EP2275743A2 - Chambre de combustion d'une turbine à gaz dotée d'un dispositif de démarrage pour un film de refroidissement de la paroi de la chambre de combustion - Google Patents

Chambre de combustion d'une turbine à gaz dotée d'un dispositif de démarrage pour un film de refroidissement de la paroi de la chambre de combustion Download PDF

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Publication number
EP2275743A2
EP2275743A2 EP10005467A EP10005467A EP2275743A2 EP 2275743 A2 EP2275743 A2 EP 2275743A2 EP 10005467 A EP10005467 A EP 10005467A EP 10005467 A EP10005467 A EP 10005467A EP 2275743 A2 EP2275743 A2 EP 2275743A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
turbine combustor
combustor according
cooling
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Withdrawn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
EP10005467A
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German (de)
English (en)
Other versions
EP2275743A3 (fr
Inventor
Miklos Dr. Gerendas
Sermed Sadig
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2275743A2 publication Critical patent/EP2275743A2/fr
Publication of EP2275743A3 publication Critical patent/EP2275743A3/fr
Withdrawn legal-status Critical Current

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    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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 gas turbine combustion chamber with a starter film for cooling the combustion chamber wall according to the features of the preamble of claim 1.
  • the combustion chamber represents the wall of a space in which fuel is burned with the compressed air from the compressor before it is relaxed in the turbine while doing work. Since the gas temperatures in the combustion chamber are usually above the melting temperature of the wall material, this wall must be cooled. To achieve a long life, far lower temperature limits must be maintained.
  • the combustion chamber can, for example, with cooling rings ( US 4,566,280 ), Effusion wells ( US 5,181,379 ), donated shingles ( EP 1 098 141 A ) or impact- and effusion-cooled shingles ( US 5,435,139 ).
  • a so-called starter film is usually applied at the beginning of the combustion chamber wall.
  • This starter film protects the wall until the actual cooling method for the combustion chamber wall shows sufficient effect.
  • the air for this starter film may come from within a space formed by a cover and a base plate or from an annulus between a combustion chamber wall and a combustion chamber housing.
  • the flow-through openings through the combustion chamber wall are usually circular, regularly distributed, perpendicular to the surface bores.
  • the starter film is blown mainly parallel to the combustion chamber wall along this.
  • the gap from which the uniformly distributed on the circumference cooling film exits, is formed by a cooling ring.
  • Such a starter film for an effusion cooled wall is in the US 5,279,127 shown.
  • the air is guided only on one side by a component belonging to the combustion chamber wall, on the other side by a flow surface of a heat shield.
  • the starter film is blown out (see Fig. 1 ) to protect this part of the combustion chamber from the hot gases of combustion. This is usually done by a number of circular holes on a particular circle.
  • the air is first blown onto the back of the heat shield. Upon impact of the rays, these cool the heat shield and combine to form a homogeneous film, which then flows parallel to the combustion chamber wall at a certain distance.
  • the size of the holes, their spacing on a pitch circle or the number of pitch circles is adapted to the locally required cooling capacity.
  • Such a starter film is off DE 102 14 573 A1 known.
  • ribs can be applied to the part of the heat shield which carries the air for the starter film, such as, for example DE 44 27 222 A1 or DE 195 08 111 A1 known.
  • the ribs shown there do not protrude radially beyond the lip of the heat shield.
  • the wall which can be executed with single wall or with additional impact-cooled shingles, is built by the air flowing through the wall or the shingle air only a certain distance downstream of a protective cooling film. Without a starter film, the beginning part of the wall would not be sufficiently protected.
  • a cooling film is formed in a stage in the combustion chamber wall by bouncing radially supplied air onto a plate while being deflected by substantially 90 degrees and blowing out as a film substantially parallel to the combustion chamber wall.
  • the cooling air is for this purpose by a kind of ribs or Shovels aligned correspondingly tangentially to these hot gases.
  • the cooling air is thus injected radially and deflected by 90 degrees.
  • it is imposed a circumferential component, so that the flow is slowed down very much.
  • only the wall cooling is also described in this document, but not the starter film training.
  • the starter film is formed by equalizing a flow formed by many individual bores by means of impingement and deflection in a cooling ring (US Pat. US 5,279,127 ) or on the heat shield ( DE 102 14 573 A1 ) educated.
  • the starter film air collects in the area between the burners.
  • the heat input into the combustion chamber wall thus increases spatially periodically with each burner and drops off again in the intermediate spaces, whereby a temperature variation in the circumferential direction inevitably arises in the combustion chamber wall.
  • the temperature limit of the material may not be exceeded.
  • the necessary amount of air of the starter film is determined by the highest loaded point on the circumference. The result is an unnecessarily strong cooling of the combustion chamber wall in the area between the burners by cold strands of air intended for the hot combustion chamber wall on the burner axis.
  • the unadapted cooling results in a significant temperature fluctuation of the combustion chamber wall in the circumferential direction, with the result of the generation of strong mechanical stresses in the combustion chamber wall.
  • the invention has for its object to provide a gas turbine combustor with starter film for cooling the combustion chamber wall of the type mentioned, which ensures a reliable starter film education and an optimized temperature distribution with a simple structure and cost manufacturability.
