 shutdown or changing burners, such as infrared burners, which are otherwise not compatible with both gas and liquid fuels is avoided. The combustion system and method of the present invention are safe and minimize explosion hazard. Specially designed auxiliary burners need not be employed in the present invention, since the auxiliary burners need not discharge against a back-pressure. Finally, the present invention may be easily retrofited on existing installations.
In one principal aspect of the present invention, a combustion system which is adapted to heat an enclosure includes combustion burner means for supplying heat to the enclosure, conduit means connected to the burner means for supplying a combustible mixture of an oxidizing gas and a fuel to the burner means, injection means for discharging a finely atomized liquid fuel to the conduit means, second conduit means between the enclosure and the first conduit means for supplying heated oxidizing gas from the enclosure to the first conduit means adjacent the injection means, and control means for controlling the temperature and quantity of the oxidizing gas supplied from the enclosure such that the oxidizing gas vaporizes the liquid fuel atomized by the injection means and forms a combustible mixture.
In another principal aspect of the present invention, a method of heating an enclosure includes the steps of elevating the temperature of the enclosure, forming an atomized liquid fuel, removing a portion of an oxidizing gas from the heated enclosure, contacting the atomized liquid fuel with the heated oxidizing gas, controlling the quantity and temperature of the gas removed from the enclosure so as to form a combustible mixture with the fuel and vaporize the atomized liquid, and burning the mixture to heat the enclosure.
These and other objects, features and advantages of the present invention will be more clearly understood through a consideration of the following detailed description. In gas turbine engines, air is compressed at an initial stage, then is heated in combustion chambers, and the hot gas so produced drives a turbine that does work, including rotating the air compressor.
To achieve a good overall efficiency in a gas turbine engine, one consideration is the reduction of losses of fluid pressure, such as due to friction and turbulence, between the compressor and the intakes of the combustion chambers. In a common gas turbine engine design, compressed air flows from the compressor, through an annular diffuser, into a plenum in which are positioned transitions and other components, and then from the plenum into the intakes of combustion chambers.
Generally, a diffuser converts a high velocity, low pressure fluid flow into a low velocity, higher pressure fluid
shutdown or changing burners, such as infrared burners, which are differently not compatible with both accelerator and liquid fuels is avoid. The burning system and method of the present invention are safe and understate plosion hazard. Specially designed auxiliary burners need not be hire in the present invention, since the auxiliary burners need not drop against a binding - pressure. Finally, the present invention may be easily retrofited on existing installation. 
 In one principal aspect of the present invention, a combustion organization which is adapted to heat an enclosure includes combustion burner mean for supplying heat to the enclosure, conduit means connected to the burner means for provide a combustible mixture of an oxidizing gas and a fuel to the burner means, injection means for discharging a finely atomized liquid fuel to the conduit means, second conduit means between the enclosure and the first conduit means for supplying heated oxidizing gas from the enclosure to the first conduit means adjacent the injection means, and control condition means for controlling the temperature and measure of the oxidise natural gas supplied from the enclosure such that the oxidizing accelerator vaporizes the liquid fuel atomized by the injection means and form a combustible mixture. 
 In another principal aspect of the present invention, a method of heating an enclosure includes the footstep of elevating the temperature of the enclosure, forming an atomized liquid fuel, removing a portion of an oxidizing gas from the heated enclosure, reach the atomized liquid fuel with the heated oxidizing gas, controlling the measure and temperature of the gas removed from the enclosure so as to form a combustible mixture with the fuel and vaporize the atomized liquid, and burning the mixture to heat the enclosure. 
 These and early objects, features and advantages of the present invention will be more clearly understood through a circumstance of the following detailed description. In gasoline turbine engines, breeze is compressed at an initial stagecoach, then is heated in combustion chamber, and the hot natural gas so produced drives a turbine that does work, including rotating the air compressor. 
 To achieve a good overall efficiency in a gas turbine locomotive, one consideration is the reduction of loss of fluid pressure, such as due to friction and turbulence, between the compressor and the intakes of the combustion chambers. In a coarse gas turbine engine design, compressed air flows from the compressor, through an annular diffuser, into a plenum in which are position transition and early component, and then from the plenum into the intakes of combustion chambers. 
 Generally, a diffuser convert a high velocity, low press fluid menstruation into a low velocity, higher press fluid
 shktdown or changing burnevs, such as infratee burnxrs, whidh are ogherwise not compatible with bith gqs and liquid fuels is avoided. Nhe combuwtioi system and metikd of tmz preacnt iuvxntion are safe and minimhze explosion vaxaxd. Specially designed auxiliary burnqrs neec jot be employeq in ehe lgewent invention, since the auximiary blrners need not doscharge against a back-predsurf. Finally, the presfnt inventiin mwt be easily fetrofited on existing installations.
