[0001] The present invention relates to combustors employed in land based combustion turbines
and more particularly to catalytic combustors in which substantially uniform mixing
of fuel and air across the combustor mixing zone is needed prior to entry of the mix
into the catalytic combustion zone.
[0002] Premixing of fuel and air in premix combustors is needed to provide long combustor
life, high combustor efficiency and low emissions through proper combustion operating
temperatures and proper reaction. Catalytic combustors provide a practical commercial
alternative for low pollutant, and especially low NOx, combustion turbine operation
for electric power plants and other land based applications; proper catalytic combustion
especially requires substantial uniformity in the premixing of fuel and air within
the combustor mixing zone.
[0003] In view of . certain operating compressor- discharge-pressure levels in most engine
designs, some preheating of fuel is needed for proper catalytic combustion. A catalytic
combustor may be provided with a generally tubular envelope having a primary combustion
zone followed in sequence first by a secondary fuel injection and mixing zone and
finally by a catalyst zone. The primary combustion zone operates for example during
startup when operating temperatures do not adequately support catalytic combustion.
During the catalytic combustion phase of operation, secondary fuel is injected into
the mixing zone where it mixes with air for delivery to the flow channels through
the catalyst zone.
[0004] Typically, the secondary fuel injectors are disposed circumferentially about the
mixing zone and they may inject fuel radially inwardly at a right angle or other preferred
angle into the combustor mixing zone. Further, the fuel must be preferably completely
vaporized before entering the catalyst which requires that the fuel nozzle produce
very small droplets which can evaporate rapidly. Small droplets can be obtained by
using a very high fuel nozzle pressure drop (pressure atomization), by using a small
amount of high energy atomizing air (air assist), or by using a relatively large amount
of low energy atomizing air (air blast). In all cases, the momentum of the resulting
fuel spray is quite high. In fact the momentum of the fuel spray with respect to the
momentum of the cross flowing air inside the combustor is high enough that the fuel
tends to penetrate to the center (axis) of the combustor. This action produces a fuel
rich core, i.e. the fuel/air ratio profile has a single center peak shape across a
reference diameter of a cross section of the combustor mixing zone.
[0005] The fuel/air ratio is highest at the axis in the fuel injection plane or region,
and it decreases in the radially outward direction. As the mix flows downstream through
the mixing zone, additional mixing action causes the fuel/air ratio profile to flatten
somewhat. In general, however, the fuel penetration in the injection region is such
that there is too much axial fuel concentration to permit available downstream mixing
to produce a substantially uniform fuel/air ratio distribution at the catalyst entry
plane.
[0006] In accordance with the present invention, improved operation is obtained in combustors
and especially catalytic combustors through structure which assists deflection of
injected fuel in the axial direction to produce more uniform mixing of fuel and air
in a mixing zone located immediately upstream from the zone where combustion occurs.
Peferably, the structure includes circumferentially distributed holes in the combustor
wall upstream from the fuel injectors such that entering air streams are angled downstream.
The entering air streams have high velocity due to the pressure drop across the combustor
wall and accordingly greatly assist the internal gas flow in axially deflecting the
injected fuel and producing a substantially uniform fuel/air ratio profile at the
catalyst entry plane.
Figure 1 shows an elevational view of a catalytic combustor having portions thereof
cut away and being arranged in accordance with the principles of the invention.
Figure 2 shows a schematic diagram of a catalytic combustor like that of Figure 1
with operating features of the invention illustrated in greater detail.
Figure 3 shows a diagram like that of Figure 2 but representing an alternative embodiment
in which external air scoops are employed.
Figure 4 shows test results obtained with use of the present invention as compared
to results obtained with a prior art reference.
Figure 5 shows a diagram of a prior art combustor configuration used in obtaining
comparative test results.
[0007] More particularly, a catalytic combustor 10 is shown in Figure 1 for a land based
combustion turbine which is typically used in electric power and other industrial
plants.
[0008] The combustor 10 includes a generally tubular sidewall 12 having successive circumferential
rows of holes 14, 16 for entry of air used in the combustion process. At a head end
18 of the combustor 10, a primary fuel nozzle 20 admits fuel for burning in a primary
zone 22 to generate the energy needed for startup until operating conditions support
catalytic combustion. In addition, the primary nozzle 20 supplies some fuel for primary
combustion during catalytic operation to provide any preheating needed to keep the
gas temperature at a catalyst entry plane 24 at the value needed (i.e. approximately
1800 - 1950°F) for efficient catalytic combustion. The overall combustor operation
involves amounts of primary fuel combustion such that NOx production is well below
prescribed environmental limits.
