Two-branch mixing passage and method to control combustor pulsations
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/34
F23R-003/28
F23M-020/00
출원번호
US-0274647
(2014-05-09)
등록번호
US-9534789
(2017-01-03)
발명자
/ 주소
Scarinci, Thomas
출원인 / 주소
INDUSTRIAL TURBINE COMPANY (UK) LIMITED
대리인 / 주소
Beusse Wolter Sanks & Maire
인용정보
피인용 횟수 :
0인용 특허 :
15
초록▼
A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is
A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct.
대표청구항▼
1. A method comprising: increasing the pressure of a working fluid within a compressor of a gas turbine engine;communicating the working fluid from the compressor toward a combustion chamber via an annular passage that surrounds the combustion chamber;introducing a fuel into the working fluid after
1. A method comprising: increasing the pressure of a working fluid within a compressor of a gas turbine engine;communicating the working fluid from the compressor toward a combustion chamber via an annular passage that surrounds the combustion chamber;introducing a fuel into the working fluid after said increasing to define a fuel and working fluid mixture;separating the fuel and working fluid mixture into at least two distinct and separate fuel and working fluid mixture streams; anddelivering one of the at least two distinct and separate fuel and working fluid mixture streams to a first location within the combustion chamber and an other of the at least two distinct and separate fuel and working fluid mixture streams to a second location within the combustion chamber via an annular shaped branch duct disposed radially inward of the annular passage and radially outward of the combustion chamber with respect to a centerline of the combustion chamber,wherein the time to deliver the fuel and working fluid mixture stream to the first location is different than the time to deliver the fuel and working fluid mixture stream to the second location, and wherein the difference in time to deliver the fuel and working fluid mixture streams to the combustion chamber is selected to maximize attenuation of combustor pulsations within the combustion chamber. 2. The method of claim 1, wherein the branch duct comprises a decreasing cross-sectional area that is effective to accelerate the other of the at least two distinct and separate fuel and working fluid mixture streams. 3. The method of claim 1, wherein in said delivering each of the fuel and working fluid mixture streams are introduced into the combustion chamber as a plurality of jets. 4. The method of claim 1, wherein in said introducing the fuel is discharged from a single fueling device. 5. The method of claim 1, wherein the branch duct comprises a decreasing cross-sectional area that is effective to accelerate the other of the at least two distinct and separate fuel and working fluid mixture streams; wherein in said delivering each of the fuel and working fluid mixture streams are introduced into the combustion chamber as a plurality of jets. 6. A gas turbine engine combustor, comprising: a combustion chamber;a mixing duct configured to convey a working fluid therein;an annular passage leading to the mixing duct and configured to convey the working fluid;a fuel delivery device in fluid communication with said mixing duct, said fuel delivery device introduces a fuel to the working fluid within said mixing duct to define a fuel and working fluid mixture;a first branch duct routing a first portion of the fuel and working fluid mixture from said mixing duct to a first location at said combustion chamber; anda second branch duct routing a second portion of the fuel and working fluid mixture from said mixing duct to a second location at said combustion chamber;wherein the first branch duct and the second branch duct each comprise an annular shape and both are located radially between and axially aligned with the annular passage and the combustion chamber with respect to a centerline of the combustion chamber;wherein the first and second branch ducts are configured such that the travel time of the first portion of the fuel and working fluid mixture to said first location is different from the travel time of the second portion of the fuel and working fluid mixture to said second location, and wherein the difference in travel time between the first portion of the fuel and working fluid mixture and the second portion of the fuel and working fluid mixture to the combustion chamber is selected to maximize attenuation of combustor pulsations within the combustion chamber. 7. The combustor of claim 6, wherein said mixing duct forms an annular fluid flow passage. 8. The combustor of claim 6, wherein each of said branch ducts comprises a decreasing cross-sectional area that is effective to accelerate their respective portion of the fuel and working fluid mixture flowing therethrough. 9. The combustor of claim 6, wherein each of said branch ducts includes an exit, and wherein said exit is divided into a plurality of spaced openings. 10. The combustor of claim 6, wherein said fuel delivery device is a fuel injecting device, and wherein all the fuel introduced into the working fluid within said mixing duct is from said fuel injecting device. 11. The combustor of claim 6, wherein said first branch duct has a first outlet and said second branch duct has a second outlet, and wherein one of the first or second outlets is downstream of the other of the first or second outlets. 