IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0274568
(2008-11-20)
|
등록번호 |
US-8087253
(2012-01-03)
|
발명자
/ 주소 |
- Ning, Wei
- Tesh, Stephen W.
- Siden, Gunnar L.
- Boyer, Bradley T.
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
6 |
초록
▼
A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentia
A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine; the injection ports comprising a port through which cooling air is injected into the hot-gas path of the turbine, the method comprising: configuring the stator blades in the first row of stator blades such that the circumferential position of a leading edge of one of the stator blades is located within +/−15% pitch of the first row of stator blades of the circumferential location of the injection port midpoint of at least a plurality of the injection ports.
대표청구항
▼
1. A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferen
1. A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine; the injection ports comprising a port through which cooling air is injected into a hot-gas path of the turbine, the method comprising: configuring the stator blades in the first row of stator blades such that the circumferential position of a leading edge of one of the stator blades is located within +/−15% pitch of the first row of stator blades of the circumferential location of the injection port midpoint of each of the injection ports;wherein the combustor comprises can combustors and the injection ports are positioned between neighboring transition piece aft frames that, during operation, direct combustion product from the can combustors into the turbine. 2. The method according to claim 1, wherein the stator blades in the first row of stator blades are configured such that the circumferential position of the leading edge of one of the stator blades is located at the circumferential location of the injection port midpoint of each of the injection ports. 3. The method according to claim 1, further comprising the step of configuring the stator blades of a second row of stator blades with the stator blades of the first row of stator blades such that at least 90% of the stator blades of the first row of stator blades and at least 90% of the stator blades of the second row of stator blades comprise a clocking relationship of between approximately −15% and 15% pitch. 4. The method according to claim 3, wherein the stator blades of the second row of stator blades are configured such that at least 90% of the stator blades of the first row of stator blades and at least 90% of the stator blades of the second row of stator blades comprise a clocking relationship of approximately 0% pitch. 5. The method according to claim 3, further comprising the step of configuring the stator blades of a third row of stator blades with the stator blades of the second row of stator blades such that at least 90% of the stator blades of the second row of stator blades and at least 90% of the stator blades of the third row of stator blades comprise a clocking relationship of between −15 and 15% pitch. 6. The method according to claim 1, wherein the injection ports expel cooling air that is used, at least in part, to cool the can combustors during operation. 7. The method according to claim 1, further comprising the step of configuring the stator blades in the first row of stator blades such that the circumferential position of the leading edge of one of the stator blades is located at the approximate circumferential location of an upstream side of each of the injection ports, wherein upstream is defined by the direction of rotation of a first row of rotor blades. 8. The method according to claim 1, wherein the number of stator blades comprises a whole number product of the number of injection ports, and wherein the whole number is greater than 1. 9. An assembly in a turbine engine, the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades; the assembly comprising: a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine, the injection ports comprising a port through which cooling air is injected into a hot-gas path of the turbine; andwherein the first row of stator blades configured such that the circumferential position of a leading edge of one of the stator blades is located within +/−15% pitch of the first row of stator blades of the circumferential location of an injection port midpoint of each of the injection ports;wherein the combustor comprises can combustors and the injection ports are positioned between neighboring transition piece aft frames that, during operation, are configured to direct combustion product from the can combustors into the turbine. 10. The assembly according to claim 9, wherein the stator blades in the first row of stator blades are configured such that the circumferential position of the leading edge of one of the stator blades is located at the approximate circumferential location of the injection port midpoint of each of the injection ports. 11. The assembly according to claim 9, further comprising a second row of stator blades; wherein the stator blades of the second row of stator blades are configured such that at least 90% of the stator blades of the first row of stator blades and at least 90% of the stator blades of the second row of stator blades comprise a clocking relationship of between approximately −15% and 15% pitch. 12. The assembly according to claim 11, wherein the stator blades of the second row of stator blades are configured such that at least 90% of the stator blades of the first row of stator blades and at least 90% of the stator blades of the second row of stator blades comprise a clocking relationship of approximately 0% pitch. 13. The assembly according to claim 11, further comprising a third row of stator blades; wherein the stator blades of a third row of stator blades are configured such that at least 90% of the stator blades of the second row of stator blades and at least 90% of the stator blades of the third row of stator blades comprise the clocking relationship of approximately 0% pitch. 14. The assembly according to claim 9, wherein the stator blades in the first row of stator blades are further configured such that the circumferential position of the leading edge of one of the stator blades is located at the approximate circumferential location of an upstream side of each of the injection ports, wherein upstream is defined by the direction of rotation of a first row of rotor blades. 15. The assembly according to claim 9, wherein the number of stator blades comprises a whole number product of the number of injection ports, and wherein the whole number is greater than 1.
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