EP1408200A2 - Attachement de la bande de recouvrement d'une turbine - Google Patents

Attachement de la bande de recouvrement d'une turbine Download PDF

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Publication number
EP1408200A2
EP1408200A2 EP03009435A EP03009435A EP1408200A2 EP 1408200 A2 EP1408200 A2 EP 1408200A2 EP 03009435 A EP03009435 A EP 03009435A EP 03009435 A EP03009435 A EP 03009435A EP 1408200 A2 EP1408200 A2 EP 1408200A2
Authority
EP
European Patent Office
Prior art keywords
housing
segments
shroud
play
bearing
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
EP03009435A
Other languages
German (de)
English (en)
Other versions
EP1408200A3 (fr
EP1408200B1 (fr
Inventor
Stuart Lee
Harald Schiebold
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 Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1408200A2 publication Critical patent/EP1408200A2/fr
Publication of EP1408200A3 publication Critical patent/EP1408200A3/fr
Application granted granted Critical
Publication of EP1408200B1 publication Critical patent/EP1408200B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • 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

Definitions

  • the invention relates to a turbine shroud segment attachment with one housing and several in the housing arranged shroud segments.
  • the individual cover band segments are usually with a corresponding game loosely stored on the housing, being the play is dimensioned in the axial and circumferential directions so that this with a temperature-related expansion of the Shroud segments do not matter with regard to gap control plays. This ensures that the radial bearing in the housing and thus the radial gap to the rotor blade largely independent of the temperature of the shroud segments is.
  • a gap seal is known from DE 14 26 857 A1, in which individual shroud segments by means of a labyrinthine Construction on one another on their circumferential sides to grab. This creates a relatively large range of motion for the shroud segments created so that these at can move without thermal contraction or expansion to jam.
  • the invention has for its object a turbine shroud segment attachment to create which with simple Structure and simple operation a reliable control of the gap, even under extreme operating conditions.
  • the individual Cover tape segments with a circumferential play in the Housings are stored that the game at a predetermined Temperature difference between the housing and the cover band segments is reduced to zero and that the shroud segments by means of an elastically deformable bearing on the Housing are stored.
  • the turbine shroud segment attachment according to the invention is characterized by a number of significant advantages.
  • the cover band segments are arranged that the radial movement of the shroud segments matches one Expansion of the rotor blades takes place in this way to be able to control the play at the rotor blade tips.
  • the present invention proves to be particularly advantageous, if very large temperature differences between the housing (cold case) and the runner (high temperature of the Rotor disks) are present.
  • the Cover tape segments due to the existing play, stored in this way are that they expand thermally accordingly and can contract, takes place with the large described Temperature difference by overcoming the invention defined game a clamping of the individual cover band segments relative to the housing.
  • the individual Cover tape segments jammed into a single ring that is in terms of its degree of expansion and its thermal Expansion behavior behaves like a single component.
  • the jammed cover tape segments can become storage continue to expand accordingly thermally while for Overcoming the game the original large one Temperature difference is taken into account. This is done namely then a faster closing of the game to one Avoid touching the tips of the rotor blades.
  • the game of Shroud segments is formed in the circumferential direction.
  • the play in the axial direction in the area of the storage of the cover band segments.
  • the individual shroud segments close through thermal expansion into a single, uninterrupted Ring, which is subject to further thermal expansion behaves like a single component.
  • Such a continuous one Ring from the cover band segment elements behaves accordingly with regard to its radial change in diameter depending on the thermal expansion behavior of the housing.
  • the individual cover band segments are individually compared the housing is jammed. Here too they form with the housing one unit and can become more warm expand to match the thermal response of the housing or contract; the kinematics acting here is determined by appropriate design of the flexible suspension achieved.
