EP0982475A1 - Turbomachine à écoulement axial avec aubage caréné - Google Patents

Turbomachine à écoulement axial avec aubage caréné Download PDF

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Publication number
EP0982475A1
EP0982475A1 EP98810855A EP98810855A EP0982475A1 EP 0982475 A1 EP0982475 A1 EP 0982475A1 EP 98810855 A EP98810855 A EP 98810855A EP 98810855 A EP98810855 A EP 98810855A EP 0982475 A1 EP0982475 A1 EP 0982475A1
Authority
EP
European Patent Office
Prior art keywords
flow
stator
rotor
flow channel
shroud
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Withdrawn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
EP98810855A
Other languages
German (de)
English (en)
Inventor
Andreas Kirschner
Ralf Dr. Greim
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 Schweiz AG
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 EP98810855A priority Critical patent/EP0982475A1/fr
Priority to JP24009199A priority patent/JP2000073705A/ja
Publication of EP0982475A1 publication Critical patent/EP0982475A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/028—Layout of fluid flow through the stages

Definitions

  • the invention relates to the blading of an axially flow Turbo machine with shrouds, consisting of at least one with one Stator of the turbomachine connected guide grid and at least one, downstream of this guide vane, with a rotor of the turbomachine connected playpen, with at least one of these vane grids a cover band is provided, which cover band with this one oppositely arranged rotor or stator part in one Embedding cavity forms a non-contact seal, and which Cover band on the downstream side of the vane grille on one of the seals facing side is cylindrical.
  • it concerns the Design of the cover tapes or cover plates on their sealing surface, as well as the Housing and hub contour between the rows of blades.
  • contactless seals such as those found in turbomachinery between the vane tips and the rotor or Blade tips and housing can be used in Depending on the grid geometry, significant amounts of the working fluid overflow without the enthalpy gradient in To implement work. In addition to the loss of available Mass flow incurs further losses when the leakage flow returns the core flow occurs, on the one hand by vortex induced thereby, on the other others also due to an incorrect flow against the subsequent vane grille.
  • the pressure conditions are also known from the shape of the flow channel to influence the seal inlet and outlet in a favorable way to the To reduce leakage current.
  • the invention is based, with a blading of the task type mentioned the inevitably existing leakage flow as low loss as possible and without resulting incorrect flow to the downstream the following vane grille back into the main flow.
  • the one flow channel delimiting walls of the rotor and stator between the rows of blades are cylindrical, and a shroud a positive axial Coverage with a stage of the embedding cavity that delimits downstream Has rotor or the stator, such that downstream of the Embedding cavity a cylindrical annular gap between the shroud and the opposite part is formed by the rotor or stator.
  • the cover tape hides the Exit cavity of the seal, which is generally a highly turbulent Flow is present.
  • the leakage flow is through the cylindrical annular gap introduced into the cylindrical mixing section as directed as possible, which again between the rows of blades through the rotor and stator wall of the flow channel is formed.
  • the advantage of this measure is, in particular, that due to the cylindrical shape of the overlap and the mixing section of the Leakage flow is introduced into the main flow without cross component. Since it is a flat outlet gap, the turbulence of the Leakage flow at the gap outlet, and thus a bursting of the Leakage jet can be avoided when entering the main flow.
  • the Cylindrical shape of cover band and flow channel wall enables undisturbed axial movements of rotor and stator. A reduction in radial play is at a minimum necessary for safe operation at this point not necessary and, as shown below, also undesirable because of the cylindrical annular gap only has the task of flow guidance. Thereby are much less demanding than a sealing function the dimensional accuracy of the cover tape and the opposite component what ultimately the design as well as manufacturing and assembly in this Area significantly simplified.
  • the effect of the flow guidance can be further improved by the Cover band on the side of the blade channel along its entire length
  • the blade head is inclined and is shaped to be pointed on the outflow side. On this way becomes a dead water area and an associated turbulent Detachment of the leakage flow downstream of the shroud avoided.
  • the leakage flow serves as a wall boundary layer in the cylindrical mixing section and the subsequent grid.
  • the turbulent Cross exchange between the leakage flow and the core flow is opened this way reduced to a minimum.
  • the exit cavity is covered by the shroud the entry cavity can be open.
  • the wall boundary layer formed upstream is sucked through the seal.
  • the inventive Guiding the leakage flow this downstream to the wall boundary layer is now in the corresponding position of the next level again Leakage flow. This is the slight interaction according to the invention between the leakage and core flow in their full scope.
  • the invention can be used with any channel shape in the Blade channels can be combined as long as the between the blade grids Condition of the cylindrical mixing section is fulfilled.
  • the well-known wavy channel contouring can be chosen with the aim of one to achieve negative radial gradients of the degree of reaction.
  • the main flow direction is the Working medium from left to right, or where there are cross sections through the machine acts out of the sheet plane.
  • Fig. 1 two rows of vanes LE and one row of blades LA are one axial turbomachine shown in longitudinal section.
  • the guide vanes are LE connected to the stator 8, the blades LA with the rotor 7.
  • Die Buckets LE, LA are provided with cover strips or cover plates 16, 23.
  • in the Housing 8 and the shaft 7 are sealing strips 17 arranged with the Form cover tapes 16, 23 non-contact seals.
  • the seals are arranged in the embedding cavities of the housing 8 or the hub 7, the embedding cavities between corresponding stages of the Housing (55.56) or the hub (57.58) can be defined.
  • the guide vane shrouds 23 seal and the blade cover bands 16 against in the rotor 7 or in the housing 8 sealing strips used 17.
  • the formed between the sealing strips Vortex chambers 22 or those present after the last sealing strips Exit cavities 42 are for the function of the seal shown here necessary. It is now necessary for understanding the invention and for the person skilled in the art can easily understand that the Seals even on those labeled A-A, B-B and C-C Cross-sectional planes end.
  • the geometry of the outlet gap can advantageously do so can be chosen that certain, shown in Fig. 2, 3 and 4 Fluid mechanical conditions are met.
  • 2 are the axial Flow conditions exemplified at the stator outlet; being this does not represent a restriction, since it leaves the impeller in the axial direction identical conditions exist.
  • 3 is the distribution of the tangential Speed components schematically shown at the stator outlet, in Fig. 4 at the impeller outlet, assuming that a purely axial Outflow from the turbine stage is to be achieved.
  • a Generalization of the flow conditions is without the expert further understandable, and is of no importance for the following Executions. For the rest, again without being restrictive To understand meaning, it is assumed that the axial flow direction the leaf plane points out, and the rotor in the direction of view Counterclockwise runs.
  • the cover strips 16, 23 are advantageously contoured in such a way that it there is no flow separation on the outflow side, that is, tapered on the outflow side.
  • the axial overlap of the stator cover tape 23 and rotor 7 or impeller shroud 16 and stator 8 can now do so be selected that a formed gap flow in the outlet gap 44 is present.
  • the gap width is also advantageously chosen to be sufficiently large in order to for both the axial and the tangential speed components laminar velocity profiles over the height of the exit gap 44 to to reach.
  • the Crevice flow now, so to speak, as a lubricating film for the core flow and thus efficiently minimizes their wall shear stress in the cylindrical Mixing section 53.
  • Flow channel in the vane grilles is from the prior art known. It can also be used in the context of the invention to influence the radial distribution of the degree of reaction. So that the Local pressure reduced at the seal inlet and increased at the seal outlet , which in turn has a positive impact on the amount of leakage given gasket and grid geometry.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98810855A 1998-08-28 1998-08-28 Turbomachine à écoulement axial avec aubage caréné Withdrawn EP0982475A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP98810855A EP0982475A1 (fr) 1998-08-28 1998-08-28 Turbomachine à écoulement axial avec aubage caréné
JP24009199A JP2000073705A (ja) 1998-08-28 1999-08-26 軸流式タ―ボ機械のシュラウドを備えた翼配列

