EP2336496A1 - Gasturbinentriebwerk mit einer Leitschaufeldichtungsanordnung - Google Patents

Gasturbinentriebwerk mit einer Leitschaufeldichtungsanordnung Download PDF

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Publication number
EP2336496A1
EP2336496A1 EP09179061A EP09179061A EP2336496A1 EP 2336496 A1 EP2336496 A1 EP 2336496A1 EP 09179061 A EP09179061 A EP 09179061A EP 09179061 A EP09179061 A EP 09179061A EP 2336496 A1 EP2336496 A1 EP 2336496A1
Authority
EP
European Patent Office
Prior art keywords
segment
rail
arrangement
engine
platform
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
EP09179061A
Other languages
English (en)
French (fr)
Other versions
EP2336496B1 (de
Inventor
David Butler
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09179061.8A priority Critical patent/EP2336496B1/de
Publication of EP2336496A1 publication Critical patent/EP2336496A1/de
Application granted granted Critical
Publication of EP2336496B1 publication Critical patent/EP2336496B1/de
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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/57—Leaf 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
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to a gas turbine engine.
  • the present invention relates to a gas turbine engine including a segment of an annular guide vane assembly, in use of the engine the segment directing hot combustion gases onto rotor blades of the engine, the segment including a platform disposed at a side of the segment radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of hot combustion gases through the segment, the trailing edge portion including a rail that extends radially inwardly/outwardly from the trailing edge portion, the engine also including a support and cooling arrangement for supporting the segment and directing a cooling fluid to cool the segment, the arrangement being located radially inward/outward of the platform, the arrangement including a flange part that extends radially outwardly/inwardly from the arrangement.
  • a gas turbine engine including a segment of an annular guide vane assembly, in use of the engine the segment directing hot combustion gases onto rotor blades of the engine, the segment including a platform disposed at a side of the segment radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of hot combustion gases through the segment, the trailing edge portion including a rail that extends radially inwardly/outwardly from the trailing edge portion, the engine also including a support and cooling arrangement for supporting the segment and directing a cooling fluid to cool the segment, the arrangement being located radially inward/outward of the platform, the arrangement including a flange part that extends radially outwardly/inwardly from the arrangement, characterised in that the arrangement further includes a leaf seal and at least one retaining pin, the retaining pin(s) extending through the leaf seal, the rail, and the flange part, thereby (i) to secure
  • the part of the gas turbine engine comprises a segment 1 of an annular guide vane assembly of the engine, a support and cooling arrangement 3, and a rotor 5.
  • the axis of rotation of the engine would run horizontally in the drawing and would be disposed below that shown in the drawing.
  • Rotor 5 includes rotor blades 9 having blade roots 7.
  • Rotor 5 also includes a rotor disk (not shown) to which rotor blades 9 are secured by means of their blade roots 7.
  • Segment 1 directs hot combustion gases travelling as indicated by arrow A in the drawing, onto rotor blades 9. It can be seen that the drawing shows only the radially inner and rearward part of segment 1, only the radially outer and rearward part of support and cooling arrangement 3, and only the radially inner and forward part of rotor blades 9 including their blade roots 7.
  • Segment 1 includes a guide vane 11 and a platform 13 at the radially inward side of segment 1. Segment 1 may further include one or more additional guide vanes 11, and a platform at the radially outward side of segment 1. All the guide vanes would extend radially between the radially inner and outer platforms. The radially inner and outer platforms would be arcuate in form. The view of segment 1 shown in the drawing is that seen looking in a circumferential direction.
  • the complete annular guide vane assembly comprises a number of segments 1 arranged in a ring or annulus.
  • the plane of the annulus is a vertical plane perpendicular to the plane of the paper - there are segments 1 adjacent to and extending contiguous with the segment 1 shown in the drawing both below and above the plane of the paper (i.e. in the circumferential direction).
  • Platform 13 has a trailing edge portion 15 downstream with respect to the flow A of hot combustion gases through segment 1.
  • Trailing edge portion 15 includes a rail 17 that extends radially inwardly from portion 15, from the radially inwardly directed face 19 of platform 13.
  • Rail 17 is shown in perspective at the bottom of the drawing. In this perspective view rail 17 is upside down as compared to its orientation above in the drawing. Rail 17 runs along trailing edge portion 15, parallel to the final trailing tip 21 of portion 15. Thus, rail 17 runs circumferentially in the engine. The circumferential extent of rail 17 is substantially the same as that of platform 13. Although rail 17 is shown as straight in the perspective view it is in fact slightly curved so that its base 22 sits in abutting relationship along its length with radially inwardly directed face 19 of platform 13 (platform 13 is of course slightly curved so as to extend circumferentially and have a radius, as is known in the art). The height of rail 17 is not the same along its length - rail 17 includes a raised portion 23 at each end and a depression 25 between portions 23. Portions 23 include holes 27. Depression 25 makes it easier for rail 17 to flex with flexing of platform 13.
  • Trailing edge portion 15 includes a channel 28 that extends in a generally downstream direction from radially inwardly directed face 19 of platform 13 to radially outwardly directed face 30 of platform 13.
  • Support and cooling arrangement 3 supports segment 1 and directs a cooling fluid to cool segment 1.
  • Arrangement 3 is located radially inward of platform 13.
