EP2700788A1 - Leit- oder Laufsschaufel mit Spitzenabdeckung - Google Patents

Leit- oder Laufsschaufel mit Spitzenabdeckung Download PDF

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Publication number
EP2700788A1
EP2700788A1 EP12181109.5A EP12181109A EP2700788A1 EP 2700788 A1 EP2700788 A1 EP 2700788A1 EP 12181109 A EP12181109 A EP 12181109A EP 2700788 A1 EP2700788 A1 EP 2700788A1
Authority
EP
European Patent Office
Prior art keywords
blade
vane
plug
blade body
peripheral surface
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Withdrawn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
EP12181109.5A
Other languages
English (en)
French (fr)
Inventor
Herbert Brandl
Marcel Koenig
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
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP12181109.5A priority Critical patent/EP2700788A1/de
Publication of EP2700788A1 publication Critical patent/EP2700788A1/de
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to vanes or blades for turbines or the like, having a blade body with at least one longitudinal end which is connected to an end or plug body, whereby both bodies are joined at a connection area in the manner of a male and female plug whereby an inner peripheral surface of one body overlaps an outer peripheral surface of the other body in the longitudinal direction of the blade.
  • Such turbine blades with a hollow formed blade body are known from US 2005/0196277 A1 .
  • a ring shaped flange with a stepped inner contour is formed in the inner periphery of the hollow blade body, whereby a correspondingly shaped plate-shaped cap can be placed onto the flange and then connected to it by electron beam welding.
  • the plate-shaped cap can be provided with a plurality of openings in order to lead away the cooling air, which is flowing through the hollow blade during operation of the turbine, at defined positions.
  • a similarly designed blade is disclosed in US 2010/0080711 A1 .
  • the plate-shaped cap optionally provided with air outlet openings, can be connected to the blade body by welding or brazing.
  • the patent US 5,797,725 relates to the design of vane ring arrangements for turbines.
  • Such ring arrangements comprise two ring surfaces arranged concentrically to one another and to the turbine axis, and are connected to one another by vanes arranged substantially radially to the turbine axis.
  • Such vane ring arrangements are often arranged axially between rows of blades in a turbine in order to direct the gas or air flow optimally onto the following row of blades.
  • US 5,797,725 provides that the radially inner or outer ends of the vanes are inserted into recesses in the ring surfaces formed corresponding to the end profile of the vanes, and fixed with a securing ring which is moulded into ring grooves which correspond with each other on the outer periphery of the blade body and the inner periphery of the opening of the recess.
  • the said securing ring can be cut by EDM (electric discharge machining) for example. This allows separation of the parts.
  • turbine blades are generally problematic because of the welded connections used. Welding of superalloys commonly used in turbine applications is problematic or even impossible. On the other hand it is generally desirable with turbine blades to be able to use hollow blade bodies with large end openings in order to simplify where possible the manufacturing of the blade body.
  • the invention is based on the general idea of using a form locking connection between the blade body and the cap or plug body, whereby the securing ring or clip providing the form locking connection is made by casting and arranged in an essentially annular channel between the bodies being connected together, the channel being practically only accessible by casting.
  • the excellent sealing effect is surprising as the region of the channel between the two bodies being connected must be strongly heated before introducing the casting material of the securing ring or clip into the essentially annular channel, whereby oxides form on the channel walls which then prevent a bonded connection between the channel walls and the material of the securing ring.
  • connection process of the invention is not limited to specific materials to be connected. Therefore, the blade body and the cap or plug body can be produced of substantially different materials which can be optimally selected in view of any requirements for the blade and cap or plug bodies respectively.
  • the cap or plug bodies can have any form and may be used to connect or arrange the turbine blades with or with respect to other turbine elements.
  • a turbine blade 1 can have a hollow formed blade body 2, whereby in the example shown the inner cavity is divided by two cross walls 3 into three chambers 4 extending in the longitudinal direction of the blade, the chambers being open at the longitudinal ends of the blade body 2.
  • the open end of a chamber 4 can be closed by a cap or plug 5.
  • the plug has an outer periphery which corresponds to the profile of the chamber 4, so that the plug 5 can be inserted in the longitudinal direction of the chamber 4 into the chamber 4.
  • the plug 5 has an annular projection 6 on its outer periphery which extends in the longitudinal direction of the chamber 4, so that the outer periphery of the plug body 5 and the inner periphery of the chamber 4 overlap over the height of the annular projection.