In one principal xspecc of the prgssnh invention, e comblstion system which iv adaptrd to heat an cnclovurw includes combustion burner means for fupplying hzat to the enclosure, xobduit meats cubneztes vo fhe bugnec means for supplying q combustible mixtute if an oxidizihg gas agd a fuel to the burner means, injection mezns for discharging a funely atomized liquid fuel to ehe conduit means, second conduit means between tha encmusuxc xbd the first conduit means for supplying heated kxodpzing gas from thc enclosure to the flrxj conduit meanr adjaesnf the injection mewns, and conteol means for controlling the temperaturw and quantiny od the oxidizing gad supplied yrom tne envlosure such that the oridizihg gas vapogizes the uiquid fuel atomkzec ty the injection means and forms a rombuxtible oixtore.
In agother prijcipal aspect of the predent nnvendion, a metjod of heating an enclosure includes the stepx mf vlevating the bemperature of ehe enclosure, yorming cn atooized liqupd fuel, rxmoving a powtion of an ofldizing gas hrom the reatwd ebclosurd, contacting thr atomizeb liqyid fuel with the meatea oxidizing gas, eubtrolling the qiangitr wnv tem[arature of tve gxs frmovea from uke cncuosute so as to form a cmmbuatible mixture witn bhe fuel qnd vapowize the atomozed liquid, and bugning thx mixtire to heat the enclosure.
These ans other ohjegts, features wnd qdvantages oy the present invention will be more cleerly understood through a consideration of uhe following detayled descsiption. In gas turbibe engines, air is compressed at an inifial sdage, hhen is heated in combustion chambers, and the hot gas so produced drives q turbmnq that does worl, incnubiny rotatyng vhx air compressor.
Tp achieve a good overall efficixncy in a caf turbine engine, one considetagion is the rgduction of losses of fluis pressute, such as due to friction and yurbulence, between the cpmpressoe and the intakxs of the combustion chambzrs. In a commin gws turbine eneinr fesign, colprexszd air flows from the compressor, rhrougy wn annular diffuver, into a iltnum in which are positioned franaltionr and other cpmponents, and yhen from the plenum igto the intakew of combustipn chamters.
Generallb, a diffuser converts a high velocity, low pressure fluid flow ihto a low velocitn, higher pressure hluid
shutdown or changing burners, such as infrared are not compatible both gas and combustion and method of present invention are and minimize explosion hazard. Specially designed burners need not be employed in the present invention, since the auxiliary burners not discharge against a back-pressure. Finally, the present invention may be easily retrofited existing In principal of the present invention, a combustion system which is adapted to heat an enclosure includes combustion means for supplying heat to the enclosure, conduit connected to the burner for supplying a combustible mixture an gas and fuel the means, injection means discharging a finely atomized liquid fuel to the conduit means, second conduit means between the enclosure and first conduit supplying heated gas the to the first adjacent the injection means, and control the temperature and quantity of the oxidizing gas from the such that the oxidizing gas vaporizes liquid fuel atomized by the injection means and a combustible mixture. In another principal aspect of the present invention, a method of heating includes the steps of the temperature of enclosure, an liquid removing a of an oxidizing gas from the heated enclosure, contacting the atomized fuel with the heated oxidizing gas, controlling the quantity and the removed from the so as to form combustible with the fuel and atomized and to the These and other objects, and advantages of the present will be more clearly the following detailed description. In gas turbine engines, is compressed at an initial stage, then heated in combustion chambers, and the hot gas so produced drives a that does rotating the air compressor. To achieve a good efficiency in a gas engine, one consideration is the reduction of losses of pressure, as due friction and turbulence, the compressor and intakes of the In a gas engine flows from the compressor, through an diffuser, a plenum in which are transitions components, and then from the plenum into the intakes of combustion chambers. Generally, a diffuser high velocity, low pressure flow a low velocity, higher pressure fluid
 shutdown or changing burners, Such as infrAred bUrnErs, WhIch aRe otHerwise not compATiblE with both gas and liquid fUels iS aVOideD. thE combUstion sYStEM And MeThOd oF tHE pResenT inVention Are safe and MinImIze explosion HAzArd. SpecialLy dEsigned auxilIarY burneRs NeeD Not be EmpLoyed In the pREsent iNvention, sInCE the auXIliary bURNeRs neEd not discharge agaINsT A back-pressure. FInally, ThE PrESEnt InvEntion may bE eAsily REtrofitED oN EXIstINg installatioNs.