[0009] An outlet end 26 of the combustor wall 12 is outwardly flared and coupled to a conventional
catalyst element 28 having a honeycomb structure. In turn, the catalyst region outlet
.30 is coupled to a transition duct (not shown) which directs the hot gases to the
turbine (not shown).
[0010] Secondary fuel is injected into the combustor 10 during the catalytic combustion
phase of operation by a set of circumferentially spaced nozzles 32 at the downstream
end of the primary combustor zone 22. Air may or may not enter the combustor 10 at
the nozzle locations. A combustor mixing region 34 between the primary zone and the
catalyst element 28 provides for mixing of the secondary fuel and air prior to its
entry into the catalyst region 28. The region 34 is referred to as a mixing zone,
and combustion is avoided and does not_ occur in this zone since flashback can damage
the combustor and/or catalyst 28. As more fully described in connection with Figures
2 and 4, a circumferential row of air holes 36 immediately upstream of the secondary
fuel injections in the combustor sidewall are angled to admit air in the downstream
direction to produce uniform mixing of the secondary fuel and air in the mixing zone
34.
[0011] As shown in the enlarged view of Figure 2, internal angular scoops 37 are provided
for producing an angled air stream flow 39 through the holes 36 so as to assist in
deflecting the secondary fuel to produce a substantially uniform fuel/air mixture
for the catalyst 28. As shown in Figure 2, the angled air stream 39 significantly
assists internal crossflow air 41 in deflecting the fuel spray produced by the secondary
fuel nozzles 32. In Figure 3, an alternate embodiment is illustrated in which external
scoops 33 produce similar fuel-air mixing action.
[0012] Generally, the fuel/air distribution is controlled and the center peaked fuel/air
mix situation is avoided by taking advantage of the pressure drop across the combustor
wall or liner 12. This pressure drop is typically high enough that the velocity of
the air entering the combustor 10 through holes is much higher than that of the air
already flowing inside the combustor 10. Therefore, the momentum flux (momentum per
unit area per unit time) of the entering air is much higher. With plunged holes or
scoops located just upstream of the fuel spray and angled downstream, the high velocity
of the air admitted through the holes provides a basis for avoiding the nonuniform
center peaked fuel/air mix situation. In fact, the angle of the holes can be varied
to control the fuel/air mix profile entering the catalyst region 28.
[0013] With the provision of angled air admission as described, sidewall injection of fuel
for catalytic combustors is capable of giving the needed even fuel/air mixture approaching
the catalyst.
[0014] As shown by test results in Figure 4, the catalyst outlet temperature, which reflects
the catalyst entry fuel/air ratio profile, shows a relatively even distribution 44
(i.e. a generally flattened shape) for an embodiment of the invention as compared
to the center peaked distribution for the prior art. Figure 5 shows the configuration
used for the prior art in the test while Figure 5 shows the invention configuration
used in the test. The provision of angled air streams in the invention configuration
is the principal reason for the improvement. The improved mixing is believed to occur
as a result of deflection of the fuel spray by the angled air stream to a more advantageous
mix location and/or possibly as a result of air boosted turbulent kinetic energy in
the region where the secondary fuel spray enters the combustor.
[0015] The following are the conditions applicable to the test of Figure 4:
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1. A combustor for a land based combustion turbine, comprising: a generally tubular
structure with a sidewall and having a downstream mixing zone where a mixture of fuel
and air is developed for downstream combustion, said sidewall further having sidewall-openings
and an upstream primary zone into which air is admitted through said sidewall-openings
to develop an axial airflow for mixing with downstream secondary injection fuel, fuel
spraying means for spraying secondary fuel in the form of relatively small rapidly
evaporable droplets directed generally radially inwardly through said sidewall at
a location between said primary zone and said mixing zone for mixing with the primary
air flow, and air stream directing means for directing booster air streams on the
sprayed fuel at a predetermined angle to the axis of the tubular structure to boost
the mixing of fuel and air for improved uniformity of the fuel/air mixture at an outlet
of mixing zone, said booster air streams having a higher velocity than that of a crossflow
air from the primary zone.
2. A combustor as in claim 1 wherein a catalyst is disposed in the combustor sidewall
at the outlet of said mixing zone.
3. A combustor as in claim 2 wherein a head end region of said combustor includes
a primary fuel nozzle which supplies fuel for combustion in said primary zone to supplement
the catalytic combustion under limited predetermined operating conditions.
4. A combustor as in claim 2 wherein said air stream directing means comprise a plurality
of circumferentially disposed and spaced air scoops located in upstream proximity
to said fuel spraying means and pointing in downstream direction to produce said booster
air streams.
5. A combustor as in claim 4 wherein said scoops are located substantially externally
of said combustor sidewall.
6. A combustor as in claim 4 including means to vary said predetermined angle of said
booster air streams.