EP1798378B1 - Disposition de montage d'une aube directrice de turbine à gaz - Google Patents

Disposition de montage d'une aube directrice de turbine à gaz Download PDF

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Publication number
EP1798378B1
EP1798378B1 EP05257826A EP05257826A EP1798378B1 EP 1798378 B1 EP1798378 B1 EP 1798378B1 EP 05257826 A EP05257826 A EP 05257826A EP 05257826 A EP05257826 A EP 05257826A EP 1798378 B1 EP1798378 B1 EP 1798378B1
Authority
EP
European Patent Office
Prior art keywords
arrangement
locators
locator
vane
tang
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
EP05257826A
Other languages
German (de)
English (en)
Other versions
EP1798378A1 (fr
Inventor
Stephen John Booth
Alison Jane Mcmillan
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to DE602005021803T priority Critical patent/DE602005021803D1/de
Priority to DK05257826.7T priority patent/DK1798378T3/da
Priority to AT05257826T priority patent/ATE470784T1/de
Priority to EP05257826A priority patent/EP1798378B1/fr
Publication of EP1798378A1 publication Critical patent/EP1798378A1/fr
Application granted granted Critical
Publication of EP1798378B1 publication Critical patent/EP1798378B1/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
    • F01D25/24—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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the present invention relates to mounting arrangements and more particularly to mounting arrangements utilised to secure vanes in a gas turbine engine.
  • Fig. 1 illustrates a typical prior mounting arrangement of a vane 1 secured between an inner mounting ring 2 and an outer casing 3.
  • the vane 1 is secured to an inner platform 4 and an outer platform 5 from which a tang arm 6 extends to a tang 7 which is engaged in an interference fit with a slot or groove 8 formed in the respective ring 2 or casing 3. This engagement may be an interference or close clearance fit.
  • the vane 1 may typically be formed from an organic matrix composite aerofoil material.
  • the vane 1 may be held in place in a bypass, fan or compressor module of a gas turbine engine.
  • the vane 1 could be formed from relatively high temperature materials which would allow operation in the turbine stages of a gas turbine engine.
  • Fig. 1 The arrangement depicted in Fig. 1 as indicated is typically used to anchor a vane in place in forward and rearward positions through insertion of tangs into circumferential slots in the casing 3 and inner ring 2.
  • a four point fixing arrangement constituted by the respective tangs 7 in the slots or grooves.
  • the respective tang 7 There is a semi freedom for the respective tang 7 to slip, subject to any clearance gap and any interference friction within their respective slot or groove 8 in order to provide a mechanism for damping any vibration in the vane which may be induced by periodic variations in gas stream flow, such as due to blading, or structural vibrations transmitted through the inner ring 2 or casing 3.
  • the tang 7 may also provide a gas seal when required.
  • a particular problem relates to the fact that four-point fixing with the arrangement as depicted in Fig. 1 can cause over-constraint upon the vane 1. It is accepted that a structure needs three distinct displacement and three distinct rotation constraints in order to provide positional retention. In practice, there are also design clearances and thermal growth effects, etc., to consider, but it is broadly accepted that a fourth tang is largely redundant and, as indicated, provides over-constraint. In such situations vibration, thermal growth or direct loading of the component, that is to say the vane 1, can result in stress or strain distributions which give rise to constraint forces at the respective fixing points. With four fixing points these constraint forces are accentuated.
  • Fig. 2 illustrates a typical prior mounting arrangement whereby a vane 21 has a platform 11 which is secured to a tang element 27 by an adhesive layer 12.
  • Such an arrangement is relatively easy to manufacture whereby the vane 21 and platform 11 can be formed and secured through the adhesive 12 to an appropriately shaped tang element member 27 with limited machining and other manufacturing processes necessary.
  • the constraint forces tend to limit the load potential of the arrangement as depicted in Fig. 1 .
  • the bonding provided by the adhesive layer 12 between the element 27 and platform 11 may be subject to straining forces or potentially more importantly the area, known as the tang arm, connecting the tang end of the element 27 with the remainder of that element will be subject to such loading. In such circumstances there is a possibility of peel failure between the element 27 about the adhesive layer 12, or failure of the tang arm.
  • EP0526058 , US3511577 and US5584654 Examples of prior mounting arrangements are given in EP0526058 , US3511577 and US5584654 .
  • EP0526058 and US3511577 avoid over constraint problems with regard to the mounting arrangement by providing only three location positions within the mounting arrangement for a vane. In such circumstances some flexibility is retained to avoid distortion but with less surety of location and sealing for the vane.