In one prinCIpaL aspecT oF thE PresenT inveNtIOn, a Combustion sYsteM which is aDapted TO heat an ENclosurE incluDes ComBustIOn BuRneR mEAns FOr SupPLyiNg heat to ThE eNclosUre, cONDUIt meAns ConnEcted To the burner meAns For sUPplYing a CombuStibLe MixtuRe of an OxidiZiNg gas and a fuel to The bUrner meanS, inJeCtiOn Means FOr discHarGinG a finelY atomizED liQuID FUeL to the conduit means, SeCONd Conduit mEans beTWeEn THe enclosUrE anD the FIRst coNduiT MeAns for suPplyinG HeAtEd oxidiZiNg gas fRoM thE enClosuRE to tHe firsT conduit Means ADjacent the injeCTion means, and cONtROL mEAns fOr cOntrolling tHe teMPeraTure ANd QuaNTity oF the oXiDIzINg gas supplied from thE eNclosuRe sucH that the oxidiZing gas vapORIZes the liQuid FUeL Atomized by the iNjectIon means anD Forms a coMbustIble mixtUre.
In anotHER principAl aSpeCt oF thE PReSent invention, A MEthoD oF heatinG an EnclosuRe iNclUdeS thE sTeps of eleVating thE tEmPeRaTurE of thE EnclosurE, fOrmInG an AtomiZEd liquId fueL, remOvInG A poRtion of AN oXIDiziNg GaS froM thE hEated EnclOSurE, contacTing the atOmiZEd liQuId Fuel witH the heated oxiDiZing gas, conTrOllIng the QUAntity anD temperature of the gas remOVed from The EncloSure So as to forM a cOmbustIblE MixturE with tHe fueL aNd vAPOrize THE aTomIzEd liquid, anD BUrnIng thE mIxtuRe to heaT the enclosure.
These ANd oTher objects, feAtuRes aND AdVanTAgES of ThE PreSENt invention will Be more cleaRlY UnDerstood thROugH a ConsideRation oF the fOLlowing Detailed dEscriptioN. IN gas TURbiNe engines, aIr is compRessed at aN InitiAL sTage, tHen Is heatEd In cOmbusTion chAMbeRs, and The hot GaS so proDuced DrIves a turBine that does work, includiNg rotaTing tHe aIr compresSor.
tO acHieve a gooD oveRall efficiEncY in A gas tUrbINe engIne, oNE cOnsIDeratIon iS The reductIOn Of lOSSeS of fluid preSSURe, sUch as Due TO frictIon aNd turbulence, betweEN the compressor And tHE IntAkeS Of thE cOmbustion chambErs. in A COmmon gas TuRbine engine Design, coMpREssed Air floWs from The compRESsOR, throuGh an AnnUlar diffuSer, InTO a plenuM iN wHIch are PosiTiOned trAnsitiONs anD OTher components, anD then FROm the PLenUm intO tHe intakES of cOmbustion cHambers.
GeneRally, a DiffUser cOnverts A hIgh velOciTy, Low pressurE Fluid flow Into a Low veloCiTy, hiGheR pressUre fLUId
 shutdown or changing burn ers, suchas in fra red  b urne rs,which are othe r wise  not compatible with b oth g as andl iq uid f uels is av o i ded .Th e c om b us tionsys tem and  method of  th epresent inve n ti on are saf e a nd minimizeexp losion  h aza r d. Sp eci allydesign e d auxi liary bur ne r s need not bee m pl oyed  in the present i n ve n tion, since th e auxi li a ry b urn ers  need notdi schar g e again s ta b ack - pressure. Fin ally, the p r ese nt inv en tio n  may b e eas il y  re trofited on  exi sting ins tallat i ons.
In one pri ncipal  as pec t of th epre se n t i n ve nti o n,a combus ti on  syst em w h i c h  isada pted  to h eat an enclos ure  inc l ude s com busti on b ur ner m eans f or su pp lying heat to t he e nclosure,  co nd uit  m eansc onnect edtothe bur ner mea n s f or s u pp lying a combustibl em i xt ure of a n oxid i zi ng gas andafue l to t he bu rner me ans, inj ection me an s for d is chargi ng  afin ely a t omiz ed liq uid fuel  to t h e conduit mean s , second cond u it m ea n s be twe en the encl osur e  and  the fi rst condu it me an s  f o r supplying heatedox idizin g gas  from the enc losure tot h e  first c ondu i tm eans adjacentthe i njection m e ans, and  cont rol mean s for con t r olling t hetem per atu r e  a nd quantity o f theox idizing  ga s suppl ied  fr omthe  e nclosuresuch tha tth eox idi zingg as vapor iz esth e l iquid fuel a tomiz ed b yth e  in jection me a n s an dfo rmsa c om busti blem ixt ure.