  • this is done according to the invention intended "soft" storage of the individual shroud segments preferably by bearing elements, which are essentially T-shaped.
  • the bearing elements thus have lateral arms with a defined cross section Inclination and stiffness with which they oppose support the housing or by means of which they on the housing are held. Due to the elastic deformability these arms, combined with a corresponding storage on Housing, the movability of the shroud segments is relative possible to the housing and if jammed, the intended radial movement causes.
  • the shroud segments are thus cold Condition, due to the present game, relatively free movable while above a defined temperature difference, due to their thermal expansion, with the Housing are jammed.
  • FIG. 1 shows a partial area of a turbine stage a rotor blade 5 which is attached to a disc.
  • the tip 6 of the rotor blade is longitudinal along a gap several shroud segments 2 performed, such as 4 shows form a ring.
  • the cover band segments 2 are on one in a manner to be described Housing 1 stored.
  • the bearing arms 7 are essentially designed to be elastically deformable. These are about approaches 8 held in grooves 9 of the housing 1. This arrangement allows a movement of the shroud segments 2 radially Outside.
  • FIG. 6 shows a modified embodiment, in which the play in the axial direction as an axial gap 12th formed between the shroud segment 2 and the housing 1 is.
  • the cover band segments are heated 2 after a corresponding thermal expansion to a clamp in the housing 1.
  • the dotted lines make it moveable the cover band segments 2 with further thermal stress shown radially outwards. Due to the "soft" storage by means of the bearing elements 4 can cover band segments accordingly move radially outward to indicate heating the rotor blades 5 to maintain the corresponding Top game to respond.
  • FIG. 4 and 5 show two views in a sectional view perpendicular to the central axis 10 of the gas turbine.
  • the individual cover band segments 2 are particularly clear to recognize, as well as their elastic bearing elements 4.
  • the Fig. 4 shows a steady state in which a game 3 in the circumferential direction between the individual shroud segments is available.
  • the housing 1 has a predetermined one Rigidity, the same applies to the bearing elements 4.
  • the cover band segments 2 are also predetermined Provide strength or rigidity. Both the housing 1 as well as the shroud segments 2 each have a predetermined one thermal expansion or contraction behavior through which the gap 3 (play) results.
  • FIG. 5 shows a transitional operating state in which a radial gap 11 between the tips 6 of the rotor blades 5 is larger than, for example, that in FIG. 4 shown steady state. Due to the thermal Expansion of the shroud segments 2 is their distance in the circumferential direction closed, so that there is no more game. The shroud segments 2 thus form a fixed, in closed ring. Another thermal expansion leads to a radial displacement of this ring, which is possible by the elasticity of the bearing elements 4.
  • FIG. 2 and 3 show an exemplary embodiment of the game 3 according to the invention.
  • FIG. 2 corresponds to the state of FIG. 4. This results in a distance a between the cover band segments 2 and the housing 1.
  • a temperature state is present which is the following equation: T Deckbandsement - T casing ⁇ ⁇ T critical
  • FIG. 3 An operating state corresponding to FIG. 5 is shown in FIG. 3.
  • the shroud segments lie against each other.
  • 3 shows a thermal state, which can be expressed as follows: T Deckbandsement - T casing > ⁇ T critical
  • the underlying principle is therefore that the shroud segments thermally more or less at the same time and with the same rate of expansion as the rotor blades expand or contract. Due to the thermal expansion the cover band segments in the radial direction become temporary raised so that contact with the tips 6 of the rotor blades 5 is avoided (see for example Fig. 5). This temporary lifting of the cover band segments 2 takes place by appropriate dimensioning of the gap or. game 3, so that this is at a predetermined thermal Situation closes.
  • the width of the game 3 thus changes with the temperature difference between the shroud segment 2 and the housing 1 or the bearing ring or storage area on which the shroud segments 2 are stored.
  • the cover tape segments thus jam in the circumferential direction and form a closed Ring, which then turns into thermal expansion its diameter changes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Plates (AREA)
EP03009435A 2002-10-10 2003-04-25 Attachement de la bande de recouvrement d'une turbine Expired - Fee Related EP1408200B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10247355 2002-10-10
DE10247355A DE10247355A1 (de) 2002-10-10 2002-10-10 Turbinendeckbandsegmentbefestigung

