EP3000991A1 - Carter de turbomachine, procédé de fabrication d'un tel carter et turbine à gaz avec un tel carter - Google Patents

Carter de turbomachine, procédé de fabrication d'un tel carter et turbine à gaz avec un tel carter Download PDF

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Publication number
EP3000991A1
EP3000991A1 EP14186851.3A EP14186851A EP3000991A1 EP 3000991 A1 EP3000991 A1 EP 3000991A1 EP 14186851 A EP14186851 A EP 14186851A EP 3000991 A1 EP3000991 A1 EP 3000991A1
Authority
EP
European Patent Office
Prior art keywords
casing
apertures
turbo machine
axial
axially extending
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Withdrawn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
EP14186851.3A
Other languages
German (de)
English (en)
Inventor
Johannes Richter
Giovanni Cataldi
Nikolas Wiedemann
Armin Busekros
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.)
GE Vernova 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 EP14186851.3A priority Critical patent/EP3000991A1/fr
Publication of EP3000991A1 publication Critical patent/EP3000991A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to the technology of turbo machines. It refers to a casing of a turbo machine according to the preamble of claim 1.
  • Fig. 3 shows in a perspective view an example of a turbo machine in form of a gas turbine of the applicant of type GT24.
  • the gas turbine 20 of Fig. 3 comprises a rotor 21 rotating about a machine axis and being enclosed by an (inner) casing 22.
  • gas turbine 20 comprises an air intake 23, a compressor 24, a first combustor 25, a first, high pressure (HP) turbine 26, a second combustor 27, a second, low pressure (LP) turbine 28 and an exhaust gas outlet 29.
  • HP high pressure
  • LP low pressure
  • the resulting hot gas drives HP turbine 26.
  • the reheated hot gas then drives LP turbine 28 and leaves the machine at exhaust gas outlet 29.
  • the root cause for the radial, thermal deformation is circumferential stresses in the casing coming from different temperatures in the casing.
  • the hotter part, which tries to expand, is under pressure, but it is held back by the adjacent colder part, which tries to contract, and is therewith under tension.
  • the result is radial deformation of the casing between ideal, independent deformation of the colder and ideal, independent deformation of the hotter section as they are linked together.
  • Document US 4,522,559 deals with a compressor section of a gas turbine engine, comprising a double wall casing, wherein a nonstructural inner wall is removably attached to a thin, structural outer casing.
  • the inner wall isolates the thin stator outer casing during transient turbine operations of throttle burst and throttle chop.
  • throttle burst and chop the nonstructural inner wall delays rapid heating and cooling of the relatively thin-walled outer casing, and reduces radial misalignment between the stator casing and rotor due to uneven thermal expansion and contraction.
  • the non structural inner wall evens-out thermal expansion and contraction of the stator casing with respect to the rotor.
  • thermal insulation material is used between the nonstructural inner wall and outer casing.
  • a casing of a turbo machine according to the invention extends along a machine axis of said turbo machine and coaxially surrounds a rotor of said turbo machine, thereby defining an annular hot gas path.
  • the casing is characterized in that it comprises at least one axial section, wherein a plurality of axially extending apertures are provided in the wall of said casing and distributed around its circumference in order to reduce the individual influence of said at least one axial section on an overall radial deformation by reducing thermally induced circumferential stresses in said at least one axial section.
  • said axially extending apertures have the form of axial slots, each said slot having an axial length and a width.
  • each of said slots has a width between 0,5mm and 10 mm and an axial length between 1 mm and 400mm, preferably between 1 mm and 200mm.
  • the number of said apertures that are distributed around the circumference of said casing in said at least one axial section is between 1 and 50.
  • said axially extending apertures are machined apertures.
  • said at least one section with said plurality of axially extending apertures is a separate element, which is axially connected to the remaining part of said casing.
  • each of said apertures is equipped with a seal.
  • each of said apertures is sealed with a sealing plate, especially in form of a sheet metal plate.
  • the width of said apertures is defined in such a way as to achieve a minimum width in the apertures during targeted, thermally stable conditions of said turbo machine.
  • the inventive method for manufacturing a casing according to the invention is characterized in that said at least one section is equipped with said axial apertures when being separated from said remaining part of said casing, and is then connected to said remaining part of said casing.
  • the gas turbine according to the invention comprises a rotor, which rotates around a machine axis and is surrounded by an axially extending casing in a coaxial arrangement. It is characterized in that said casing is a casing according the invention.
  • the invention comprises (in one embodiment) the "slotting" of the casing of an axial turbo machine, especially a gas turbine, in areas with a temperature profile or a temperature gradient in axial direction.
  • Fig. 1 (a) shows a part of such a turbo machine 10 comprising a rotor 11 with rotating blades 14, which extends along and rotates around a machine axis 12, and is coaxially surrounded by a casing 13, which is equipped on its inner side with stationary guiding vanes 15.
  • the casing 13 shows a temperature gradient with temperature T2 at the right end being higher than temperature T1 at a distance to the left (T2 > T1) or vice versa.
  • the casing 13 which is assembled from an upper half-shell 13a and a lower half-shell 13b in a parting plane by means of flanges 18a and 18b, comprises an equally distributed plurality of slots 16 (the embodiment of Fig. 2 has 5 slots 16 in upper half-shell 13a and 5 slots 16 in the lower half-shell 13b).
  • each slot 16 is sealed with a sealing plate 19 (see Figs. 1(b) and 2 ).
  • This sealing plate 19 may especially be a sheet metal plate.
  • the casing 13 of a turbo machine 10 receives at distinct sections a distinct number of axial apertures, especially slots 16, over its entire height/wall thickness, distributed around its circumference, with the purpose to prevent the individual influence of said sections on the overall radial deformation by reducing circumferential stresses in said section.
  • Said sections influence the overall radial deformation of said casing 13 due to thermally induced stresses.
  • said axially extending apertures around the circumference of solid casing are machined.
  • said section with said apertures is axially separated from the remaining part of said casing 13. Moreover the axially separated section is first equipped with said axial apertures around its circumference and then reconnected to the casing 13.
  • the width W of said apertures (slots) is defined in such a way to achieve a minimum width in the apertures during targeted, thermally stable conditions.
  • apertures are defined in such a way as to meet also the geometrical requirements of interfacing parts.
  • the number of said apertures (slots) around the circumference of said casing 13 may vary between 1 and 50.
  • the width W is preferably between 0,5mm and 10mm and an axial length L between 1 mm and 200mm.
  • Said apertures may additionally be equipped with seals. Especially, they may be sealed with sheet metal plates.
  • Said apertures are especially used to influence asymmetric deformations of said casing during transient and stead state conditions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14186851.3A 2014-09-29 2014-09-29 Carter de turbomachine, procédé de fabrication d'un tel carter et turbine à gaz avec un tel carter Withdrawn EP3000991A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14186851.3A EP3000991A1 (fr) 2014-09-29 2014-09-29 Carter de turbomachine, procédé de fabrication d'un tel carter et turbine à gaz avec un tel carter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14186851.3A EP3000991A1 (fr) 2014-09-29 2014-09-29 Carter de turbomachine, procédé de fabrication d'un tel carter et turbine à gaz avec un tel carter

