EP3176388A1 - Segment d'aube directrice à sécurité radiale - Google Patents

Segment d'aube directrice à sécurité radiale Download PDF

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Publication number
EP3176388A1
EP3176388A1 EP16201368.4A EP16201368A EP3176388A1 EP 3176388 A1 EP3176388 A1 EP 3176388A1 EP 16201368 A EP16201368 A EP 16201368A EP 3176388 A1 EP3176388 A1 EP 3176388A1
Authority
EP
European Patent Office
Prior art keywords
radial
securing element
shroud
vane segment
outer shroud
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
EP16201368.4A
Other languages
German (de)
English (en)
Other versions
EP3176388B1 (fr
Inventor
Markus Schlemmer
Manfred Feldmann
Rudolf Stanka
Oliver Thiele
Bernd Kislinger
Manuel Hein
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
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3176388A1 publication Critical patent/EP3176388A1/fr
Application granted granted Critical
Publication of EP3176388B1 publication Critical patent/EP3176388B1/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
    • B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material

Definitions

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16201368.4A 2015-12-04 2016-11-30 Segment d'aube directrice à sécurité radiale Active EP3176388B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015224378.8A DE102015224378A1 (de) 2015-12-04 2015-12-04 Leitschaufelsegment mit Radialsicherung

Publications (2)

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

Family

ID=57471672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16201368.4A Active EP3176388B1 (fr) 2015-12-04 2016-11-30 Segment d'aube directrice à sécurité radiale

Country Status (4)

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

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016202519A1 (de) * 2016-02-18 2017-08-24 MTU Aero Engines AG Leitschaufelsegment für eine Strömungsmaschine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1431517A2 (fr) * 2002-12-20 2004-06-23 General Electric Company Aubes statoriques d'une turbine
DE602004003757T2 (de) * 2003-07-23 2007-10-11 Alstom Technology Ltd. Verfahren zur Aufbereitung und Verfahren zur Herstellung einer Turbinenschaufel
EP2811118A1 (fr) * 2013-06-06 2014-12-10 MTU Aero Engines GmbH Segment d'aube directrice d'une turbomachine et turbine
US20150125289A1 (en) * 2012-05-16 2015-05-07 Snecma Turbomachine distributor and production method
EP2878769A1 (fr) * 2013-11-27 2015-06-03 MTU Aero Engines GmbH Aube rotorique d'une turbine à gaz avec des léchettes d'étanchéité de plateforme

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL2615243T3 (pl) 2012-01-11 2017-12-29 MTU Aero Engines AG Segment wieńca łopatkowego do maszyny przepływowej i sposób jego wytwarzania
JP5962915B2 (ja) * 2012-10-29 2016-08-03 株式会社Ihi タービンノズルの固定部構造及びこれを用いたタービン
US9835038B2 (en) * 2013-08-07 2017-12-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
GB201417150D0 (en) * 2014-09-29 2014-11-12 Rolls Royce Plc Carriers for turbine components

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1431517A2 (fr) * 2002-12-20 2004-06-23 General Electric Company Aubes statoriques d'une turbine
DE602004003757T2 (de) * 2003-07-23 2007-10-11 Alstom Technology Ltd. Verfahren zur Aufbereitung und Verfahren zur Herstellung einer Turbinenschaufel
US20150125289A1 (en) * 2012-05-16 2015-05-07 Snecma Turbomachine distributor and production method
EP2811118A1 (fr) * 2013-06-06 2014-12-10 MTU Aero Engines GmbH Segment d'aube directrice d'une turbomachine et turbine
EP2878769A1 (fr) * 2013-11-27 2015-06-03 MTU Aero Engines GmbH Aube rotorique d'une turbine à gaz avec des léchettes d'étanchéité de plateforme

Also Published As

Publication number Publication date
ES2700953T3 (es) 2019-02-20
US10370989B2 (en) 2019-08-06
EP3176388B1 (fr) 2018-11-14
DE102015224378A1 (de) 2017-06-08
US20170159466A1 (en) 2017-06-08

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