EP1045115A1 - Bouclier thermique pour turbine à gaz - Google Patents

Bouclier thermique pour turbine à gaz Download PDF

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Publication number
EP1045115A1
EP1045115A1 EP99810297A EP99810297A EP1045115A1 EP 1045115 A1 EP1045115 A1 EP 1045115A1 EP 99810297 A EP99810297 A EP 99810297A EP 99810297 A EP99810297 A EP 99810297A EP 1045115 A1 EP1045115 A1 EP 1045115A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
carrier
segments
segment
gas turbine
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.)
Withdrawn
Application number
EP99810297A
Other languages
German (de)
English (en)
Inventor
Christoph Nagler
Christof Pfeiffer
Ulrich Wellenkamp
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP99810297A priority Critical patent/EP1045115A1/fr
Publication of EP1045115A1 publication Critical patent/EP1045115A1/fr
Withdrawn legal-status Critical Current

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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

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a heat shield for a gas turbine, which heat shield as coaxial ring is formed around the turbine axis and consists of a A plurality of individual heat shield segments arranged one behind the other in the circumferential direction composed, which is releasably attached to the Casings of the gas turbine are connected, and wherein securing means are provided are, which the heat shield segments each against displacement or rotation secure in the circumferential direction.
  • Such a heat shield is e.g. known from US-A-3,864,056.
  • Guide vanes and heat shield segments must be attached in gas turbines in such a way that they are both in the axial direction, i.e. in the direction of the turbine axis, as well are fixed in the circumferential direction.
  • the axial fixation is usually carried out by means of a stop.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention consists in the already existing parts (fasteners and heat shield segments) so that they can be modified without complicated additional aids in the manner of an anti-rotation device engage with each other stand.
  • the securing element can, for example, be in the heat shield segment inserted or screwed in pin or pin.
  • a first preferred embodiment of the heat shield according to the invention is characterized in that the fastening means an annular carrier comprise, which concentrically surrounds the heat shield, and on which the Heat shield segments are attached by means of laterally arranged brackets, and that the securing element protrudes radially outwards on the heat shield segment molded nose is formed, which in the provided on the carrier Recess engages.
  • a second preferred embodiment is characterized in that the Carrier and the heat shield segments in the axial direction approximately the same width have that the nose is arranged on the edge of the heat shield segment, and that the associated recess is designed as a radial groove on the edge of the carrier is.
  • the invention is based on a gas turbine configuration as comparable in US-A-3,864,056.
  • the blades are in the hot gas area of the rotor each surrounded by an annular heat shield, which consists of a A plurality of ring segment-shaped heat shield segments is formed.
  • the Heat shield segments are attached to the (inner) housing with suitable fasteners attached to the gas turbine. 1 of the present application, the in a section transverse to the circumferential direction (section plane BB in FIG. 2) a preferred one Embodiment of a heat shield according to the invention shows each heat shield segment 14 by means of two brackets 12 and 13 on an annular Carrier 11 attached, which concentrically surrounds the heat shield segments 14.
  • the brackets 12 and 13 grip with hook-shaped inwards Ends in corresponding grooves 15 and 16 on the long sides of the heat shield segments 14 are arranged.
  • the heat shield segments 14 are through Brackets 12, 13 secured against axial displacement.
  • each heat shield segment 14 To prevent rotation in the circumferential direction is on the top or outside of each heat shield segment 14 a protruding radially outward Molded nose 18, with which the segment in a corresponding recess 17 engages the carrier 11. 1 is the Molded nose 18 on the right edge of the heat shield segment 14. Because heat shield segment 14 and carrier have approximately the same width, is the corresponding Recess 17 placed accordingly on the right edge of the carrier 11. This opens up the possibility of the recess 17 in a simple manner as being in a radial In the direction extending groove in the right outside of the carrier 11, as can be seen from Fig. 2. Instead of or in addition to (Right) nose 18 can be provided on the opposite (left) side become.
  • the lateral arrangement of the anti-rotation device 17, 18 then has one in particular Advantage if the cavity 19 between the heat shield segment 14 and the Carrier 11 is used for cooling the heat shield segment 14 with cooling air.
  • the cavity 19 is in this way without restrictions and obstructions available for cooling.
  • the invention results in a heat shield for a gas turbine, at which with slight changes to the already existing parts an easy to manufacture, assemble and functionally secure anti-twist device for the heat shield segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99810297A 1999-04-12 1999-04-12 Bouclier thermique pour turbine à gaz Withdrawn EP1045115A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP99810297A EP1045115A1 (fr) 1999-04-12 1999-04-12 Bouclier thermique pour turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99810297A EP1045115A1 (fr) 1999-04-12 1999-04-12 Bouclier thermique pour turbine à gaz

Publications (1)

Publication Number Publication Date
EP1045115A1 true EP1045115A1 (fr) 2000-10-18

Family

ID=8242761

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810297A Withdrawn EP1045115A1 (fr) 1999-04-12 1999-04-12 Bouclier thermique pour turbine à gaz

Country Status (1)

Country Link
EP (1) EP1045115A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2867224A1 (fr) * 2004-03-04 2005-09-09 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
FR2922589A1 (fr) * 2007-10-22 2009-04-24 Snecma Sa Controle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine
FR3003895A1 (fr) * 2013-03-26 2014-10-03 Snecma Anneau d'etancheite entre un carter fixe et une partie rotative d'une turbine basse pression

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3864056A (en) 1973-07-27 1975-02-04 Westinghouse Electric Corp Cooled turbine blade ring assembly
GB2068270A (en) * 1980-01-31 1981-08-12 Mtu Muenchen Gmbh Assembling turbines
EP0356305A1 (fr) * 1988-08-18 1990-02-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Anneau de stator de turbine associé à un support de liaison au carter de turbine
GB2239678A (en) * 1989-12-08 1991-07-10 Rolls Royce Plc Gas turbine engine shroud assembly
WO1995012056A1 (fr) * 1993-10-27 1995-05-04 United Technologies Corporation Systeme de montage et d'etancheite pour element d'enveloppe de turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3864056A (en) 1973-07-27 1975-02-04 Westinghouse Electric Corp Cooled turbine blade ring assembly
GB2068270A (en) * 1980-01-31 1981-08-12 Mtu Muenchen Gmbh Assembling turbines
EP0356305A1 (fr) * 1988-08-18 1990-02-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Anneau de stator de turbine associé à un support de liaison au carter de turbine
GB2239678A (en) * 1989-12-08 1991-07-10 Rolls Royce Plc Gas turbine engine shroud assembly
WO1995012056A1 (fr) * 1993-10-27 1995-05-04 United Technologies Corporation Systeme de montage et d'etancheite pour element d'enveloppe de turbine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2867224A1 (fr) * 2004-03-04 2005-09-09 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
EP1577506A1 (fr) * 2004-03-04 2005-09-21 Snecma Dispositif de mainten axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
US7360989B2 (en) 2004-03-04 2008-04-22 Snecma Device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine
CN1664318B (zh) * 2004-03-04 2010-12-08 斯奈克玛公司 用于轴向保持涡轮机高压涡轮环形垫片段的装置
FR2922589A1 (fr) * 2007-10-22 2009-04-24 Snecma Sa Controle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine
EP2053200A1 (fr) * 2007-10-22 2009-04-29 Snecma Contrôle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine
US8100635B2 (en) 2007-10-22 2012-01-24 Snecma Control of clearance at blade tips in a high-pressure turbine of a turbine engine
FR3003895A1 (fr) * 2013-03-26 2014-10-03 Snecma Anneau d'etancheite entre un carter fixe et une partie rotative d'une turbine basse pression

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