EP3428402A1 - Segment d'aube directrice à joint de décharge courbé - Google Patents

Segment d'aube directrice à joint de décharge courbé Download PDF

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Publication number
EP3428402A1
EP3428402A1 EP18179434.8A EP18179434A EP3428402A1 EP 3428402 A1 EP3428402 A1 EP 3428402A1 EP 18179434 A EP18179434 A EP 18179434A EP 3428402 A1 EP3428402 A1 EP 3428402A1
Authority
EP
European Patent Office
Prior art keywords
section
vane segment
guide vane
segment according
wall element
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.)
Granted
Application number
EP18179434.8A
Other languages
German (de)
English (en)
Other versions
EP3428402B1 (fr
Inventor
Markus Uecker
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 AG
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 AG filed Critical MTU Aero Engines AG
Publication of EP3428402A1 publication Critical patent/EP3428402A1/fr
Application granted granted Critical
Publication of EP3428402B1 publication Critical patent/EP3428402B1/fr
Active 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to a stator segment for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud and a radially inner shroud, which extend along a respective arc and together form a ring portion, wherein in the radial direction between the outer shroud and the inner shroud a plurality of guide vanes are arranged side by side in the circumferential direction, which are connected to the inner shroud and the outer shroud, preferably material fit, in particular in one piece, wherein the outer shroud comprises an axially forward sealing wall member and an axially rear sealing wall member, such that the outer shroud and the two sealing walls in longitudinal section form a trough-like profile, wherein at the axially front and / or rear sealing wall element at least one relief gap with an example substantially linearly extending Hau Is provided ptabites, which extends from a radial outer edge of the respective front and / or rear sealing wall element along the sealing wall element substantially radially
  • Relief joints in guide blade segments of gas turbines are used in particular to reduce the resulting thermal expansion in the component.
  • other areas can be protected in which cracks would lead to a vibration fatigue of the entire component, in particular an entire vane ring, which is formed by a plurality of vane segments.
  • the object of the invention is to provide a vane segment in which cracking is reduced.
  • the relief gap has at least one additional section which adjoins the main section radially inward, wherein the additional section is formed by at least one curved section.
  • an additional section with at least one curved section leads to an improved stress distribution in the region of the relief section having the main section and at least one curved section.
  • a base or joint bottom directly adjoining the linear main portion can be avoided, which counteracts the high stresses in the region of the base or joint floor.
  • the relief gap may extend in its radially innermost region in the circumferential direction and / or terminate in one or more end regions, which are located radially farther outward than a radially innermost region of the relief joint.
  • the additional portion has at least one curved first section and at least one curved second section, which are interconnected.
  • the first section may be curved with a first radius
  • the second section may be curved with a second radius, wherein the first radius may be greater than the second radius.
  • the two sections may be connected to a third radius.
  • the relief gap may have an optimized design with respect to the stress distribution. In this case, concentrating forces can be absorbed distributed along the differently curved sections so far in the ground or joint floor.
  • the first subsection may be arranged so as to have a tangent in the region of the connection to the main section which is substantially orthogonal to the main section runs.
  • the tangent to the main portion may also be a tangent to an arcuate circumferential direction imagined in the region of the terminal.
  • the first section may be formed convex so that it extends radially outward starting from the region of the connection to the main section.
  • the first section of the additional section of the relief joint thus has a radially inwardly convex curvature and extends substantially in the circumferential direction.
  • the first section forms an arc section whose chord extends substantially in the circumferential direction or substantially orthogonal to the radial direction.
  • the second subsection may be arranged to have a tangent parallel to the main section.
  • the second subsection may be convexly formed in the circumferential direction away from the main section.
  • the second subsection of the additional section of the relief joint thus has a convex curvature in a direction pointing away from the main section in the circumferential direction.
  • Such a second subsection extends substantially in the radial direction.
  • the second section forms an arc section whose chord extends substantially in the radial direction or substantially parallel to the main section or substantially orthogonal to the circumferential direction.
  • first section and the second section may preferably be concavely curved in the direction of the main section.
  • the main portion may be connected to the first portion, in particular, the main portion may be connected to a central region of the first portion.
  • a respective second subsection is arranged, which is connected to the first subsection.
  • the first section and the two adjoining second sections thereby form two hook-shaped sections connected to the main section.
  • the discharge gap with main section and the additional section which has the first section and two second section, form a kind of anchor shape of the relief joint.
