Turbo Machinery Dynamics Part 10 pptx

High temperature fluctuations outside the combustion zone are caused from mixingbetween the hot reaction products and the surrounding air, and suggest a stream of ambient airentrained to

(Gupta, Lewis, and Daurer, 2000) A 30° swirler for annulus # 1 and +50° and –50° swirlersfor annulus # 2 are used to investigate flames produced from the change of swirl direction

in the annuli The arrangement with both swirlers having positive angles is referred to asproducing coswirl flame, while angles of opposite directions have a counterswirl flame.Figure 9.22 provides a diagram of the burner outlet where the flame stabilization zoneoccurs, and Fig 9.23 shows details of the swirling flow field and the regions of a swirl-stabilized premixed flame (Marshall, 1996)

High-frequency temperature measurements are taken with a microthermocouple probe,with a wire diameter small enough not to cause interference on the flame’s structure whileproviding rigidity for the probe At every location in the flame, the signal is amplified anddigitized for a sampling time of 30 s to allow averaging over low-frequency temperaturemeasurements and to assure a good statistical representation of the thermal field Largevariations in the temperature are present at any location in the flame The sampling fre-quency used is 10 kHz, which is high enough to resolve small thermal time scales in theflame Direct flame photographs taken during the tests provide data about the overall fea-tures of the flame and its stability Negative images of the photographs determine the size

of the flame in proportion to the burner

Raw temperature data have to be compensated for radiation losses and thermal inertiaeffects of the thermocouple Radiation losses can be significant, particularly at high tem-peratures Similarly, the level of fluctuations obtained without compensating the thermo-couple output can be considerable Fluctuating temperatures are lower by as much as 250°C

at some locations in the flame without compensation Qi, Gupta, and Lewis (1997) provide

a method for making corrections The compensated mean temperature maps, shown inFig 9.24, display substantial differences between the left and right sides of the counter-swirling flame, with a flat hot shear layer present at the left side where temperaturesexceed 1700 K The shear layer on the right is steeper but comparatively cooler at about

1500 K The nonsymmetric behavior of the counterswirling flame is observed by ing it with the coswirling map In the postflame region large differences exist in the meantemperatures on both sides The coswirling map tends to be wider with a long area of

compar-FIGURE 9.22 Double concentric burner let region (Gupta, Lewis, and Daurer, 2000).

out-reduced temperature fluctuations A thin but intense reaction zone in the counterswirl casecauses nonsymmetrical fluctuations in a smaller area of the flame But overall differences

in mean temperatures between the two cases are not large

The temperature maps make it possible to locate the combustion area, the recirculationzone and the postflame region Outside the shear layers the flame tends to show higher

FIGURE 9.23 Swirling flow field of premixed flame (Marshall, 1996).

Product recirculation Postflame regionrear stagnation

point

Recirculation zoneboundary

Recirculatingfluid

Shear layer

Shear layer Environment

Fresh reactant ignition

Forward stagnationpoint

Axial location (z/D) Axial location (z/D)

Radial location (r/D) Radial location (r/D)

500

900 700

fluctuating temperatures than in the recirculation zone The regions of low fluctuations arecaused by continuous combustion, and represent pockets of burned gases within the recircula-tion zone High temperature fluctuations outside the combustion zone are caused from mixingbetween the hot reaction products and the surrounding air, and suggest a stream of ambient airentrained toward the flame caused by the recirculation zone of the swirling flow field Thus,the regions of high temperature fluctuations are outside the hot regions Examination of theeffects of swirl on the flame shape, mean and fluctuating temperatures can be useful in evalu-ating eddies present in the flame, which subsequently affect formation of NOx.

Cogeneration systems using a gas turbine as the prime mover offer high total thermal ciency They are subject to strict NOxregulations since air pollution in major populationcenters shows no sign of improvement Water or steam injection or SCR is widely used ingas turbines to reduce the emissions, but the methods tend to increase the operating cost.Lean premixed combustion offers a convenient method to reduce NOxemissions with lowinitial and running cost

effi-Tokyo Gas has focused on the development of dry low NOxcombustors for a ation system in the 1 to 4 MW output range (Sato, Mori, and Nakamura, 1996) Engine out-put is controlled by varying the fuel gas flow, thus eliminating the need for complexvariable geometries for air flow control The double swirler staged combustor uses tertiarypremix nozzles located around the liner Multistaged combustion offers the benefit of sus-taining stable combustion with flame temperature in a range under 1650 K Figure 9.25shows the flow of air and gas in the double swirler combustor concept

