EP0648979B1 - Verfahren und Vorrichtung zur Kühlung einer Gasturbinenbrennkammer - Google Patents
Verfahren und Vorrichtung zur Kühlung einer Gasturbinenbrennkammer Download PDFInfo
- Publication number
- EP0648979B1 EP0648979B1 EP94115334A EP94115334A EP0648979B1 EP 0648979 B1 EP0648979 B1 EP 0648979B1 EP 94115334 A EP94115334 A EP 94115334A EP 94115334 A EP94115334 A EP 94115334A EP 0648979 B1 EP0648979 B1 EP 0648979B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- combustion chamber
- wall
- gas turbine
- duct
- 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
Links
Images
Classifications
-
- 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
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
- F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Definitions
- the invention relates to a method and an apparatus for Cooling one by means of impingement and convection cooling or pure convection cooling cooled gas turbine combustion chamber.
- combustion chamber wall is cooled inside by film cooling.
- the combustion chamber wall is made up of several layers. A Part of the in the annulus between this combustion chamber wall and the Cooling air flowing along the outer wall flows through openings in spaces within the combustion chamber wall and from there in the downstream direction through parallel cooling channels in the Flame tube into where the air is on the inside of the The combustion chamber wall lays and cools it.
- a disadvantage of this film cooling method is that due to the loss of cooling air pressure with a large excess of air must be worked and the NOx emission values are quite high.
- the invention tries to avoid all these disadvantages. you the task is based on an impact and convection cooling or pure convection cooling cooled gas turbine combustion chamber a method and an apparatus for To create cooling with which it is possible to occur minor local damage, such as holes, in the cooling channel to prevent further enlargement of this damage.
- this is the case with a method for cooling the gas turbine combustion chamber according to the preamble of the main claim achieved in that the compensating flow in Cooling duct is guided past the outer wall of the combustion chamber.
- this is done in a cooling device the gas turbine combustion chamber according to the preamble of the main claim achieved in that between adjacent cooling channels Connection openings are arranged, the connection openings on the outside wall in each of the cooling fins staggered on opposite sides of a cooling channel are.
- the advantages of the invention include that a chain reaction when local damage occurs is avoided in the cooling channel and "self-healing" of the damaged cooling duct.
- the flow rate in the damaged cooling duct even after the Damage point always a critical limit, so that the temperature falls below a critical limit. If the equalizing flow on the outer wall of the combustion chamber is led along, cooling film flows form on the outer wall, which is the outer wall in the area of the damage point cool intensely and completely.
- connection openings are the same size, because of that favorable cooling conditions can be achieved.
- connection openings between the cooling ducts are dimensioned so that the product average opening width and cooling channel length based on the Cross-sectional area of the cooling channel in the range between 2 and 8 lies. Then the most effective cooling can be achieved.
- FIG. 1 A gas turbine combustion chamber is shown in simplified form in FIG. 1.
- a convective Cooling system used to cool the combustion chamber wall 1 .
- the entire cooling air flows in cooling channels 2 between the outer wall 3 and the combustion chamber wall 1 along before being fed to the combustion chamber as combustion air becomes.
- cooling channels 2 there are between the cooling channels 2 cooling fins 4, in which according to the invention Connection openings 5 are present. These connection openings 5 are on opposite sides each a cooling channel 2 arranged offset.
- connection openings 5 between the cooling channels 2 is advantageously carried out according to the design rule 2 ⁇ sL / A ⁇ 8, that is, the product of the average opening width s between two cooling channels 2 and the cooling channel length L, based on the cross-sectional area A of the cooling channel 2, is in the range greater than 2 and less than 8. If the value falls below the lower limit of this interval, a very large hole can lead to overheating of the cooling channel 2 after the hole. If the upper value is clearly exceeded, then a very large hole or a longitudinal slot in one or more cooling channels can lead to such a high air loss that the burners locally overheat the primary zone of the combustion chamber in full load operation.
- connection openings 5 ensures that there is air at least in every axial position flow into an adjacent duct in the damaged cooling duct 2 can.
- the compensating flow takes place at the Combustion chamber outer wall 3.
- the invention has particular very important for thin combustion chamber walls with high heat loads.
Description
- Fig. 1
- eine vereinfachte perspektivische Darstellung der Gasturbinenbrennkammer;
- Fig. 2
- einen Teil der Kühlkanäle der Brennkammer;
- Fig. 3
- einen Längsschnitt durch einen Kühlkanal.
