EP1321627A1 - Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement - Google Patents

Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement Download PDF

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Publication number
EP1321627A1
EP1321627A1 EP01130727A EP01130727A EP1321627A1 EP 1321627 A1 EP1321627 A1 EP 1321627A1 EP 01130727 A EP01130727 A EP 01130727A EP 01130727 A EP01130727 A EP 01130727A EP 1321627 A1 EP1321627 A1 EP 1321627A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
air
steam
edge
gas turbine
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Withdrawn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
EP01130727A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP01130727A priority Critical patent/EP1321627A1/fr
Priority to PCT/EP2002/013619 priority patent/WO2003054357A2/fr
Publication of EP1321627A1 publication Critical patent/EP1321627A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the invention relates to an air and steam cooled Turbine blade, in particular gas turbine blade, the inside is hollow and can be cooled by air and steam the generic term of claim 1 and a method for Cooling a turbine blade.
  • a gas turbine blade is known from EP 1 126 134 A, which can be cooled by steam and air.
  • the steam cooling takes place in the front area of the gas turbine blade, i.e. in the field of Leading edge, instead, the air cooling in the area of Trailing edge of the gas turbine blade takes place.
  • EP 0 955 449 A discloses a gas turbine blade which is also air and steam cooled, with only the Trailing edge is cooled by air.
  • the object of the invention is accordingly a Turbine blade to specify efficient cooling the turbine blade and its brushing edge at the same time high efficiency, i.e. without excessive loss of compressed air, ensured and the areodynamically favorable.
  • Another object of the invention is to provide a method for cooling a gas turbine blade.
  • the object directed to a turbine blade is achieved on the basis of a turbine blade with the features of the preamble of patent claim 1 by at least partially air cooling the brushing edge.
  • Advantageous further developments of claim 1 are listed in the subclaims.
  • the turbine blade according to the invention is suitable advantageously as a moving blade.
  • an air cavity for the Air cooling is L-shaped, with an L-leg in the area of The scraper edge is arranged because this means the entire Area of the brushing edge can be air-cooled and the Brushed edge is very cool and very thin is.
  • An open air cooling is advantageous accomplished that in a vane wall to the air cavity for the air cooling has at least one opening from which the air can escape.
  • openings in the area of Contact edge and / or trailing edge and / or leading edge arranged.
  • the inner area is advantageously steam-cooled because the steam cooling within the turbine blade through the Bucket wall is closed.
  • Figures 1a, 1b, 1c and 1d schematic solution steps various embodiments of an invention trained turbine blade
  • Figure 2 shows a gas turbine.
  • FIG. 1a shows a steam and air-cooled turbine blade 1.
  • the turbine blade 1 for example a gas turbine blade 1, has a leading edge 4 and a trailing edge 7.
  • a rubbing edge 10 forms a radial end of the gas turbine blade 1.
  • the other radial end of the gas turbine blade 1 is not shown in detail and is arranged, for example, in a disk for a blade ring.
  • a hot medium flows around the turbine blade 1 in a flow direction 30.
  • a blade wall 13 encloses at least two cavities. In this exemplary embodiment, there is a first steam cavity 16 and, for example, a second steam cavity 17.
  • the two steam cavities 16 and 17 can also be connected to one another and thus form a single steam cavity.
  • the first and second steam cavities 16, 17 are part of a closed cooling system, ie a cooling steam does not emerge at any point in a hot gas duct 51 (FIG. 2) through a surface of the gas turbine blade 1. Steam cooling would be used for design reasons, particularly in the area of the rubbing edge 10
  • the air cavity 18 runs, for example, approximately parallel to the trailing edge 7 and lies downstream of the steam cavities 16, 17.
  • At least one opening 21 is present in the blade wall 13, which connects the first air cavity 18 to an outer region, the hot gas duct 51. Through this at least one opening 21, the air flows out of the first air cavity 18 into the hot gas duct, which also provides additional cooling of the blade wall 13 in this area.
  • At least one opening 21 is provided, through which cooling air flows into the hot gas duct 51.
  • the openings 21 can also be present in the region of the trailing edge 7. Through the openings 21, which form film cooling holes, film cooling of the outer blade wall 13 is possible.
  • Part of the heated cooling air can also be returned to one Compressed air circuit are returned.
  • FIG. 1b shows a further exemplary embodiment of a turbine blade 1 designed according to the invention.
  • the first air cavity 18 is L-shaped in longitudinal section, an L-leg 27 extending along the brushing edge 10 against the flow direction 30 and an L-neck 28 extending approximately parallel to the trailing edge 7.
  • several openings 21 are provided in the L-leg 27, for example, through which air exits into the hot gas duct 51 in the region of the contact edge 10.
  • the L-leg 27 can taper towards its tip 33, for example, in the vicinity of the leading edge, in order to be able to make the contact edge 10 particularly thin and filigree.
  • the proportion of the steam-cooled area is still very high at 80%, for example.
  • FIG. 1c shows a further exemplary embodiment of a turbine blade 1 designed according to the invention.
  • the L-shape is arranged such that the L-leg 27 is in turn arranged on the brushing edge 10, whereas the L-neck 28 is arranged in the region of the leading edge 4.
  • openings 21 can be formed on the leading edge, which form film cooling holes. Due to the effective air cooling, the leading edge 4 can be made particularly thin and filigree.
  • FIG. 1d shows a further exemplary embodiment of a turbine blade 1 designed according to the invention.
  • the air cavity 18 has a U-shape with a first U-leg 25 and a second U-leg 26, so that both the leading edge 4, the brushing edge 10 and the trailing edge 7 are air-cooled.
  • openings 21 can be provided, which lead to film cooling of the turbine blade 1.
  • the openings 21 can optionally only on the contact edge 10, only on the leading edge 4, only on the trailing edge 7, on the leading edge 4 and the tip 10, on the leading edge 4 and trailing edge 7 or on the trailing edge 7 and the contact edge 10 or as shown to be present on leading edge 4, rubbing edge 10 and trailing edge 7.
  • FIG. 2 shows schematically in a longitudinal section Gas turbine 36.
  • Gas turbine shaft 39 arranged one behind the other a compressor 42, a combustion chamber 45 and a turbine part 48.
  • the turbine part 48 has one Hot gas channel 51 on.
  • Gas turbine blades 1 arranged in the hot gas channel 51.
  • Alternating following are vane rings and moving vane rings intended.
  • the first in the direction of flow Gas turbine blades 1 belong to a guide vane ring a first stage of the gas turbine 36. This first stage is particularly high temperatures from combustion chamber 45 escaping hot gas exposed.
  • the gas turbine blades 1 are - as explained above - via a combined air and Steam cooling cooled.
  • the compressor 42 Compressed air removed and 54 den via air supply Gas turbine blades 1 supplied.
  • Via a steam supply 57 steam is also supplied to the gas turbine blades. This steam preferably comes from a steam turbine combined gas and steam process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01130727A 2001-12-21 2001-12-21 Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement Withdrawn EP1321627A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP01130727A EP1321627A1 (fr) 2001-12-21 2001-12-21 Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement
PCT/EP2002/013619 WO2003054357A2 (fr) 2001-12-21 2002-12-02 Aube de turbine a refroidissement par l'air et la vapeur, et procede de refroidissement d'une aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01130727A EP1321627A1 (fr) 2001-12-21 2001-12-21 Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement

