EP0949404A1 - Segmented cascade made from individual vanes which are bolted together - Google Patents

Segmented cascade made from individual vanes which are bolted together Download PDF

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Publication number
EP0949404A1
EP0949404A1 EP98302733A EP98302733A EP0949404A1 EP 0949404 A1 EP0949404 A1 EP 0949404A1 EP 98302733 A EP98302733 A EP 98302733A EP 98302733 A EP98302733 A EP 98302733A EP 0949404 A1 EP0949404 A1 EP 0949404A1
Authority
EP
European Patent Office
Prior art keywords
stationary blade
shroud
blade
integrated
stationary
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Withdrawn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
EP98302733A
Other languages
German (de)
French (fr)
Inventor
Masato c/o Mitsubishi Heavy Ind. Ltd. Kataoka
Masao c/o Mitsubishi Heavy Ind. Ltd. Terazaki
Yukihiro c/o Mitsubishi Heavy Ind. Ltd. Hashimoto
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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
Priority to JP9002974A priority Critical patent/JPH10196308A/en
Priority claimed from JP9002974A external-priority patent/JPH10196308A/en
Priority to CA002231986A priority patent/CA2231986A1/en
Priority claimed from CA002231986A external-priority patent/CA2231986A1/en
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to EP98302733A priority patent/EP0949404A1/en
Priority to US09/414,394 priority patent/US6261058B1/en
Publication of EP0949404A1 publication Critical patent/EP0949404A1/en
Withdrawn legal-status Critical Current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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • 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
    • 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
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the present invention relates to a gas turbine stationary blade and, more particularly, to a gas turbine stationary blade of such a construction that thermal barrier coating (TBC) can be applied to the blade surface and a crack can be prevented from being made by a thermal stress etc. at the shroud portion.
  • TBC thermal barrier coating
  • FIG. 4 is a perspective view of a gas turbine stationary blade
  • FIG. 5 is a plane cascade view.
  • one inside shroud 11 and one outside shroud 12 are provided with respect to one stationary blade 1 as shown in FIG. 4.
  • the stationary blade 1 has a construction such that a seal plate is put between the shrouds which are adjacent to each other to supply cooling air, by which the leakage of cooling air is decreased.
  • the decrease in leakage of cooling air caused by blade division is prevented conventionally by one-piece casting the stationary blades as an integrated segment or by welding singly cast blades into an integrated segment.
  • singly cast blades are welded into an integrated segment, a high thermal stress cannot be allowed to escape by the temperature difference between the dorsal side and ventral side of blade, so that a crack develops in the shroud.
  • thermal barrier coating etc. are applied to the blade surface by spraying using a coating gun to reduce the thermal load of blade surface to the utmost.
  • the coating gun does not enter a curvedly formed space between the blades, so that coating cannot be applied to the whole blade surface.
  • an object of the present invention is to provide a gas turbine stationary blade of integrated segment construction, in which thermal barrier coating can be applied to the whole blade surface and an excessive stress is not produced in a shroud, and a manufacturing method therefor.
  • a plate seat for bolt tightening is provided at each end face portion of an inside shroud and an outside shroud for a gas turbine stationary blade, and several stationary blades are integrated by joining the plate seats of the adjacent shrouds by means of bolts and nuts.
  • thermal barrier coating be applied to the whole surface of stationary blade to reduce thermal load on the stationary blade surface.
  • the number of seals inserted between the blades can be decreased, so that the leakage of cooling air can be reduced, whereby the performance of gas turbine is improved.
  • the plate seat for bolt tightening is provided at each end face portion of the inside shroud and the outside shroud for the gas turbine stationary blade, and several stationary blades are integrated by joining the plate seats of the adjacent shrouds by means of bolts and nuts.
  • the mechanically joined stationary blade of integrated segment construction in accordance with the present invention since the number of portions where a seal is inserted can be decreased by making several stationary blades an integrated segment, the leakage of cooling air can further be reduced, whereby the performance of gas turbine can be improved.
  • thermal barrier coating can be applied to the whole blade surface by performing the thermal barrier coating operation before joining the plate seats by means of bolts and nuts, the thermal load on the blade can be reduced, so that a higher temperature of gas turbine can be overcome.
  • the present invention achieves large effects contributing to increased reliability and performance of gas turbine.
  • FIGS. 1 to 3 reference numeral 1 denotes a stationary blade, 2 denotes an inside shroud, and 3 denotes an outside shroud.
  • the stationary blade 1 is provided between the shrouds 2 and 3.
  • plate seats 4 and 5 for bolt tightening are erected, respectively.
  • These plate seats 4 and 5 each are formed with a bolt hole for inserting a bolt 6.
  • the plate seats 4 and 5 of the adjacent shrouds 2 and 3 are joined mechanically by means of the bolts 6 and nuts 7, by which several single blades are joined into an integrated segment.
  • the stationary blade of integrated segment construction can be obtained by integrating several stationary blades 1 by joining the plate seats 4 and 5 of the adjacent shrouds 2 and 3 by means of the bolts 6 and nuts 7 after thermal barrier coating is applied to a single stationary blade 1.