  • Cooperating essentially annular grooves 7 and 8 are formed in the outer periphery of the annular projection 6 and the inner periphery of the chamber 4.
  • the annular grooves 7, 8 face each other with their open sides and form accordingly an essentially annular channel surrounding the plug 5.
  • Half of the cross-section of the essentially annular channel is arranged in the essentially annular projection 6 of the plug 5 and the other half in the wall of the chamber 4.
  • the essentially annular channel formed by the essentially annular grooves 7 and 8 is accessible from outside through openings which are formed, similarly to the annular channel, by grooves 9 and 10 which are substantially perpendicular to the essentially annular grooves 7 and 8.
  • the grooves 9 and 10 being formed in the facing inner or outer peripheral surfaces of the plug body 5 or the chamber 4.
  • the blade body 2 and the plug body 5 are heated in order to avoid a too rapid cooling of metal melt which has been poured in. During this heating a thin oxide layer forms on the walls of the annular grooves 7 and 8, which prevents a bonded connection of the cast material with the material of the blade body 2 or with the plug body 5. As a result the cast securing ring 11 forms purely a form-locking connection between the blade body 2 and the plug body 5.
  • the essentially annular groove 7 is arranged directly on the inner side of the wall of the blade body 2.
  • Figures 3 and 4 show that this must not always be the case.
  • a flange 12 in the form of a annular projection can be formed on the inner side of a chamber 4 of the blade body 2, the flange 12 surrounds an opening which is smaller than the cross-section of the chamber 4, whereby the opening can be closed by a correspondingly formed plug body 5.
  • the said opening is smaller than the cross-section of the chamber 4, however it is large enough that the blade body 2 can be made from a cast material or a sinter material using moulding tools without excessive complexity or fragileness.
  • the said opening has in particular a cross-section which facilitates a necessary, regular removal of a mould core.
  • the securing ring 11 again serves to fix the plug body 5 in the opening surrounded by the flange 12 in the form of the annular projection, whereby the essentially annular channel receiving the securing 11 is again formed by the essentially annular grooves 7 and 8 which in this case are formed on the inner peripheral edge of the flange 12 and in the outer peripheral edge of the plug body 5 respectively.
  • the plug body 5 is inserted in the way of a plug into an opening in the end of a blade body 2. This is appropriate and advantageous if the only or predominant function of the plug body 5 is a closing function.
  • plug body 5 is to have further functions it may be appropriate to form the plug body 5 as a cap over the open end of the blade body 2.
  • FIGS 5 and 6 show such an embodiment.
  • an essentially annular step 13 is formed on the outside of the open end of the blade body 2 which is filled by an annular projection 14 arranged on a plug body 5, so that the outer periphery of the essentially annular projection 14 is aligned with the outer periphery of the blade body under the essentially annular step 13.
  • the cross-section of the chamber formed in the blade body 2 can narrow in the shape of a cone, as shown, in the direction of the open end of the blade body 2.
  • the plug body 5 can have practically any form as a continuation of the blade body, whereby according to figures 5 and 6 it is possible to form the plug body 5 as a segment of a turbine shroud 17 or as a winglet of the respective blade, the turbine shroud or the winglets having ribs 15 which extend in the circumferential direction of the blades and cooperate with ribs or grooves in adjacent stationary parts of the turbine housing as a kind of labyrinth seal in order to ensure that the working medium in the form of a gas or steam flowing through the turbine blades cannot flow radially outside of the turbine blades.
  • FIG. 7 It is also possible to connect the blade body 2 of a turbine blade 1 with an associated root 16 according to figure 7 .
  • This root 16 has an upside down fir tree shape with which the turbine blade 1 can be inserted into a correspondingly formed recess in the rotor shaft of a turbine.
  • the connection of the blade body 2 and the root 16 can also be arranged similar to the arrangement in figure 6 where the plug body extends from the blade body 2 at its radially outer end.
  • the securing ring or clip 11 mentioned above can have an annular ring shape, but this must not always be the case. It is for example also possible to use an "open" ring shape like a C-shape ring or clip 11 in accordingly formed grooves 9 and 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12181109.5A 2012-08-21 2012-08-21 Leit- oder Laufsschaufel mit Spitzenabdeckung Withdrawn EP2700788A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12181109.5A EP2700788A1 (de) 2012-08-21 2012-08-21 Leit- oder Laufsschaufel mit Spitzenabdeckung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12181109.5A EP2700788A1 (de) 2012-08-21 2012-08-21 Leit- oder Laufsschaufel mit Spitzenabdeckung

Publications (1)

