EP2268902B1 - Entretoise pour carter intermédiaire de turbine et carter intermédiaire de turbine - Google Patents

Entretoise pour carter intermédiaire de turbine et carter intermédiaire de turbine 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
Authority
EP
European Patent Office
Prior art keywords
strut
flange
turbine
housing
centre frame
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP09733098.9A
Other languages
German (de)
English (en)
Other versions
EP2268902A1 (fr
Inventor
Alexander Böck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2268902A1 publication Critical patent/EP2268902A1/fr
Application granted granted Critical
Publication of EP2268902B1 publication Critical patent/EP2268902B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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).

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

Claims (9)

  1. Entretoise pour carter intermédiaire de turbine d'une turbomachine comportant une première extrémité prévue pour l'arrangement à une structure interne du carter intermédiaire de turbine et une deuxième extrémité (12), située en face de la première, pour fixer l'entretoise (10) sur un carter (42) ou une paroi de délimitation interne du carter intermédiaire de turbine, au moins un élément en forme de flasque (14), comportant une première ouverture (18) destinée à recevoir ou faire passer un moyen de fixation, étant placé de manière amovible sur la deuxième extrémité (12), l'entretoise (10) présentant, au niveau de la deuxième extrémité (12) au moins une rainure ou un évidement (32) dans laquelle ou lequel une saillir correspondante (34) de l'élément en forme de flasque (14) se met en prise, et un flasque périphérique ou non-périphérique (16) étant aménagé sur la deuxième extrémité (12),
    caractérisé en ce que
    l'entretoise (10) présente, sur la deuxième extrémité (12), au moins une deuxième ouverture (22) destinée à recevoir ou à faire passer un moyen de fixation et
    la deuxième ouverture (22) est formée dans au moins un flasque (16).
  2. Entretoise selon la revendication 1,
    caractérisée en ce qu'
    le flasque (16) forme au moins une surface d'appui (38) pour supporter un épaulement (36) de l'élément en forme de flasque (14).
  3. Entretoise selon la revendication 1 ou la revendication 2,
    caractérisée en ce que
    l'élément en forme de flasque (14) présente au moins une surface d'appui (44) pour le support sur le carter (42) ou la paroi de délimitation interne du carter intermédiaire de turbine.
  4. Entretoise selon l'une quelconque des revendications 1 à 3,
    caractérisée en ce que
    des ouvertures correspondantes (26, 28) destinées à recevoir au moins une goupille de serrage (30) est aménagée dans le flasque (16) et l'élément en forme de flasque (14).
  5. Entretoise selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    le moyen de fixation est une vis.
  6. Entretoise selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    l'entretoise (10) forme une seule pièce avec la structure interne du carter intermédiaire de turbine.
  7. Entretoise selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    l'entretoise (10) est entourée, au moins en partie, par un habillage d'entretoise.
  8. Carter intermédiaire de turbine pour une turbomachine comportant plusieurs entretoises (10) disposées radialement à une structure interne pour la liaison avec un carter (42) ou une paroi de délimitation interne du carter intermédiaire de turbine,
    caractérisé en ce que
    les entretoises (10) sont configurées selon l'une quelconque des revendications 1 à 7.
  9. Carter intermédiaire de turbine selon la revendication 8,
    caractérisé en ce que
    la turbomachine est une turbine à gaz.
EP09733098.9A 2008-04-17 2009-04-17 Entretoise pour carter intermédiaire de turbine et carter intermédiaire de turbine Not-in-force EP2268902B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008019156A DE102008019156A1 (de) 2008-04-17 2008-04-17 Strebe für ein Turbinenzwischengehäuse, Turbinenzwischengehäuse und Verfahren zur Herstellung eines Turbinenzwischengehäuses
PCT/DE2009/000527 WO2009127203A1 (fr) 2008-04-17 2009-04-17 Entretoise pour carter intermédiaire de turbine, carter intermédiaire de turbine, et procédé de production d'un carter intermédiaire de turbine

Publications (2)

Publication Number Publication Date
EP2268902A1 EP2268902A1 (fr) 2011-01-05
EP2268902B1 true EP2268902B1 (fr) 2013-07-10

Family

ID=41055177

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09733098.9A Not-in-force EP2268902B1 (fr) 2008-04-17 2009-04-17 Entretoise pour carter intermédiaire de turbine et carter intermédiaire de turbine

Country Status (4)

Country Link
US (1) US8579583B2 (fr)
EP (1) EP2268902B1 (fr)
DE (1) DE102008019156A1 (fr)
WO (1) WO2009127203A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008019156A1 (de) * 2008-04-17 2009-10-22 Mtu Aero Engines Gmbh Strebe für ein Turbinenzwischengehäuse, Turbinenzwischengehäuse und Verfahren zur Herstellung eines Turbinenzwischengehäuses
FR2981700B1 (fr) * 2011-10-24 2016-08-26 Snecma Propulsion Solide Dispositif de fixation d'une piece creuse
US9822667B2 (en) 2015-04-06 2017-11-21 United Technologies Corporation Tri-tab lock washer
CA2936182C (fr) 2015-07-24 2023-08-15 Pratt & Whitney Canada Corp. Systeme et methode de refroidissement multi ailette de chassis mi-turbine
US10247035B2 (en) 2015-07-24 2019-04-02 Pratt & Whitney Canada Corp. Spoke locking architecture
US10443449B2 (en) 2015-07-24 2019-10-15 Pratt & Whitney Canada Corp. Spoke mounting arrangement
DE102016204660A1 (de) 2016-03-22 2017-09-28 MTU Aero Engines AG Verfahren zum Herstellen eines Gehäuses einer Strömungsmaschine und Gehäuse einer Strömungsmaschine
US10781721B2 (en) 2018-02-09 2020-09-22 General Electric Company Integral turbine center frame
DE102021128979A1 (de) * 2021-11-08 2023-05-11 MTU Aero Engines AG Verstellhebel für eine strömungsmaschine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2058476A1 (fr) * 2007-11-09 2009-05-13 Snecma Raccordement de bras radiaux a une virole circulaire par imbrication de pieces rapportees

Family Cites Families (8)

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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 (fr) * 1992-01-02 1993-07-07 General Electric Company Bouclier thermique pour post-combusteur
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 (de) * 2008-04-17 2009-10-22 Mtu Aero Engines Gmbh Strebe für ein Turbinenzwischengehäuse, Turbinenzwischengehäuse und Verfahren zur Herstellung eines Turbinenzwischengehäuses

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2058476A1 (fr) * 2007-11-09 2009-05-13 Snecma Raccordement de bras radiaux a une virole circulaire par imbrication de pieces rapportees

Also Published As

Publication number Publication date
EP2268902A1 (fr) 2011-01-05
DE102008019156A1 (de) 2009-10-22
US20110033290A1 (en) 2011-02-10
US8579583B2 (en) 2013-11-12
WO2009127203A1 (fr) 2009-10-22

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