EP0640745B1 - Verfahren zur Kühlung eines Bauteils - Google Patents

Verfahren zur Kühlung eines Bauteils Download PDF

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Publication number
EP0640745B1
EP0640745B1 EP94112390A EP94112390A EP0640745B1 EP 0640745 B1 EP0640745 B1 EP 0640745B1 EP 94112390 A EP94112390 A EP 94112390A EP 94112390 A EP94112390 A EP 94112390A EP 0640745 B1 EP0640745 B1 EP 0640745B1
Authority
EP
European Patent Office
Prior art keywords
cooling
cooling air
wall
duct
partition
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.)
Expired - Lifetime
Application number
EP94112390A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0640745A1 (de
Inventor
Frank Reiss
Stefan Tschirren
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 AG Germany
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0640745A1 publication Critical patent/EP0640745A1/de
Application granted granted Critical
Publication of EP0640745B1 publication Critical patent/EP0640745B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present invention relates to the field of mechanical engineering, in particular thermal machines. It relates to a method for cooling a thermally stressed component with a flat outer wall, in which method cooling air is supplied in a first cooling section of the component by supplying cooling air in the direction of the outer wall and deflected laterally in front of the outer wall and in a second cooling section in a cooling air duct which adjoins the side is continued parallel to the outer wall for further cooling.
  • the invention further relates to an apparatus for performing the method.
  • cooling by means of cooling air is often provided.
  • the cooling air flows (Fig. 1) for the purpose of convective cooling parallel to the outer wall 2 of the component 1 in a cooling air duct 3 along the outer wall 2.
  • the cooling air duct 3 is formed, for example, by the outer wall 2 and a duct wall 6 surrounding the outer wall 2 at a distance in the form of a guide plate.
  • the cooling air in the gas turbine usually comes from the compressor part and flows from the so-called plenum, which surrounds the hot gas housing, into the cooling air duct 3.
  • a gap-shaped opening as cooling air supply 5 is usually left open at the entrance of the cooling air duct 3 between the duct wall 6 and the opposite boundary wall 4, through which the cooling air can enter the cooling air duct 3.
  • the cooling air in the area of the cooling air supply 5 generally has a vertical speed component, so that the cooling air more or less impacts the outer wall 2 of the component 1 before entering the cooling air duct 3 and only then in the laterally outgoing cooling air duct 3 is redirected.
  • the object is achieved in a method of the type mentioned at the outset in that, in order to reduce the impingement cooling in the first cooling section, the cooling air flow coming from the cooling air supply is divided into a main flow and a bypass flow, the main flow being led directly along the outer wall of the component to the cooling air duct the bypass flow is led to the cooling air duct without contact with the outer wall, and both partial flows are brought together again at the entrance of the cooling air duct.
  • the essence of the invention is, through a selectable division of the entire cooling air into a first partial flow, which participates in the impingement cooling, and a second partial flow, which is transferred directly into the cooling air duct without impingement cooling, the cooling in the first cooling section to the cooling in the second To make the cooling section adaptable.
  • the main flow is additively composed of a plurality of small partial flows which are distributed over the first cooling section and branched off from the incoming cooling air flow.
  • the cooling arrangement according to the invention for carrying out the method is characterized by the features of claim 4.
  • a first preferred embodiment of the cooling arrangement according to the invention is characterized in that the intermediate wall extends so far into the area of the cooling air supply that it forms a supply opening with the opposite boundary wall of the cooling air supply, the width of which is smaller than the width of the cooling air supply.
  • a second preferred embodiment of the cooling arrangement according to the invention is characterized in that a plurality of adjacent holes are provided in the intermediate wall, through which cooling air can flow into the main duct. This results in a particularly smooth transition between the two cooling sections.
  • a third preferred embodiment is characterized in that the component is a thermally loaded part of a gas turbine, that the gas turbine has a turbine part, a combustion chamber and a turbine inlet leading from the combustion chamber to the turbine part, which turbine inlet guides the hot combustion gases and from an inner shell and an outer shell is formed, and that the cooled component is the inner shell and / or the outer shell of the turbine inlet.