Abstract

The present invention provides a stationary blade of integrated segment construction, in which thermal barrier coating can be applied to the whole blade surface and an excessive stress is not produced in a shroud. A plate seat for bolt tightening is provided at each end face portion of an inside shroud and an outside shroud for a gas turbine stationary blade. Several stationary blades are integrated by joining the plate seats of the adjacent shrouds by means of bolts and nuts to provide a stationary blade of integrated segment construction.

Description

    FIELD OF THE INVENTION AND RELATED ART STATEMENT
  • The present invention relates to a gas turbine stationary blade and, more particularly, to a gas turbine stationary blade of such a construction that thermal barrier coating (TBC) can be applied to the blade surface and a crack can be prevented from being made by a thermal stress etc. at the shroud portion.
  • FIG. 4 is a perspective view of a gas turbine stationary blade, and FIG. 5 is a plane cascade view. For the present gas turbine stationary blade, one inside shroud 11 and one outside shroud 12 are provided with respect to one stationary blade 1 as shown in FIG. 4.
  • The stationary blade 1 has a construction such that a seal plate is put between the shrouds which are adjacent to each other to supply cooling air, by which the leakage of cooling air is decreased. When a single blade construction, in which blades are divided separately, is used because of the need for applying thermal barrier coating to the blade surface, the number of portions where the seal plate is inserted increases, resulting in increased leakage of cooling air.
  • Also, in order to decrease the leakage of cooling air, several stationary blades are one-piece cast as an integrated segment, or singly cast blades are joined by welds into an integrated segment. In this case, however, thermal barrier coating cannot be applied to the whole surface of blade.
  • As described above, the decrease in leakage of cooling air caused by blade division is prevented conventionally by one-piece casting the stationary blades as an integrated segment or by welding singly cast blades into an integrated segment. However, if singly cast blades are welded into an integrated segment, a high thermal stress cannot be allowed to escape by the temperature difference between the dorsal side and ventral side of blade, so that a crack develops in the shroud.
  • With the recent increase in the gas turbine inlet temperature, thermal barrier coating etc. are applied to the blade surface by spraying using a coating gun to reduce the thermal load of blade surface to the utmost. In this case, if stationary blades are one-piece cast or singly cast blades are welded into an integrated segment, the coating gun does not enter a curvedly formed space between the blades, so that coating cannot be applied to the whole blade surface.
    • OBJECT AND SUMMARY OF THE INVENTION
  • The present invention was made to solve the above problems. Accordingly, an object of the present invention is to provide a gas turbine stationary blade of integrated segment construction, in which thermal barrier coating can be applied to the whole blade surface and an excessive stress is not produced in a shroud, and a manufacturing method therefor.
  • To achieve the above object, a plate seat for bolt tightening is provided at each end face portion of an inside shroud and an outside shroud for a gas turbine stationary blade, and several stationary blades are integrated by joining the plate seats of the adjacent shrouds by means of bolts and nuts.
  • In the stationary blade of integrated segment construction in accordance with the present invention, it is preferable that thermal barrier coating be applied to the whole surface of stationary blade to reduce thermal load on the stationary blade surface.
  • To manufacture the above-mentioned stationary blade of integrated segment construction in accordance with the present invention, after thermal barrier coating is applied to a single stationary blade, several stationary blades are integrated by joining plate seats by means of bolts and nuts. Thereby, a stationary blade to the whole surface of which thermal barrier coating is applied can be manufactured easily.
  • By employing the stationary blade of integrated segment construction in accordance with the present invention, the number of seals inserted between the blades can be decreased, so that the leakage of cooling air can be reduced, whereby the performance of gas turbine is improved.
