EP0774100B1 - Hitzeschild für eine gasturbinen-brennkammer - Google Patents
Hitzeschild für eine gasturbinen-brennkammer Download PDFInfo
- Publication number
- EP0774100B1 EP0774100B1 EP95926909A EP95926909A EP0774100B1 EP 0774100 B1 EP0774100 B1 EP 0774100B1 EP 95926909 A EP95926909 A EP 95926909A EP 95926909 A EP95926909 A EP 95926909A EP 0774100 B1 EP0774100 B1 EP 0774100B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- heat shield
- combustion chamber
- burner
- air
- hole
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
-
- 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
- F05B2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
Definitions
- the invention relates to a heat shield for a combustion chamber, in particular for an annular combustion chamber of a gas turbine, with a passage opening for a burner, the back of the combustion chamber facing away from the Heat shield is acted upon by cooling air and one at the edge of the passage opening has surrounding web.
- the known state of the art is referred to US 5,307,637, the web for receiving or Storage of the burner is used.
- the heat shield provided in the head of a combustion chamber serves as is known for this, the dome-shaped combustion chamber head area or the inside provided front panel before the action of that in the combustion chamber To protect hot gas and excessive heat radiation.
- the heat shield must itself be cooled will.
- conventional heat shields have so-called effusion holes in the the surface facing the combustion chamber, via the cooling air from the rear forth can pass a film of cooling air on the hot surface of the heat shield. This is detailed in the above font explained.
- Another heat shield arrangement is shown in EP-A-0 521 687, air passage openings being provided in a web-like section are, through which cooling air can get into the combustion chamber.
- the object of the invention is to demonstrate further measures, with the help of which an improved heat shield cooling can be achieved can.
- the web is a Has a plurality of air transfer openings, which are at an angle the direction pointing towards the center of the passage opening are that one through the air transfer openings in an annular channel between the heat shield and the burner entering and from there into the Airflow entering the combustion chamber forms a vortex that is in the same direction with the vortex formed by the combustion air supplied through the burner, and the one vertebral axis perpendicular to the surface of the heat shield having.
- Advantageous training and further education are included in the Subclaims.
- the ring combustion chamber is one Designated gas turbine, the head side a dome-like end wall 2 and then one also as a retaining wall has functioning front panel 3.
- this ring combustor corresponds this ring combustor the known prior art.
- several burners 4 arranged in a circle over which Fuel and combustion air swirl into the Combustion chamber 1 is introduced.
- the direction of the vortex is the combustion air introduced via the burner 4 3, 4 represented by arrows 5.
- a heat shield 6 is provided, the so-called. Combustion chamber cathedral, d. H. the front panel 3 and the end wall 2 in front of the hot burner gases and inadmissible protects against high levels of radiation.
- This The heat shield is via bolt 7 (see FIG. 2) on the front panel 3 fastened and has a passage opening 8 for the burner 4.
- the burner 4 is one Surround sealing part 9, which in particular ensures that much of the breakthrough 10 in the end wall 2 supplied combustion air over the Burner 4 flows into the combustion chamber 1.
- the heat shield points at the edge of the passage opening 8 one from the rear 6a to the rear, d. H. opposed cantilevering to the combustion chamber 1, rotating Bridge 14 on.
- the individual dimensions are included chosen so that between the web 14 and the sealing part 9 results in an annular channel 15.
- this ring channel 15 can cool air from the rear 6a of the heat shield 6th forth through air transfer openings 16, several of which are provided in the web 14, flow. Because the free end of the circumferential web 14 on a clamped ring 23, which fixes the sealing part 9, can also only through these air transfer openings 16 cooling air in the Ring channel 15 arrive.
- the air stream flowing into the annular duct 15 arrives finally into the combustion chamber 1, but should on the way there the particularly highly stressed areas of the Cool heat shield 6 intensively. To do this, this should the air duct exiting the annular duct 15 into the combustion chamber 1 also as a cooling air film on the combustion chamber 1 facing hot surface 6b of the heat shield 6 place, especially in the edge region of the passage opening 8.
- the Air flow in the ring channel impressed a vortex that is in the same direction is with the vortex which is fed via the burner 8 Combustion air.
- the emerging from the ring channel 15 Cooling air is said to describe a vortex, which has the same direction as the arrows 5 with which the vortex of the combustion air supplied via the burner 4 is shown.
- the swirl axes of these two Air vortices are essentially vertical to the plane or surface 6b of the heat shield 6.
- the transition area between the web 14 and the hot surface 6b of the heat shield 6 is as a chamfer 18 trained, but can also be rounded be. This measure enables this via the ring channel 15 incoming cooling air flow, maintaining itself its flow direction as a cooling air film on the surface 6b to apply the heat shield 6. Particularly promoted this application of the cooling air flow as a cooling air film however, in that the swirl directions of the air flow guided over the annular duct 15 and that entering the combustion chamber 1 via the burner 4 Combustion air flow match.
- the heat shield 6 is still with effusion holes 19 provided, which are called from the rear 6a Guide surface 6b and thus the passage of cooling air enable by the heat shield 6.