  • Arrangement 3 comprises a carrier ring 29, a metal leaf seal 31, two retaining pins 33 (only one of which is shown in the drawing), and a cooling plate 35.
  • Carrier ring 29 includes a flange part comprising main and subsidiary flanges 37, 39 that extend radially outwardly from carrier ring 29.
  • the reduced thickness of subsidiary flange 39 as compared to main flange 37 creates a recessed area 41 that runs around the periphery of carrier ring 29.
  • Carrier ring 29, including its flanges 37, 39, is centred on the axis of rotation of the engine. In the drawing the plane of carrier ring 29 is a vertical plane perpendicular to the plane of the paper.
  • Leaf seal 31 extends into and out of the paper, and has a length substantially the same as rail 17 of segment 1.
  • Retaining pins 33 extend through leaf seal 31, then through holes 27 in raised portions 23 of rail 17, and then into holes 43 in subsidiary flange 39 (holes 43 in subsidiary flange 39 corresponding in position to holes 27 in rail 17).
  • Pins 33 have an interference fit with one of rail 17 and subsidiary flange 39, and have a tight fit, less tight than an interference fit, with the other of rail 17 and subsidiary flange 39.
  • Pins 33 have a relatively loose fit with leaf seal 31.
  • Cooling plate 35 is disposed just below and parallel to radially inwardly directed face 19 of platform 13, thereby to form a cooling channel 45 between plate 35 and face 19.
  • Segment 1 includes a further rail (not shown) parallel to rail 17 that extends radially inwardly from a leading edge portion (not shown) of platform 13. The downstream end of cooling plate 35 locates into rail 17 and the upstream end of the plate (not shown) locates into the further rail.
  • Cooling plate 35 includes a number of cooling holes 47.
  • Cooling fluid is supplied to a cavity 49 present between carrier ring 29 and segment 1 upstream of main and subsidiary flanges 37, 39, rail 17, leaf seal 31, and retaining pins 33.
  • Radially outwardly directed jets of cooling fluid are formed by cooling holes 47 in cooling plate 35. These jets impinge upon and cool radially inwardly directed face 19 of platform 13.
  • Some of the cooling fluid in cooling channel 45 travels through platform 13 to the interior of guide vane 11, as indicated by arrow B, and some travels via channel 28 in trailing edge portion 15 to film cool that part of radially outwardly directed face 30 of platform 13 downstream of the exit from channel 28.
  • cooling fluid is supplied to a region 51 between carrier ring 29 and rotor blades 9, as indicated by arrow C. This fluid travels generally upwards in the drawing to join the fluid that leaves channel 28.
  • Retaining pins 33 are dual function: they both (i) secure segment 1 to carrier ring 29 to determine the radial position of segment 1, and (ii) retain leaf seal 31 in a position to seal the interface 53 between rail 17 and flanges 37, 39 against the ingress of cooling fluid from cavity 49.
  • This dual function on the part of retaining pins 33 simplifies the form of the engagement between segment 1 and support and cooling arrangement 3. Further, advantageously, leaf seal 31 achieves the sealing of interface 53 without appreciably adding to the stiffness of platform 13.
  • Rail 17 runs along circumferentially extending recessed area 41, and upstream directed face 55 of rail 17 lies flush with (in the same plane as) upstream directed face 57 of main flange 37.
  • Planar leaf seal 31 lies against flush faces 55 and 57 and bridges interface 53 between rail 17 and flanges 37, 39.
  • Downstream directed face 59 of rail 17 opposes upstream directed face 61 of subsidiary flange 39.
  • holes 27, 43 in rail 17 and holes 43 in subsidiary flange 39 corresponds to the diameter of the shafts of retaining pins 33, and so the form of holes 27, 43 is such as to determine not only the radial but also the circumferential position of segment 1. If it is desired to permit adjustment of the circumferential position of segment 1 then this can be achieved by holes 27, 43 in rail 17 and/or subsidiary flange 39 comprising circumferentially extending slots.
  • the radial and circumferential position of segment 1 can be determined, and yet circumferential thermal growth of segment 1 not constrained, by: the holes 27, 43 in respect of one of the two retaining pins 33 having diameters corresponding to the diameter of the shafts of the retaining pins, and either or both of the holes 27, 43 in respect of the other of the two retaining pins 33 comprising circumferentially extending slots.
  • the above description concerns a platform of a segment of an annular guide vane assembly, wherein the platform is disposed at the radially inward side of the segment. It is to be appreciated that the present invention could also be used in respect of a platform of a segment of an annular guide vane assembly, wherein the platform is disposed at the radially outward side of the segment.
  • An example of this would be as follows: (a) a support and cooling arrangement analogous to arrangement 3 would be located radially outward of the platform and would include flanges analogous to flanges 37, 39 that extend radially inwardly from the arrangement, and (b) the trailing edge portion of the platform would include a rail analogous to rail 17 that extends radially outwardly from the trailing edge portion.
  • the above description concerns a segment of an annular guide vane assembly wherein a number of the segments are arranged in a ring or annulus to construct the complete annular guide vane assembly. It is to be understood that in a limiting case the segment may be the complete annular guide vane assembly in that only one segment is required to construct the complete annular guide vane assembly, i.e. the complete annular guide vane assembly is made up of only one segment that is itself a full ring or annulus.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09179061.8A 2009-12-14 2009-12-14 Gasturbinentriebwerk mit einer Leitschaufeldichtungsanordnung Not-in-force EP2336496B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09179061.8A EP2336496B1 (de) 2009-12-14 2009-12-14 Gasturbinentriebwerk mit einer Leitschaufeldichtungsanordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09179061.8A EP2336496B1 (de) 2009-12-14 2009-12-14 Gasturbinentriebwerk mit einer Leitschaufeldichtungsanordnung

