EP0985803A1 - Etage de turbine avec entrée radiale et sortie axiale - Google Patents

Etage de turbine avec entrée radiale et sortie axiale Download PDF

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Publication number
EP0985803A1
EP0985803A1 EP98810899A EP98810899A EP0985803A1 EP 0985803 A1 EP0985803 A1 EP 0985803A1 EP 98810899 A EP98810899 A EP 98810899A EP 98810899 A EP98810899 A EP 98810899A EP 0985803 A1 EP0985803 A1 EP 0985803A1
Authority
EP
European Patent Office
Prior art keywords
flow
axial
radial
channel
main
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
EP98810899A
Other languages
German (de)
English (en)
Other versions
EP0985803B1 (fr
Inventor
Roland Löpfe
Said Dr. Havakechian
Patrick Dr. Escher
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.)
Alstom SA
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 EP19980810899 priority Critical patent/EP0985803B1/fr
Priority to DE59807746T priority patent/DE59807746D1/de
Publication of EP0985803A1 publication Critical patent/EP0985803A1/fr
Application granted granted Critical
Publication of EP0985803B1 publication Critical patent/EP0985803B1/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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/048—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial admission

Definitions

  • the present invention relates to a turbine stage with radial inflow and axial outflow, in which a main flow in one Guide blading is directed radially towards a machine axis and one Barrel blading is flowed through in the main axial flow direction a housing-side duct wall and a hub-side duct wall one Include flow channel, which flow channel from a radial extending part, a part extending in the main axial direction, and one There is radial-axial flow deflection, which radial-axial flow deflection a main radial flow into an axial one Redirects main flow.
  • the first stage of a steam turbine group is often of the radial-axial type executed, in which the guide blading in radial and the Blades are blown through in the main axial direction.
  • the main advantage of this arrangement is that it is simple
  • the staggering of the guide vanes has to be adapted Power and volume flow class can take place.
  • the radial flow In this case, guide vanes can be attached to the housing on both sides, so that no seal against the rotating shaft is installed here got to.
  • the necessary radial-axial flow deflection a very inhomogeneous and lossy flow of the impeller are accepted. Because of the flow diversion a radial pressure gradient is induced in the flow channel in such a way that the pressure from the housing to the hub increases.
  • the object of the present invention is in a turbine stage with radial Inflow and axial outflow, in which a main flow in one Guide blading is directed radially towards a machine axis and one Barrel blading is flowed through in the main axial flow direction a housing-side duct wall and a hub-side duct wall one Include flow channel, which flow channel from a radial extending part, a part extending in the main axial direction, and one There is radial-axial flow deflection, which radial-axial flow deflection a main radial flow into an axial one Redirects main flow, the most homogeneous flow possible To create playpens.
  • the Exit gap of the seal should be designed so that the leakage is as possible parallel to the main flow along the hub, creating potential harmful interactions with the main flow are further reduced become.
  • the single figure shows an example of the embodiment according to the invention a radial-axial turbine stage.
  • the outer radius of the flow deflection is indeed through the housing formed, due to the function, the designation "hub-side Flow diversion "used.
  • the housing-side wall 27 of the overflow channel 50 receives the housing-side wall 27 of the overflow channel 50 for this purpose, immediately downstream of the deflection, a kink A, downstream which it is guided divergent by the machine axis 10. From the Counter-kink B, the housing-side wall 27 again runs parallel to Machine axis 10, or towards this. Likewise, the hub-side wall 28 downstream of a kink AA away from the machine axis 10 and from Counter kink point BB again parallel.
  • the location of the hub-side kinks AA and BB advantageously becomes one Distance downstream of the corresponding bends A and B on the housing side chosen.
  • the pronounced maximum speed, which is on the hub side Deflection 26 forms, dismantled; furthermore, the seal exit gap 30 additionally supplied mass flow of the main flow under largely avoid harmful interactions.
  • the flow upstream of the Impeller La accelerated in the axial direction which if necessary Areas of excessive impeller incorrect flow occur in particular of the hub-side channel wall 28 can be significantly reduced.
  • the location of the seal exit gap 30 is advantageously at one point selected the highest possible pressure in the flow channel, and such that by the centrifugal force of the main flow the penetration depth of the Leakage flow in the flow channel is limited. The latter can continue to be supported by the fact that the exit gap 30 at the end of the Radial-axial deflection is placed, and the outlet gap 30 through its Design the leakage flow as laminar as possible and parallel to the hub side Channel wall 28 leads.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19980810899 1998-09-10 1998-09-10 Etage de turbine avec entrée radiale et sortie axiale Expired - Lifetime EP0985803B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19980810899 EP0985803B1 (fr) 1998-09-10 1998-09-10 Etage de turbine avec entrée radiale et sortie axiale
DE59807746T DE59807746D1 (de) 1998-09-10 1998-09-10 Turbinenstufe mit radialer Zuströmung und axialer Abströmung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19980810899 EP0985803B1 (fr) 1998-09-10 1998-09-10 Etage de turbine avec entrée radiale et sortie axiale