Publications (3)

Publication Number Publication Date
EP1408200A2 true EP1408200A2 (fr) 2004-04-14
EP1408200A3 EP1408200A3 (fr) 2005-08-31
EP1408200B1 EP1408200B1 (fr) 2007-04-11

Family

ID=32010430

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03009435A Expired - Fee Related EP1408200B1 (fr) 2002-10-10 2003-04-25 Attachement de la bande de recouvrement d'une turbine

Country Status (3)

Country Link
US (1) US7189057B2 (fr)
EP (1) EP1408200B1 (fr)
DE (2) DE10247355A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2913051A1 (fr) * 2007-02-28 2008-08-29 Snecma Sa Etage de turbine dans une turbomachine
EP1965035A1 (fr) * 2007-03-02 2008-09-03 Siemens Aktiengesellschaft Minimisation des colonnes axiales sur des grilles de guidage réglables et sur le contourage pour extenseur de gaz chauds
EP2154335A1 (fr) * 2005-06-23 2010-02-17 Siemens Energy, Inc. Système de fixation de joint de bague
EP2495399B1 (fr) * 2011-03-03 2016-11-23 Safran Aero Booster S.A. Virole externe segmentée apte à compenser un désalignement du rotor par rapport au stator
EP3179054A1 (fr) * 2015-12-08 2017-06-14 General Electric Company Enveloppe souple pour le réglage de jeu de turbine à gaz
US11773741B2 (en) 2021-06-09 2023-10-03 General Electric Company Compliant shroud designs with variable stiffness

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2462581B (en) * 2008-06-25 2010-11-24 Rolls Royce Plc Rotor path arrangements
US20100054911A1 (en) * 2008-08-29 2010-03-04 General Electric Company System and method for adjusting clearance in a gas turbine
GB0914523D0 (en) * 2009-08-20 2009-09-30 Rolls Royce Plc A turbomachine casing assembly
US8079807B2 (en) * 2010-01-29 2011-12-20 General Electric Company Mounting apparatus for low-ductility turbine shroud
US8985944B2 (en) * 2011-03-30 2015-03-24 General Electric Company Continuous ring composite turbine shroud
US8939709B2 (en) * 2011-07-18 2015-01-27 General Electric Company Clearance control for a turbine
US9506356B2 (en) * 2013-03-15 2016-11-29 Rolls-Royce North American Technologies, Inc. Composite retention feature
EP3102794B1 (fr) * 2014-01-27 2019-12-18 United Technologies Corporation Support d'un joint d'étanchéité de stator externe pour une aube de turbine
GB2533544B (en) 2014-09-26 2017-02-15 Rolls Royce Plc A shroud segment retainer
US9945243B2 (en) 2014-10-14 2018-04-17 Rolls-Royce Corporation Turbine shroud with biased blade track
US10100649B2 (en) 2015-03-31 2018-10-16 Rolls-Royce North American Technologies Inc. Compliant rail hanger
RU2650013C2 (ru) * 2016-02-17 2018-04-06 Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" Лабиринтное уплотнение-демпфер газовой турбины
US10655491B2 (en) 2017-02-22 2020-05-19 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine with radial retention features
WO2018174739A1 (fr) * 2017-03-21 2018-09-27 Siemens Aktiengesellschaft Système fournissant la mobilité d'un carénage de stator dans un étage de turbine
US10392957B2 (en) 2017-10-05 2019-08-27 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having load distribution features
US10704560B2 (en) 2018-06-13 2020-07-07 Rolls-Royce Corporation Passive clearance control for a centrifugal impeller shroud
IT201900001173A1 (it) * 2019-01-25 2020-07-25 Nuovo Pignone Tecnologie Srl Turbina con un anello avvolgente attorno a pale rotoriche e metodo per limitare la perdita di fluido di lavoro in una turbina
US11149563B2 (en) * 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features
CN116517641A (zh) * 2022-01-24 2023-08-01 通用电气公司 弯曲梁堆叠结构柔性的护罩
US20240011410A1 (en) * 2022-07-05 2024-01-11 General Electric Company Variable flowpath casings for blade tip clearance control