  • Alternatively as illustrated in US5584654 four point location of a rigid nature is identified but with potential problems with respect to over constraint for the vane but as indicated greater surety with regard to consistency of location.
  • a vane mounting vane arrangement for a gas turbine engine, the vane mounting arrangement comprising four locators arranged in use to substantially retain the vane in position, the arrangement characterised in that one of the locators is more resilient in a mounting than the other locators, the one more resilient locator configured to define less constraint upon the vane position in the arrangement by relative distortion and/or displacement in the mounting compared to other locators.
  • the locators are tangs laterally extending from the component in order to provide location, and are secured in respective slots.
  • the tangs may allow a degree of relative sliding movement.
  • the locators are arranged in pairs, the locators of each pair being laterally opposed to each other.
  • the more resilient locator may comprise a narrower section segment for reduced interference clearance compared to the other locators within the arrangement.
  • the more resilient locator may comprise a locator portion having a greater unsupported length in comparison to the other locators whereby the locator portion has less resistance to deflection.
  • the more resilient locator may be formed as a spring structure.
  • the more resilient locator may incorporate cut-outs for increased relative flexibility compared to the other locators.
  • the more resilient locator may incorporate a curved joint possessing varying resistance to deformation.
  • the curved joint may lead to a tang of a form as described above, in the eleventh paragraph.
  • the more resilient locator may be formed from a less rigid material than the other locators.
  • the other locators may provide three distinct displacement and three rotational constraints upon the vane in use.
  • the mounting arrangement may be formed from an organic matrix composite material.
  • Captive type locators in the form of an entrant member, such as tangs, held within opposed grooves are well known and depend upon interference for location.
  • platforms at either end are associated with tang members which extend into slots or grooves in respective mounting rings and outer casings (see Fig. 1 ).
  • tang members which extend into slots or grooves in respective mounting rings and outer casings (see Fig. 1 ).
  • there are four associated locators that is to say the tangs presenting constraint upon the vane and its platform in generally opposed pairs.
  • all that is required is three locators to ensure vane component position. It will be appreciated that there are also possible requirements with respect to friction damping and gas sealing, but nevertheless over-constraint leads to limitations upon mechanical performance.
  • one of the locators is configured as a resilient locator.
  • it is configured to provide a reduced or relatively lower interference or other fixation of location in comparison with the other locators.
  • one of the four fixing points that is to say one of the tangs extending into the mounting ring or casing slot, is rendered more compliant by being resilient.
  • the inner platform of the vane is generally much smaller than the outer it is likely that one its inner locators will be chosen as that which is more resilient and compliant under loading.
  • the stiffness of the region between the vane platform and the locator is reduced so that this particular locator is more compliant.
  • generally tangs will enter slots in order to provide the locator fixings and so it is one of these tangs which will be rendered more compliant.
  • a tang 37 as a more compliant locator will be arranged to have a thinner cross-section and so beam stiffness in comparison with the other more rigidly secured locator tangs utilised for positioning a vane 31.
  • a platform 32 of the vane 31 is secured to a tang member 33 through an adhesive layer 34 in a conventional manner.
  • the tang member 33 as shown has one tang 37 which is of a narrower cross-section in comparison with other tang locators (not shown).
  • the member 33 generally thickens at a portion 35 away from the compliant or resilient locator tang 37 in order to provide the thicker locator tangs (not shown) which are engaged with typically slots or grooves as described previously with regard to Fig. 1 in order to provide location of the component vane 31 in use. It is known that beam stiffness is proportional to thickness in a ratio of the power of three so a relatively small reduction in the thickness of the resilient locator tang 37 provides a relatively high variation in the compliance or resilience of the tang 37 in comparison with other locators (not shown).
  • the minimum number of locators are utilised in order to ensure component vane 31 position and so limit constraint upon that component 31 with respect to accommodating vibration or other loading upon the component vane 31 which may cause premature failure or mechanical ageing particularly about junctions between the vane 31 and the platform 32/tang member 33.