Publications (2)

Publication Number Publication Date
EP0985803A1 true EP0985803A1 (fr) 2000-03-15
EP0985803B1 EP0985803B1 (fr) 2003-04-02

Family

ID=8236307

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19980810899 Expired - Lifetime EP0985803B1 (fr) 1998-09-10 1998-09-10 Etage de turbine avec entrée radiale et sortie axiale

Country Status (2)

Country Link
EP (1) EP0985803B1 (fr)
DE (1) DE59807746D1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1496196A1 (fr) * 2003-07-08 2005-01-12 Siemens Aktiengesellschaft Turbine à vapeur
GB2440344A (en) * 2006-07-26 2008-01-30 Christopher Freeman Impulse turbine design
CN101094971B (zh) * 2004-11-02 2011-03-09 阿尔斯托姆科技有限公司 涡轮机装置的优化的涡轮机级以及设计方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2429936A (en) * 1943-12-18 1947-10-28 Allis Chalmers Mfg Co Turbine mounting
DE1076145B (de) * 1953-08-25 1960-02-25 Siemens Ag Hochdruckturbine mit Radialbeschaufelung der Gleichdruckregelstufe
GB1162440A (en) * 1967-06-05 1969-08-27 Shell Int Research Gas Turbine.
DE2231015A1 (de) * 1972-05-31 1973-12-20 Bbc Brown Boveri & Cie Erste stufe einer zweiflutigen niederdruck-dampfturbine grosser leistung
EP0024275A1 (fr) * 1979-08-15 1981-03-04 BBC Aktiengesellschaft Brown, Boveri & Cie. Fixation des anneaux de tuyères
DE4014976C1 (en) * 1990-05-10 1991-07-25 Mtu Friedrichshafen Gmbh Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2429936A (en) * 1943-12-18 1947-10-28 Allis Chalmers Mfg Co Turbine mounting
DE1076145B (de) * 1953-08-25 1960-02-25 Siemens Ag Hochdruckturbine mit Radialbeschaufelung der Gleichdruckregelstufe
GB1162440A (en) * 1967-06-05 1969-08-27 Shell Int Research Gas Turbine.
DE2231015A1 (de) * 1972-05-31 1973-12-20 Bbc Brown Boveri & Cie Erste stufe einer zweiflutigen niederdruck-dampfturbine grosser leistung
EP0024275A1 (fr) * 1979-08-15 1981-03-04 BBC Aktiengesellschaft Brown, Boveri & Cie. Fixation des anneaux de tuyères
DE4014976C1 (en) * 1990-05-10 1991-07-25 Mtu Friedrichshafen Gmbh Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1496196A1 (fr) * 2003-07-08 2005-01-12 Siemens Aktiengesellschaft Turbine à vapeur
WO2005005783A1 (fr) * 2003-07-08 2005-01-20 Siemens Aktiengesellschaft Turbine a vapeur
CN101094971B (zh) * 2004-11-02 2011-03-09 阿尔斯托姆科技有限公司 涡轮机装置的优化的涡轮机级以及设计方法
GB2440344A (en) * 2006-07-26 2008-01-30 Christopher Freeman Impulse turbine design

Also Published As

Publication number Publication date
DE59807746D1 (de) 2003-05-08
EP0985803B1 (fr) 2003-04-02

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