  • the central axes of the openings for the passage of the cooling air are formed inclined at a shallow angle to the combustion chamber wall.
  • This weak deflection is achieved according to the invention by the existence of an intersection point between the center axis 17 of the starter film opening 6 and the combustion chamber wall 4 (FIG. Fig. 2 and 3 ) and described by an angle ⁇ less than 30 degrees.
  • the strongest deflection must take place on the component on which the largest film cooling effect is to be produced, ie the hot side of the combustion chamber wall 4, where the air flowing in against the wall is deflected wall-parallel.
  • the angle of the deflection ⁇ is preferably smaller or at most equal to the deflection on the combustion chamber wall 4, which is described by the angle ⁇ .
  • This deflection angle ⁇ is measured as the angle between the central axis 17 of the beam of a starter film opening 6 to the surface of the component 5 at the point at which the projection of the starter film opening 6 meets this component 5.
  • the direction of rotation of the two deflections is preferably in the opposite direction.
  • the angle of the deflection of the starter film jet on the combustion chamber wall should not exceed 30 degrees according to the invention, and is preferably limited to less than 20 degrees, in a favorable embodiment 5 -15 degrees provided.
  • the projection of the wall of the starter film opening in the direction of the combustion chamber wall 4 touches the heat shield 5 only at one point, or the projection runs as a tangent to the heat shield contour. In both cases there is no real intersection of the projection with the heat shield contour (see Fig. 3 ), so there is no diversion in the true sense.
  • the angle ⁇ of the deflection of the starter film 3 on the combustion chamber wall 4 (measured as the angle between the axis of the starter film opening 6 and the hot side surface of the combustion chamber wall 4) according to the invention should not exceed 30 degrees, and is preferably limited to less than 20 degrees, in a favorable embodiment are provided 5-15 degrees.
  • ribs 14 are provided in an advantageous development of the invention, which are aligned substantially at the intended flow direction and extend radially inwardly beyond the starter film lip, see Fig. 2 and 3 , as well as 4, 5, 6 and 7.
  • the flow direction is predetermined by the projection direction of the starter film openings 6 in the direction of the combustion chamber wall 4. And therefore, the ribs do not substantially deflect the air in the circumferential direction.
  • the openings 6 which form the narrowest cross-section are made not only in the radial direction but also in the circumferential direction, see Fig. 5 .
  • the angle ⁇ between the axial direction of the engine and the axis of the opening according to the invention is less than 60 degrees, preferably 30-45 degrees.
  • the ribs 14 are arranged on the part of the heat shield 5, which leads the air for the starter film. However, these deflect the air according to the invention not in the circumferential direction, but the Peripheral component is generated substantially by the cooling holes 6 and only preserved by the ribs 14.
  • the ribs can be located on both the cold side of the heat shield ( Fig. 2 and 3 ) as well as on the downstream side of the base plate 2, see Fig. 6 , or the inside of the combustion chamber wall 4 may be placed.
  • the ribs can be connected to the heat shield 5, or the base plate 2 or wall 4 as an integral component or form-fitting or frictionally engaged. Since the ribs 14 do not have to generate a deflection of the flow, no major forces occur, so that they can also be placed as a loose component between the heat shield 5 and the base plate 2 and the combustion chamber wall 4, provided by a suitable connecting element between the individual ribs 14 as for example soldered wire, see Fig. 7 , the direction and the distance of the ribs 14 are set according to the requirements.
  • the starter film openings 6 can vary, individually or in groups, in the size of their circumferential angle ⁇ , see Fig. 8 , then mediate the ribs by a thickness variation in the flow direction between these two directions. If the starter film openings point away from one another, the ribs 14 become thicker in the flow direction or the starter film openings point towards one another, the ribs 14 become thinner in the flow direction.
  • the principle according to the invention is maintained that the ribs 14 do not determine the direction of the flow, but are predetermined by the direction of the starter film openings 6 and are essentially only obtained by the ribs.
  • the speed of the starter film air 3 is maintained near the maximum velocity at the opening 6 in the combustion chamber wall.
  • the resulting on the hot side of the combustion chamber wall 4 cooling film maintains its high momentum and can push away the flame of the burner from the wall 4.
  • the additional speed of the cooling film in the circumferential direction reduces the difference in the flow direction between the starting film and the outflow from the burner or the flow direction in the flame, which in turn results in a reduction in the mixing of the flame and the starter film.
  • the starter film air flows over the wall in the area of the highest wall heat load and ensures a low wall temperature on the burner axis due to the very low mixing with the hot gas over a large run length. Since no starter film air 3 is displaced from the burner axis, there are no cold air strands and no over-cooled strips between the burners. It decreases the temperature gradient in the circumferential direction and thus the thermally induced voltage in the combustion chamber wall drastically, thus the life at a given temperature for a given material is increased. Thus, however, the operating temperature of a component for the same life and predetermined material can be increased or it can be avoided on a weaker and cheaper material at the same temperature and life.
EP10005467.5A 2009-07-17 2010-05-26 Chambre de combustion d'une turbine à gaz dotée d'un dispositif de démarrage pour un film de refroidissement de la paroi de la chambre de combustion Withdrawn EP2275743A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009033592A DE102009033592A1 (de) 2009-07-17 2009-07-17 Gasturbinenbrennkammer mit Starterfilm zur Kühlung der Brennkammerwand