  • When an excessive force is applied to the stationary blade of the present invention, a relative slide occurs at the tightening face of bolted plate seat etc., by which an excessive stress created at the shroud portion can be prevented. Also, because the stationary blades can easily be disassembled into a single blade by removing the bolts, a coating gun reaches the whole area, so that the whole blade surface can be coated.
  • As described above, in the gas turbine stationary blade in accordance with the present invention, the plate seat for bolt tightening is provided at each end face portion of the inside shroud and the outside shroud for the gas turbine stationary blade, and several stationary blades are integrated by joining the plate seats of the adjacent shrouds by means of bolts and nuts.
  • According to the mechanically joined stationary blade of integrated segment construction in accordance with the present invention, since the number of portions where a seal is inserted can be decreased by making several stationary blades an integrated segment, the leakage of cooling air can further be reduced, whereby the performance of gas turbine can be improved.
  • Also, for the stationary blade in accordance with the present invention, since thermal barrier coating can be applied to the whole blade surface by performing the thermal barrier coating operation before joining the plate seats by means of bolts and nuts, the thermal load on the blade can be reduced, so that a higher temperature of gas turbine can be overcome.
  • Further, since the thermal deformation caused by the temperature difference between the dorsal side and ventral side of blade can be absorbed by the relative slide on the bolted faces, an excessive stress created in the shroud can be prevented, so that the reliability of blade is increased.
  • As described above, the present invention achieves large effects contributing to increased reliability and performance of gas turbine.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is an elevation showing a stationary blade of integrated segment construction in accordance with one embodiment of the present invention;
  • FIG. 2 is a plan view of the stationary blade of integrated segment construction shown in FIG. 1;
  • FIG. 3 is a sectional view taken along the line B-B of FIG. 2, showing a bolt tightening portion;
  • FIG. 4 is a perspective view showing a construction of a conventional gas turbine stationary blade; and
  • FIG. 5 is a plane cascade view for the conventional gas turbine stationary blade.
    • DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
  • One embodiment of the present invention will be described in detail with reference to the accompanying drawings. In FIGS. 1 to 3, reference numeral 1 denotes a stationary blade, 2 denotes an inside shroud, and 3 denotes an outside shroud. The stationary blade 1 is provided between the shrouds 2 and 3. At each end of the inside shroud 2 and outside shroud 3 for the stationary blade 1, plate seats 4 and 5 for bolt tightening are erected, respectively. These plate seats 4 and 5 each are formed with a bolt hole for inserting a bolt 6. As shown in FIG. 2, the plate seats 4 and 5 of the adjacent shrouds 2 and 3 are joined mechanically by means of the bolts 6 and nuts 7, by which several single blades are joined into an integrated segment.
  • Thus, several stationary blades 1 are integrated to form an integrated segment. By using this construction, when an excessive force due to a thermal stress is applied, a relative slide occurs on the tightening faces A of the plate seats 4 and 5 and shrouds 2 and 3, by which an excessive stress created at the shroud portion can be prevented. Also, the whole surface of blade can be coated because the blades can easily be disassembled into a single blade by removing the bolts 6.
  • That is, the stationary blade of integrated segment construction can be obtained by integrating several stationary blades 1 by joining the plate seats 4 and 5 of the adjacent shrouds 2 and 3 by means of the bolts 6 and nuts 7 after thermal barrier coating is applied to a single stationary blade 1.
  • In this specification the terms 'radial' and 'axial' are used with reference to the longitudinal shaft axis of a gas turbine engine.

Claims (6)

