EP2915957A1 - Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication - Google Patents

Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication Download PDF

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Publication number
EP2915957A1
EP2915957A1 EP14157781.7A EP14157781A EP2915957A1 EP 2915957 A1 EP2915957 A1 EP 2915957A1 EP 14157781 A EP14157781 A EP 14157781A EP 2915957 A1 EP2915957 A1 EP 2915957A1
Authority
EP
European Patent Office
Prior art keywords
duct
inner tube
turbine
outer tube
parts
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Withdrawn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
EP14157781.7A
Other languages
German (de)
English (en)
Inventor
Magnus Hasselqvist
Janos Szijarto
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 EP14157781.7A priority Critical patent/EP2915957A1/fr
Publication of EP2915957A1 publication Critical patent/EP2915957A1/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Withdrawn legal-status Critical Current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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • 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
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the present invention relates to a tubular duct for connecting a combustion chamber and a turbine of a gas turbine - i.e. a gas turbine engine -, comprising a first opening designed to face said combustion chamber and a second opening designed to face said turbine. Furthermore, the invention relates to a manufacturing method for a tubular duct of the kind above. Finally, the present invention relates to a gas turbine, comprising a compressor, a turbine, a burning chamber and duct of the kind above.
  • a tubular duct and a gas turbine as presented above are generally known.
  • a duct is made of a number of metal sheets, which are reshaped into three-dimensional parts by means of plastic deformation and then welded together.
  • such a manufacturing method suffers from imprecision of the reshaped parts, on the one hand, and from the limitation to a more or less constant thickness of the parts over the whole curved plane, on the other hand.
  • Another problem of prior art gas turbines is the cooling of the turbine parts, which in particular counts for the vane platforms, which are generally more difficult to cool than airfoils. Cooling air released as film (or as jets) into the hot gas stream has a strong tendency to be swept up by the residual swirl from the burner and aggregate in cold streaks. When this happens, the cold streaks can cause thermal stresses, which result in premature crack initiation. Furthermore, the positions of said cold streaks are difficult to predict and may to some extent change with loading conditions (pilot flow, fuel, mass flow etc.). Accordingly, the associated crack initiation life is difficult to assess.
  • a tubular duct as disclosed in the opening paragraph, wherein said duct is cast by means of precision casting technology.
  • a gas turbine comprising a compressor, a turbine, a burning chamber and a duct of the kind above.
  • cast parts may be produced with high precision, so that the duct can easily be integrated into a gas turbine without reworking.
  • cast ducts allow for a variable thickness and complex shapes, in particular embossments.
  • the inner (concave) duct surface may be even and smooth so as to provide for beneficial flow conditions for the hot burnt gas, whereas the outer (convex) duct surface may be uneven and structured.
  • a highly effective convective cooling system may be realized also causing a beneficial temperature profile in the turbine by reducing/eliminating cold streaks.
  • IN939 may be chosen as a material for the duct respectively parts of the duct.
  • said duct comprises a plurality of parts. In this way assembly of the duct may be eased.
  • said duct comprises an outer tube and an inner tube with a gap in-between, wherein the outer tube and the inner tube are cast in separate molds.
  • the manufacturing method comprises the steps of molding an outer tube and an inner tube in separate molds and mounting the outer tube to the inner tube, whereby a gap between the outer tube and the inner tube is created. Accordingly, not just assembly of the duct is eased, but also a channel for cooling air is provided, so that the temperature of the duct may be kept low.
  • the outer tube and/or the inner tube is/are split into separate tube parts in an axial plane of the duct. Accordingly, the manufacturing method comprises the steps of
  • the gap is connected to a first vent in the outer tube situated in the region of the first opening and to a second vent in the inner tube situated in the region of the second opening.
  • cooling air is drawn into the gap from the outside by means of the first vent and then drawn into the inner tube by means of the second vent. Accordingly, the temperature of the duct can be kept low.
  • the outer tube and/or the inner tube comprise(s) assembly points and/or bumps and/or fins facing the gap.
  • spacers are provided so that the gap is created in a predetermined way when the outer tube is mounted to the inner tube.