  • the main section can be connected by means of a third section to a second section, in particular connected to a radially outer end of the second section.
  • the first subsection can adjoin the second subsection connected to the main section.
  • a further second subsection can adjoin the first subsection.
  • the third section and the subsequent second section can be S-shaped.
  • the third section and the second section flow into each other.
  • the third section is arranged between the main section and the one second section.
  • a type of hook shape or loop shape of the relief joint is formed by the sequence of third subsection, second subsection, first subsection and further second subsection.
  • S-shaped may mean in particular that the respective sections together form an S-shape and / or are curved in opposite directions.
  • the relief gap may be in the form of a question mark without a dot.
  • the main portion may, in this and other embodiments, be arranged in a circumferentially central region of the relief gap, e.g. within a range of 20% to 80%, or even 35% to 65% of the circumferential extent.
  • the relief gap can also be unbranched and / or have only a single end within the relevant front or rear sealing wall element.
  • a respective transition between the first section and the second section may be formed by a transition section, wherein preferably the transition section has a transition radius which is smaller than the first radius and smaller than the second radius.
  • the radii transitions can take place substantially tangentially, that is to say at a point at which a tangent to both adjacent but differently curved sections can be formed.
  • At least one second section can be assigned an end section.
  • the end portion with the same radius (second radius) may be curved as the second portion. But it is also conceivable that the end portion has a radius which is smaller than the second radius. In this case, the end portion is formed so that a tangent inclined to the main portion, in particular the main portion would cut.
  • the invention further relates to a gas turbine, in particular an aircraft gas turbine, with at least one compressor assembly, a combustion chamber and at least one turbine assembly, wherein the compressor assembly and / or the turbine assembly comprises at least one vane assembly by a plurality of circumferentially juxtaposed vane segments according to any one of the preceding claims is formed.
  • the present invention also includes such embodiments in which, alternatively or additionally, a corresponding relief gap is provided in the inner shroud.
  • the inner shroud may also (i.e., like the outer shroud) comprise an axial forward seal wall member and an axially rearward seal wall member such that the inner shroud and these two seal walls form a (reverse) trough-like profile in longitudinal section.
  • this alternative or additional radially inner relief joint may be provided on the axially front and / or rear sealing wall element (also) with a main section which extends essentially from a radial inner edge of the respective front and / or rear sealing wall element along the sealing wall element extends radially outward.
  • This additional or alternative radial relief joint may have at least one additional section which adjoins the main section radially on the outside and which may also be formed by at least one curved section.
  • This radially inner relief gap may be formed corresponding to or analogous to the previously defined and described in more detail below with reference to the figures (outer) relief joint, ie it may correspond to a mirrored outer relief joint according to one or more of the preceding and / or following embodiments or substantially correspond.
  • Fig. 1 shows in a simplified and schematic perspective view a section of a vane segment 10.
  • the vane segment comprises a plurality of circumferentially UR arranged side by side vanes 12.
  • Fig. 1 is shown in the radial direction RR outer and upper shroud 14 of the vane segment 10. with respect to an axial direction AR, an axially forward sealing wall element 18 and an axially rearward sealing wall element 20 are arranged on the shroud 14.
  • the outer shroud 14 and the two sealing walls 16, 18 form a trough-like profile in longitudinal section.
  • the sides 20, 22 of the sealing walls 16, 18 which are respectively remote from the formed trough form receptacles for connecting the vane segment 10 to further structural components, not shown, of a gas turbine.
  • a plurality of relief joints 24 are arranged along the circumferential direction.
  • the in the Fig. 1 Relief joints 24 shown extend substantially linearly in the radial direction RR and along the inclined sealing wall element 18th
  • the linearly extending relief joints 24 are disadvantageous in that high stresses or tensile forces occur at the base 28, which is particularly the case in FIG Fig. 5 in the upper voltage curve diagram and is marked with a white arrow.
  • Related investigations have shown values of over 1000MPa for a linear relief joint.
  • Fig. 2 shows in a simplified and schematic representation, which can also be designated as a plan view of the sealing wall element 18, a relief joint 24 according to a first embodiment.
  • the relief gap 24 comprises a main portion 26.
  • the relief gap 24 comprises a first portion 30 and in the example shown, two second portions 32, which adjoin the first portion in the circumferential direction left and right.
  • the first section 30 and the two second sections 32 together form an additional section 34 which, together with the main section 26, forms the entire relief gap 24.
  • the main section 26 merges into the first section 30, in particular the main section 26 is connected to the central section of the first section 30 in a central region of the first section 30 relative to the circumferential direction UR.
