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
  • F23R3/02—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
  • F23R3/12—Air inlet arrangements for primary air inducing a vortex
  • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
  • F23C7/00—Combustion apparatus characterised by arrangements for air supply
  • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
  • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
  • F23D11/36—Details, e.g. burner cooling means, noise reduction means
  • F23D11/38—Nozzles; Cleaning devices therefor
  • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
  • F23D14/46—Details, e.g. noise reduction means
  • F23D14/70—Baffles or like flow-disturbing devices
• • 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
  • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
  • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
  • F23C2900/07001—Air swirling vanes incorporating fuel injectors
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
  • F23D2900/14—Special features of gas burners
  • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

• the invention relates to a swirler vane and a swirler, in particular for a gas turbine engine.
• the first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction.
• the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NO x is not excessively formed.
• the second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NO x will be.
• FIG. 2 shows a prior art swirler of a gas turbine engine, comprising a plurality of swirler vanes disposed about a central axis and arranged on a swirler vane support with a central opening.
• the swirler vanes can be fixed to a burner head (not shown) with their sides showing away from the swirler vane support.
• Swirler passages are defined and delimited by opposing side faces of swirler vanes, by the surface of the swirler vane support which shows to the burner head and by a surface of the burner head to which the swirler vanes are fixed. Compressor air flows into these passages and starts mixing with fuel which is added through fuel injection openings (not shown) . Further downstream, the fuel/air mixture enters the combustion zone with a swirling motion about the central axis of the swirler and is ignited by the heat of the combustion gases.
• An object of the invention is to provide an improved swirler vane, in particular for a swirler in a gas turbine engine, which is advantageous in providing a homogeneous fuel/air mixture .
• An inventive swirler vane comprises a through hole connecting at least two surfaces of the swirler vane.
• the respective openings of the through hole are positioned on the respective side faces of the swirler vane.
• the pressure gradients between swirler passages allow the fuel to pass from the high pressure to the low pressure sides of the swirler vanes and therefore provide a more even fuel distribution and an increased level of premix by cross flow between swirler passages which reduces the fraction of nitrous oxide in the exhaust gases of a gas turbine engine.
• the through hole is tube-shaped
• the invention may be implemented with other shapes.
• the preferred location of the openings is at a height of between 10% and 90% of a swirler vane height.
• the homogeneity of the fuel/air mixture over the cross sectional area of a swirler passage can be advantageously increased when respective openings are arranged at different swirler vane heights.
• a further improvement is achieved by more than only one through hole per swirler vane.
• the fuel injection system may either be a liquid fuel injection system or a gaseous fuel injection system.
• the main outlet opening can be provided with turbulence elements, in particular if it is driven with gaseous fuel. Those elements may be present on the circumference of the openings and may e.g. comprise triangular cuts on the circumference.
• the turbulence enhancing features provide additional mixing and direction of a gaseous fuel/air mixture leaving the through hole .
• Openings arranged on the side faces of swirler vanes do not necessarily need to be arranged at the same radius about the central axis of the swirler vane support.
• the invention may be implemented with openings having different distances to a central opening of the swirler vane support.
• Figure 1 schematically shows a section through a burner of a combustion chamber assembly
• FIG 2 shows a perspective view of a prior art swirler shown in Figure 1
• Figure 3 shows a side view of an inventive swirler vane
• Figure 4 shows a cut through the swirler vane of Figure 3
• Figure 5 shows a cut through an alternative embodiment of the inventive swirler vane
• Figure 6 shows a cut through the swirler vane of Figure 3
• Figure 7 shows a cut through an alternative embodiment of the inventive swirler vane
• Figure 8 shows a perspective view of a swirler with inventive swirler vanes.
• Figure 1 illustrates a longitudinal section through a combustor.
• the combustor comprises relative to a flow direction: a burner with swirler 2 and a burner-head 1 attached to the swirler 2, a transition piece referred to as combustion pre-chamber 3 and a main combustion chamber 4.
• the main chamber 4 has a diameter being larger than the diameter of the pre-chamber 3.
• the combustion chamber 4 is connected to the pre-chamber 3 via a dome portion 10 comprising a dome plate 11.
• the transition piece 3 may be implemented as a one part continuation of the burner head 1 towards the main chamber 4, as a one part continuation of the main chamber 4 towards the burner head 1, or as a separate part between the burner head 1 and the main chamber 4.