  • the locators utilised for locating a component vane 31 may be of an interference type where the tangs enter slots or grooves such that there is a close clearance fit between the entrant tang and the slot or groove.
  • the resilient locator tang 37 has a narrower cross-section and therefore the ability of the tang 37 to deform in compliance with loadings is enhanced in comparison with the other locators such that there are only three robust and substantially rigid locators.
  • best location of the vane component 31 is achieved with adequate surety with respect to position, but with a limitation with respect to constriction which may result in stresses and strains being applied to the arrangement due to the more compliant nature of the resilient locator tang 37.
  • Fig. 4 illustrates a second embodiment of a locator in accordance with the present invention in which a tang 47 is presented relative to a component vane 41 by attachment to a platform 42 through an adhesive layer 44.
  • the locator tang 47 is secured to a tang member 43 which is then secured to the platform 42 through the adhesive 44.
  • the tang 47 is secured with a greater unsupported length than with previous tangs (see Figs. 1 to 3 ).
  • a tang arm 45 extends with a longer and more oblique angle to present the tang 47.
  • the tang 47 may be deflected for compliance in the directions of arrowheads 46 under load deformation.
  • three of the locators may be of a conventional tang within a slot groove, whilst a fourth resilient locator may be as depicted in Fig. 4 to allow adjustments as a result of vibrational and other loadings presented upon the component vane 41.
  • the component vane 41 is appropriately located and positioned with the rigid three point locator requirements as described previously with the fourth locator provided by the resilient arrangement of a cantilevered tang arm 45 depicted in Fig. 4 which has a greater unsupported length and therefore susceptibility to deformation and so is less rigid for the purposes of engagement for location.
  • the arrangement depicted in Fig. 4 may also allow the spacing between the vane 41 and any neighbouring vanes or blades within a gas turbine engine to be reduced, and so axial length with regard to the engine.
  • the opposing locator as indicated previously will generally be of the more robust rigid interference type necessary to provide three point positioning of the component vane 41.
  • the outer casing provides a greater potential for such close spacing of the vanes, whereas with regard to the inner mounting ring of a much smaller circumference, such close association with adequate mounting of the vane may be more difficult.
  • a principal objective with respect to the present invention is to provide resilience or compliance with regard to the one locator in comparison with the other locators for the component in the arrangement.
  • Fig. 5 illustrates a further manner by which such compliance can be achieved.
  • a vane component 51 has a platform 52 secured to a tang member 53 by an adhesive layer 54.
  • the tang member 53 creates a tang arm 55 which has a relatively soft spring nature through creating a folded back Z or S configuration in order that a tang 57 is presented in use to a slot or groove as described previously with respect to Fig. 1 .
  • the tang locator 57 can be more readily displaced in the direction of arrowheads 56 than other locators as described previously of a conventional nature for presentation and location of the component vane 51.
  • Creation of the spring configuration in the tang arm 55 introduces a significant manufacturing step in provision of the tang member 53.
  • these tang members 33, 43, 53 and subsequent tang members described below are generally formed separately and secured to the platforms 52 through the adhesive layers as described. In such circumstances, forming the tang members 53 can be more readily achieved than through casting as part of the vane component 51/platform 52 combination.
  • the thickness of the tang arm 55 that the degree of spring provided and therefore resilience/compliance provided in the tang 57 can be adjusted as required for operational performance in use.
  • the relative positioning of the tang arm 55 may be adjusted through the final section 58 in terms of angle and length to again adjust the compliance of the tang 57 in its receptive slot or groove.
  • Fig. 6 illustrates a vane component 61 secured upon a platform 62 via an adhesive layer to a tang member 63.
  • a tang arm 65 is incorporated in the tang member 63 between the part secured through the adhesive 64 and an entrant locator tang 67 which in use is located within a slot or groove.
  • the tang arm 65 incorporates cut-out windows 68 which render the tang 67 more compliant to allow deformations in the direction of arrowheads 66 in use within the slot accommodating the tang 67.
  • the component vane 61 can be adequately located by three other relatively rigid locators in accordance with conventional three point displacement and rotation resistance, whilst by means of a locator as depicted in Fig. 6 , no further constriction is placed upon adjustment of the mounting arrangement in order to accommodate loadings upon the component vane 61 as a result of vibration or blading, etc.
