EP0849529B1

EP0849529B1 - Tangential entry fuel nozzle

Info

Publication number: EP0849529B1
Application number: EP19970310463
Authority: EP
Inventors: Timothy S. Snyder; William A. Sowa; Stephen K. Kramer
Original assignee: United Technologies Corp
Current assignee: Raytheon Technologies Corp
Priority date: 1996-12-20
Filing date: 1997-12-22
Publication date: 2004-03-03
Anticipated expiration: 2017-12-22
Also published as: EP0849529A2; EP0849529A3; DE69727899D1; DE69727899T2

Description

This invention relates to low NOx premix fuel nozzles, and particularly to such nozzles for use in gas turbine engines.
The production of nitrous oxides (hereinafter "NOx") occurs as a result of combustion at high temperatures. NOx is a notorious pollutant, and as a result, combustion devices which produce NOx are subject to ever more stringent standards for emissions of such pollutants. Accordingly, much effort is being put forth to reduce the formation of NOx in combustion devices.
One solution has been to premix the fuel with an excess of air such that the combustion occurs with local high excess air, resulting in a relatively low combustion temperature and thereby minimizing the formation of NOx. A tangential entry fuel nozzle which so operates is shown in U.S. Pat. No. 5,307,634, which discloses a scroll swirler with a conical center body. The scroll swirler comprises two offset cylindrical-arc scrolls connected to two endplates. Combustion air enters the swirler through two rectangular slots formed by the offset scrolls, and exits through a combustor inlet in one endplate and flows into the combustor. A linear array of orifices located on the outer scroll opposite the inner trailing edge injects fuel into the airflow at each inlet slot from a manifold to produce a uniform fuel air mixture before exiting into the combustor. Further examples of a tangential entry fuel nozzle is shown in WO 96/19699 and WO 95/23316.
Premix fuel nozzles of this type have demonstrated low emissions of NOx relative to fuel nozzles of the prior art. Unfortunately, the nozzle experienced durability problems related to severe deterioration of the centerbody as a result of attachment of the flame to the centerbody. As a result, the operational life of such nozzles when used in gas turbine engines has been limited.
What is needed is a method of combustion and a tangential entry nozzle that significantly reduces the tendency of the combustion flame to attach to the centerbody of a tangential entry nozzle, and tends to disgorge the flame if it does attach thereto.
It is therefore an object of the present invention to provide a method of combustion which significantly reduces the tendency of the combustion flame to attach to the centerbody of a tangential entry nozzle.
From a first aspect, the invention provides a method for burning fuel in the combustor of a gas turbine engine, as claimed in claim 1.
From a second aspect, the invention provides a fuel nozzle as claimed in claim 3.
Accordingly, a method of combustion which prevents or reduces the tendency of the combustion flame to stabilise within a tangential entry nozzle is disclosed which comprises mixing fuel and air in a mixing zone within a fuel nozzle assembly, and combusting the mixture downstream of the throat of a combustor inlet port while isolating the combustion products from the mixed fuel and air within the nozzle at all operating conditions of the engine.
Further there is disclosed a tangential air entry fuel nozzle which has a longitudinal axis and two cylindrical-arc scrolls with the centerline of each offset from that of the other. Overlapping ends of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle. A combustor-end endplate has a central opening to permit air and fuel to exit into a combustor, while at the opposite end another endplate blocks the nozzle flow area. The scrolls are secured between these endplates. A frusto-conical centerbody is located between the scrolls coaxial with the axis. The centerbody has a base which includes at least one air supply port extending therethrough, and first and second cylindrical members that have an internal passageway. The frusto-conical member tapers towards, and terminates at a discharge orifice at the passageway of the first cylindrical member. The passageway of the second cylindrical member is located within the frusto-conical member and has a diameter greater than the discharge orifice. In preferred embodiments a fuel-lance that is coaxial with the axis and extends through the base and terminates within the second passageway provides fuel to the air flow in the centerbody.
A preferred embodiment of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which:
Figure 1 is a cross-sectional view of the fuel nozzle of the present invention, taken along line 1-1 of Figure 2.