Publications (1)

Publication Number Publication Date
EP1321627A1 true EP1321627A1 (fr) 2003-06-25

Family

ID=8179666

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01130727A Withdrawn EP1321627A1 (fr) 2001-12-21 2001-12-21 Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement

Country Status (2)

Country Link
EP (1) EP1321627A1 (fr)
WO (1) WO2003054357A2 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0302810A2 (fr) * 1987-08-06 1989-02-08 United Technologies Corporation Aube refroidie par triple passage
EP0939196A2 (fr) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Aube de turbine à gaz
US6019579A (en) * 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
US6033181A (en) * 1997-09-01 2000-03-07 Asea Brown Boveri Ag Turbine blade of a gas turbine
FR2798421A1 (fr) * 1990-01-24 2001-03-16 United Technologies Corp Pales refroidies pour moteurs a turbine a gaz
EP1126134A1 (fr) * 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Aube de turbine à refroidissement à air et à vapeur

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0302810A2 (fr) * 1987-08-06 1989-02-08 United Technologies Corporation Aube refroidie par triple passage
FR2798421A1 (fr) * 1990-01-24 2001-03-16 United Technologies Corp Pales refroidies pour moteurs a turbine a gaz
US6019579A (en) * 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
US6033181A (en) * 1997-09-01 2000-03-07 Asea Brown Boveri Ag Turbine blade of a gas turbine
EP0939196A2 (fr) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Aube de turbine à gaz
EP1126134A1 (fr) * 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Aube de turbine à refroidissement à air et à vapeur

Also Published As

Publication number Publication date
WO2003054357A3 (fr) 2003-09-25
WO2003054357A2 (fr) 2003-07-03

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