EP0992656A1 - Turbomachine pour comprimer ou détendre un fluide comprimable - Google Patents

Turbomachine pour comprimer ou détendre un fluide comprimable Download PDF

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Publication number
EP0992656A1
EP0992656A1 EP98810999A EP98810999A EP0992656A1 EP 0992656 A1 EP0992656 A1 EP 0992656A1 EP 98810999 A EP98810999 A EP 98810999A EP 98810999 A EP98810999 A EP 98810999A EP 0992656 A1 EP0992656 A1 EP 0992656A1
Authority
EP
European Patent Office
Prior art keywords
ring channel
ring
channel system
housing
opening
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
EP98810999A
Other languages
German (de)
English (en)
Other versions
EP0992656B1 (fr
Inventor
Jakob Prof. Dr. Keller
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.)
GE Vernova GmbH
Original Assignee
ABB Schweiz AG
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 Schweiz AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Schweiz AG
Priority to DE59809578T priority Critical patent/DE59809578D1/de
Priority to EP98810999A priority patent/EP0992656B1/fr
Priority to US09/397,510 priority patent/US6264425B1/en
Publication of EP0992656A1 publication Critical patent/EP0992656A1/fr
Application granted granted Critical
Publication of EP0992656B1 publication Critical patent/EP0992656B1/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
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel

