EP0924388A2 - Système pour maintenir le jeu des extrémités des aubes d'une turbine à gaz à constant - Google Patents

Système pour maintenir le jeu des extrémités des aubes d'une turbine à gaz à constant Download PDF

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Publication number
EP0924388A2
EP0924388A2 EP98121690A EP98121690A EP0924388A2 EP 0924388 A2 EP0924388 A2 EP 0924388A2 EP 98121690 A EP98121690 A EP 98121690A EP 98121690 A EP98121690 A EP 98121690A EP 0924388 A2 EP0924388 A2 EP 0924388A2
Authority
EP
European Patent Office
Prior art keywords
ring
turbine
gap
gas turbine
stator ring
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
EP98121690A
Other languages
German (de)
English (en)
Other versions
EP0924388B1 (fr
EP0924388A3 (fr
Inventor
Alexander Böck
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
BMW Rolls Royce GmbH
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, BMW Rolls Royce GmbH filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0924388A2 publication Critical patent/EP0924388A2/fr
Publication of EP0924388A3 publication Critical patent/EP0924388A3/fr
Application granted granted Critical
Publication of EP0924388B1 publication Critical patent/EP0924388B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • the invention relates to a passive gap holding system in the turbine part, in particular in the high-pressure turbine, a gas turbine, in its turbine housing next to guide vanes arranged on a rotor, preferably a Blades having shrouds are provided, or their Tips from jacket ring segments suspended in the turbine housing below Formation of one of a temperature control duct system in terms of its width Controlled gap are surrounded, this tempering channel system from the compressor part of the gas turbine past its combustion chamber Air flow can be fed in through a large number of metering holes ring chamber delimited by a stator ring.
  • the environment is referred to DE 30 40 594 C2
  • a gap system with the additional features of The preamble of claim 1 forms at least the internal state of the art.
  • the turbine gap just explained in cruise mode is used by the so-called. hot reslam characteristic ".
  • the so-called hot reslam case " is a briefly explained hot re-acceleration of the gas turbine engine, which is explained briefly below.
  • both the turbine housing and the rotor part, ie the turbine rotor disk (s) carrying the rotor blades are complete If you then switch to low-load operation, e.g. idle, the turbine housing cools down more due to its thin wall than the rotor disks, which are thick blocks, so to speak.
  • each turbine rotor disk expands further towards the turbine housing due to the centrifugal force and can undesirably come into contact with the tip region thereof.
  • the present invention Based on the knowledge that the turbine housing in one hot reslam case "in the low-load operation of the (flight) gas turbine should be heated rather than cooled in order not to allow the latter to shrink so much, since this makes it possible to avoid the above-described digging of the blade shroud into the shroud segments, the present invention the task of developing a passive gap holding system according to the preamble of claim 1 so that the turbine housing is heated rather than cooled, especially when idling.
  • the solution to this problem is characterized by one with the metering holes interacting aperture ring, which depends on the Temperature of the air flow brought to these the metering holes closes more or less, with a gap between the Stator ring and the shroud segments at least at low turbine loads a fraction of what flows over the guide vanes and blades Hot gas in the annular chamber and preferably in the direction of flow the gas turbine viewed the rear area of the same can.
  • Advantageous training and further education are included in the subclaims.
  • measures are thus provided with the aid of which the temperature of the air stream which is introduced into the temperature control duct system can be influenced. Specifically, this airflow is obtained from different sources. If the metering holes mentioned are exposed through the orifice ring, the air flow conveyed by the compressor part past the gas turbine combustion chamber, which is relatively cold in relation to the hot gas flow of the gas turbine, can get into the temperature control duct system and thus cool the turbine housing as usual. If, on the other hand, the metering hole is closed by the so-called orifice ring, a fraction of the hot gas flow reaches the temperature control duct system, as a result of which the turbine housing is cooled less or even heated.
  • This gap holding system is advantageously a passive system, i.e. the aperture ring takes its required, the Metering holes either releasing or closing position automatically depending on the current boundary conditions, namely of the temperature of the compressor part of the gas turbine at its combustion chamber airflow conveyed past. So that the aperture ring this Function, it could be built using bimetal technology, for example his; A device according to the invention works particularly simply and reliably Gap system, however, when the aperture ring from a Material with a higher coefficient of thermal expansion than that of the stator ring consists. Alone by the different Thermal expansion of the stator ring on the one hand and of the aperture ring on the other the metering holes are either closed or Approved.