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2634090A (en) * 1950-07-28 1953-04-07 Westinghouse Electric Corp Turbine apparatus
US6406256B1 (en) * 1999-08-12 2002-06-18 Alstom Device and method for the controlled setting of the gap between the stator arrangement and rotor arrangement of a turbomachine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1426857A1 (de) * 1964-06-11 1968-12-19 Siemens Ag Spaltabdichtung fuer Maschinen mit umlaufenden Schaufeln
DE2907749C2 (de) * 1979-02-28 1985-04-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Minimierung von Konstanthaltung des bei Axialturbinen von Gasturbinentriebwerken vorhandenen Schaufelspitzenspiels
GB2206651B (en) * 1987-07-01 1991-05-08 Rolls Royce Plc Turbine blade shroud structure
GB8903000D0 (en) * 1989-02-10 1989-03-30 Rolls Royce Plc A blade tip clearance control arrangement for a gas turbine engine
US5228828A (en) * 1991-02-15 1993-07-20 General Electric Company Gas turbine engine clearance control apparatus
US5456576A (en) * 1994-08-31 1995-10-10 United Technologies Corporation Dynamic control of tip clearance

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2634090A (en) * 1950-07-28 1953-04-07 Westinghouse Electric Corp Turbine apparatus
US6406256B1 (en) * 1999-08-12 2002-06-18 Alstom Device and method for the controlled setting of the gap between the stator arrangement and rotor arrangement of a turbomachine

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2154335A1 (fr) * 2005-06-23 2010-02-17 Siemens Energy, Inc. Système de fixation de joint de bague
FR2913051A1 (fr) * 2007-02-28 2008-08-29 Snecma Sa Etage de turbine dans une turbomachine
EP1965034A1 (fr) 2007-02-28 2008-09-03 Snecma Etage de turbine dans une turbomachine
US8403636B2 (en) 2007-02-28 2013-03-26 Snecma Turbine stage in a turbomachine
EP1965035A1 (fr) * 2007-03-02 2008-09-03 Siemens Aktiengesellschaft Minimisation des colonnes axiales sur des grilles de guidage réglables et sur le contourage pour extenseur de gaz chauds
CN101255804B (zh) * 2007-03-02 2016-03-30 西门子公司 流体机，尤其是热气膨胀机
EP2495399B1 (fr) * 2011-03-03 2016-11-23 Safran Aero Booster S.A. Virole externe segmentée apte à compenser un désalignement du rotor par rapport au stator
EP3179054A1 (fr) * 2015-12-08 2017-06-14 General Electric Company Enveloppe souple pour le réglage de jeu de turbine à gaz
CN106988805A (zh) * 2015-12-08 2017-07-28 通用电气公司 用于燃气涡轮发动机空隙控制的顺应性护罩
CN106988805B (zh) * 2015-12-08 2019-08-20 通用电气公司 用于燃气涡轮发动机空隙控制的顺应性护罩
US10822972B2 (en) 2015-12-08 2020-11-03 General Electric Company Compliant shroud for gas turbine engine clearance control
US11773741B2 (en) 2021-06-09 2023-10-03 General Electric Company Compliant shroud designs with variable stiffness

Also Published As

Publication number Publication date
DE50307000D1 (de) 2007-05-24
EP1408200A3 (fr) 2005-08-31
US20040115043A1 (en) 2004-06-17
US7189057B2 (en) 2007-03-13
EP1408200B1 (fr) 2007-04-11
DE10247355A1 (de) 2004-04-22

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