• the burner head 1 and the main chamber 4 assembly show rotational symmetry about a longitudinally central axis 12.
• a fuel conduit 5 is provided for leading fuel to the burner which is to be mixed with in-streaming air in the swirler 2.
• the fuel/air mixture 7 is then guided towards the primary combustion zone 9 where it is burnt to form hot, pressurised exhaust gases streaming in a direction 8 indicated by arrows to a turbine of the gas turbine engine (not shown) .
• FIG. 2 A perspective view of a prior art swirler 2 is shown in Figure 2.
• the swirler comprises a ring-shaped swirler vane support 13 with a central opening 14.
• Six swirler vanes 15 with pie slice shape are disposed about the central axis 12 and arranged on the swirler vane support 13.
• the swirler vanes 15 can be fixed to the burner head (see Figure 1) with their sides showing away from the swirler vane support 13.
• Swirler passages 16 are defined and delimited by opposing side faces 17 of swirler vanes 15, by the surface of the swirler vane support 13 which shows to the burner head and by a surface of the burner head to which the swirler vanes 15 are fixed.
• Compressor air 6 flows into these swirler passages 16 and starts mixing with fuel which is added through fuel injection openings (not shown).
• Figure 3 schematically shows a side view of an isolated inventive swirler vane 15 arranged on a swirler vane support 13.
• the surface 20 of the swirler vane 15 shown is a side face 17 with openings 18 of through holes 19.
• On the left is the edge of the outer surface 21 of the swirler vane 15.
• Compressor air 6 inflow is from this side and compressor air 6 flows along the surface 20 of the swirler vane 15 as indicated by the arrow.
• the opening 18 on the right of Figure 3 comprises additional turbulence elements 22 for causing a turbulence of a fuel/air mixture guided through the through hole 19. These elements 22 comprise triangular cuts 23 on the circumference of the opening 18.
• Figure 4 shows a cut through the swirler vane 15 of Figure 3, with swirler passages 16 delimited by the swirler vane support 13 and by side faces 17 of the swirler vane 15.
• the through hole 19 can be straight and horizontal, as shown here, or inclined, as shown in Figure 5, or curved (not shown) when using, for example, different production methods.
• the preferred location of the openings 18 is at a height of between 10% and 90% of the swirler vane height.
• Figures 6 and 7 show alternative embodiments of the inventive swirler vane 15 with through holes 19 not being tangential to a circle about the central axis 12 of the swirler 2, but with openings 18 of a through hole 19, the openings arranged at different radii 24, 25 about the central axis 12.
• FIG 8 a perspective view of a swirler 2 with inventive swirler vanes 15 is shown. Twelve swirler vanes 15 are disposed about a central axis 12 and arranged on a swirler vane support 13. The top face of the swirler vanes 15 according to the orientation of the swirler vanes 15 as shown in Figure 8 would be connected to the burner head.
• Figure 8 shows an embodiment of the inventive swirler vanes 15 with openings 18 arranged on the side faces 17 as well as on curved outer surfaces 21 of the swirler vanes 15.
• compressor air 6 is introduced through a plenum (not shown) and flows through the swirler passages 16 with a pressure gradient from the accelerating flow towards the central opening 14 of the swirler vane support 13.
• the curvature of the swirler vanes 15 in Figure 8 from an inlet 26 of the swirler passage 16 to an outlet 27 of the swirler passage 16 which gradually is turning the flow, whereas in Figure 2, there is a straight but staggered swirler passage 16, giving rise to a more sudden deflection of fuel and air.
• the pressure gradient generates a rotating flow, with a cork screw like appearance, as the flow moves from the outside towards the central opening 14 of the swirler 2.
• a pressure gradient in the through holes 19 between swirler passages 16 allows the fuel to pass from the high pressure side to the low pressure side of a swirler vane 15 to more evenly distribute the fuel.
• Some fraction of the compressor air enters the swirler passages 16 via through holes 19 with openings 18 arranged on curved outer surfaces 21 of the swirler vanes 15 and with openings 20 arranged on side faces 17 of the swirler vanes 15, thus creating additional turbulence in the swirler passages 16 which in turn further improves the mixing of fuel and air.
• the fuel/air mixture 7 then leaves the swirler passages 16 and streams through a central opening 14 of the swirler vane support 13 into the pre-chamber 3 (see Figure 1) . From the pre-chamber 3 the fuel/air mixture 7 streams into the combustion zone 9 of the main chamber 4 where it is burned.
• the swirler 2 of the present embodiment has twelve swirler vanes 15, the invention may be implemented with a swirler 2 having a different number of swirler vanes 15, which may either be higher or lower than in the described embodiment.
• the side faces 17 of the swirler vanes 15 may be curved, as shown in Figure 8, or straight, as shown in Figure 2.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)

Applications Claiming Priority (2)

Publications (1)

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ID=38596884

Family Applications (1)

Country Status (2)

Families Citing this family (4)

Citations (4)

• 2007
  • 2007-05-24 EP EP07010376A patent/EP1995521A1/de not_active Withdrawn
• 2008
  • 2008-05-09 WO PCT/EP2008/055777 patent/WO2008141959A1/en active Application Filing

Patent Citations (4)

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