  • reference number 1 is the turbine housing referred to, within which a plurality of blades 2 - only one of these is shown in fragments - load-bearing Rotor is arranged. Based on the flow direction 3, according to which a hot gas flow is led through the turbine part of the gas turbine shown is located upstream of the moving blade 2 or upstream the rotor disk represented by this rotor blade 2 has a ring of Guide vanes 4, of which only one is also shown in fragments is.
  • This guide vane (s) 4 is / are, as usual, with their not shown End section over several intermediate parts, also not shown connected to the turbine housing 1.
  • jacket ring segments 5 are also here as usual in the circumferential area of the blades 2.
  • These shroud segments 5 form as usual with respect to the turbine axis, not shown - its axial direction is equal to the flow direction 3 - a closed ring and carry a so-called running-in layer on their inner side facing the moving blades 2 5a.
  • the individual are via one or more lugs 5b Sheath ring segments 5 in corresponding recesses 1a of the turbine housing 1 hung.
  • the blades 2 are provided with a circumferential shroud 6, but this is irrelevant to the essence of the present invention.
  • a gap designated by the letter s is located between the tips 6a of the shroud 6 serving to seal against gap losses and the running-in layer 5a of the casing ring segment 5.
  • this gap s is located between the tips of the blades 2 and the inlet layer 5a, which is why the name Tips 6a "is equally used for blades 2 with or without cover band 6 or can be.
  • the gap s is functionally required, of course, after the blades 2 compared to the shroud segments 5 around the not shown Rotate the longitudinal axis of the gas turbine, however this gap s should be avoided leakage losses should be as small as possible.
  • this gap s should be avoided leakage losses should be as small as possible.
  • the turbine rotor or the blades 2 during operation of the gas turbine due to the action of heat can expand or expand differently than this Rotor blades 2 surrounding turbine housing 1. After the shroud segments 5 but are suspended in the turbine housing 1 changes then the size of the gap s.
  • this air flow 8 is promoted by the compressor part of the gas turbine and can branched off from this introduced into the turbine housing 1 at a suitable point become; the embodiment shown here is this airflow 8 around a wall of the engine combustion chamber or gas turbine combustion chamber - only the end section of this is shown from the outer wall 9 - bypassed partial air flow.
  • a component of the above-mentioned temperature control duct system 7 is an annular chamber 7a, which is delimited by a so-called stator ring 10 and in the area the guide blades 4 between this stator ring 10 and the turbine housing 1 lies.
  • this annular chamber 7a can the side of the combustion chamber outer wall 9 introduced airflow 8 via the end face in the stator ring 10 the provided metering holes 7b.
  • the air flow 8 can leave this annular chamber 7a again and arrives then - as already explained - on the back of these jacket ring segments 5 or in a cavity 7c located there and further on from there not shown, for example, in a similar annular chamber 7a ' between the next guide vane 4 'in the axial direction 3 and the turbine housing 1 is provided.
  • This diaphragm ring 11 has a so-called full ring section 11a, which with respect the longitudinal axis of the turbine, not shown, forms a circumferential ring, whose central axis is the turbine longitudinal axis. From this full ring section 11a, a plurality of so-called diaphragm sections are arranged in a ring 11b, which - as can be seen - against the direction of flow 3 or in the axial direction 3 up to the metering holes 7b or almost up to the inside of the front wall having these metering bores 7b 10a of the stator ring 10 extend. The is supported by several arms 11c Aperture ring 11 on the stator ring 10, which in a suitable manner with the rest is connected to the turbine housing 1. Regarding this support of the Distinguish the aperture ring 11 and the design of the stator ring 10 the two exemplary embodiments according to FIGS. 1, 2, on what will be discussed in more detail later.
  • the diaphragm ring 11 consists of a material whose coefficient of thermal expansion is greater than that of the stator ring 10 carrying the diaphragm ring 11.
  • This airflow 8 - as mentioned - is relatively hot due to the compression in the compressor part of the gas turbine, ie in this normal, normal operating state the gas turbine is operated at high load or full load, ie it is in cruise operation or even in take-off operation ".
  • the temperature of the air flow 8 is significantly lower. This causes due to the different thermal expansion behavior the stator ring 10 on the one hand and the aperture ring 11 on the other hand that the panel sections 11b against the direction of the arrow 12 again in the in the Figures 1, 2 shown, the metering holes 7b again substantially move covering position.