12. The combustor of claim 6, wherein said mixing duct forms an annular fluid flow passage;wherein each of said branch ducts comprises a decreasing cross-sectional area that is effective to accelerate a respective portion of the fuel and working fluid mixture flowing therethrough;wherein each of said branch ducts includes an exit, and wherein each of said exits is divided into a plurality of circumferentially spaced openings; andwherein said first branch duct has a first outlet and said second branch duct has a second outlet, and wherein one of the first or second outlets is downstream of the other of the first or second outlets. 13. A gas turbine engine combustor for burning a fuel and air mixture, comprising: a combustion chamber;a first mixing duct;an annular passage leading to the first mixing duct;a first fuel delivery device in fluid communication with said first mixing duct, said first fuel delivery device introduces fuel to the air within said first mixing duct to define a first fuel and air mixture;a second mixing duct with working fluid therein, said second mixing duct forming an annular passage around at least a portion of said combustion chamber;a second fuel delivery device in fluid communication with said second mixing duct, said second fuel delivery device introduces fuel to the air within said second mixing duct to define a second fuel and air mixture;a first branch duct in flow communication with said second mixing duct, said first branch duct receiving and routing a portion of the second fuel and air mixture to a first location at said combustion chamber; anda second branch duct in flow communication with said second mixing duct, said second branch duct receiving and routing another portion of the second fuel and air mixture to a second location at said combustion chamber, said second location is spaced downstream from said first location;wherein the first branch duct and the second branch duct each comprise an annular shape and both are located radially between and axially aligned with the annular passage and the combustion chamber with respect to a centerline of the combustion chamber; andwherein the first and second branch ducts are configured such that the residence time of the portion of the second fuel and air mixture within said first branch duct is not equal to the residence time of the another portion of the second fuel and air mixture within said second branch duct, and wherein the difference in residence times within said first branch duct and said second branch duct is selected to maximize attenuation of combustor pulsations within the combustion chamber. 14. The combustor of claim 13, which further includes a plurality of swirler vanes in fluid flow communication with said first mixing duct; wherein said branch ducts each include an outlet, and wherein each branch duct comprises a decreasing cross-sectional area that that is effective to accelerate a respective portion of the fuel and air mixture flowing therethrough. 15. The combustor of claim 14, wherein one of said outlets is downstream from the other of said outlets; wherein each of said outlets is a circumferential outlet having a plurality of spaced discrete openings for the passage of the fuel and air mixture to said combustion chamber. 16. The combustor of claim 13, wherein the difference in residence time has been determined to attenuate combustor pulsations originating from a burning zone within the combustion chamber. 17. A combustor, comprising: a combustion chamber;an annular mixing duct;an annular passage leading to the annular mixing duct;a fuel injector disposed in flow communication with said annular mixing duct, said fuel injector delivering a fuel into air flowing within said mixing duct to define a fuel and air mixture; andat least two branch passages connected with said annular mixing duct, each of said at least two branch passages receiving a portion of the fuel and air mixture and delivering their respective portion of the fuel and air mixture to a distinct location within said combustion chamber separate from the other branch passages,wherein each of said at least two branch passages comprises an annular shape and both are located radially between and axially aligned with the annular passage and the combustion chamber with respect to a centerline of the combustion chamber; andwherein each of said at least two branch passages are configured such that the delivery of the fuel and air mixture through each of said at least two branch passages is phased to prevent the occurrence of fuel air ratio fluctuations, and wherein a difference in travel time between the respective portions of the fuel and air mixture within each of said at least two branch passages to the combustion chamber is selected to maximize attenuation of combustor pulsations within the combustion chamber. 18. The combustor of claim 17, wherein each of said at least two branch passages comprises a decreasing cross-sectional area that that is effective to accelerate a respective portion of the fuel and air mixture flowing therethrough; and which further includes a second mixing duct with a plurality of swirler vanes,wherein said plurality of swirler vanes impart swirl to a fuel and air mixture discharged into a primary combustion zone within the combustion chamber.
Takahara Takeshi (Yokohama JPX) Kobayashi Tadashi (Chigasaki JPX) Itoh Masao (Yokohama JPX), Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure.
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