公开(公告)号：JPH07150977A

公开(公告)日：1995-06-13

申请号：JP21266194

申请日：1994-09-06

Applicant: ABB MANAGEMENT AG

Inventor： RORUFU ARUTOHAUSU ,  YOUUPIN CHIYOU ,  HANSU URURITSUHI FURUUCHI ,  KURISUTEIAN GENEETO ,  PIITAA KANBAA ,  ANDERUSU RINDOBUARU ,  PEETAA RUFURI ,  TOOMASU ZATSUTERUMAIYAA ,  PEETAA ZENIOORU

IPC: F02C9/00 ,  F02C6/00 ,  F02C6/02 ,  F02C9/28 ,  F02C9/34

Abstract: PURPOSE: To perform a partial load operation by reducing a fuel quantity in a second combustion chamber to zero, maintaining the outlet temperature of a first turbine almost constant, and maintaining a fuel quantity in a first combustion chamber almost constant during the reduction of the fuel quantity in the second combustion chamber so as to maintain the inlet temperature of the first turbine almost constant. CONSTITUTION: A gas turbine compresses sucked air 2 in a compressor 1, and the compressed air 3 flows into a high-pressure combustion chamber 4. A high-pressure turbine 5 is operated downstream of the high-pressure combustion chamber 4, heated gas 6 is partially expanded and exhaust gas 7 is discharged. The exhaust gas ignites fuel in a low-pressure combustion chamber 8. At this time, a fuel quantity 9 in the low-pressure combustion chamber 8 is reduced to zero, and the outlet temperature of the high-pressure turbine 5 is maintained approximately constant. In addition, a fuel quantity 4a in the high-pressure combustion chamber 4 is maintained approximately constant during the reduction of the fuel quantity 9 in the low-pressure combustion chamber 8, and the inlet temperature of the high-pressure turbine 5 is maintained constant. Thus, the low-pressure combustion chamber 8 performs a partial load operation up to 40% of the high-pressure combustion chamber 4.

公开(公告)号：JPH0777316A

公开(公告)日：1995-03-20

申请号：JP18858194

申请日：1994-08-10

Applicant: ABB MANAGEMENT AG

Inventor： ADONAN EROGURU ,  FURANTSU YOOSU ,  PEETAA NOBUATSUETSUKU ,  PEETAA ZENIOORU

IPC: B05B1/00 ,  F23D11/10 ,  F23D14/22 ,  F23D14/78 ,  F23D17/00

Abstract: PURPOSE: To enhance combustion efficiency while reducing emission of harmful components by providing an appropriate nozzle and a cooling air supply unit surrounding a lance like an outer shell and cooling the lance and fuel with cooling air thereby preventing early firing. CONSTITUTION: A fuel lance for use in a combustion chamber defined by the casing of a gas turbine includes a liquid fuel pipe 7 surrounded by an elongated lance outer shell 11 and secured to the easing by a holding arm projecting sideways, a gas pipe 9 forming a gas passage around the liquid fuel pipe 7, and the lance outer shell 11 forming an air passage 10 around the gas pipe 9. An air/fuel nozzle 12 is provided on the side at the downstream end part of the fuel lance, a gas pipe 9 is provided with a gas nozzle 15 for ejecting gas from a gas passage 8 together with air, and the liquid fuel pipe 7 is provided with a liquid fuel nozzle 18 for ejecting liquid fuel through the air passage 10 and the air/fuel nozzle 12.