cogener-FIGURE 9.25 Double-swirler-staged combustor arrangement (Sato, Mori, and

Primary swirlerSecondary swirler

Air

Exhaust gas

Tertiary nozzlesPilot nozzle

Pilot swirler

The primary and secondary premixing nozzles are placed coaxially with the radialswirlers A pilot nozzle installed at the center of the premixing nozzles generates a diffu-sion flame rather than a perfect premixed flame, hence it stabilizes the flames at the othernozzles adequately The swirlers generate swirling flows in the same direction Four sepa-rate fuel lines lead to the pilot, primary, secondary, and tertiary nozzles Figure 9.26 pro-vides the fuel supply schedule to the nozzles The schedule is designed to provide constantair excess ratios for the pilot and primary nozzles over the whole engine operating loadregime to generate stable combustion with low NOxemission In the 0 to 30 percent loadmode the schedule eliminates fuel supply to the tertiary nozzle to generate a lean fuel-airmixture with an excess air ratio of about 2.0 in the secondary nozzle, thereby igniting andoxidizing while directly contacting the stable combustion products of the primary and pilotnozzles The flame temperature is low because of the excess air, producing practically no

NOx In the high engine load mode up to 100 percent fuel is supplied to the tertiary nozzle,fuel flow to the other nozzles remaining constant at maximum levels Excess air ratio in thetertiary nozzle is also high to reduce NOxformation substantially

Operating conditions and target performance of the combustor are shown in Table 9.6.Target NOxlevel is 9 ppm at engine load between 50 and 100 percent, the normal operatingrange of gas turbines for cogeneration At less than 50 percent load the target is 25 ppm Thesetarget levels convert to 3.0 and 8.3 ppm under atmospheric pressure, assuming the generalrelationship that NOxemission is proportional to the square root of operating pressure

FIGURE 9.26 Fuel gas supply schedule (Sato, Mori, and Nakamura, 1996).

Low mode100

40

High modeTotal fuel

Primary fuel

Engine load (%)

Tertiary fuelSecondary fuel

Pilot fuel

Full load outlet gas temperature 1473 K

Full load excess air ratio 2.7

A schematic representation of the test facility is shown in Fig 9.27 Air is preheatedand rectified before introduction into the test combustor The natural gas used in the test

is 89 percent methane, with ethane, propane, and other hydrocarbons forming the rest.Combustion exhaust gas is sampled with a five-point water-cooled probe positioned down-stream of the exhaust, then introduced into the gas analyzer O2is analyzed by a magneticanalyzer, CO and CO2with a nondispersive infrared analyzer, NOx with a chemilumines-cence analyzer and UHCs with a flame ionization detector Temperature distribution at thecombustor outlet is measured in the same plane as the gas-sampling probe at 24 positions

to obtain an acceptable pattern factor Total flow rate of the process air is calculated fromexhaust gas composition and measured fuel flow, and flow rate to each nozzle assumes asplit proportional to the open area of the respective air nozzle

The charts of Fig 9.28 provide performance characteristics of the combustion system,showing the effects of excess air ratio and corresponding engine load on NOx, CO, UHCs,and combustion efficiency Engine loads of 100, 50, and 0 percent are associated with 2.7,

3.9, and 6.8 of excess air ratio ltot The NOx level is considerably influenced by the

high/low engine load In the low mode, when ltotis between 5.0 and 7.0, the NOxholdssteady at 5 ppm The secondary flame produces virtually no NOxin this range But a sharp

increase is observed when ltotdecreases from 5.0 to 4.0, with NOxlevel reaching 8 ppm Inthe high mode, the additional tertiary fuel with its sufficiently high excess air produceslesser NOx, dipping under 2 ppm when ltotis 3.3 Thus, a higher excess air ratio helps tocurtail thermal NOxproduction

Combustion efficiency reaches a low value of 95 percent during the low mode engine

operation for ltot= 6.2, with a corresponding increase in UHC formation The efficiencycurve recovers, as excess air ratio reaches a maximum Combustion efficiency and CO and

UHC emissions at maximum ltot are affected by the combination of pilot and primary

TV camera

Water

Exhaust

SilencerSpray

CoolingtowerHeatexchanger

Blower

Preheatburner

Test combustorNatural

FIGURE 9.28 Combustor performance characteristics (Sato, Mori, and Nakamura, 1996).

FIGURE 9.29 Double-swirler-staged combustor design (Sato, Mori, and

633

flames A similar drop in combustion efficiency occurs in the high operating engine mode

when ltotincreases from 4.0 to 4.6, where the tertiary flame plays the same role as the ondary flame does in the low mode Considering that the pilot burner is designed for a sta-ble diffusion flame, the majority of CO and UHC is originated in the primary flame Unlikethe pilot, the primary flame mixes directly with the secondary airflow, so the swirling pri-mary flame has a limited residence time and results in high emissions of CO and UHC Therelatively simplified geometry of the double-swirler-staged combustor designed to operate

sec-at standard sec-atmospheric pressure is shown in Fig 9.29

FOR UTILITY TURBINE

The SCR method is useful in chemically reducing NOxto nitrogen and water vapor; ever, the costs associated with heat rate deterioration due to diluent injection and the capi-tal and operating costs for the required systems make it financially unattractive forapplication in combined cycle and cogeneration power plants incorporating gas turbines.Direct catalytic combustion offers good potential for reducing formation of NOx, CO, andUHC in tests carried out at General Electric for model MS9001E gas turbine (Dalla Betta

how-et al., 1996; Schlatter how-et al., 1997) The design calls for partial reaction of fuel-air mixturewithin the catalytic reactor to generate a gas temperature of 800–1000°C at reactor exit Atthis temperature in the reactor, the catalyst can include precious metals, and the substratemay be cordierite or metal