Publications (1)

Publication Number Publication Date
EP3000991A1 true EP3000991A1 (fr) 2016-03-30

Family

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Family Applications (1)

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EP14186851.3A Withdrawn EP3000991A1 (fr) 2014-09-29 2014-09-29 Carter de turbomachine, procédé de fabrication d'un tel carter et turbine à gaz avec un tel carter

Country Status (1)

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EP (1) EP3000991A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110219708A (zh) * 2018-03-01 2019-09-10 通用电气公司 带有可调节的栅格结构的壳

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0073689A1 (fr) * 1981-08-31 1983-03-09 Elliott Turbomachinery Company, Inc. Méthode et dispositif pour contrôler les dilatations thermiques
US4522559A (en) 1982-02-19 1985-06-11 General Electric Company Compressor casing
US20050132707A1 (en) * 2001-11-20 2005-06-23 Andreas Gebhardt Gas turbo set
US20090097968A1 (en) * 2007-10-12 2009-04-16 General Electric Company Apparatus and method for clearance control of turbine blade tip
EP2623719A1 (fr) * 2012-01-30 2013-08-07 Pratt & Whitney Canada Corp. Fentes de soulagement de contrainte pour bague d'aube de turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0073689A1 (fr) * 1981-08-31 1983-03-09 Elliott Turbomachinery Company, Inc. Méthode et dispositif pour contrôler les dilatations thermiques
US4522559A (en) 1982-02-19 1985-06-11 General Electric Company Compressor casing
US20050132707A1 (en) * 2001-11-20 2005-06-23 Andreas Gebhardt Gas turbo set
US20090097968A1 (en) * 2007-10-12 2009-04-16 General Electric Company Apparatus and method for clearance control of turbine blade tip
EP2623719A1 (fr) * 2012-01-30 2013-08-07 Pratt & Whitney Canada Corp. Fentes de soulagement de contrainte pour bague d'aube de turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110219708A (zh) * 2018-03-01 2019-09-10 通用电气公司 带有可调节的栅格结构的壳

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