Publications (2)

Publication Number Publication Date
EP2336496A1 true EP2336496A1 (de) 2011-06-22
EP2336496B1 EP2336496B1 (de) 2016-06-15

Family

ID=42103004

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09179061.8A Not-in-force EP2336496B1 (de) 2009-12-14 2009-12-14 Gasturbinentriebwerk mit einer Leitschaufeldichtungsanordnung

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10156150B2 (en) 2013-03-14 2018-12-18 United Technologies Corporation Gas turbine engine stator vane platform cooling
CN109611163A (zh) * 2018-12-12 2019-04-12 中国北方发动机研究所(天津) 一种涡轮密封结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
US5797723A (en) * 1996-11-13 1998-08-25 General Electric Company Turbine flowpath seal
EP1340885A2 (de) * 2002-02-27 2003-09-03 General Electric Company Halterung für ein Dichtband bei einem Gasturbinenleitapparat
US20090110549A1 (en) * 2007-10-31 2009-04-30 General Electric Company Gas turbines having flexible chordal hinge seals
US20090169369A1 (en) * 2007-12-29 2009-07-02 General Electric Company Turbine nozzle segment and assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
US5797723A (en) * 1996-11-13 1998-08-25 General Electric Company Turbine flowpath seal
EP1340885A2 (de) * 2002-02-27 2003-09-03 General Electric Company Halterung für ein Dichtband bei einem Gasturbinenleitapparat
US20090110549A1 (en) * 2007-10-31 2009-04-30 General Electric Company Gas turbines having flexible chordal hinge seals
US20090169369A1 (en) * 2007-12-29 2009-07-02 General Electric Company Turbine nozzle segment and assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10156150B2 (en) 2013-03-14 2018-12-18 United Technologies Corporation Gas turbine engine stator vane platform cooling
CN109611163A (zh) * 2018-12-12 2019-04-12 中国北方发动机研究所(天津) 一种涡轮密封结构
CN109611163B (zh) * 2018-12-12 2021-05-11 中国北方发动机研究所(天津) 一种涡轮增压器密封结构

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EP2336496B1 (de) 2016-06-15

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