  • Particularly favorable cooling conditions can be achieved in a gas turbine with the device according to the invention.
  • Fig. 1 a greatly simplified schematic of a conventional cooling is shown in sections, on which the problem underlying the present invention can be explained.
  • the starting point is a thermally stressed component 1, for example a shell or wall, which is caused by a current of Cooling air should be cooled.
  • a duct wall 6 which runs parallel to the outer wall 2 of the component 1 and is spaced apart from the outer wall 2, is provided outside the component 1, which together with the outer wall 2 forms a cooling air duct 3.
  • the cooling air flows largely parallel to the outer wall 2 through the cooling air duct 3 and cools the component 1 by convective cooling (the cooling air flows are indicated by the arrows shown).
  • the cooling air for the cooling air duct 3 is supplied from a source (not shown) along a boundary wall 4 through a cooling air supply 5.
  • the supply usually takes place in such a way that the cooling air impacts the outer wall 2 vertically or at least with a vertical speed component, is deflected laterally and flows into the cooling air duct 3 which adjoins the side.
  • the supplied mass flow dm e / dt (in FIG. 1 as well as in the further FIGS. 2 to 4, the time derivatives of the masses m are abbreviated in a known manner with a point above them for reasons of space) is unchanged as the outgoing mass flow dm a / dt fed into the cooling air duct 3.
  • FIG. 1 Due to the geometry of the cooling air supply, the structure shown in FIG. 1 results in a very effective impingement cooling in a first cooling section A, which is directly opposite the cooling air supply 5, while in an adjacent second cooling section B, which is connected to the area of the cooling air duct 3 together, less effective convective cooling prevails.
  • component 1 is cooled very inhomogeneously overall, i.e. in the first cooling section A it has a significantly lower temperature than in the cooling section B.
  • FIG. 2 shows a schematized cooling device comparable to FIG. 1.
  • the incoming cooling air flow dm e / dt behind the cooling air supply 5 is divided into a main flow (dm 1 / dt) and a bypass flow (dm 2 / dt).
  • the main flow in a main duct 11 is first brought into direct contact with the outer wall 2 and then fed into the cooling air duct 3
  • the bypass flow is passed through a bypass duct 8 past the outer wall 2 directly to the entrance of the cooling air duct 3.
  • the proportion of impingement cooling can be reduced, defined, or made to disappear entirely.
  • the separation of the space between the cooling air supply 5 and the entrance of the cooling air duct 3 is advantageously carried out by an intermediate wall 7, which is arranged, for example, parallel to the outer wall 2 and at a distance therefrom.
  • the intermediate wall 7 extends from the beginning of the cooling air duct 3 into the area of the cooling air supply 5 and, in a preferred embodiment, ends at a distance in front of the opposite boundary wall 4, so that a supply opening 10 with a width C, which is smaller, results for the main flow is than the width D of the cooling air supply 5.
  • the channel wall 6 expediently widens at the beginning of the cooling air channel 3 and overlaps the intermediate wall 7 with the enlarged area, the distance from the outer wall 2 of which is preferably less than the corresponding distance from the channel wall 6.
  • the size of the main flow in relation to the total cooling air flow in this case depends on the ratio of the width C of the supply opening 10 to the width D of the cooling air supply 5 and can be easily adapted to the requirements.
  • holes 9 can be provided distributed in the intermediate wall 7, through which a mass flow dm 3 / dt in the form of small partial flows successively passes from the bypass duct 8 into the main duct 11.
  • the hole density and the size and depth of the individual holes 9 are then also available as parameters for setting the cooling effectiveness in the deflection area.
  • the invention can also be used more generally in cases where the included angle deviates from 90 °, ie is either blunt (e.g. up to 170 °) or pointed (e.g. up to 10 °). Both cases are indicated in FIGS. 3 and 4. It goes without saying that in these cases, in particular at an obtuse angle, the impingement cooling is less pronounced because the velocity component of the flow perpendicular to the outer wall 2 is correspondingly lower.
