EP0103159B1

EP0103159B1 - Turbine combustor having more uniform mixing of fuel and air for improved downstream combustion

Info

Publication number: EP0103159B1
Application number: EP19830107832
Authority: EP
Inventors: Joel L. Toof
Original assignee: Westinghouse Electric Corp
Current assignee: CBS Corp
Priority date: 1982-08-19
Filing date: 1983-08-09
Publication date: 1987-01-07
Also published as: JPS622216B2; IE54394B1; IE831719L; MX156751A; CA1209813A; AR229741A1; EP0103159A1; JPS5944524A; DE3368974D1

Description

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. Especially the invention relates to a combustor according to the preamble of claim 1, as already known from GB-A-1 575 427.
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.
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.
Typically, see for example GB-A-1 575 427, 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 (as shown in US-A-3 937 008, Figs. 9, 10) 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 (prsesure 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.
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.
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. 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.

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.
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 982-106rC (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.
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).
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.
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.
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 scopps 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.
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.
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 1 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.
The following are the conditions applicable to the test of Figure 4:

Claims

1. A combustor (10) for a land-based combustion turbine comprising a generally tubular sidewall (12) having a downstream mixing zone (34) where a mixture of fuel and air is developed for downstream combustion, said sidewall (12) further having sidewall-openings (14,16) and an upstream primary zone (22) into which air is admitted through said sidewall openings (14,16) to develop an axial airflow (41) for mixing with downstream secondary injection fuel, means (32) for spraying fuel in small rapidly evaporable droplets substantially radially inwardly through said sidewall (12) at a location between said primary zone (22) and said mixing zone (34) for mixing with the primary air flow, a catalyst element (28) being disposed in the combustor sidewall (12) at the outlet of the mixing zone (34), whereby the fuel spraying means (32) include a plurality of circumferentially located air holes (36) being so located against the sprayed fuel to boost the mixing of fuel and air with uniformity of the fuel/air mixture at the outlet of the mixing zone (34), characterized in that

(a) the air holes (36) are located upstream from said fuel spraying means (32) and direct booster air streams (39) angularly downstream,

(b) the air holes (36) include air scoops (37),

(c) the booster air stream has a higher velocity than that of the axial air flow from the primary zone,

(d) the air holes (36) include means to vary said predetermined angle of said booster air streams (39).

2. A combustor (10) as in claim 1, characterized in that a head end (18) region of said combustor (10) includes a primary fuel nozzle (20) which supplies fuel for combustion in said primary zone (22) to supplement the catalytic combustion under limited predetermined operating conditions.

3. A combustor as in claim 1 or 2, characterized in that said scoops (37) are located substantially externally of said combustor sidewall (12).