EP1389670A1 - Stator de turbine avec pales - Google Patents

Stator de turbine avec pales Download PDF

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Publication number
EP1389670A1
EP1389670A1 EP02018488A EP02018488A EP1389670A1 EP 1389670 A1 EP1389670 A1 EP 1389670A1 EP 02018488 A EP02018488 A EP 02018488A EP 02018488 A EP02018488 A EP 02018488A EP 1389670 A1 EP1389670 A1 EP 1389670A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
turbine blades
vane carrier
carrier
ring element
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Withdrawn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
EP02018488A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP02018488A priority Critical patent/EP1389670A1/fr
Publication of EP1389670A1 publication Critical patent/EP1389670A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the invention relates to a guide vane carrier Turbine blades according to the preamble of claim 1 and 2.
  • a turbine in particular a gas turbine, consists of two housing halves on which the guide blades are arranged directly or indirectly.
  • a rotor with the turbine blades is arranged within the housing that forms the stator.
  • the upper housing part can be removed and the guide vanes of the removed, upper housing half are therefore easily accessible.
  • the guide vanes of the lower half of the housing are still difficult to access because the rotor would first have to be removed. This means a considerable effort.
  • the task is solved by using a guide vane carrier the features of claim 1 or 2.
  • the turbine guide vanes are in the radial direction Mountable from the outside, making it easier Assembly and disassembly of turbine blades on the Guide vane carrier is possible without dismantling a rotor.
  • FIG. 1 shows a guide vane carrier 1, which is, for example, a housing of a turbine and, for example, consists of two halves, each half being designed, for example, in the shape of a semi-tube around a longitudinal axis 19 (axis of rotation of the turbine), ie semi-circular in cross section perpendicular to the longitudinal axis 19.
  • At least one receptacle 4 extends in the circumferential direction 34 around the axial longitudinal axis 19 on the inside 28 of the guide vane carrier 1, which receptacle is an annular groove-like depression starting from the inside 28 of the guide vane carrier 1.
  • Within the receptacle 4 there are several holes 7 which extend from the outside 25 of the guide vane carrier 1 to the inside 28 in the radial direction 22, that is to say perpendicular to the longitudinal axis 19.
  • Figure 2 shows a ring element 10 which can be attached in the receptacle 4 of the guide vane carrier 1.
  • the ring element 10 is detachable from the guide vane carrier 1 and is also displaceable in the receptacle 4 in the circumferential direction 34 (FIG. 4).
  • the ring element 10 likewise has holes in the form of bushings 13 through which components 16, in particular turbine blades 16 designed as guide blades, can be mounted in the radial direction 22.
  • the holes 7 and the bushings 13 are aligned with one another in the installed state, so that the turbine blades 16 can be mounted through the holes 17 and the bushings in the radial direction 22 from the outside 25 to the inside 28.
  • the turbine blades 16 are each fastened to the ring element 10, for example, by a bayonet coupling system which is arranged at the base of the turbine blade 16.
  • the turbine blade 16 closes off the bushing 13. It is also possible to install the turbine guide vanes 16 only when the ring element 10 is arranged in the guide vane carrier 1. When assembling a turbine, however, the ring element 10 can also be completely inserted into the receptacle 4 with the turbine blades 16.
  • FIG. 3 shows how the turbine blade 16 is attached directly to the guide blade carrier 1 or to the ring element 10.
  • the turbine blade 16 has, for example, a thread 31 on its foot in the area of an outer side 25 of the guide vane carrier in the assembled state, by means of which it is screwed into the ring element 10 or the guide vane carrier 1 from the outside. This is an alternative to fastening using a bayonet coupling. Further attachment options for the turbine blade 16 on the ring element 10 and / or on the guide blade carrier 1 are possible.
  • the guide vanes 16 may need to be removed to be repaired, replaced, or inspected.
  • the rotor which is still located in the guide vane carrier 1 but is not shown, prevents the turbine blades 16 from being able to be removed in the axial direction 19 or in the radial direction 22 toward the inside.
  • expansion of the turbine blades 16 is possible without removing the rotor. This is done by moving the ring element 10 in the circumferential direction 34 (FIG. 4). The attachment of the turbine blade 16 and the ring element 10 is released and the turbine blade 16 can be removed in the radial direction 22 to the outside 25.
  • the ring element 10 is pushed out of the receptacle 4 bit by bit and the further turbine blades 16 can be removed. It is also possible to mount and secure the turbine blades from the outside through the holes 7 and bushings 13. Furthermore, it is possible to unscrew the entire ring element 10 in the radial circumferential direction 34 from the guide vane carrier 1, ie, for example by 180 °, so that it can be completely removed from the guide vane carrier 1 while the rotor is still installed.
  • FIG. 5 shows another guide vane carrier 1 according to the invention.
  • the guide vane carrier 1 does not have a receptacle 4 for a ring element, but only the holes 7 through which the turbine blade 16 can be mounted from the outside 25 to the inside 28 and can be dismantled vice versa.
  • the turbine blade 16 is fastened to the guide blade carrier 1. To dismantle the turbine blade, only the fastening between the turbine blade 16 and the guide blade carrier 1 has to be loosened and the turbine blades 16 can be removed from the outside 25 in the radial direction 22.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP02018488A 2002-08-16 2002-08-16 Stator de turbine avec pales Withdrawn EP1389670A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02018488A EP1389670A1 (fr) 2002-08-16 2002-08-16 Stator de turbine avec pales

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02018488A EP1389670A1 (fr) 2002-08-16 2002-08-16 Stator de turbine avec pales

Publications (1)

Publication Number Publication Date
EP1389670A1 true EP1389670A1 (fr) 2004-02-18

Family

ID=30470277

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02018488A Withdrawn EP1389670A1 (fr) 2002-08-16 2002-08-16 Stator de turbine avec pales

Country Status (1)

Country Link
EP (1) EP1389670A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
GB846623A (en) * 1958-06-30 1960-08-31 Elmer Pershing Warnken A stator casing and blade assembly for an axial flow compressor
FR2671140A1 (fr) * 1990-12-27 1992-07-03 Snecma Aubage redresseur pour compresseur de turbomachine.
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
EP1104836A2 (fr) * 1999-12-03 2001-06-06 General Electric Company Resort de serrage pour secteurs des aubes de guidage et méthode de fixation

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
GB846623A (en) * 1958-06-30 1960-08-31 Elmer Pershing Warnken A stator casing and blade assembly for an axial flow compressor
FR2671140A1 (fr) * 1990-12-27 1992-07-03 Snecma Aubage redresseur pour compresseur de turbomachine.
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
EP1104836A2 (fr) * 1999-12-03 2001-06-06 General Electric Company Resort de serrage pour secteurs des aubes de guidage et méthode de fixation

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