  • the homogenization of the cooling according to the invention can be used particularly advantageously in the case of thermally loaded components of gas turbines, in particular the shells of the turbine inlet arranged between the combustion chamber and the turbine part. Exemplary embodiments for such an application are shown in FIG. 5 (outer shell of the turbine inlet) and in FIG. 6 (inner shell of the turbine inlet).
  • the outer part of a turbine inlet 13 shown in longitudinal section (in sections) in FIG. 5 comprises the outer shell 24 as a component to be cooled.
  • the outer shell 24 outwardly delimits the space through which the hot gases (from right to left in the figure) from the combustion chamber be directed into the turbine part.
  • the outer shell 24 is surrounded on the outside by a baffle plate 19, which is supported on the outer shell 24 by means of spacers 20 and runs approximately parallel to the shell at a distance defined by the spacers 20.
  • the cooling air duct 23, through which cooling air flows along the outer shell 24, lies between the guide plate 19 and the outer wall 22 of the outer shell 24.
  • the outer shell 24 merges into an inner segment bearing 18, in which a plurality of sealing segments 17 with an appropriately designed foot part are mounted in an annular arrangement.
  • the sealing segments 17 are mounted in an outer segment bearing 15, which is part of a blade carrier 14 which carries the guide blades of the turbine part, not shown.
  • the outer shell 24 with the guide plate 19 is surrounded on the outside by the so-called plenum 12 of the turbine, in which there is compressed air from the compressor part, which is used both as combustion air and as cooling air.
  • the cooling air flows from the plenum 12 to cool the outer shell 24 into the cooling air duct 23, where it is deflected.
  • the sealing segments 17 take on the function of the boundary wall 4 from FIGS. 1 to 4. In the example shown, they form a right angle with the outer shell 24 (comparable to the situation shown in FIG. 2).
  • an intermediate wall 27 in the form of a sheet is arranged there.
  • the intermediate wall 27 runs parallel to the outer wall 22 of the outer shell and at a distance which is smaller than the distance of the guide plate 19. It is also supported on the outer shell 24 by means of spacers 21 and defines the main channel 26 between itself and the outer wall 22.
  • the intermediate wall 27 does not quite reach the opposite sealing segments 17 at one end, so that cooling air can flow into the main duct 26 through the gap there, which corresponds to the feed opening 10 from FIGS. 2 to 4.
  • the intermediate wall 27 extends into the opening of the cooling air channel 23, so that a short bypass channel is formed between the intermediate wall 27 and the beginning of the guide plate 19.
  • a stable fastening in this area can be achieved for the intermediate wall 27 in that an end section of the sheet, which is connected to the rest of the sheet by a tab 25, is bent up and fixed to the spacers 20 together with the beginning of the guide sheet 19.
  • the intermediate wall 27 is also provided with uniformly distributed holes 28 through which cooling air can reach the main duct 26 in small partial flows.
  • the application of the principle according to the invention to the inner shell of the turbine inlet 13 is shown as an exemplary embodiment in FIG. 6.
  • the inner shell 29 surrounds the turbine housing 39.
  • a channel-like cooling air supply 40 is provided in the turbine housing, through which cooling air flows onto the outer wall 35 of the inner shell 29.
  • the actual cooling takes place in turn in a cooling air channel 36 which is formed by the inner shell 29 and a baffle plate 37 surrounding it at a distance.
  • an intermediate wall 32 made of sheet metal is used, which preferably runs parallel to the inner shell 29 and has a smaller distance from it than the guide plate 37. Both the intermediate wall 32 and the guide plate 37 are supported by spacers 30, 33 or 38 on the inner shell 29.
  • the intermediate wall 32 delimits the main channel 31 on the one hand. On the other hand, it in turn overlaps with the guide plate 37 to form a short bypass channel 34. Holes are not provided in the intermediate wall in this example but can also be easily introduced to increase the cooling effect in the deflection area.
  • the invention provides an effective means of achieving a homogenization of the cooling in the case of thermally stressed components in which cooling air coming from outside has to be deflected into a cooling air duct running parallel to the component surface.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94112390A 1993-08-23 1994-08-09 Verfahren zur Kühlung eines Bauteils Expired - Lifetime EP0640745B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4328294A DE4328294A1 (de) 1993-08-23 1993-08-23 Verfahren zur Kühlung eines Bauteils sowie Vorrichtung zur Durchführung des Verfahrens
DE4328294 1993-08-23