  • dotted lines 36 are drawn in, which illustrate a possible transition from one to the other subsection. It should be noted, however, that the purely schematically drawn lines 36 indicate only where a transition between subsections can be qualitatively arranged approximately.
  • the first section 30 has a radially inwardly convex curvature. It is thus concavely curved toward the main section 26.
  • the curvature is formed by a first radius R1, which in the Fig. 2 illustratively drawn as a dashed line.
  • R1 which in the Fig. 2 illustratively drawn as a dashed line.
  • the first section 30 extends substantially in the circumferential direction UR.
  • the first section 30 is curved so as to have a tangent T1 orthogonal to the radial direction RR.
  • the second section 32 has a convex curvature away from the main section 26 in the circumferential direction.
  • the curvature is formed by a second radius R2, which in the Fig. 2 illustratively drawn as a dashed line.
  • the second section 32 extends substantially in the radial direction RR. At least it runs in sections across the circumferential direction UR. In other words, it can also be said that the second subsection 32 is arranged to have a tangent T2 that is parallel to the radial direction or parallel to the main section 26.
  • the first radius R1 is greater than the second radius R2.
  • a transition section 38 may be provided in a region of the respective lines 36 or the transitions between two subsections 30, 32. Such a transition section may be curved with a third radius which is smaller than the first radius R1 and the second radius R2.
  • the purely schematically and simplified illustrated curvature of the additional portion 34 with different radii of the sections 30, 32 is preferably carried out in reality so that no cracks or steps arise along the changing curvatures.
  • the radii transitions between two adjacent partial or transition sections 30, 32, 38 are tangential.
  • the free ends 39 of the second sections 32 may also be provided by outlet sections 40, which are not shown in detail here.
  • Such outlet portions 40 have a fourth radius of curvature which is smaller than the second radius R2.
  • the second sections 32 or their free ends 39 can be aligned with the main section 26.
  • relief gap 24 has a kind of double hook shape or anchor shape.
  • Fig. 3 shows a second embodiment of a relief joint 24 with the main portion 26, a first portion 30 and two second portions 32nd Unlike in the embodiment of Fig. 2 the main section 26 is connected by means of a third section 42 with the right in the circumferential direction UR second section 32.
  • the third section 42 forms a counterbending to the adjoining second section 32.
  • These two sections 32, 42 form a kind of S-shaped connection between the main section 26 and the first section 30.
  • a transition section can also be provided at the transition between the third subsection 42 and the adjoining second subsection 32 in the region of the line 36. The same applies, of course, to the other transitions 38 between the second subsections 32 and the first subsection 30 at the lines 36, as stated above with reference to Fig. 2 has already been described.
  • the relief joint 24 according to Fig. 3 has a single free end 39 on the left second section. Also, this end 39 may be formed by a spout portion 40, as described above with reference to the Fig. 2 has already been described. Overall, results for the relief gap 24 according to Fig. 3 a kind of hook shape or loop shape.
  • Fig. 4 shows a modification of the relief joint 24 according to Fig. 2 , It has been shown that the relief gap does not necessarily have to have two second sections 32. Rather, a second section 32 may be provided on the first section 30 only on one side. Whether the second portion 32 in such a configuration with respect to the circumferential direction UR left or, as in the Fig. 4 is shown, right on the first section 30 is arranged, is arbitrary. With regard to the dimensions of the radii of curvature, essentially the same applies as for the embodiment according to FIG Fig. 2 , as well as for transition areas between the sections 30, 32nd
  • Fig. 5 shows purely illustratively the vane segment 10 of Fig. 1 , wherein simplified and purely illustrative relief joints 24 according to Fig. 2 and Fig. 3 are drawn.
  • This illustration serves only to show the arrangement of such relief joints with curved sections 30, 32.
  • the specific number of relief joints 24 on a vane segment 10 is arbitrary.
  • a plurality of similar or only similar relief joints 24 are provided for a vane segment 10.
  • a mix of relief joints, as in Fig. 5 thus, as a rule, this does not correspond to a real embodiment, but merely serves the purpose of illustration here.
  • FIG. 6 shows a typical voltage curve for a relief joint 24 according to an embodiment as shown in FIG Fig. 2 has been shown and explained there. It has been found that in the region of the transition from the main section 26 to the first section 30, a significantly reduced tension occurs due to the configuration of the relief joint with the curved sections Subsections 30, 32. It has been found, in particular, that the stresses in the region of interest at the radially inner end of the main section 26 are less than 500 MPa.
  • a vane ring may be formed by a plurality of vane segments 10 described above, which are arranged side by side in the circumferential direction.
  • Such a vane ring can be assigned to a compressor side or a turbine side of the gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18179434.8A 2017-07-11 2018-06-25 Segment d'aube directrice à joint de décharge courbé Active EP3428402B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017211866.0A DE102017211866A1 (de) 2017-07-11 2017-07-11 Leitschaufelsegment mit gekrümmter Entlastungsfuge