Publications (2)

Publication Number Publication Date
EP2275743A2 true EP2275743A2 (fr) 2011-01-19
EP2275743A3 EP2275743A3 (fr) 2017-12-06

Family

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EP10005467.5A Withdrawn EP2275743A3 (fr) 2009-07-17 2010-05-26 Chambre de combustion d'une turbine à gaz dotée d'un dispositif de démarrage pour un film de refroidissement de la paroi de la chambre de combustion

Country Status (3)

Country Link
US (1) US8938970B2 (fr)
EP (1) EP2275743A3 (fr)
DE (1) DE102009033592A1 (fr)

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US9057523B2 (en) * 2011-07-29 2015-06-16 United Technologies Corporation Microcircuit cooling for gas turbine engine combustor
US9335049B2 (en) 2012-06-07 2016-05-10 United Technologies Corporation Combustor liner with reduced cooling dilution openings
US9239165B2 (en) 2012-06-07 2016-01-19 United Technologies Corporation Combustor liner with convergent cooling channel
US9243801B2 (en) 2012-06-07 2016-01-26 United Technologies Corporation Combustor liner with improved film cooling
US9217568B2 (en) 2012-06-07 2015-12-22 United Technologies Corporation Combustor liner with decreased liner cooling
US9599343B2 (en) * 2012-11-28 2017-03-21 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
US10030524B2 (en) 2013-12-20 2018-07-24 Rolls-Royce Corporation Machined film holes
US10267521B2 (en) 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
US10473332B2 (en) * 2016-02-25 2019-11-12 General Electric Company Combustor assembly
GB201715366D0 (en) 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber
US11092076B2 (en) 2017-11-28 2021-08-17 General Electric Company Turbine engine with combustor
DE102018212394B4 (de) 2018-07-25 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement
US11293638B2 (en) * 2019-08-23 2022-04-05 Raytheon Technologies Corporation Combustor heat shield and method of cooling same
US11525577B2 (en) 2020-04-27 2022-12-13 Raytheon Technologies Corporation Extended bulkhead panel

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US3420058A (en) 1967-01-03 1969-01-07 Gen Electric Combustor liners
US4566280A (en) 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US5181379A (en) 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
US5279127A (en) 1990-12-21 1994-01-18 General Electric Company Multi-hole film cooled combustor liner with slotted film starter
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
EP0434361B1 (fr) 1989-12-22 1995-09-27 Hitachi, Ltd. Chambre et méthode de combustion
DE4427222A1 (de) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
DE19508111A1 (de) 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
EP1098141A1 (fr) 1999-11-06 2001-05-09 Rolls-Royce Plc Eléments de paroi pour turbomachine
DE10214573A1 (de) 2002-04-02 2003-10-16 Rolls Royce Deutschland Brennkammer einer Gasturbine mit Starterfilmkühlung

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3420058A (en) 1967-01-03 1969-01-07 Gen Electric Combustor liners
US4566280A (en) 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
EP0434361B1 (fr) 1989-12-22 1995-09-27 Hitachi, Ltd. Chambre et méthode de combustion
US5181379A (en) 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
US5279127A (en) 1990-12-21 1994-01-18 General Electric Company Multi-hole film cooled combustor liner with slotted film starter
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
DE4427222A1 (de) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
DE19508111A1 (de) 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
EP1098141A1 (fr) 1999-11-06 2001-05-09 Rolls-Royce Plc Eléments de paroi pour turbomachine
DE10214573A1 (de) 2002-04-02 2003-10-16 Rolls Royce Deutschland Brennkammer einer Gasturbine mit Starterfilmkühlung

Also Published As

Publication number Publication date
US20110011093A1 (en) 2011-01-20
DE102009033592A1 (de) 2011-01-20
US8938970B2 (en) 2015-01-27
EP2275743A3 (fr) 2017-12-06

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