Figure 2 is a cross-sectional view looking down the longitudinal axis of the nozzle of the present invention.
Figure 3 is a cross-sectional view of the fuel nozzle of the present invention, taken along line 3-3 of Figure 2.
Referring to Figure 1, a low NOx premix fuel nozzle 10 embodying the present invention includes a centerbody 12 within a scroll swirler 14. The scroll swirler 14 includes first and second endplates 16,18, and the first endplate is connected to the centerbody 12 and is in spaced relation to the second endplate 18, which has a combustor inlet port 20 extending therethrough. A plurality, and preferably two, cylindrical-arc scroll members 22, 24 extend from the first endplate 16 to the second endplate 18.
The scroll members 22, 24 are spaced uniformly about the longitudinal axis 26 of the nozzle 10 thereby defining a mixing zone 28 therebetween, as shown in Figure 2. Each scroll member 22, 24 has a radially inner surface which faces the longitudinal axis 26 and defines a surface of partial revolution about a centerline 32, 34. As used herein, the term "surface of partial revolution" means a surface generated by rotating a line less than one complete revolution about one of the centerlines 32, 34.
Each scroll member 22 is in spaced relation to the other scroll member 24, and the centerline 32, 34 of each of the scroll members 22, 24 is located within the mixing zone 28, as shown in Figure 2. Referring to Figure 3, each of the centerlines 32, 34 is parallel, and in spaced relation, to the longitudinal axis 26, and all of the centerlines 32, 34 are located equidistant from the longitudinal axis 26, thereby defining inlet slots 36, 38 extending parallel to the longitudinal axis 26 between each pair of adjacent scroll members 22, 24 for introducing combustion air 40 into the mixing zone 28. Combustion supporting air 42 from the compressor (not shown) passes through the inlet slots 36, 38 formed by the overlapping ends 44, 50, 48, 46 of the scroll members 22, 24 with offset centerlines 32, 34.
Each of the scroll members 22, 24 further includes a fuel conduit 52, 54 for introducing fuel into the combustion air 40 as it is introduced into the mixing zone 28 through one of the inlet slots 36, 38. A first fuel supply line (not shown), which may supply either a liquid or gas fuel, but preferably gas, is connected to each of the fuel conduits 52, 54. The combustor inlet port 20, which is coaxial with the longitudinal axis 26, is located immediately adjacent the combustor 56 to discharge the fuel and combustion air from the present invention into the combustor 56, where combustion of the fuel and air takes place.
Referring back to Figure 1, the centerbody 12 has a base 58 that has at least one, and preferably a plurality, of air supply ports 60, 62 extending therethrough, and the base 58 is perpendicular to the longitudinal axis 26 extending therethrough. The centerbody 12 also has an internal passageway 64 that is coaxial with the longitudinal axis 26 and discharges into the combustor inlet port 20. The air passing through the internal passageway 64, which is preferably co-rotating with the combustion air entering through the inlet slots 36,38 but may be counter-rotating, may or may not be fuelled. In a preferred embodiment of the invention, (particularly where fuelling of the centerbody is desired) the internal passageway 64 includes a first cylindrical passage 66 having a first end 68 and a second end 70, and a second cylindrical passage 72 of greater diameter than the first cylindrical passage 66 and likewise having a first end 74 and a second end 76. The second cylindrical passage 72 communicates with the first cylindrical passage 66 through a tapered passage 78 having a first end 80 that has a diameter equal to the diameter of the first cylindrical passage 66, and a second end 82 that has a diameter equal to the diameter of the second cylindrical passage 72. Each of the passages 66, 72, 78 is coaxial with the longitudinal axis 26, and the first end 80 of the tapered passage 78 is integral with the second end 70 of the first cylindrical passage 66, while the second end 82 of the tapered passage 78 is integral with the first end 74 of the second cylindrical passage 72. The first cylindrical passage 66 includes a discharge orifice 68 that is circular and coaxial with the longitudinal axis 26, and is located at the first end 68 of the first cylindrical passage 66. As stated above, while in a preferred embodiment of the embodiment, both fuel and combustion air flow through the centerbody 12, the present invention in other embodiments may be used with a centerbody that flows either fuel, combustion air or neither fuel nor air.
