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Publication Title | UnitedStatesPatent Willis et al. GAS TURBINE ENGINE HAVING A MULTI-STAGE MULTI-PLANE COMBUSTION SYSTEM

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Text | UnitedStatesPatent Willis et al. GAS TURBINE ENGINE HAVING A MULTI-STAGE MULTI-PLANE COMBUSTION SYSTEM | 001



(12)UnitedStatesPatent Willis et al.

(54) GAS TURBINE ENGINE HAVING A MULTI-STAGE MULTI-PLANE COMBUSTION SYSTEM

US006684642B2 (10)PatentN0.: US 6,684,642B2

. . . -

(75) Inventors. Je?l'reyW.Willis,Lexington,KY (US),

Guillermo Pont, LosAngeles, CA _ _ _

(US);BenJammE-T°bY>SW“ Madre> CA Robert D. McKeirnan, J12, Westlake Vlllage, CA (US)

(73) Assignee: CapstoneTurbineCorporation, Chatsworth, CA (Us)

(*) Notice: Subjecttoanydisclaimer,thetermofthis patent is extended or adjusted under 35

U-S-C- 154(k)) by 0 days-

(21) APPLNO;10/171684 ’

3,676,329 A

3,691,762 A

3,765,171A

3,797,231 A

3,846,979 A 3,866,413A

3875047 A , ,

3,893,297A 3,895,488A 3,914,090 A

7/1972 Dalsoneta1.

9/1972 Ryberg et91 10/1973 Hageneta1.

3/1974 McLean

11/1974 Pfefferle 2/1975 sturgess

4

/1975 Dalsonetal.

(22) (65)

(63)

(52) (58)

(56)

Filedi JlIl- 17, 2002

...

Pnor Pubhcatlon Data

US 2002/0148232 A1 Oct. 17, 2002 RelatedUS ApplicationData

ContinuationofapplicationNo.09/512,986,?ledonFeb. 24’2000'

Int. (:1-7 .. US.Cl...60/746;60/737 Field of Search .. 60/746, 734, 733,

60/749, 737, 804

ReferencesCited U.S. PATENT DOCUMENTS

1,698,963 A 1,826,776 A 17874970 A

1/1929 Oslundeta1. 10/1931 Gunther

8/1932 Hall

4/1952 Clad“eta1‘

2’593’849 A

2,829,494 A 4/1958 Christensen

2,946,185 A 2,982,099 A

3,658,691 A 3,676,328 A

7/1960 Bayer 5/1961 Carlisleetal.

4/1972 Keitheta1. 7/1972 Dalsoneta1.

,

(45) Date of Patent:

Feb. 3, 2004

7/1975 Tatem,Jr.etal.

7/1975 Koch 10/1975 Pfefferle

(L15t Continued on next Page) FOREIGN PATENT DOCUMENTS

EP

GB 2239056 6/1991

OTHER PUBLICATIONS

Gessaman et al., Industrial Trent Dry LoW Emissions Gas Fuel Control System,ASME, 2001—GT—0024, pp. 1—5 (Pre sentedattheInternationalGasTurbine& AeroengineCon gress & Exhibition, NeW Orleans, LA, Jun. 4—7, 2001). US. patent application Ser. No. 09/207,817, Gilbreth et al.,

?led DCC. 1998.

PrimaryExaminer—MichaelKocZo

(74) Attorney, Agent, or Firm—Sterne, Kessler, Goldstein & FOXPLLC

(57) ABSTRACT

A low emissions Combustion system a of

tangentialfuelinjectorstointroduceafuel/airmixtureatthe

combustor dome end of an annular combustion chamber in

tWo spaced injector planes. Each of the spaced injector

planesincludesmultipletangentialfuelinjectorsdelivering

premixedfuelandairintotheannularcombustor.A gener

allyskirt-shaped?oW controlbaffleextendsfromthetapered

inner liner into the annular combustion chamber doWn

streamofthefuelinjectorplanes.A pluralityofairdilution

holesinthetaperedinnerlinerunderneaththeHowcontrol

baffle introduce dilution air into the annular combustion

chamberWhileanotherpluralityofairdilutionholesinthe

. . . . . . . cylindrical outer liner introduces more dilution air doWn

f h ? 1b f? Stream mm t6 ‘WVComm a @

13Claims,5DrawingSheets

0445652A1 9/1991

Image | UnitedStatesPatent Willis et al. GAS TURBINE ENGINE HAVING A MULTI-STAGE MULTI-PLANE COMBUSTION SYSTEM



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