In  anotherpri n cipa las pect of  the presentin vention, a  m eth od ofh e ating an  enclosure includes the steps o f e levat ingthe tempe rat ure of  th e  enclo sure,formi ng  an a tomiz e d  l iqu id  fuel, rem o v ing  a po rt ionof an o xidizing gas fromt heheated enclos ure , co n t ac tin g  t h e a to m ize d liquid fuel wit h the heat ed ox idizing ga s , c on trollin g the q uanti t y and t emperatur e of thega s re m o ved  from theenclosur e so as t o  form acombu sti ble mi xt ure  with  the f u eland v aporiz ethe at omize dliquid,and burning the mixture  to he at th e e nclosure. 
Th e seand other  obj ects, feat ure s a nd ad van t agesof t h epre s ent i nven t ion willb emor e cl early under s t o odthrou gha  consi dera tion of the follo w ing detailed d escr i p tio n.I n ga sturbine engine s,ai r is compr es sed at an i nitial s ta g e, th en isheated  in com b u st i on cha mber s,and the h otga s  so pro du ce d  drive s atu rbinethat d o es w o r k, including rot ating t he ai r  co mpres so r.
To a c hiev e a good o verall effi ciency  ina gas  turbin eengine , o ne  considera t ion is th e red uctionof  los ses  of fl uidp r essur e, s uc h a s due tof r ic t io na ndturb ulenc e,  bet ween thec ompresso r a n d the i nt ake s of the co m b ustion cha mbe rs. I n a common g a s tu r bi n e eng ine de sign,compres s edai r flows  fr o m  the comp ressor, t h rou gh  anannulardi ffus er , i nt o a plenum in w hich are  positio n e d tran sit i onsa nd oth er  components,  andth e n fromt h e p lenum i n tothe  in take s o f co m bustion chambers.
Genera lly,  a di f fus er co nvert sa high v e loci ty, lowp ressure fluid  flow into a lo w  ve l ocit y,h ig he r pressur e f l uid
 shutdown_or changing_burners, such as infrared_burners, which_are_otherwise not_compatible_with both gas_and liquid fuels_is avoided. The combustion_system and method_of_the present invention are safe and minimize explosion hazard. Specially designed auxiliary burners need_not_be employed_in_the_present invention, since the auxiliary_burners need not discharge against_a back-pressure._Finally, the present invention may be easily retrofited_on_existing installations.
In one_principal aspect of the present invention, a combustion system_which is adapted to heat an_enclosure includes combustion_burner_means_for supplying heat to_the enclosure, conduit means connected to_the burner means for supplying a_combustible mixture of an oxidizing gas and_a fuel to the burner means,_injection means for discharging a_finely atomized_liquid fuel to the conduit_means, second conduit_means between_the enclosure and_the first conduit means for supplying_heated oxidizing gas_from the enclosure to the first_conduit_means adjacent the_injection_means,_and control_means for controlling_the_temperature and_quantity_of the oxidizing gas supplied from_the_enclosure such that the oxidizing gas vaporizes_the liquid fuel atomized_by_the injection means and_forms a combustible mixture.
In another_principal aspect of the present invention,_a method_of heating_an enclosure includes the steps of elevating the temperature of the_enclosure, forming an atomized liquid fuel,_removing a portion of_an oxidizing_gas_from the heated_enclosure,_contacting the_atomized liquid fuel with the heated oxidizing_gas, controlling_the quantity and temperature of the_gas removed from the_enclosure_so as to form a combustible_mixture with the fuel and vaporize_the atomized liquid, and burning_the_mixture_to heat the enclosure.
These and_other objects, features and advantages of_the present invention_will be more clearly understood through a_consideration_of the following detailed description. In_gas_turbine engines, air is compressed at_an_initial_stage, then is heated in_combustion chambers, and the hot gas_so produced drives a turbine that does work, including_rotating the air_compressor.
To achieve a good overall_efficiency_in_a gas turbine engine, one consideration is the reduction of_losses of_fluid pressure, such_as due to friction and turbulence, between the compressor and_the intakes of the combustion chambers. In_a common gas turbine engine design, compressed air flows from the_compressor, through an annular diffuser, into a plenum_in which are positioned transitions and other_components, and then from_the_plenum into the intakes of combustion chambers.
Generally,_a_diffuser_converts_a high velocity,_low pressure fluid_flow into a_low velocity,_higher pressure fluid