The combustion system design (Fig 9.30) requires a preburner, fuel and air preparationsystem, catalytic reactor, and a combustion liner downstream of the reactor The preburnercarries machine load at conditions when temperature levels do not allow satisfactory cat-alytic combustion, and also preheats to achieve catalytic reactor ignition at high loads.Catalytic staging initiates at turbine inlet temperature of 700°C when the main fuel injec-tor activates The fuel and air preparation system provides the components and preburnerproducts to the reactor bed at a uniform strength, pressure, velocity, and temperature

Preburner

fuel inlet Preburner

Mainfuel inlet

Main fuelinjector Catalyst

Videocamera Postcatalystreaction volumeTransition pieceNozzle box(turbine inlet)

Air inlet

Perforated plate

The catalytic reactor promotes oxidation of hydrocarbons and CO for lean mixtures atadiabatic flame temperature below the threshold for thermal NOx formation Combustioninitiated by the catalyst is then completed by homogeneous burning in the postcatalystregion where high temperatures are obtained Catalytic reactor technology developed bythe manufacturers gives a bed for full fuel and airflow required for maximum power, whileavoiding exposure of the catalyst to high temperatures that may damage the supporting sub-strate Use of ceramic catalytic materials maintains the catalyst surface below the adiabaticcombustion temperature Advantage is taken of the palladium oxide in catalyzing methaneoxidation, while metallic palladium is appreciably less active (McCarty, 1994) Palladiumhas the unique thermodynamic characteristic of oxidizing and reducing Depending onpressure, the oxide decomposes to the metal between 780 and 920°C The reactor consists

of three separate catalyst stages, with the stages formed by corrugating and foiling metalfoil to constitute a channeled monolithic structure Active ceramic material is coated on thefoil The stages are supported in a reactor container by large cell honeycomb structuresmade of Hastelloy X

Experimental data are obtained over a range of conditions from full speed without load

to base load of the engine Combustor discharge temperature ranges from 543°C at no load

to 1195°C at base load Reactor operation is started by heating the system with the burner, then turning on the main fuel flow to provide a smooth light-off of the reactor with

pre-a uniform temperpre-ature profile pre-across the fpre-ace

Figure 9.31 shows measured pollutant emissions data corresponding to ISO ambientwith 15 percent oxygen concentration for average combustor temperatures at the nozzlebox The peak NOxvalue of 55 ppm in the 519–626°C range results from the diffusionflame in the preburner when no fuel is delivered to the main burner and the catalyst As thecombustor is taken to higher exit temperatures, fuel is shifted to the main fuel injector NOxlevels drop to a less-than-desirable 11 ppm, mostly due to the need for higher temperature

in the preburner to keep the catalytic reactor fully active Introduction of steam into the burner zone lowers the NOx to 3 ppm These data are consistent with existing data for NOxsuppression by steam injection for diffusion combustors using natural gas (Touchton,1984) At base load the catalytic reactor fuel is about 80 percent of the total, indicatingessentially no NOxproduction by the reactor

pre-CO emission shows a similar trend, peaking to 3200 ppm at 930°C during preburner onlyoperation, when catalyst staging is in a transient condition between no load and base load

FIGURE 9.31 NO , CO, UHC Emissions (Dalla Betta, 1996).

Combustion temperature rise subsequently transfers to the catalytic combustor At baseload the reaction temperature is noted at 1196°C, when CO emission falls to a minimumvalue of 10 ppm Preburner exit temperature must be maintained at a high enough level tokeep the catalyst fully active Considerable scatter is noted at the base point, mostly due tosensitivity to the preburner exit temperature UHC emissions show a major peak at 800°Cduring preburner fuel operation, reducing to negligible levels at 1200°C At the simulatedbase load operating point with preburner exit temperature at 563°C, the overall combustion

of fuel to equilibrium combustion products is greater than 99.99 percent

Dynamic pressure measurements indicate that the catalytic combustor system ences oscillations lower than in conventional combustors The maximum discrete peak has

experi-a mexperi-agnitude of 0.00173 MPexperi-a experi-at experi-a frequency of 252 Hz, experi-and occurs during steexperi-am injection