Publications (2)

Publication Number Publication Date
EP3428402A1 true EP3428402A1 (fr) 2019-01-16
EP3428402B1 EP3428402B1 (fr) 2020-10-28

Family

ID=62778726

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18179434.8A Active EP3428402B1 (fr) 2017-07-11 2018-06-25 Segment d'aube directrice à joint de décharge courbé

Country Status (4)

Country Link
US (1) US10731489B2 (fr)
EP (1) EP3428402B1 (fr)
DE (1) DE102017211866A1 (fr)
ES (1) ES2836120T3 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11814991B1 (en) * 2022-07-28 2023-11-14 General Electric Company Turbine nozzle assembly with stress relief structure for mounting rail
US11885241B1 (en) * 2022-07-28 2024-01-30 General Electric Company Turbine nozzle assembly with stress relief structure for mounting rail

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3781125A (en) * 1972-04-07 1973-12-25 Westinghouse Electric Corp Gas turbine nozzle vane structure
FR2929983A1 (fr) * 2008-04-14 2009-10-16 Snecma Sa Secteur de distributeur de turbine de turbomachine.
US20150300192A1 (en) * 2014-04-21 2015-10-22 Honeywell International Inc. Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof
DE102015207760A1 (de) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Heißgasführendes Gehäuse

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5071313A (en) * 1990-01-16 1991-12-10 General Electric Company Rotor blade shroud segment
US5593276A (en) * 1995-06-06 1997-01-14 General Electric Company Turbine shroud hanger
US7097422B2 (en) * 2004-02-03 2006-08-29 Honeywell International, Inc. Hoop stress relief mechanism for gas turbine engines
US7293957B2 (en) * 2004-07-14 2007-11-13 Power Systems Mfg., Llc Vane platform rail configuration for reduced airfoil stress
US7887299B2 (en) * 2007-06-07 2011-02-15 Honeywell International Inc. Rotary body for turbo machinery with mistuned blades
US8297416B2 (en) * 2008-11-07 2012-10-30 Kitchell Edward W Rotor device and method of making same
US8511089B2 (en) * 2009-07-31 2013-08-20 Rolls-Royce Corporation Relief slot for combustion liner
US8721289B2 (en) * 2009-10-30 2014-05-13 General Electric Company Flow balancing slot
US20150239052A1 (en) 2014-02-27 2015-08-27 Robert Bosch Tool Corporation Circular Saw Blade
US10648346B2 (en) * 2016-07-06 2020-05-12 General Electric Company Shroud configurations for turbine rotor blades
FR3068071B1 (fr) * 2017-06-26 2019-11-08 Safran Aircraft Engines Ensemble pour la liaison par palonnier entre un carter de turbine et un element annulaire de turbomachine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3781125A (en) * 1972-04-07 1973-12-25 Westinghouse Electric Corp Gas turbine nozzle vane structure
FR2929983A1 (fr) * 2008-04-14 2009-10-16 Snecma Sa Secteur de distributeur de turbine de turbomachine.
US20150300192A1 (en) * 2014-04-21 2015-10-22 Honeywell International Inc. Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof
DE102015207760A1 (de) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Heißgasführendes Gehäuse

Also Published As

Publication number Publication date
US10731489B2 (en) 2020-08-04
ES2836120T3 (es) 2021-06-24
DE102017211866A1 (de) 2019-01-17
US20190017397A1 (en) 2019-01-17
EP3428402B1 (fr) 2020-10-28

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