RADIAL EQUILIBRATED COMBUSTION NOZZLE ARRAY

Abstract

A fuel injection system for a gas turbine engine includes a first plurality of fuel nozzles arrayed in a circular pattern. Each of the nozzles in the first plurality of fuel nozzles includes a first airflow area defined therethrough. A second plurality of fuel nozzles radially inward from the first plurality of fuel nozzles. Each of the nozzles in the second plurality of fuel nozzles includes a second airflow area defined therethrough. The first airflow area is larger than the second airflow area. A third plurality of fuel nozzles can be radially inward from the second plurality of fuel nozzles. Each of the nozzles in the third plurality of fuel nozzles can include a third airflow area defined therethrough. The second airflow area can be larger than the third airflow area.

Claims

1. A fuel injection system for a gas turbine engine comprising: a first plurality of fuel nozzles arrayed in a circular pattern, wherein each of the nozzles in the first plurality of fuel nozzles includes a first airflow area defined therethrough; a second plurality of fuel nozzles radially inward from the first plurality of fuel nozzles, wherein each of the nozzles in the second plurality of fuel nozzles includes a second airflow area defined therethrough, wherein the first airflow area is larger than the second airflow area.

2. The system as recited in claim 1, further comprising a third plurality of fuel nozzles radially inward from the second plurality of fuel nozzles, wherein each of the nozzles in the third plurality of fuel nozzles includes a third airflow area defined therethrough, wherein the second airflow area is larger than the third airflow area.

3. The system as recited in claim 2, wherein each of the first, second, and third pluralities of fuel nozzles includes an equal number of fuel nozzles.

4. The system as recited in claim 2, further comprising at least one additional plurality of fuel nozzles, each radially inward from another one of the pluralities of fuel nozzles, and each having a smaller airflow area than one of the plurality of fuel nozzles that is immediately radially outward therefrom.

5. The system as recited in claim 2, wherein each fuel nozzle in the first plurality of fuel nozzles has a first fuel flow area defined therethrough, wherein each fuel nozzle in the second plurality of fuel nozzles has a second fuel flow area defined therethrough, and wherein each nozzle in the third plurality of fuel nozzles has a third flow area defined therethrough.

6. The system as recited in claim 5, wherein the second fuel flow area is smaller than the first fuel flow area in proportion to the difference in size between the second airflow area and the first air flow area, and wherein the third fuel flow area is smaller than the second fuel flow area in proportion to how much smaller the third airflow area is relative to the second air flow area.

7. The system as recited in claim 5, wherein the first, second, and third fuel flow areas are each fed by separate respective fuel manifolds, wherein the first fuel flow area is pressurized higher than the second fuel flow area, which is pressurized higher than third fuel flow area, wherein pressurization of the separate respective fuel manifolds are proportionate to the respective air flow areas of the first, second, and third pluralities of fuel nozzles.

8. The system as recited in claim 2, wherein the third plurality of fuel nozzles is positioned within an annulus having an inner diameter D1 and an outer diameter D2, wherein the second plurality of fuel nozzles is positioned within an annulus having an inner diameter D2 and an outer diameter D3, and wherein the first plurality of fuel nozzles is positioned within an annulus having an inner diameter D3 and an outer diameter D4, wherein D4−D3=D3−D2=D2−D1.

9. The system as recited in claim 2, wherein each fuel nozzle in the first plurality of fuel nozzles has a channel height defined between a prefilmer and an outer air shroud, H.sub.o1, wherein each fuel nozzle in the second plurality of fuel nozzles has a channel height defined between a prefilmer and an outer air shroud, H.sub.o2, wherein each fuel nozzle in the third plurality of fuel nozzles has a channel height defined between a prefilmer and an outer air shroud, H.sub.o3, and wherein H.sub.o1>H.sub.o2>H.sub.o3 to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

10. The system as recited in claim 9, wherein each fuel nozzle in the first, second, and third pluralities of fuel nozzles has an equal outer air shroud diameter.

11. The system as recited in claim 2, wherein each fuel nozzle in the first, second, and third pluralities of fuel nozzles has an outer air circuit comprised of discrete holes distributed circumferentially around the nozzle, wherein the discrete holes of the first plurality of fuel nozzles have a first hole diameter d.sub.o1, wherein the discrete holes of the second plurality of fuel nozzles have a second hole diameter d.sub.o2, wherein the discrete holes of the third plurality of fuel nozzles have a third hole diameter d.sub.o3.