Maximum overall root-mean-square (rms) noise level of 0.00836 MPa also occurs at the

same time Without steam injection the dynamic pressure measures about 20 percent less.Combustor exit temperature distribution factor, defined by the ratio of maximum variationfrom the mean to the overall combustor temperature, is 0.138 Preburner exit temperaturenonuniformity contributes substantially to this variation The tests indicate improvement inthe structural integrity of reactor, with the diameter experiencing minimal distortion afterseveral hours of operation

Combustion of the air and fuel mixture is accompanied by noise directly as a quence of the process and indirectly due to the flow of burned gases through the turbineand exhaust nozzle Combustion noise can become detrimental when instabilities aris-ing in the burning process couple with acoustic modes inside the chamber The naturalfrequencies of the combustor can be excited by resonant pressure waves in the main gasflow along the axial and radial directions, as also by lateral modes in the tangentialdirection (Paxson et al., 1995; Ohtsuka et al., 1998) Sustained oscillating phenomenadue to a higher level of mixing of the fuel and air prior to combustion lead to enginenoise and vibration problems

conse-Premixed combustion in gas turbines helps produce low levels of NOxemissions, butpractical application of this concept is limited by self-excited combustion oscillations.When operation in a lean, premix combustor is close to the flammability limit, slightchanges in operating conditions can lead to sudden flame extinction or to excessive COemissions In addition to static stability, lean premix combustors must achieve dynamic sta-bility, meaning the combustion must not oscillate Oscillation must be eliminated in a com-bustor design because the associated pressure oscillations tend to have life shorteningconsequences (Richards and Janus, 1997) Figure 9.32 shows cracks experienced in a tran-sition piece due to excessive acoustic oscillations Operation near the lean limit is especiallyprone to oscillation problems, where minor variations in fuel-air ratio lead to appreciablevariations in combustion reaction rate When these variations in the reaction rate couple withthe acoustic modes, significant pressure oscillations occur, with frequencies ranging fromhundreds to a few thousand Hertz

The task of studying and eliminating combustion oscillations in a gas turbine is plicated by the specific acoustic response of a combustor’s design The combustion processinteracts with the acoustic field, leading to instabilities Rapid changes in air and fuel sup-ply and aerodynamic disturbances may lead to the instability because of a sequence ofextinction and reignition of the flame in parts of the combustor If the heat release rate doesnot take place uniformly and periodic spikes occur, acoustic waves of the same frequencymay be expected in the combustion zone Reflection from the liner causes pressure waves

com-to be returned com-to the combustion zone after a time delay, and the waves are reinforced whenthe heat release and pressure wave peaks coincide As defined by Lord Rayleigh’s criterion,oscillations set in when changes in heat release are in phase with acoustic pressure distur-bances Conversely, oscillations are dampened when heat-release fluctuations are out ofphase with pressure fluctuations This criterion serves as the cornerstone for the develop-ment of combustion oscillation analysis Variation in heat release results from changes inflame structure produced by acoustic pressure disturbances Time delay between pressuredisturbance and heat-release variation determines the phase and, consequently, the stabil-ity of the system.

Based on these observations, lean premix combustors can be characterized by a simpletime-lag approach Figure 9.33 shows for a specific case a schematic diagram of the impor-tant processes, where a sinusoidal pressure disturbance produces a sinusoidal variation inairflow 180° out of phase with the pressure

FIGURE 9.32 Acoustic oscillations damaged transition piece (Lieuwen and

McManus, 2002).

Time lag τ is estimated from the distance between the point of fuel injection and theflame front divided by average axial velocity, or

where L is the distance from fuel injection point to nozzle tip, L′ is the distance of nozzle

tip to flame front, and Uavgis the average velocity of the air-fuel mixture in the nozzle

A positive pressure fluctuation in the combustor produces a momentary decrease in flow If the fuel supply is choked, rate of fuel flow will not change with pressure variation.Thus, the reduced airflow will receive a proportionally higher amount of fuel, creating afuel-rich pocket This richer pocket arrives at the flame front with a time lag, indicated bythe equation given above If the additional fuel produces an immediate increase in heatrelease, oscillations will be most likely when the pressure fluctuation peak is in phase with

air-the increased heat release, that is, when air-the time lag (t2− t1) is an integer multiple ofacoustic period This criterion for oscillations may be stated as (time lag)/(acoustic period) =

1, 2, 3, Since acoustic period is the reciprocal of frequency f, (time lag) × (frequency) =

