EP0990772A2 - Dispositif et méthode de refroidissement d'une paroi dont la surface extérieure est en contact avec un courant de gaz chaud - Google Patents

Dispositif et méthode de refroidissement d'une paroi dont la surface extérieure est en contact avec un courant de gaz chaud Download PDF

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Publication number
EP0990772A2
EP0990772A2 EP99810803A EP99810803A EP0990772A2 EP 0990772 A2 EP0990772 A2 EP 0990772A2 EP 99810803 A EP99810803 A EP 99810803A EP 99810803 A EP99810803 A EP 99810803A EP 0990772 A2 EP0990772 A2 EP 0990772A2
Authority
EP
European Patent Office
Prior art keywords
cooling
wall
recesses
insert
recess
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Withdrawn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
EP99810803A
Other languages
German (de)
English (en)
Other versions
EP0990772A3 (fr
Inventor
Günter Dr Wilfert
Carsten Hermann
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.)
ABB Research Ltd Switzerland
Original Assignee
ABB Research Ltd Switzerland
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 ABB Research Ltd Switzerland filed Critical ABB Research Ltd Switzerland
Publication of EP0990772A2 publication Critical patent/EP0990772A2/fr
Publication of EP0990772A3 publication Critical patent/EP0990772A3/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Withdrawn legal-status Critical Current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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape

Definitions

  • the invention relates to a device and a method for cooling a one-sided wall surrounded by hot gas, in particular the hollow profile body Gas turbine blade, according to the preamble of claim 1.
  • the blown-out cooling air must be as quick as possible are diverted and flow protectively along the profile surface. Around Protecting the areas between the wells is also one rapid lateral expansion of the cooling air required.
  • the mixing areas of the hot gas with the cooling air jets creates a wide variety of vortices, which is of crucial importance for the protective effect of a cooling configuration have.
  • kidney vertebra i.e. one out of one a pair of vertebrae consisting of right and left rotating vertebrae.
  • this kidney vertebra transports part of the hot gas between the Drilled holes directly on the profile surface of the turbine blade and thus below the cooling air jets, which proves to be a serious disadvantage.
  • a serious disadvantage of this solution is the weak intensity of the inner vertebra, so that it dissolves relatively quickly and not permanently for improvement the cooling effectiveness can be used.
  • DE 196 12 840 A1 has already been known to improve this. To do this, in the cooling cavity, upstream of the cooling hole, a rib arranged and the cooling insert in the area the cooling holes are deformed in the direction of the wall to be cooled. In this way can the inflow of the cooling fluid into the cooling holes and thus the cooling effectiveness be improved.
  • the invention tries to avoid all these disadvantages. It is based on the task a device and a corresponding method for cooling a Wall surrounded by hot gas on one side with a further improved cooling effect to accomplish.
  • this is achieved in that with a device according to the preamble of claim 1, in the cooling cavity, upstream of each recess, a deflection element for the cooling fluid opening into the latter is arranged.
  • the Deflection element is also opposite the cooling cavity by means of side walls completed.
  • the cooling fluid not captured by the deflection elements can be relative flow undisturbed between the adjacent deflection elements.
  • the individual deflection elements act as cooling fins, which also makes the convective Cooling of the wall in the area between the recesses improved becomes. The conclusion is not only the film cooling, but the whole Cooling of the wall significantly improved. This can save cooling air and are used elsewhere.
  • a wall cooled in this way can not only be used as a hollow profile body of a gas turbine blade trained, but also advantageously as a combustion chamber wall or can be used as a heat accumulation segment of a gas turbine.
  • each recess has a central axis and each Deflection element has a deflection surface, each deflection surface directly upstream of the associated recess at least approximately parallel to Center axis of this recess is aligned.
  • the deflection surface is curved and one at least approximately constant radius of curvature.
  • deflection elements connected to the wall and are also on Cooling insert, they also advantageously serve as a spacer between the one to be cooled Wall and the cooling insert.
  • the guide vane 1 of a gas turbine consists of a hollow profile body 2, the one Wall 3 formed as an outer jacket, one arranged at a distance from it Cooling insert 4 and a cooling cavity 5 formed between the two.
  • a blade cavity 6 is formed in the interior of the cooling insert 4, which in a conventional manner with the compressor of the gas turbine system, not shown is connected and acted upon by this as cooling fluid 7 cooling air becomes.
  • the outer jacket 3 has an outer and an inner surface 8, 9, between which several rows of recesses designed as cooling bores 10 are arranged.
  • the blade cavity 6 is in several Cooling insert 4 arranged openings 11 connected to the cooling cavity 5 (Fig. 1).
  • the guide vane 1 can also only have a single row of cooling bores Own 10.
  • hot gas 12 does not flow out of the Combustion chamber shown on the guide vanes 1 and also not shown Blades of the gas turbine. Therefore, they have to be constantly cooled.
  • the cooling of the guide blades 1 takes place by means of those brought up by the compressor Cooling air 7, this via the openings 11 of the cooling insert 4 in penetrates the cooling cavity 5 and first the inner surface 9 of the outer jacket 3 convectively cools. Then the cooling air 7 through the cooling holes 10 in a plurality of cooling air jets on the outer surface 8 the outer shell 3 blown out.
  • the curvature of these cooling air jets at her Exit into the main flow of hot gas 12 occurs at an exit angle 13 of about 30 °.
  • FIG. 3 shows an enlarged section of a design according to the invention Guide vane 1 shown.
  • this guide vane 1 is upstream in the cooling cavity 5 each row of cooling bores 10, a deflecting element opening into the latter 15 arranged for the cooling fluid 7 and by means of side walls 16 opposite the Cooling cavity 5 completed (Fig. 4, Fig. 5).
  • Each cooling hole 10 has one Central axis 17 and each deflecting element 15 have a deflecting surface 18. It is each deflecting surface 18 approximately upstream of the associated cooling bore 10 aligned parallel to the central axis 17 of this cooling bore 10.
  • the deflection surface 18 is curved and has an approximately continuous Radius of curvature r.
  • the latter which is the transition radius from Cooling insert 4 to the cooling bore 10 corresponds to one at an angle of 30 ° trained cooling bore 10 about 15 times the diameter d of the associated Cooling hole 10 (Fig. 3). With larger distances between the cooling insert 4 the wall 3, the transition radii are larger, with larger exit angles 13 however smaller.
  • the deflection elements assigned to a row of cooling bores 10 15 are connected via a wall-side web 19 to a deflection insert 20 connected (Fig. 4, Fig. 5, Fig. 7).
  • the deflection elements 15 are made of solid material, connected to the wall 3 and are also on the cooling insert 4. Every deflection element 15 thus simultaneously forms a spacer between the cooling insert 4 and the wall to be cooled 3.
  • Figure 7 is a second embodiment of the invention with one of a deep-drawn sheet metal deflection element 15 or a corresponding Deflection insert 20 shown.
  • the function of this solution is essentially analogous to the first embodiment.
  • Such a cooling configuration is of course not on the guide vanes 1 of gas turbines limited. It can also be used for blades, combustion chamber walls, Heat accumulation segments of gas turbines or others, one side of hot gas 12 surrounding walls 3 are used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
EP99810803A 1998-10-01 1999-09-07 Dispositif et méthode de refroidissement d'une paroi dont la surface extérieure est en contact avec un courant de gaz chaud Withdrawn EP0990772A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19845147 1998-10-01
DE1998145147 DE19845147B4 (de) 1998-10-01 1998-10-01 Vorrichtung und Verfahren zur Kühlung einer einseitug von Heißgas umgebenen Wand