- 1
- Brennkammerwand
- 2
- Kühlkanal
- 3
- Aussenwand
- 4
- Kühlrippe
- 5
- Verbindungsöffnung
- 6
- lokale Schadensstelle
- LO
- Öffnungslänge
- LB
- Steglänge
- s
- mittlere Öffnungsbreite
- L
- Kühlkanallänge
- A
- Querschnittsfläche eines Kühlkanals
- d
- Breite der Öffnung
Claims (4)
- Verfahren zur Kühlung einer Gasturbinenbrennkammer, bei welchem die gesamte Kühlluft in durch Kühlrippen (4) voneinander getrennten Kühlkanälen (2) zwischen Brennkammerwand (1) und Aussenwand (3) geführt wird, wobei die Gasturbinenbrennkammer mittels Prall- und Konvektionskühlung oder reiner Konvektionskühlung gekühlt wird, und nach Auftreten einer lokalen Schadensstelle (6) im Kühlkanal (2) eine Ausgleichsströmung der Kühlluft aus benachbarten Kühlkanälen (2) in den beschädigten Kühlkanal (2) geführt wird, dadurch gekennzeichnet, dass die Ausgleichsströmung im Kühlkanal (2) an der Brennkammeraussenwand (3) vorbeigeführt wird.
- Vorrichtung zur Durchführung des Verfahrens nach Anspruch 1, bestehend aus einer mittels Prall- und Konvektionskühlung oder reiner Konvektionskühlung gekühlten Gasturbinenbrennkammer, bei welcher zwischen Brennkammerwand (1) und Aussenwand (3) durch Kühlrippen (4) voneinander getrennte Kühlkanäle (2) angeordnet sind, dadurch gekennzeichnet, dass zwischen benachbarten Kühlkanälen (2) Verbindungsöffnungen (5) angeordnet sind, wobei die Verbindungsöffnungen (5) aussenwandseitig in den Kühlrippen (4) jeweils versetzt auf den gegenüberliegenden Seiten eines Kühlkanals (2) angeordnet sind.
- Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass die Steglängen (LB) und die Öffnungslängen (LO)der Verbindungsöffnungen (5) gleich gross sind.
- Vorrichtung nach Anspruch 2 oder 3, dadurch gekennzeichnet, dass die Verbindungsöffnungen (5) zwischen den Kühlkanälen (2) so dimensioniert sind, dass das Produkt aus mittlerer Öffnungsbreite (s) und Kühlkanallänge (L) bezogen auf die Querschnittsfläche (A) des Kühlkanals (2) im Bereich grösser 2 und kleiner 8 liegt.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE4335413A DE4335413A1 (de) | 1993-10-18 | 1993-10-18 | Verfahren und Vorrichtung zur Kühlung einer Gasturbinenbrennkammer |
DE4335413 | 1993-10-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0648979A1 EP0648979A1 (de) | 1995-04-19 |
EP0648979B1 true EP0648979B1 (de) | 1999-10-20 |
Family
ID=6500380
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP94115334A Expired - Lifetime EP0648979B1 (de) | 1993-10-18 | 1994-09-29 | Verfahren und Vorrichtung zur Kühlung einer Gasturbinenbrennkammer |
Country Status (4)
Country | Link |
---|---|
US (2) | US5615546A (de) |
EP (1) | EP0648979B1 (de) |
JP (1) | JP3863576B2 (de) |
DE (2) | DE4335413A1 (de) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19812236C2 (de) | 1998-03-20 | 2001-10-18 | Daimler Chrysler Ag | Verfahren zur Unterdrückung hochfrequenter Schwingungen an gelenkten Achsen eines Fahrzeugs |
US8959886B2 (en) * | 2010-07-08 | 2015-02-24 | Siemens Energy, Inc. | Mesh cooled conduit for conveying combustion gases |
US8894363B2 (en) | 2011-02-09 | 2014-11-25 | Siemens Energy, Inc. | Cooling module design and method for cooling components of a gas turbine system |
EP2397653A1 (de) | 2010-06-17 | 2011-12-21 | Siemens Aktiengesellschaft | Plattformsegment zur Stützung einer Gasturbinenleitschaufel und Kühlungsverfahren |
JP6005287B2 (ja) | 2012-09-06 | 2016-10-12 | 三菱日立パワーシステムズ株式会社 | 燃焼ガス冷却装置、燃焼ガス冷却装置を備えた脱硝装置、および燃焼ガス冷却方法 |
US9957816B2 (en) | 2014-05-29 | 2018-05-01 | General Electric Company | Angled impingement insert |