- effusion holes 19 are deposited as a cooling air film on the surface 6b.
- the central axes are of the effusion holes 19 inclined twice.
- the first angle of inclination lies between the central axis of the effusion holes and a perpendicular to the surface 6b of the Heat shield 6, which means that the central axes of the Effusion holes 19 inclined to the surface 6b are so that the emerging from an effusion hole 19 Air flow at least partially sweeps across surface 6b.
- Another angle of inclination ⁇ occurs in one perpendicular projection onto the surface 6b, whereby in this projection the central axis 20 of each effusion hole inclined to the tangent 21 to one around the center 17 the passage opening 8 through the respective effusion hole 19 placed circle 22 is.
- 4 apparent design of the Effusion holes 19 form through these effusion holes 19 generated cooling air film a vortex that both a radially outward with respect to the center 17 Velocity component VR, as well as a tangential speed component extending to the pitch circle 22 VT has.
- the angle of inclination ⁇ is chosen such that that the tangential component VT rectified is with the vortex that supplied via the burner 4 Combustion air, which is represented by the arrows 5. This rectification of the vertebrae ensures that a cooling air film lying optimally on the surface 6b can form.
Abstract
Description
- Fig. 1
- einen Teilschnitt durch den Kopf einer erfindungsgemäßen Gasturbinen-Ringbrennkammer,
- Fig. 2
- die obere Hälfte eines Hitzeschildes im Schnitt,
- Fig. 3
- die Aufsicht auf die kalte Rückseite des Hitzeschildes , sowie
- Fig. 4
- die Aufsicht auf die der Brennkammer zugewandte heiße Oberfläche.
Claims (6)
- Hitzeschild für eine Brennkammer, insbesondere für eine Ring-Brennkammer einer Gasturbine, mit einer Durchtrittsöffnung (8) für einen Brenner (4), wobei die der Brennkammer (1) abgewandte Rückseite (6a) des Hitzeschildes (6) mit Kühlluft beaufschlagt ist und einen am Rand der Durchtrittsöffnung (8) umlaufenden Steg (14) aufweist,
dadurch gekennzeichnet, daß der Steg (14) eine Vielzahl von Luftübertrittsöffnungen (16) aufweist, die unter einem Winkel (α) gegenüber der ins Zentrum (17) der Durchtrittsöffnung (8) weisenden Richtung derart geneigt sind, daß ein durch die Luftübertrittsöffnungen (16) in einen Ringkanal (15) zwischen dem Hitzeschild (6) und dem Brenner (4) eintretender und von da aus in die Brennkammer (1) gelangender Luftstrom einen Wirbel bildet, der gleichsinnig ist mit dem Wirbel (Pfeile 5), den die über den Brenner (4) zugeführte Verbrennungsluft bildet, und der eine senkrecht zur Oberfläche (6b) des Hitzeschildes (6) stehende Wirbelachse aufweist. - Hitzeschild nach Anspruuch 1,
dadurch gekennzeichnet, daß der Ringkanal (15) vom Hitzeschild (6) mit seinem Steg (14) sowie von einem den Brenner (4) umgebenden Dichtungsteil (9) begrenzt ist. - Hitzeschild nach Anspruch 1 oder 2,
dadurch gekennzeichnet, daß der Übergangsbereich zwischen dem Steg (14) und der der Brennkammer (1) zugewandten (heißen) Oberfläche (6b) als Fase (18) oder abgerundet ausgebildet ist. - Hitzeschild nach einem der vorangegangenen Ansprüche mit einer Vielzahl von Effusionslöchern (19) in der der Brennkammer (1) zugewandten Oberfläche (6b) durch die Kühlluft von der Rückseite (6a) her durchtreten kann, um einen Kühl luft film auf die heiße Oberfläche (6b) zu legen,
dadurch gekennzeichnet, daß die Mittelachsen (20) der Effusionslöcher (19) geneigt zur Oberfläche (6b) sind und in einer senkrechten Projektion auf die Oberfläche (6b) derart geneigt zur jeweiligen Tangente (21) an einen um das Zentrum (17) der Durchtrittsöffnung (8) durch das jeweillige Effusionsloch (19) gelegten Teilkreis (22) sind, daß der Kühlluftfilm einen Wirbel bildet, der sowohl eine bezüglich des Zentrums (17) radial nach außen gerichtete Geschwindigkeits-Komponente (VR), als auch eine tangential zum Teilkreis (22) verlaufende Geschwindigkeits-Komponente (VT) aufweist, wobei die Richtung der Tangential-Komponente (VT) gleich ist mit dem Wirbel (Pfeile 5) der über den Brenner (4) zugeführten Verbrennungsluft. - Hitzeschild nach Anspruch 4,
dadurch gekennzeichnet, daß der Betrag der radialen Geschwindigkeitskomponente (VR) größer ist als derjenige der Tangential-Komponente (VT). - Hitzeschild nach einem der vorangegangenen Ansprüche,
gekennzeichnet durch Bolzen (7), über die das Hitzeschild (6) mit einer ebenfalls das Dichtungsteil (9) tragenden Frontplatte (3) verschraubt ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE4427222 | 1994-08-01 | ||