12. The system as recited in claim 11, wherein d.sub.o1>d.sub.o2>d.sub.o3 to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

13. The system as recited in claim 12, wherein d.sub.o1=d.sub.o2=d.sub.o3, and wherein each fuel nozzle of the first plurality of fuel nozzles has more discrete holes than those of the second plurality of fuel nozzles, and wherein each fuel nozzle of the second plurality of fuel nozzles has more discrete holes than those of the third plurality of fuel nozzles to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

14. The system as recited in claim 2, wherein each fuel nozzle in the first, second, and third pluralities of fuel nozzles has an outer air circuit comprised of vanes with vane passages circumferentially spaced apart by the vanes, wherein the vane passages of the first plurality of fuel nozzles have a larger vane passage area a.sub.o1 than that (a.sub.o2) of the second plurality of fuel nozzles, and wherein the vane passages of the second plurality of fuel nozzles have a larger vane passage area (a.sub.o2) larger than that (a.sub.o3) of the third plurality of fuel nozzles, to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

15. The system as recited in claim 14, wherein the vane passage area a.sub.o1 has a larger vane passage height and/or larger vane passage width than the vane passage area a.sub.o2, and wherein the vane passage area a.sub.o2 has a larger vane passage height and/or larger vane passage width than a third vane passage area a.sub.o3 of the third plurality of fuel nozzles.

16. The system as recited in claim 2, wherein each fuel nozzle in the first, second, and third pluralities of fuel nozzles has an inner air circuit comprised of discrete holes distributed circumferentially around the nozzle, wherein the discrete holes of the first plurality of fuel nozzles have a first hole diameter d.sub.i1, wherein the discrete holes of the second plurality of fuel nozzles have a second hole diameter d.sub.i2, wherein the discrete holes of the third plurality of fuel nozzles have a third hole diameter d.sub.i3.

17. The system as recited in claim 16, wherein d.sub.i1>d.sub.i2>d.sub.i3 to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

18. The system as recited in claim 16, wherein d.sub.i1=d.sub.i2=d.sub.i3, and wherein each fuel nozzle of the first plurality of fuel nozzles has more discrete holes than those of the second plurality of fuel nozzles, and wherein each fuel nozzle of the second plurality of fuel nozzles has more discrete holes than those of the third plurality of fuel nozzles to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

19. The system as recited in claim 2, wherein each fuel nozzle in the first, second, and third pluralities of fuel nozzles has an inner air circuit comprised of vanes with vane passages circumferentially spaced apart by the vanes, wherein the vane passages of the first plurality of fuel nozzles have a larger vane passage area a.sub.i1 than that (a.sub.i2) of the second plurality of fuel nozzles, and wherein the vane passages of the second plurality of fuel nozzles have a larger vane passage area (a.sub.i2) larger than that (a.sub.i3) of the third plurality of fuel nozzles, to achieve the difference in the first and second airflow areas, and the difference between the second and third airflow areas.

20. The system as recited in claim 19, wherein the vane passage area a.sub.i1 has a larger vane passage height and/or larger vane passage width than the vane passage area a.sub.i2, and wherein the vane passage area a.sub.i2 has a larger vane passage height and/or larger vane passage width than a third vane passage area a.sub.i3 of the third plurality of fuel nozzles.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0014] FIG. 1 is a schematic, cross-sectional perspective view of a portion of a gas turbine engine constructed in accordance with the present disclosure, showing the nozzles for issuing air from the compressor section into the combustor;

[0015] FIG. 2 is a schematic, downstream end elevation view of the combustor of FIG. 1, showing the arrangement of the nozzles;

[0016] FIG. 3 is a schematic cross-sectional side elevation view of one of the nozzles of FIG. 2, showing how the outer air circuit can be varied to vary the effective area;

[0017] FIGS. 4, 5, and 6 are schematic cross-sectional side elevation, perspective, and end elevation views, respectively, of another embodiment of nozzle having discrete holes in the outer air circuit;

[0018] FIGS. 7 and 8 are schematic cross-sectional side elevation and side elevation views showing another embodiment of an outer air circuit with vanes, wherein the outer portions of the nozzle are removed in FIG. 8 to show the vanes;

[0019] FIGS. 9 and 10 are schematic cross-sectional side elevation and downstream end elevation views of another embodiment of nozzle, wherein the discrete holes of the inner air circuit can vary in diameter from one nozzle to another to provide different effective areas for air flow; and

[0020] FIGS. 11 and 12 are schematic cross-sectional side elevation and downstream end elevation views of another embodiment of nozzle, wherein vane passages in an inner air circuit can vary in dimension from one nozzle to another to provide different effective areas for air flow.

