structure of the turbine centre frame.
  7. A strut according to one of the preceding claims, characterised in that the strut (10) is surrounded at least in part by a strut casing.
  8. A turbine centre frame for a jet engine having a plurality of struts (10) that are arranged radially on an inner structure for connection to a housing (42) or an inner boundary wall of the turbine centre frame, characterised in that the struts (10) are formed according to one of claims 1 to 7.
  9. A turbine centre frame according to claim 8, characterised in that the jet engine is a gas turbine.
EP09733098.9A 2008-04-17 2009-04-17 Strut for an intermediate turbine housing and intermediate turbine housing Not-in-force EP2268902B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008019156A DE102008019156A1 (en) 2008-04-17 2008-04-17 Strut for a turbine intermediate housing, turbine intermediate housing and method for producing a turbine intermediate housing
PCT/DE2009/000527 WO2009127203A1 (en) 2008-04-17 2009-04-17 Strut for an intermediate turbine housing, intermediate turbine housing, and method for producing an intermediate turbine housing

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EP2268902A1 EP2268902A1 (en) 2011-01-05
EP2268902B1 true EP2268902B1 (en) 2013-07-10

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EP (1) EP2268902B1 (en)
DE (1) DE102008019156A1 (en)
WO (1) WO2009127203A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008019156A1 (en) * 2008-04-17 2009-10-22 Mtu Aero Engines Gmbh Strut for a turbine intermediate housing, turbine intermediate housing and method for producing a turbine intermediate housing
FR2981700B1 (en) * 2011-10-24 2016-08-26 Snecma Propulsion Solide DEVICE FOR FIXING A HOLLOW PIECE
US9822667B2 (en) 2015-04-06 2017-11-21 United Technologies Corporation Tri-tab lock washer
US10247035B2 (en) 2015-07-24 2019-04-02 Pratt & Whitney Canada Corp. Spoke locking architecture
CA2936180A1 (en) 2015-07-24 2017-01-24 Pratt & Whitney Canada Corp. Multiple spoke cooling system and method
US10443449B2 (en) 2015-07-24 2019-10-15 Pratt & Whitney Canada Corp. Spoke mounting arrangement
DE102016204660A1 (en) 2016-03-22 2017-09-28 MTU Aero Engines AG Method for producing a housing of a turbomachine and housing of a turbomachine
US10781721B2 (en) 2018-02-09 2020-09-22 General Electric Company Integral turbine center frame

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2058476A1 (en) * 2007-11-09 2009-05-13 Snecma Connection of radial struts to a circular casing by interleaving inserts

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
EP0550126A1 (en) * 1992-01-02 1993-07-07 General Electric Company Thrust augmentor heat shield
US5292227A (en) 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5483792A (en) * 1993-05-05 1996-01-16 General Electric Company Turbine frame stiffening rails
US5438756A (en) * 1993-12-17 1995-08-08 General Electric Company Method for assembling a turbine frame assembly
US6358001B1 (en) * 2000-04-29 2002-03-19 General Electric Company Turbine frame assembly
US6860716B2 (en) * 2003-05-29 2005-03-01 General Electric Company Turbomachine frame structure
DE102008019156A1 (en) * 2008-04-17 2009-10-22 Mtu Aero Engines Gmbh Strut for a turbine intermediate housing, turbine intermediate housing and method for producing a turbine intermediate housing

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2058476A1 (en) * 2007-11-09 2009-05-13 Snecma Connection of radial struts to a circular casing by interleaving inserts

Also Published As

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EP2268902A1 (en) 2011-01-05
DE102008019156A1 (en) 2009-10-22
US8579583B2 (en) 2013-11-12
US20110033290A1 (en) 2011-02-10
WO2009127203A1 (en) 2009-10-22

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