EP1350924A2 - Attachement des éléments de stator dans une turbine à gaz - Google Patents

Attachement des éléments de stator dans une turbine à gaz Download PDF

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Publication number
EP1350924A2
EP1350924A2 EP03003358A EP03003358A EP1350924A2 EP 1350924 A2 EP1350924 A2 EP 1350924A2 EP 03003358 A EP03003358 A EP 03003358A EP 03003358 A EP03003358 A EP 03003358A EP 1350924 A2 EP1350924 A2 EP 1350924A2
Authority
EP
European Patent Office
Prior art keywords
stator blade
blade segment
housing
gas turbine
attachment according
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
EP03003358A
Other languages
German (de)
English (en)
Other versions
EP1350924B1 (fr
EP1350924A3 (fr
Inventor
Christian Seydel
Andrej Golowin
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1350924A2 publication Critical patent/EP1350924A2/fr
Publication of EP1350924A3 publication Critical patent/EP1350924A3/fr
Application granted granted Critical
Publication of EP1350924B1 publication Critical patent/EP1350924B1/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
    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • the invention relates to a stator blade segment attachment for a gas turbine with a housing on which several stator blade segments are stored.
  • Stator blades of gas turbines are usually considered segment-like Components designed to be used in a housing or attached to a housing. Constructions of the named Art shows, for example, US 6,296,443 B1.
  • stator blade segments vane spans
  • they assign, for example, as in the above US document mentions feet or grooves on that are correspondingly positively connected to the housing.
  • the invention has for its object a stator blade segment attachment to create for a gas turbine which at simple structure and inexpensive to manufacture Avoids disadvantages of the prior art and one reliable fastening of the stator blade segments allows.
  • the object is achieved by the combination of features of the main claim solved, the sub-claims show more advantageous embodiments of the invention.
  • stator blade segment fastening according to the invention is distinguished is characterized by a number of significant advantages.
  • the principle underlying the invention is that Bracing the stator blade segments against the housing. This are slightly deformed. In the same way can also subjected the housing to a corresponding deformation become. Through this deliberately caused elastic deformation tolerances or play of the fasteners are eliminated. Unwanted vibrations or the like are thus completely prevented or at least strongly suppressed. Farther can be achieved by the configuration according to the invention that the respective free ends of the stator blade segments fit tightly against the housing and therefore not itself detach from the housing.
  • the means for bracing the stator blade segment include preferably an actuating element, which has a favorable design of the invention in the form of a screw can be.
  • This screw can, for example, in a threaded recess of the housing. It is then, for example designed as a lag screw. Alternatively it is also possible to use pressure screws or others Provide preloading means.
  • the radius of the housing in the area of the stator blade segments is smaller than the radius of the respective Stator vane. This ensures that the free end areas of the stator blade segments against the housing fit and can be tensioned accordingly.
  • FIG. 1 shows a perspective view of a stator blade segment, such as this from the prior art per se is already known.
  • This includes several stator blades that are attached to a circular segment-shaped outer support 6 and optionally a circular segment-shaped inner support 7 are attached.
  • the outer carrier 6 and the inner carrier 7 can with lateral Feet or approaches or provided with appropriate grooves be the attachment in a housing 1 (see Fig. 3) or on an inside cover tape. These configurations are known from the prior art, so that on can be referred to this.
  • a rotation of the stator blade segments 2 in the housing can by so-called vane stops be prevented.
  • the stator blade segment shown in FIG. 1 has for example, a groove 8.
  • FIG. 2 shows the schematic mode of operation in a side view the invention before tightening.
  • a housing 1 With the outside Circular arc is shown a housing 1, while the inner Circular arc reproduces a stator blade segment 2.
  • the reference number 3 refers to pretensioners.
  • Fig. 2 is a tension of the stator blade segment 2 to form a space in the middle Area so that the free ends of the stator blade segment bear against the housing 1 or be pressed against it.
  • Fig. 3 shows a simplified side view in the unstressed Condition in which it can be seen that the prestressing means 3 are in the form of a screw 4 which in a thread recess of the not shown in detail Housing 1 is guided.
  • the screw is, for example, as Traction screw designed to the stator blade segment 2 in the described way to deform.

