EP2677123B2 - Diffusor für Turbomaschinen - Google Patents

Diffusor für Turbomaschinen Download PDF

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Publication number
EP2677123B2
EP2677123B2 EP12172393.6A EP12172393A EP2677123B2 EP 2677123 B2 EP2677123 B2 EP 2677123B2 EP 12172393 A EP12172393 A EP 12172393A EP 2677123 B2 EP2677123 B2 EP 2677123B2
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EP
European Patent Office
Prior art keywords
diffuser
straight
section
wall
vertical cross
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.)
Active
Application number
EP12172393.6A
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English (en)
French (fr)
Other versions
EP2677123B1 (de
EP2677123A1 (de
Inventor
Christoph Pfoster
Thomas Mokulys
Michael Sell
Hans-Ludwig Boxheimer
Silvia Gafner
Beate Grzondziel
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 Technology GmbH
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General Electric Technology GmbH
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=46318990&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2677123(B2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP12172393.6A priority Critical patent/EP2677123B2/de
Priority to US13/919,332 priority patent/US20130336783A1/en
Priority to CN201310240850.4A priority patent/CN103511008B/zh
Priority to JP2013127715A priority patent/JP5726236B2/ja
Publication of EP2677123A1 publication Critical patent/EP2677123A1/de
Application granted granted Critical
Publication of EP2677123B1 publication Critical patent/EP2677123B1/de
Publication of EP2677123B2 publication Critical patent/EP2677123B2/de
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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

Definitions

  • the present invention relates to improvements to a diffuser for a turbomachine. It is particularly, but not exclusively, relevant to the diffuser following the last stage of a low pressure (LP) steam turbine.
  • LP low pressure
  • Diffusers as found in large steam turbines are used for example to guide the steam from the last stage of the turbine to a condenser.
  • a diffuser has two or more essentially concentric walls arranged at least initially with an axial orientation around the rotor axis of the turbine.
  • the diffuser following the last stage has tasks of decelerating the flowing medium, increasing the usable pressure or enthalpy drop across the turbines, converting a proportion of the kinetic energy to pressure energy and reducing flow losses at the diffuser outlet toward the condenser groups. It is hence clear that the design of the diffuser contributes to the overall efficiency of a turbine machine and for that reason many efforts have been made to optimize the diffuser layout.
  • the straight lines can be formed as a sequence of kinks in the wall of the diffuser to deliberately cause flow separation from the wall.
  • the configuration allows shock boundary layer pulsations to be suppressed.
  • the measure may be associated with a considerable reduction in the diffuser efficiency.
  • a further example of a diffuser comprising straight parts is provided in European Patent application EP1921278A . As discussed in this application, it may be advantagoues to geometrically smooth the curves created by the straight parts.
  • a yet further example is provided by U.S patent publication no. 3802187 .
  • the exhaust comprises a concial shaped diffuser connected to an elbow duct having an elliptical shaped outlet.
  • a diffuser according to A claim 1.
  • the 2 nd order elliptical curve is a segment of an ellipse but excluding circle segments.
  • FIG. 1 there is shown a schematic vertical cross-section of a diffuser for a low pressure steam turbine stage as proposed in the GT2011 publication as referenced above.
  • the figure shows a cross-section of the upper half of an essentially rotationally symmetrical diffuser. It also shows a part of the rotor 10 and of the inner casing 11. Between the rotor and the casing and attached to one, respectively, are rotating blades and stator blades.
  • the last stage of the turbine includes a circumferential arrangement of stator blades 111 attached to the casing 11 and a circumferential arrangement of rotating blades 101 attached to the rotor 10.
  • the diffuser 12 Following the last stage 111 , 101 is the diffuser 12 . It has an outer wall 121 and an inner wall 122 , which together form an annular conduit guiding the steam to a condenser (not shown).
  • the enlarged detail of FIG. 1 shows a part of the outer wall 121 of the diffuser and illustrates the parameters which can be used to optimize the diffuser for a given turbine and steam flow.
  • the wall Following the direction of the steam flow, the wall has first straight part of length I1 followed by a second straight part of length I2 .
  • the second straight part forms an angle ⁇ 1 with respect to a horizontal line, i.e. in axial direction.
  • the two straight parts are followed by a curved part.
  • the curved part has an angle ⁇ 2 with respect to a horizontal line at its entry and a radius of R and an angle ⁇ 3 with respect to a horizontal line at its exit.
  • the arc is followed by another essentially straight section with the length I3 in direction of the exit 123.
  • all the parameters shown can be altered in order to configure an optimized diffuser 12.
  • FIG. 2 a modified diffuser in accordance with an example of the invention is shown overlaid over the diffuser of FIG. 1 (shown as dashed lines 121 ).
  • the new diffuser has a higher number of straight parts (3 over 4) and a higher order curve 21 following the straight parts.
  • the curve 21 is essentially an elliptical curve.
  • the elliptical shape 21 has a higher curvature at the beginning or entry and flares out into a flatter part towards the exit 123 compared to the circular curve 121 (dashed).
  • Other numerals in FIG. 2 are the same as in FIG. 1 . when denoting identical or similar elements.
  • FIG. 3 A comparison of the efficiency of the two designs of FIG. 2 is shown in FIG. 3 illustrating the slice diffuser recovery.
  • the graph is a plot of the recovery Chi between the diffuser inlet (last stage blade exit) and the diffuser exit (2R plane)over the medium speed in axial direction C z ⁇ in m/s at the diffuser inlet.
  • the upper line illustrates the recovery of the new diffuser. This recovery is at least 3 per cent above the line of a known diffuser as shown in FIG. 1 . From this comparison it becomes clear that hybrid diffusers in accordance with the invention have the potential to improve diffuser recovery in a significant manner.
  • the hybrid diffuser with 4 or more straight parts followed by an elliptical can be regarded as the one with a better improvement potential than the prior art diffuser of FIG. 1 .
  • a diffuser with a higher number of straight parts and their respective lengths angles between them followed by a curve of the general shape a 11 x 2 + a 12 xy + a 22 y 2 + 2 a 13 x + 2 a 23 y + a 33 0 with at least one mixed coefficient not being zero has a higher potential of being further improved than the more limited designs following the prior art.
  • Such optimisation can be made using any of the known tools such as ANSYS CFX or other methods as described in the above referenced GT2011 publication.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (2)