1, 2, 3, or f(L + L′)/Uavg= 1, 2, 3, This is a restatement of Rayleigh’s criterion In tice, heat release and pressure do not necessarily need to be exactly in phase to drive oscil-lations Heat release fluctuations leading or lagging pressure by as much as 1/4 of theacoustic cycle will also cause some oscillations, although driving is greatest for integer val-ues where pressure and heat release are exactly in phase

prac-The discussion above is specific to the example where positive pressure produces animmediate decrease in airflow, and assumes that the fuel-rich pocket produces an immediateincrease in reaction rate when arriving at the flame front Other mechanisms for variable heatrelease can complicate the criterion for oscillations such that the expression may have valuesother than 1, 2, 3, Similar criteria can be developed to account for fuel system impedance,

or to describe oscillations linked to the tangential velocity component in the fuel nozzle swirlvane The geometry of the flame front has also been shown to produce a numeric series.Radiated sound may have frequencies ranging from 100 to 2000 Hz Sound pressure fre-quencies mostly do not depend on engine power or flame temperature, but radiated noiselevel tends to vary with these factors In the presence of combustion instability, a rumbling

or growling form of noise is audible in the low frequency (50 to 180 Hz) range when theengine may be in the subidle operating condition The growl is objectionable because itincreases the time to start an engine while also reducing the stall margin in the compressor

At higher frequencies corresponding to takeoff condition (200 to 500 Hz) the generatednoise takes a more distinct howling or humming pattern Unstable operation in the com-pressor tends to play a role, and may even act to trigger the noise Increase in air tempera-ture to combustor inlet has been noted to decrease the rate of occurrence and intensity ofgrowling noise, while raising combustor pressure has the opposite effect Fluctuations infuel pressure may also induce high-frequency noise

Thermoacoustic response of a gas turbine engine combustor for two different fuel tors has been investigated in a study conducted by the U.S Air Force (Arana et al., 2000),with the intention of identifying design features that cause an increase in the acoustic pres-sure A hybrid air blast injector presently in use with inner and outer flow passages isselected as a baseline design To lower the smoke production level, the investigationfocused on using higher swirl flow in the proximity of the spray point, while lean blowoutand dynamic stability can be obtained with lower swirl in the zone Simultaneously achiev-ing the apparently conflicting requirements for high and low swirls near the spray point led

injec-to the development of a new design concept with variances Figure 9.34 provides details ofthe baseline and new fuel injector designs

The new injector design differs from the baseline in the configuration of the venturi,the counterrotating swirlers of the venturi and the middle passage, and the ratio of vaneand discharge areas The last parameter is 50 percent larger than in the baseline design,

suggesting that the new swirler exhibits less resistance to dynamic changes in pressure athigher frequencies Use of velocity on the downstream side may be expected to maintain ahigher level of the transfer function.

Corotating and counterrotating swirlers are characterized for different passages Theinjectors are initially tested at atmospheric and high-pressure conditions in an ignition rig,

FIGURE 9.34 Baseline- (left) and new-fuel (right) injector designs (Arana, Sekar, Mawid, Graves, 2000).

Inner-passage

swirler

Inner passage

Middle passage Outer

passage

Ventury Fuel nozzle

Bearing plate

Air

Shear layer Spray

and then assembled in the combustor of a development engine demonstrator employing 24injectors around the circumference of the bulkhead Air is fed to the combustor through astepped diffuser.

The radial swirlers are the primary conduits of air between the external combustorshrouds and the internal combustion chamber If coupling and amplification between thechambers is the root cause of the instability, then swirler response to a forcing functionneeds to be checked by measuring the impedance of the conduit Impedance defines thetotal resistance and reactance opposition exerted by the swirlers to the forced, or pulsed,airflow of a given frequency, and is determined by measuring the transfer function of theswirlers Pressure is measured as the upstream parameter and velocity on the downstreamside for a number of frequencies

Figure 9.35 shows the measured transfer functions and corresponding phase angles forthe two designs The new design swirlers exhibit a higher value of the transfer function inthe frequency range of 400 to 500 Hz, where the natural frequency of the annular combus-tor occurs The phase angle relation between the pressure and velocity oscillations alsopoints to this aspect, and is indicative of a dynamic response as opposed to a static one Theimplication is that if the frequency of the acoustic chamber of less than 400 Hz is obtained,the new fuel injector design provides better attenuation and less acoustic response

is optimized

A similar situation has been experienced on a Siemens model V84.3 gas turbineequipped with a new ring (or annular) combustor design (Seume et al., 1997) Dynamicpressure and heat release rate are measured at different locations in the combustor, anddominant signals are recognized at 217 and 433 Hz due to oscillations in the combustor.Several cross power density spectra and transfer functions are derived from two dynamicpressure signals in different areas of the combustor Modal analysis indicated the oscilla-tions excite standing sound waves in the structure The standing waves consist of alternat-ing regions of high and low sound pressure amplitudes, related to each other by acharacteristic difference in phase Azimuthal modes in the form of waves are distributed

along the circumferential coordinate With a mean diameter of d= 2.5 m and speed of sound

c = 844 m/s at a mean temperature of 1500°C, the frequency of vibration f n = nc/pd yields