Definitions

  • the invention relates to a turbomachine for compression or Relaxing a compressible medium according to the preamble of the claim 1.
  • Turbomachines of the type mentioned above are as rotary machines formed and have blade elements along their axis of rotation on, the free blade ends of the inner wall of the Stand opposite flow housing.
  • the are flowed through axially to the rotor axis of the medium to be compressed usually guide vane plates fixed on one side to the inner wall of the housing attached to the rotary machine and stand with their free end corresponding Contours on the rotor shaft freely opposite.
  • An essential aspect at the optimization of compression efficiency or turbine efficiency is the reduction of leakage currents, i.e. of flow components, of the compressible flowing through the rotary machine Medium between the blade ends or guide blade ends and pass through the contours opposite these.
  • labyrinth seals used, which consist of a large number of interlocking contours, which are almost gastight the spaces between the rotating parts and the fixed housing parts together with the guide vane are able to seal. So can the leakage current is significantly reduced when using labyrinth seals the labyrinth seals themselves with a multitude of individual sealing lips be provided, but this seal form has the disadvantage that ever more labyrinth seals are provided inside a rotary machine and these consist of a large number of individual sealing lips, the larger they become the frictional forces exerted, for example, on the rotating blades from the outside act, causing the mechanical stress on the rotating parts within a rotary machine is increased. In addition, it is rarely possible a sufficient number of labyrinth elements for a high sealing effect to accommodate.
  • Figure 2a shows a cross section through a radial compressor, the one central Has rotor shaft 5, which is arranged in the interior of the housing 4 of the radial compressor is.
  • a nozzle-like contour 11 is connected to the rotor shaft 5 by which by way of rotation preferably air by centrifugal acceleration from the inside to the outside, is driven through the nozzle opening 12.
  • the nozzle opening 12 of the contour 11, an outlet opening 13 is provided within the housing 4, through which the compressed air leaves the radial compressor.
  • the invention has for its object a turbomachine in the preamble of claim 1, namely an axial compressor arrangement or to design an axial turbine arrangement such that without known use of labyrinth seals minimizes the leakage flow the disadvantageous friction effects with labyrinth seals, which not least leads to increased material stresses in the control and Guide blades and limit their lifespan should. Rather, it should be based on the measure known for radial compressors found a practical solution to reduce leakage currents be, the Lekagestrom largely contactless between the rotating and to reduce fixed components of the rotary machine.
  • a turbomachine for compressing or relaxing a compressible medium, with a rotor, on which at least one row of rotor blades is arranged perpendicular to the rotor axis, the individual rotor blades of which have free rotor blade ends on the radial side, which face the inner wall of a housing surrounding the rotor, through the interior of which the compressible one Medium flows axially to the rotor axis, designed in such a way that an annular channel system is provided radially opposite the free ends of the rotor blade of a rotor blade row within the housing surrounding the rotor.
  • the ring channel system preferably extends radially within the housing of the turbomachine around the entire peripheral peripheral edge of a row of moving blades.
  • the area of the The ring channel system is open on one side and is delimited by the blade ends such that an opening channel remains on both sides of a row of blades, through the opening channel of which the compressible medium, preferably air, from the interior of the housing, through which the air flows axially, into the interior flows of the ring channel system and exits the air from the ring channel system into the interior of the housing through the second opening channel.
  • the opening channels mentioned above correspond in the above case to the intermediate gaps between the rotating and stationary components of the turbine arrangement or the compressor arrangement.
  • a ring flow flowing within the ring channel system has the ring channel system and the blade ends at least in areas, which border on the opening channels, surface contours through which the points within the ring channel system where the opening channels open, Pressure conditions are created, which are characterized by the formation of a Set dynamic ring flow within the ring channel system and in correspond approximately to the static pressure conditions in the interior of the housing prevail in the area of the opening channels.
  • the ring flow is preferably generated within the ring channel system in which a small proportion of the compressible medium axially passing through the rotary machine, preferably air, passes into the opening channel between the blade end and the housing, preferably through the opening channel, which is provided in the flow direction in front of the blade, and shortly before entering the ring channel system, it has a flow inner contour which is designed such that the flow passing through the opening channel enters the ring channel with a preferred direction.
  • a ring flow can be induced within the ring channel system opposite the blade ends, which generates the desired pressure conditions after appropriate design of the inner contour of the ring channel system.
  • the blade ends each have a cover band into which the surface contour is incorporated, which is directly opposite the ring channel system.
  • the idea underlying the invention is that the flow is lost within of the ring channel system during the operation of the rotary machine so low as possible. For this it is necessary to keep the pressure conditions within of the ring channel system and the interior of the turbomachine in the Adjust areas of the opening channels.
  • the static pressure conditions in the The interior of the turbomachine is due to its dimensions and performance given to the machine itself. Accordingly, the ring channel system can be designed in such a way as to prevail in the interior static pressure conditions in the area of the opening channels also in the To generate ring channel system yourself.
  • the flow cross section is within the Ring channel system, especially in the area of the opening channels, is reduced in size, that in relation to the flow cross section of the other areas within the Ring channel system, so that a pressure equalization due to a local nozzle effect between the inside of the ring channel and the inside of the flow housing leads.
  • Airflow entering the ring channel can be targeted to cooling channels either in the housing the rotary machine and / or in the rotor blades are provided, through the cooling air in the ring duct system can be specifically fed, with a certain specification of the angle of entry of the cooling line into the ring channel system both the direction as well as the flow velocity within of the ring flow setting ring flow can be specified or influenced can.
  • the air to be compressed passes the turbomachine shown in partial cross-section from right to left (see Arrow display).
  • the blade 1 rotates about the rotor axis 5.
  • the end of the blade 2 has a shroud 9 with a surface contour that is S-shaped is formed and roughly the opposite contour of the inner wall of the ring channel 6 corresponds in this area.
  • On the side of the sound scoop 1 there is an inlet opening channel 7 in the area of the housing provided, through which air can enter the interior of the annular channel 6.
  • the contour of the inlet opening channel 7 is in the region of the transition into the Ring channel 6 formed such that the incoming flow with a preferred direction is introduced into the ring channel.
  • the ring channel flow counterclockwise (see Figure 1a) or clockwise (see FIG. 1b).
  • the Lekagestrom which is through the gap between the Blade end 2 and the housing 4 would form, is limited Ring channel 6 formed in this section as a diffuser, so that the ring flow the inlet channel opening with relatively low flow velocities overflows, which forms a high dynamic pressure, which is about that corresponds to that before entry into the inlet channel opening 7 in the interior of the rotary machine prevails.
  • the inlet opening channel 7 opens inside a curved ring channel course in the ring channel 6 and in particular in the area of the outer curvature of the ring channel, in which the Pressure increase is particularly strict.
  • the exit port channel 8 occurs in particular in a concave annular channel wall section in the ring channel in order to flow in the area of the smallest to lie in the ring channel of the prevailing pressure.
  • the S-shaped contour at the blade end 2 one into the interior of the housing 4 protruding contour section 9 ', a concave section 9 "and a convex section 9 '' 'on the contour sections 9', 9 '' and 9 '' ' are designed as protruding blade ribs, which arise from the plane of the Raise the blade end 2 and protrude into the ring channel system 6.
  • Cooling channel 10 is supplied with cooling air.
  • the flow rate of Ring current influenced within the ring channel 6 and its direction of flow become.
  • the cooling channel enters the ring channel 6 in such a way that so that an increased ring current is formed counterclockwise.
  • a corresponding arrangement for the formation of a ring current clockwise is shown in Figure 3b.
  • the blade 1 each has a cooling outlet channel 10, which depending on its direction of entry into the cooling channel 6 Ring flow with regard to their flow direction and flow speed can influence.
  • the embodiments according to 4a and b with a cooling system 10 passing through the housing 4 can be combined according to the embodiment 3a, b.
  • FIGS. 5 a and b show different embodiments of the shroud 9 shown on a Lautschaufel 2.
  • Figure 5a are on the blade end 2 several small rotor blades 15 are provided, which over the Elevate blade end 2 and extend into ring channel 6.
  • the representation corresponds to the view within the ring channel on the shroud 9 of the blade end 2.
  • Spaced by a gap 14 closes the housing 4 to the left and right of the blade.
  • the housing 4 has adjacent to the gaps 14, also ribs 16, which the Lead ring flow within the ring channel 6.
  • a Ring flow oriented from left to right and corresponds essentially to that Embodiment according to Figure 1a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98810999A 1998-10-05 1998-10-05 Turbomachine pour comprimer ou détendre un fluide comprimable Expired - Lifetime EP0992656B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE59809578T DE59809578D1 (de) 1998-10-05 1998-10-05 Strömungsmaschine zum Verdichten oder Entspannen eines komprimierbaren Mediums
EP98810999A EP0992656B1 (fr) 1998-10-05 1998-10-05 Turbomachine pour comprimer ou détendre un fluide comprimable
US09/397,510 US6264425B1 (en) 1998-10-05 1999-09-17 Fluid-flow machine for compressing or expanding a compressible medium