  1. Ein Diffusor nach der letzten Stufe einer Turbine, der eine äußere Wand (121) mit einem Eintrittsabschnitt einschließlich, an einem vertikalen Querschnitt, mehrerer nachfolgender gerader Wandteile, die in einem Winkel zueinander stehen, hat, dadurch gekennzeichnet, dass den geraden Wandteilen am vertikalen Querschnitt ein gekrümmter Wandteil folgt, wobei der gekrümmte Abschnitt die geraden Abschnitte mit einer Diffusorlippe oder einem Diffusorausgang verbindet und eine elliptische Kurve der Ordnung 2 am vertikalen Querschnitt hat.
  2. Der Diffusor nach Anspruch 1, wobei die Anzahl von geraden Teilen vier oder mehr beträgt.
EP12172393.6A 2012-06-18 2012-06-18 Diffusor für Turbomaschinen Active EP2677123B2 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP12172393.6A EP2677123B2 (de) 2012-06-18 2012-06-18 Diffusor für Turbomaschinen
US13/919,332 US20130336783A1 (en) 2012-06-18 2013-06-17 Diffuser for turbomachines
CN201310240850.4A CN103511008B (zh) 2012-06-18 2013-06-18 用于涡轮机的扩散器
JP2013127715A JP5726236B2 (ja) 2012-06-18 2013-06-18 ターボ機械用のディフューザ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12172393.6A EP2677123B2 (de) 2012-06-18 2012-06-18 Diffusor für Turbomaschinen

Publications (3)

Publication Number Publication Date
EP2677123A1 EP2677123A1 (de) 2013-12-25
EP2677123B1 EP2677123B1 (de) 2014-10-08
EP2677123B2 true EP2677123B2 (de) 2018-04-25

Family

ID=46318990

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12172393.6A Active EP2677123B2 (de) 2012-06-18 2012-06-18 Diffusor für Turbomaschinen

Country Status (4)

Country Link
US (1) US20130336783A1 (de)
EP (1) EP2677123B2 (de)
JP (1) JP5726236B2 (de)
CN (1) CN103511008B (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7458947B2 (ja) * 2020-09-15 2024-04-01 三菱重工コンプレッサ株式会社 蒸気タービン

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2960306A (en) * 1956-01-16 1960-11-15 Gen Motors Corp Turbine
GB1050879A (de) * 1965-01-28
US3802187A (en) * 1972-06-01 1974-04-09 Avco Corp Exhaust system for rear drive engine
US4344737A (en) * 1978-01-30 1982-08-17 The Garrett Corporation Crossover duct
DE3206626A1 (de) * 1982-02-24 1983-09-01 Kraftwerk Union AG, 4330 Mülheim Abgaskanal fuer gasturbinen
AT383396B (de) * 1984-08-17 1987-06-25 Proizv Ob Turbostroenia Niederdruckzylinder einer dampfturbine
GB9415685D0 (en) * 1994-08-03 1994-09-28 Rolls Royce Plc A gas turbine engine and a diffuser therefor
DE19905994A1 (de) 1999-02-15 2000-08-24 Peter Kraus Vorrichtung und Verfahren zur Aufhebung von Stoß-Grenzschicht-Oszillationen bei kreisringförmigen Diffusoren (axial-radial) an Dampfturbinen
EP1921278A1 (de) * 2006-11-13 2008-05-14 ALSTOM Technology Ltd Diffusor-und Abdampfsystem für Turbine
US8475125B2 (en) * 2010-04-13 2013-07-02 General Electric Company Shroud vortex remover
US8591185B2 (en) * 2010-11-16 2013-11-26 General Electric Company Low pressure exhaust gas diffuser for a steam turbine

Also Published As

Publication number Publication date
US20130336783A1 (en) 2013-12-19
JP5726236B2 (ja) 2015-05-27
CN103511008A (zh) 2014-01-15
JP2014001735A (ja) 2014-01-09
EP2677123B1 (de) 2014-10-08
CN103511008B (zh) 2015-07-15
EP2677123A1 (de) 2013-12-25

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