215 and 430 Hz for the second and fourth harmonics, indicating good agreement with themeasurements Significant amplitudes are not observed for the first and third harmonics of

108 and 326 Hz Figure 9.36 provides details of the second and fourth modes

Passive methods rely on making changes in operating parameters (such as equivalenceratio) or geometry of the combustion system to hinder the self-exciting mechanism The soundpressure amplitude can also be decreased to a tolerable level by dissipative baffles or mufflers(Culick, 1988) By contrast, active methods use a feedback control loop Heat release or pres-sure in the combustor is processed by a controller and is used as an input signal for an actua-tor to influence the oscillating combustion that counteracts the self-excitation process (Candel,1992; McManus, Poinsot, and Candel, 1993) Fluid stream inside the combustion chambercan be modulated to reduce pressure fluctuations by introducing inversed sound pressure

oscillations, as in a loud speaker The method is impractical for bigger turbines because oflarge amounts of air and exhaust gas to be handled Combustion oscillations can be sup-pressed if the rate of fuel reaching the flame is anticyclical to the oscillations of the heatrelease rate In either case, modulation of gases or fuel must take place at the frequency ofthe self-excited vibrations Since these can often reach 1000 Hz, suitable actuators must beused to meet the requirement.

The active stability control system for the V84.3 gas turbine uses pressure transducermeasurements in the chamber, and the signals are sent to a control unit to derive an inputsignal for the actuator to modulate the fuel flow rate A few basic problems are needed to

be solved for operation on a ring combustor In the premixed mode and at base load theengine uses 9 kg/s of gas Thus, the actuator has to handle this mass flow rate at theobserved frequencies Active control is secured through additional diffusion flames thatcontribute about 10 percent of the total power of the burner to stabilize the main premixedflame Fuel flow rate to the pilot flame is modulated to influence the heat release in the mainflame accordingly A special high-speed direct-drive valve serves to actuate the pilot gasflow The success of the control mechanism heavily depends on the pressure amplitudes in

FIGURE 9.36 Excited modes in combustion chamber (Seume et al., 1997).

the pilot gas pipes, with higher amplitudes increasing the heat release in the flame Hence,the length of the pipe to the pilot must be acoustically tuned to the frequency to be con-trolled When the pilot’s gas piping layout is complex and introduces damping, a suitabledevice may be placed upstream of the actuator to acoustically decouple it Figure 9.37shows a schematic of the control mechanism.

The second problem is associated with the azimuthal modes of the instabilities Sinceseveral control systems are placed in different locations along the circumference, the con-trol devices are also situated in different regions of the excited acoustic field, with prevail-ing oscillating parameters strongly differing in amplitude and phase The symmetry of theazimuthal modes is marked by a characteristic distribution of nodes and antinodes, withregions of high and low amplitudes related to each other by a constant phase shift.Consequently, it is possible to use a signal measured at a certain circumferential location

on the ring combustor to calculate not only the actuator signal for the particular location butalso for other defined locations One control unit can then be used for all the actuators inthe system Figure 9.38 depicts this principle for the second harmonic to provide the inputsignal for four actuators located 90° to each other

Performance of the active control system can be gauged from shop test measurements ofthe 170 MW gas turbine’s ring combustor (Fig 9.39) The mechanism reduced the oscilla-tions at the dominant frequency of 433 Hz by up to 17 dB With active control turned off, mea-sured sound pressure amplitudes rose to 210 mbar (corresponding to sound pressure level of

177 dB), falling to about 30 mbar with the control system turned on

Modulation of the fuel flow rate is commonly achieved by using reciprocating flowdevices where instability occurrence is at about 200 Hz or when the level of modulationrequired is small In instances where instability frequencies are in the 200 to 500 Hz rangeand attenuation requires modulation of large fractions of engine fuel flow rate of hundreds

of pounds per hour, a spinning drum valve has proved more useful (Barooah, Anderson,and Cohen, 2002) The spinning valve design is based on a rotary concept to generatemaximum frequency response A rotating drum with a selected number of holes equallyspaced around the circumference is used, with the holes aligned in the surrounding enclo-sure to pass the liquid fuel flow By minimizing the clearance between the drum and theenclosure, leakage is reduced when the holes in the rotating and stationary componentscome in line The holes in the enclosure are radially opposed to balance the pressure and to

Compressor

Flame

Turbine

Ring combustionchamberPiezo pressure

transducer

minimize the traverse loads Unlike a reciprocating device, the upper frequency limit is notaffected by the inertia of the spool or the low power requirement to accelerate it.

