Method of controlling bypass air split to gas turbine combustor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-009/18
F02C-009/00
출원번호
UP-0163025
(2005-10-03)
등록번호
US-7549292
(2009-07-01)
발명자
/ 주소
Peck, Amanda Rose
Thatcher, Jonathan Carl
Venkataraman, Krishna
출원인 / 주소
General Electric Company
대리인 / 주소
Cantor Colburn LLP
인용정보
피인용 횟수 :
13인용 특허 :
4
초록▼
Disclosed herein is a method for controlling a bypass air split for a gas turbine combustor, the method comprising determining a target exhaust temperature, wherein the target exhaust temperature is based on at least one parameter of a group of parameters consisting of low pressure turbine speed, hi
Disclosed herein is a method for controlling a bypass air split for a gas turbine combustor, the method comprising determining a target exhaust temperature, wherein the target exhaust temperature is based on at least one parameter of a group of parameters consisting of low pressure turbine speed, high pressure turbine speed, inlet guide vane angle, and bypass valve air split. Using the target exhaust temperature to calculate a required percentage of bypass air split based on maintaining maximum CO levels or minimum NOx levels. And, applying the required percentage of bypass air split to control a position of the bypass air valve.
대표청구항▼
What is claimed is: 1. A method for controlling a bypass air split for a gas turbine combustor comprising: determining a target exhaust temperature, wherein the target exhaust temperature is based on at least one parameter of a group of parameters consisting of low pressure turbine speed, high pres
What is claimed is: 1. A method for controlling a bypass air split for a gas turbine combustor comprising: determining a target exhaust temperature, wherein the target exhaust temperature is based on at least one parameter of a group of parameters consisting of low pressure turbine speed, high pressure turbine speed, inlet guide vane angle, and bypass valve air split; using the target exhaust temperature to calculate a required percentage of bypass air split based on maintaining maximum CO levels or minimum NOx levels; and, applying the required percentage of bypass air split to control a position of the bypass air valve. 2. A method as in claim 1 wherein the target exhaust temperature is further based on at least one parameter of a group of parameters consisting of compressor pressure ratio, specific humidity, compressor inlet pressure loss, turbine exhaust back pressure, and compressor exit temperature. 3. A method as in claim 2 wherein the compressor pressure ratio provides a correction to the target exhaust temperature based on a plurality curves. 4. A method as in claim 1 wherein the determining a target exhaust temperature, using the target exhaust temperature to calculate a required percentage of bypass air split, and applying the required percentage of bypass air split to control a position of the bypass air valve are repeated periodically during operation of the gas turbine. 5. A method as in claim 1 wherein absent a CO limit violation, the preferred position of the bypass valve is at a minimum setting. 6. A method as in claim 1 wherein the CO levels are correlated to at least one group of parameters including compressor discharge temperature, combustor exit temperature, turbine inlet temperature, compressor discharge pressure, and minimum NOx boundary. 7. A method for determining a target exhaust temperature for a two-shaft gas turbine comprising: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of low pressure turbine speed, high pressure turbine speed, inlet guide vane angle, and bypass valve air split; and, adjusting the target exhaust temperature by applying the temperature adjustment; wherein the determining a target exhaust temperature, determining a temperature adjustment, and adjusting the target exhaust temperature are repeated periodically during the operation of the two-shaft gas turbine. 8. A method as in claim 7 wherein the target exhaust temperature is further based on at least one parameter of a group of parameters consisting of compressor pressure ratio, specific humidity, compressor inlet pressure loss, turbine exhaust back pressure, and compressor exit temperature. 9. A method as in claim 7 further comprising generate a plurality of the target exhaust temperatures, and selecting one of the plurality of target exhaust temperatures to be applied to control the two-shaft gas turbine.
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