EP0903468A1 - Bandage annulaire pour turbine axiale - Google Patents

Bandage annulaire pour turbine axiale Download PDF

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Publication number
EP0903468A1
EP0903468A1 EP97810686A EP97810686A EP0903468A1 EP 0903468 A1 EP0903468 A1 EP 0903468A1 EP 97810686 A EP97810686 A EP 97810686A EP 97810686 A EP97810686 A EP 97810686A EP 0903468 A1 EP0903468 A1 EP 0903468A1
Authority
EP
European Patent Office
Prior art keywords
stator
cover plate
labyrinth
cavity
flow
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
EP97810686A
Other languages
German (de)
English (en)
Other versions
EP0903468B1 (fr
Inventor
Franz Kreitmeier
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.)
General Electric Switzerland GmbH
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 EP97810686A priority Critical patent/EP0903468B1/fr
Priority to DE59710621T priority patent/DE59710621D1/de
Priority to US09/153,270 priority patent/US6102655A/en
Priority to JP26168598A priority patent/JP4199855B2/ja
Priority to CN98119296.3A priority patent/CN1294341C/zh
Publication of EP0903468A1 publication Critical patent/EP0903468A1/fr
Application granted granted Critical
Publication of EP0903468B1 publication Critical patent/EP0903468B1/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