Liquid-fueled low NOxcombustors can mitigate combustion instability at realistic ating conditions by modifying the fuel nozzle (Cohen et al., 1998) The fuel is injectedthrough axial tubes with spray tips protruding from the nozzle centerpiece A pilot injector

oper-is placed a short doper-istance downstream of the fuel ejection plane After passing through a

FIGURE 9.38 Sensor and signal input controller for second harmonic mode (Seume et al., 1997).

venturi, the airflow is split between the fuel nozzle and a bypass segment Airflow from thebypass is injected at the downstream end combustor, and represents dilution air To obtaincontrol of the acoustic oscillations, one tube delivers the fuel to a metering system and asolenoid valve The tubing between the valve and the injection point is minimized to reduceattenuation and time lag due to capacitive effects The main fuel flow takes place throughthe other injection tubes The solenoid valve is driven at varying frequencies independent

of the combustor behavior using a signal generator, with an on/off duty cycle of 50 percent.Combustor pressure and heat release rate are measured When the control sensor signalcrosses a predetermined threshold level, a command sent to the solenoid valve turns it on

or off Time delay between the instant of crossing and valve command is also taken intoaccount The threshold level and the time delay are manipulated through a user interface tothe control algorithm A proper choice of the two parameters yields 15 dB attenuation ofthe objectionable oscillating mode The control system is also effective in holding the NOxemission relatively constant across the range of equivalence ratios

OF COMBUSTOR LINER

The functional nature of a combustion liner imposes on it high temperature levels and steepthermal gradients The mechanical strength of nickel- and cobalt-based alloys used for theliner deteriorates considerably when temperatures exceed 1100 K, and hence means must

be designed to relieve the heat buildup With gas turbines employing higher operating sures and temperatures to improve performance and power, the need for cooling the com-bustion liner becomes even more acute At the same time the liner is required to possess aminimum number of operating hours (Lefebvre, 1999)

pres-The temperature of the liner increases due to the combination of heating by radiationand convection from the internal hot gas flow and cooling due to radiation to the outercase and convection to the air in the annulus Depending on the volume, pressure, temper-ature, and chemical composition of the gases flowing through it, as also the dimensions andshape of the component, a considerable amount of heat is radiated on the liner The size andnumber of hot and glowing soot particles formed during the combustion also control theintensity of radiation The geometric shape factor between the liner and the casing and sur-face areas of the liner and outer case will govern the heat radiated by the liner to the cas-ing Internal heat convected to the liner walls from the gases is complicated by the rapidlychanging physical and chemical characteristics, as also the temperature, of the gases Steepgradients in flow velocities and pressures add even more uncertainties, because the state ofboundary layer development makes it difficult to prepare an adequate model In a can com-bustor, reversal of flow designed in the primary zone permits only a portion of the flow to

be modeled using the pipe analogy Using a Reynolds number based index consistent withobserved parameters for extreme turbulence, an expression using the hydraulic diameter(proportional to the ratio of cross-sectional flow area and wetted perimeter) may be used

When a swirler is used, local gas velocity at the wall increases by the factor 1/(cos b ) ative to the downstream velocity, where b is the angle between the velocity vector and axis

rel-of the combustor The bulk gas temperature used for internal convection in the primaryzone may also need to be modified by reducing the corresponding radiation temperature byabout 15 percent External convection from the cylindrical surface requires the Reynoldsnumber to be calculated using the hydraulic mean diameter of the annular air space.Film cooling of the inner surface of the liner is useful in achieving additional extraction

of heat, and is accomplished by injecting air along the wall axially through slots and holesmachined in the liner The small diameter, closely spaced holes may be provided by laser

drilling or by the electrical discharge machining (EDM) method Since the turbulent hot

gases gradually eliminate this film, the hole and slot pattern is repeated at specific intervalsalong the length Cooling air is supplied through rings rolled or machined in the liner, throughstacked rings with holes sized to deliver adequate amounts of cooling air and through corru-gated spacers attached between overlapping segments of the liner Depending on the designand method of attachment, the rings also serve to provide stiffness to the liner Cooling effi-ciency in the liner is enhanced by improving the heat transfer coefficient on the coolant side(Nealy, 1980) and by increasing surface roughness of the heat transferring areas

Cooling effectiveness can be increased by impinging the coolant flow against the wall,

as shown in Fig 9.40 The double-walled passage is closed at the upstream end, and theouter wall is provided with holes The impingement jets may be located at selected high-temperature locations Provision must be made for the difference in thermal growth, how-ever, and the consequent increased thermal stresses in the region Convective heat transfer

on the external surface of the liner can be improved by providing fins, ribs, or other trusions to add to the surface area for heat exchange by convection The ribs may run lon-gitudinally, and have been used on industrial turbine combustors Rolls Royce has elected