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810999A EP0992656B1 (fr) 1998-10-05 1998-10-05 Turbomachine pour comprimer ou détendre un fluide comprimable

Publications (2)

Publication Number Publication Date
EP0992656A1 true EP0992656A1 (fr) 2000-04-12
EP0992656B1 EP0992656B1 (fr) 2003-09-10

Family

ID=8236370

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810999A Expired - Lifetime EP0992656B1 (fr) 1998-10-05 1998-10-05 Turbomachine pour comprimer ou détendre un fluide comprimable

Country Status (3)

Country Link
US (1) US6264425B1 (fr)
EP (1) EP0992656B1 (fr)
DE (1) DE59809578D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008011864A1 (fr) * 2006-07-26 2008-01-31 Mtu Aero Engines Gmbh Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation
EP2039872A2 (fr) 2007-09-21 2009-03-25 Oscar Ristolfi Rail de guidage agencé verticalement et déformable élastiquement pour portes à enroulement avec un vantail flexible coulissant

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6585479B2 (en) 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
CA2496543C (fr) * 2002-08-23 2010-08-10 Mtu Aero Engines Gmbh Structure de recirculation d'un turbocompresseur
US7074006B1 (en) 2002-10-08 2006-07-11 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Endwall treatment and method for gas turbine
WO2012052740A1 (fr) * 2010-10-18 2012-04-26 University Of Durham Dispositif d'étanchéité pour réduire la fuite de fluide dans une turbine
US9995165B2 (en) 2011-07-15 2018-06-12 United Technologies Corporation Blade outer air seal having partial coating
US9062558B2 (en) * 2011-07-15 2015-06-23 United Technologies Corporation Blade outer air seal having partial coating
US20150285259A1 (en) * 2014-04-05 2015-10-08 Arthur John Wennerstrom Filament-Wound Tip-Shrouded Axial Compressor or Fan Rotor System
US10041500B2 (en) * 2015-12-08 2018-08-07 General Electric Company Venturi effect endwall treatment
US10106246B2 (en) 2016-06-10 2018-10-23 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10315754B2 (en) 2016-06-10 2019-06-11 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11293293B2 (en) 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
US11111025B2 (en) 2018-06-22 2021-09-07 Coflow Jet, LLC Fluid systems that prevent the formation of ice
US11920617B2 (en) 2019-07-23 2024-03-05 Coflow Jet, LLC Fluid systems and methods that address flow separation
US12202602B2 (en) 2020-06-17 2025-01-21 Coflow Jet, LLC Fluid systems having a variable configuration
WO2022204278A1 (fr) 2021-03-26 2022-09-29 Coflow Jet, LLC Pales d'éolienne et systèmes d'éolienne comprenant un jet à écoulement descendant
US11702945B2 (en) * 2021-12-22 2023-07-18 Rolls-Royce North American Technologies Inc. Turbine engine fan case with tip injection air recirculation passage

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3597102A (en) * 1968-06-10 1971-08-03 English Electric Co Ltd Turbines
US4752185A (en) * 1987-08-03 1988-06-21 General Electric Company Non-contacting flowpath seal
EP0497574A1 (fr) * 1991-01-30 1992-08-05 United Technologies Corporation Virole avec canaux de récirculation pour soufflante
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5282718A (en) * 1991-01-30 1994-02-01 United Technologies Corporation Case treatment for compressor blades
US5493855A (en) * 1992-12-17 1996-02-27 Alfred E. Tisch Turbine having suspended rotor blades
US5607284A (en) * 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
JP3816150B2 (ja) * 1995-07-18 2006-08-30 株式会社荏原製作所 遠心流体機械

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3597102A (en) * 1968-06-10 1971-08-03 English Electric Co Ltd Turbines
US4752185A (en) * 1987-08-03 1988-06-21 General Electric Company Non-contacting flowpath seal
EP0497574A1 (fr) * 1991-01-30 1992-08-05 United Technologies Corporation Virole avec canaux de récirculation pour soufflante
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008011864A1 (fr) * 2006-07-26 2008-01-31 Mtu Aero Engines Gmbh Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation
US8092148B2 (en) 2006-07-26 2012-01-10 Mtu Aero Engines Gmbh Gas turbine having a peripheral ring segment including a recirculation channel
EP2039872A2 (fr) 2007-09-21 2009-03-25 Oscar Ristolfi Rail de guidage agencé verticalement et déformable élastiquement pour portes à enroulement avec un vantail flexible coulissant

Also Published As

Publication number Publication date
EP0992656B1 (fr) 2003-09-10
US6264425B1 (en) 2001-07-24
DE59809578D1 (de) 2003-10-16

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