Air biasing system in a gas turbine combustor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/14
F23R-003/28
F23R-003/26
F23R-003/54
출원번호
US-0832099
(2010-07-08)
등록번호
US-10054313
(2018-08-21)
발명자
/ 주소
Portillo Bilbao, Juan Enrique
Martin, Scott M.
Ritland, David M.
출원인 / 주소
SIEMENS ENERGY, INC.
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A combustor (10) including: a first premix main burner (14) comprising a first swirler airfoil section (38); a second premix main burner (15) comprising a second swirler airfoil section (40); and a supply air reversing region upstream of the premix burners (14), (15). The first swirler airfoil secti
A combustor (10) including: a first premix main burner (14) comprising a first swirler airfoil section (38); a second premix main burner (15) comprising a second swirler airfoil section (40); and a supply air reversing region upstream of the premix burners (14), (15). The first swirler airfoil section (38) and the second swirler airfoil section (40) are effective to impart swirl to a first airflow and a second airflow characterized by a same swirl number as the airflows exit respective burners (14), (15). The combustor (10) is effective to generate a first airflow volume through the first premix main burner (14) that is different than a second airflow volume through the second premix main burner (15).
대표청구항▼
1. A combustor comprising: a first premix main burner comprising a first swirler airfoil section;a second premix main burner comprising a second swirler airfoil section; anda supply air reversing region upstream of the premix main burners,wherein the first premix main burner and the second premix ma
1. A combustor comprising: a first premix main burner comprising a first swirler airfoil section;a second premix main burner comprising a second swirler airfoil section; anda supply air reversing region upstream of the premix main burners,wherein the first premix main burner and the second premix main burner, collectively called premix main burners, constitute a part of an annular array of burners;wherein the first swirler airfoil section and the second swirler airfoil section comprise respective airfoil geometries effective to impart swirl to a respective first airflow and second airflow that is characterized by a same swirl number as the airflows exit respective of the premix main burners, andwherein the first premix main burner comprises a first diameter, and wherein the second premix main burner comprises a second diameter that is different than the first diameter and is effective to generate a first airflow mass flow rate of the first airflow through the first premix rosin burner that is different than a second airflow mass flow rate of the second airflow through the second premix main burner. 2. The combustor of claim 1, comprising an annular supply airflow conditioning plate disposed upstream of the premix main burners and transverse to a supply airflow, through which the supply airflow flows; which is effective to deliver a different amount of the supply airflow to the first swirler airfoil section than to the second scarier airfoil section. 3. The combustor of claim 2, wherein the supply airflow conditioning plate comprises circumferentially spaced perforations arranged in a pattern effective to deliver the different amount of the supply airflow to respective of the premix main burners. 4. The combustor of claim 3, wherein the supply airflow conditioning plate is disposed in the supply air reversing region. 5. The combustor of claim 1, wherein a geometry of the first swirler airfoil section differs from a geometry of the second swirler airfoil section and a difference results in the first airflow mass flow rate that is different than the second airflow mass flow rate. 6. The combustor of claim 5, wherein a thickness of the first swirler airfoil differs from a thickness of the second swirler airfoil. 7. The combustor of claim 5, wherein the first swirler airfoil section comprises airfoils of differing geometry. 8. The combustor of claim 7, wherein a thickness of at least one of the first swirler airfoil differs from a thickness of another one of the first swirler airfoil. 9. The combustor of claim 7, wherein a shape of at least one of the first swirler airfoil differs from a shape of another one of the first swirler airfoil. 10. The combustor of claim 1, wherein the first premix main burner and the second premix main burner are configured to provide the first airflow and the second airflow, respectively, with the same fuel/air ratio when supplied by a single common fuel stage. 11. A combustor for a gas turbine engine, comprising: a plurality of premix main burners arranged in an annular array, each premix main burner of the plurality of premix main burners each comprising a swirler, anda supply air reversing region upstream of the premix main burners,wherein each of the swirler is configured to produce swirled flow characterized by the same swirl number upon exiting respective of the plurality of premix main burners, andwherein the plurality of premix main burners comprises different burner diameters effective to result in a different percentage of total supply air volume flowing from one of the plurality of premix main burners than from another one of the plurality of premix main burners. 12. The combustor of claim 11, comprising an annular supply airflow conditioning plate, through which a supply airflow flows, disposed upstream of the premix main burners and transverse to the supply airflow flow, which is effective to deliver different percentage of total supply air volume to the one of the plurality of premix main burners than to another one of the plurality of premix main burners. 13. The combustor of claim 11, wherein different swirler geometry in the one of the plurality of premix main burners results in the different percentage of total supply air volume flowing from the one of the plurality of premix main burners than from another one of the plurality of premix main burners. 14. The combustor of claim 13, wherein a thickness of airfoils of at leas one of the swirler is different than a thickness of airfoils of another one of the swirler. 15. The combustor of claim 11, wherein each of the plurality of premix main burners comprises at least one fuel outlet effective to produce a same fuel/air ratio in each airflow when all fuel outlets are controlled by a single fuel stage. 16. The combustor of claim 15, comprising a separate fuel stage for the at least one fuel outlet. 17. The combustor of claim 11, comprising separate fuel stages. 18. An improvement for a gas turbine engine combustor comprising a plurality of premix main burners arranged in an annular array and an upstream airflow reversing region, the improvement comprising: a combustor effective to produce an airflow from each premix main burner of the plurality of premix main burners, wherein each of the airflow is characterized by a same swirl number upon exiting the premix main burner, and wherein the plurality of premix main burners comprises different burner diameters effective to produce at least one airflow mass flow rate through a given burner of the plurality of premix main burners that is different from another airflow mass flow rate through a different burner of the plurality of premix main burners. 19. The improvement of claim 18, wherein a thickness of airfoils of at least one swirler is different, resulting in the different airflow mass flow rate.
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이 특허에 인용된 특허 (11)
Bland, Robert J., Axially staged combustion system for a gas turbine engine.
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