Publications (2)

Publication Number Publication Date
EP0640745A1 EP0640745A1 (de) 1995-03-01
EP0640745B1 true EP0640745B1 (de) 1997-04-23

Family

ID=6495797

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94112390A Expired - Lifetime EP0640745B1 (de) 1993-08-23 1994-08-09 Verfahren zur Kühlung eines Bauteils

Country Status (4)

Country Link
US (1) US5581994A (ja)
EP (1) EP0640745B1 (ja)
JP (1) JP3665369B2 (ja)
DE (2) DE4328294A1 (ja)

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US5542246A (en) * 1994-12-15 1996-08-06 United Technologies Corporation Bulkhead cooling fairing
DE19751299C2 (de) 1997-11-19 1999-09-09 Siemens Ag Brennkammer sowie Verfahren zur Dampfkühlung einer Brennkammer
US6224329B1 (en) * 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US6722872B1 (en) * 1999-06-23 2004-04-20 Stratasys, Inc. High temperature modeling apparatus
US7104068B2 (en) * 2003-08-28 2006-09-12 Siemens Power Generation, Inc. Turbine component with enhanced stagnation prevention and corner heat distribution
US7900459B2 (en) * 2004-12-29 2011-03-08 United Technologies Corporation Inner plenum dual wall liner
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US20070276309A1 (en) * 2006-05-12 2007-11-29 Kci Licensing, Inc. Systems and methods for wound area management
EP2245374B1 (de) 2008-02-20 2017-11-15 General Electric Technology GmbH Thermische maschine
US8015817B2 (en) * 2009-06-10 2011-09-13 Siemens Energy, Inc. Cooling structure for gas turbine transition duct
DE102009046066A1 (de) 2009-10-28 2011-05-12 Man Diesel & Turbo Se Brenner für eine Turbine und damit ausgerüstete Gasturbine
US8646276B2 (en) * 2009-11-11 2014-02-11 General Electric Company Combustor assembly for a turbine engine with enhanced cooling
US8973365B2 (en) * 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators
KR102114069B1 (ko) * 2012-10-26 2020-05-22 삼성전자주식회사 전자기기의 냉각장치
US20140130504A1 (en) * 2012-11-12 2014-05-15 General Electric Company System for cooling a hot gas component for a combustor of a gas turbine
KR102076863B1 (ko) * 2019-03-07 2020-02-12 (주)한국에너지기술단 알칼리금속 열전기 변환장치가 장착된 발전 및 연소시스템
EP3835657A1 (en) * 2019-12-10 2021-06-16 Siemens Aktiengesellschaft Combustion chamber with wall cooling

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US4236870A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
CH633347A5 (de) * 1978-08-03 1982-11-30 Bbc Brown Boveri & Cie Gasturbine.
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
US4526226A (en) * 1981-08-31 1985-07-02 General Electric Company Multiple-impingement cooled structure
JPH0660740B2 (ja) * 1985-04-05 1994-08-10 工業技術院長 ガスタービンの燃焼器
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
EP0204553B1 (en) * 1985-06-07 1989-06-07 Ruston Gas Turbines Limited Combustor for gas turbine engine
JPH0752014B2 (ja) * 1986-03-20 1995-06-05 株式会社日立製作所 ガスタ−ビン燃焼器
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US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
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DE4222391C2 (de) * 1992-07-08 1995-04-20 Gutehoffnungshuette Man Zylindrisches Brennkammergehäuse einer Gasturbine

Also Published As

Publication number Publication date
JP3665369B2 (ja) 2005-06-29
DE59402500D1 (de) 1997-05-28
EP0640745A1 (de) 1995-03-01
DE4328294A1 (de) 1995-03-02
US5581994A (en) 1996-12-10
JPH0777061A (ja) 1995-03-20

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