  • an air stream 8 is brought in at a significantly elevated temperature.
  • the one then passed through the metering holes 7b Airflow 8 further heats the aperture ring 11, causing this Metering holes 7b continue to be released until the already mentioned so-called normal, but not shown operating state reached is, in which practically only the air flow in the temperature control duct system 7 8 is initiated.
  • stator ring 10 is directly connected to the Screwed turbine casing 1 in a parting line 1b.
  • stator ring 10 formed such that the annular chamber 7a of this and the Turbine housing 1 is limited.
  • the aperture ring 11 is in this embodiment via his arms 11c on the inside of the front wall 10a of the Stator ring 10 attached.
  • Ring carrier 15 attached, which in turn the Stator ring 10 carries.
  • the stator ring 10 lies on the inside on the suitably designed Ring carrier 15 and the stator ring 10 is not in several bores penetrating pins 16 designated by Welding points 17 attached to the stator ring 10 and thus against falling out are secured, fixed to the ring carrier 15. These pins 16 do not protrude into this specified bore holes into the ring carrier 15.
  • annular chamber 7a substantially completely delimited by the stator ring 10, which, as can be seen on the outside, serves as a Has a U-shaped or channel-shaped cross section.
  • the aperture ring 11 is different designed and hung as in the embodiment of FIG. 1.
  • the aperture ring 11 also has the so-called full ring section 11a and the aperture sections cooperating with the metering bores 7b 11b, wherein between two adjacent such aperture sections 11b one of said pins 16 can pass through the annular chamber 7a, however, here the arms 11c are opposite to the panel sections 11b from the full ring portion 11a and engage with their free ends into suitable recesses 10c in the ring carrier 15 Wall of the stator ring 10 a.
  • This construction enables a particularly effective movement of the diaphragm sections 11b of the diaphragm ring 11 with respect to the metering holes 7b in the event of thermal expansion, as can also be seen in FIG. 3, which is explained briefly below and shows the stator ring 10 and the diaphragm ring 11 in enlarged positions in enlarged positions .
  • the various positions of the diaphragm ring 11 or more precisely its diaphragm sections 11b and its arms 11c are designated by the Roman numerals I to IV, these designations being located in each case on the lower edge of the diaphragm sections 11b and on the upper edge of the arms 11c.
  • the number I stands for the installed state of the aperture ring 11, the number II for the position when idling ( idle "), Section III for cruise operations ( cruise ”) and section IV for full load operation ( Max. take off”).
  • the arms 11c allow the aperture ring 11 to be free radial movement according to its thermal expansion, however, it due to its radial support or support over the free ends of the Arms 11c is twisted. Due to the radially different temperature expansion and occurs due to the just mentioned torsion of the aperture ring 11 increased radial movement at the ends of the aperture portions 11b in or against the direction of arrow 12 relative to the metering holes 7b, similarly a seesaw. This allows relatively large movements in the direction of the arrow 12 already at the occurrence of small temperature differences on the Metering holes 7b can be reached. These relatively large relative movements allow relatively large holes for the metering holes 7b use what with regard to the manufacturing and component tolerances to be observed is advantageous.
  • the air flow 8 assumes such high temperatures that the aperture ring 11 is heated further and expands more than the stator ring 10 or the ring carrier 15 due to its higher coefficient of thermal expansion.
  • the aperture ring 11 twists in its full ring section 11a and thereby opens the metering bores 7b, after which the air flow 8 conveyed past the combustion chamber by the compressor part into the annular chamber 7a and thus into the temperature control duct system 7, so that the turbine housing 1 is then cooled as desired explained change with regard to the gap 13, via which a fraction of hot gas can get into the temperature control duct system 7, namely that this gap 13 is much narrower in the high-load operation of the gas turbine than in idle operation.
  • the main difference of the embodiment according to FIG Fig. 1 lies However, the fact that, due to the described torsional effect, relatively small temperature differences of, for example, 200 ° C. are sufficient to either expose the metering bores 7b or to shut them off by means of the panel sections 11b.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98121690A 1997-12-19 1998-11-13 Système pour maintenir le jeu des extrémités des aubes d'une turbine à gaz à constant Expired - Lifetime EP0924388B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19756734 1997-12-19
DE19756734A DE19756734A1 (de) 1997-12-19 1997-12-19 Passives Spalthaltungssystem einer Gasturbine