Referring to Figure 3, the radially outer surface 84 of the centerbody 12 includes a frustum portion 86, which defines the outer surface of a frustum that is coaxial with the longitudinal axis 26 and flares toward the base 58, and a curved portion 88 which is integral with the frustum portion 86 and preferably defines a portion of the surface generated by rotating a circle, which is tangent to the frustum portion 86 and has a center which lies radially outward thereof, about the longitudinal axis 26. In the preferred embodiment, the frustum portion 86 terminates at the plane within which the discharge orifice 68 is located, the diameter of the base (not to be confused with the base 58 of the centerbody) of the frustum portion 86 is 2.65 times greater than the diameter of the frustum portion 86 at the apex thereof, and the height 90 of the frustum portion 86 (the distance between the plane in which the base of the frustum portion 86 is located and the plane in which the apex of the frustum portion 86 is located) is approximately 1.90 times the diameter of the frustum portion 86 at the base thereof. As described in further detail below, the curved portion 88, which is located between the base 58 and the frustum portion 86, provides a smooth transitional surface that directs and turns axially combustion air 40 entering the tangential entry nozzle 10 adjacent the base 58. As shown in Figure 3, the internal passageway 64 is located radially inward from the radially outer surface 84 of the centerbody 12, the frustum portion 86 is coaxial with the longitudinal axis 26, and the centerbody 12 is connected to the base 58 such that the frustum portion 86 tapers toward, and terminates at the discharge orifice 68 of the first cylindrical passage 66.
As shown in Figure 2, the base of the frustum portion 86 fits within a circle 92 inscribed in the mixing zone 28 and having its center 94 on the longitudinal axis 26. As those skilled in the art will readily appreciate, since the mixing zone 28 is not circular in cross section, the curved portion 88 must be cut to fit therein. A ramp portion 96, 98 is left on the curved portion 88 where the curved portion 88 extends into each inlet slot 36, 38, and this portion is machined to form an aerodynamically shaped ramp 96, 98 that directs the air entering the inlet slot 36, 38 away from the base 58 and onto the curved portion 88 within the mixing zone 28.
Referring to Figure 1, in the preferred embodiment, particularly if the centerbody is fuelled, an internal chamber 100 is located within the centerbody 12 between the base 58 and the second end 76 of the second cylindrical passage 72, which terminates at the chamber 100. Air 102 is supplied to the chamber 100 through the air supply ports 60, 62 in the base 58 which communicate therewith, and the chamber 100, in turn, supplies air to the internal passageway 64 through the second end 76 of the second cylindrical passage 72. The first endplate 16 has openings 104, 106 therein that are aligned with the air supply ports 60, 62 of the base 58 so as not to interfere with the flow of combustion air 102 from the compressor of the gas turbine engine. A swirler 108, preferably of the radial inflow type known in the art, is coaxial with the longitudinal axis 26 and is located within the chamber 100 immediately adjacent the second end 76 of the second cylindrical passage 72 such that all air entering the internal passageway 64 from the chamber 100 must pass through the swirler 108.
The preferred embodiment also includes a fuel lance 110, which likewise is coaxial with the longitudinal axis 26, extends through the base 58, the chamber 100, and the swirler 108, and into the second cylindrical passage 72 of the internal passageway 64. The larger diameter of the second cylindrical passage 72 accommodates the cross-sectional area of the fuel-lance 110, so that the flow area within the second cylindrical passage 72 is essentially equal to the flow area of the first cylindrical passage 66. A second fuel supply line (not shown), which may supply either a liquid or gas fuel, is connected to the fuel lance 110 to supply fuel to an inner passage 112 within the fuel lance 110. Fuel jets 114 are located in the fuel lance 110, and provide a pathway for fuel to exit from the fuel lance 110 into the internal passageway 64.
Referring to Figure 3, the combustor inlet port 20 is coaxial with the longitudinal axis 26 and includes a convergent surface 116 and a divergent discharge surface 118, and a throat 117 therebetween. The discharge surface 118 extends to the exit plane 124 of the fuel nozzle and controls the amount of isolation between the premixed fuel and air and the combustion products thereof. The convergent surface 116 and the divergent surface 118 are coaxial with the longitudinal axis 26, and the convergent surface 116 is located between the first endplate 16 and the divergent surface 118. The convergent surface 116 is substantially conical in shape and tapers toward the divergent surface 118. The divergent surface 118 extends between the intermediate or throat plane 120 and the combustor surface 122 of the combustor inlet port 20, which is perpendicular to the longitudinal axis 26, and defines the exit plane 124 of the fuel nozzle 10 of the present invention. To achieve the desired axial location of a central fuel recirculation zone with respect to the exit plane and maintain the fuel nozzle airflow capacity, the discharge surface may be optimised from cylindrical, convergent or divergent, ie it can be cylindrical, convergent or divergent.