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810855A EP0982475A1 (fr) 1998-08-28 1998-08-28 Turbomachine à écoulement axial avec aubage caréné

Publications (1)

Publication Number Publication Date
EP0982475A1 true EP0982475A1 (fr) 2000-03-01

Family

ID=8236289

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810855A Withdrawn EP0982475A1 (fr) 1998-08-28 1998-08-28 Turbomachine à écoulement axial avec aubage caréné

Country Status (2)

Country Link
EP (1) EP0982475A1 (fr)
JP (1) JP2000073705A (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6575693B2 (en) 2000-06-23 2003-06-10 Alstom (Switzerland) Ltd Labyrinth seal for rotating shaft
EP1382797A2 (fr) * 2002-07-20 2004-01-21 Rolls-Royce Deutschland Ltd & Co KG Passage d'une machine à écoulement avec étages à contraction augmentée
DE102009052314A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Dichtanordnung für eine Gasturbine und eine derartige Gasturbine
CN104912604A (zh) * 2015-06-01 2015-09-16 西安交通大学 一种具有止旋抑振作用的防旋板结构

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5328326A (en) * 1991-04-19 1994-07-12 Gec Alsthom Sa Impulse turbine with a drum rotor, and improvements to such turbines
EP0799973A1 (fr) 1996-04-01 1997-10-08 Asea Brown Boveri Ag Contour de paroi pour une turbomachine axiale

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5328326A (en) * 1991-04-19 1994-07-12 Gec Alsthom Sa Impulse turbine with a drum rotor, and improvements to such turbines
EP0799973A1 (fr) 1996-04-01 1997-10-08 Asea Brown Boveri Ag Contour de paroi pour une turbomachine axiale

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6575693B2 (en) 2000-06-23 2003-06-10 Alstom (Switzerland) Ltd Labyrinth seal for rotating shaft
EP1382797A2 (fr) * 2002-07-20 2004-01-21 Rolls-Royce Deutschland Ltd & Co KG Passage d'une machine à écoulement avec étages à contraction augmentée
EP1382797A3 (fr) * 2002-07-20 2005-01-12 Rolls-Royce Deutschland Ltd & Co KG Passage d'une machine à écoulement avec étages à contraction augmentée
EP1637697A2 (fr) * 2002-07-20 2006-03-22 Rolls-Royce Deutschland Ltd & Co KG Passage d'une machine à écoulement avec intervalle axial ayant une concentration inférieure à 1
EP1637697A3 (fr) * 2002-07-20 2006-04-05 Rolls-Royce Deutschland Ltd & Co KG Passage d'une machine à écoulement avec intervalle axial ayant une concentration inférieure à 1
DE102009052314A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Dichtanordnung für eine Gasturbine und eine derartige Gasturbine
CN104912604A (zh) * 2015-06-01 2015-09-16 西安交通大学 一种具有止旋抑振作用的防旋板结构

Also Published As

Publication number Publication date
JP2000073705A (ja) 2000-03-07

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