Publications (3)

Publication Number Publication Date
EP0924388A2 true EP0924388A2 (fr) 1999-06-23
EP0924388A3 EP0924388A3 (fr) 2000-08-16
EP0924388B1 EP0924388B1 (fr) 2003-09-24

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EP98121690A Expired - Lifetime EP0924388B1 (fr) 1997-12-19 1998-11-13 Système pour maintenir le jeu des extrémités des aubes d'une turbine à gaz à constant

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Country Link
US (1) US6126390A (fr)
EP (1) EP0924388B1 (fr)
DE (2) DE19756734A1 (fr)

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FR2899273A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
WO2010112421A1 (fr) * 2009-03-31 2010-10-07 Siemens Aktiengesellschaft Turbomachine axiale à contrôle passif des jeux
DE102014217832A1 (de) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Kühlvorrichtung und Flugzeugtriebwerk mit Kühlvorrichtung
EP3324003A1 (fr) * 2016-11-18 2018-05-23 Ansaldo Energia Switzerland AG Lame pour interface de bouclier thermique de stator dans une turbine à gaz
US11236631B2 (en) 2018-11-19 2022-02-01 Rolls-Royce North American Technologies Inc. Mechanical iris tip clearance control

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Cited By (7)

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Publication number Priority date Publication date Assignee Title
FR2899273A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
WO2010112421A1 (fr) * 2009-03-31 2010-10-07 Siemens Aktiengesellschaft Turbomachine axiale à contrôle passif des jeux
EP2239423A1 (fr) * 2009-03-31 2010-10-13 Siemens Aktiengesellschaft Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube
DE102014217832A1 (de) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Kühlvorrichtung und Flugzeugtriebwerk mit Kühlvorrichtung
EP3324003A1 (fr) * 2016-11-18 2018-05-23 Ansaldo Energia Switzerland AG Lame pour interface de bouclier thermique de stator dans une turbine à gaz
US11255212B2 (en) 2016-11-18 2022-02-22 Ansaldo Energia Switzerland AG Blade to stator heat shield interface in a gas turbine
US11236631B2 (en) 2018-11-19 2022-02-01 Rolls-Royce North American Technologies Inc. Mechanical iris tip clearance control

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EP0924388B1 (fr) 2003-09-24
DE19756734A1 (de) 1999-06-24
US6126390A (en) 2000-10-03
DE59809709D1 (de) 2003-10-30
EP0924388A3 (fr) 2000-08-16

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