Definitions

  • the invention relates to a device for sealing the gap between the Blades and the conical contoured housing one Turbo machine, the blades being provided with circumferential cover plates are, which form radial gaps against the one provided with sealing strips Seal housing.
  • Such devices are known. They make a smooth or stepped Half-labyrinth with pure radial gaps. Such a seal is later on in the descriptive Fig. 2 shown.
  • the invention seeks to remedy this. It is based on the task Buckets of the type mentioned with a new shroud geometry To create a seal, which at the fulfillment of all boundary conditions to one leads to better efficiency.
  • an embodiment of the invention is based on the penultimate Stage of an axially flow-through condensation steam turbine is shown.
  • FIG. 1 are the middle three, each from a leading row Le and a running row
  • the existing stages of low-pressure blading are shown.
  • the Level Le3 / La3 corresponds to the penultimate level.
  • the one with her feet 21 in Rotations of the rotor 9 used blades La are at their Blade ends provided with cover plates 16.
  • the radially outer contours of the Depending on the row, cover plates are geometrically differently graded.
  • Under Formation of labyrinths 15 seal with their steps against sealing strips, which are arranged in a suitable manner in the stator 9.
  • the one with her feet 13 in Turnings of the stator 8 inserted guide blades Le are on their Provide blade ends with cover plates 20. Forming labyrinths 19 they also seal against sealing strips which are arranged in the rotor 9 in a suitable manner are.
  • the flow through channel 50 has the conically extending as the starting position outer contour 51 on the stator and the cylindrical inner contour 11 on the rotor. However, neither is mandatory. Regardless of the actual course in any case, the walls become the outer flow-restricting one Contour 10 in the area of the airfoil through the channel facing Cover plate 16 of the blades La formed.
  • Axial gaps 26, which represent the labyrinth outlets 42 are Usually will the column on the other hand limited by stator parts, which the Take over flow guidance in the non-bladed levels.
  • Fig. 2 is the cover plate seal of the row La3, as the beginning corresponds to the prior art mentioned. It essentially exists from the cover plate 16A, which extends over the entire blade width and with their outer diameter and the four caulked in the stator 8A Sealing strip 17A forms a half-labyrinth with pure radial gaps. Is recognizable the spacious labyrinth inlet 40A and the unfavorably designed labyrinth outlet 42A. With 54 the channel wall is designated when it is in a tap flows.
  • both the geometry of the shroud and its embedding in the stator improved in three ways.
  • the radial cavity at the labyrinth entrance is in its radial Extension divided into two axially offset cavities. i.e. in the Example designed zigzag.
  • the contour of the recess runs in the stator first inwards, then outwards in the axial direction Formation of a prong 41 protruding into the cavity Cover plate 16 configured.
  • It is provided with an understitch 43, which is adapted to the point shape.
  • the axial part of the backstitch is in its diameter so that on the occasion of assembly and Do not touch the cover plate and stator during the operating transients.
  • a Comparison with FIG. 2 shows that in the operating position there is a much smaller one Passage gap 18 between stator and cover plate. The gap mass flow will therefore be significantly reduced with the new measure.
  • a third measure serves to improve the re-inflow of the Maze mass flow in the main channel.
  • the cavity at the labyrinth exit 42 reduced to a permissible minimum dimension in the radial direction Crevice flow is immediately followed by a conical after the general outside stator wall bent. This can be the harmful Cross exchange of flow material significantly reduce and unnecessary Avoid dissipation of the high-energy gap flow as much as possible.
  • the total pressure profile of the Main flow favorably influenced.
  • the flow-limiting wall of the channel 50 is directly on Provide an outlet angle A at the blades La3.
  • This kink angle is dimensioned so that the outflow from the blades with respect to Total pressure and outflow angle is homogenized.
  • the kinked part of the wall runs radially outwards, i.e. it is from the machine axis, not shown directed away.
  • the choice of the articulation angle is based on the following considerations: At the outlet the blades have a divergent flow, with co-rotation on the cylinder. At least the flow in the radially outer zone has an essential higher energy than in the radially inner rotor zone, which is in the form of manifested significantly higher total pressures in the radially outer zone.
  • the idea behind the kink angle is now to have the lowest possible total pressure and outflow angle inhomogeneity to achieve above the bucket height. The equation for that radial balance teaches that this is primarily about the meridian curvature the streamlines can be reached. This has to be influenced primarily by adjusting the articulation angle. A homogeneous total pressure distribution the outer boundary wall can only be achieved if the corresponding one Kink angle A with respect to the conical contour of the channel in each Fall opens to the outside. Here, the desired total pressure reduction in achieved in this area.
  • the wall expediently becomes at least approximately further downstream in the entrance area of the guide vanes of the following stage, not shown a bend angle B directed radially inwards.
  • the wall with this bend angle B in the foot area of the downstream guide vane then runs again at the counter kink angle radially inwards so that the resulting flow restricting wall, which between the guide blade root and the following blade cover plate is interrupted by the axial gap 18, at least approximately in the plane of the Blade entry of this subsequent stage has a common point P with that Original straight channel contour.
  • FIG. 3 illustrates by means of that wall which is located upstream of the cavity and which and possibly the flow-restricting part of the previous one Guide blade root can be.
  • the counter-kink angle on the upstream wall increases the negative pressure or lowers the plus pressure over the downstream labyrinth, resulting in a leads to a further reduction in the gap mass flow.
  • FIG. 3 shows a solution in which the shroud has the same taper of approx. Has 25 ° as that in Fig. 2 and 3.
  • the cavity at the entrance to the labyrinth is in its radial extent in three axially offset cavities 40a, 40b and 40c divided.
  • three are caulked into the stator Sealing strip 17 arranged.
  • the main channel is the cavity at the labyrinth outlet 42 immediately behind the last sealing strip in the radial direction to an admissible minimum dimension reduced.
  • this minimum dimension is also in the front cavities intended.
  • the cover plate 16 is step-shaped. With in her the first section approximately horizontally and then curved Sealing strips 52 are used to seal the individual cavities. These sealing strips 52 are preferably with their horizontally extending section in the axially extending Housing parts caulked. It goes without saying that others Fastening methods and geometries are possible.
  • Fig. 4 shows the cover plate in the normal operating position.
  • the front Sealing strips 52 act on the front edges of the horizontally directed cover plate gradations.
  • the rear sealing strips 17 act horizontally on the last one directional cover plate gradation.
  • the cover plate is in its extreme positions on a somewhat reduced scale shown, namely in the case of transients such as those when starting and leaving of the machine. It can be seen that in the dash-dotted position the sealing strips 52 in the intersection between axially and radially directed Intervene in the step part. One of the ways to make this easier is the radial one Step part formed obliquely against the flow direction. In addition, the Curvature of the sealing strips a problem-free evasion in the event that the Cover plate would take an even more extreme position. In this position continues to seal the foremost of the sealing strips 17 against the horizontally directed rear cover plate part. The sealing strips are in the dashed position 52 no longer engaged. Here only the last of the sealing strips 17 and thus prevents working fluid from flowing uncontrolled through the gap 42.
  • Fig. 6 shows the new solution for a cover plate with a taper of only approx. 10 ° as used in the front stages of low pressure parts Steam turbines.
  • the cavity here is divided into two partial cavities 40a and 40c. These partial cavities are separated by one in its first section sealing strip 52 which runs approximately horizontally and is then curved. This strip acts on a simply stepped cover plate 16.
  • the rest Sealing strips 17 are arranged in such a way that at least one, even in extreme situations strip 52 or 17 is effective.
  • FIG. 7 finally shows the new solution for a cover plate with a taper of approximately 45 °, as used in the rear low pressure stages of Steam turbines. It can be seen here that even with such extreme channel openings the solution of FIG. 4 is easily transferable. It also offers Solution the advantage that the above described radially inward and aerodynamically damaging bend angles B at the inlet avoided can be. This means that the cover band contour corresponds to the globally specified one Channel contour.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP97810686A 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice Expired - Lifetime EP0903468B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP97810686A EP0903468B1 (fr) 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice
DE59710621T DE59710621D1 (de) 1997-09-19 1997-09-19 Vorrichtung zur Spaltdichtung
US09/153,270 US6102655A (en) 1997-09-19 1998-09-14 Shroud band for an axial-flow turbine
JP26168598A JP4199855B2 (ja) 1997-09-19 1998-09-16 軸流タービンのためのシュラウドバンド
CN98119296.3A CN1294341C (zh) 1997-09-19 1998-09-18 用于轴流式汽轮机的围带