Publication Number Publication Date
EP2700788A1 true EP2700788A1 (de) 2014-02-26

Family

ID=46704529

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12181109.5A Withdrawn EP2700788A1 (de) 2012-08-21 2012-08-21 Leit- oder Laufsschaufel mit Spitzenabdeckung

Country Status (1)

Country Link
EP (1) EP2700788A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108406233A (zh) * 2018-03-05 2018-08-17 重庆天骄航空动力有限公司 不规则壳体构件内腔底部环形槽的加工方法
EP3536433A1 (de) * 2018-03-08 2019-09-11 Rolls-Royce Corporation Techniken und baugruppen zum verbinden von komponenten
US10766105B2 (en) 2015-02-26 2020-09-08 Rolls-Royce Corporation Repair of dual walled metallic components using braze material

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4314160A1 (de) * 1992-05-13 1993-11-18 Siemens Ag Fügeverbindung und Verfahren zu ihrer Herstellung
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
US20050196277A1 (en) 2004-03-02 2005-09-08 General Electric Company Gas turbine bucket tip cap
EP1772593A2 (de) 2005-10-04 2007-04-11 The General Electric Company Doppelschicht-Schaufelspitzekappe
US20070258825A1 (en) 2006-05-08 2007-11-08 General Electric Company Turbine blade tip cap
EP2022944A1 (de) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Schaufelbefestigung in einer Umfangsnut mittels aushärtbarer Keramikmasse
US20090196761A1 (en) * 2008-02-01 2009-08-06 Siemens Power Generation, Inc. Metal injection joining
US7686571B1 (en) * 2007-04-09 2010-03-30 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US20100080711A1 (en) 2006-09-20 2010-04-01 United Technologies Corporation Turbine blade with improved durability tip cap
US7704044B1 (en) * 2006-11-28 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with attachment shear inserts
US8052391B1 (en) * 2009-03-25 2011-11-08 Florida Turbine Technologies, Inc. High temperature turbine rotor blade
DE102011120691A1 (de) * 2010-12-21 2012-06-21 Alstom Technology Ltd. Gebaute Schaufelanordnung für eine Gasturbine sowie Verfahren zum Betrieb einer solchen Schaufelanordnung

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4314160A1 (de) * 1992-05-13 1993-11-18 Siemens Ag Fügeverbindung und Verfahren zu ihrer Herstellung
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
US20050196277A1 (en) 2004-03-02 2005-09-08 General Electric Company Gas turbine bucket tip cap
EP1772593A2 (de) 2005-10-04 2007-04-11 The General Electric Company Doppelschicht-Schaufelspitzekappe
US20070258825A1 (en) 2006-05-08 2007-11-08 General Electric Company Turbine blade tip cap
US20100080711A1 (en) 2006-09-20 2010-04-01 United Technologies Corporation Turbine blade with improved durability tip cap
US7704044B1 (en) * 2006-11-28 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with attachment shear inserts
US7686571B1 (en) * 2007-04-09 2010-03-30 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
EP2022944A1 (de) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Schaufelbefestigung in einer Umfangsnut mittels aushärtbarer Keramikmasse
US20090196761A1 (en) * 2008-02-01 2009-08-06 Siemens Power Generation, Inc. Metal injection joining
US8052391B1 (en) * 2009-03-25 2011-11-08 Florida Turbine Technologies, Inc. High temperature turbine rotor blade
DE102011120691A1 (de) * 2010-12-21 2012-06-21 Alstom Technology Ltd. Gebaute Schaufelanordnung für eine Gasturbine sowie Verfahren zum Betrieb einer solchen Schaufelanordnung

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10766105B2 (en) 2015-02-26 2020-09-08 Rolls-Royce Corporation Repair of dual walled metallic components using braze material
US11731218B2 (en) 2015-02-26 2023-08-22 Rolls-Royce Corporation Repair of dual walled metallic components using braze material
CN108406233A (zh) * 2018-03-05 2018-08-17 重庆天骄航空动力有限公司 不规则壳体构件内腔底部环形槽的加工方法
CN108406233B (zh) * 2018-03-05 2019-08-09 重庆天骄航空动力有限公司 不规则壳体构件内腔底部环形槽的加工方法
EP3536433A1 (de) * 2018-03-08 2019-09-11 Rolls-Royce Corporation Techniken und baugruppen zum verbinden von komponenten
US11338396B2 (en) 2018-03-08 2022-05-24 Rolls-Royce Corporation Techniques and assemblies for joining components
US20230033578A1 (en) * 2018-03-08 2023-02-02 Rolls-Royce Corporation Techniques and assemblies for joining components

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