pro-to use pedestals in the dome region of RB211 combuspro-tor liners

Another method for obtaining a relatively uniform temperature distribution is a linerwith a large number of small holes perforated in it to assure the impinging jets spread theflow close to the wall The flow must be controlled to prevent rapid mixing with main hotgas flow and to deter the cooling film from gradually rising in temperature by the sur-rounding combustion gases The process, called effusion cooling, uses a larger amount ofcooling air, but is effective in suppressing local hot spots Drilling the holes (approxi-mately 0.4 mm in diameter) at a shallow angle of 20° offers the twin benefits of increasedsurface area and reduced penetration of the exiting jet for a better film along the wall sur-face (Dodds and Ekstedt, 1989) Wall thickness needs to be increased to compensate forthe holes and for protection against buckling The angled effusion cooling hole concept isused on the General Electric GE90 engine combustor The manufacturing cost of drilling

so many holes at precise locations is a factor to be taken into account in the use of thistechnique

Many industrial turbine combustors are lined with refractory bricks to decrease heatflux into the supporting liner The bricks are large in weight, but lighter metal tiles cast fromturbine blade alloys with good resistance to high temperatures have been used on aero-engines Since the tiles are exposed to the hot gases, relatively lower temperatures and ther-mal stresses are experienced by the supporting shell, which may be made of a cheaper alloy

FIGURE 9.40 Film cooling of liner with impingement jets

The cooler temperatures help to limit thermal growth in the shell The tiles are equippedwith pedestals on the rear surface, and cooling air flows around the pedestals to eject at theends to form a layer of cooler air The cost of repairs is reduced since only the tile experi-encing distress needs to be replaced instead of repairing the liner.

Sheets of cobalt- or nickel-based alloys are commonly used to produce combustor ers exposed to severe temperatures and pressures Resistance to oxidation and corrosion is

lin-a primlin-ary considerlin-ation in the selection of mlin-aterilin-al lin-and mlin-anuflin-acturing process, but lowcoefficient of expansion and Young’s modulus, resistance to thermal fatigue, and high ther-mal conductivity also play a major role Steep thermal gradients are encountered around theedges of cooling holes and in isolated hot spots The pace of oxidation is noted to appre-

ciably increase when metal temperature approaches 1300 K A thin layer of a thermal

bar-rier coating (TBC) may be applied on the inner surface of the liner for extra protection The

refractory material of low thermal conductivity has the capacity to reflect much of the ated heat from combustion while offering increased resistance to heat flow to reduce thetemperature of the metallic liner To adequately provide the protection, the thermal barriercoat must be chemically inert, be resilient to thermal shocks, and have good erosion andwear characteristics Also, its coefficient of thermal expansion must match that of theunderlying substrate A base metallic coat of Ni-Cr-Al-Y is overlaid with one or two coats

radi-of ceramics to constitute many TBCs Plasma flame spraying is found effective in ing durability, consistency, and thickness uniformity of the coats

A trade-off between adequate flexibility to minimize thermal stress and stiffness toavoid vibration problems is thus required Once a specific temperature distribution is avail-able, thermal stresses may be computed with relative ease Vibratory stresses, however,cannot be so readily defined Complexities in geometry, loading pattern, and contact behav-ior are some reasons Strain measurements may also be of limited usefulness because crit-ical locations are not generally known, often are inaccessible, and have high levels of metaltemperature

Field experience gained from years of operation may permit setting limits on tion dynamic pressure fluctuations to ensure structural integrity Direct application of thisexperience to new applications, however, is questionable Analytical prediction of compo-nent life and development of a method to include effects of dynamic pressure loading maythus be essential Nonlinear transient finite element analytical procedures are useful in pre-dicting the dynamic behavior, and can compare measured strains and accelerations withreasonable accuracy (Barnes, 1996) Component stiffness and mass characteristics, as alsodistributed pressure loading, can then be accurately modeled Contact behavior, includingsliding friction at supports and seals, is required to compute response, since it adds consid-erably to the damping coefficient Nonlinear gap conditions capable of maintaining orbreaking physical contact in accordance with relative displacements between componentsare also essential Verification of natural frequencies and mode shapes computed frommodal analysis may be made through laboratory modal testing, and to determine proximity

combus-to resonant conditions

Figure 9.41 shows the finite element model Mesh density requires special attention bepaid to supports, fillets, and areas of known stress concentration This level of detail cap-tures stress concentration in a forced response analysis, but may not be required for a modalanalysis Linear eight-noded brick elements help to maintain the number of elements withinlimits in a large model, especially in a computationally intensive solution Effects of non-symmetric loading and support features generally do not permit taking advantage of geo-metric symmetry Seals on forward and aft ends of the liner may be modeled as acombination of a normal spring and a tangential friction element Seal stiffness may becomputed independently from its own finite element model, while friction coefficient must

FIGURE 9.41 Combustion liner and transition piece finite element model (Barnes, 1996).

Combustion liner

Transition piece

Aft mountand bracket