  • said assembly points or bumps may be ring shaped or dot shaped.
  • the bumps and spacers may also be used for guiding the cooling air in the gap in a desired way.
  • bumps may be used to cause turbulences, which in turn increase cooling in this area. Accordingly, the local cooling effect in a particular area of the duct may be influenced by the design of the bumps/fins.
  • a pin can be welded onto an assembly point on the inner tube and to the outer tube.
  • a screw can be screwed into a (ring shaped and threaded) assembly point.
  • the outer tube can be mounted to the screws by means of screw nuts.
  • a threaded pin can be welded onto an assembly point on the inner tube and used for mounting the outer tube to the inner tube by means of screw nuts.
  • Fig. 1 and 2 show a tubular duct 1 for connecting a combustion chamber and a turbine of a gas turbine ( Fig. 1 shows a back view and Fig. 2 shows a cross section)
  • the duct 1 is cast by means of precision casting technology and comprises a first opening 2 designed to face said combustion chamber and a second opening 3 designed to face said turbine.
  • said duct 1 comprises an outer tube 4 and an inner tube 5 with a gap 6 in-between, wherein the outer tube 4 and the inner tube 5 are cast in separate molds.
  • the gap 4 is connected to a first vent 7 in the outer tube 2 situated in the region of the first opening 2 and to second vents 8 in the inner tube 3 situated in the region of the second opening 3. In this way, cooling air is drawn into the gap 6 from the outside by means of the first vent 7 and then drawn into the inner tube 5 (and as a consequence into the turbine) by means of the second vents 8.
  • the duct 1 may also comprise a number of separate vents 7. Accordingly, there may also be a single second vent 8 instead of the plurality of second vents 8 shown in Figs. 1 and 2 .
  • Fig. 3 now shows an exploded view of the duct 1 disclosing that it comprises a plurality of parts 4a, 4b, 5a, 5b.
  • the outer tube 4 is split into separate tube parts 4a, 4b
  • the inner tube 5 is split into separate tube parts 5a, 5b in this example.
  • Both the outer tube 4 and the inner tube 5 are split an axial plane of the duct 1 in Fig. 3 .
  • the outer tube 4 and the inner tube 5 respectively their parts 4a, 4b, 5a, 5b are cast in separate molds and are assembled in a further step.
  • the part 5a is mounted to part 5b and the parts 4a and 4b are mounted to the resulting inner tube 5.
  • Fig. 4 shows the part 5a of the inner tube 5
  • Fig. 5 shows the inner tube 5 separate from the outer tube 4.
  • assembly points 9, bumps 10 and fins 11 are arranged on the part 5a respectively on the inner tube 5.
  • the gap 6 is created when the outer tube 4 is mounted to the inner tube 5.
  • cooling air is guided within the gap 6 in a desired way.
  • the bumps 10 cause turbulences which in turn increase cooling in this area.
  • the local cooling effect in a particular area of the duct 1 may be influenced by the density of said bumps 10 or generally by the design of the embossments 9, 10 and 11.
  • the inner tube 5 and the outer tube 4 respectively their parts 4a, 4b, 5a and 5b may be welded together, in particular by means of the assembly points 9, which have the form of ring shaped bumps and face holes in the outer tube 4 in this example.
  • a pin can be welded onto respectively into the ring shaped bump 9 on the inner tube 5 and into the hole of the outer tube 4 to keep the tubes 4 and 5 at distance.
  • a screw can be screwed into the ring shaped bump 9 if this is threaded on its inside.
  • the outer tube 4 can be mounted to the screws by means of screw nuts.
  • FIG. 6 finally discloses an exemplary gas turbine 12 - i.e. a exemplary gas turbine engine -, comprising a compressor 13, a burning chamber 14, a turbine 15 and a duct 1 as presented before.
  • the duct 1 is situated between the combustion chamber 14 and the turbine 15 and connects the same. A fluid flow will be guided by the duct 1 from the combustion chamber 14 to the turbine 15.
  • the temperature profile in the duct 1 and in particular in the turbine 15 benefits from the inventive measures. Cooling air, which is released as film into the hot gas stream close to the combustor outlet is beneficial in particular for the first vane of the turbine 15 since it decreases the hot gas temperature on the vane platforms. Consequently, it is beneficial for the first vane, which is always a very critical part of a gas turbine 12, that most of the cooling air used in the combustor is released into the hot gas stream close to the outlet of said combustor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14157781.7A 2014-03-05 2014-03-05 Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication Withdrawn EP2915957A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14157781.7A EP2915957A1 (fr) 2014-03-05 2014-03-05 Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14157781.7A EP2915957A1 (fr) 2014-03-05 2014-03-05 Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication

Publications (1)

Publication Number Publication Date
EP2915957A1 true EP2915957A1 (fr) 2015-09-09

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Application Number Title Priority Date Filing Date
EP14157781.7A Withdrawn EP2915957A1 (fr) 2014-03-05 2014-03-05 Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication

Country Status (1)

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EP (1) EP2915957A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3450851A1 (fr) * 2017-09-01 2019-03-06 Ansaldo Energia Switzerland AG Conduit de transition pour une chambre de combustion tubulaire de turbine à gaz et turbine à gaz comportant un tel conduit de transition

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3844116A (en) * 1972-09-06 1974-10-29 Avco Corp Duct wall and reverse flow combustor incorporating same
WO2000077348A1 (fr) * 1999-06-10 2000-12-21 Pratt & Whitney Canada Corp. Appareil servant a reduire le refroidissement de la gaine de sortie du dispositif combustor
EP1398462A1 (fr) * 2002-09-13 2004-03-17 Siemens Aktiengesellschaft Turbine à gaz et pièce de transition
EP2206886A2 (fr) * 2009-01-07 2010-07-14 General Electric Company Conduit de transition pour un moteur à turbine à gaz, moteur à turbine à gaz et procédé de fabrication associés
US20120272521A1 (en) * 2011-04-27 2012-11-01 Ching-Pang Lee Method of fabricating a nearwall nozzle impingement cooled component for an internal combustion engine
EP2657453A2 (fr) * 2012-04-24 2013-10-30 General Electric Company Système de combustion comprenant une pièce de transition et procédé de formation utilisant un superalliage coulé

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3844116A (en) * 1972-09-06 1974-10-29 Avco Corp Duct wall and reverse flow combustor incorporating same
WO2000077348A1 (fr) * 1999-06-10 2000-12-21 Pratt & Whitney Canada Corp. Appareil servant a reduire le refroidissement de la gaine de sortie du dispositif combustor
EP1398462A1 (fr) * 2002-09-13 2004-03-17 Siemens Aktiengesellschaft Turbine à gaz et pièce de transition
EP2206886A2 (fr) * 2009-01-07 2010-07-14 General Electric Company Conduit de transition pour un moteur à turbine à gaz, moteur à turbine à gaz et procédé de fabrication associés
US20120272521A1 (en) * 2011-04-27 2012-11-01 Ching-Pang Lee Method of fabricating a nearwall nozzle impingement cooled component for an internal combustion engine
EP2657453A2 (fr) * 2012-04-24 2013-10-30 General Electric Company Système de combustion comprenant une pièce de transition et procédé de formation utilisant un superalliage coulé

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3450851A1 (fr) * 2017-09-01 2019-03-06 Ansaldo Energia Switzerland AG Conduit de transition pour une chambre de combustion tubulaire de turbine à gaz et turbine à gaz comportant un tel conduit de transition

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