Publications (2)

Publication Number Publication Date
EP0990772A2 true EP0990772A2 (fr) 2000-04-05
EP0990772A3 EP0990772A3 (fr) 2001-10-04

Family

ID=7883001

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810803A Withdrawn EP0990772A3 (fr) 1998-10-01 1999-09-07 Dispositif et méthode de refroidissement d'une paroi dont la surface extérieure est en contact avec un courant de gaz chaud

Country Status (2)

Country Link
EP (1) EP0990772A3 (fr)
DE (1) DE19845147B4 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19845147B4 (de) * 1998-10-01 2006-11-23 Alstom Vorrichtung und Verfahren zur Kühlung einer einseitug von Heißgas umgebenen Wand
EP3176374A1 (fr) * 2015-12-03 2017-06-07 General Electric Company Refroidissement de bord de fuite pour une pale de turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4191578B2 (ja) * 2003-11-21 2008-12-03 三菱重工業株式会社 ガスタービンエンジンのタービン冷却翼

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0258754A2 (fr) 1986-09-03 1988-03-09 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Aube de turbine avec noyau de refroidissement
DE19612840A1 (de) 1996-03-30 1997-10-02 Abb Research Ltd Vorrichtung und Verfahren zur Kühlung einer einseitig von Heissgas umgebenen Wand

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2782597A (en) * 1952-03-15 1957-02-26 Gen Electric Combustion chamber having improved air inlet means
DE1199541B (de) * 1961-12-04 1965-08-26 Jan Jerie Dr Ing Sammler von Treibgasen fuer das Leitrad von Gasturbinen
AT237973B (de) * 1961-12-04 1965-01-25 Jan Ing Dr Jerie Sammler von Treibgasen für das Leitrad der Gasturbine
US5407133A (en) * 1989-12-26 1995-04-18 United Technologies Corporation Cooled thin metal liner
US5271715A (en) * 1992-12-21 1993-12-21 United Technologies Corporation Cooled turbine blade
DE19845147B4 (de) * 1998-10-01 2006-11-23 Alstom Vorrichtung und Verfahren zur Kühlung einer einseitug von Heißgas umgebenen Wand

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0258754A2 (fr) 1986-09-03 1988-03-09 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Aube de turbine avec noyau de refroidissement
DE19612840A1 (de) 1996-03-30 1997-10-02 Abb Research Ltd Vorrichtung und Verfahren zur Kühlung einer einseitig von Heissgas umgebenen Wand

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
G. WILFERT: "Dissertationsschrift zum Thema "Experimentelle und numerische Untersuchungen derMischungsvorgänge zwischen Kühlfilmen und Gitterströmung an einem hochbelastetenTurbinengitter", 1994, MONCHEN, pages: 54/70-74

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19845147B4 (de) * 1998-10-01 2006-11-23 Alstom Vorrichtung und Verfahren zur Kühlung einer einseitug von Heißgas umgebenen Wand
EP3176374A1 (fr) * 2015-12-03 2017-06-07 General Electric Company Refroidissement de bord de fuite pour une pale de turbine
US10344598B2 (en) 2015-12-03 2019-07-09 General Electric Company Trailing edge cooling for a turbine blade
US11208901B2 (en) 2015-12-03 2021-12-28 General Electric Company Trailing edge cooling for a turbine blade

Also Published As

Publication number Publication date
DE19845147B4 (de) 2006-11-23
EP0990772A3 (fr) 2001-10-04
DE19845147A1 (de) 2000-04-06

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