DETAILED DESCRIPTION

[0021] Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an embodiment of a system in accordance with the disclosure is shown in FIG. 1 and is designated generally by reference character 100. Other embodiments of systems in accordance with the disclosure, or aspects thereof, are provided in FIGS. 2-12, as will be described. The systems and methods described herein can be used to improve combustion uniformity in multi-point lean direct injection (MLDI) combustion systems for gas turbine engines.

[0022] The fuel injection system 100 is part of a gas turbine engine 102 that includes a compressor section 104 that feeds compressed gas to a combustor 108, which issues combustion products to a turbine section 106. The compressed air from the compressor section 104 enters the combustor 108 through fuel nozzles, specifically, three rings or pluralities of fuel nozzles 110, 112, 114. The fuel for combustion is also issued from the fuel nozzles 110, 112, 114.

[0023] With reference now to FIG. 2, a first plurality of fuel nozzles 110 are arrayed in a circular pattern around the center axis C of the engine 102. A second plurality of fuel nozzles 112 are arrayed radially inward from the first plurality of fuel nozzles 110. The first airflow area A1 is larger than the second airflow area A2. A1 and A2 are not reference characters in the drawings, but are used in mathematical expressions below and are further described below with reference to the Figures. The circumferential spacing S1 between each adjacent pair of nozzles 110 is wider than the circumferential spacing S2 between each adjacent pair of the nozzles 112, which is in turn greater than the circumferential spacing S3 between each adjacent pair of the nozzles 114. There are the same number of nozzles 110 in the outer most first plurality of fuel nozzles 110 as there are in the second plurality of fuel nozzles 112 as there are in the inner most third plurality of fuel nozzles 114. The third plurality of fuel nozzles 114 is positioned within an annulus having an inner diameter D1 and an outer diameter D2. The second plurality of fuel nozzles 112 is positioned within an annulus having an inner diameter D2 and an outer diameter D3. The first plurality of fuel nozzles 110 is positioned within an annulus having an inner diameter D3 and an outer diameter D4, wherein D4-D3=D3-D2=D2-D1. Therefore, each nozzle 110 services a larger volume V1 of the combustion space than does each nozzle 112, and each nozzle 112 services a larger volume V2 than that (V3) serviced by each nozzle 114. V1 is not a reference character in the Figures, but is a conical annular volume bounded between D4 and D3 of FIG. 2. Similarly, V2 is a conical annular volume bounded by D3 and D2, and V3 is an annular volume bounded by D2 and D1.

[0024] Each of the nozzles 110 in the first plurality of fuel nozzles 100 includes a first effective airflow area A1 defined therethrough (A1 is not shown in the drawings, but is used in the inequality below and is further described below with reference to the Figures). Each of the nozzles 112 in the second plurality of fuel nozzles 112 includes a second airflow area A2 defined therethrough (A2 is not shown in the drawings, but is used in the inequality below and is further described below with reference to the Figures). A third plurality of fuel nozzles 114 is radially inward from the second plurality of fuel nozzles 112. Each of the nozzles 114 in the third plurality of fuel nozzles 114 includes a third airflow area A3 defined therethrough (A3 is not shown in the drawings, but is used in the inequality below and is further described below with reference to the Figures). The second airflow area A2 is larger than the third airflow area A3. Given that all three pluralities of fuel nozzles 110, 112, 114 have the same pressure drop across the nozzles 110, 112, 114, the inequality A1>A2>A3 provides for uniform volumetric flow of air into the combustor, compensating for the different respective volumes V1, V2, V3 serviced by each nozzle 110, 112, 114 for uniform combustion. The uniform combustion reduces temperature variation across the combustion volume, which reduces the amount of emission of undesired exhaust products such as NO.sub.x.