US10422235B2 (en) | 2014-05-29 | 2019-09-24 | General Electric Company | Angled impingement inserts with cooling features |
CA2949539A1 (en) | 2014-05-29 | 2016-02-18 | General Electric Company | Engine components with impingement cooling features |
WO2016069599A1 (en) * | 2014-10-31 | 2016-05-06 | General Electric Company | Engine component assembly |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2644302A (en) * | 1948-06-17 | 1953-07-07 | Gen Electric | Combustion chamber having a flat wall liner with oppositely disposed apertures |
US3408812A (en) * | 1967-02-24 | 1968-11-05 | Gen Electric | Cooled joint construction for combustion wall means |
SE314558B (de) * | 1968-10-28 | 1969-09-08 | Stal Laval Turbin Ab | |
US3777484A (en) * | 1971-12-08 | 1973-12-11 | Gen Electric | Shrouded combustion liner |
US4071194A (en) * | 1976-10-28 | 1978-01-31 | The United States Of America As Represented By The Secretary Of The Navy | Means for cooling exhaust nozzle sidewalls |
US4236378A (en) * | 1978-03-01 | 1980-12-02 | General Electric Company | Sectoral combustor for burning low-BTU fuel gas |
CH633347A5 (de) * | 1978-08-03 | 1982-11-30 | Bbc Brown Boveri & Cie | Gasturbine. |
GB2033071B (en) * | 1978-10-28 | 1982-07-21 | Rolls Royce | Sheet metal laminate |
US4302941A (en) * | 1980-04-02 | 1981-12-01 | United Technologies Corporation | Combuster liner construction for gas turbine engine |
GB2077635B (en) * | 1980-06-13 | 1984-01-04 | Rolls Royce | Manufacture of laminated material |
GB2087065B (en) * | 1980-11-08 | 1984-11-07 | Rolls Royce | Wall structure for a combustion chamber |
GB2118710B (en) * | 1981-12-31 | 1985-05-22 | Secr Defence | Improvements in or relating to combustion chamber wall cooling |
US4773227A (en) * | 1982-04-07 | 1988-09-27 | United Technologies Corporation | Combustion chamber with improved liner construction |
US4653279A (en) * | 1985-01-07 | 1987-03-31 | United Technologies Corporation | Integral refilmer lip for floatwall panels |
US4642993A (en) * | 1985-04-29 | 1987-02-17 | Avco Corporation | Combustor liner wall |
EP0225527A2 (de) * | 1985-12-02 | 1987-06-16 | Siemens Aktiengesellschaft | Kühlfluidkanäle aufweisende Wand, insbesondere für Gasturbinenanlagen, und Verfahren zu ihrer Herstellung |
DE3615226A1 (de) * | 1986-05-06 | 1987-11-12 | Mtu Muenchen Gmbh | Heissgasueberhitzungsschutzeinrichtung fuer gasturbinentriebwerke |
DE59010740D1 (de) * | 1990-12-05 | 1997-09-04 | Asea Brown Boveri | Gasturbinen-Brennkammer |
US5246341A (en) * | 1992-07-06 | 1993-09-21 | United Technologies Corporation | Turbine blade trailing edge cooling construction |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
-
1993
- 1993-10-18 DE DE4335413A patent/DE4335413A1/de not_active Withdrawn
-
1994
- 1994-09-29 DE DE59408840T patent/DE59408840D1/de not_active Expired - Lifetime
- 1994-09-29 EP EP94115334A patent/EP0648979B1/de not_active Expired - Lifetime
- 1994-10-17 JP JP25104294A patent/JP3863576B2/ja not_active Expired - Lifetime
- 1994-10-17 US US08/323,688 patent/US5615546A/en not_active Expired - Lifetime
-
1996
- 1996-08-20 US US08/699,731 patent/US5651253A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JP3863576B2 (ja) | 2006-12-27 |
EP0648979A1 (de) | 1995-04-19 |
DE4335413A1 (de) | 1995-04-20 |
DE59408840D1 (de) | 1999-11-25 |
US5615546A (en) | 1997-04-01 |
US5651253A (en) | 1997-07-29 |
JPH07167436A (ja) | 1995-07-04 |
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