  1. A stationary blade of integrated segment construction, in which a plate seat for bolt tightening is provided at each end face portion of an inside shroud and an outside shroud for a gas turbine stationary blade, and several stationary blades are integrated by joining said plate seats of the adjacent shrouds by means of bolts and nuts.
  2. A stationary blade of integrated segment construction according to claim 1, wherein thermal barrier coating is applied to the whole surface of said stationary blade.
  3. A manufacturing method for a stationary blade of integrated segment construction, in which after thermal barrier coating is applied to a single stationary blade, several stationary blades are integrated by joining plate seats for bolt tightening provided at each end face portion of an inside shroud and an outside shroud by means of bolts and nuts.
  4. A stationary blade for a gas turbine engine, the blade being of integrated segment construction and comprising a blade portion having an inside shroud member at a radially inner end and an outside shroud member at a radially outer end thereof; the inside and outside shroud members having generally axially directed faces which align with the corresponding faces of adjacent stationary blade shroud members to form an integrated segment, the stationary blade being characterised by having plate seat members adjacent said generally axially directed shroud faces, said plate seat members of adjacent blades being fixable together to form an integrated segment.
  5. A stationary blade according to claim 4 wherein adjacent blades are fixed together with bolts and nuts passing through apertures in the plate seat members.
  6. A stationery blade according to either claim 4 or claim 5 wherein the plate seat members permit relative movement between adjacent blades under stress.
EP98302733A 1997-01-10 1998-04-08 Segmented cascade made from individual vanes which are bolted together Withdrawn EP0949404A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
JP9002974A JPH10196308A (en) 1997-01-10 1997-01-10 Integrated segment structure stationary blade and manufacture therefor
CA002231986A CA2231986A1 (en) 1997-01-10 1998-03-12 Stationary blade of integrated segment construction and manufacturing method therefor
EP98302733A EP0949404A1 (en) 1997-01-10 1998-04-08 Segmented cascade made from individual vanes which are bolted together
US09/414,394 US6261058B1 (en) 1997-01-10 1999-10-07 Stationary blade of integrated segment construction and manufacturing method therefor

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
JP9002974A JPH10196308A (en) 1997-01-10 1997-01-10 Integrated segment structure stationary blade and manufacture therefor
CA002231986A CA2231986A1 (en) 1997-01-10 1998-03-12 Stationary blade of integrated segment construction and manufacturing method therefor
US4960998A 1998-03-27 1998-03-27
EP98302733A EP0949404A1 (en) 1997-01-10 1998-04-08 Segmented cascade made from individual vanes which are bolted together
US09/414,394 US6261058B1 (en) 1997-01-10 1999-10-07 Stationary blade of integrated segment construction and manufacturing method therefor

Publications (1)

Publication Number Publication Date
EP0949404A1 true EP0949404A1 (en) 1999-10-13

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP98302733A Withdrawn EP0949404A1 (en) 1997-01-10 1998-04-08 Segmented cascade made from individual vanes which are bolted together

Country Status (1)

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EP (1) EP0949404A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1199440A2 (en) 2000-10-16 2002-04-24 ALSTOM (Switzerland) Ltd Stator nozzle segments with flange connection
EP1239058A2 (en) * 2001-03-06 2002-09-11 Mitsubishi Heavy Industries, Ltd. Coating for gas turbine blades
US8371810B2 (en) 2009-03-26 2013-02-12 General Electric Company Duct member based nozzle for turbine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4015910A (en) * 1976-03-09 1977-04-05 The United States Of America As Represented By The Secretary Of The Air Force Bolted paired vanes for turbine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4015910A (en) * 1976-03-09 1977-04-05 The United States Of America As Represented By The Secretary Of The Air Force Bolted paired vanes for turbine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1199440A2 (en) 2000-10-16 2002-04-24 ALSTOM (Switzerland) Ltd Stator nozzle segments with flange connection
US6592326B2 (en) 2000-10-16 2003-07-15 Alstom (Switzerland) Ltd Connecting stator elements
EP1199440A3 (en) * 2000-10-16 2004-01-21 ALSTOM (Switzerland) Ltd Stator nozzle segments with flange connection
USRE43611E1 (en) 2000-10-16 2012-08-28 Alstom Technology Ltd Connecting stator elements
EP1239058A2 (en) * 2001-03-06 2002-09-11 Mitsubishi Heavy Industries, Ltd. Coating for gas turbine blades
EP1239058A3 (en) * 2001-03-06 2004-03-17 Mitsubishi Heavy Industries, Ltd. Coating for gas turbine blades
US6811373B2 (en) 2001-03-06 2004-11-02 Mitsubishi Heavy Industries, Ltd. Turbine moving blade, turbine stationary blade, turbine split ring, and gas turbine
US8371810B2 (en) 2009-03-26 2013-02-12 General Electric Company Duct member based nozzle for turbine

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Inventor name: HASHIMOTO, YUKIHIRO C/O MITSUBISHI HEAVY IND. LTD

Inventor name: TERAZAKI, MASAO, C/O MITSUBISHI HEAVY IND. LTD.

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