[0025] Similar to airflow, the fuel flow through each nozzle 110, 112, 114 can be tailored for its radial position in the combustor 108. Each fuel nozzle 110 in the first plurality of fuel nozzles 110 has a first fuel flow area FA1 defined therethrough (FA1 is not shown in the drawings, but is governed by an inequality given below). Each fuel nozzle 112 in the second plurality of fuel nozzles 112 has a second fuel flow area FA2 defined therethrough (FA1 is not shown in the drawings, but is governed by an inequality given below). Each nozzle 114 in the third plurality of fuel nozzles 114 has a third flow area FA3 defined therethrough (FA1 is not shown in the drawings, but is governed by an inequality given below). The fuel flow areas FA1, FA2, FA3 conform to the inequality FA1>FA2>FA3. The second fuel flow area FA2 is smaller than the first fuel flow area FA1 in proportion to how much smaller the second airflow area A2 is relative to the first air flow area A1. Similarly, the third fuel flow area FA3 is smaller than the second fuel flow area FA2 in proportion to how much smaller the third airflow area A3 is relative to the second air flow area A2. This relationship allows for the fuel nozzles 110, 112, 114 to all be set to the same fuel pressure and provide volumetrically even fuel distribution within the combustor 108. It is also contemplated that the first, second, and third fuel flow areas FA1, FA2, FA3 can each be fed by separate respective fuel manifolds M1, M2, M3. In this case, the first fuel flow area FA1 is pressurized higher than the second fuel flow area FA2, which is pressurized higher than third fuel flow area FA3. Thus pressurization of the separate respective fuel manifolds M1, M2, M3 can be proportionate to the respective air flow areas A1, A2, A3 of the first, second, and third pluralities of fuel nozzles 110, 112, 114 for uniform volumetric issuance of fuel into the combustor 108.

[0026] Referring now to FIG. 3, one nozzle 110, 112, 114 is shown, as representative of all of the nozzles 110, 112, 114. Each fuel nozzle 110 in the first plurality of fuel nozzles 110 has a channel height H.sub.o1 defined between a prefilmer 116 and an outer air shroud 118, where H.sub.o is labeled generically for all the nozzles 110, 112, 114 in FIG. 3. Similarly, each fuel nozzle 112 in the second plurality of fuel nozzles 112 has a channel height H.sub.o2 defined between a prefilmer and an outer air shroud, and each fuel nozzle 114 in the third plurality of fuel nozzles 114 has a channel height H.sub.o3 defined between a prefilmer and an outer air shroud 118. The channel heights can be made to conform to the inequality H.sub.o1>H.sub.o2>H.sub.o3 to achieve the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3 as explained above with respect to FIG. 2. Each fuel nozzle 110, 112, 114 can have the same outer air shroud diameter D.sub.o, in which case the prefilmer diameters D.sub.p vary among the three pluralities of fuel nozzles 110, 112, 114, respectively. It is also considered that the prefilmer diameters D.sub.p can be the same across all the nozzles 110, 112, 114, and the outer air shroud diameters D.sub.o can be varied from one plurality of fuel nozzles to another to achieve the air flow areas A1, A2, A3, or that both the diameters D.sub.p and D.sub.o can vary. For example, if D.sub.p is increased, and H.sub.o is kept constant, the effective area of the outer air circuit will be increased. Note that FIG. 3 shows the diameters of D.sub.o, D.sub.p, which for each given nozzle 110, 112, 114 gives an outer air circuit effective area that is proportional to π(D.sub.0.sup.2−D.sub.p.sup.2)/4.

[0027] With reference now to FIGS. 4, 5, and 6, another nozzle is shown as representative of all of the nozzles 110, 112, 114. Each fuel nozzle 110, 112, 114 has an outer air circuit 120 outboard of its respective fuel circuit 122 comprised of discrete holes 124 distributed circumferentially around the nozzle 110, 112, 114, each individual hole having hole diameter d.sub.o. The discrete holes 124 of the first plurality of fuel nozzles 110 have a first hole diameter d.sub.o1, the discrete holes 124 of the second plurality of fuel nozzles 112 have a second hole diameter d.sub.o2, and the discrete holes 124 of the third plurality of fuel nozzles 114 have a third hole diameter d.sub.o3. The hole diameters can conform to the inequality d.sub.o1>d.sub.o2>d.sub.o3 to achieve the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3 as explained above with reference to FIG. 2. It is also contemplated that it is possible for d.sub.o1=d.sub.o2=d.sub.o3, wherein each fuel nozzle 110 of the first plurality of fuel nozzles 110 has more discrete holes 124 than those of the second plurality of fuel nozzles 114, and wherein each fuel nozzle 112 of the second plurality of fuel nozzles 112 has more discrete holes 124 than those of the third plurality of fuel nozzles 114 to achieve the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3.