  • the windows 68 will generally be distributed to achieve the desired enhanced flexibility for compliance and resilience in comparison with the other more rigid locators (not shown).
  • the windows 68 may as indicated simply be of an rectangular shape or themselves be machined, particularly in relation to orientation or shape, to facilitate deformation either symmetrically or asymmetrically as required for best resilience and compliance response in use.
  • the windows can be a variety of shapes normally the geometry would be chosen to avoid corners, as these would be stress raisers.
  • a component is secured upon a platform and this platform is then secured to a locator or locators as appropriate.
  • loads are transferred through the platform to the respective locators, typically as depicted locator tangs entering slots or grooves in respective casing or mounting rings.
  • the platform may be arranged whereby the vane component is variably secured across the platform.
  • the joint to secure the vane to the platform is wavy with respect to its resilience as a locator. In such circumstances effectively a further locator is provided in the form of a joint across the platform.
  • Fig. 7 illustrates this fifth embodiment of the present invention.
  • a vane component 71 is presented across the platform 72 and secured by a locator depicted as a curved joint 73 between them.
  • the curved joint 73 will be determined to optimise operational performance in order to balance any over-constraint loads caused by conventional interference tang locators in slot mounting arrangements under particular loading conditions or excitation frequencies presented to the vane 71.
  • the joint 73 acts as a normal locator for operational performance until such particular loading conditions or excitation frequencies are presented to the vane 71 whereupon due to the nature of the curve of the joint, variable slippage occurs for the desired resilient compliance as described previously to accommodate such loadings.
  • region 72a could extend below region 72b, and form a tang arm as shown in Fig. 4 , but where the joint line is now curved.
  • Fig. 8 illustrates a sixth embodiment of the invention.
  • a vane component 81 is secured upon a platform 82 via an adhesive layer 84 to a tang member 83.
  • a tang arm 85 is incorporated in the tang member 83 between the part secured through the adhesive 84 and an entrant locator tang 87 which in use is located within a slot or groove.
  • a step 89 is provided between the tang arm 85 and the part of the tang member 83 secured through the adhesive 84.
  • the compliance of the tang arm 85 may be altered to achieve the desired flexibility, as described for the previous embodiments.
  • the presence of the step 89 may also reduce the tendency for the adhesive bond between the tang member 83 and the adhesive 84 to break at the point where the two separate.
  • Fig. 9 shows a further embodiment of the invention.
  • This embodiment is generally similar to that shown in Fig. 4 , but the adhesive 94 terminates further along the platform 92, away from the junction between the tang member 93 and the tang arm 95. Because the adhesive bond is over a shorter length of the tang arm 93, the locator tang 97 will tend to have a higher flexibility than an otherwise equivalent arrangement, for example as shown in Fig. 4 . Also, as in the previous embodiment, this configuration may reduce the tendency for the adhesive bond between the tang member 83 and the adhesive 84 to break at the point where the two separate.
  • the resilient locator for the component may be simply formed from a material having a different, that is to say less rigid, nature than the other locators utilised with respect to providing location and positioning of the component in use.
  • a tang arm or tang entrant in a slot may be formed from a material having a lower Young's modulus than for the other locators, or where the locators are formed from composite materials the outer layers of the composite may be formed from such lower Young's modulus materials in order to create a less rigid effect and therefore compliance in accordance with the present invention.
  • the locators in the form of tangs located within slots in accordance with the present invention would be formed from organic matrix composites in order to achieve the desired effects with respect to altering the compliance of one particular resilient locator in comparison with the other locators.
  • metallic materials with an appropriate local thinning of the locator in the form of a tang arm at the point where it joins the platform such that the tang end is therefore rendered more compliant in comparison with other locators in which there is no such localised thinning.
  • Such thinning may be achieved through creation of a rolled sheet with a bulge in the roller to give a local pocket in the eventually formed platform or alternatively such localised thinning may be achieved through masked chemical etching.