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)
EP03003358A 2002-04-02 2003-02-14 Attachement des éléments de stator dans une turbine à gaz Expired - Lifetime EP1350924B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10214569A DE10214569A1 (de) 2002-04-02 2002-04-02 Statorschaufelsegmentbefestigung für eine Gasturbine
DE10214569 2002-04-02

Publications (3)

Publication Number Publication Date
EP1350924A2 true EP1350924A2 (fr) 2003-10-08
EP1350924A3 EP1350924A3 (fr) 2005-02-02
EP1350924B1 EP1350924B1 (fr) 2007-01-24

Family

ID=27816105

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03003358A Expired - Lifetime EP1350924B1 (fr) 2002-04-02 2003-02-14 Attachement des éléments de stator dans une turbine à gaz

Country Status (3)

Country Link
US (1) US6863497B2 (fr)
EP (1) EP1350924B1 (fr)
DE (2) DE10214569A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103154524A (zh) * 2010-08-11 2013-06-12 航空技术空间股份有限公司 轴向涡轮机压缩器的外壳
CN103154524B (zh) * 2010-08-11 2016-11-30 赛峰航空助推器股份有限公司 轴向涡轮机压缩器的外壳

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080221710A1 (en) * 2006-10-13 2008-09-11 General Electric Company System and methods for reducing an effect of a disturbance
US7421354B2 (en) * 2006-10-13 2008-09-02 General Electric Company Systems and methods for reducing an effect of a disturbance
EP2573328A1 (fr) * 2011-09-20 2013-03-27 Siemens Aktiengesellschaft Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator
US10428832B2 (en) 2012-08-06 2019-10-01 United Technologies Corporation Stator anti-rotation lug
US20160017731A1 (en) * 2014-07-17 2016-01-21 Rolls-Royce Corporation Vane assembly
EP2977548B1 (fr) * 2014-07-22 2021-03-10 Safran Aero Boosters SA Aube et turbomachine associée
US11125092B2 (en) 2018-08-14 2021-09-21 Raytheon Technologies Corporation Gas turbine engine having cantilevered stators

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE826673C (de) * 1945-04-04 1952-01-03 Maschf Augsburg Nuernberg Ag Leitapparat mit keramischen Leitschaufeln
US2857093A (en) * 1954-12-02 1958-10-21 Cincinnati Testing & Res Lab Stator casing and blade assembly
GB856599A (en) * 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
DE2152365C3 (de) * 1971-02-03 1973-12-06 Carrier Corp., Syracuse, N.Y. (V.St.A.) Einrichtung zum Lagern der inneren Enden von drehbar gelagerten Leitschaufeln einer Axial Stromungs maschine
DE2165529A1 (de) * 1971-12-30 1973-07-05 Kloeckner Humboldt Deutz Ag Einrichtung zum zentrieren und fixieren eines koerpers
DE2643285C3 (de) * 1976-09-25 1979-03-08 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Abstützvorrichtung für eine ein in Umfangsrichtung wirkendes Drehmoment aufnehmende Komponente in einem Stapel von Komponenten eines Gasturbinentriebwerkes, insbesondere eines Leitschaufelkranzes, im Gehäuse
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring
US6296443B1 (en) 1999-12-03 2001-10-02 General Electric Company Vane sector seating spring and method of retaining same

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103154524A (zh) * 2010-08-11 2013-06-12 航空技术空间股份有限公司 轴向涡轮机压缩器的外壳
CN103154524B (zh) * 2010-08-11 2016-11-30 赛峰航空助推器股份有限公司 轴向涡轮机压缩器的外壳

Also Published As

Publication number Publication date
US6863497B2 (en) 2005-03-08
US20030185683A1 (en) 2003-10-02
DE50306344D1 (de) 2007-03-15
EP1350924B1 (fr) 2007-01-24
EP1350924A3 (fr) 2005-02-02
DE10214569A1 (de) 2003-10-16

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