The convergent surface 116 terminates at the intermediate, or throat plane 120, where the diameter of the convergent surface 116 is equal to the diameter of the divergent surface 118. As shown in Figure 3, the intermediate or throat plane 120 is located between the exit plane 124 and the discharge orifice 68 of the internal passageway 64, and the convergent surface 116 is located between the divergent surface 118 and the first endplate 16.
In operation, combustion air from the compressor of the gas turbine engine flows through the openings 104, 106 and the air supply ports 60, 62 in the base 58 and into the chamber 100 of the centerbody 12. The combustion air exits the chamber 100 through the radial inflow swirler 108 and enters the internal passageway 64 with a substantial tangential velocity, or swirl, relative to the longitudinal axis 26. When this swirling combustion air passes the fuel lance 110, fuel (if the centerbody is fuelled), preferably in gaseous form, is sprayed from the fuel lance 110 into the internal passage 64 and mixes with the swirling combustion air. The mixture of fuel and combustion air then flows from the second cylindrical passage 72 into the first cylindrical passage 66 through the tapered passage 78. The mixture then proceeds down the length of the first cylindrical passage 66, exiting the first cylindrical passage 66 just short of, or at, the throat plane 120 of the combustor inlet port 20, providing a central stream of fuel air mixture.
Additional combustion air from the compressor of the gas turbine engine enters the mixing zone 28 through each of the inlet slots 36, 38. Air entering the inlet slots 36, 38 immediately adjacent the base 58 is directed by the ramps 96, 98 onto the curved portion 88 within the mixing zone 28 of the scroll swirler 14. Fuel, preferably gaseous fuel, supplied to the fuel conduits 52, 54 is sprayed into the combustion air passing through the inlet slots 36, 38 and begins mixing therewith. Due to the shape of the scroll members 22, 24, this mixture establishes an annular stream swirling about the centerbody 12, and the fuel/air mixture continues to mix as it swirls thereabout while progressing along the longitudinal axis 26 toward the combustor inlet port 20.
The swirl of the annular stream produced by the scroll swirler 14 is preferably co-rotational with the swirl of the fuel/air mixture in the first cylindrical passage 66, and preferably has an angular velocity at least as great as the angular velocity of the fuel/air mixture in the first cylindrical passage 66. Due to the shape of the centerbody 12, the axial velocity of the annular stream is maintained at speeds which prevent the combustor flame from migrating into the scroll swirler 14 and attaching to the outer surface 84 of the centerbody 12. Upon exiting the first cylindrical passage 66, the swirling fuel/air mixture of the central stream is surrounded by the annular stream of the scroll swirler 14, and the two streams enter the throat 117 of the combustor inlet port 20 and flow radially inward of the convergent surface 116 and the divergent surface 118 until reaching the exit plane 124 of the combustion inlet port 20 downstream of the mixing zone 28, and then flowing into the flame zone adjacent the divergent surface 118 of the combustor inlet port 20.
The present invention significantly increases useful life of the centerbody 12 by significantly increasing the axial velocity of the fuel/air mixture swirling about the centerbody 12. The increased axial velocity results from the curved portion 88, which prevents air entering the mixing zone 28 through the inlet slots 36, 38 immediately adjacent the base 58 from recirculating with little or no axial velocity, and the frustum portion 86, which maintains the axial velocity of the annular stream at speeds which prevent attachment of a flame to the centerbody 12, and tend to disgorge the flame if it does attach thereto.
Although this invention has been shown and described with respect to a detailed embodiment thereof, it will be understood by those skilled in the art that various changes in form and detail thereof may be made without departing from the scope of the claimed invention. For example, in certain embodiments, it may be possible to dispense with the outer surface 84 of the centerbody 12 around the inner part of the centerbody.