Landscapes

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

Claims (13)

  1. Agencement de montage d'aube directrice pour un moteur thermique de type à turbine à gaz, (31, 41, 51, 61, 71, 81, 91), l'agencement de montage d'aube directrice comprenant quatre organes positionneurs, agencés de manière à, en utilisation, sensiblement retenir l'aube directrice en position, l'agencement étant caractérisé de manière qu'un des organes positionneurs (37, 47, 57, 67, 87, 97) soit plus élastique dans un montage (8) que les autres organes positionneurs (7), l'organe positionneur (37, 47, 57, 67, 87, 97) plus élastique étant configuré pour définir moins de contraintes à la position de l'aube directrice dans l'agencement, sous l'effet d'une distorsion relative et/ou d'un déplacement relatif dans le montage (8), par rapport aux autres organes positionneurs (7).
  2. Agencement selon la revendication 1, dans lequel les organes positionneurs (7, 37, 47, 57, 67, 87, 97) sont des pattes s'étendant latéralement à partir du composant, de manière à fournir un positionnement.
  3. Agencement selon la revendication 2, dans lequel les pattes (7, 37, 47, 57, 67, 87, 97) sont fixées dans des fentes (8) respectives.
  4. Agencement selon la revendication 2 ou la revendication 3, dans lequel les pattes (7, 37, 47, 57, 67, 87, 97) permettent un certain degré de coulissement relatif.
  5. Agencement selon l'une quelconque des revendications précédentes, dans lequel les organes positionneurs sont agencés par paires, les organes positionneurs de chaque paire étant opposés latéralement les uns aux autres.
  6. Agencement selon l'une quelconque des revendications précédentes, dans lequel l'organe positionneur (37) plus élastique comprend un segment à section plus étroite, de manière à fournir un jeu à interférence réduite par rapport aux autres organes positionneurs (7) se trouvant dans l'agencement.
  7. Agencement selon l'une quelconque des revendications 1 à 5, dans lequel l'organe positionneur plus élastique comprend une partie d'organe positionneur (45, 47) présentant une longueur non supportée plus grande que pour les autres organes positionneurs (7), de manière que la partie d'organe positionneur (45, 47) présente une plus faible résistance à la flexion.
  8. Agencement selon l'une quelconque des revendications 1 à 5, dans lequel l'organe positionneur (57) plus élastique est réalisé sous forme de structure formant ressort.
  9. Agencement selon l'une quelconque des revendications 1 à 5, dans lequel l'organe positionneur (67) plus élastique présente des découpures (68) destinées à augmenter la flexibilité relative par rapport aux autres organes positionneurs (7).
  10. Agencement selon l'une quelconque des revendications 1 à 5, dans lequel l'organe positionneur plus élastique incorpore un joint (73) courbe, présentant une résistance à la déformation variable.
  11. Agencement selon l'une quelconque des revendications précédentes, dans lequel l'organe positionneur plus élastique est formé en un matériau moins rigide que les autres organes positionneurs.
  12. Agencement selon l'une quelconque des revendications précédentes, dans lequel les autres organes positionneurs (7) imposent à l'aube directrice trois contraintes de translation et trois contraintes de rotation distinctes, en utilisation.
  13. Agencement selon l'une quelconque des revendications précédentes, dans lequel l'agencement de montage est formé à partir d'un matériau composite à phase dispersée organique.
EP05257826A 2005-12-19 2005-12-19 Disposition de montage d'une aube directrice de turbine à gaz Not-in-force EP1798378B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE602005021803T DE602005021803D1 (de) 2005-12-19 2005-12-19 Aufbauanordnung einer Gasturbinenleitschaufel
DK05257826.7T DK1798378T3 (da) 2005-12-19 2005-12-19 Monteringsarrangement til gasturbineskovl
AT05257826T ATE470784T1 (de) 2005-12-19 2005-12-19 Aufbauanordnung einer gasturbinenleitschaufel
EP05257826A EP1798378B1 (fr) 2005-12-19 2005-12-19 Disposition de montage d'une aube directrice de turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05257826A EP1798378B1 (fr) 2005-12-19 2005-12-19 Disposition de montage d'une aube directrice de turbine à gaz

Publications (2)

Publication Number Publication Date
EP1798378A1 EP1798378A1 (fr) 2007-06-20
EP1798378B1 true EP1798378B1 (fr) 2010-06-09

Family

ID=36143218

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05257826A Not-in-force EP1798378B1 (fr) 2005-12-19 2005-12-19 Disposition de montage d'une aube directrice de turbine à gaz

Country Status (4)

Country Link
EP (1) EP1798378B1 (fr)
AT (1) ATE470784T1 (fr)
DE (1) DE602005021803D1 (fr)
DK (1) DK1798378T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2456770A (en) * 2008-01-22 2009-07-29 Rolls Royce Plc A stator vane for a gas turbine engine
FR2935430B1 (fr) * 2008-08-26 2012-03-09 Snecma Turbine haute-pression de turbomachine amelioree, secteur de distributeur et moteur d'aeronef associes
US9447693B2 (en) * 2012-07-30 2016-09-20 United Technologies Corporation Compliant assembly

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
GB2037901B (en) * 1978-11-25 1982-07-28 Rolls Royce Nozzle guide vane assembly
DE3003470C2 (de) * 1980-01-31 1982-02-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbinenleitschaufelaufhängung für Gasturbinenstrahltriebwerke
CA2070511C (fr) * 1991-07-22 2001-08-21 Steven Milo Toborg Support de distributeur de turbine
US5584654A (en) * 1995-12-22 1996-12-17 General Electric Company Gas turbine engine fan stator
DE102004006706A1 (de) * 2004-02-11 2005-08-25 Mtu Aero Engines Gmbh Dämpfungsanordnung für Leifschaufeln

Also Published As

Publication number Publication date
DE602005021803D1 (de) 2010-07-22
DK1798378T3 (da) 2010-10-04
ATE470784T1 (de) 2010-06-15
EP1798378A1 (fr) 2007-06-20

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