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810686A EP0903468B1 (fr) 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice

Publications (2)

Publication Number Publication Date
EP0903468A1 true EP0903468A1 (fr) 1999-03-24
EP0903468B1 EP0903468B1 (fr) 2003-08-20

Family

ID=8230394

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810686A Expired - Lifetime EP0903468B1 (fr) 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice

Country Status (5)

Country Link
US (1) US6102655A (fr)
EP (1) EP0903468B1 (fr)
JP (1) JP4199855B2 (fr)
CN (1) CN1294341C (fr)
DE (1) DE59710621D1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1001139B1 (fr) * 1998-11-10 2004-01-07 ALSTOM (Switzerland) Ltd Dispositif d'étanchéité pour les extrémités des aubes de turbine
DE102009042857A1 (de) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Deckband-Labyrinthdichtung
DE102009052314A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Dichtanordnung für eine Gasturbine und eine derartige Gasturbine

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US6761530B1 (en) * 2003-03-21 2004-07-13 General Electric Company Method and apparatus to facilitate reducing turbine packing leakage losses
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US7255531B2 (en) * 2003-12-17 2007-08-14 Watson Cogeneration Company Gas turbine tip shroud rails
US7234918B2 (en) * 2004-12-16 2007-06-26 Siemens Power Generation, Inc. Gap control system for turbine engines
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US7708520B2 (en) * 2006-11-29 2010-05-04 United Technologies Corporation Gas turbine engine with concave pocket with knife edge seal
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US8317465B2 (en) * 2009-07-02 2012-11-27 General Electric Company Systems and apparatus relating to turbine engines and seals for turbine engines
US20110070072A1 (en) * 2009-09-23 2011-03-24 General Electric Company Rotary machine tip clearance control mechanism
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US8333557B2 (en) * 2009-10-14 2012-12-18 General Electric Company Vortex chambers for clearance flow control
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US8834107B2 (en) * 2010-09-27 2014-09-16 General Electric Company Turbine blade tip shroud for use with a tip clearance control system
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JP5517910B2 (ja) * 2010-12-22 2014-06-11 三菱重工業株式会社 タービン、及びシール構造
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GB933618A (en) * 1961-05-27 1963-08-08 Rolls Royce A sealing device
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DE2032328A1 (de) * 1969-07-01 1971-03-18 Rabouyt, Denis, Clamart, Hauts de Seine, Marsot Charles Louis, Paris (Frankreich) Düsenpropeller mit Ummantelung
FR2226555A1 (fr) * 1973-04-19 1974-11-15 Gen Electric
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EP0536575A1 (fr) * 1991-10-08 1993-04-14 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
US5632598A (en) * 1995-01-17 1997-05-27 Dresser-Rand Shrouded axial flow turbo machine utilizing multiple labrinth seals

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GB767656A (en) * 1953-11-12 1957-02-06 Rolls Royce Improvements in or relating to axial-flow fluid machines such as turbines and compressors
GB933618A (en) * 1961-05-27 1963-08-08 Rolls Royce A sealing device
GB1008526A (en) * 1964-04-09 1965-10-27 Rolls Royce Axial flow bladed rotor, e.g. for a turbine
DE2032328A1 (de) * 1969-07-01 1971-03-18 Rabouyt, Denis, Clamart, Hauts de Seine, Marsot Charles Louis, Paris (Frankreich) Düsenpropeller mit Ummantelung
FR2226555A1 (fr) * 1973-04-19 1974-11-15 Gen Electric
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
FR2384949A1 (fr) * 1977-03-26 1978-10-20 Rolls Royce Dispositif d'etancheite pour rotor de turbine a gaz
US4662820A (en) * 1984-07-10 1987-05-05 Hitachi, Ltd. Turbine stage structure
EP0536575A1 (fr) * 1991-10-08 1993-04-14 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
US5632598A (en) * 1995-01-17 1997-05-27 Dresser-Rand Shrouded axial flow turbo machine utilizing multiple labrinth seals

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1001139B1 (fr) * 1998-11-10 2004-01-07 ALSTOM (Switzerland) Ltd Dispositif d'étanchéité pour les extrémités des aubes de turbine
DE102009042857A1 (de) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Deckband-Labyrinthdichtung
DE102009052314A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Dichtanordnung für eine Gasturbine und eine derartige Gasturbine
WO2011054341A3 (fr) * 2009-11-07 2011-07-07 Mtu Aero Engines Gmbh Ensemble d'étanchéité pour une turbine à gaz et turbine à gaz de ce type

Also Published As

Publication number Publication date
DE59710621D1 (de) 2003-09-25
CN1294341C (zh) 2007-01-10
EP0903468B1 (fr) 2003-08-20
JP4199855B2 (ja) 2008-12-24
CN1212321A (zh) 1999-03-31
US6102655A (en) 2000-08-15
JPH11148308A (ja) 1999-06-02

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