Claims

A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion, comprising

providing a scroll swirler(14) having first and second endplates (16,18), said first endplate (16) in spaced relation to said second endplate (18) defining a mixing zone (28) therebetween, said second endplate (18) having a combustor inlet port (20) extending therethrough;

providing a centerbody (12) located within said mixing zone (28) and having a radially outer surface (84) that tapers toward the combustor inlet port (20) and extends substantially the entire length of the mixing zone (28);

introducing a first portion of combustion air tangentially into said mixing zone (28) substantially continuously along the length thereof;

introducing a first portion of fuel into said combustion air as said combustion air is introduced into said mixing zone (28);

mixing said combustion air and fuel by swirling said combustion air and fuel about said centerbody (12) while flowing said combustion air and fuel towards said combustor inlet (20)

introducing a second portion of combustion air into said first portion of combustion air radially inwardly thereof at said combustor inlet port (20);

introducing a second portion of combustion air into said first portion of combustion air radially inwardly thereof at said combustor inlet port (20), the step of introducing a second portion of combustion air into said first portion radially inward thereof at said combustor inlet (20) including introducing a second portion of combustion air into said centerbody (12); and

burning said fuel external of said mixing zone, characterised by

introducing a second portion of fuel into said second portion of combustion air within said centerbody (12), and

mixing said second portion of fuel within said second portion of combustion air within said centerbody (12).
The method of claim 1 wherein the step of introducing a second portion of combustion air into said first portion radially inward thereof at said combustor inlet port (20) is preceded by the step of
swirling said second portion of combustion air within said centerbody (12) at an angular velocity substantially equal to the angular velocity of the first portion.
A fuel nozzle assembly for use a gas turbine engine, comprising:

a centerbody (12) including

a longitudinal axis (26),

a base (58), and

a radially outer surface including a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and flares towards the base;

a scroll swirler (14) having first and second endplates (16, 18) said first endplate in spaced relation to said second endplate, said second endplate having a combustor inlet port (20)extending therethrough,

at least two cylindrical-arc scroll members (22,24) , each scroll member defining a body of partial revolution about a centerline (32,34), each of said scroll members extending from said first endplate to said second endplate and spaced uniformly about the axis thereby defining a mixing zone (28) therebetween, each of said scroll members in spaced relation to each of the other scroll members, each of said centerlines located within said mixing zone, each of said centerlines in spaced relation to, equidistant from, and parallel to said axis, thereby defining inlet slots (36,38) extending parallel to said axis between each pair of adjacent scroll members for introducing combustion air into said mixing zone, each of said scroll members including a fuel conduit (52,54) for introducing fuel into combustion air introduced through one of said inlet slots;

wherein said base (58) is connected to said first endplate (16) and characterised in that said frustum portion (84) extends into said combustor inlet port(20).
The fuel nozzle of claim 3 wherein said centerbody (12) has a curved portion (88) which is integral with the frustum portion (86).
The fuel nozzle of claim 4 wherein said curved portion (88) defines a portion of the surface generated by rotating a circle which is tangent to the frustum portion and has a center which lies radially outward thereof about the longitudinal axis (26).
The fuel nozzle of claim 3, 4 or 5 wherein said base (58) has at least one air supply port (60,62) extending therethrough, and the center body (12) further includes an internal passageway (64) that is coaxial with the longitudinal axis (26) and communicates with said air supply port, said internal passageway including a discharge orifice (68) that is circular, coaxial with said axis and located within said combustor inlet port (20).
The fuel nozzle of claim 6 wherein said centerbody (12) further includes an internal chamber (100) located between said base (58) and said internal passageway (64), said air supply ports (60,62) communicating with said internal passageway through said chamber.
The fuel nozzle of claim 7 wherein said internal passageway (64) includes a first cylindrical passage (66), a second cylindrical passage (72), and a tapered passage (78), each passage having a first end (68,74,80) and a second end (70,76,82), said second cylindrical passage having a diameter greater than said first cylindrical passage, said second cylindrical passage communicating with said first cylindrical passage through said tapered passage, said first end of said tapered passage integral with said second end of said first cylindrical passage, said second end of said tapered passage integral with said first end of said second cylindrical passage, said first end of said tapered passage having a diameter equal to the diameter of the first cylindrical passage, and said second end of said tapered passage having a diameter equal to the diameter of the second cylindrical passage, each of said passages coaxial with the longitudinal axis (26), said first cylindrical passage including said discharge orifice (68) located at the first end of said first cylindrical passage.
The fuel nozzle of claim 8, wherein said centerbody (12) further includes a swirler (108) coaxial with the axis (26) and located within the chamber (100) immediately adjacent the second end (76) of the second cylindrical passage (72), and
a fuel lance (110) coaxial with the axis (26) and extending through said base (58), said internal chamber, and said swirler (108) and terminating within said second cylindrical passage.