DE4427222A DE4427222A1 (de) | 1994-08-01 | 1994-08-01 | Hitzeschild für eine Gasturbinen-Brennkammer |
PCT/EP1995/002795 WO1996004510A1 (de) | 1994-08-01 | 1995-07-17 | Hitzeschild für eine gasturbinen-brennkammer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0774100A1 EP0774100A1 (de) | 1997-05-21 |
EP0774100B1 true EP0774100B1 (de) | 1998-09-16 |
Family
ID=6524660
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95926909A Expired - Lifetime EP0774100B1 (de) | 1994-08-01 | 1995-07-17 | Hitzeschild für eine gasturbinen-brennkammer |
Country Status (5)
Country | Link |
---|---|
US (1) | US5956955A (de) |
EP (1) | EP0774100B1 (de) |
CA (1) | CA2196310C (de) |
DE (2) | DE4427222A1 (de) |
WO (1) | WO1996004510A1 (de) |
Cited By (3)
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---|---|---|---|---|
US7681398B2 (en) | 2006-11-17 | 2010-03-23 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US7721548B2 (en) | 2006-11-17 | 2010-05-25 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US7748221B2 (en) | 2006-11-17 | 2010-07-06 | Pratt & Whitney Canada Corp. | Combustor heat shield with variable cooling |
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US11391461B2 (en) * | 2020-01-07 | 2022-07-19 | Raytheon Technologies Corporation | Combustor bulkhead with circular impingement hole pattern |
US11686474B2 (en) * | 2021-03-04 | 2023-06-27 | General Electric Company | Damper for swirl-cup combustors |
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Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2616257A (en) * | 1946-01-09 | 1952-11-04 | Bendix Aviat Corp | Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities |
GB2044912B (en) * | 1979-03-22 | 1983-02-23 | Rolls Royce | Gas turbine combustion chamber |
US4322945A (en) * | 1980-04-02 | 1982-04-06 | United Technologies Corporation | Fuel nozzle guide heat shield for a gas turbine engine |
GB2221979B (en) * | 1988-08-17 | 1992-03-25 | Rolls Royce Plc | A combustion chamber for a gas turbine engine |
US5129231A (en) * | 1990-03-12 | 1992-07-14 | United Technologies Corporation | Cooled combustor dome heatshield |
GB9018013D0 (en) * | 1990-08-16 | 1990-10-03 | Rolls Royce Plc | Gas turbine engine combustor |
GB9018014D0 (en) * | 1990-08-16 | 1990-10-03 | Rolls Royce Plc | Gas turbine engine combustor |
GB2247522B (en) * | 1990-09-01 | 1993-11-10 | Rolls Royce Plc | Gas turbine engine combustor |
US5220795A (en) * | 1991-04-16 | 1993-06-22 | General Electric Company | Method and apparatus for injecting dilution air |
GB2257781B (en) * | 1991-04-30 | 1995-04-12 | Rolls Royce Plc | Combustion chamber assembly in a gas turbine engine |
CA2070518C (en) * | 1991-07-01 | 2001-10-02 | Adrian Mark Ablett | Combustor dome assembly |
US5307637A (en) * | 1992-07-09 | 1994-05-03 | General Electric Company | Angled multi-hole film cooled single wall combustor dome plate |
US5419115A (en) * | 1994-04-29 | 1995-05-30 | United Technologies Corporation | Bulkhead and fuel nozzle guide assembly for an annular combustion chamber |
US5623827A (en) * | 1995-01-26 | 1997-04-29 | General Electric Company | Regenerative cooled dome assembly for a gas turbine engine combustor |
-
1994
- 1994-08-01 DE DE4427222A patent/DE4427222A1/de not_active Withdrawn
-
1995
- 1995-07-17 DE DE59503631T patent/DE59503631D1/de not_active Expired - Fee Related
- 1995-07-17 EP EP95926909A patent/EP0774100B1/de not_active Expired - Lifetime
- 1995-07-17 WO PCT/EP1995/002795 patent/WO1996004510A1/de active IP Right Grant
- 1995-07-17 CA CA002196310A patent/CA2196310C/en not_active Expired - Fee Related
- 1995-07-17 US US08/776,615 patent/US5956955A/en not_active Expired - Fee Related
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7681398B2 (en) | 2006-11-17 | 2010-03-23 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US7721548B2 (en) | 2006-11-17 | 2010-05-25 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US7748221B2 (en) | 2006-11-17 | 2010-07-06 | Pratt & Whitney Canada Corp. | Combustor heat shield with variable cooling |
Also Published As
Publication number | Publication date |
---|---|
US5956955A (en) | 1999-09-28 |
EP0774100A1 (de) | 1997-05-21 |
DE4427222A1 (de) | 1996-02-08 |
CA2196310C (en) | 2006-11-07 |
CA2196310A1 (en) | 1996-02-15 |
DE59503631D1 (de) | 1998-10-22 |
WO1996004510A1 (de) | 1996-02-15 |
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