[0028] With reference now to FIGS. 7 and 8, another way in which the differing air flow areas A1, A2, and A3 is shown, where one nozzle is shown as representative of each of the different nozzles 110, 112, 114. Each fuel nozzle 110, 112, 114 has an outer air circuit 126, outboard of its respective fuel circuit 122, comprised of vanes 128 with vane passages 130 circumferentially spaced apart by the vanes 128. The vane passages 130 have cross-sectional flow areas a.sub.o, i.e. where a.sub.o is the product of the width w and height h of the individual vane passage 130. The vane passages 130 of the first plurality of fuel nozzles 110 have a larger vane passage area a.sub.o1 than that (a.sub.o2) of the second plurality of fuel nozzles 112. The vane passages 130 of the second plurality of fuel nozzles 112 have a larger vane passage area (a.sub.o2) larger than that (a.sub.o3) of the third plurality of fuel nozzles 114. This allows for achieving the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3 as described above with reference to FIG. 2. It is also contemplated that the vane passage area a.sub.o1 can have a larger vane passage height h and/or larger vane passage width w than the vane passage area a.sub.o2, and wherein the vane passage area a.sub.o2 has a larger vane passage height h and/or larger vane passage width w than a third vane passage area a.sub.o3 of the third plurality of fuel nozzles 114. It is also contemplated that the thickness of the vanes 128 can be varied among nozzles 110, 112, 114 so the number of vane passages 130 varies to achieve the differences between A1, A2, and A3.

[0029] With reference now to FIGS. 9 and 10, another way in which the differing air flow areas A1, A2, and A3 is shown, where one nozzle is shown as representative of each of the different nozzles 110, 112, 114. Each fuel nozzle 110, 112, 114 has an inner air circuit 132 inboard of its respective fuel circuit 122 comprised of discrete holes 136 distributed circumferentially around the nozzle 110, 112, 114. The discrete holes 136 of the first plurality of fuel nozzles 110 have a first hole diameter d.sub.i1, the discrete holes 136 of the second plurality of fuel nozzles 112 have a second hole diameter d.sub.i2, and the discrete holes 136 of the third plurality of fuel nozzles 114 have a third hole diameter d.sub.i3. The hole diameters can conform to the inequality d.sub.i1>d.sub.i2>d.sub.i3 to achieve the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3. It is also contemplated that the hole diameters can be d.sub.i1=d.sub.i2=d.sub.i3, where each fuel nozzle 110 of the first plurality of fuel nozzles 110 has more discrete holes 136 than those of the second plurality of fuel nozzles 112, and wherein each fuel nozzle 112 of the second plurality of fuel nozzles 112 has more discrete holes 136 than those of the third plurality of fuel nozzles 114 to achieve the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3.

[0030] With reference now to FIGS. 11 and 12, another way in which the differing air flow areas A1, A2, and A3 is shown, where one nozzle is shown as representative of each of the different nozzles 110, 112, 114. Each fuel nozzle 110, 112, 114 has an inner air circuit 132 (inboard of the fuel circuit 122) comprised of vanes 134 with vane passages 136 circumferentially spaced apart by the vanes 134. The vane passages 136 of fuel nozzles 110 have a larger vane passage area a.sub.i1 than that (a.sub.i2) of the second plurality of fuel nozzles 112, and the vane passages of the second plurality of fuel nozzles 112 have a larger vane passage area (a.sub.i2) larger than that (a.sub.i3) of the third plurality of fuel nozzles 114. This can achieve the difference in the first and second airflow areas A1, A2, and the difference between the second and third airflow areas A2, A3. It is also contemplated that the vane passage area a.sub.i1 has a larger vane passage height V.sub.H and/or larger vane passage width V.sub.W than the vane passage area a.sub.i2, and wherein the vane passage area a.sub.i2 has a larger vane passage height V.sub.H and/or larger vane passage width V.sub.W than a third vane passage area a.sub.i3 of the third plurality of fuel nozzles 114. It is also possible to change the number of vane passages 136 in addition to or in lieu of changing the vane passage area a.sub.i.

[0031] While shown and described herein with three different pluralities of fuel nozzles, 110, 112, 114, those skilled in the art will readily appreciate that any suitable number rings or pluralities of nozzles can be used, including 2, 4, 5, or more. Regardless of how many rings or pluralities of nozzles are used, each ring or plurality radially inward from another one of the pluralities of fuel nozzles has a smaller airflow area than whichever one of the plurality of fuel nozzles is immediately radially outward therefrom. Moreover, those skilled in the art will readily appreciate that the various strategies of varying effective area described above with reference to FIGS. 3-12 can be used in combination with one another without departing from the scope of this disclosure.

[0032] While the apparatus and methods of the subject disclosure have been shown and described, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the scope of the subject disclosure.